Aeronautical Engineering a Continuing Bibliography with Indexes NASA SP-7037(211) March 1987 National Aeronautics and Space Ad M

Aeronautical NASA SP-7037(211) Engineering March 1987 A Continuing Bibliography with Indexes

National Aeronautics and Space Ad ministration NASA SP-7037(211)

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

(Supplement 211)

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in February 1987 in

Scientific and Technical Aerospace Reports (STAR) International Aerospace Abstracts (IAA).

Scientific and Technical Information Branch 1986 National Aeronautics and Space Administration Washington, DC This supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, price code A07. INTRODUCTION

This issue of Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 519 reports, journal articles and other documents originally announced in February 1987 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged by the first nine STAR specific categories and the remaining STAR major categories. This arrangement offers the user the most advantageous breakdown for individual objectives. The citations include the original accession numbers from the respective announcement journals.The lAA items will precede the STAR items within each category Seven indexes -- subject, personal author, corporate source, foreign technology, contract number, report number, and accession number -- are included. An annual cummulative index will be published.

Information on the availability of cited publications including addresses of organizations and NTlS price schedules is located at the back of this bibliography.

iii TABLE OF CONTENTS

Page Category 01 Aeronautics (General) 63

Category 02 Aerodynamics 66 Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 78 Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation 85 Includes digital and voice communication with aircraft; air navigation systems (satellite and ground based); and air traffic control.

Category 05 Aircraft Design, Testing and Performance 87 Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 101 Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 103 Includes prime propulsion systems and systems components, e.g., gas turbine engines and compressors; and onboard auxiliary power plants for aircraft.

Category 08 Aircraft Stability and Control 108 Includes aircraft handling qualities; piloting; flight controls; and autopilots.

Category 09 Research and Support Facilities (Air) 117 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.

Category 10 Astronautics 120 Includes astronautics (general); astrodynamics; ground support systems and facilities (space); launch vehicles and space vehicles; space transportation; space communications, spacecraft communications, command and tracking; spacecraft design, testing and performance; spacecraft instrumentation; and spacecraft propulsion and power.

Category 11 Chemistry and Materials 120 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing. Category 12 Engineering 123 Includes engineering (general); communications and radar; electronics and electrical engineering; fluid mechanics and heat transfer; instrumentation and photography; lasers and masers; mechanical engineering; quality assurance and reliability; and structural mechanics.

Category 13 Geosciences 132 Includes geosciences (general); earth resources and remote sensing; energy production and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography.

Category 14 Life Sciences N.A. Includes life sciences (general); aerospace medicine; behavioral sciences; man/ system technology and life support; and space biology.

Category 15 Mathematical and Computer Sciences 133 Includes mathematical and computer sciences (general); computer operations and hardware; computer programming and software; computer systems; cybernetics; numerical analysis; statistics and probability; systems analysis; and theoretical mathematics.

Category 16 Physics 137 Includes physics (general); acoustics; atomic and molecular physics; nuclear and high-energy physics; optics; plasma physics; solid-state physics; and thermodynamics and statistical physics.

Category 17 Social Sciences 139 Includes social sciences (general); administration and management; documentation and information science; economics and cost analysis; law, political science, and space policy; and urban technology and transportation.

Category 18 Space Sciences N.A. Includes space sciences (general); astronomy; astrophysics; lunar and planetary exploration; solar physics; and space radiation.

Category 19 General N.A.

Subject Index ...... A-1 Personal Author Index ...... B-1 Corporate Source Index ...... C-1 Foreign Technology index ...... D-1 Contract Number Index ...... E-1 Report Number Index ...... F-1 Accession Number Index ...... G-1

vi TYPICAL REPORT C lTATl0 N ANDABSTRACT

NASA SPONSORED IrON MICROFICHE ACCESSION NUMBER -N87-10039'# National Aeronautics and Space Administration. -CORPORATE SOURCE Langley Research Center, Hampton, Va. TITLE -WIND-TUNNEL INVESTIGATION OF THE FLIGHT CHARACTERISTICS OF A CANARD GENERAL-AVIATION DATE AIRPLANE CONFIGURATION AUTHOR -D. R. SATRAN Oct. 19866 /-AVAILABILITY SOURCE REPORT NUMBERS- (NASA-TP-2623; L-15929; NAS 1..60:2623) Avail: NTIS-HC PRICE CODE- A04/MF A01 CSCL OlA 4 COSATI CODE A 0.36-scale model of a canard general-aviation airplane with a single pusher propeller and winglets was tested in the Langley 30- by 60-Foot Wind Tunnel to determine the static and dynamic stability and control and free-flight behavior of the configuration. Model variables made testing of the model possible with the canard in hiqh and low positions, with increased winglet area, with outboard win9 leading-edge droop. with fuselage-mounted vertical fin and rudder, with enlarged rudders, with dual deflecting rudders, and with ailerons mounted closer to the wing tips. The basic model exhibited generally good longitudinaland lateral stability and control characteristics. The removal of an outboard leading-edge droop degraded roll damping and produced lightly damped roll (wing rock) oscillations. In general, the model exhibited very stable dihedral effect but weak directional stability. Rudder and aileron control power were sufficiently adequate for control of most flight conditions, but appeared to be relatively weak for maneuvering compared with those of more conventionally configured models. Author

TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT

NASA SPONSORED 1 ACCESSION NUMBER-A87-11487' National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. COMPUTATION OF TURBULENT SUPERSONIC FLOWS -TITLE AROUND POINTED BODIES HAVING CROSSFLOW SEPARATION AUTHORS-D. DEGANI and L. B. SCHIFF (NASA. Ames Research Center. -AUTHOR'S AFFILIATION Moffett Field, CA Journal of Computational Physics (ISSN 0021-9991), vol. 66! zpt. 1986. p. 173-196. refs The numerical method developed bv Schiff and Sturek (1.,980) on the basis of the thin-layer parabolized Navier-Stokes equations of Schiff and Steger (1980) is extended to the case of turbulent supersonic flows on pointed bodies at high angles of attack. The goilerning equations, the numerical scheme, and modifications to the algebraic eddy-viscosity turbulence model are described; and results for three cones and one ogive-cylinder body (obtained using grids of 50 nonuniformly spaced points in the radial direction between the body and the outer boundary) are presented graphically and compared with published experimental data. The grids employed are found to provide sufficient spatial resolution of the leeward-side vortices; when combined with the modified turbulence model, they are shown to permit accurate treatment of flows with large regions of crossflow separation. T.K.

vii AERONAUTICAL A Continuing Bibliography (Suppl. 21 1)

MARCH 1987

01 structure size and weight, self-aligning parts, tolerance, two-piece fasteners, adhesive bonding, repairabiilty and maintainability, and modular design. The use of robots is then discussed together AERONAUTICS (GENERAL) with other requirements, such as standardization, a simplified human assembly system, integrated computer aided manufacturing, closed box internal assembly, flexible fixturing, and inspection. The need for artificial intelligence technology arising with the development of new and more sophisticated robots and sensors A87-13062 is emphasized. V.L. IMPLEMENTATION OF A ROBOTIC ASSEMBLY CELL R. J. MOL2 and R. PETERSON (Fairchild Republic Co., Farmingdale, NY) IN: International SAMPE Symposium and Exhibition, 31st, Los Angeles, CA, April 7-10, 1986, Proceedings . Covina, CA, Society for the Advancement of Material and Process Engineering, 1986, p. 191-202. A87-13157 The hardware design and software architecture of an automated COST DRIVERS AND DESIGN METHODOLOGY FOR robotic assembly cell is described. The integrated cell consists of AUTOMATED AIRFRAME ASSEMBLY an MV4000 Cell Controller, a GCA XR6100 gantry robot, an B. R. NOTON (Battelle Memorial Institute, Columbus, OH) IN: automated GEMCOR Driv-matic, a custom-designed flexible International SAMPE Symposium and Exhibition, 31 st, Los Angeles, assembly station, several custom-designed and effectors, and CA, April 7-10, 1986, Proceedings . Covina, CA, Society for the various tooling fixtures. The use of MCL (Manufacturing Control Advancement of Material and Process Engineering, 1986, p. Language), developed for the Air Force, in programming the cell 1441-1455. refs off-line is also discussed. The cell is designed and programmed An evaluation is made of a design tool for the reduction of to assemble flat sheet metal parts, with or without flanges, into large aircraft discrete part acquisition and automated assembly subassemblies for modern aircraft. No human intervention is costs, in light of cost drivers related to system performance, design required during the assembly process except for recoverable configuration, structural materials and fabrication methods for both errors. Author primary and secondary airframe structures. Emphasis is given to the need for developing a series of ground rules for cost driver A87-13063 analysis and the subsequent structural performance/acquisition AUTOMATED FLEXIBLE ASSEMBLY OF AEROSPACE cost tradeoff studies. Because of the high cost associated with STRUCTURES the introduction of design changes in the course of a production 0. WEINGART (Rohr Industries, Inc., Riverside, CA) IN: run, the significance of decisions made during the conceptual International SAMPE Symposium and Exhibition, 31 st, Los Angeles, design phase is stressed. It is noted that while assembly operations CA, April 7-10, 1986, Proceedings . Covina, CA, Society for the for airframe subassemblies can represent 50 percent of an aircraft’s Advancement of Material and Process Engineering, 1986, p. acquisition costs, secondary structures can represent fully 30 203-214. percent of the cost of a subassembly. O.C. The objective of the US. Air Force’s Flexible Assembly Subsystem Program is the development and demonstration of the technologies required for the achievement of aerospace structures’ automated assembly. Initial development efforts will concentrate on the configuration of a programmable robotic cell that will function as an ’island of automation’ in an otherwise conventional aerospace A87-13630 assembly environment; the technologies thereby refined will THE DEVELOPMENT OF BALANCE TUBES FOR DOWrY subsequently be generalizable into a fully integrated automated ROTOL COMPOSITE BLADED PROPELLERS manufacturing facility. The automated cell encompasses parts R. D. TIMMS (Courtaulds Research, Coventry, England) IN: Fibre presenter, flexible assembly fixture, articulated arm robot, automatic reinforced composites 1986; Proceedings of the Second fastening machine, vision system, and microcomputer International Conference, Liverpool, England, April 8-10, 1986 . components. O.C. London, Mechanical Engineering Publications, Ltd., 1986, p. 199-202. A87-13105 The successive stages in the development of a one-piece CFRP AUTOMATED ASSEMBLY-TRENDS, CONCEPTS AND balance tube for use in a propeller blade assembly is described, REQUIREMENTS together with the modifications made in the mold tool. The balance T. F. W. HALL (Northrop Corp., Aircraft Div., Hawthorne, CA) IN: tubes, made of 40 percent GrafiVnylon, were tested to failure. International SAMPE Symposium and Exhibition, 31 st, Los Angeles, The last version of the single-pocket tubes showed test failing CA, April 7-10, 1986, Proceedings . Covina, CA, Society for the loads ranging from 18.6 to 23.5 kN. The multipocket component, Advancement of Material and Process Engineering, 1986, p. which has eight additional small pockets around the flange to 795-809. make it possible to balance the blade about its two cross-sectional An attempt is made to identify the requirements for automated axes, showed failing loads ranging from 23.6 to 26.5 kN. Three manufacturing of aircraft structures from advanced composite variants of the balance tube are now being made for different materials. First, attention is given to design considerations, including size propellers. IS.

63 01 AERONAUTICS (GENERAL)

A87-13635 samples, cables, and two-by-four whiffletrees. A hydraulic system ISRAEL ANNUAL CONFERENCE ON AVIATION AND consisting of a 3000-psi hand pump, 10,000-pound actuator, ASTRONAUTICS, 27l”, HAIFA, ISRAEL, FEBRUARY 27, 28, pressure gage and lines, and a Barksdale valve are described. 1985, COLLECTION OF PAPERS Load cell calibration and pressure indicator calibration procedures Conference organized by Israel Society of Aeronautics and are also described. A description of the strain and deflection Astronautics; Supported by the Technion - Israel Institute of measurement system is included. Preliminary data obtained to date Technology, Tel Aviv University, Ministry of Defence of Israel, et are compared to the analytical predictions. Author al. Haifa, Israel, Technion - Israel Institute of Technology, 1986, 247 p. For individual items see A87-13636 to A87-13660. A87- 14687 Papers are presented on such topics as the parametric sizing AUTOMATION OF SUPPORT PROCESSES FOR AIRCRAFT of agricultural aircraft based on varying levels of technology; an PRODUCTION USING COMPUTERS AND NUMERICAL analytical parametric investigation of numerical nonlinear CONTROL [AVTOMATIZATSIIA PROTSESSOV PODGOTOVKI vortex-lattice methods; equilibrium configurations of a cable drogue AVIATSIONNOGO PROIZVODSTVA NA BAZE EVM I system towed in helical motion; the combination of suction and OBORUDOVANIIA S CHPU] tangential blowing in boundary layer control for STOL aircraft; and V. A. VAISBURG, B. A. MEDVEDEV, A. N. BAKUMSKII, G. M. a split canard configuration for improved control at high angles of MIKHAELIAN, V. IA. ELCHIBEKOV et al. Moscow, Izdatel’stvo attack. Consideration is also given to: pursuit-evasion games with Mashinostroenie, 1985, 216 p. In Russian. refs finite detection ranges; the use of three-dimensional programs for Methods and means of the automated support of aircraft aircraft design and development; the improvement of an production using CAD and numerical control techniques are expendable turbojet engine flight envelope; and the direct solution examined with particular reference to the design and manufacture of flutter equations with an interactive graphics procedure. B.J. of unique large components and parts of complex three-dimensional geometry. Specific topics discussed include the design of a A87-13911 manufacturing process involving the use of numerically controlled AMES ACCELERATES RESEARCH ON HYPERSONIC machine tools; software support for numerically controlled machine TECHNOLOGY tools and automation of software development; and ways of J. T. MERRIFIELD Aviation Week and Space Technology (ISSN increasing the precision of machining. The discussion also covers 0005-2175), vOI. 125, Aug. 25, 1986, p. 85, 88, 92. methods of increasing the efficiency of the generation and The recent announcement of program goals for a National transmission of control information to numerically controlled Aerospace Plane has prompted an acceleration of hypersonic machine tools using computers and the organizational aspects of research at NASA’s Ames Research Center. NASA hopes to be programmed control. V.L. able to validate the technologies to be integrated in the aerospace plane’s design by 1995, on the basis of an experimental flight A87-15414 research program. Ames hypersonic research focuses on MULTI-ECHELON REPAIR LEVEL ANALYSIS - MERLA computational fluid dynamics, trajectory analysis, and thermal S. L. DEVRIES and S. A. WICKER (Northrop Corp., Aircraft Div., protection materials, as well as such life support systems as an Hawthorne, CA) IN: 1986 Annual Reliability and Maintainability advanced pressure suit; in addition, aircraft flight and thermal load Symposium, Las Vegas, NV, January 28-30, 1986, Proceedings . tests for structures, digital control of propulsion and other systems, New York. Institute of Electrical and Electronics Engineers, Inc., and flight test plans for hypersonic vehicles are being developed. 1986, p. 126-132. Such flight testing is rendered critical by the limitations of Existing Repair Level Analysis (RLA) models were contrasted component size associated with ground test facilities. O.C. to the ’Air Force 2000’ requirement and found inadequate in the areas of maintenance and basing scenario. A new RIA model, A87-14015# Multi-Echelon Repair Level Analysis (MERLA), was developed RESULTS OF RESEARCH ON MATERIALS AND which provides for up to four alternative levels of support with a CONSTRUCTION METHODS BY THE DFVLR [ERGEBNISSE DER more comprehensive representation of support cost. Author WERKSTOFF- UND BAUWEISENFORSCHUNG IN DER DFVLR] C.-J. WINTER BMFT, Statusseminar ueber Luftfahrtforschung A87-15418 und Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, MD-80 SERVICE MATURITY PROGRAM Paper. 32 p. In German. refs D. M. BLACKMORE and M. S. GEORGIADES (Douglas Aircraft The research being conducted on materials and construction Co.. Long Beach, CA) IN: 1986 Annual Reliability and methods by four institutes of the DFVLR is reviewed. The general Maintainability Symposium, Las Vegas, NV, January 28-30, 1986, roles of the four institutes are reviewed, and work done in the Proceedings . New York, Institute of Electrical and Electronics areas of structural mechanics, optimization of structures, new Engineers, Inc., 1986, p. 224-227. materials, aeroelastics and structural dynamics are described in This paper outlines the in-service reliability improvement detail. Research on modern active flutter suppression systems program developed and implemented for McDonnell Douglas and on the crushing behavior of construction techniques, on AI-Li MD-80 airplane project. The key reasons for initiating such a alloys, on improving the fatigue behavior of high-strength titanium program are summarized. The main objectives and goals are alloys, and on thermoplastic composites made of fiber-reinforced defined and the methods for achievement are explained. The paper PEEK is emphasized. C.D. shows that a closed-loop system of tracking malfunction-caused departure delays, and subsequent corrective action, are effective A87-14034’# Kansas Univ., Lawrence. in increasing and maintaining high dispatch reliability. The key STATIC TEST OF AN ULTRALIGHT AIRPLANE conclusion is that an in-sewice reliability improvement program be H. W. SMITH (Kansas, University, Lawrence) AIAA, General established for each new-airplane project to aid in the reduction Aviation Technology Conference, Anaheim, CA, Sept. 29-Oct. 1, of failures that delay airplanes from departing as scheduled. 1986. 7 p. Research supported by the University of Kansas. Author refs (Contract NAG1-345) A87-154 19 (AIAA PAPER 86-2600) F/A-18 HORNET RELIABILITY PROGRAM - STATUS REPORT This paper describes all of the work necessary to perform the T. W. GORDON (McDonnell Douglas Corp., Saint Louis, MO) IN: static test of an ultralight airplane. A steel reaction gantry was 1986 Annual Reliability and Maintainability Symposium, Las Vegas, designed first, then all of the loading whiffletrees, the hydraulic NV, January 28-30, 1986, Proceedings . New York, Institute of actuation system, and instrumentation systems were designed. Electrical and Electronics Engineers, Inc., 1986, p. 228-231. refs Loads and stress analyses were performed on the airplane and ’New Look’ steps inplemented to upgrade aircraft reliability the gantry and whiffletrees. Components tested to date are: tubing during procurement of the F/A-18 fighter in 1976 and results from

64 01 AERONAUTICS (GENERAL)

4-yr tracking of reliability in the field are summarized. The efforts N87-11686# Transportation Systems Center, Cambridge, Mass. expended to identify and record component and system faults GENERAL AVIATION ACTIVITY AND AVIONICS SURVEY and to develop more reliable components and track their Annual Summary Report, CY 1984 effectiveness are delineated. The aircraft required only a third the Oct. 1985 248 p number of maintenance man-hours per hour of flight as did the (AD-A168582; DOT-TSC-FAA-85-3; FAA-MS-85-5) Avail: NTlS aircraft it replaced. M.S.K. HC A1 1/MF A01 CSCL 01 B This report presents and a description of the 1984 General Aviation Activity and Avionics Survey. The survey was conducted A87-15436 during 1985 by the FAA to obtain information on the activity and DEMONSTRATION OF COMBAT DAMAGE REPAIR avionics of the United States registered general aviation aircraft ESTIMATOR fleet, the dominant component of civil aviation in the U.S. The D. H. KOVATCH (LTV Aerospace and Defense Co., Dallas, TX) survey was based on a statistically selected sample of about 12.7 and M. WEISENBACH (USAF, Aeronautical Systems Div., percent of the general aviation fleet. A response rate of 59.5 Wright-Patterson AFB, OH) IN: 1986 Annual Reliability and percent was obtained. Survey results are based upon responses Maintainability Symposium, Las Vegas, NV, January 28-30, 1986, but are expanded upward to represent the total population. Survey Proceedings . New York, Institute of Electrical and Electronics results revealed that during 1984 an estimated 36.1 million hours Engineers, Inc., 1986, p. 508-513. of flying time were logged by the 220,943 active general aviation This paper describes the results of an aircraft combat damage aircraft in the U.S. fleet, yielding a mean annual flight time per repair estimating procedure that was developed to evaluate the aircraft of 158 hours. The active aircraft represented about 82.6 survivability and reparability of existing inventory aircraft and percent of the registered general aviation fleet. The report contains conceptual designs. Geometric modeling techniques and an aircraft breakdowns of these and other statistics by manufactured/model battle damage repair data base form the nucleus of a simulation group, aircraft type, state and region of based aircraft, and primary model that identifies items damaged, applicable repair concepts, use. Also included are fuel consumption, lifetime airframe hours, repair time estimates, and resources required to return an aircraft avionics, and engine hours estimates. In addition, tables are to a combat ready status. Demonstration case results are presented included for detailed analysis of the avionics capabilities of the for various threat/attack scenarios. Author general aviation fleet. Estimates of general aviation miles flown in 1984 have also been included in this report. broken down by aircraft type. GRA

A87-16396 N87-11687# Naval Postgraduate School, Monterey, Calif. AEROSPACE PLANE - FACT OR FANTASY? A DYNAMIC MODEL FOR AIRFRAME COST ESTIMATION M.S. J. MOXON Flight International (ISSN 0015-3710), vol. 130, Aug. Thesis 30, 1986, p. 106, 107, 109, 110. R. L. BROWN Mar. 1986 80 p An evaluation is made of the technology development (AD-A168842) Avail: NTlS HC A05/MF A01 CSCL 14A prospects, economic feasibility, and commercial and military The Department of Defense has historically favored a relatively usefulness of the proposed NASA aerospace plane. Attention is simple parametric approach to cost estimation. Economic theory given to propulsion system-related questions, which hinge on the has largely been ignored and the learning curve has become the need for more than one powerplant to efficiently negotiate the customary analytical tool for relating production quantities to low-speed (under Mach 6) and high-speed (up to Mach 25) phases airframe costs. This thesis examines an effort to synthesize of a single-stage flight to LEO. Ramjets, pulsejets, scramjets and neoclassical economic theory with the traditional learning curve rockets in various combinations are under consideration; an methodology. The proposed model implements a dynamic cost airturboramjet system that combines rockets, ramjet and turbojet function that considers the effects of learning and production rate features is noted to be promising. O.C. on the production process. To empirically test its validity, the model is applied to the F-4 Phantom II production program and parameters are estimated using historical production data. Author (GRA) A87-16397 THE INSPECTABLE STRUCTURE N87-11688# National Aerospace Lab., Amsterdam (Netherlands). J. M. RAMSDEN Flight International (ISSN 0015-3710). vol. 130, Flight Div. Aug. 30, 1986, p. 113-116. A BRIEF INTRODUCTION TO THE HELICOPTER An evaluation is made of the prospects for airliner-structure H. J. G. C. VODEGEL 16 Sep. 1986 23 p Submitted for service-life extension through improved inspection, maintenance, publication materials choice, manufacturing quality control, and repair methods. (NLR-MP-85062-U; 88667019 ETN-86-98494) Avail: NTlS HC Attention is given to the unique characteristics of composites, A02/MF A01 aluminum-lithium alloys, and bonded structures in this context. Helicopter geometrical configurations, means of control, and O.C. general design features are introduced. Characteristics of the helicopter which differ from those of fixed wing aircraft are described. ESA A87-16398 US AIR TRANSPORT TECHNOLOGY - WHERE NEXT? N87-12533# Air Force Systems Command, Wright-Patterson AFB, D. LEARMOUNT Flight International (ISSN 0015-3710), vol. 130, Ohio. Foreign Technology Div. Aug. 30, 1986, p. 120-122, 124, 128. THE EFFECT OF A WINGLET ON THE SPATIAL VORTEX OF An evaluation is made of the fuel-choice and A SLENDER BODY AT HIGH ANGLE OF AlTACK thermodynamic-cycle-efficiency issues raised by the hypersonic W. ZlXlNG and W. GENXING 7 Jul. 1986 15 p Transl. into airliner, as well as to the powerplant configuration and airframe ENGLISH from Konggi Donglixue Xuebao (China), v. 3, no. 1, materials choices under consideration for the next-generation 1985 p 49-53 subsonic airliners. The structural performance improvements and (AD-A169925; FTD-ID(RS)T-0267-86) Avail: NTlS HC AO2/MF difficulties encountered to date with aluminum-lithium alloys and A01 CSCL20D thermoplastic composite matrices are discussed. The strongest The experimental investigation of the effect of a winglet on selling point of the 'Orient Express' hypersonic airliner is its the spatial vortex of a slender body at a high angle of attack is completion of a Los Angeles-Sydney flight in less than 2.5 hr; the presented. This investigation clearly shows that the circulation of development cost and small production runs anticipated for this the body vortex is minimized by the winglet and the vortex position aircraft, however, are projected to make financing prohibitively is lower than that without the winglet, so that the asymmetric expensive. O.C. problem can be solved. GRA

65 01 AERONAUTICS (GENERAL)

N87-12534# Air Force Inst. of Tech., Wright-Patterson AFB, flow and is independent of the effective core size of a vortical Ohio spot which can be much smaller than the grid size. Numerical THE PORTFOLIO MODEL OF TECHNOLOGICAL DEVELOP- results are presented to demonstrated the strong interaction MENT IN THE AIRCRAFT INDUSTRY M.S. Thesis between the trajectjories of the vortical spots and the redistribution D. M. SNYDER May 1986 56 p of vorticity in the background flowfield. Author (AD-A170832; AFIT/CI/NR-86-84T) Avail: NTlS HC A04/MF A01 CSCLO5C A87-13501 The aircraft industry has long been considered the quintessential AN AERODYNAMIC ANALYSIS AND THE SUBSEQUENT high technology industry. By examining the dynamics of MOTION OF EXTERNAL STORE technological change in this industry the portfolio model of C.-M. LEE and S.-J. HSlEH (National Cheng Kung University, technological advancement is developed. This model may be used Tainan, Republic of China) IN: Applied numerical modeling . San to describe technological advancement in large sophisticated, Diego, CA, Univelt, Inc., 1986, p. 671-678. refs technology intensive systems. The rapid advancement of individual A rational analytical method for the trajectory motion of an technologies as measured by improvements in specific performance external store after separation from an aircraft is presented. The parameters is evident in the aircraft industry. However, the ability nonuniform flow field around the store and the resultant force of a technology to improve performance in one or more key and moment acting on the store are obtained with the panel performance parameter may lead to adverse effects in other method, and the theory of rigid body motion is used to predict performance parameters or may not be compatible with other the subsequent motion of the store. A computationally efficient technological developments that are occurring in the industry. iterative scheme is employed to treat the mutual interference effect Individual technical improvements can be characterized as either among the wing, fuselage, and store. Results indicate that the portfolio reinforcing or portfolio shifting depending on whether or displacement of the store from the aircraft is independent of its not they promote shift in the way the technologies are combined hanging position, while the angular momentum is significant when into a total system or portfolio. The commercially and economically the store is released from the wing tip. R.R. successful products appear to be those that combine technologies into an optimum bundle of performance characteristics or portfolio. A87-13502 Technologies that flourish are not always the technologies on the COMPUTATION OF TWO-DIMENSIONAL SUPERSONIC leading edge of the performance frontier, but are those technologies TURBULENT FLOW OVER A COMPRESSION CORNER that product the optimum portfolio. Author (GRA) M.-S. LlOU and D.4. WANG (National Cheng Kung University, Tainan, Republic of China) IN: Applied numerical modeling . San Diego, CA, Univelt, lnc., 1986, p. 679-684. refs A two-layer equilibrium eddy-viscosity model is combined with 02 mass-averaged Navier-Stokes equations to form a closed system of equations for the calculation of supersonic flow over a AERODYNAMICS compression corner. The equations are solved by the fast and simple implicit numerical scheme of MacCormack (1981). Results Includes aerodynamics of bodies, combinations, wings, rotors, and demonstrate good prediction of the complicated shock/boundary control surfaces; and internal flow in ducts and turbomachinery. layer interacting flow, and significant improvement in the prediction of upstream pressure propagation and separated flow. R.R.

A87-13050 A87-13503 QUESTIONS AND PROBLEMS IN AERODYNAMICS SHOCK BOUNDARY LAYER INTERACTIONS IN LAMINAR [AERODINAMIKA V VOPROSAKH I ZADACHAKH] TRANSONIC FLOW OVER AIRFOILS USING A HYBRID N. F. KRASNOV, V. N. KOSHEVOI, A. N. DANILOV, V. F. METHOD ZAKHARCHENKO, E. E. BOROVSKll et al. Moscow, Izdatel’stvo S. N. TIWARI, C. S. VEMURU, and R. B. RAM (Old Dominion Vysshaia Shkola, 1985, 760 p. In Russian. refs University, Norfolk, VA) IN: Applied numerical modeling . San The principal questions and problems related to the main fields Diego. CA, Univelt. Inc.. 1986, p. 685-691. refs of modern aerodynamics are formulated, and answers to these A very economical method has been developed to investigate questions and problems are then supplied. Particular attention is the laminar viscous-inviscid interaction over airfoils in transonic given to the kinematics of a fluid medium; fluid and gas dynamics; flows. The external flow over airfoil is obtained by using a the theory of shock waves; the method of characteristics; flow finite-difference-relaxation technique and the method of integral past airfoils, wings, and bodies of revolution; friction and heat relations is used to obtain the Euler solution near the shock. The transfer; aerodynamic interference; and the aerodynamics of a laminar boundary-layer equations are solved by an integral method. rarefied medium. In addition to stationary aerodynamics, attention The streamline angle is a common variable between the inviscid is given to questions and problems related to nonstationary flow and viscous flows and accounts for the strong interaction. A new of a gas past isolated surfaces (wings and bodies) and aircraft as flow field is generated after the original airfoil is updated by adding a whole. V.L. the displacement thickness; the procedure is repeated until convergence occurs. The results obtained for a six percent A87-13499’ National Aeronautics and Space Administration. circular-arc airfoil are found to be in good agreement with the Langley Research Center, Hampton, Va. experimental results. The results for a swept super-critical airfoil INTERACTION OF DECAYING TRAILING VORTICES IN compare well with other available solutions. Author GROUNDSHEAR C. H. LIU (NASA, Langley Research Center, Hampton, VA) and L. A87-13504 TlNG (New York University, NY) IN: Applied numerical modeling NUMERICAL CALCULATION OF THREE-DIMENSIONAL . San Diego, CA, Univelt, Inc., 1986, p. 646-655. refs INVISCID SUPERSONIC FLOWS (Contract NO001 4-80-(2-0324; NCC1-58) M.-S. LlOU (National Cheng Kung University, Tainan, Republic of The drift of trailing vortices in a cross wind near to the ground China) and W.-C. HO IN: Applied numerical modeling . San is modeled by an unsteady, two-dimensional, rotational flowfield Diego, CA, Univelt, Inc., 1986, p. 692-697. refs with a concentration of large vorticity in spots having finite total An accurate and simple computational scheme for the strength. The problem is analyzed by a combination of the method space-marched solution of the three-dimensional Euler equations of matched asymptotic analyses for the decay of the vortical spots around bodies of varying shapes in supersonic flow is presented and the Euler solution for the unsteady rotational flow. A primary which uses a shock-capturing approach. The governing hyperbolic feature of the numerical scheme is that the grid size and time differential equations in Cylindrical coordinates are normalized step depend only the length and velocity scales of the background between the body and the bow shock, which completely surrounds

66 02 AERODYNAMICS the disturbed flow region, and the equations, in conservation-law force on the control surfaces grows monotonically. Initial formulations, are integrated from an initial data plane downstream experiments prove the potential of this solution and lead to further over the body using the explicit scheme of MacCormack (1969). development possibilities. Author The bow shock is treated as a sharp discontinuity, and the shock-fitting technique is employed, while the embedded shocks are captured automatically. Computational results for cones, a complex forebody, and several projectiles show the flowfields generated by these bodies for different angles of attack and Mach A87-13652# numbers, and good agreement is found with experimental data EXPERIMENTAL INVESTIGATION OF VORTEX FLOW OVER obtained for small angles of attack. R.R. DOUBLE-DELTA WING AT HIGH ALPHA D. MANOR (Saint Louis University, Cahokia, IL) IN: Israel Annual A87-13638# Conference on Aviation and Astronautics, 27th, Haifa, Israel, AN ANALYTICAL PARAMETRIC INVESTIGATION OF February 27, 28, 1985, Collection of Papers . Haifa, Israel, Technion NUMERICAL NONLINEAR VORTEX-LATTICE METHODS - Israel Institute of Technology, 1986, p. 166-172. refs Z. RUSAK and A. SEGINER (Technion - Israel Institute of The effects of large angles of attack, with and without sideslip, Technology, Haifa) IN: Israel Annual Conference on Aviation on the performance and stability of 65 deg/80 deg double-delta and Astronautics, 27th, Haifa, Israel, February 27, 28, 1985, wing configuration were determined experimentally using Collection of Papers . Haifa, Israel, Technion - Israel Institute of six-component force measurements, surface oil flow, and wake Technology, 1986, p. 13-22. refs total pressure surveys. The force measurement results are The analytical equations of the discretized numerically model presented in graphical form, and flow-field photographs of the that describes the vortex-lattice methods (VLM), are analyzed wake and surface oil flow are also included. Sideslip angle resulted parametrically. The analysis shows that the formulation of the in a decreased stall angle of attack, lower C(LMAX), enhancement computational grid and of the equations used for the numerical of post-stall lift recovery, and increased upwind vortex sheet size solution depends on two basic parameters of the method. One is and decreased downwind vortex size. The change in vortex size the chord length of the vortex panel on the wing, which is the is believed to cause out of plane forces and moments. These basic discretization length scale of the wing. The other is the adverse out of plane forces and moments are attributed to ratio of the segment length of a free vortex in the wake (the asymmetric vortex bursting and an increase in vortex spanwise basic wake-discreetization length) to wing-panel chord. This spacing at prestall angles, observed in the wake surveys. As angle conclusion is independent of either the specific paneling scheme of attack increased, vortex merging caused a reduction in sideforce. that is used on the wing or of the integration method of the The wake surveys color prints show that a narrow band at the trajectories of the free vortices in the wake. It is shown that the edge of the vortex sheet has a very steep total pressure gradient ratio of the two length scales governs the numerical uniqueness present in all configurations. Interior gradients are not as steep. and the convergence characteristics of the VLM solution. This is Author also demonstrated by numerical examples for flow over several slender delta wings. Author

A87-1364 1# A87- 13653# COMBINATION OF SUCTION AND TANGENTIAL BLOWING IN AERODYNAMIC COEFFICIENTS OF A CIRCULAR WING IN BOUNDARY LAYER CONTROL STEADY SUBSONIC FLOW M. BOASSON (Ministry of Defence, Haifa, Israel) and J. L. LOTH A. HAUPTMAN and T. MILOH (Tel Aviv University, Israel) IN: (West Virginia University, Morgantown) IN: Israel Annual Israel Annual Conference on Aviation and Astronautics, 27th, Haifa, Conference on Aviation and Astronautics, 27th, Haifa, Israel, Israel, February 27, 28, 1985, Collection of Papers . Haifa, Israel, February 27, 28, 1985, Collection of Papers . Haifa, Israel, Technion Technion - Israel Institute of Technology, 1986, p. 173-179. refs - Israel Institute of Technology, 1986, p. 53-60. refs An analytic solution is presented for the linearized lifting surface The paper presents a method for finding the optimal blowing problem of a thin circular wing with arbitrary twist and camber in parameters for achieving the highest values of lift for a STOL steady incompressible flow. The analysis is based on expansion aircraft. The airfoil is simulated as a flat plate with an adverse of the acceleration potential in infinite series of spheroidal pressure gradient produced by a source type flow. The transformed harmonics. Unlike previous analyses, which involve inversion of boundary layer equations are solved numerically using a finite infinite sets of linear equations or numerically solving integral difference method until flow separation is reached. Suction can equations, the present method leads to rather simple explicit be incorporated through a boundary condition. A wall jet is added expressions for the lift and moment coefficients, as well as for at the separation point, and calculations continue until separation the spanwise lift distribution and the induced drag. Author occurs once again. Lift is then calculated as a function of the centerline velocity ratio and the blowing momentum or blowing power coefficients: and the optimal parameters are computed. B.J. A87-13788# A87-13643# NOTES ON A GENERIC PARACHUTE OPENING FORCE A SPLIT CANARD CONFIGURAION FOR IMPROVED CONTROL ANALYSIS AT HIGH ANGLES OF ATTACK W. P. LUDTKE (US. Navy, Naval Surface Weapons Center, Silver D. LEVIN (Technion - Israel Institute of Technology, Haifa), A. Spring, MD) IN: Aerodynamic Decelerator and Balloon Technology KATZ, and A. DAVIDOVITCH IN: Israel Annual Conference on Conference, 9th, Albuquerque, NM, October 7-9, 1986, Technical Aviation and Astronautics, 27th, Haifa, Israel, February 27, 28, Papers . New York, American Institute of Aeronautics and 1985, Collection of Papers . Haifa, Israel, Technion - Israel Institute Astronautics, 1986, p. 72-85. refs of Technology, 1986, p. 65-73. refs (AIAA PAPER 86-2440) The ever growing demands for improving the performance of This paper develops a generic opening shock analysis that air-to-air missiles call for exploring the region of high angles of permits calculation of velocity profiles, shock factors, maximum attack. In this range the common canard controlled missile shock forces and their time of occurrence during deployment for configuration tends to lose its maneuverability. This effect is many types of parachutes. Criteria are presented and methods of attributed to the failure to maintain a monotonically growing lift calculation developed. Application of the analysis to an apparent force on the control surfaces when positioned a high combined anomaly in solid cloth parachute finite mass deployment, verifies angles. A dual surface canard configuration is intended to overcome the parachute diameter effect shown in the test performance. This this problem, by extending the range of angles for which the lift is illustrated by an example. Author

67 02 AERODYNAMICS

A87-13795# parachutes were also flight tested to evaluate their opening and ON THE UTILIZATION OF VORTEX METHODS FOR damping characteristics in a dynamic environment. The PARACHUTE AERODYNAMIC PREDICTIONS decelerators were configured to a maximum uninflated length of J. H. STRICKLAND (Sandia National Laboratories, Albuquerque, three feet for safety reasons. The results showed that the slotted NM) IN: Aerodynamic Decelerator and Balloon Technology square parachute was as stable and produced more drag, for a Conference, 9th, Albuquerque, NM, October 7-9, 1986, Technical nominal surface area greater than 3.5 sq ft, compared to a Papers . New York, American Institute of Aeronautics and cross-type parachute. Author Astronautics, 1986, p. 132-139. refs (Contract DE-AC04-76DP-00789) A87-13807# (AIAA PAPER 86-2455) IMPROVED MEASUREMENT OF THE DYNAMIC LOADS ACTING The purpose of this paper is to provide a brief review of vortex ON ROTATING PARACHUTES methods with application to parachute aerodynamics. A somewhat 2. SHPUND and D. LEVIN (Technion Foundation for Research generalized discussion of analysis techniques which are applicable and Development, Wind Tunnel Laboratory, Haifa, Israel) IN: to development of both two- and three-dimensional numerical Aerodynamic Decelerator and Balloon Technology Conference, 9th, solutions will be presented. A brief review of results from several Albuquerque, NM, October 7-9, 1986, Technical Papers . New bluff body simulations will also be presented. Author York, American Institute of Aeronautics and Astronautics, 1986, p. 22 2 - 2 2 7. A87-13796# (AIAA PAPER 86-2473) AXISYMMETRIC VORTEX LATTICE METHOD APPLIED TO An experimental apparatus for measuring the steady and PARACHUTESHAPES non-steady aerodynamic loads acting on parachutes and H. H. MCCOY and T. D. WERME (US. Navy, Recovery Systems decelerators has been designed and built in the wind tunnel Div., China Lake, CA) IN: Aerodynamic Decelerator and Balloon laboratory in the Technion. This apparatus was installed in the Technology Conference, 9th, Albuquerque, NM, October 7-9, 1986, subsonic wind tunnel. Calibration tests were carried out with both Technical Papers . New York, American Institute of Aeronautics dead weights and a rigid body simulating the flow around a rotating and Astronautics, 1986, p. 140-146. refs parachute. Good agreement was obtained between the results of (AIAA PAPER 86-2456) these tests and previously recorded data. The experiments with The Naval Weapons Center is developing a dynamic, unsteady parachutes included both the static and rotating cases, of a cross aerodynamic model to investigate the dynamics of inflating type parachute, with W/L of .333. The measurements in the static parachutes. In this report, analysis of axisymmetric, rigid shapes case included all six component of the force and moment. In the is presented. The model replaces the body with a series of vortex rotating case five load components were measured plus the roll rings. The generated vorticity is shed as discrete vortices and damping, and the roll transfer capability. The results obtained prove allowed to freely convect. The predicted drag and pressure the ability of the modified system in measuring accurately the distributions are compared to available data for ribbon parachutes. aerodynamic loads without interrupting the flow field of the Wake interactive, apparent mass calculations are also presented. parachute, as well as the versatility of the apparatus in obtaining Author dynamic data unobtainable in wind tunnel measurements before. Author A87-13798# AERODYNAMIC CHARACTERISTICS AND FLOW ROUND A87-13900 CROSS PARACHUTES IN STEADY MOTION NUMERICAL SOLUTION OF TRANSONIC POTENTIAL FLOWS C. Q. SHEN (Hongwei Machinery Factory, Xiangfan, People’s WITH FINITE ELEMENTS METHOD USING MULTIGRID Republic of China) and D. J. COCKRELL (Leicester, University, TECHNIQUE England) IN: Aerodynamic Decelerator and Balloon Technology V. DANEK (Ceskoslovenska Akademie Ved, Ustav Conference, 9th, Albuquerque, NM, October 7-9, 1986, Technical Termomechaniky. Prague, Czechoslovakia) Acta Technica CSAV Papers . New York, American Institute of Aeronautics and (ISSN 0001-7043), vol. 31, no. 3, 1986, p. 359-373. refs Astronautics, 1986, p. 157-165. Research supported by lrvin Great Techniques are presented for applying a multigrid finite element Britain, Ltd. refs model (MFEM) to modeling steady transonic potential flows in (AIAA PAPER 86-2458) channels and cascades. A full potential equation with Neumann Making extensive force-measurement and flow-visualization boundary equation is defined and solved with an iterative tests in a wind tunnel and also conducting blockage-effect successive line overrelaxation (SLOR) method. Interpolation experiments under water, the authors considered the physical expressions are formulated for generating connected multiple grids reasons for the aerodynamic characteristics of cross parachute to decompose the partial differential equations for easier solution. canopies. The arm ratio of the canopy is a significant aerodynamic Residual terms are restricted to an original coarse grid and parameter in the determination of its drag and stability accounted for over several SLOR iterations. The interpolation and characteristics, but the porosity of the canopy fabric is equally restrictions operators necessary for transitions from a coarse grid important. Physical reasons are advanced for the importance of to a fine mesh are described in detail. The flow around a NACA these two parameters, and recommendations are made as to their 0012 airfoil at Mach 0.8 is modeled to illustrate the effectiveness best choice in a given application. Author of the method in the presence of shock. M.S.K.

A87-13805# A87-13994# DRAG AND STABILITY IMPROVEMENTS OF A SQUARE THEORETICAL INVESTIGATIONS OF TRANSONIC ROTOR- PARACHUTE BLADE AERODYNAMICS FHEORETISCHE UNTERSUCH- C. T. CALIANNO (US. Navy, Naval Air Development Center, UNGEN ZUR TRANSSONISCHEN ROTORBLATI-AERODY- Warminster, PA) IN: Aerodynamic Decelerator and Balloon NAMIK] Technology Conference, 9th. Albuquerque, NM, October 7-9, 1986, J. HERTEL, E. KRAEMER, and S. WAGNER (Muenchen, Technical Papers . New York, American Institute of Aeronautics Universitaet der Bundeswehr, Neubiberg, West Germany) BMFT, and Astronautics, 1986, p. 21 1-216. Statusseminar ueber Luftfahrtforschung und Luftfahrttechnologie, (AIAA PAPER 86-2471) Munich, West Germany, Apr. 28-30, 1986, Paper. 27 p. In A modified square parachute aimed toward producing a stable, German. refs low cost replacement for the cross-type parachute was evaluated. Techniques for computing the three-dimensional transonic flow Wind tunnel tests were conducted to determine the drag and around a helicopter rotor blade are developed and demonstrated. stability characteristics of square type parachutes modified by A number of theoretical approaches and spatial discretization lowering their normal suspension line length/canopy diameter ratio schemes are characterized, and a procedure based on a from 1.0 to 0.45 and 0.60, or slotting the canopies. These finite-volume-method solution of the Euler equations is applied to

68 02 AERODYNAMICS the transonic flow around a wing profile using a modified H-type A87-14028# conforming grid. The results are presented graphically, and the COMPARISON OF NUMERICAL SOLUTIONS OF LOWER accuracy obtained is shown to be equal to that of a C-type grid. ORDER AND HIGHER ORDER INTEGRAL EQUATION METHODS The modification of the method to treat rotor-blade flows is FOR TWO-DIMENSIONAL AEROFOILS described, and preliminary results (for an isolated nontwisted blade M. J. SHEU (National Tsing Hua University, Hsinchu, Republic of at tip Mach number 0.85, neglecting the effects of tip vortices) China) and D. R. CHENG AIAA, General Aviation Technology are presented and discussed. T.K. Conference, Anaheim, CA, Sept. 29-Oct. 1, 1986. 8 p. refs (AIAA PAPER 86-2591) A number of numerical solutions of lower-order and higher-order A87-13995# panel methods are presented and compared for predicting the IMPROVEMENT OF MATHEMATICAL MODELS OF properties of two-dimensional steady incompressible, inviscid flow HELICOPTERS BY ANALYTICAL PRESENTATION OF past lifting airfoils. The effects of higher-order approximations (i.e., NONLINEAR AERODYNAMICS [VERBESSERUNG DER the use of the curved element and linear varying sigularity on the MATHEMATISCHEN MODELLE VON HUBSCHRAUBERN airfoils) are investigated. This paper presents the significance of DURCH ANALYTISCHE DARSTELLUNG NICHTLINEARER the higher-order curved-panel models and the lower-order flat-panel AERODYNAMIK] models for the computational accuracy and for the numerical U. LEES and WAGNER (Muenchen, Universitaet der S. stability versus both the geometric shape and the effect of the Bundeswehr, Munich, West Germany) BMFT, Statusseminar ueber distribution of the singularities. Author Luftfahrtforschung und Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, Paper. 31 p. In German. refs A new procedure has been developed for analyzing the steady A87-14035'# PRC Kentron, Inc., Hampton, Va. and unsteady aerodynamic coefficients of helicopters. Arbitrary flow EFFECT OF AN UPSTREAM WAKE ON A PUSHER states on rotor blades are given as attached and separated flow, PROPELLER and a logical departure from steady and unsteady flow clarifies M. A. TAKALLU (PRC Kentron, Inc., Hampton, VA) AIAA, General partial effects. The elimination of blade elements by analytic Aviation Technology Conference, Anaheim, CA, Sept. 29-Oct. 1, integration of the blade is an essential step to reducing the 1986. 11 p. refs calculating time. C.D. (Contract NASI -17993) (AIAA PAPER 86-2602) An analyticaVcomputationa1 study has been conducted to A87- 140 10# predict the effect of an upstream wake on an operating propeller. NUMERICAL CALCULATION OF VISCOUS INTERNAL FLOWS The upstream wing/pylon was modeled by a constant chord wing [NUMERISCHE BERECHNUNG REIBUNGSBEHAFTETER of NACA 0012 sections and was placed at a variable distance INNENSTROEMUNGEN] (0.1 - 0.3 chord) upstream of a scaled model propeller (SR-2). D. HAENEL, K. DORTMANN, W. SCHROEDER, and R. SCHWANE The wake model was a similarity formulation. The periodic behavior (Aachen, Rheinisch-Westfaelische Technische Hochschule, West ofthe flow during the passage through the wake was formulated Germany) BMFT, Statusseminar ueber Luftfahrtforschung und in terms of time-dependent variation of each blade section's angle Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, of attack. It was found that the final expressions for the unsteady Paper. 16 p. In German. refs pressure distribution on each blade section are periodic and that Calculative procedures using two different concepts were the unsteady circulation and lift coeff icieents exhibit a hysteresis developed to evaluate viscous compressible flows. One procedure loop. Author uses the boundary-layer concept and solves flow by coupling solutions of the flow with boundary-layer solutions, using both direct A87-14038*# National Aeronautics and Space Administration. and inverse methods. The other procedure uses the Navier-Stokes Langley Research Center, Hampton, Va. equations and finite-difference methods to obtain a numerical WIND-TUNNEL INVESTIGATION OF THE OMAC CANARD solution. The first method provides solutions more economically, CONFIGURATION but its validity is lessened by the boundary layer approximation. W. C. INGRAM, L. P. YIP (NASA, Langley Research Center, The second method provides more comprehensive solutions, and Hampton, VA), and E. L. COOK (OMAC, Inc., Albany, GA) AIM, its greater cost is partly offset by using improved solution General Aviation Technology Conference, Anaheim, CA, Sept. methods. C.D. 29-Oct. 1, 1986. 9 p. refs (AIAA PAPER 86-2608) A87-14022# Wind-tunnel tests were conducted on a 0.175-scale model of THEORETICAL STUDIES OF THE ETW DIFFUSER AND OF THE the OMAC Laser 300 canard configuration in the NASA Langley SECOND THROAT [THEORETISCHE ARBEITEN ZUM 12-Foot Low-Speed Wind Tunnel to determine its low-speed high ETW-DIFFUSOR UND ZUR ZWEITEN VERENGUNG] angel-of-attack aerodynamic characteristics. The Laser 300 is a H. W. STOCK, W. HAASE, S. LECHER, and W. SEIBERT (Dornier general aviation turboprop pusher aircraft utilizing a canard GmbH, Friedrichshafen, West Germany) BMFT, Statusseminar configuration. The design incorporates a low forward wing and a ueber Luftfahrtforschung und Luftfahrttechnologie, Munich, West high main wing with a leading-edge droop installed on the outboard Germany, Apr. 28-30, 1986, Paper. 34 p. In German. refs panel and tip fins mounted on the wing tips. The model was The flow fields in the diffuser and near the second throat of tested over a range of -6 to 50-deg angle-of-attack and 20 to -20 the modified configuration of the European Transonic Wind Tunnel deg sideslip. Static force and moment data were measured, and (ETW) at inlet Mach numbers 0.54-0.6 are investigated theoretically the longitudinal and lateral-directional characteristics were using numerical simulations. The diffuser is treated in two ways, determined. Author in two dimensions as an equivalent circular-cross-section diffuser and in three dimensions using an iterative method for compressible A87-14095' Princeton Univ., N. J. inviscid turbulent boundary-layer flows and a finite-volume scheme NUMERICAL SOLUTION OF THE EULER EQUATION FOR to solve the Euler equations; the throat flow is simulated by COMPRESSIBLE INVISCID FLUIDS assuming it is inviscid and two-dimensional and applying the A. JAMESON (Princeton University, NJ) IN: Numerical methods finite-volume Euler method. The results are presented in tables, for the Euler equations of fluid dynamics. Philadelphia, PA, Society diagrams, and graphs, compared with experimental data obtained for Industrial and Applied Mathematics, 1985, p. 199-245. refs in the ETW test-rig configuration, and characterized. It is found (Contract NO0014-81-K-0379; NAG1-1 86) that the ETW configuration with the second throat is much more An effort is made to develop a satisfactory numerical method susceptible to separation than the test-rig configuration. A new for the calculation of steady solutions of the Euler equations for throat geometry with two joints and more rounded contours is inviscid compressible gas flows. The intended application is the recommended to improve the flow characteristics. T.K. prediction of the aerodynamic properties of aircraft flying at

69 02 AERODYNAMICS transonic speeds. Particular consideration is given to the A87-14104'# National Aeronautics and Space Administration. modification of the equations to improve convergence to a steady Ames Research Center, Moffett Field, Calif. state; finite volume formulation; adaptive dissipation; schemes COMPUTATION OF SHARP-FIN-INDUCED SHOCK designed to improve the resolution of shock waves; hybrid WAVE/TURBULENT BOUNDARY-LAYER INTERACTIONS multistage time stepping schemes; residual averaging; a multigrid C. C. HORSTMAN (NASA, Ames Research Center, Moffett Field, scheme; and trials with Burgers' equation. Results clearly CA) AlAA Journal (ISSN 0001-1452), vol. 24, Sept. 1986, p. demonstrate that the convergence of a time-dependent hyperbolic 1433-1440. Previously cited in issue 17, p. 2466, Accession no. system to a steady state can be substantially accelerated by the A86-38409. refs introduction of multiple grids. B.J. A87-14105'# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. A87-14096' National Aeronautics and Space Administration. CONVERGENCE ACCELERATION FOR A THREE-DIMEN- Langley Research Center, Hampton, Va. SIONAL EULEWNAVIER-STOKES ZONAL APPROACH ACCELERATION TO A STEADY STATE FOR THE EULER APPROACH EQUATIONS F. FLORES (NASA, Ames Research Center, Moffett Field, CA) E. TURKEL (NASA, Langley Research Center, Hampton, VA; Tel (Computational Fluid Dynamics Conference, 7th, Cincinnati, OH, Aviv University, Israel) IN: Numerical methods for the Euler July 15-17, 1985, Technical Papers, p. 75-86) AlAA Journal (ISSN equations of fluid dynamics . Philadelphia, PA, Society for Industrial 0001-1 452), vol. 24, Sept. 1986, p. 1441, 1442. Abridged. Previously and Applied Mathematics, 1985, p. 281 -311. Previously announced cited in issue 19, p. 2743, Accession no. A85-40934. in STAR as N84-29852. refs (Contract NASl-16394; NASI-17130) A multistage Runge-Kutta method is analyzed for solving the A87-14108*# National Aeronautics and Space Administration. Euler equations exterior to an airfoil. Highly subsonic, transonic Langley Research Center, Hampton, Va. and supersonic flows are evaluated. Various techniques for TURBULENT FLOW AROUND A WING/FUSELAGE-TYPE accelerating the convergence to a steady state are introduced JUNCTURE and analyzed. Author L. R. KUBENDRAN (NASA, Langley Research Center, Hampton, VA), H. M. MCMAHON, and J. E. HUBBARTT (Georgia Institute of Technology, Atlanta) AlAA Journal (ISSN 0001-1452), vol. 24, Sept. 1986, p. 1447-1452. Previously cited in issue 07, p. A87-14099 835, Accession no. A85-19475. refs VORTEX-SHEET CAPTURING IN NUMERICAL SOLUTIONS OF (Contract NAG1-40) THE INCOMPRESSIBLE EULER EQUATIONS A. RlZZl and L.-E. ERIKSSON (Flygtekniska Forsoksanstalten, Bromma, Sweden) IN: Numerical methods for the Euler equations A87-14109'# National Aeronautics and Space Administration. of fluid dynamics . Philadelphia, PA, Society for Industrial and Langley Research Center, Hampton, Va. Applied Mathematics, 1985, p. 437-469. refs COMPARISON OF FINITE VOLUME FLUX VECTOR SPLllTlNGS Numerical solutions to the Euler equations that contain vorticity FOR THE EULER EQUATIONS appear qualitatively correct, but how the vorticity is generated is W. K. ANDERSON, J. L. THOMAS (NASA, Langley Research still an open question. The simpler case of incompressible flow Center, Hampton, VA), and B. VAN LEER (Delft, Technische where the only allowable discontinuity is a vortex sheet is a good Hogeschool, Netherlands) AlAA Journal (ISSN 0001-1 452), vol. model to use for studying this question. The present approach is 24, Sept. 1986, p. 1453-1460. Previously cited in issue 07, p. the artificial compressibility method which leads to a hyperbolic 838, Accession no. A85-19533. refs system of equations that are solved by finite-volume differences centered in space and explicit multistage time stepping. The stability of this novel system is analyzed, its allowable discontinuities are A87-141 lo'# National Aeronautics and Space Administration. described, and appropriate far-field and solid wall boundary Langley Research Center, Hampton. Va. conditions are introduced. Results are presented for both two- SPECTRAL METHODS FOR MODELING SUPERSONIC and three-dimensional flows. Whether vorticity is produced or not CHEMICALLY REACTING FLOWFIELDS depends very strongly on the body geometry and the transient J. P. DRUMMOND, M. Y. HUSSAINI, and T. A. ZANG (NASA, discontinuities that evolve in the flow field. The results are analyzed Langley Research Center, Hampton, VA) AlAA Journal (ISSN for the entropy produced in the flow-field, and for the difffusion of 0001-1452), vol. 24, Sept. 1986, p. 1461-1467. Previously cited in the vortex sheets. Author issue 07. p. 843, Accession no. A85-19651. refs

A87-14111'# National Aeronautics and Space Administration. A87- 14 10 1# Langley Research Center, Hampton, Va. FINITE ELEMENT NAVIER-STOKES CALCULATION OF TWO-DIMENSIONAL BLADE-VORTEX FLOW VISUALIZATION THREE-DIMENSIONAL TURBULENT FLOW NEAR A INVESTIGATION PROPELLER E. R. BOOTH, JR. and J. C. YU (NASA, Langley Research Center, D. H. PELLETIER (Montreal, Universite. Montreal, Canada) and J. Hampton, VA) AlAA Journal (ISSN 0001-1452), vol. 24, Sept. A. SCHETZ (Virginia Polytechnic Institute and State University, 1986, p. 1468-1473. Previously cited in issue 01, p. 2, Accession Blacksburg) AlAA Journal (ISSN 0001-1452). vol. 24, Sept. no. A85-10858. refs 1986, p. 1409-141 6. Navy-supported research. Previously cited in issue 07, p. 844. Accession no. A85-19698. refs A87-14117'# Washington Univ., Seattle. EXPERIMENTAL AND NUMERICAL INVESTIGATION OF SUPERSONIC TURBULENT FLOW THROUGH A SQUARE A87-14102# DUCT VORTEX PANEL CALCULATION OF WAKE ROLLUP BEHIND D. 0. DAVIS, F. B. GESSNER (Washington, University, Seattle), A LARGE ASPECT RATIO WING and G. D. KERLICK (NASA, Ames Research Center; Informatics A. PLOTKIN (San Diego State University, CA) and D. T. YEH General Corp., Moffett Field, CA) AlAA Journal (ISSN 0001-1452), AlAA Journal (ISSN 0001-1452), vol. 24, Sept. 1986, p. 1417-1423. vol. 24, Sept. 1986, p. 1508-1515. Previously cited in issue 19, p. Army-supported research. Previously cited in issue 19, p. 2737, 2739, Accession no. A85-40728. refs Accession no. A85-40686. refs (Contract NCA2-IR-850-401)

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A87-14 119# calculated, and the results are compared with the one-dimensional EFFECT OF TWO ENDWALL CONTOURS ON THE theory. Author PERFORMANCE OF AN ANNULAR NOZZLE CASCADE S. H. MOUITAPHA (Pratt and Whitney Canada, Longueuil) and A87-14263# R. G. WILLIAMSON (National Research Council of Canada, Gas STUDY OF A BOUNDED JET FLOW CONSIDERING THE INITIAL Dynamics Laboratory, Ottawa) AlAA Journal (ISSN 0001 -1452), TURBULENCE. I1 - IN THE CASE OF RELATIVELY LARGE vol. 24, Sept. 1986, p. 1524-1530. Previously cited in issue 18, p. NOZZLE ASPECT RATIO 261 0, Accession no. A85-39661. refs M. NAKASHIMA (Kagoshima National College of Technology, Japan), T. NOZAKI (Kagoshima University, Japan), and K. HATTA A87-14 125# (Chubu University, Kasugai, Japan) JSME, Bulletin (ISSN INFLUENCE OF TRAILING-EDGE MESHES ON SKIN FRICTION 0021-3764), vol. 29, July 1986, p. 2042-2048. refs IN NAVIER-STOKES CALCULATIONS For an approximate calculation of the bounded jet flow, a W. HAASE (Dornier GmbH, Friedrichshafen, West Germany) AlAA velocity distribution function on the bounded jet center-plane is Journal (ISSN 0001-1452), VOI.24, Sept. 1986, p. 1557-1559. proposed, considering the effects of the wall turbulence and the Sponsorship: Bundesministerium der Verteidigung. refs free turbulence. Also, in order to determine the empirical parameter (Contract BMVG-T/R41/D0007/D1407) contained in this function, experiments were carried out using a Calculations at a Mach number of 0.73, Reynolds number of nozzle having an aspect ratio of 16 with the initial turbulence 6.5 million, and an angle of attack of 3.19 deg are performed to intensity prescribed. As a result, the velocity distributions of the interpret the trailing-edge skin-friction distribution with respect to bounded jet flow are well expressed by the proposed function, the mesh structure in the trailing-edge vicinity of the RAE 2822 regardless of the initial turbulence intensity. Furthermore, the airfoil. Results for skin friction and pressure distributions were variation of the flow patterns towards downstream can be shown obtained in the case of aligning the trailing edge mesh with the by means of the parameter contained in the function. Author flow direction, and additional tests showed the results to be independent of mesh type, finite approach, filtering technique and A87-14360# turbulence model. Wakeline-adapted meshes are shown to AERODYNAMIC FORCE CALCULATIONS OF AN ELLIPTICAL overcome some trailing edge problems, and make possible the CIRCULATION CONTROL AIRFOIL performance of physically plausible flowfield predictions even in I. CHOPRA (Maryland, University, Collage Park), M. SUN, and S. highly viscous interaction regions. R.R. I. PA1 Journal of Aircraft (ISSN 0021-8669), vol. 23, Sept. 1986, p. 673-680. refs (Contract NO0167-85-C-0077) AB?-14 127# A method is developed to predict the aerodynamic forces on CONSTANT-DENSITY APPROXIMATION TO TAYLOR-MAC- a circulation control elliptical airfoil in a two-dimensional flow COLL SOLUTION environment. By distributing source panels on the airfoil surface C. S. MOORTHY (Indian Institute of Technology, Kanpur, India) in the separation region and using conformal mapping techniques, AlAA Journal (ISSN 0001-1452), vol. 24, Sept. 1986, p. a simple solution for the potential flow including effects of separated 1561-1 563. refs wake is obtained. The development of boundary layers and wall-jet The Taylor-Maccoll equation is arranged with the nonlinearities is calculated by a finite difference method. The potential flow with grouped into one term which is zero on the cone surface as well separated wake effect calculations and boundary layer and wall-jet as at the oblique shock, and it is shown that the constant-density calculations are combined in an iterative process to determine approximation may be accurately employed in the supersonic range the aerodynamic forces under given jet momentum coefficient and by neglecting this term. The transonic and hypersonic similarity freestream condition. The effect of separated wake is found parameters for conical flow are derived from the wedge flow significant for a cylinder. The correlation of the calculation results parameters, and a Newtonian approximation is obtained at high with the available experimental data appears reasonable. Author Mach numbers. Shock detachment is found to occur at the shock angle at which the density ratio across the shock is maximized, A87-14362# for a given half-angle of the wedge or cone. R.R. SPANWISE VARIATION OF LAMINAR SEPARATION BUBBLES ON WINGS AT LOW REYNOLDS NUMBER A87-14129# W. G. BASTEDO, JR. and T. J. MUELLER (Notre Dame, University, COMMENT ON 'COMPUTATION OF CHOKED AND IN) Journal of Aircraft (ISSN 0021-8669), vol. 23, Sept. 1986, SUPERSONIC TURBOMACHINERY FLOWS BY A MODIFIED p. 687-694. Research supported by the University of Notre Dame. POTENTIAL METHOD Previously cited in issue 19, p. 2738, Accession no. A85-40706. T. C. ADAMSON, JR., J. MACE, and A. F. MESSITER (Michigan, refs University, Ann Arbor) AlAA Journal (ISSN 0001-1452), vol. 24, (Contract N00014-83-K-0239) Sept. 1986, p. 1566; Author's Reply, p. 1566, 1567. refs A87-14363*# National Aeronautics and Space Administration. A87-14261# Langley Research Center, Hampton, Va. AN IMPLICIT TIME-MARCHING SCHEME FOR TRANSONIC IMPACT OF AIRFOIL PROFILE ON THE SUPERSONIC FLOW AERODYNAMICS OF DELTA WINGS H. DAIGUJI (Tohoku University, Sendai, Japan) and M. KUZUHARA R. M. WOOD and D. S. MILLER (NASA, Langley Research Center, (Mitsubishi Research Institute Inc., Tokyo, Japan) JSME, Bulletin Hampton, VA) Journal of Aircraft (ISSN 0021-8669), vol. 23, (ISSN 0021-3764), vol. 29, July 1986, p. 2032-2035. refs Sept. 1986, p. 695-702. Previously cited in issue 01, p. 4, Accession An implicit time-marching finite-difference scheme is developed no. A86-11038. refs for computing steady two-dimensional inviscid transonic flows with arbitrary shaped boundaries. Most of the existing implicit A87-14365# time-marching schemes, including the Beam-Warming scheme, are DIRECT-INVERSE TRANSONIC WING ANALYSIS-DESIGN unconditionally stable according to Neumann's stability criterion, METHOD WITH VISCOUS INTERACTION but actually cannot take a sufficiently large Courant number L. A. CARLSON (Texas A & M University, College Station) and R. because the diagonally dominant condition of the coefficient matrix A. WEED (Lockheed-Georgia Co., Marietta) Journal of Aircraft is lost. In the present scheme, in order to remove this restriction (ISSN 0021-8669), vol. 23, Sept. 1986, p. 711-718. Research Of the Courant number, the Robert-Weiss convective-difference supported by the Lockheed-Georgia Co. and Texas A & M Research scheme is applied in place of the Crank-Nicholson scheme in the Foundation. Previously cited in issue 01, p. 5, Accession no. Beam-Warming delta-form approximate-factorization algorithm. As A86-11040. refs a numerical example, shocked flows through a nozzle are (Contract NO0167-81 -C-0078-P00004)

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A87-14370# A87-15 189# VISUALIZATION OF WING TIP VORTICES IN ACCELERATING THE USE OF MATHEMATICAL MODELS IN AERODYNAMICS AND STEADY FLOW (THE W. RUPERT TURNBULL LECTURE) P. FREYMUTH. W. BANK (Colorado, University, Boulder), and F. P. MANDL (Carleton University, Ottawa, Canada) (CASI, Annual FlNAlSH Journal of Aircraft (ISSN 0021-8669), vol. 23, Sept. General Meeting, Vancouver, Canada, May 12, 1986) Canadian 1986, p. 730-733. Previously cited in issue 17, p. 2469, Accession Aeronautics and Space Journal (ISSN 0008-2821), vol. 32, June no. A86-38457. refs 1986, p. 1 13-121. refs The interactions which are required between experimental aerodynamicists and applied mathematicians for fruitful progress to be made in research are illustrated with several design evaluation results. The discussion covers the characterization of potential A87- 14372# flow around suction airfoils with split flaps, an application of rotating LOWER-SIDE NORMAL FORCE CHARACTERISTICS OF DELTA parachute shape theory, and analysis of inviscid hypersonic flow WINGS AT SUPERSONIC SPEEDS around a conical, flat-top wing-body configuration. A rotating E. LARSON (Flygtekniska Forsoksanstalten, Bromma, Sweden) S. parachute is shown to be superior to a similarly-shapednon-rotating Journal of Aircraft (ISSN 0021-8669). vol. 23, Sept. 1986, p. 735, parachute in terms of drag per unit weight and per unit volume. 736. Sponsorship: Forsvaret Materielverk. refs Finally, numerical modeling efforts are employed to predict a shape (Contract FMV-AU-2154) which achieve an optimum L/D for a hypersonic wing-body A simplified analytical model is presented for the lower-side configuration. M.S.K. normal force characteristics of flat, sharp leading-edge delta wings at supersonic speeds. The model is based on a two-term formulation for estimating the normal force on slender bodies. A87-15206 Mach number effects are shown to decrease with increasing sweep. START-UP OF A WIND TUNNEL WITH A MULTICHANNEL Results are provided from sample calculations for Mach number DIFFUSER [ZAPUSK AERODINAMICHESKOI TRUBY S vs. angle of attack, lift curve slope vs. Mach number and normal MNOGOKANAL'NOM DIFFUZOROM] force vs. angle of attack. Good agreement was found with model I. IU. VASILEV, N. N. ZAKHAROV, E. S. IVANOV, V. IU. predictions and experimental results for Mach numbers above the NIKOLENKO, and K. N. PICHKOV Aviatsionnaia Tekhnika (ISSN threshold of conical flow and below the threshold of supersonic 0579-2975), no. 2, 1986, p. 28-32. In Russian. refs leading-edge flow. M.S.K. The effect of the principal geometrical parameters of the test section on the pressure gradient during the start-up of a supersonic wind tunnel with a short multichannel vaned diffuser is investigated experimentally in the Mach range 3.8-4.5. An analysis of A87-14652'# National Aeronautics and Space Administration. experimental results indicates that multichannel vaned diffusers of Langley Research Center, Hampton, Va. wind tunnels can be made much shorter than monodiffusers but VECTORIZABLE MULTIGRID ALGORITHMS FOR are somewhat less efficient. The pressure gradient during the TRANSONIC-FLOW CALCULATIONS start-up of wind tunnels with a multichannel diffuser can be reduced N. D. MELSON (NASA, Langley Research Center, Hampton, VA) by improving flow structure in the outer channels, which can be Applied Mathematics and Computation (ISSN 0096-3003). vol. 19, achieved, for instance, by using a boundary layer control system. 1986, p. 21 7-238. refs V.L. The analysis and the incorporation into a multigrid scheme of several vectorizable algorithms are discussed. von Neumann analyses of vertical-line, horizontal-line, and alternating-direction A87-15216 ZEBRA algorithms were performed; and the results were used to THE EFFECT OF RANDOM WIND GUSTS ON THE STABILITY predict their multigrid damping rates. The algorithms were then OF A PARACHUTE SYSTEM [O VLllANll SLUCHAINYKH successfully implemented in a transonic conservative full-potential PORYVOV VETRA NA USTOICHIVOST' PARASHIUTNOI computer program. The convergence acceleration effect of multiple SISTEMY] grids is shown, and the convergence rates of the vectorizable V. M. CHURKIN and A. E. PRAVOTOROV Aviatsionnaia Tekhnika algorithms are compared with those of standard successive-line (ISSN 0579-2975), no. 2, 1986, p. 72-76. In Russian. refs overrelaxation (SLOR) algorithms. Author The theory of high-frequency random processes is used to determine stability conditions for the motion of a geometrically invariable parachute system subjected to the effect of random wind gusts. The predictions of the theory are found to be in good agreement with the results of a numerical integration of the initial A87-14771 equations of motion of the parachute system. V.L. PERFORMANCE EVALUATION OF AN INVERSE INTEGRAL EQUATION METHOD APPLIED TO TURBOMACHINE CASCADES A87-15223 D. MARTIN (Brown Boveri et Cie. AG, Dietlikon, Switzerland) and DETERMINATION OF DYNAMIC STRESSES IN THE M. RIBAUT (Brown Boveri et Cie. AG, Wettingen, Switzerland) HEAT-INSULATING COATINGS OF FLIGHT VEHICLES DURING International Journal for Numerical Methods in Fluids (ISSN AERODYNAMIC HEATING [OPREDELENIE DlNAMlCHESKlKH 0271-2091), vol. 6, Aug. 1986, p. 573-583. refs NAPRlAZHENll V TEPLOZASHCHITNYKH POKRYTIIAKH An improved formulation of the inverse integral equation method LETATEL'NYKH APPARATOV PRI AERODINAMICHESKOM proposed by Ribaut and Martin (1986) which allows, in particular, NAGREVE] a well-posed problem to be ensured is presented. The L. I. KUDRIASHEV, N. L. MENSHIKH, and A. F. FEDCHEV corresponding computation code is tested in an exhaustive manner Aviatsionnaia Tekhnika (ISSN 0579-2975), no. 2, 1986, p. 92-95. for axial and radial compressor and turbine cascades. The In Russian. agreement between the velocity field obtained with the inverse The paper is concerned with the thermoelasticity problem for method and that resulting from a direct calculation is examined a two-layer thin-walled shell of the type commonly used in the for subsonic, transonic, and supersonic flows. The accuracy and structures of aircraft and engines. Under conditions of aerodynamic reliability of the solution to the boundary condition problem are heating, when the dilatation term characterizing the mutual effect excellent for the subsonic and transonic flows. However, for the of the temperature and strain fields can be neglected, the supersonic flow, the application of the method seems to be limited thermoelasticity problem is solved in two stages. First, the heat by the use of elementary solutions of the Laplace operator. conduction equation is solved for given boundary and initial Author conditions; after this, the stresses are determined. V.L.

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A87-15229 A87-15454" National Aeronautics and Space Administration. CALCULATION OF AERODYNAMIC FORCE COEFFICIENTS [K Ames Research Center, Moffett Field, Calif. RASCHETU KOEFFITSIENTOV AERODINAMICHESKIKH SIL] MODELING OF TURBULENT SEPARATED FLOWS FOR 0. P. SIDOROV Aviatsionnaia Tekhnika (ISSN 0579-2975), no. AERODYNAMIC APPLICATIONS 2, 1986, p. 109-112. In Russian. J. G. MARVIN (NASA, Ames Research Center, Moffett Field, CA) The graphic relationships based on experimental and theoretical IN: Recent advances in aerodynamics . New York, Springer-Verlag, data which have been used in several earlier studies to determine 1986, p. 99-164. Previously announced in STAR as N83-33849. the aerodynamic characteristics of flight vehicles are presented refs here in analytical form. In particular, analytical expressions are Steady, high speed, compressible separated flows modeled given for the friction coefficient of the fuselage, aerodynamic through numerical simulations resulting from solutions of the braking coefficients in the region of the front and tail lifting surfaces, mass-averaged Navier-Stokes equations are reviewed. Emphasis Mach number at the front and tail lifting surfaces, profile drag is placed on benchmark flows that represent simplified (but realistic) coefficient of the lifting surfaces, and wave-drag coefficient of the aerodynamic phenomena. These include impinging shock waves, tail unit. V.L. compression corners, glancing shock waves, trailing edge regions, and supersonic high angle of attack flows. A critical assessment of modeling capabilities is provided by comparing the numerical simulations with experiment. The importance of combining A87-15451 Florida State Univ., Tallahassee. experiment, numerical algorithm, grid, and turbulence model to RECENT ADVANCES IN AERODYNAMICS effectively develop this potentially powerful simulation technique A. KROTHAPALLI, ED. (Florida State University, Tallahassee) and is stressed. S.L. C. A. SMITH, ED. (NASA, Ames Research Center, Moffett Field, CA) New York, Springer-Verlag, 1986, 767 p. For individual A87-15459 items see A87-15452 to A87-15469. THE INDUCED AERODYNAMICS OF JET AND FAN POWERED Papers are presented on unsteady transonic aerodynamics and V/STOL AIRCRAFT aeroelasticity, the unsteady separation phenomenon, and a wind R. E. KUHN IN: Recent advances in aerodynamics . New York, tunnel method for V/STOL testing. Also considered are vortex-edge Springer-Verlag, 1986, p. 337-373. refs interactions, jet instability theory, large-scale organized motions in The flow phenomena encountered in the hovering and jets and shear layers, and the evolution of adaptive-wall wind low-speed flight of jet- and fan-powered V/STOL and STO/VL tunnels. Other topics include advances in ejector thrust aircraft are examined, with attention to empirically based methods augmentation, multiple jet impingement flowfields, and recent for the estimation of aerodynamic characteristics. While the design advances in prediction methods for jet-induced effects on V/STOL principles required to minimize adverse effects and to take aircraft. R.R. advantage of favorable ones are well known, the current ability to make accurate estimates of many of the induced effects is limited. Expensive experimental programs are accordingly required at the A87-15452 outset of any aircraft development effort in order to obtain the ADVANCES IN THE UNDERSTANDING AND COMPUTATION OF accurate data required for design finalization. O.C. UNSTEADY TRANSONIC FLOW A. R. SEEBASS (Colorado, University, Boulder), K. Y. FUNG, and A87-15461' McDonnell Aircraft Co., St. Louis, Mo. S. M. PRZYBYTKOWSKI (Arizona, University, Tucson) IN: Recent MULTIPLE JET IMPINGEMENT FLOWFIELDS advances in aerodynamics . New York, Springer-Verlag, 1986, p. D. R. KOTANSKY (McDonnell Aircraft Co., Saint Louis, MO) IN: 3-37. refs Recent advances in aerodynamics . New York, Springer-Verlag, Numerical calculations of the effect of small unsteady motions 1986, p. 435-469. Research supported by McDonnell Aircraft Co. on unsteady transonic flows around airfoils are presented, and refs the effect of wind-tunnel walls on unsteady transonic flows whose (Contract N62269-76-C-0086; N62269-81-C-0717; NAS2-9646; steady state is free from interference is considered. It is NAS2-10184; NO0014-79-C-0130) demonstrated that the resonances of linear theory remain in the Attention is given to the prediction of lift-system-induced nonlinear flow and can cause substantial discrepancies between aerodynamic effects in lift-jet VTOL aircraft, considering both unbounded flow and the flow in the wind tunnel, even for tunnel analytical fluid-dynamics models and an empirical database. The heights in excess of five times the wingspan and 20 times its methodology takes into account the effects of aircraft geometry chord. The results suggest that wind tunnel walls be acoustically and orientation as well as height above ground, lift-jet vector and treated to further reduce wall reflections during unsteady testing. splay directions, jet exit-flow conditions, and nozzle exit geometry. R.R. O.C. A87-15462 RECENT ADVANCES IN PREDICTION METHODS FOR A87-15453 JET-INDUCED EFFECTS ON V/STOL AIRCRAFT UNSTEADY TRANSONIC AERODYNAMICS AND AEROELAS- R. K. AGARWAL (McDonnell Douglas Corp., Saint Louis, MO) TlClTY IN: Recent advances in aerodynamics . New York, Springer-Verlag, E. H. DOWELL (Duke University, Durham, NC) IN: Recent 1986, p. 471 -521. Research supported by the McDonnell Douglas advances in aerodynamics . New York, Springer-Verlag, 1986, p. Independent Research and Development Program. refs 39-98. refs This paper summarizes the currently used methodologies in (Contract AF-AFOSR-81-0213A) aircraft industry for predicting forces and moments on a V/STOL Aeroelastic applications of unsteady transonic aerodynamics aircraft in hover and transition modes of flight. These methodologies are considered. It is suggested that the aerodynamic forces will are based on a synthesis of various flow regions each of which be linear functions of the airfoil motion for sufficiently small airfoil accommodates a specific flow phenomena such as motions, which lead to sufficiently small shock motions, and that jet-ground-interactions, jet-in-crossflow, and fountain-airframe the field panel method of Hounjet (1981) is a viable alternative impingement. The progress made in recent years in theoretical solution technique to finite difference methods. Flutter analysis in modeling of the flowfield of representative jet-flow configurations: the frequency domain and simultaneous time integration of the single-jet impingement, twin-jet impingement with fountain fluid-dynamical and structural-dynamical equations of motion are formation, and jet-in-crossflow is surveyed. The prediction methods considered for determination of the aeroelastic response, and ranging from semiempirical approaches to the solution of methods for generating the frequency-domain aerodynamic forces Reynolds-averaged Navier-Stokes equations are discussed. are discussed. R.R. Author

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A87-15467' National Aeronautics and Space Administration. A87-15561 Ames Research Center, Moffett Field, Calif. DETERMINATION OF THE REGIME COEFFICIENTS IN THE LASER VELOCIMETRY FOR TRANSONIC AERODYNAMICS LOCAL THEORY OF INTERACTION FROM PLATE DATA D. A. JOHNSON (NASA, Ames Research Center, Moffett Field, [OPREDELENIE KOEFFITSIENTOV REZHIMA LOKAL'NOI CA) IN: Recent advances in aerodynamics . New York, TEORll VZAlMODElSTVllA PO DANNYM 0 PLASTINEI Springer-Verlag, 1986, p. 631 -655. refs I. 1. KHOLlABlN Leningradskii Universitet, Vestnik, Matematika, Applications of laser velocimetry to the measurement of Mekhanika, Astronomiia (ISSN 0024-0850), April 1986, p. 125-128. turbulent flow properties of strong transonic viscous-inviscid In Russian. refs interactions are reviewed. The data resulting from these studies Regime coefficients are calculated on the basis of the are then discussed in relation to their importance in the aerodynamic characteristics of the plate, with particular attention development of improved viscous-flow calculation methods. Also given to the effect of the Mach number on the regime coefficients considered are the current limitations of laser velocimetry, the at angles of attack of 20 deg or greater. The regime coefficients need for further improvements in the method, and potential future are determined as a function of the Knudsen number over a wide applications. Author range of Knudsen numbers with varying accuracy with respect to the Mach number. It is shown that satisfactory results are obtained even if no allowance is made for the Mach number. V.L.

A87-15468 THE AERODYNAMICS AND DYNAMICS OF ROTORS - A87-15761 PROBLEMS AND PERSPECTIVES COMPUTATION OF OPTIMUM-OPTIMORUM WING-FUSELAGE R. H. MILLER (MIT, Cambridge, MA) IN: Recent advances in CONFIGURATION FOR FUTURE GENERATION OF aerodynamics . New York, Springer-Verlag, 1986, p. 659-722. SUPERSONIC AIRCRAFT refs A. NASTASE (Aachen, Rheinisch-Westfaelische Technische Rotary wing aircraft blades trail intense tip vortices, generate a Hochschule, West Germany) IN: Integral methods in science curved, spiraling wake that initially remains close to a rotor and and engineering; Proceedings of the First International Conference causes strong blade/vortex interaction, are subject to a high on Global Techniques, Integral Methods in Science and centrifugal force field, and have large steady state displacements Engineering, Arlington, TX, March 18-21, 1985 . Washington, DC, out of the plane of rotation. The vibration reduction, blade stability Hemisphere Publishing Corp., 1986, p. 259-279. refs and hovering flight control problems thus posed are noted to Two computational methods for the design of optimum strongly depend on a precise, and as yet unaccomplisheddefinition optimorum integrated wing-fuselage configurations are presented: of blade aerodynamics; the dynamics of such rotor systems has, an analytical method and a hybrid graphic-analytical method. The however, been formulated to a high degree of precision, furnishing design of optimum optimorum integrated wing-fuselage valuable guidelines for design and for flight development. O.C. configuration using the graphic-analyticalmethod requires computer time of about 5 seconds on Cyber 175. Author

A87-15469' National Aeronautics and Space Administration. N87-11691 ESDU International Ltd., London (England). Ames Research Center, Moffett Field, Calif. PITOT AND STATIC ERRORS IN STEADY LEVEL FLIGHT SPECIAL OPPORTUNITIES IN HELICOPTER AERODYNAMICS Jut. 1986 42 p W. J. MCCROSKEY (NASA, Ames Research Center, Moffett Field, (ESDU-86006; ISBN-0-85679-558-5;ISSN-0141-4054) Avail: CA) IN: Recent advances in aerodynamics . New York. ESDU Springer-Verlag, 1986, p. 723-752. Previously announced in STAR This Data Item ESDU 86006 is an addition to the Aircraft as N84-16138. refs Performance Sub-series. All contributions to pressure errors and Aerodynamic research relating to modern helicopters includes the implications of the various tests needed to determine the errors the study of three dimensional, unsteady, nonlinear flow fields. A in steady level flight are considered. Typical magnitudes of the selective review is made of some of the phenomenon that hamper various contributions are tabulated for typical installations and, the development of satisfactory engineering prediction techniques, where appropriate, estimation methods are given for particular but which provides a rich source of research opportunities: flow effects for Mach numbers up to 4 at altitudes up to 120,000 ft separations, compressibility effects, complex vortical wakes, and (36,000 m). ESDU 85011 deals with corrections for nonsteady aerodynamic interference between components. Several examples flight and ESDU 83029 introduces the overall process of correcting of work in progress are given, including dynamic stall alleviation, for all error sources in flight-test analysis and, in particular, the the development of computational methods for transonic flow, need for a proper sequence of error correction. ESDU rotor-wake predictions, and blade-vortex interactions. Author

N87-11695'# Georgia Inst. of Tech., Atlanta. Center for Roatary Wing Aircraft Technology. A87-15553 SOME OBSERVATIONS ON THE BEHAVIOR OF THE LANGLEY SOME ASYMPTOTIC TYPES OF TRANSONIC VORTEX FLOWS MODEL ROTOR BLADE Semiannual Status Report [NEKOTORYE ASIMPTOTICHESKIE TlPY TRANSZVUKOVYKH L. W. REHFIELD and A. R. ATILGAN Jul. 1986 49 p VIKHREVYKH TECHENIII (Contract NAG1-638; PROJ. El6-668) A. G. KUZMIN Leningradskii Universitet, Vestnik, Matematika, (NASA-CR-179880; NAS 1.26179880) Avail: NTlS HC AOWMF Mekhanika, Astronomiia (ISSN 0024-0850), April 1986, p. 61-65. A01 CSCL01A In Russian. refs The design of the model rotor and the comparative study of Steady-state plane parallel vortex flows of an ideal gas are coupled beam theory and the finite element analysis performed investigated analytically. In particular, a study is made of the earlier at the Aerostructures Directorate by Robert Hodges and qualitative flow patterns in the vicinity of a point where the sonic Mark Nixon is examined. Attention is focused upon two matters: line is orthogonal with respect to the velocity vector and in the (1) an examination of the small discrepancies between twist angle vicinity of a point on the sonic line where acceleration is equal to predictions under pure torque and radial loading, and (2) an zero. Together with the results of Shifrin (1966), the results obtained assessment of nonclassical effects in bending behavior. The here provide information on all possible flow patterns near the primary objective is understanding, particularly with regard to cause point where the sonic line is orthogonal to the velocity vector and and effect relationships. Understanding, together with the simple, demonstrate a large variety of possible flow patterns near the affordable nature of the coupled beam analysis, provides a sound zero acceleration point. V.L. basis for design. Author

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N87-11699'# National Aeronautics and Space Administration. the pressure measurements. Clean airfoil data were found to Ames Research Center, Moffett Field, Calif. compare well to existing airfoil analysis methods. Author TIP VORTICES OF WINGS IN SUBSONIC AND TRANSONIC FLOW A NUMERICAL SIMULATION N87-11702'# National Aeronautics and Space Administration. G. R. SRINIVASAN (JAI Associates, Mountain View, Calif.) and Langley Research Center, Hampton, Va. W. J. MCCROSKEY Jut. 1986 7 p Original contains color FORWARD-SWEPT WING CONFIGURATION DESIGNED FOR illustrations HIGH MANEUVERABILITY BY USE OF A TRANSONIC (Contract DAAG29-85-C-0002) COMPUTATIONAL METHOD (NASA-TM-88334; A-8641 5; NAS 1.1 5188334; M. J. MANN and C. E. MERCER Nov. 1986 185 p USAAVSCOM-TM-86-A-4) Avail: NTlS HC A02/MF A01 CSCL (NASA-TP-2628; L-16120; NAS 1.60:2628) Avail: NTlS HC 01A AO9/MF A01 CSCL 01A Thin layer Navier-Stokes and Euler equations are numerically A transonic computational analysis method and a transonic solved using a multi-block zonal approach to simulate the formation design procedure have been used to design the wing and the and roll up of tip vortices of wings in subsonic and transonic canard of a forward-swept-wing fighter configuration for good flows. Several wing planforms were considered to examine the transonic maneuver performance. A model of this configuration influence of tip-cap shape, planform geometry and free stream was tested in the Langley 16-Foot Transonic Tunnel. Oil-flow Mach number on the formation process. A good definition of the photographs were obtained to examine the wind flow patterns at formation and qualitative roll up of tip vortices was achieved. Mach numbers from 0.60 to 0.90. The transonic theory gave a Author reasonably good estimate of the wing pressure distributions at transonic maneuver conditions. Comparison of the N87-11700"# Iowa State Univ. of Science and Technology, forward-swept-wing configuration with an equivalent Ames. College of Engineering. aft-swept-wing-configuration showed that, at a Mach number of APPLICATION OF VISCOUS-INVISCID INTERACTION 0.90 and a lift coefficient of 0.9, the two configurations have the METHODS TO TRANSONIC TURBULENT FLOWS Final Report same trimmed drag. The forward-swept wing configuration was D. LEE and R. H. PLETCHER Nov. 1986 292 p also found to have trimmed drag levels at transonic maneuver (Contract NAG2-152) conditions which are comparable to those of the HiMAT (highly (NASA-CR-179900; NAS 1.26:179900; HTL-42; CFD-16; maneuverable aircraft technology) configuration and the X-29 ISU-ERI-AMES-87055) Avail: NTlS HC A13/MF A01 CSCL forward-swept-wing research configuration. The configuration of 01 A this study was also tested with a forebody strake. Author Two different viscous-inviscid interaction schemes were developed for the analysis of steady, turbulent, transonic, separated N87-11704# Max-Planck-lnstitut fuer Stroemungsforschung, flows over axisymmetric bodies. The viscous and inviscid solutions Goettingen (West Germany). are coupled through the displacement concept using a transpiration VORTEX SHEDDING OF A SQUARE CYLINDER IN FRONT OF velocity approach. In the semi-inverse interaction scheme, the A SLENDER AIRFOIL AT HIGH REYNOLDS NUMBERS. PART viscous and inviscid equations are solved in an explicitly separate 2 COMPRESSIBILITY EFFECT manner and the displacement thickness distribution is iteratively T. NAKAGAWA, G. E. A. MEIER, R. TIMM, and H. M. LENT updated by a simple coupling algorithm. In the simultaneous Oct. 1985 33 p Sponsored by Minna-James-Heinemann interaction method, local solutions of viscous and inviscid equations Foundation, Hannover, West Germany are treated simultaneously, and the displacement thickness is (MPIS-24/1985; ISSN-0436-1199; ETN-86-98222) Avail: NTlS treated as an unknown and is obtained as a part of the solution HC AOS/MF A01 ; Fachinformationszentrum, Karlsruhe, West through a global iteration procedure. The inviscid flow region is Germany DM 28 described by a direct finite-difference solution of a velocity potential The compressibility effect on vortex shedding behind a square equation in conservative form. The potential equation is solved on cylinder in front of a NACA 0018 airfoil was visualized. The mean a numerically generated mesh by an approximate factorization pressure decreases with increasing Mach number (or Reynolds (AF2) scheme in the semi-inverse interaction method and by a number). There is a tendency for the amplitude of the pressure successive line overrelaxation (SLOR) scheme in the simultaneous fluctuations and the fundamental frequency (or vortex shedding interaction method. The boundary-layer equations are used for frequency) to increase with increasing Mach number (or Reynolds the viscous flow region. The continuity and momentum equations number) except in the very high subsonic Mach number range. are solved inversely in a coupled manner using a fully implicit When the spacing between the square cylinder and the airfoil is finite-difference scheme. Author fixed, the Strouhal number behind the square cylinder is kept at an almost constant value up to M=0.63. If the Mach number N87-11701"# Ohio State Univ., Columbus. Dept. of Aero- and exceeds a critical value the Strouhal number either decreases or Astro-Engineering. increases suddenly. With increasing Mach number (or Reynolds AN EXPERIMENTAL STUDY OF THE AERODYNAMICS OF A number), the formation region behind the square cylinder becomes NACA 0012 AIRFOIL WITH A SIMULATED GLAZE ICE smaller and more asymmetric, and the separating shear layers ACCRETION Interim Technical Report become more corrugated. ESA M. B. BRAGG Nov. 1986 318 p (Contract NAG3-28; RF PROJ. 712620/762009) N87-11738'# National Aeronautics and Space Administration. (NASA-CR-179897; NAS 1.26:179897) Avail: NTlS HC A14/MF Langley Research Center, Hampton, Va. A01 CSCL01A CALCULATED EFFECTS OF VARYING REYNOLDS NUMBER An experimental study was conducted in the Ohio State AND DYNAMIC PRESSURE ON FLEXIBLE WINGS AT University subsonic wind tunnel to measure the detailed TRANSONIC SPEEDS aerodynamic characteristics of an airfoil with a simulated glaze R. L. CAMPBELL In its Recent Experiences in Multidisciplinary ice accretion. A NACA 0012 model with interchangeable leading Analysis and Optimization, Part 1 (date] 19 p 1984 edges and pressure taps every one percent chord was used. Avail: NTlS HC A22/MF A01 CSCL 01A Surface pressure and wake data were taken on the airfoil clean, A computational method is described that includes the effects with forced transition and with a simulated glaze ice shape. Lift of static aeroelastic wing deflections in steady transonic and drag penalties due to the ice shape were found and the aerodynamic calculations. This method, known as the Transonic surface pressure clearly showed that large separation bubbles were Aero-elastic Program System (TAPS), interacts a 3D transonic Present. Both total pressure and split-film probes were used to computer code with boundary layer and a linear finite element measure velocity profiles, both for the clean model and for the structural analysis codes to calculate wing pressures and model with a simulated ice accretion. A large region of flow deflections. The nonlinear nature of the transonic flow makes it separation was seen in the velocity profiles and was correlated to necessary to couple the aerodynamic and structures codes in an

75 02 AERODYNAMICS iterative manner. TAPS has been arranged in a modular fashion contoured bodies with a tractor propeller at or near the nose or a so that different aerodynamic or structures programs may be used pusher propeller at or near the tail and the propellers may be with a minimum of coding changes required. Results obtained counter-rotating. It applies to Mach numbers up to 80 per cent of using two different aerodynamic codes in TAPS are given, and critical for the spinner-body combination. The method predicts the those results are correlated with experimental data. Author propulsive thrust in terms of the shaft thrust developed to within 2 or 3 per cent of thrust. A detailed discussion of the factors N87-12535 Texas Univ., Austin. affecting the interaction effects is included. A comprehensive VISCOUSINVISCID INTERACTION IN TRANSONIC worked example shows how the method is used in combination SEPARATED FLOW OVER SOLID AND POROUS AIRFOILS AND with the method of ESDU 83001 for the propeller free-air thrust CASCADES Ph.D. Thesis and of ESDU 78019 for the body drag propeller-off. ESDU C. R. OLLING 1985 185 p Avail: Univ. Microfilms Order No. DA8609621 Viscous-inviscid interaction is used to compute steady two-dimensional, transonic separated flows for cascades and N87-12538*# National Aeronautics and Space Administration. isolated airfoils. The full-potential code of Dulikravich is coupled Langley Research Center, Hampton, Va. with both a laminar/transition/turbulent integral MACH 6 EXPERIMENTAL AND THEORETICAL STABILITY AND boundary-layer/tubulent wake code written by the author and the PERFORMANCE OF A FINNED CYLINDRICAL BODY AT finite-difference boundaty-layer code of Drela using the ANGLES OF ATTACK UP TO 65 DEG semi-inverse method of Carter or Wigton. The transpiration coupling E. R. HARTMAN and P. J. JOHNSTON Sep. 1986 45 p concept is applied. An option for a porous airfoil with passive (NASA-TM-89050; NAS 1.15:89050) Avail: NTlS HC AO3IMF physical transpiration is also included. Examples are presented A01 CSCL01A which demonstrate that such flows can be calculated with A theoretical and experimental investigation of the longitudinal engineering accuracy by the present code. The equivalent and lateral-directional stability and control of a finned cylindrical transpiration velocity can be larger in cascades than for isolated body has been conducted at Mach 6. The angle-of-attack range airfoils. Carter's update formula gives smoother solutions for a extended from 20 to 65 deg. to encompass maximum lift. Stability, strong shock than Wigton's update formulas, although Wigton's performance, and trim could be accurately predicted with the fins formulas are preferred in the early coupling cycles for cascades. in the + arrangement but this was not the case when the fins The computations show that passive physical transpiration can were in the x orientation where windward fin choking occurred at lead to a lower drag coefficient and higher lift coefficient, a weaker angles of attack above 50 deg. reducing their effectiveness and shock and elimination of shock-induced separation. The extent of causing pitch up. Author the porous region and permeability factor distribution of the porous region must be chosen carefully if these improvements are to be achieved. Dissert. Abstr.

N87-12536 ESDU International Ltd., London (England). N87-12539'# National Aeronautics and Space Administration. INTRODUCTION TO AERODYNAMICS DERIVITIVES, Ames Research Center, Moffett Field, Calif. EQUATIONS OF MOTION AND STABILITY AN EXPERIMENTAL INVESTIGATION OF FREE-TIP RESPONSE Oct. 1986 64 p Supersedes ESDU-Aero-A.00.00.02, TO A JET ESDU-Aero-A.00.00.03, ESDU-Aero-A.00.00.04. and ESDU-67039 L. A. YOUNG Sep. 1986 56 p (ESDU-86021; ISBN-0-85679-573-9; ISSN-0141-397X) Avail: (NASA-TM-88250; A-86234; NAS 1.1588250) Avail: NTlS HC ESDU A04/MF A01 CSCL 01A This Data Item ESDU 86021 is an addition to the Aerodynamics The aerodynamic response of passively oscillating tips Sub-series. It is a comprehensive introduction to the concept and appended to a model helicopter rotor was investigated during a use of derivatives in determining aircraft stability. After explaining whirl test. Tip responsiveness was found to meet free-tip rotor a systematic method for expressing aerodynamic forces, moments, requirements. Experimental and analytical estimates of the free-tip and derivatives in dimensionless form, the equations of motion for aerodynamic spring, mechanical spring, and aerodynamic damping an aircraft treated as a rigid body are developed and the linearized were calculated and compared. The free tips were analytically small-perturbation form introduced. The conditions are outlined for demonstrated to be operating outside the tip resonant response the separation of the equations into a lateral and a longitudinal region at full-scale tip speeds. Further, tip resonance was shown set, and a detailed study is made of the behavior of an aircraft to be independent of tip speed, given the assumption that the tip disturbed with controls fixed from straight symmetric level flight. A forcing frequency is linearly dependent upon the rotor rotational comprehensive practical worked example illustrates the use of speed. Author the techniques. A comparison is made between the IS0 notation for derivatives used by ESDU, and the most widely used notation in the US, equations are given for deriving the longitudinal derivatives from the force and moment coefficients, and reference N87-12540# Royal Aircraft Establishment, Farnborough is included to all the ESDU validated data for lateral derivatives. (England). Also included is the traditional treatment for static stability leading AN APPROXIMATE METHOD OF ESTIMATING THE to the definitions of static and maneuver margins, and the relation AERODYNAMIC INTERFERENCE BETWEEN TWO PARALLEL between static stability and dynamic stability is discussed. Finally, BODIES IN A SUPERSONIC FLOW (AXIAL FORCE) a description is given in simple physical terms of commonly H. KONDO Mar. 1985 28 p Transl. into ENGLISH from occurring lateral modes of an aircraft following a small Technical Report of National Aerospace Laboratory, TR-751, disturbance. ESDU 1983 (BR-100271; RAE-TRANS-2131) Avail: NTlS HC AO3/MF A01 N87-12537 ESDU International Ltd.. London (England). An approximate method of estimating the aerodynamic PROPELLAR/BODY INTERACTION FOR THRUST AND DRAG interference between two parallel bodies in a supersonic flow is Aug. 1986 20 p discussed. The formulae are derived from linearized theory. The (ESDU-86017; ISBN-0-85679-569-0; ISSN-0141-397X) Avail: formulae for calculating the wave drag on one body are obtained ESDU as functions of Mach number, cone semi-vertex angle, and the Available as part of the ESDU Sub-series on Aerodynamics, relative distances between bodies. Theoretical calculations are this document gives a simple method of estimating the thrust compared with wind tunnel test results, and fairly good agreement decrement and drag increment due to the interaction of propeller is noted. It is pointed out that the present method can easily be flow with a body (or nacelle) at zero incidence. It applies to smoothly applied to a combination of more than two bodies. Author

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N87-12541’# National Aeronautics and Space Administration. N87-12544# JAI Associates, Mountain View, Calif. Langley Research Center, Hampton, Va. NUMERICAL SIMULATION OF TIP VORTICES OF WINGS IN EFFECT OF PORT CORNER GEOMETRY ON THE INTERNAL SUBSONIC AND TRANSONIC FLOWS PERFORMANCE OF A ROTATING-VANE-TYPE THRUST G. R. SRINIVASAN, W. J. MCCROSKEY, J. D. BAEDER, and T. REVERSER A. EDWARDS 1986 26 p B. L. BERRIER and F. J. CAPONE Dec. 1986 51 p (Contract DAAG29-85-C-0002) (NASA-TP-2624; L-16135; NAS 1.60:2624) Avail: NTlS HC (AD-A169116; ARO-21731.1-EG) Avail: NTlS HC A03/MF A01 A04/MF A01 CSCL 01A CSCL 20D An investigation has been conducted in the static-test facility The formation and roll up process of the tip vortices of wings of the Langley 16-Foot Transonic Tunnel to determine the effects in subsonic and transonic flows is numerically simulates using a of reverser port geometry on the internal performance of a hybrid scheme of solving a zonal algorithm for thin layer Navier nonaxisymmetric rotating-vane-typethrust reverser. Thrust reverser Stokes/Euler equations. The results are in good agreement with vane positions representing a spoiled-trust (partially deployed) the available limited experimental data including the tip vortex position and a full-reverse-thrust (fully deployed) position were strength. GRA tested with each port geometry variable. The effects of upstream port corner radius and wall angle on internal performance were determined. In addition, the effect of the length of a simulated N87-12545# Analytical Methods, Inc., Redmond, Wash. cooling liner (blunt-base step) near the reverser port entrance A SUMMARY OF THE DEVELOPMENT OF INTEGRAL was investigated; five different lengths were tested. All tests were AERODYNAMIC METHODS FOR THE COMPUTATION OF conducted with no external flows, and nozzle pressure ratio was ROTOR WAKE INTERACTIONS Final Report, 1 Aug. 1981 - 30 varied from 1.2 to 5.0. Author Aug. 1984 J. M. SUMMA Mar. 1986 13 p (Contract DAAG29-81-C-0032) (AD-A169254; AMI-8605; ARO-18391.3-EG-S) Avail: NTlS HC AO2/MF A01 CSCL 20D The purpose of the research reported here is to develop basic methodology for a generalized forward flight aerodynamic analysis N87-12542’# Queensland Univ., St. Lucia (Australia). Dept. of method for isolated rotors. All of the work thus far has been Mechanical Engineering. concerned with the development of integral methods. Efforts have FURTHER SHOCK TUNNEL STUDIES OF SCRAMJET concentrated on analytical modeling studies and code development PHENOMENA for fundamental vortex/blade interactions that occur in forward R. G. MORGAN, A. PAULL, N. A. MORRIS, and R. J. STALKER flight. Calculations show that vortex core deformations can be 12 May 1986 112 p simulated but that numerical errors in the core growth should be (Contract NAGW-674) removed in order to study such phenomena as bursting. The (NASA-CR-179937; NAS 1.26179937; RR-10-86) Avail: NTlS computed trajectory of a tip vortex passing another wing is also HC AO6/MF A01 CSCL 01A validated with experiment as well as the prediction of vortex induced Scramjet phenomena were studied using the shock tunnel T3 separations. The calculation of the rotor wake in hover has been at the Australian National University. Simple two dimensional improved and the importance of secondary vortex roll ups for a models were used with a combination of wall and central injectors. modern rotor is discussed. Finally, a time stepping panel method Silane as an additive to hydrogen fuel was studied over a range has been formulated and verified by application to impulsively of temperatures and pressures to evaluate its effect as an ignition started wings. A pilot code version for unsteady rotor motions is aid. The film cooling effect of surface injected hydrogen was described along with its preliminary application to a two bladed measured over a wide range of equivalence. Heat transfer rotor. GRA measurements without injection were repeated to confirm previous indications of heating rates lower than simple flat plate predictions for laminar boundary layers in equilibrium flow. The previous results N87-12547 Stanford Univ., Calif. were reproduced and the discrepancies are discussed in terms of AN ANALYSIS OF BLADE VORTEX INTERACTION the model geometry and departures of the flow from equilibrium. AERODYNAMICS AND ACOUSTICS Ph.D. Thesis In the thrust producing mode, attempts were made to increase D. J. LEE 1985 176p specific impulse with wall injection. Some preliminary tests were Avail: Univ. Microfilms Order No. DA8602500 also performed on shock induced ignition, to investigate the The impulsive noise associated with helicopter flight due to possibility in flight of injecting fuel upstream of the combustion blade-vortex interaction, sometimes called blade slap, is analyzed chamber, where it could mix but not burn. B.G. especially for the case of a close encounter of the blade-tip vortex with a following blade. Three parts of the phenomena are considered: the tip-vortex structure generated by the rotating blade, the unsteady pressure produced on the following blade during the interaction, and the acoustic radiation due to the unsteady pressure field. To simplify the problem, we confine our analysis to the N87-12543# Department of the Air Force, Washington, D.C. situation where the vortex is aligned parallel to the blade span in LENGTH ADJUSTABLE STRUT LINK WITH LOW which case the maximum acoustic pressure results. The AERODYNAMIC DRAG Patent 2-dimensional incompressible flow is assumed with uniform motion D. 0. NASH and J. A. CROWLEY, inventors (to Air Force) 25 of the blade. The tip-vortex is modelled so that the circulation Feb. 1986 8 p Supersedes AD-DO1 1851 near the tip is rolled into a concentrated vortex and the extreme (AD-DO12279; US-PATENT-4,571,936; case of the interaction is studied when the following blade cuts US-PATENT-APPL-SN-753462; US-PATENT-CLASS-60-39.31) through the center of this vortex core, which is turbulent and Avail: US Patent and Trademark Office CSCL 13E viscous. It is further assumed that during the interaction, there is This invention relates to a low aerodynamic drag structural link no distortion of the vortex path or of the vortex itself, in other suitable for use within the housing of a turbofan jet engine. The words the interaction occurs only through the boundary condition link includes length adjustment capability, pivotal end mounting on the blade giving an unsteady pressure on the blade surface. provision, maintained airstream orientation capability, low mass Acoustic radiation due to the interaction is analyzed in space-fixed and jam nut length and orientation locking. Several variations in coordinates and in the time domain with the unsteady pressure link construction including a single ball and socket arrangement, on the blade surface as the source of chordwise compact, but varying link cross-section along its longitudinal length and the use spanwise noncompact radiation. Maximum acoustic pressure is of fairing nose and tail inserts are disclosed. GRA related to the vortex core size and Reynolds number which are in

77 03 AIR TRANSPORTATION AND SAFETY turn functions of the blade-tip aerodynamic parameters. Finally and landing are identified as the most hazardous flight phases, noise reduction and performance are considered. Dissert. Abstr. and pleasure flying is shown to be the most significant contributer to general aviation accidents. M.S.K.

03 A87-13627 AIRWORTHINESS OF COMPOSITE STRUCTURES - SOME AIR TRANSPORTATION AND SAFETY EXPERIENCES FROM CIVIL CERTIFICATION J. W. BRISTOW (Civil Aviation Authority, Redhill, England) IN: Fibre reinforced composites 1986; Proceedings of the Second Includes passenger and cargo air transport operations; and aircraft International Conference, Liverpool, England, April 8-10, 1986 . accidents. London, Mechanical Engineering Publications, Ltd., 1986, p. 147-152. refs In this paper details are given of the guidance material used A8743186 in the application of airworthiness requirementsto primary structure FIRE SAFETY SCIENCE PROCEEDINGS OF THE FIRST in composite material in recent years. Some experience gained INTERNATIONAL SYMPOSIUM, GAITHERSBURG, MD, from the application of these requirements from the viewpoint of OCTOBER 7-11, 1985 an airworthiness authority is also presented. Author C. E. GRANT, ED. and P. J. PAGNI, ED. (California, University, Berkeley) Symposium supported by the University of California. Washington, DC, Hemisphere Publishing Corp., 1986. 1241 p. For A87-13684 individual items see A87-13187 to A87-13189. REALISTIC CIVIL HELICOPTER CRASH SAFETY A symposium of papers discussing various aspects of fire R. G. FOX (Bell Helicopter Textron, Fort Worth, TX) IN: National research and their application to solving problems posed by Specialist’s Meeting on Crashworthy Design of Rotorcraft, Atlanta, destructive fire is presented. The invited lecture concerns fluid GA. April 7-9, 1986. Proceedings . Alexandria, VA. American dynamic aspects of room fires. The rest of the papers are grouped Helicopter Society, 1986, 14 p. refs into ten technical topics, including: fire physics; structural behavior; Realistic crashworthiness criteria established by the Rotorcraft fire chemistry; people-fire interactions; translation of research into Airworthiness Requirement Committee of AIA for the seats, practice; detection; specialized fire problems; statistics, risk, and restraints, and fuel systems of future civil helicopters are discussed. system analysis; smoke toxicity hazard; and suppression. C.D. Energy attenuating seats with shoulder harnesses and the Crash Resistant Fuel System are recommended as future requirements, A87-13187 which should be introduced into the initial design concept to TURBULENT BUOYANT FLOW AND PRESSURE VARIATIONS minimize the weight increase.Furthermore. these requirements must AROUND AN AIRCRAFT FUSELAGE IN A CROSS WIND NEAR be realistic for the civil helicopter crash environment and not suffer THE GROUND the severe weight penalties of military requirements. IS. H. S. KOU, K. T. YANG (Notre Dame, University, IN), and J. R. LLOYD (Michigan State University, East Lansing, MI) IN: Fire safety science; Proceedings of the First International Symposium, A87-13685 Gaithersburg. MD, October 7-11, 1985 . Washington, DC. ANALYSIS OF U.S. CIVIL ROTORCRAFT ACCIDENTS FOR Hemisphere Publishing Corp.. 1986, p. 173-184. FAA-supported DEVELOPMENT OF IMPROVED DESIGN CRITERIA research. refs J. W. COLTMAN (Simula, Inc., Phoenix, AZ) and L. M. NERl (FAA (Contract NBS-NB-81-NADA-2000) Technical Center, Atlantic City, NJ) IN: National Specialist’s Two-dimensional numerical finite-difference calculations have Meeting on Crashworthy Design of Rotorcraft, Atlanta, GA, April been carried out to study the effects of cross wind speeds and 7-9, 1986, Proceedings . Alexandria, VA, American Helicopter the elevation of the fuselage on turbulent buoyant flow and pressure Society, 1986, 8 p. refs variations around an aircraft fuselage engulfed in a simulated fire A review was conducted of US. civil helicopter accidents in a uniform cross wind near the ground. Detailed velocity, occurring between 1974 and 1978 to determine typical impact temperature, smoke concentration, and pressure fields have been conditions. A total of 311 accident cases were evaluated out of obtained and it is found that a major influence on the physical 1351 accidents which occurred during the five year period. Accident phenomena is the relative strength of the cross flow and the reconstruction techniques were used to determine the impact buoyant flow. Author velocities and aircraft orientation at impact. This paper presents a summary of the important impact parameters and discusses six A87-13578 typical ’crash scenarios’ for civil rotorcraft. Also, a comparison is AIRCRAFT ACCIDENT INVESTIGATION made between the severity of injuries received by occupants with R. R. MCMEEKIN (U.S. Armed Forces Institute of Pathology, lap-belt only restraint, and those wearing a lap belt and shoulder Washington, DC) IN: Fundamentals of aerospace medicine . harness. The data developed in this study provides a basis for Philadelphia, PA, Lea and Febiger, 1985, p. 762-814. refs formulating design criteria for future civil rotorcraft. Author Aircraft accident investigations are described, emphasizing post-mortem examinations and administrative planning. The NTSB has the authority to perform autopsies on all victims of civil aircrat A87-13686 accidents. Attention is given to community and municipality planning ACQUISITION AND USE OF DATA FOR CRASHWORTHINESS for disasters and the necessity of drills for identifying weak areas IMPROVEMENTS IN U.S. ARMY AIRCRAFT in planning. M.S.K. B. H. ADAMS (US. Army Safety Center, Fort Rucker, AL) IN: National Specialist’s Meeting on Crashworthy Design of Rotorcraft, A87-13581 Atlanta, GA, April 7-9, 1986, Proceedings . Alexandria, VA, AIRCRAFT ACCIDENTS, SURVIVAL, AND RESCUE American Helicopter Society, 1986, 9 p. refs R. L. DEHART (Industrial Medicine Employer’s Service of Mishap data continue to serve as one of the principal Oklahoma, Inc.; Hillcrest Occupational Medicine Services, Tulsa; foundations for the establishment of crashworthiness criteria for Oklahoma, University, Norman) and K. N. BEERS (Wright State U.S. Army aircraft. This paper reviews the Army process for University, Dayton, OH) IN: Fundamentals of aerospace medicine gathering the data and discusses its use in demonstrating the . Philadelphia, PA, Lea and Febiger, 1985. p. 862-887. refs cost effectiveness of crashworthiness enhancements for future The database on air accidents is reviewed, with emphasis on Army aircraft. This paper discusses the need for the data to support survivability and the chances for rescue. The discussion covers management decisions in the area of remedying crashworthiness civil transport, general aviation and military aircraft crashes. Takeoff deficiencies in existing aircraft systems. Author

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A87-13687 A87-13794# IMPACT SEVERITY AND POTENTIAL INJURY PREVENTION IN AVERAGE LANDING FORCE DEPENDENCE ON LENGTH AND GENERAL AVIATION ACCIDENTS DIRECTION OF LANDING, PARACHUTE VELOCITY F. A. SHERERTZ (National Transportation Safety Board, COMPONENTS AND WIND SPEED Washington, DC) IN: National Specialist's Meeting on Crashworthy J. MEYER (Arizona, University, Tucson) IN: Aerodynamic Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . Decelerator and Balloon Technology Conference, 9th, Albuquerque, Alexandria, VA, American Helicopter Society, 1986, 9 p. NM, October 7-9, 1986, Technical Papers . New York, American The National Transportation Safety Board examined 535 general Institute of Aeronautics and Astronautics, 1986. p. 127-131. aviation accidents in order to determine the limits of real-world (AIAA PAPER 86-2452) survivable crash loads and to determine the potential benefits of Average landing forces were calculated in the present paper occupant restraints and energy-absorbing seats in survivable by applying work-kinetic energy principles to a pilot landing under accidents. The data developed suggest that the survivable envelope a parachute on solid level ground. The landing event started when is defined by impact speeds of 45 knots at 90 degrees of impact the pilot's feet first touched the ground and stopped when the angle, 60 knots at 45 degrees, and 75 knots at zero degrees. pilot came to rest on the ground. The dragging of a pilot by a Data are presented which demonstrate that if all occupants wore wind-inflated parachute was not considered. Parachute velocity shoulder harnesses, fatalities could be expected to be reduced by components, landing direction and distance, and wind speed were 20 percent. Author varied to determine their effects on average landing forces. Results, in the form of average net force contour plots, were used to find optimal parachute velocity components for a sample scenario. The A87-13776 AERODYNAMIC DECELERATOR AND BALLOON contour plots showed that an optimal ground speed exists for each descent rate, longer landing distances lowered landing forces, TECHNOLOGY CONFERENCE, 9TH, ALBUQUERQUE, NM, landing along the parachute's glide path minimized landing forces OCTOBER 7-9, 1986, TECHNICAL PAPERS and slightly off heading landings increase the landing forces by a Conference sponsored by AIAA. New York, American Institute of Aeronautics and Astronautics, 1986, 338 p. For individual items small amount. Author see A87-13777 to A87-13818. The present conference discusses such topics a flight risk index, balloon flight mechanics in homothermic and nonhomothermic conditions, parachute design for supersonic and subsonic payload recovery, NASA wind-tunnel testing of supersonic ribbon parachutes, and the prediction of decelerator behavior with CFD. Also considered are the controlled terminal descent and recovery of large aerospace components, the degradation of nylon and A87-13806# Kevlar materials, a computer design code for conical ribbon LOW COST AERIAL TESTING OF PARACHUTES parachutes, and a two-stage parachute system for the delivery of J. V. HOGAN (Irvin Industries Canada, Ltd., Fort Erie, Canada) troops from high speed aircraft. O.C. IN: Aerodynamic Decelerator and Balloon Technology Conference, 9th, Albuquerque, NM, October 7-9, 1986, Technical Papers . New York, American Institute of Aeronautics and Astronautics, 1986, p. A87-13777# 21 7-221. TECHNICAL-HISTORICAL DEVELOPMENT OF PARACHUTES (AIAA PAPER 86-2472) AND THEIR APPLICATIONS SINCE WORLD WAR I The methods used by lrvin Canada for instrumented aerial T. W. KNACKE IN: Aerodynamic Decelerator and Balloon testing of parachutes are described. It has been found that through Technology Conference, 9th, Albuquerque, NM, October 7-9, 1986, the use of a digital data logger onboard a simple air launched Technical Papers . New York, American Institute of Aeronautics C.T.V. (Cylindrical Test Vehicle), sustained testing at the notably and Astronautics, 1986, p. 1-10. refs low labor level of 10 man-hours per drop is attainable. A live (AIAA PAPER 86-2423) jump installation of virtually the Same equipment yields similar data A development history is presented for parachute designs and collection economy. Typical results from both C.T.V. and live jump applications, with attention to several highly specialized parachute tests are provided. Author types. Also noted are effects on parachute development due to the requirement of ejection-seat escape systems aboard high-speed aircraft and to the need for recovery of spacecraft after reentry. Parachute types treated include ribbon parachutes, extended skirt parachutes, airfoil/annular parachutes, ram air-inflated 'ballute' decelerators, ringsail parachutes, parafoil maneuverable parachutes, and Rogallo wing maneuverable parachutes. O.C. A87-13809# A87-13784# PERFORMANCE PREDICTION FOR FULLY-DEPLOYED AUTOMATIC VARIABLE REEFING OF PARACHUTES BY PARACHUTE CANOPIES APPLICATION OF INFLATION FORCES T. YAVUZ (Erciyes University, Kayseri, Turkey) IN: Aerodynamic D. B. WEBB (Irvin Industries Canada, Ltd., Fort Erie, Canada) Decelerator and Balloon Technology Conference, 9th, Albuquerque, IN: Aerodynamic Decelerator and Balloon Technology Conference, NM, October 7-9, 1986, Technical Papers . New York, American 9th, Albuquerque, NM, October 7-9, 1986, Technical Papers. New Institute of Aeronautics and Astronautics, 1986, p. 231-238. refs York, American Institute of Aeronautics and Astronautics, 1986, p. (AIAA PAPER 86-2475) 44-48. In this paper, introducing experimentally determined apparent (AIAA PAPER 86-2434) mass terms into the equations of motion the performance The automatic inflation modulation concepts presented for characteristics of a descending parachute-store system have been automatic parachute reefing employ a small, Webb-type auxiliary determined to resemble those observed, so as to give an parachute inside the mouth of the main parachute canopy to exert appropriate basis for performance prediction. Using phase lag a controlled, circular opening force on the main canopy mouth. instead of the variable apparent mass terms in the equations, the The reefing action of the main parachute is obtained by using the dynamic stability of the system has also been analysed. It was force generated at its crown to restrain the main canopy lines. found that, for a parachute which has high value of d(C) sub This restraining force diminishes as the dynamic pressure in the N/d(alpha) about the equilibrium angle, the influences of the canopy crown decays, so that the canopy can inflate slowly to its apparent masses and the phase lag on the performance fully open state. O.C. characteristics of the system are not significant. Author

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A87-13815# conditions and scale lengths during a microburst, when turbulence A COMPARISON OF MEASURED AND CALCULATED STRESS is nonhomogeneous. M.S.K. IN SOLID AND RIBBON PARACHUTE CANOPIES W. L. GARRARD, M. L. KONICKE. and K. S. WU (Minnesota, A87-14620 University, Minneapolis) IN: Aerodynamic Decelerator and Balloon NOW HEAR THIS Technology Conference, 9th, Albuquerque, NM, October 7-9, 1986, H. HOPKINS Flight International (ISSN 0015-3710). VOI.130, Technical Papers . New York, American Institute of Aeronautics Aug. 23, 1986, P. 26-28. and Astronautics, 1986, p. 299-309. Research supported by Sandia The need for distinctive warning sounds which are matched to National Laboratories. refs the level of cockpit noise is discussed. The problems of warning (AIAA PAPER 86-2488) loudness and of having numerous auditory warnings were studied. This paper reports the results of a study of measured and It is determined that pilots can quickly learn between four to six calculated stress distributions in solid, ribbon, and simulated different sounds and confusion occurs between different sounds ring-slot parachutes. Stress measurements were accomplished with similar repetition rates. The development and testing of warning using Omega sensors and the stresses were calculated using a sets for civil and military helicopters are examined. The use of finite element stress analysis code called CANO. In the case of auditory signals composed of bursts to warn of problems is the ribbon parachute the inflated shape was measured and described. I.F. compared with the shape predicted using CANO. Author A87-14861# A87-138 18# GROUND-BASED DETECTION OF AIRCRAFT ICING DESIGN AND DEVELOPMENT OF A TWO-STAGE PARACHUTE CONDITIONS USING MICROWAVE RADIOMETERS SYSTEM FOR DELIVERY OF TROOPS FROM A HIGH-SPEED I. A. POPA FOTINO, M. T. DECKER (Cooperative Institute for AIRCRAFT Research in Environmental Sciences, Boulder, CO), and J. A. J. W. WATKINS (US. Army, Natick Research, Development and SCHROEDER (NOOA, Wave Propagation Laboratory, Boulder, Engineering Center, MA) IN: Aerodynamic Decelerator and Balloon CO) (1 985 International Geoscience and Remote Sensing Technology Conference, 9th. Albuquerque, NM, October 7-9, 1986, Symposium 1IGARSS '851, Amherst, MA, Oct. 7-9, 1985) IEEE Technical Papers . New York, American Institute of Aeronautics Transactions on Geoscience and Remote Sensing (ISSN and Astronautics, 1986, p. 327-334. 0196-2892), vol. GE-24, Nov. 1986, p. 975-982. refs (AIAA PAPER 86-2448) (Contract DOT-FA01-84-2-02021 ) A two-stage parachute system has been designed to meet The potential role of ground-based remote sensors in the US. Army requirements for the parachute dropping of small groups detection of atmospheric conditions conducive to aircraft icing is of special troops behind enemy lines in a high-threat environment, evaluated. Zenith measurements of liquid water and profiles of from aircraft that approach the drop zone at high speed and low atmospheric temperature were made by microwave radiometers altitude. In the first system stage, a small drogue parachute located at Stapleton International Airport, Denver, CO. Radiometer decelerates and stabilizes the jumper. A time-delay pyrotechnic data and sky cover observations for a two-year period were cutter then initiates deployment of the second stage, or main correlated with icing occurrences reported by aircraft pilots in the recovery parachute. Extremely high reliability is made a critical area. Given certain limitations, it is concluded that the liquid consideration by the preclusion of a reserve parachute in this measurement makes a critical contribution to the detection of icing system's requirements; it must also not generate forces that could conditions. This measurement is not generally available (e.g., from injure a jumper. Attention is presently given to first stage parachute radiosondes), except from sensors like the radiometer. Author and staging component modifications conducted on the basis of initial test results. The modified system has successfully completed A87-15001 preliminary testing. O.C. INTERNATIONAL AEROSPACE AND GROUND CONFERENCE ON LIGHTNING AND STATIC ELECTRICITY, 1lTH, DAYTON, A87-13823# OH, JUNE 24-26, 1986, TECHNICAL PAPERS THE ANNULAR PARACHUTE - AN APPROACH TO A LOW Conference sponsored by the National Interagency Coordination ALTITUDE PERSONNEL PARACHUTE Group. Fairborn, OH, National Interagency Coordination Group, E. J. FALLON, J. WATKINS (US. Army, Natick Research, 1986, 390 p. For individual items see A87-15002 to A87-15041. Development and Engineering Center, MA), and E. D. VICKERY The present conference on the status of research activities, (Pioneer Parachute Co., Manchester, CT) AIAA, Aerodynamic theoretical characterizations, and practical measures related to Decelerator and Balloon Technology Conference, 9th, Albuquerque, atmospheric electricity effects on aerospace systems gives NM, Oct. 7-9. 1986. 18 p. refs attention to the prediction of temperature rises in conductors (AIM PAPER 86-2449) carrying impulse currents, results from NASA's storm hazards This paper discusses the use of the Annular Parachute for a lightning research in 1980-1985, a threat-level lightning simulator, low altitude personnel parachute. The discussion includes a lightning strikes to German military aircraft, and EM measurements historical narrative as well as current research on the Annular on an aircraft from direct lightning attachment. Also discussed are Parachute. Based upon the historical narrative and flight tests at a comparison between aircraft lightning-induced transient test data this time, the Annular Parachute shows a high drag efficiency and and predictions, the corona from simulated aircraft surfaces and good stability making it a good candidate for a low altitude their contribution to the triggered discharge, lightning current personnel parachute. Author redistributions, and intercloud discharges. O.C.

A87-14371'# Michigan Technological Univ., Houghton. A87-15003'# National Aeronautics and Space Administration. AIRPLANE FLIGHT THROUGH WIND-SHEAR TURBULENCE Langley Research Center, Hampton, Va. G. TREVINO (Michigan Technological University, Houghton) SUMMARY OF NASA STORM HAZARDS LIGHTNING Journal of Aircraft (ISSN 0021-8669), vol. 23, Sept. 1986, p. RESEARCH, 1980-1985 733-735. NASA-supported research. refs B. D. FISHER, P. W. BROWN (NASA, Langley Research Center, An analytical model is developed for the interaction between Hampton, VA), and J. A. PLUMER (Lightning Technologies, Inc., wind shear and turbulence to improve the database for realistic Pittsfield. MA) IN: International Aerospace and Ground Conference flight simulator programming. Shear is treated as a spatially on Lightning and Static Electricity, 1lth, Dayton, OH, June 24-26, nonconstant mean flow, with consideration given to the associated 1986, Technical Papers . Fairborn, OH, National Interagency anisotropy which can be a critical factor in landing approaches Coordination Group, 1986, p. 4-1 to 4-16. refs and take-offs during microburst events. A two-point velocity Lightning swept-flash attachment patterns and the associated correlation is defined for anisotropic turbulence and the dynamical flight conditions were recorded from 1980-1985 during 1378 implications are analyzed. Emphasis is placed on turbulence thunderstorm penetrations and 690 direct strikes with a NASA

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F-lO6B research airplane. The individual lightning attachment spots, A87-15013# along with crew comments and onboard photographic data have SPATIAL AND TEMPORAL DESCRIPTION OF STRIKES TO THE been used to identify lightning swept-flash attachment patterns FAA CV-580 AIRCRAFT and the orientations of the lightning channels with respect to the J. S. REAZER and A. V. SERRANO (Technology/Scientific airplane. The altitudes, ambient temperatures, and the relative Services, Inc., Dayton, OH) IN: International Aerospace and turbulence and precipitation levels at which the strikes occurred Ground Conference on Lightning and Static Electricity, 1lth, also are summarized and discussed, with an emphasis on the Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, differences between high and low altitude strikes. Author National Interagency Coordination Group, 1986, p. 15-1 to 15-11. refs An analysis is made of lightning strike waveforms recorded digitally by the wideband EM sensors and current shunts of the FAA CV-580 research aircraft, during thunderstorm flights at 2000 A87-15004'# National Aeronautics and Space Administration. to 18,000 ft. The waveforms were recorded at a sample rate of Langley Research Center, Hampton, Va. 5 nsec in order to yield 10-microsec windows with a 100-MHz F-106 DATA SUMMARY AND MODEL RESULTS RELATIVE TO frequency response. Current paths on the wings and fuselage are THREAT CRITERIA AND PROTECTION DESIGN ANALYSIS illustrated for several strikes. The inferred attachment points are F. L. PIlTS, G. B. FlNELLl (NASA, Langley Research Center, correlated with recordings from the four video cameras installed Hampton, VA), R. A. PERALA, and T. H. RUDOLPH (Electro on the aircraft. O.C. Magnetic Applications, Inc., Lakewood, CO) IN: International Aerospace and Ground Conference on Lightning and Static Electricity, 11th, Dayton, OH, June 24-26, 1986, Technical Papers A87-15014# . Fairborn, OH, National Interagency Coordination Group, 1986, p. SIMULTANEOUS AIRBORNE AND GROUND MEASUREMENT 5-1 to 5-20. refs OF LOW ALTITUDE CLOUD-TO-GROUND LIGHTNING STRIKE The NASA F-106 has acquired considerable data on the ON CV-580 AIRCRAFT rates-of-change of EM parameters on the aircraft surface during J. S. REAZER (Technology/Scientific Services, Inc., Dayton, OH) 690 direct lightning strikes while penetrating thunderstorms at and R. D. RICHMOND (USAF, Wright Aeronautical Laboratories, altitudes from 15,000 to 40,000 feet. The data are presently being Wright-Patterson AFB, OH) IN: International Aerospace and used in updating previous lightning criteria and standards. The Ground Conference on Lightning and Static Electricity, 1lth, new lightning standards will, therefore, be the first which reflect Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, actual aircraft responses measured at flight altitudes. Author National Interagency Coordination Group, 1986, p. 16-1 to 16-4. The instrumented CV-580 aircraft used during the 1984-1985 Airborne Lightning Characterization Program was struck three times while flying at low altitude. Attention is presently given to one event, during which simultaneous ground measurements of the A87-15005'# Military Academy, West Point, N. Y. electric and magnetic fields were made; these are used to estimate INTERPRETATION OF A CLASS OF IN-FLIGHT LIGHTNING peak channel current at the point of impact, in order to predict SIGNATURES the current encountered at the aircraft altitude of 600 m. The T. F. TROST (US. Army, Military Academy, West Point, NY) IN: results obtained are compared with aircraft data, and the current International Aerospace and Ground Conference on Lightning and amplitudes, polarities, and paths, as well as the predicted currents, Static Electricity, 1lth, Dayton, OH, June 24-26, 1986, Technical are used to determine the portion of the cloud-to-ground lightning Papers . Fairborn, OH, National Interagency Coordination Group, stroke that was intercepted by the aircraft. O.C. 1986, p. 6-1 to 6-9. refs (Contract NAG1-28) A87-15015# Data recorded on the NASA F-106B research aircraft during COMPARISON OF ELECTROMAGNETIC MEASUREMENTS ON lightning strikes often reveals electric field waveforms which begin AN AIRCRAFT FROM DIRECT LIGHTNING AlTACHMENT AND with a series of abrupt changes and end in an exponential variation. SIMULATED NUCLEAR ELECTROMAGNETIC PULSE A possible interpretation of such events is that an ionized channel H. D. BURKET (USAF, Wright Aeronautical Laboratories, is completed to the aircraft during the time of the abrupt changes, Wright-Patterson AFB, OH) IN: International Aerospace and and the charge on the aircraft dumps into this channel during the Ground Conference on Lightning and Static Electricity, llth, time of the exponential. An analysis of measured waveforms Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, assuming a simple RC-circuit model has been carried out for one National Interagency Coordination Group, 1986, p. 17-1 to 17-17. event, and the results include I = 1000 A, V = -650 kV, R = refs 1000 Ohms, and W = 100 J. Author The FAA CV-580 aircraft was flown in Florida thunderstorms during 1984-1985 in order to measure aircraft response to direct lightning attachment; the EM field and current levels continuously recorded with a 28-channel analog recorder were time-synchronized A87-15008# with ten-microsec windows of digital data having 5-nsec sample LIGHTNING STRIKES TO AIRCRAFT OF THE GERMAN intervals. The aircraft was then subjected to simulated nuclear FEDERAL ARMED FORCES EMP. Comparisons are presently made between the EM field levels W. ZIEGLER (Bundesamt fuer Wehrtechnik und Beschaffung, recorded aboard the aircraft during simulated nuclear EMP, Coblenz, West Germany) IN: International Aerospace and Ground scale-model extrapolations based on responses from scale model Conference on Lightning and Static Electricity, 11th, Dayton, OH, tests, and responses from two direct lightning attachments. O.C. June 24-26, 1986, Technical Papers . Fairborn, OH, National Interagency Coordination Group, 1986, p. 10-1 to 10-6. A87- 150 16# A survey is given of the lightning strikes from 1973 through ANALYSIS OF THE FIRST MILLISECONDS OF AIRCRAFT 1985. About 80 percent of the more than 345 lightning strikes LIGHTNING AlTACHMENT reported involved the following four types of aircraft: F-l04G, F-4, J. P. MOREAU and J. C. ALLIOT (ONERA, Chatillon-sous-Bagneux, C-160, and BR-1150. For these four aircraft the lightning strike France) IN: International Aerospace and Ground Conference on rates per year and the average rates for the whole period of 13 Lightning and Static Electricity, 11th, Dayton, OH, June 24-26, years are shown. The hazard to the respective aircraft at the time 1986, Technical Papers . Fairborn, OH, National Interagency of the lightning strike is assessed with respect to each incident of Coordination Group, 1986, p. 18-1 to 18-6. DRET-supported damage and classified according to four hazard severity categories, research. refs as specified: catastrophic, critical, tolerable and negligible. This paper presents a characterization of the lightning Author attachment to an aircraft based on the study of field and current

81 03 AIR TRANSPORTATION AND SAFETY measurements made during the first milliseconds of the amplitude predictions selected for these comparisons were from phenomenon. The data have been collected during the CV-580 1.2 to 7.4 times greater than the measured peak amplitudes, and 1984 program (20 strikes), the C-160 program (12 strikes) and that the predicted responses were more oscillatory than the the CV-580 1985 program (30 strikes). The parameters being measured response. O.C. characterized are the current and the electric and magnetic field on the aircraft surface. It is shown how the pulse-repetition rate of the electromagnetic pulses found during this first period indicates that the aircraft sustains different physical processes. This A87-15024# phenomenology will be the one encountered in a laboratory CORONA FROM SIMULATED AIRCRAFT SURFACES AND experiment, using a 6 MV generator sparking over a floating 4-m THEIR CONTRIBUTION TO THE TRIGGERED DISCHARGE cylinder. All these studies lead to some conclusions about lightning R. W. SHELTON and J. A. BICKNELL (University of Manchester simulation for indirect effects on aircraft. Author Institute of Science and Technology, England) IN: International Aerospace and Ground Conference on Lightning and Static A87-15017# Electricity, 1lth, Dayton, OH, June 24-26, 1986, Technical Papers CURRENT LEVELS AND DISTRIBUTIONS ON AN AIRCRAFT . Fairborn, OH, National Interagency Coordination Group, 1986, p. DURING GROUND LIGHTNING SIMULATION TESTS AND 28-1 to 28-9. refs IN-FLIGHT LIGHTNING AlTACHMENTS (Contract AF-AFOSR-83-0083) J. L. HEBERT (USAF, Wright Aeronautical Laboratories, Evidence that aircraft may trigger an high current discharge, Wright-Patterson AFB, OH), J. S. REAZER, J. G. SCHNEIDER, M. including the lightning strike, has been accumulating in recent D. RISLEY, and A. V. SERRANO (Technology/Scientific Services, years. The results of some experiments designed to simulate this Inc.. Dayton, OH) IN: International Aerospace and Ground type of breakdown suggest that a crucial part of the mechanism Conference on Lightning and Static Electricity, 11th, Dayton, OH, involves the interaction of positive corona streamers with the June 24-26, 1986, Technical Papers . Fairborn, OH, National precipitation. Based on this idea the required breakdown fields Interagency Coordination Group, 1986. p. 19-1 to 19-21. refs have been estimated experimentally as a function of altitude. The current levels and distributions obtained during lightning Author strikes on the FAA CV-580 aircraft are compared with those gathered by means of ground simulation tests employing two generators and two return path configurations. It is found that the A87-15033# choice of lightning simulation generators and return path IMPLEMENTATION OF GEMACS FOR LIGHTNING configurations has a pronounced effect on the current levels and INTERACTIONS ANALYSIS distributions experienced on the aircraft, as is demonstrated by E. L. COFFEY (Advanced Electromagnetics.Albuquerque, NM) and the transfer tunctions generated by each configuration. O.C. J. L. HEBERT (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB, OH) IN: International Aerospace and A87-15021# Ground Conference on Lightning and Static Electricity, 11th, ATMOSPHERIC ELECTRICITY HAZARDS PROTECTION (AEHP) Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, DEMONSTRATION National Interagency Coordination Group, 1986. p. 42-1 to 42-9. R. C. BEAVIN and M. P. HEBERT (USAF, Wright Aeronautical refs Laboratories, Wright-Patterson AFB, OH) IN: International The General Electromagnetic Model for the Analysis of Complex Aerospace and Ground Conference on Lightning and Static Systems (GEMACS), presently implemented for the analysis of Electricity, 11th, Dayton, OH, June 24-26, 1986, Technical Papers lightning-aircraft interactions in the specific case of skin current . Fairborn, OH, National Interagency Coordination Group, 1986, p. distributions on an advanced composite helicopter testbed. 24-1 to 24-5. incorporates the method of moments and the geometrical theory (Contract F33615-82-C-3406) of diffraction, as well as a hybrid solution technique. The emphasis The Wright Laboratory Atmospheric Electricity Hazards of the present GEMACS predictions of lightning-aircraft coupling Projection (AEHP) advanced development program has is on ease of use, including the generation of structure geometry. demonstrated AEHP schemes for fighter, transportlbomber, physics, and surface current computations. Examples considered helicopter and cruise missile classes using the modified F-14 and include free field and direct attachment coupling, as well as All-Composite Airframe Program testbeds. Various protection perfectly conducting versus finite conduction airframes. O.C. concepts will be applied to configure additional demonstrator testbeds; the concepts encompass circuit shielding, terminal protection, conducting floors, and cable protection methods. AEHP investigations also address the problems of physical and thermal A87-15034# damage as a result of direct attachment to both composite and COMPARISON OF ABSORPTION AND RADIATION BOUNDARY metallic airframes. The application of both swept-frequency CW CONDITIONS IN A TIME-DOMAIN THREE-DIMENSIONAL and time-domain pulses to the AEHP program is discussed. FINITE-DIFFERENCE CODE O.C. C. F. WILLIFORD, R. JOST (USAF, Institute of Technology, Wright-Patterson AFB, OH), and J. L. HEBERT (USAF, Wright A87-15022# Aeronautical Laboratories, Wright-Patterson AFB, OH) IN: AIRCRAFT LIGHTNING-INDUCED TRANSIENT TEST AND International Aerospace and Ground Conference on Lightning and PROTECTION COMPARISON Static Electricity, 1lth, Dayton, OH, June 24-26, 1986, Technical M. M. SIMPSON (Boeing Military Airplane Co.. Seattle, WA) IN: Papers . Fairborn, OH, National Interagency Coordination Group, International Aerospace and Ground Conference on Lightning and 1986, p. 44-1 to 44-10. refs Static Electricity, 11th. Dayton, OH, June 24-26, 1986, Technical Three three-dimensional finite difference codes have been used Papers . Fairborn, OH, National Interagency Coordination Group, to furnish effective time-domain predictions of skin current 1986, p. 25-1 to 25-6. refs distributions due to an aerospace vehicle’s interaction with nearby (Contract F33615-82-C-3406) and direct lightning strikes. The use of absorption and radiation Attention is given to the features and results of a distributed boundary conditions in these codes is analyzed, and the codes parameter network model, consisting of both transmission line are validated in light of airborne lightning strike data for a models and lumped parameter networks, for calculating the nose-to-tail strike on an F-16. These predictions are compared moderate level current pulse responses of a modified F-14A testbed with data from a CV-580 instrumented aircraft during an actual in order to evaluate its lightning protection design. Ten transfer wing-to-wing lightning strike event. The results, advantages, and function and nine moderate level pulse comparisons were made disadvantages of the use of each type of boundary condition are between test responses. It is noted that the moderate level peak discussed. O.C.

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A87-15038# Survey results presented in this report reflect the airlines’ MINIMUM IGNITION LEVELS OF AIRCRAFT FUEL adherence to the clean aircraft concept as presented in Advisory CONSTITUENTS TO LIGHTNING RELATED IGNITION Circular 20-117, and also indicates the need for a better SOURCES understanding of the different types of deicing fluids and facilities K. E. CROUCH (Lightning Technologies, Inc., Pittsfield, MA) IN: currently available. Author International Aerospace and Ground Conference on Lightning and Static Electricity, 1lth, Dayton, OH. June 24-26, 1986, Technical N87-11708# RMS Technologies, Inc., Trevose, Pa. Papers . Fairborn, OH, National Interagency Coordination Group, CRASH DYNAMICS PROGRAM TRANSPORT SEAT 1986, p. 48-1 to 48-17. refs PERFORMANCEAND COST BENEFIT STUDY Final Report, Mar. Three basic ignition sources were investigated to establish 1984 - Oct. 1985 conditions leading to the minimum ignition of mixtures of fuel vapors M. R. CANNON and R. E. ZIMMERMANN Oct. 1986 97 p and air. A 200 microjoule spark was found to have an ignition Prepared in cooperation with Simula, Inc., Tempe, Ariz. probability of 0.01 to 0.1 percent. Sparks of 600 to 700 microjoules (Contract DTFA03-81-C-00040) represent a 50-percent ignition probability. Hot spots of 1 sq cm (DOT/FAA/CT-85/36; TR-85433) Avail: NTlS HC AOWMF A01 required temperatures of greater than 800 C to ignite. Corona Work performed to support the Federal Aviation Administration’s (glow discharge) was found incapable of ignition until the discharge Crash Dynamics Program is described. An element of the program transitioned into an arc. Author was the Controlled Impact Demonstration (CID) of a Boeing 720 aircraft. Work related to the CID involved developing modifications A87-15180 of commercial transport seats to improve their structural AIRLINES LOOK AT 150-SEATERS crashworthiness, then installing them alongside standard, B. SWEETMAN and D. WOOLLEY Exxon Air World, vol. 38, no. unmodified seats aboard the test aircraft. This was followed by 2, 1986, p. 12-15, 30. posttest analyses of the CID data and examination of the test The effects of economic changes and deregulation on the specimens. Other supporting work included a literature review of structuring of airlines are considered. The rebalancing of airline the development of transport seats from the 1950’s to the present, fleets from large aircraft to 150-seaters due to changing interest an investigation of the elements affecting transport seats’ rates and lower fuel cost is examined. The conversion of performance in a crash environment, and recommended changes turbofan-powered aircraft to propeller-powered aircraft is that would improve the seats’ survival. Additionally, a study was proposed. I.F. performed of severe survivable transport accidents between 1970 and 1983 to determine the effect transport seat performance had N87-11706# National Transportation Safety Board, Washington, on passenger survival, and to identify instances where an improved D. C. seathestraint system might have been beneficial. Author NATIONAL TRANSPORTATION SAFETY BOARD SAFETY RECOMMENDATION N87-11709# European Space Agency, Paris (France). 16 Jan. 1986 12 p COMPARATIVE FLIGHT MEASUREMENT OF ICING Avail: NTlS HC A02/MF A01 PARAMETERS FOR THE DO 28 D2 PROPELLER-DRIVEN On November 3, 1984, a Cessna T210L, with a commercial AIRCRAFT OF THE GERMAN ARMY TESTING OFFICE 61 AND pilot and a private pilot on board, was involved in a flight control FOR DFVLR’S FALCON 20 E JET AIRCRAFT IN STRATUS malfunction incident during a takeoff ground run at Palwaukee CLOUDS Airport, Wheeling, Illinois. The commercial pilot stated that during K. P. SCHICKEL and K. UWlRA Sep. 1985 54 p Transl. into the preflight and just before takeoff, the flight controls operated ENGLISH from “Vergleichende Flukgmessung der normally. After adding power to take off, he attempted to apply Vereisungsparameter des Propellerflugzeugs DO 28 D2 der back pressure to rotate, but was unable to move the control yoke. Erprobungsstelle 61 der Bundeswehr und des Strahlflugzeugs The takeoff was aborted without further incident. A postincident Falcon 20 E der DFVLR in Stratiformen Wolken” inspection of the airplane revealed that the ribbon wire, Cessna (Oberpfaffenhofen, W. Germany Original language document was Part No.1570308-1, for the control yoke electrical switches had announced as N86-10720 jammed under the control column bearings, thus restricting the (ESA-l7-941; DFVLR-FB-85-16; ETN-86-98240) Avail: NTIS HC movement of the yoke. When the ribbon wire was removed from A04/MF A01; original German version available at DFVLR, under the bearings, but while still installed in the airplane, Cologne, West Germany DM 15.50 investigators found an excessive amount of slack in the wire. Two aircraft of different types and instrumentation were When the flight controls were moved to their full extension limit, compared during a flight operation in icing stratus clouds. The some slack still remained in the ribbon wire. On May 14, 1979, results of the measurements are comparable. It is established the Cessna Aircraft Corporation issued Service Information Letter that differences between icing and nonicing stratus clouds can be No. SE 79-26, regarding 1978 and 1979 Cessna 210 and P210 detected in infrared satellite pictures; possible causes of these models. The letter recommended that guides be installed under differences are given. The improvement of forecasts of icing stratus two of the four bearings to prevent the ribbon wire from becoming clouds is planned. ESA caught under the bearings. However, the letter did not address Cessna 210 models manufactured between 1970 and 1977, serial N87-11710# National Transportation Safely Board, Washington, numbers (SN’s) 59200 through 62273, or four other Cessna D. C. Bureau of Field Operations. airplanes which incorporate the same ribbon wire arrangement. AIRCRAFT ACCIDENT REPORTS BRIEF FORMAT, US CIVIL Author AND FOREIGN AVIATION, ISSUE NUMBER 5 OF 1985 ACCIDENTS N87-11707# Arinc Research Corp., Annapolis, Md. 2 Jun. 1986 412 p GROUND AIRCRAFT DEICING TECHNOLOGY REVIEW Final (PB86-916919; NTSB/AAB-86/19) Avail: NTIS HC Al8/MF A01; Report, Sep. 1984 - Mar. 1986 also available on subscription, North American Continent HC D. MAYER, J. MICHITSCH, and R. YU Mar. 1986 116 p $230.00/year, all others write for quote CSCL 01B (Contract DTFA03-84-(2-00086) The publication contains selected aircraft accident reports in (DOT/FAA/CT-85/21; REPT-3038-01-1-3985) Avail: NTlS HC Brief Format occurring in U.S. civil and foreign aviation operations AOG/MF A01 during Calendar Year 1985. Approximately 200 General Aviation A review and update of operational, procedural, and system and Air Carrier accidents contained in the publication represent a information regarding on-ground deicing of aircraft prior to flight is random selection. The publication is issued irregularly, normally presented. It reflects current practices of the different segments eignteen times each year. The Brief format represents the facts, Of aviation with the preponderance of information addressing the conditions, circumstances and probable cause(s) for each ground deicing operations and procedures employed by the airlines. accildent. GRA

83 03 AIR TRANSPORTATION AND SAFETY

N87-11711# National Transportation Safety Board, Washington, N87-11746’# Kentron International, Inc., Hampton, Va. D. C. Bureau of Accident Investigation. MULTIDISCIPLINARY OPTIMIZATION APPLIED TO A RUNWAY INCURSIONS AT CONTROLLED AIRPORTS IN THE TRANSPORT AIRCRAFT UNITED STATES Special Investigation Report, 1985 - 1986 G. L. GlLES and G. A. WRENN (Kentron International, Inc., 6 May 1986 109 p Hampton, Va.) ln NASA. Langley Research Center Recent (Pt386-917003: NTSB/SIR-86/01) Avail: NTlS HC AO6/MF A01; Experiences in Multidisciplinary Analysis and Optimization, Part 1 &io-available on subscription, North American Continent HC 15p 1984 $60.00/year, all others write for quote CSCL 01B Avail: NTlS HC A22/MF A01 CSCL 01C A special investigation discusses the problem of runway Decomposition of a large optimization problem into several incursions based on the results of the Safety Board investigations smaller subproblems has been proposed as an approach to making of 26 selected incidents. Details of the 26 incursions are large-scale optimization problems tractable. To date, the summarized in an appendix to the report. The report discusses characteristics of this approach have been tested on problems of the issues that the Safety Board found most relevant to the runway limited complexity. The objective of the effort is to demonstrate incursion problem at controlled airports in the United States. The the application of this multilevel optimization method on a report includes a review of previous runway incursion incidents large-scale design study using analytical models comparable to and accidents that led to recommendations to the Federal Aviation those currently being used in the aircraft industry. The purpose of Administration for remedial actions. The effectiveness and status the design study which is underway to provide this demonstration of the remedial actions are evaluated in the report, which concludes is to generate a wing design for a transport aircraft which will with new safety recommendations for actions that the Board perform a specified mission with minimum block fuel. A definition believes would significantly reduce the frequency of runway of the problem; a discussion of the multilevel composition which incursions. GRA is used for an aircraft wing; descriptions of analysis and optimization procedures used at each level; and numerical results obtained to date are included. Computational times required to perform various N87-11712# National Transportation Safety Board, Washington, steps in the process are also given. Finally, a summary of the D. C. Bureau of Field Operations. current status and plans for continuation of this development effort AIRCRAFT ACCIDENT REPORTS BRIEF FORMAT, US CIVIL are given. Author AND FOREIGN AVIATION, ISSUE NUMBER 4 OF 1985 ACCIDENTS 3 Jun. 1986 406 p (PB86-916918; NTSB/AAB-86/18) Avail: NTlS HC A18/MF A01 CSCL 01 B Selected aircraft accident reports in Brief Format occurring in N87-12549# National Transportation Safety Board, Washington, US. civil and foreign aviation operations during Calendar Year D. C. 1985 are given. Approximately 200 General Aviation and Air Carrier AIRCRAFT ACCIDENTANCIDENT SUMMARY REPORTS ERIE, accidents contained in the publication represent a random PENNSYLVANIA, OCTOBER 14, 1984; ALBUQUERQUE, NEW selection. The Brief Format represents the facts, conditions, MEXICO, FEBRUARY 11, 1985 circumstances and probable cause(s) for each accident. GRA 30 Sep. 1986 17 p (PB86-910407; NTSB-AAR-86-02-SUM) Avail: NTlS HC AO2/MF A0 1 N87-11713# National Transportation Safety Board, Washington, This publication is a compilation of the reports of two separate D. C. Bureau of Field Operations. aircraft accidents investigated by the National Transportation Safety AIRCRAFT ACCIDENT REPORTS BRIEF FORMAT, US CIVIL Board. The accident locations and their dates are as follows: Erie, AND FOREiGN AVIATION, ISSUE NUMBER 3 OF 1985 Pennsylvania, October 14, 1984; and Albuquerque, New Mexico, ACCIDENTS February 11, 1985. Author 30 Apr. 1986 416 p (PB86-916917; NTSB/AAB-86/17) Avail: NTlS HC A18/MF A01 CSCL 01 B Selected aircraft accident reports in Brief Format occurring in US. civil and foreign aviation operations during Calendar Year 1985 are given. Approximately 200 General Aviation and Air Carrier N87-12550# National Transportation Safety Board, Washington, accidents contained in the publication represent a random D. C. Bureau of Accident Investigation. selection. The Brief Format represents the facts, conditions, AIRCRAFT ACCIDENT REPORT: BAR HARBOR AIRLINES circumstances and probable cause(s) for each accident. GRA FLIGHT 1808, BEECH BE-99, N300WP, AUBURN-LEWISTON MUNICIPAL AIRPORT, AUBURN, MAINE, AUGUST 25, 1985 30 Sep. 1986 77 p N87-11714# National Transportation Safety Board, Washington, (PB86-910408; NTSB-AAR-86-06) Avail: NTlS HC A05/MF A01 D. C. Bureau of Safety Programs. About 2205 e.d.t. on August 25. 1985, Bar Harbor Airlines REVIEW OF ACCIDENT DATA US GENERAL AVIATION Flight 1818, a Beech Aircraft Corporation Model 99 crashed about CALENDAR YEAR 1982 Annual Report 1 mile southwest of the Auburn-Lewiston Municipal Airport at 16 Feb. 1986 246 p Auburn, Maine, while making an instrument landing system (ILS) (PB86-201910; NTSB/ARG-86/01) Avail: NTlS HC A1 1/MF A01 approach to runway 4. The weather was indefinite 300-foot ceiling, CSCL 01 B sky obscured, visibility 1 mile in light drizzle and fog. The flight A statistical compilation and review of general aviation accidents was a regularly scheduled commuter flight between Boston-Logan which occurred in 1982 in the United States, its territories and International Airport and Bangor, Maine, with intermediate stops possessions, and in international waters are given. The accidents at Auburn, Augusta, and Watewille, Maine. All six passengers and reported are all those involving U.S. registered aircraft not the two flightcrew members were killed in the accident. The airplane conducting air carrier revenue operations under 14 CFR 121, 14 was destroyed by impact forces and postcrash fire. The National CFR 125. 14 CFR 127, or 14 CFR 135. A review of a subset of Transportation Safety Board determined that the probable cause all general aviation accidents is given. Each subset represents of the accident was the captain’s continuation of an unstabilized aircraft of similar types or aircraft being operated for particular approach which resulted in a descent below glidescope. purposes. Several tables present accident parameters for 1982 Contributing to the unstabilized approach was the radar controller’s only, and each section includes tabulations which present issuance and the captain’s acceptance of a nonstandard air traffic comparative st-!i,tics for 1982 and for the five-year period 1977 control radar vector resulting in an excessive intercept with the to 1981. GRA localizer. Author

04 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

N87-12551# Sverdrup Technology, Inc., Arnold Air Force Station, accurate guidance possible for a vehicle launched from a carrier Tenn. aircraft without performing a preflight field alignment/calibration. ANALYSIS AND VERIFICATION OF THE ICING SCALING The carrier aircraft possesses a master navigator which provides EQUATIONS. VOLUME 1: REVISION Final Report, 1 Aug. 1981 the reference information for LCINS operating as a slave navigator - 31 Mar. 1984 during the alignmentkalibration process. Delco's alignmentkali- G. A. RUFF Mar. 1986 80 p Prepared in cooperation with bration implementation employs a 25-state Kalman estimator that Arnold Engineering Development Center, Arnold AFS, Tenn. uses carousel-induced modulation and IMU indexing to optimally (AD-A167976; AEDC-TR-85-30-VOL-1-REV) Avail: NTlS HC estimate the IMU attitude and calibrate the unknown instrument co- AO5/MF A01 CSCL 08L efficients. Author Study objectives were to evaluate the equations governing the ice-accretion process to identify proposed scaling parameters and A87-13532 to conduct tests to determine which, is any, of the proposed ION, NATIONAL TECHNICAL MEETING, LONG BEACH, CA, methods produced scale ice accretions. Study results include: (1) JANUARY 21-23, 1986, PROCEEDINGS A set of equations that can be used to calculate test conditions Meeting sponsored by ION, Bell Aerospace Textron, Northrop so that scaled ice shapes are produced on geometrically similar Corp., et al. Washington, DC, Institute of Navigation, 1986. 134 p. bodies was developed and experimentally verified. (2) Posttest For individual items see A87-13533 to A87-13547. evaluation of the scaling parameters based on the actual test Papers are presented on GPS satellite buildup strategy, PGS conditions was necessary for accurate evaluation of test results. user equipment, the USAF Standard RLG INU program, navigation (3) An icing similitude computer code, SIMICE, was developed to systems for multiple target formulation flight control, and differential calculate similitude conditions using the verified scaling equations. GPS in the range application program. Also considered are (4) The equations were applicable over the range of meteorological GPSIJITDS compatibility, PGS application for air defense, weather conditions found in natural icing, with the possible exception of safety aspects in future civil air navigation, satellite based position velocity. (5) Velocity is the primary limitation of the scaling determination systems and concepts for air traffic surveillance, equations. To maintain scaled flow fields and droplet impingement and GPS/lnmarsat. Other topics include a vehicle tracking system, characteristics, both the model and full-scale velocities must yield improving LORAN coverage at minimum cost, precision point target a Reynolds number > or = 200,000 and < the velocity giving tracking, and ring laser gyros for space precision pointing and the critical Mach number of the body geometry. (6) At values of navigation applications. Papers are also presented on reduction dynamic pressure of approximately 1.6 psia, shedding of missile impact CEP via carouseling for a two- or three-gimbaled characteristics of the ice accretion were observed to affect the platform during free-fall, GPS/Doppler processing for precise final ice shape. GRA positioning in dynamic applications, and an evaluation of the GPS single frequency user ionospheric time-delay model. R.R.

04 A87-13533# NAVSTAR GLOBAL POSITIONING SYSTEMS COLLINS USER EQU!PYENT - AN EYOLU?!QNARY ASSESSMEN? G. J. HUDAK (Rockwell International Corp., Collins Government Avionics Includes digital and voice communication with aircraft; air navigation Dw., Cedar Rapids, IA) IN: ION, National Technical systems (satellite and ground based); and air traffic control. Meeting, Long Beach, CA, January 21-23, 1986, Proceedings . Washington, DC, Institute of Navigation, 1986, p. 5-13. The evolution of Collins GPS Receiver architecture, beginning with the Phase I concept validation, and the development of user A87-13362' National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. equipment such as a Generalized Development Model, High and TIME-BASED AIR TRAFFIC MANAGEMENT USING EXPERT Medium Dynamics sets, and manpacks, are described. Phase II SYSTEMS Life Cycle Cost trade studies suggested changes including the L. TOBIAS and J. L. SCOGGINS (NASA, Ames Research Center, deletion of high risk LSI (RF) and Bubble Memory (processor), Moffett Field, CA) IN: 1986 American Control Conference, 5th, and the inclusion of custom LSI for code generators. The resultant Seattle, WA, June 18-20, 1986, Proceedings. Volume 2 . New receiver design has a 75 percent hardware commonality figure, York, Institute of Electrical and Electronics Engineers, 1986, p. with software commonality extending across 84 percent of ail Host 693-700. refs Vehicle (HV) applications. Software implementation minimized the A prototype expert system has been developed for the time hardware required, utilized an efficient HOL, and minimized logistics. scheduling of aircraft into the terminal area. The three functions Phase II changes were geared towards accommodating the of the air-traffic-control schedule advisor are as follows: (1) for requirements of the 120 candidate HVs planned for integration, each new arrival, it develops an admisible flight plan for that aircraft; and involved the standardizing of interfaces while allowing for necessary flexibility. R.R. (2) as the aircraft progresses through the terminal area, it monitors deviations from the aircraft's flight plan and provides advisories to return the aircraft to its assigned schedule; and (3) if major A87-13540# disruptions such as missed approaches occur, it develops a revised WEATHER SAFETY ASPECTS IN FUTURE CIVIL AIR plan. The advisor is operational on a Symbolics 3600, and is NAVIGATION programmed in MRS (a logic programming language), Lisp, and P. R. MAHAPATRA (Indian Institute of Science, Bangalore, India) Fortran. Author and D. S. ZRNlC (NOAA, National Severe Storms Laboratory, Norman, OK) IN: ION, National Technical Meeting, Long Beach, A87-13438 CA, January 21-23, 1986, Proceedings . Washington, DC, Institute IN-FLIGHT TRANSFER ALIGNMENT/CALIBRATION OF A of Navigation, 1986, p. 57-64. refs STRAPDOWN INS THAT EMPLOYS CAROUSELED Weather factors affecting civil aviation are reviewed, and present INSTRUMENTS AND IMU INDEXING and future approaches to obtain weather information and integrate C. JOHNSON (Delco Electronics Corp., Goleta, CA) IN: 1986 it into ATC procedures are discussed. Topics examined include American Control Conference, 5th, Seattle, WA, June 18-20, 1986, wind shear and its effects, turbulence and gusts, precipitation, Proceedings. Volume 3 . New York, Institute of Electrical and ground-based and airborne in situ sensors and radars, satellite Electronics Engineers, 1986, p. 1572, 1573. sensing, and the future potential of Doppler radars and frequency An in-flight transfer alignment/calibration technique has been and polarization diversity radars. Consideration is given to software developed for the new Delco Electronics low cost inertial navigation and system-integration aspects such as multiparameter displays; system (LCINS). In-flight transfer alignment/calibration makes cell, mesocyclone, divergence, and gust-front detection; wind-field,

85 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

multimoment. and composite displays; and expert systems. Graphs, A87- 15427 diagrams, and a sample multimoment display are provided. T.K. FAULT-TOLERANT C31 SYSTEM A(O), A(I), MTBF ALLOCATIONS R. FLEMING, J. JOSSELYN, and R. DEHOFF (Systems Control Technology, Inc., Palo Alto, CA) IN: 1986 Annual Reliability and A87-13543# Maintainability Symposium, Las Vegas, NV, January 28-30, 1986, IMPROVING LORAN COVERAGE AT MINIMUM COST Proceedings . New York, Institute of Electrical and Electronics W. N. DEAN (ARNAV Systems, Inc., Portland, OR) IN: ION, Engineers, Inc., 1986, p. 352-357. National Technical Meeting, Long Beach, CA, January 21-23, 1986, A generic technique is discussed for allocation of command, Proceedings . Washington, DC, Institute of Navigation, 1986, p. control, communications, and intelligence ((231)) system availability 95-99. and MTBF to subsystems, projects, or equipment. The technique Measures to extend Loran-C coverage of the continental U.S. can be used both for allocations and for reliability, maintainability, are discussed and illustrated with diagrams, graphs, maps, and availability (RMA) design evaluations. Once set up, the methodology tables. It is shown that dual-rating of one station in Alaska and permits easily updated analyses, evalutions, or reallocations as one in Texas would improve service there remarkably. A the design evolves. Such analyses can support or form the basis minimum-cost joint US-Canadian expansion plan involving only for design changes, and the methodology can also be used to six new stations and successfully filling the midcontinent gap over support specific project or subsystem designs. This analysis the U.S. and Canada (up to 60 deg N) is proposed. T.K. technique forms the first step in the establishment and automation of the link between RMA subsystem equipment designlrequirementsand fault-tolerant C31 system operational RMA requirements throughout the system development or acquisition process. An air traffic control system forms a good testbed for A87-13544# fault-tolerant C31 system RMA allocation because of its COMBINING LORAN AND GPS - THE BEST OF BOTH complexities. The procedure for allocation of mission operational WORLDS availability requirements to the subsystem level is demonstrated P. BRAISTED, R. ESCHENBACH, and A. TlWARl (Trimble using a generic air traffic control system example. Author Navigation, Mountain View, CA) IN: ION, National Technical Meeting, Long Beach, CA, January 21-23, 1986, Proceedings . Washington, DC, Institute of Navigation, 1986, p. 101-1 04. The use of the current Loran-C network and the future GPS A87-15563 for marine navigation is described, and their use in combination SYNTHESIS OF DEVICES FOR THE OPTIMAL PROCESSING (now planned for the period before GPS becomes fully operational OF PULSED RADIO SIGNALS IN LORAN SYSTEMS [SINTEZ in 1988) is shown to offer significant advantages over either system USTROISTV OPTIMAL'NOI OBRABOTKI IMPUL'SNYKH alone. Loran provides GPS initialization and continuous coastal RADIOSIGNALOV V RADIOTEKHNICHESKIKH SISTEMAKH coverage when GPS is out of sight, while GPS improves Loran by DAL'NEI NAVlGATSllJ aiding cycle selection, ambiguity treatment, and ASF-factor P. P. FILATOV Radiotekhnika (ISSN 003343486), July 1986, p. calibration. Graphs and diagrams are included. T.K. 16-19. In Russian. refs

A87-15569 A87-14004# RADIO-NAVIGATION METERS BASED ON THE K588 SERIES DEVELOPMENT AND TESTING OF NEW TECHNOLOGIES FOR MICROPROCESSOR UNIT [RADIONAVIGATSIONNYE FLIGHT OPERATION AND SAFETY [ENTWICKLUNG UND IZMERITELI NA OSNOVE MPK SERll K5881 ERPROBUNG NEUER TECHNOLOGIEN FUER DIE G. N. GROMOV, V. V. GAVRISHCHUK, R. V. DROZDOV, IU. T. FLUGFUEHRUNG UND FLUGSICHERUNG] KRIVORUCHKO, B. V. PONOMARENKO et al. Radiotekhnika H. WINTER (DFVLR, lnstitut fuer Flugfuehrung, Brunswick, West (ISSN 003343486). July 1986, p. 77-80. In Russian. refs i Germany) BMFT, Statusseminar ueber Luftfahrtforschung und It is demonstrated that a unified family of onboard Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, radio-navigation search-tracking meters can be built on the basis Paper. 45 p. In German. of the K588 series microprocessor unit. These meters provide for Recent technological advances in flight operation and safety real-time signal processing and meet modern requirements on the are reviewed. Advances in ring-laser technology are addressed, organization of aircraft navigation instruments and the ~ and research on resonator geometry and on possibilities for a standardization of engineering solutions and software. The design low-cost ring laser is reviewed. The use of helicopters as test of meters on the basis of a microcomputer with a parallel pipeline beds for avionics systems is examined, including the HETAS project interface makes possible the independent improvement of the meter modules while retaining the appropriate sequence of ~ and the DISCUS system. C.D. engineering solutions by changing the software. B.J.

A8?-14140# A8?-1602?# OPTIMAL GUIDANCE LAW WITH FIRST ORDER LAG LOOP MOBILE COMMUNICATIONS, NAVIGATION AND AND NORMAL CONSTRAINT SURVEILLANCE Z. ZHAN (Northwestern Polytechnical University, Xian, People's C. ROSETI (ESA, Paris, France) IAF, International Astronautical I Republic of China) Acta Aeronautica et Astronautica Sinica, vol. Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. 20 p. 7, June 1986. p. 291-297. In Chinese, with abstract in English. (IAF PAPER 86-333) refs The possible developments and changes in mobile An optimal guidance law based on the maximum principle is communications and navigation in terms of traffic density, discussed in this paper. It is assumed that the kinetic characteristics composition, technical requirements, and institutional organization of 'vehicle-target' are that of a first order lag loop, the performance by the year 2000 are discussed. In particular, it is noted that the index is the minimum control energy consumption, the terminal whole structure and organization of air traffic as well as states belong to a intercept curved surface with control cut-off, communications, navigation, and surveillance networks will have and the terminal acceleration of the vehicle equals zero. Based to be redefined; the shift from ground-based technologies to space on these assumptions, an analytical form of the closed loop optimal is unavoidable, for reasons of both operational efficiency for the intercept guidance law has been deduced. Author user and economy for the provider of the system. V.L. 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

N87-11715# Massachusetts Inst. of Tech., Lexington. Lincoln 05 Lab. MODE S BEACOM SYSTEM: FUNCTIONAL DESCRIPTION AIRCRAFT DESIGN, TESTING AND V. A. ORLANDO and P. R. DROUILHET 29 Aug. 1986 159 p (Contract DOT-FA72WAI-261; F19628-85-C-0002) PERFORMANCE (DOT/FAA/PM-86/19; ATC-42-REV-D) Avail: NTlS HC A08/MF A01 Includes aircraft simulation technology. Provided is a functional description of the Mode S beacon System, a combined secondary surveillance radar (beacon) and ground-air-ground data link system capable of providing the aircraft A87-13101 surveillance and communications necessary to support ATC ADVANCED COMPOSITES APPLICATIONS FOR THE 6-16 automation in future traffic environments. Mode S is capable of BOMBER - AN OVERVIEW common-channel interoperation with the current ATC beacon L. G. HANSEN, D. LOSSEE, and W. L. OBRIEN (Rockwell system, and may be implemented over an extended transition International Corp., Pittsburgh, PA) IN: International SAMPE period, Mode S will provide the surveillance and communication Symposium and Exhibition, 31 st, Los Angeles, CA, April 7-10, 1986, performance required by ATC automation, the reliable Proceedings. Covina, CA, Society for the Advancement of Material communications needed to support data link services, and the and Process Engineering, 1986, p. 71 2-724. capability of operating with a terminal or enroute, radar An overview of the advanced composites applications for the digitizer-equipped, ATC surveillance radar. This material updates production B-1B Bomber is given. The applications cover the total that presented in Mode S Beacon System: Functional Description, gamut of complexity from wing type spar/cover construction used DOT/FAA/PM-83/8, 15 July 1983. Author in the overwing movable fairings to full depth sandwich structure with varying cover thickness from minimum gage to thick laminates for such applications as the weapons bay and avionics doors, N87-11716# Department of the Air Force, Washington, D.C. structural mode control vane and preloaded pivot fairings, plus ELECTROLUMINESCENT (EL) REMOTELY-CONTROLLED thick filament wound application used in the development of a LANDING ZONE MARKER LIGHT SYSTEM Patent 180 inch long rotary launcher. This paper covers design C. S. PIEROWAY, A. BLOUNT, G. L. BRITTON, and D. J. KRILE, configurations, manufacturing methods and structural certification inventors (to Air Force) 20 May 1986 10 p Supersedes as they apply to the production program. Author AD-DO1 0858 (AD-DO12386; US-PATENT-4,590,471; US-PATENT-APPL-SN-566351; US-PATENT-CLASS-340-825.69) Avail: US Patent and Trademark Office CSCL 17G A remotely-controlled lighting system for austere landing zone lighting includes a plurality of light units each having dual A87- 1315 1 electroluminescent light panels, a plurality of remote controllers DESIGN CONSIDERATIONS FOR SUPERPLASTICALLY each having an electrical receiver, and a separate electrical FORMED COMPLEX AIRCRAFT STRUCTURES :;ansmiEe:. The ligh? pane! uni?s 2nd :Pmz!e cC!?!r"!!ors, 2ttttlchod H. ZAMANi, M. M. FiATvVAiii, E.VASTAL'A jliiortiirop Cwrp., Aiiciiifi electrically, may also be attached physically and placed along the Div., Hawthorne, CA), and J. TUSS (USAF, Wright Aeronautical sides of a landing zone, while the separate transmitter is located Laboratories, Wright-Patterson AFB, OH) IN: International SAMPE at a remote, covert place, such as a foxhole. The transmitter and Symposium and Exhibition, 31 st, Los Angeles, CA, April 7-10, 1986, receivers of the remote controllers are capable of being preset to Proceedings. Covina, CA, Society for the Advancement of Material respectively transmit and receive a first sequence of coded pulses and Process Engineering, 1986, p. 1350-1361. USAF-supported for turning on the light panel units and a second sequence for research. turning off the light units. Also, the transmitter may be operated A research program has been conducted in order to assess to repeatedly transmit one of the first or second sequence without the effect of the geometry of the structure, the forming parameters transmitting the other sequence between one sequence to ensure of the selected material, and the component-forming feasibility on that all of the light units are either turned on or turned off. GRA the final design of complex superplastically formed structures. Particular emphasis is placed on ways to avoid such problems as N87-12552'# Douglas Aircraft Co., Inc., Long Beach, Calif. subminimum thickness and cavitation. The design of the F-5F lower GUIDANCE LAW SIMULATION STUDIES FOR COMPLEX avionics deck and the F-5F leading edge extension, used as APPROACHES USING THE MICROWAVE LANDING SYSTEM demonstration parts in this program, is reviewed. V.L. (MLS) J. B. FEATHER Nov. 1986 80 D I (Contract NAS1-18028) I (NASA-CR-178182; NAS 1.26:178182) Avail: NTlS HC AO5/MF A01 CSCL 17G This report documents results for MLS guidance algorithm A87-13354 development conducted by DAC for NASA under the Advance OPTIMAL STOCHASTIC OBSERVERS APPLIED TO HYDRAULIC Transport Operating Systems (ATOPS) Technology Studies ACTUATION SYSTEMS program (NAS1-18028). The study consisted of evaluating guidance H. V. PANOSSIAN (HR Textron, Inc., Valencia, CA) IN: 1986 laws for vertical and lateral path control, as well as speed control, American Control Conference, 5th, Seattle, WA, June 18-20, 1986, by simulating an MLS approach for the Washington National Airport. Proceedings. Volume 1 . New York, Institute of Electrical and This work is an extension and generalization of a previous ATOPS Electronics Engineers, 1986, p. 602-604. refs contract (NAS1-16202) completed by DAC in 1985. The Washington Fault detection and isolation in supersonic aircraft river approach was simulated by six waypoints and one glideslope electrohydraulic servosystems is normally carried out by the flight change and consisted of an eleven nautical mile approach path. control computer (FCC). A technique is presented for relieving the ' Tracking performance was generated for 10 cases representing computational load on the FCC by inserting a linearly programmed several different conditions, which included MLS noise, steady wind, microprocessor into the loop between a control surface actuator turbulence, and windshear. Results of this simulation phase are and the FCC. The linear stochastic observer features a state 1 suitable for use in future fixed-base simulator evaluations employing equation which includes an expression for white Gaussian noise. actual hardware (autopilot and a performance management Simulation results show that the piston measurement is sufficient I system), as well as crew procedures and information requirements data for calculating the acceleration, velocity and position of the for MLS. Author actuator, along with leakage along the piston seal. M.S.K.

87 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

A87-13360' National Aeronautics and Space Administration. A87-13628 Langley Research Center, Hampton, Va. AV-BBIGR MK 5 AIRFRAME COMPOSITE APPLICATIONS IMPACT OF MISMODELED IDLE ENGINE PERFORMANCE ON B. L. RILEY (McDonnell Douglas Corp., Saint Louis, MO) IN: CALCULATION AND TRACKING OF OPTIMAL 4-D DESCENT Fibre reinforced composites 1986; Proceedings of the Second TRAJECTORIES International Conference, Liverpool, England, April 8-10, 1986 . D. H. WILLIAMS (NASA, Langley Research Center, Hampton, VA) London, Mechanical Engineering Publications, Ltd., 1986, p. IN: 1986 American Control Conference, 5th. Seattle, WA, June 153-172. refs 18-20, 1986, Proceedings. Volume 2 . New York, Institute of Applications of composites (carbodepoxy, fiberglass/epoxy, Electrical and Electronics Engineers, 1986. p. 681 -686. refs carbon/BMI, and fiberglass/BMl) to the AV-BB/GR Mk 5 airframe Advanced flight management systems are being developed are described. Primary structural applications include the wing which are capable of calculating optimal 3-0 and 4-D flight torque box and control surfaces, horizontal tail, and forward trajectories for arbitrary fuel and time costs. These systems require fuselage; secondary applications are the gun and ammo pods, mathematical models of airplane performance in order to compute strakes, LIDS fence, ventral fin, rudder, engine bay doors, nose the optimal profiles. Mismodeled idle engine characteristics can cone, overwing fairing, and outrigger fairing. The use of composite result in descent trajectories requiring excessive throttle and/or materials for 25 percent of the airframe weight resulted in a weight speedbrake activity in order to achieve the desired end conditions. saving of 525 Ibs per aircraft. The design philosophy, test programs, This paper evaluates the cost and fuel penalties, trajectory interpretation and evaluation of test results, and the aspects of variations, and flight control requirements associated with typical repairs and manufacturing defects are discussed. Multiple design idle engine modeling errors for a twin-jet transport airplane. diagrams are included. IS. Variations in idle power setting, thrust, fuel flow, and surge bleed operation were evaluated for a cruise/descent flight segment. The results of this analysis provide insight into the penalties associated with uncertainties in idle engine performance and suggest methods of modeling which minimize these penalties. Author

A87-13637# THE EQUIVALENT MASSES AT NOSE LANDING-GEARS DURING LANDING-IMPACTS AND WHEN TAXIING OVER A87-13361' Boeing Commercial Airplane Co., Seattle, Wash. RUNWAY PERTURBATIONS SENSITIVITY STUDIES OF 4D DESCENT STRATEGIES IN AN D. H. CHESTER (Israel Aircraft Industries, Ltd., Lod) IN: Israel ADVANCED METERING ENVIRONMENT Annual Conference on Aviation and Astronautics, 27th, Haifa, Israel, K. H. IZUMl (Boeing Commercial Airplane Co., Seattle, WA) IN: February 27,28, 1985, Collection of Papers . Haifa, Israel, Technion 1986 American Control Conference, 5th, Seattle, WA, June 18-20, - Israel Institute of Technology, 1986, p. 7-12. refs 1986. Proceedings. Volume 2 . New York, Institute of Electrical The problem of analysis of landing impacts at the nose-gear and Electronics Engineers, 1986, p. 687-692. on aircraft having a tricycle landing-gear arrangement is considered. (Contract NASl-17635) The main-gears are assumed to be landed and the reaction on An investigation of utilizing various 40 airplane descent them is mainly due to the proportion of the total weight normally strategies in an advanced time-based metering environment was acting there. During nose-gear landing impact, the vertical conducted. The three strategies considered were clean-idle acceleration of both translational and pitching motions of the rigid MachKAS, constant flight path angle (CFPA) Mach/CAS, and aircraft. Expressions are found for the equivalent mass at the fuel-optimal. Traffic inputs consisted of all combinatory pairs of nose-gear, including an allowance for elasticity of the tires and three types of commercial turbojets (8737-300. 8747-200, and shock-absorbers. Using realistic aircraft mass properties it is seen 8767-200) and two weight classes for each airplane type. that the equivalent masses are between two and three times the Sensitivities of traffic throughput and fleet fuel to descent strategies, mass fraction under static conditions. It is concluded that the both among themselves and in combination, for different assigned equivalent mass at the nose-gear applies during landing-impact, meter fix times and traffic pairings were studied under controlled but for calculating obstacle crossing loads it should be used with initial conditions. Author certain reservations. Author

A87-13596' Virginia Polytechnic Inst. and State Univ.. Blacksburg. COMPARISON OF TWO PROPELLER SOURCE MODELS FOR AIRCRAFT INTERIOR NOISE STUDIES A87-13646# J. R. MAHAN and C. R. FULLER (Virginia Polytechnic Institute UTILIZATION OF 3-0 PROGRAMS FOR AIRCRAFT DESIGN AND and State University, Blacksburg) IN: Aero- and hydro-acoustics; DEVELOPMENT Proceedings of the Symposium, Ecully, France, July 3-6, 1985 . H. ROSS (Messerschmitt-Boelkow-Blohm GmbH. Ottobrunn, West Berlin and New York, Springer-Verlag, 1986, p. 135-143. refs Germany) IN: Israel Annual Conference on Aviation and (Contract NAGl -493; NAGl -390) Astronautics, 27th, Haifa, Israel, February 27, 28, 1985, Collection The sensitivity of the predicted synchrophasing (SP) of Papers . Haifa, Israel, Technion - Israel Institute of Technology, effectiveness trends to the propeller source model issued is 1986, p. 99-107. investigated with reference to the development of advanced This paper describes a three dimensional computer program turboprop engines for transport aircraft. SP effectiveness is shown which is being used as a mathematical tool for the geometric to be sensitive to the type of source model used. For the virtually definition of air vehicles. The graphic interactive program allows rotating dipole source model, the SP effectiveness is sensitive to the surface definition of irregular bodies and the analysis of the direction of rotation at some frequencies but not at others. kinematic problems as well as the analysis of installation problems. The SP effectiveness obtained from the virtually rotating dipole Typical examples of the application of a three-dimensional program model is not very sensitive to the radial location of the source for the design and development of high-performance fighter aircraft distribution within reasonable limits. Finally, the predicted SP are given. The software- and hardware characteristics are effectiveness is shown to be more sensitive to the details of the discussed. Problems associated with the introduction of the system source model used for the case of corotation than for the case of are described and the relative cost of the system is identified. counterrotation. B.J. Author

88 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

A87-13662 velocities within this range of percentiles and the even larger NATIONAL SPECIALIST’S MEETING ON CRASHWORTHY increase in the energy content. IS. DESIGN OF ROTORCRAFT, GEORGIA INSTITUTE OF TECHNOLOGY, ATLANTA, APRIL 7-9, 1986, PROCEEDINGS D. P. SCHRAGE, ED., S. V. HANAGUD, ED., and S. A. MEYER, ED. (Georgia Institute of Technology, Atlanta) Meeting sponsored A87-13665 by AHS and Georgia Institute of Technology. Alexandria, VA, SURVIVABILITY AND CRASHWORTHINESS DESIGN American Helicopter Society, 1986, 263 p. For individual items CRITERIA see A87-13663 to A87-13687. J. K. SEN (McDonnell Douglas Helicopter Co., Culver City, CA) The topics discussed include crashworthy design criteria, IN: National Specialist’s Meeting on Crashworthy Design of specific aircraft and component crashworthy designs, structural Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . Alexandria, crashworthiness research and analytical techniques, human VA, American Helicopter Society. 1986, 7 p. tolerance and crashworthy seating systems, testing and Crashworthiness design criteria, determined for a helicopter in instrumentation, materials and material properties related to terms of vertical speed and helicopter attitude at crash impact, crashworthy designs, and accident investigations and analysis of were established for the lightest helicopter encompassing the crash sequences. Papers are presented on the status of highest cumulative frequency of occurrence of survivable accidents. crashworthiness design criteria, design of aircraft structures for The weight trade-off study was based on the results of the crash impact, landing gear performance simulation by the KRASH crash-impact analysis by Sen et al. (1985) of a 10,000-lb program, and crashworthy crewseat limit load optimization through crashworthy utility helicopter, conducted for a maximum vertical dynamic testing. Consideration is given to Kane’s method for velocity of 42 ft/s, maximum roll angle of +/-15 deg, and pitch analyzing crash sequences and crashworthy design, the role of angles ranging between -5 and +15 deg, using the KRASH fiber and matrix in the crash energy absorption of composite program. The conclusions from the weight trade-off study are materials, correlation of the experimental static and dynamic compared to accident kinematics and survivability data of US. response of simple structural components, the analysis of civil Army Utility Helicopters from 1975 to 1980. IS. rotorcraft accidents for the development of improved design criteria, and impact severity and potential injury prevention in general aviation accidents. IS. A87-13666 THE DEVELOPMENT OF DYNAMIC PERFORMANCE A87-13663 STANDARDS FOR CIVIL ROTORCRAFT SEATS EVOLUTION OF MIL-STD-129OA, LIGHT FIXED AND J. H. MAJOR (FAA, Fort Worth, TX) and S. J. SOLTIS (FAA, ROTARY-WING AIRCRAFT CRASHWORTHINESS Long Beach, CA) IN: National Specialist‘s Meeting on Crashworthy L. T. BURROWS (US. Army, Aviation Applied Technology Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . Directorate, Fort Eustis, VA) IN: National Specialist’s Meeting on Alexandria, VA, American Helicopter Society, 1986, 13 p. refs Crashworthy Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, Civil aircraft seats have traditionally been designed to comply Proceedings . Alexandria, VA, American Helicopter Society, 1986, with static strength requirements. Dynamic performance standards 8 p. :e!s which address both seat strength and the occupant impact Modern-day training and tactical employment requirements for protection characteristics of the seat have recently been defined the US. Army helicopter dictate that a large percentage of for aircraft seats. The FAA has funded a program to research operations occur in the low-speed, low altitude flight regime, with US. rotorcraft accidents. Accident scenarios were developed from reduced margins of safety normally associated with higher airspeed this research. Further analysis of the results of those data led to and higher altitude operations in case of emergency. This increased the formulation of new dynamic performance standards for probability of accident occurrence, coupled with the lack of an rotorcraft seats and occupant restraint. The FAA has proposed in-flight egress capability, makes design for crashworthiness that those newly developed seat dynamic performance criteria be essential for Army helicopters. The evolution of crash survival incorporated into Parts 27 and 29 of the Federal Aviation design criteria, its influence on the formulation of a US. Army Regulations. The development of those standards is reviewed. military standard for rotary-wing aircraft crashworthiness, and its Author application to current and new-generation Army helicopters is discussed. Emphasis is given to the need for a total systems’ approach in design for crashworthiness and the necessity for considering crashworthiness early in the design phase of a new A87-13667 aviation weapon systems development effort. The actual application STATE-OF-THE-ART CRASHWORTHY CARGO RESTRAINT of crashworthiness to Army helicopters is presented with statistics SYSTEMS FOR MILITARY AIRCRAFT that show dramatic reductions in fatalities and injuries with R. L. HATE (US. Navy, Naval Air Development Center, Warminster, implementation of a crashworthy fuel system. Author PA), R. F. CAMPBELL (Boeing Vertol Co., Philadelphia, PA), H. L. GEORGE (US. Naval Air Systems Command, Washington, DC), and J. SHEFRIN IN: National Specialist’s Meeting on Crashworthy A87-13664 Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . THE STATUS OF CRASHWORTHINESS DESIGN CRITERIA Alexandria, VA, American Helicopter Society, 1986, 11 p. refs J. C. WARRICK and S. P. DESJARDINS (Simula, Inc., Phoenix, The aspects of designing cargo restraint systems by matching AZ) IN: National Specialist’s Meeting on Crashworthy Design of the cargo restraint’s structural strength to the actual crash Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . Alexandria, conditions of shipboard and land-based transports are discussed. VA, American Helicopter Society, 1986, 11 p. refs Special attention is given to advanced technology materials, The development of aircraft crashworthiness criteria is described cargo-related accidents, design and system integration, cargo crash with reference to military helicopters (e.g., The Black Hawk). The simulation testing, and energy management. The user benefits dangers of permitting either an increase or a decrease in the established by this cargo crash energy management program are: severity of the criteria are discussed. Special consideration is given (1) the use of one crash pulse criterion, MIL-STD-1290, for all to the hazard of misinterpreting the crashworthiness scenario data. Navy cargo transports, rotary or fixed wing; (2) work load reduction It is shown that the selection of a new 85-percentile survivable in restraining cargo; (3) the use of energy absorbers in any cargo crash velocity magnitude (instead of the old 95-percentile aircraft, old or new; (4) upgraded crash survivability in cargo requirement) could result in protection for only about 55 percent transport during combat, during a peacetime mission, and when of the survivable crashes. The disproportionate share of the injuries augmenting 463L restraint; and (5) reduced weight of mission and fatalities occurs between the 85th-percentile and the equipment and the associated restraint structure in new aircraft. 95th-percentile velocity levels because of the large increase in I.S.

89 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

A87-13668 A87-13671 DESIGN OF AIRFRAME STRUCTURES FOR CRASH IMPACT COMPUTER MODELING OF CRASHWORTHY SEATING J. D. CRONKHITE (Bell Helicopter Textron, Fort Worth, TX) IN: SYSTEMS National Specialist’s Meeting on Crashworthy Design of Rotorcraft, A. 0. BOLUKBASI (Simula, Inc., Phoenix, AZ) IN: National Atlanta, GA, April 7-9, 1986, Proceedings . Alexandria, VA, Specialist’s Meeting on Crashworthy Design of Rotorcraft, Atlanta, American Helicopter Society, 1986, 13 p. refs GA, April 7-9, 1986, Proceedings . Alexandria, VA, American Due to recent trends in helicopter design, vertical impact has Helicopter Society, 1986, 8 p. refs been identified as the primary determinant of crashworthiness for The purpose Of this paper is to describe the application Of airframes. This factor has prompted the development of Program SOM-LA (Seat/Occupant Model - Light Aircraft) to energy-absorbing fuselage underfloor structure concepts that have modeling of crashworthy seating systems. Program SOM-LA been demonstrated by full scale structure tests under the aegis combines a three-dimensional dynamic model of the human body of both NASA and the U.S. Army. The results obtained by these with a model of the seat structure. The specific seating system test programs are presented together with previously obtained data modeled is a guided energy-absorbing helicopter seat. The model based on the comparison of KRASH and DYCAST nonlinear predictions are compared with measured data from dynamic tests structural crash simulations with several other full scale crash tests. of the seat. Author An attempt is made to identify the most important design parameters, the most promising energy-absorbing structure A87-13672 concepts, and those existing crash analysis methods that may PROGRAM KRASH - THE EVOLUTION OF AN ANALYTICAL prove most useful in the design of efficient crash impact-response TOOL TO EVALUATE AIRCRAFT STRUCTURAL CRASH helicopter airframes. O.C. DYNAMICS RESPONSE G. WllTLlN (Lockheed-California Co., Burbank, CA) IN: National Specialist’s Meeting on Crashworthy Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . Alexandria, VA, American Helicopter Society, 1986, 12 p. refs The evolution of program KRASH, developed under the A87-13669 sponsorships of the U.S. Army and the FAA, is described. The CREW SEAT STROKE REQUIREMENTS FOR HELICOPTER program, referred to as ’hybrid’, presents an approach which ROLLED AlTITUDE IMPACT CRASHWORTHINESS incorporates experimental data as input and provides for L. C. LAMBORN (McDonnell Douglas Helicopter Co., Mesa, AZ) approximate representations of complex structures and nonlinear IN: National Specialist’s Meeting on Crashworthy Design of behavior. The program’s applicability to rotary-wing, light fixed-wing, Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . Alexandria, and large transport aircraft is demonstrated. The updated version VA, American Helicopter Society, 1986, 5 p. of the program was used to support the Controlled Impact The systems approach to crashworthiness is applied to a study Demonstration test performed by the FAA and NASA. The new of crew seat stroke sensitivity for varied crash impact attitudes. program’s features, analytical models, and comparisons with test Using the computer program ’KRASH’ as a preliminary design data are presented. The use of the program in the course of tool, two three-dimensional helicopter models were created to developing design criteria and evaluating new material designs is develop seat stroke trends for vehicle impact attitudes including also addressed. I.S. pitch and roll. Due to the reduced energy absorbed by the landing gear and fuselage during impact conditions combining pitch and roll, the crew seat stroke requirements were found to be highly A87-13673 sensitive to vehicle attitude at impact. The maximum crew seat MODELLING STRATEGIES FOR FINITE ELEMENT CRASH stroke was found to be approximately two and one-half times the SIMULATION OF COMPLETE VEHICLES stroke for the no pitch, no roll crash. This trend becomes a design R. WINTER and A. B. PIFKO (Grumman Corporate Research driver for the cockpit and crew seat, and allowing for the ’extra’ Center, Bethpage, NY) IN: National Specialist’s Meeting on stroke is an absolute necessity for crashworthy helicopter design. Crashworthy Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, Author Proceedings . Alexandria, VA, American Helicopter Society, 1986, 6 P. This paper will discuss strategies and procedures for preparing finite element models for full vehicle crash simulation using nonlinear structural dynamic finite element computer codes. The limitations imposed on such models by existing computer systems, A87-13670 and the overall and specific procedures used to model full vehicles LANDING GEAR PERFORMANCE SIMULATION BY KRASH is outlined, based on experience with actual automobile and PROGRAM helicopter structures, using the DYCAST computer code. Results M. B. PRAMANIK and B. L. CARNELL (United Technologies Corp., are shown for a particular helicopter impact in comparison with test data. Author Sikorsky Aircraft Div., Stratford, CT) IN: National Specialist’s Meeting on Crashworthy Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . Alexandria, VA, American Helicopter A87-13674 Society, 1986, 6 p. KRASH ANALYSIS CORRELATION WITH FULL SCALE YAH-63 A computer program, KRASH-85, was used to simulate the HELICOPTER CRASH TEST dynamic performance of helicopter landing gear. To demonstrate V. L. BERRY and J. D. CRONKHITE (Bell Helicopter Textron, the validity of the method, several landing gears used on Sikorsky Fort Worth, TX) IN: National Specialist’s Meeting on Crashworthy helicopters have been modeled for the program. A retractable, Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . conventional oleo landing gear was simulated at 8 ft/s; a Alexandria, VA, American Helicopter Society, 1986, 14 p. refs crashworthy, swinging arm gear with dual-oleo shock strut was A full scale crash test of the YAH-63 prototype Advanced Attack simulated at 34.5 ft/s; and an articulating gear with both an oleo Helicopter, designed to requirements similar to MIL-STD-1290, is and a crushable honeycomb shock strut was simulated at 20 ft/s. described, and the test results on the crashworthiness performance A comparison of ground loads, drop mass displacements, and are compared with those obtained using KRASH-simulatedanalysis. impact velocities has demonstrated good correlation between the It is shown that the crashworthy landing gear, crushable structure, predicted and actual results. The KRASH program also predicts stroking seats, crashworthy fuel system, and high mass component the loads on all the structural members of the landing gear and retention all functioned successfully. The overall sequence of makes it possible to improve the accuracy of design and stress events and structural response time histories from the KRASH ana I y s i s . IS. analysis agreed well with the measured test data. IS.

90 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

A87-13675 A87-13821# CRASHWORTHY CREWSEAT LIMIT LOAD OPTIMIZATION STATUS REPORT OF A NEW RECOVERY PARACHUTE SYSTEM THROUGH DYNAMIC TESTING FOR THE Flll AIRCRAFT CREW ESCAPE MODULE J. W. COLTMAN, C. VAN INGEN (Simula, Inc., Phoenix, AZ), and D. W. JOHNSON (Sandia National Laboratories, Albuquerque, K. F. SMITH (U.S. Army, Aviation Applied Technology Directorate, NM) AIAA, Aerodynamic Decelerator and Balloon Technology Fort Eustis, VA) IN: National Specialist‘s Meeting on Crashworthy Conference, 9th, Albuquerque, NM, Oct. 7-9, 1986. 6 p. Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . (Contract AF PROJECT 84-10A-71) Alexandria, VA, American Helicopter Society, 1986, 10 p. refs (AIAA PAPER 86-2437) The objective of this research was to experimentally determine A new recovery parachute system for the F111 aircraft crew a limit-load setting for energy-absorbing seating systems that would escape module was designed at the Sandia National Laboratories minimize the incidence of spinal injury. The threshold of spinal in Albuquerque, New Mexico with the support of the U.S. Air Force. injury for seated humans subjected to vertical (+Gz) decelerative The design of the proposed system is presented, and the results loading was investigated. The +Gz loading was induced by of six proof-of-design tests are discussed. Test results indicate simulating impact conditions typically found in helicopter crashes that the parachute system will meet the 25 ft/sec at 5000 ft and was modified by the incorporation of energy-absorbing altitude descent velocity requirement specified in the draft mechanisms in the seat structure. Fifteen dynamic tests were Mil-Specs. The development program for the new recovery conducted with unembalmed cadavers at various limit-load settings parachute consists of 20 drop tests and one sled-launched ejection to identify the load threshold causing spinal injury. Vertebral test. The former will use a U.S. Air Force test vehicle that will be strength test results were used to normalize the data from the released from the NASA operated 852 aircraft. Testing is scheduled dynamic test program. A correlation was derived relating the to start in January 1987. K.K. frequency of spinal injury to the energy absorber limit-load factor. The results are applicable to the design of military and civilian crashworthy seating systems. Comparison of the incidence of spinal injury between the experimental cadaver data and field performance data on production energy-absorbing seats is discussed. Author

A87-13678 A87-13987# FULL SCALE CRASH TEST OF A BK117 HELICOPTER RESULTS OF HELICOPTER RESEARCH AT DFVLR M. ONlSHl and T. YOSHIMURA (Kawasaki Heavy Industries, Ltd., [ERGEBNISSE DER HUBSCHRAUBERFORSCHUNG IN DER Airframe Engineering Section, Gifu, Japan) IN: National Specialist’s DFVLR] Meeting on Crashworthy Design of Rotorcraft, Atlanta, GA. April B. GMELIN (DNLR, lnstitut fuer Flugmechanik, Brunswick, West 7-9, 1986, Proceedings . Alexandria, VA, American Helicopter Germany) and H. HELLER (DFVLR, lnstitut fuer Society, 1986, 9 p. refs Entwurfsaerodynamik, Brunswick, West Germany) BMFT, A full scale crash test of a BK117 helicopter was performed Statusseminar ueber Luftfahrtforschung und Luftfahrttechnologie, by dropping the helicopter from a height of 15 m above the ground Munich, West Germany, Apr. 28-20, 1986, Paper. 34 p. In ana using the originai periduiurii iileiiiud of crash tesiiiig. The German. refs instrumentation for obtaining data on the dynamic behavior of the Results obtained in the DFVLR middle-term (1 985-1990) helicopter structure and dummies consisted of the onboard helicopter-technology program are summarized, with a focus on accelerometer, high-speed motion picture cameras, and video the program areas flight simulation, wind-tunnel simulation, and cameras. External coverage of the crash sequence was provided rotor aeroacoustics. Consideration is given to the conversion of by ground-based fixed cameras. The analysis has established the the BO 105-S3 to an Advanced Technology Testing Helicopter actual resultant impact velocity of 75.5 m/sec and the actual System (ATTHeS) with model-following control system, the ground attitude at the impact of 5.7-deg pitch up, 0.9-deg roll right, 2.2-deg simulation testing of the control system at NASA Ames, AlTHeS yaw left. The results showed that the helicopter has a good simulations of roll damping and roll control moments, wind-tunnel protective shell and provides sufficient (by the criteria of the tests of optimized rotor blades and higher-harmonic rotor-control MIL-STD-1290) occupiable volume during severe crash loading. systems, and aeroacoustic wind-tunnel tests. T.K. The maximum dynamic response index for the occupants was 35, as opposed to the value of 21 recommended by Sen et al. (1985). I.S.

A87-13679 THE DESIGN AND QUALIFICATION TESTING OF AN ENERGY-ABSORBING SEAT FOR THE NAVY’S H-53 AID A87-13992# HELICOPTERS THE AMPHIBIAN TECHNOLOGY TEST VEHICLE - SUMMARY S. J. SHANE (Sirnula, Inc., Phoenix, AZ) and B. L. CARNELL AND RESULTS [AMPHIBISCHER TECHNOLOGIETRAEGER (United Technologies Corp., Sikorsky Aircraft Div., Stratford, CT) (Am- ZUSAMMENFASSUNG UND ERGEBNISSE] IN: National Specialist’s Meeting on Crashworthy Design of G. KRIECHBAUM (Dornier GmbH, Friedrichshafen, West Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . Alexandria, Germany) BMFT, Statusseminar ueber Luftfahrtforschung und VA, American Helicopter Society, 1986, 10 p. refs Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, The design and qualification testing of an armored Paper. 29 p. In German. energy-absorbing crewseat for retrofit to the US. Navy’s H-53 The development and testing of an experimental amphibian AID helicopters are described. Design aspects described include aircraft (AT) based on the Do 24 are described, summarizing the the composite armor system and the energy absorption systems. results obtained in phases I (1979-1980) and II (1980-1984) of Energy absorption in the vertical direction is used to limit the the R&D program. Consideration is given to land tests, inland-water forces on the occupant and in the forward direction to limit the and high-sea tests (demonstrating the improved seaworthiness of loads on the seat attachments to not exceed the floor strength of the ATT vis a vis amphibians now in service), the ATT the existing aircraft. Qualification testing of the seat included advanced-technology wing (using the Do A-5 profile employed in operational, static, ballistic, environmental and dynamic tests. Data the Do 228), the performance of turboprop engines with inertial presented from the static testing includes performance of both waterhe separators, the use of corrosion-resistant materials and the vertical and forward energy-absorbing systems. The dynamic anticorrosion treatment, and tests of CFRP and GFRP structural tests series included three vertical tests using 5th-, 50th-, and components. Graphs, drawings, and photographs are provided, 95th-percentile anthropomorphic dummies, and a single horizontal and the implications of the results for the cost-effective design of test, using a 95th-percentile dummy. Author future amphibians are discussed. T.K.

91 A87-13993# The measurement system and avionics are discussed, and the DEVELOPMENT OF A GFRP WING IN ACCORDANCE WITH economics of ATTAS are briefly addressed. C.D. FAR PART 23 [ ENTWICKLUNG EINES GLASFASERTRAGFLUEGELS NACH FAR PART 231 A87-14008# H. LUCAS (Claudius Dornier Seastar GmbH und Co., MODELS FOR ROTOR AND HELICOPTER DESIGN [MODELLE Oberpfaffenhofen, West Germany) BMFT, Statusseminar ueber ZUR ROTOR- UND HUBSCHRAUBERBERECHNUNGI Luftfahrtforschung und Luftfahrttechnologie, Munich, West G. REICHERT, K. LIESE, and J. EWALD (Braunschweig, Germany, Apr. 28-30, 1986, Paper. 31 p. In German. refs Technische Universitaet, Brunswick, West Germany) BMFT, (Contract BMFT-LFK-8531) Statusseminar ueber Luftfahrtforschung und Luftfahrttechnologie, The design and fabrication of a GFRP wing for the 4.2-tonne Munich, West Germany, Apr. 28-30, 1986, Paper. 59 p. In Seastar amphibian aircraft are reported. The cost advantages (in German. refs material and processing) of GFRP systems (hardening at The use of models to calculate parameters of interest in rotor 0.7-0.9-bar air pressure) over CFRP systems (requiring autoclave and helicopter design is discussed. The influence of models on processing) are explained; the ability of a GFRP wing to meet the the trim and performance values is addressed with regard to rotor FAR Part 23 requirements is discussed; and the development of geometry, blade degree of freedom, rotor downwash and tip loss, a damage-tolerant three-spar sandwich-skin wing structure with and measurement polarities for rotor blade and airframe. Data projected service life 30,000 h is described and illustrated with reduction in flight performance measurements for hover flight and drawings. The static and fatigue tests of the wing planned for forward flight is discussed. C.D. summer 1986 are listed, and consideration is given to the fabrication of the GFRP-forming tools. T.K. A87-14012# TESTING OF FIBER-REINFORCEDCONSTRUCTION ELEMENTS A87-13997# - SIMULATION OF MECHANICAL LOADS AND DEVELOPMENT AND TESTING OF CRITICAL COMPONENTS ENVIRONMENTAL INFLUENCES [PRUEFUNG VON FOR THE TECHNOLOGICAL PREPARATION OF A CFK OUTER FASERVERBUNDBAUTEILEN - SIMULATION VON WING [ENTWICKLUNG UND ERPROBUNG VON KRlTlSCHEN MECHANISCHEN BELASTUNGEN UND KOMPONENTEN ZUR TECHNOLOGISCHEN VORBEREITUNG UMWELTEINFLUESSEN] EINES CFK-AUSSENFLUEGELS] K. WOITHE (Industrieanlagen-Betriebsgesellschaft mbH, Munich, H. SCHNELL (Messerschmitt-Boelkow-Blohm GmbH, Bremen, West Germany) BMFT, Statusseminar ueber Luftfahrtforschung West Germany) BMFT, Statusseminar ueber Luftfahrtforschung und Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, und Luftfahrttechnologie. Munich, West Germany, Apr. 28-30, 1986, Paper. 17 p. In German. Paper. 22 p. In German. A test facility for fiber-reinforced construction elements is (Contract BMFT-LFK-85508) described, and its application is demonstrated. The systems for (MBB-UT-224-86) air circulation, tempering, moistening, control, and loading are The most important technological issues concerning the described, and important design data are given. Illustrative tests development of a CFK outer wing box and corresponding solution on the fiberglass fuselage of the Seastar amphibious aircraft and approaches are discussed. Components developed and perfected on the fiberglass wings of the Speed Canard, a two-seater canard in order to manage the problem of highly loaded joints in the airplane, are described, and results are presented. C.D. disconnection area between metal and CFK wings and the problem of the stability behavior of stiffened shells with high load A87-14014# characteristic values are presented and discussed. First results ESSY - AN ELECTROMECHANICAL ADJUSTMENT SYSTEM from load tests are reported. C.D. FOR AIRCRAFT CONTROL SURFACES [ESSY - EIN ELEKTROMECHANISCHES STELLSYSTEM FUER STEUERFLAECHEN VON FLUGZEUGEN] G. QUANDT (Teldix GmbH, Heidelberg, West Germany) and E. A87-14002# PIEPKA (Zahnradfabrik Friedrichshafen AG. West Germany) LOAD LIGHTENING AND FLUTTER DAMPING FOR FUTURE BMFT, Statusseminar ueber Luflfahrtforschung und AIRBUS PROJECTS [LASTMINDERUNG UND FLATTER- Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, DAEMPFUNG FUER ZUKUENFTIGE AIRBUSPROJEKTE] Paper. 32 p. In German. W. KOLANDER (Messerschmitt-Boelkow-Blohm GmbH, Hamburg, (Contract BMFT-LFL-8571-0) West Germany) BMFT, Statusseminar ueber Luftfahrtforschung The electromechanical adjustment system ESSY, a und Luftfahrttechnologie,Munich, West Germany, Apr. 28-30. 1986. future-oriented alternative to hydraulic adjustment actuation of Paper. 50 p. In German. refs aircraft control surfaces, is described. The system specifications (Contract BMFT-LFK-8360) are summarized, and the adjustment actuation and its components (MBB-UT-004-86) are described, including the requirements and dimensioning of the Existing rudders, flaps, and spoilers are investigated in order brushless direct-current motor, the actuator layout, the brake, the to determine their suitability as control surfaces, and existing actuator electronics, and the monitor. The test facilities for the systems are studied to see how they could be used as components system are summarized, the testing of the system is described, in load-lightening and flutter-damping systems. Advances made to and the adjustments made due to the test results are reviewed. achieve greater flight economies are reviewed, and their C.D. significance for Airbus technology is considered. C.D. A87-14016# A87-14003# TESTING A TAIL ROTOR SYSTEM IN FIBER-REINFORCED ATTAS - THE NEW TEST BED [ATTAS - DER NEUE CONSTRUCTION MANNER [ERPROBUNG EINES ERPROBUNGSTRAEGER] HECKROTORSYSTEM IN FASERVERBUNDBAUWEISE] P. HAMEL (DFVLR, lnstitut fuer Flugmechanik, Brunswick, West V. KLOEPPEL and B. ENENKL (Messerschmitt-Boelkow-Blohm Germany) and H. KRUEGER (DFVLR. Cologne, West Germany) GmbH, Munich, West Germany) BMFT, Statusseminar ueber BMFT, Statusseminar ueber Luftfahrtforschung und Luftfahrtforschung und Luftfahrttechnologie, Munich, West Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, Germany, Apr. 28-30,1986, Paper. 25 p. In German. refs Paper. 47 p. In German. refs A fiber-reinforced experimental version of a bearingless tail The AlTAS (Advanced Technologies Testing Aircraft System) rotor was developed in order to improve aerodynamic effectiveness, is discussed. The energy supply is addressed, including the structural simplicity, weight, and costs. A four-bladed, soft inplane hydraulics, electronics, and orientation system. The fly-by-wire light bearingless rotor was selected. An extended ground test program system is described, including terminal functions and computer. is described using results based on precessional motion and

92 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE simulation of ground resonance conditions. Finally, ground and A87-14026# flight tests performed on a BK 117 are reviewed. C.D. DESIGN AND MANUFACTURING OF A CFRP TAIL FIN FOR THE A300 [BAUWEISE UND FERTIGUNGSVERFAHREN DES A3OO-SEITENLEITWERKS IN KOHLEFASERBAUWEISE] K.-H. HEIDTMANN (Messerschmitt-Boelkow-Blohm GmbH, Hamburg, West Germany) BMFT, Statusseminar ueber Luftfahrtforschung und Luftfahrttechnologie, Munich, West A87-14017# Germany, Apr. 28-30, 1986, Paper. 41 p. In German. DEVELOPMENT OF A NEW TYPE OF BEARINGLESS ROTOR (MBB-UT-006-86) SYSTEM [ENTWICKLUNG NEUARTIGER LAGERLOSER The design, manufacture, and testing of a CFRP tail fin for the ROTORSYSTEME] A300-310 transport aircraft are described and illustrated with H. STREHLOW and H. FROMMLET (Messerschmitt-Boelkow- photographs, drawings, diagrams, graphs, and tables of numerical Blohm GmbH, Munich, West Germany) BMFT, Statusseminar ueber data. Consideration is given to the selection of materials; the Luftfahrtforschung und Luftfahrttechnologie, Munich, West Germany, modular fabrication techniques used on the shells, ribs, spars, Apr. 28-30, 1986, Paper. 44 p. In German. refs. Work being done to develop an efficient, bearingless main rotor and fittings of the prototype fins (and taken over, for the most part, into the series manufacturing); and the procedures and results system for a light multipurpose helicopter is discussed. Two of static, dynamic, environmental, lightning-strike, and flight testing. bearingless rotors with different designs and blade angle steering After loading equivalent to three times the normal life of the aircraft, were tested on a test stand and on the BO 105 helicopter in no damage to the CFRP box-spar structure and no growth of the flight. Corresponding constructive and theoretical investigations artificially induced damage-zones were observed. The CFRP fin including necessary component tests were conducted. The results has been in use on line aircraft since December 1985. T.K. are used to define a final prototype, stressing the aerodynamic and structural system optimization. The eventual bearingless rotor will have a new blade form and the DM-H3 and DM-H4 profiles. C.D. A87-14027# NEW FUSELAGE TECHNOLOGIES FOR GENERAL-AVIATION AIRCRAFT [NEUE RUMPFTECHNOLOGIEN FUER FLUGZEUGE DER ALLGEMEINEN LUFTFAHRT] A87- 140 18# K. H. DOST, D. WELTE, and 6. WAGNER (Dornier GmbH, ACTUATING SYSTEM WITH DIGITAL SIGNAL CONVERTERS Friedrichshafen, West Germany) BMFT, Statusseminar ueber AND FIBER-OPTIC CONTROL [STELLANTRIEB MlT DIGITALEN Luftfahrtforschung und Luftfahrttechnologie, Munich, West SIGNALWANDLERN UND LICHTLEITERANSTEUERUNG] Germany, Apr. 28-30, 1986, Paper. 47 p. In German. refs TH. ANNESER and H. MANG (Liebherr-Aero-Technik GmbH, The current status of a BMFT R&D program begun in 1985 to Lindenberg im Allgaeu, West Germany) BMFT, Statusseminar extend advanced design principles and fabrication techniques to ueber Luftfahrtforschung und Luftfahrttechnologie, Munich, West the fuselages of light passenger aircraft is reported, and wind-tunnel +ne,- C.,- &,..A.."- -rrlAr ..-r Ai,.-.. rrrl D-'-r.... ^I Germany, Apr 28-30. 1986, Paper 29 p In Gerrngn .." ,"u iuariayc; llluuvla amc; umauu~aru.riiiiiaiy yvals S: the Preliminary results of developmental studies on advanced present phase of the fuselage program (to be completed in 1988) aircraft actuating systems are summarized. The limitations of are improved aerodynamics, cost-effective structural realization (low conventional electrohydraulic systems are reviewed; the fiber-optic fabrication costs, low weight, and high reliability with little transmission of control signals to the actuator is discussed; maintenance), and reduced internal noise. Two-abreast and actuators with piezoelectric bending elements are described; and three-abreast versions of a 19-passenger aircraft based on the the principles of digital control are explained. Graphs, drawings, Do-228 have been designed, and mechanical testing of a CFRP tables of numerical data, and flow charts are provided, and the front half is underway. The definition, construction, and wind-tunnel results of computer simulations of the control performance are testing of 1:8 models of these two configurations are described included. T.K. and illustrated with drawings, photographs, and graphs; and the determination of fabrication tolerances on the basis of both aerodynamic considerations and technical limitations is considered. T.K. A87-14025# A REDUNDANT ACTUATING SYSTEM WITH SERVO VALVES OF LOW HYDRAULIC LOSS [REDUNDANTES STELLANTRIEBSSYSTEM MIT SERVOVENTILEN NlEDRlGER A87-14033# HYDRAULISCHER VERLUSTLEISTUNG] GUST AND MANEUVER SPECTRA FOR GENERAL AVIATION G. DIESSEL and H. MUELLER (Feinmechanische Werke Mainz AIRCRAFT GmbH, West Germany) BMFT, Statusseminar ueber W. M. REYER and J. OGG (Kansas, University, Lawrence) AIAA, Luftfahrtforschung und Luftfahrttechnologie, Munich, West General Aviation Technology Conference, Anaheim, CA, Sept. Germany, Apr. 28-30, 1986, Paper. 35 p. In German. 29-Oct. 1, 1986. 6 p. refs The operating principle, design, development status, and (AIAA PAPER 86-2599) preliminary performance of a redundant electrohydraulic actuating Gust- and maneuver-induced loading spectra are presented for system for transport-aircraft ailerons are presented. The system various aircraft operations in the general aviation category. These employs two identical actuating systems (comprising single-stage spectra depict the cumulative frequency of incremental acceleration linear-motor-driven servo valves, bypass and anticavitation valves, (departure from 1-g flight condition) occurrence as a function of actuating cylinders with two displacement pickups, and electrical incremental acceleration magnitude. The spectra were derived from control and monitoring hardware), each supplying 75 percent of the data base collected in the NASA VGH General Aviation the required actuating force. Active, passive, and damped operating Program. The information represented by the gust and maneuver modes; signal flow; fly-by-wire system architecture; preflight and spectra can be used in the analytical determination of aircraft inflight monitoring; options evaluated in designing the individual fatigue life. The cumulative frequency of occurrence gives the components; and test procedures and results are described and number of cycles the aircraft structure experiences. The incremental illustrated with drawings, circuit diagrams, graphs, and tables of acceleration magnitude is a factor in determining the magnitude numerical data. Preliminary results indicate actuating force 650 of the alternating stresses in the structure. Comparisons are made and 720 N at current 4 and 6 A, respectively, with internal leakage with existing gust and maneuver spectra, with the conclusion made less than 0.15 l/min at flow rate 13.8 l/min and supply pressure that the gust and maneuver environments which contribute to 21 0 bar. T.K. aircraft fatigue are more severe that previously indicated. Author

93 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

A87-14036'# National Aeronautics and Space Administration. A87-14717 Langley Research Center, Hampton, Va. A STUDY OF THE EFFECT OF SURFACE ROUGHNESS ON POTENTIAL INFLUENCES OF HEAVY RAIN ON GENERAL THE HEAD RESISTANCE OF AN AIRCRAFT [ISSLEDOVANIE AVIATION AIRPLANE PERFORMANCE VLllANllA SHEROKHOVATOSTI POVERKHNOSTI NA R. E. DUNHAM, JR. (NASA, Langley Research Center, Hampton, LOBOVOE SOPROTIVLENIE SAMOLETA] VA) AIAA, General Aviation Technology Conference, Anaheim, R. I. ZUKAKISHVILI, A. M. ILLARIONOV, and V. IA. BELIAEV CA, Sept. 29-Oct. 1, 1986. 8 p. refs (Gruzinskii Politekhnicheskii Institut, Tbilisi, Georgian SSR) (AIAA PAPER 86-2606) Akademiia Nauk Gruzinskoi SSR, Soobshcheniia (ISSN 0132-1447), Recent NASA wind tunnel tests of airfoils in a simulated rain vol. 122, May 1986, p. 357-360. In Russian. environment under extremely heavy rain conditions have shown The effect of the roughness of a painted surface on the head reductions in maximum lift and increases in drag. Conventional resistance of an aircraft is investigated by using a physical model airfoils were tested with and without high lift devices and tests of of flow past such a surface. It is found that a surface roughness laminar-flow airfoils without high-lift devices were conducted. Both of 2-10 microns has a noticeable effect on the head resistance of types of airfoils indicated performance decrements when exposed the aircraft and that the density of the surface projections to a simulated heavy rain environment. For the laminar flow airfoil, determines the friction coefficient increment. It is further shown the rain influence was observed to occur throughout the angle of that the use of polyurethane coatings, rather than paint coatings, attack range, whereas for the conventional airfoil in a high lift makes it possible to reduce the head resistance of the aircraft configuration, the rain influence occurred mostly at the higher and its fuel consumption by 2 percent. V.L. angles of attack. The performance decrement for the laminar-flow airfoil appeared to be a result of laminar-to-turbulentboundary-layer transition whereas the performance penalty for the conventional airfoil appeared to be the result of premature separation. The results of these tests are presented and the implication of the results to general aviation airplanes are discussed. Author

A87-14103*# California Univ., Los Angeles. A87-14925' Virginia Polytechnic Inst. and State Univ., APPLICATION OF TIME-DOMAIN UNSTEADY AERODYNAMICS Blacksburg. TO ROTARY-WING AEROELASTICITY ANALYTICAL MODEL FOR INVESTIGATION OF INTERIOR M. A. H. DlNYAVARl and P. P. FRIEDMANN (California, University, NOISE CHARACTERISTICS IN AIRCRAFT WITH MULTIPLE Los Angeles) (Structures, Structural Dynamics and Materials PROPELLERS INCLUDING SYNCHROPHASING Conference, 26th, Orlando, FL, April 15-1 7, 1985, Technical Papers. C. R. FULLER (Virginia Polytechnic Institute and State University, Part 2, p. 522-535) AIAA Journal (ISSN 0001-1452), vol. 24, Sept. Blacksburg) Journal of Sound and Vibration (ISSN 0022-46OX), 1986, p. 1424-1432. Previously cited in issue 13, p. 1849, Accession vol. 109. Aug. 22, 1986, p. 141-156. refs no. A85-30380. refs (Contract NAG1-390) (Contract NAG2-209) A simplified analytical model of transmission of noise into the interior of propeller-drivenaircraft has been developed. The analysis A87-14368# includes directivity and relative phase effects of the propeller noise AEROELASTIC DIVERGENCE OF TRIMMED AIRCRAFT sources, and leads to a closed form solution for the coupled L. T. NIBLETT (Royal Aircraft Establishment, Farnborough, motion between the interior and exterior fields via the shell England) Journal of Aircraft (ISSN 0021-8669), vol. 23, Sept. (fuselage) vibrational response. Various situations commonly 1986, p. 727, 728. encountered in considering sound transmission into aircraft A set of equations for an aircraft with unswept wings in an fuselages are investigated analytically and the results obtained idealized trimmed shallow pullout is subjected to static analysis to are compared to measurements in real aircraft. In general the identify the speed at which the equations become indeterminate. model has proved successful in identifying basic mechanisms The speed, which corresponds to the unconstrained divergence behind noise transmission phenomena. Author speed of the aircraft, is found to be high relative to the fixed-root divergence speed (FDS). Control problems may, however, arise at the lower FDS speed because the pitch angle is negative near the FDS, thus constraining lift to be obtained from the angle of attack due to torsion alone. The equations and the analytical techniques can be easily extended to forward-swept and tapered wing aircraft. M.S.K. A87- 15009 A87-14369*# National Aeronautics and Space Administration. ZONING OF AIRCRAFT FOR LIGHTNING ATTACHMENT AND Langley Research Center, Hampton. Va. CURRENT TRANSFER DYNAMIC LOADS ON TWIN JET EXHAUST NOZZLES DUE TO C. C. R. JONES (British Aerospace, PLC, Military Aircraft Div., SHOCK NOISE Warton, England), G. A. M. ODAM (Royal Aircraft Establishment, T. D. NORUM and J. G. SHEARIN (NASA, Langley Research Farnborough, England), and A. W. HANSON IN: International Center, Hampton, VA) Journal of Aircraft (ISSN 0021-8669). vol. Aerospace and Ground Conference on Lightning and Static 23, Sept. 1986. p. 728, 729. refs Electricity, 1lth, Dayton, OH, June 24-26, 1986, Technical Papers Acoustic near field data were collected with model single and . Fairborn, OH, National Interagency Coordination Group, 1986, p. twin jet nozzles to determine if closely spaced nozzles produce 11-1 to 11-1 3. Research supported by Culham Laboratory and higher acoustic loading than do single nozzles. The tests were British Aerospace, PLC. refs spurred by structural failure of the 6-1 exhaust nozzle external Currently accepted zonings of aircraft into regions of differing flaps and similar damage on the F-15. The test was performed susceptibility to lightning attachment and current transport were using two 518 in. ID pipes machined and placed side-by-side to originally determined on the basis of data on lightning strikes to mimic 6-1 nozzles. A microphone mounted on the internozzle fairing fixed-wing aircraft. It is presently suggested that the observations measured acoustic levels near the nozzle exit plane. The nozzles used in the original zoning work may have overlooked vital evidence oscillated significantly more than did a single nozzle over a wide more recently noted in tests tracing natural lightning attachment. range of nozzle pressure ratios. Acoustic levels in the dual jets Attention is also given to zoning criteria applicable to helicopters, exceeded single jet noise by as much as 20 dB. making acoustic VTOL aircraft, and delta-planform wing aircraft. An alternative set resonance a definite candidate for structural damage in the twin of zones based on incident threat rather than the lightning jet configuration. M.S.K. component at an attachment point is presented. O.C.

94 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

A87-15011 A87-15027# SIMULATED LIGHTNING CURRENT TESTS ON A LYNX EFFECT OF E-FIELD MILL LOCATION ON ACCURACY OF HELICOPTER ELECTRIC FIELD MEASUREMENTS WITH INSTRUMENTED C. J. HARDWICK, V. P. DUNKLEY (Culham Laboratory, Abingdon, AIRPLANE England), R. H. EVANS, J. S. P. HARDY, and R. A. HOBBS (Royal V. MAZUR (NOAA, National Severe Storms Laboratory, Norman, Aircraft Establishment, Farnborough, England) IN: International OK), L. H. RUHNKE (U.S. Navy, Naval Research Laboratory, Aerospace and Ground Conference on Lightning and Static Washington, DC), and T. RUDOLPH (Electromagnetic Applications, Electricity, 11th, Dayton, OH, June 24-26, 1986, Technical Papers Inc., Denver, CO) IN: International Aerospace and Ground . Fairborn, OH, National Interagency Coordination Group, 1986, p. Conference on Lightning and Static Electricity, 11th, Dayton, OH, 13-1 to 13-9. June 24-26, 1986, Technical Papers . Fairborn, OH, National Simulated lightning tests were carried out jointly by RAE and Interagency Coordination Group, 1986, p. 31-1 to 31-7. refs Culham Laboratory on a Lynx helicopter, involving the application It is common in airborne observations to measure the ambient of test current pulses up to 90 kA peak. The test current was electric field and self-charge of the instrumented airplane with applied by discharging a capacitor bank into the rotor head in two four field mills. In this case, the sensors' locations on the airplane alternative configurations to provide a current path from the rotor are critical for accurate measurement. It is shown that positioning head to either the tail or the wheels, corresponding to the most sensors on or near crossing points of the lines of the airplane's likely paths for a lightning strike. Extensive measurements of skin electrical symmetry (neutrality) decreases significantly the current densities on the helicopter for both configurations were amplification of errors in the signal processing system that are made. Measurement of transient-induced currents in seven wiring transferred into errors in the ambient field estimates. The looms showed good linearity against amplitude of fuselage current; calculations are made using the computer simulated model of the extrapolation to full-threat levels indicated somewhat higher levels NASA F-1066 research airplane placed in a uniform electric field. than those previously experienced. Author Two new calibration procedures for the net charge on the airplane are suggested. Author

A87-15037# ELECTROSTATIC FIELD MEASUREMENTS IN A FOAM FILLED A87-15012# C-130 FUEL TANK DURING FUEL SLOSHING PREDICTION OF SKIN CURRENTS FLOWING ON A LYNX A. R. BIGELOW, M. P. HEBERT, H. JlBlLlAN (USAF, Wright HELICOPTER DUE TO A SIMULATED LIGHTNING STRIKE Aeronautical Laboratories, Wright-Patterson AFB, OH), and J. S. A. MALLIK (Kimberley Communications Consultants, Nottingham, REAZER (Technology/Scientific Services, Inc., Dayton, OH) IN: England), C. CHRISTOPOULOS (Nottingham University, England), International Aerospace and Ground Conference on Lightning and and J. M. THOMSON (Royal Aircraft Establishment, Farnborough, Static Electricity, 1lth, Dayton, OH, June 24-26, 1986, Technical England) IN: International Aerospace and Ground Conference Papers . Fairborn, OH, National Interagency Coordination Group, on Lightning and Static Electricity, 1lth, Dayton, OH, June 24-26, 1986, p. 47-1 to 47-6. 1986, Technical Papers . Fairborn, OH, National Interagency The electric field inside a (2-130 external fuel tank has been Coordination Group, 1986, p. 14-1 to 14-7. Research supported measured during fuel sloshing by means of five flush plate dipole by !he !!inis!!-; e! De!e~se (P:ec~reme~!Execu!ive). refs sensors, In order to ascertain the electrostatic charging A simulated lightning strike on a Lynx helicopter is presently characteristics of the tank's explosion-suppressant foam. Two foam modeled by means of a three-dimensional transmission line configurations were tested: the currently operational nonconductive modeling program which has proved capable of identifying the foam and an experimental conductive foam. Electric fields as high origin of the three principal resonances reported in measurements as 136 kV/m were recorded during slosh tests with the elsewhere. All three resonances are noted to be affected by the nonconductive foam at 600-gal fuel levels; no measurable fields charging circuit, which is constituted by the return conductor, the were recorded with the conductive foam. Two electrostatic ground plane, and the capacitor bank; the configuration of the discharges and ignitions occurred during testing of the experimental facility will accordingly strongly affect the three nonconductive foam, while none occurred during the principal resonances. O.C. conductive-foam testing. O.C.

A87-15181 MANUFACTURERS PLAN NEW LONG-RANGE AIRCRAFT A87-15018'# National Aeronautics and Space Administration. B. SWEETMAN and P. CONDOM Exxon Air World, vol. 38, no. Langley Research Center, Hampton, Va. 2, 1986, p. 16-19. JOINT THUNDERSTORM OPERATIONS USING THE NASA The development of long-range aircraft with increased-thrust F-106B AND FAATWAFWAL CONVAIR 580 AIRPLANES low-fuel-consumptionengines is discussed. Twin-engine aircraft are B. D. FISHER, P. W. BROWN (NASA, Langley Research Center, being permitted to travel new routes, and aircraft with increased Hampton, VA), A. J. WUNSCHEL, JR. (USAF, Systems Command, range are being manufactured. The designs of twin aircraft with Andrews AFB, MD), H. D. BURKET (USAF, Wright Aeronautical 10,600-km and 11,300-1 2,050-km ranges are examined. Laboratories, Wright-Patterson AFB, OH), and J. S. TERRY (FAA, Long-range trijets with capabilities of 12,400 and 13,900 km are Technical Center, Atlantic City, NJ) IN: International Aerospace being constructed. I.F. and Ground Conference on Lightning and Static Electricity, 1lth. Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, A87-15205 National Interagency Coordination Group, 1986, p. 20-1 to 20-10. MATHEMATICAL MODELING OF THE MOTION OF A refs STATICALLY DEFORMED DELTA-SHAPED GLIDER During the 1985 thunderstorm season, three joint thunderstorm [MATEMATICHESKOE MODELIROVANIE DVlZHENllA research flights were conducted within 100 nmi. of NASA Langley STATICHESKI DEFORMIRUEMOGO DEL'TAPLANAI by the NASA Storm Hazards F-106B and the FAAIUSAF CV-580 1. I. BUKHTOIAROV, V. I. MOROZOV, and A. I. PONOMAREV research airplanes with ground-based weather radar measurements Aviatsionnaia Tekhnika (ISSN 0579-2975), no. 2, 1986, p. 24-28. by NASA Wallops. This paper discusses the thunderstorm In Russian. refs penetration capabilities of each airplane and the techniques used Nonlinear equations are presented which describe the to safely place the two airplanes into the same thunderstorm cell three-dimensional motion of a power version of the delta-shaped for collection of correlated EM data. It is concluded that joint glider with allowance for the static deformation of the structure thunderstorm research operations of two aircraft with significantly and balancing control. The elastic displacements of the glider frame dissimilar thunderstorm penetration capabilities are are determined by using the finite element method; the changes counterproductive to both airplanes. Author in the shape of the fabric covering are considered in an approximate

95 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

manner; the nonlinear stationary aerodynamic characteristics are g-control law with pitch-rate feedback originally developed by calculated by using the discrete vortex method. V.L. NASA. AS a whole, the most significant capability of the A320 flight control System is its ability to protect the aircraft from stalling, A87-15214 overspeeding, overloading, excessive attitudes, and windshear A SYSTEM MODEL, A LOGIC DESIGN DIAGRAM, AND A conditions. O.C. GENERAL SYNTHESIS ALGORITHM FOR OPTIMAL SYSTEMS OF ONBOARD ELECTRICAL EQUIPMENT IN COMPUTER-AIDED A87-16400 DESIGN [SISTEMNAIA MODEL', LOGICHESKAIA SKHEMA V-22 OSPREY - MULTI-SERVICE WORKHORSE PROEKTlROVANllA I OBSHCHll ALGORITM SINTEZA J. MOXON Flight International (ISSN 0015-3710), vol. 130. Aug. OPTIMAL'NYKH SISTEM BORTOVOGO KOMPLEKSA 30, 1986, p. 154-157. ELEKTROOBORUDOVANIIA V SAPR] An account is given of the development history and existing V. S. TERESHCHUK Aviatsionnaia Tekhnika (ISSN 0579-2975), deployment plans for the V-22 tilt-rotor VTOL aircraft; these no. 2, 1986, p. 62-68. In Russian. services will employ it as an assault troop transport, ASW platform, The structure of an onboard electrical complex is described by supply transport and field hospital. Attention is given to the a model based on the geometrical and structural aspects of the extensive use of commposites to maintain minimum weight, the system. The structural model consists of a tree of components performance advantages of the T406 powerplant, the projected based on the geometrical decomposition of the system and trees flight envelope, and the winghotor blade stowage feature for of external and internal circuits. A system model is implemented shipboard use. O.C. by formalizing the solution of interrelated design problems in the form of a logical design scheme. V.L. A87-16408 A REVIEW OF THE TECHNICAL DEVELOPMENT OF A87-15220 CONCORDE A SIMULATION OF THE DYNAMICS OF THE MECHANISMS C. S. LEYMAN (British Aerospace, PLC, Civil Div., Bristol, OF THE AIRCRAFT LANDING GEAR [MODELIROVANIE England) Progress in Aerospace Sciences (ISSN 0376-0421), DlNAMlKl MEKHANIZMOV SHASSI SAMOLETA] vol. 23, no. 3, 1986, p. 185-238. refs V. V. BERDNIKOV and I. P. IAKUPOVA Aviatsionnaia Tekhnika The technical problems encountered during the development (ISSN 0579-2975), no. 2, 1986, p. 86, 87. In Russian. and certification of Concorde are reviewed. The topics covered A simulation of the dynamics of landing gear mechanisms is are mainly associated with aerodynamics, but other areas are carried out using a set of application software for modeling the discussed where they interact with the aerodynamic design or if kinematics and kinestatics of the landing gear mechanisms, with there were conditions peculiar to supersonic transportation which an additional module used for modeling the operation of the had to be considered. Author mechanisms during the lowering and retraction of the landing gear. Since the dynamic characteristics of the mechanisms depend to N87-11717'# National Aeronautics and Space Administration. a large degree on the characteristics of the hydraulic drive and Langley Research Center, Hampton, Va. its feed system, the simulation uses a sufficiently accurate RECENT EXPERIENCES IN MULTlDlSClPLlNARY ANALYSIS mathematical model of the hydraulic drive. The dynamic simulation AND OPTIMIZATION, PART 1 of the landing gear mechanisms makes it possible to identify the J. SOBIESKI. comp. 1984 517 p Symposium held in Hampton, operating conditions that involve particularly high stresses and then Va., 24-26 Apr. 1984 use the results to improve the performance of the landing gear. (NASA-CP-2327-PT-1; NAS 1532327-PT-1) Avail: NTlS HC V.L. A22/MF A01 CSCL 01C Papers presented at the NASA Symposium on Recent A87-15424 Experiences in Multidisciplinary Analysis and Optimization held at ASSESSING THE RIM ATTRIBUTES OF ADVANCED NASA Langley Research Center, Hampton, Virginia April 24 to STRUCTURES 26, 1984 are given. The purposes of the symposium were to T. N. COOK (United Technologies Corp., Sikorsky Aircraft Div., exchange information about the status of the application of Stratford, CT) and T. E. CONDON (US. Army, Aviation Applied optimization and associated analyses in industry or research Technology Directorate, Fort Eustis, VA) IN: 1986 Annual laboratories to real life problems and to examine the directions of Reliability and Maintainability Symposium, Las Vegas, NV, January future developments. Information exchange has encompassed the 28-30, 1986, Proceedings . New York, Institute of Electrical and following: (1) examples of successful applications; (2) attempt and Electronics Engineers, Inc., 1986. p. 312-31 7. failure examples; (3) identification of potential applications and A methodology has been developed to assess the R&M benefits; (4) synergistic effects of optimized interaction and attributes of advanced composite structures. The method begins trade-offs occurring among two or more engineering disciplines with a definition of the impact-related hazards to which the structure and/or subsystems in a system; and (5) traditional organization of will be exposed in service and the frequency and intensity of the a design process as a vehicle for or an impediment to the progress impact exposures. The frequency and severity of the inflicted in the design methodology. damage are predicted on the basis of empirically-developed damage vs. impact energy curves. These predictions are used to N87-11719"# Lockheed-Georgia Co., Marietta. derive damage rates and repair costs for use in life-cycle cost OPTIMIZATION IN THE SYSTEMS ENGINEERING PROCESS studies and design tradeoffs. The reparability attributes of an L. A. LEMMERMAN ln NASA. Langley Research Center Recent advanced structure are assessed through an analysis of four key Experiences in Multidisciplinary Analysis and Optimization. Part 1 design variables: type of structure, design loading condition, margin 16p 1984 of safety, and repair access. A mapping procedure is used to Avail: NTlS HC A22/MF A01 CSCL 01C quantify the reparability of small-area and large-area damage. The objective is to look at optimization as it applies to the Author design process at a large aircraft company. The design process at Lockheed-Georgia is described. Some examples of the impact A87-16394 that optimization has had on that process are given, and then A320 - FLY-BY-WIRE AIRLINER some areas that must be considered if optimization is to be G. WARWICK Flight International (ISSN 0015-3710), vol. 130, successful and supportive in the total design process are indicated. Aug. 30. 1986, p. 86-90, 93, 94. Optimization must continue to be sold and this selling is best An account is given of the design features, performance done by consistent good performance. For this good performance capabilities and market prospects of the A320, with attention to to occur, the future approaches must be clearly thought out so the fly-by-wire system it incorporates to improve handling qualities that the optimization methods solve the problems that actually and reduce pilot workload. The A3203 pitcn-control law is a occur during design. The visibility of the design process must be

96 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE maintained as further developments are proposed. Careful attention conceptual design of an aircraft involves a complex trade-off of must be given to the management of data in the optimization many independent variables that must be investigated before process, both for technical reasons and for administrative purposes. deciding upon the basic configuration. Some of these variables Finally, to satisfy program needs, provisions must be included to are discrete (number of engines), some represent different supply data to support program decisions, and to communicate configurations (canard vs conventional tail) and some may with design processes outside of the optimization process. If represent incorporation of new technologies (aluminum vs designers fail to adequately consider all of these needs, the future composite materials). At Lockheed-Georgia, the sizing program is acceptance of optimization will be impeded. Author known as GASP (Generalized Aircraft Sizing Program). GASP is a large program containing analysis modules covering the many N87-11720*# Douglas Aircraft Co., Inc., St. Louis, Mo. different disciplines involved fin defining the aricraft, such as PRACTICAL CONSIDERATIONS IN AEROELASTIC DESIGN aerodynamics, structures, stability and control, mission B. A. ROMMEL and A. J. DODD In NASA. Langley Research performance, and cost. These analysis modules provide first-level Center Recent Experiences in Multidisciplinary Analysis and estimates the aircraft properties that are derived from handbook, Optimization, Part 1 12 p 1984 experimental, and historical sources. Author Avail: NTlS HC A22/MF A01 CSCL 01C The structural design process for large transport aircraft is described. Critical loads must be determined from a large number N87-11723'# National Aeronautics and Space Administration. of load cases within the flight maneuver envelope. The structural Langley Research Center, Hampton, Va. design is also constrained by considerations of producibility, EXPERIENCES PERFORMING CONCEPTUAL DESIGN reliability, maintainability, durability, and damage tolerance, as well OPTIMIZATION OF TRANSPORT AIRCRAFT as impact dynamics and multiple constraints due to flutter and P. D. ARBUCKLE and S. M. SLIWA In its Recent Experiences aeroelasticity. Aircraft aeroelastic design considerations in three in Multidisciplinary Analysis and Optimization, Part 1 15 p distinct areas of product development (preliminary design, 1984 advanced design, and detailed design) are presented and Avail: NTlS HC A22/MF A01 CSCL 01C contrasted. The present state of the art is challenged to solve Optimum Preliminary Design of Transports (OPDOT) is a the practical difficulties associated with design, analysis, and computer program developed at NASA Langley Research Center redesign within cost and schedule constraints. The current practice for evaluating the impact of new technologies upon transport consists of largely independent engineering disciplines operating aircraft. For example, it provides the capability to look at with unorganized data interfaces. The need is then demonstrated configurations which have been resized to take advantage of active for a well-planned computerized aeroelastic structural design controls and provide and indication of economic sensitivity to its optimization system operating with a common interdisciplinary data use. Although this tool returns a conceptual design configuration base. This system must incorporate automated interfaces between as its output, it does not have the accuracy, in absolute terms, to modular programs. In each phase of the design process, a common yield satisfactory point designs for immediate use by aircraft finite-element model for static and dynamic optimization is required manufacturers. However, the relative accuracy of comparing to reduce errors due to modeling discrepancies. As the design OPDOT-generated configurations while varying technological proceeds from the simple models in preliminary design to the assumptions has been demonstrated to be highly reliable. Hence, more complex models in advanced and detailed design, a means OPDOT is a useful tool for ascertaining the synergistic benefits of of retrieving design data from the previous models must be active controls, composite structures, improved engine efficiencies established. Author and other advanced technological developments. The approach used by OPDOT is a direct numerical optimization of an economic N87-11721*# McDonnell Aircraft Co., St. Louis, Mo. performance index. A set of independent design variables is FLUlTER OPTIMIZATION IN FIGHTER AIRCRAFT DESIGN iterated, given a set of design constants and data. The design W. E. TRIPLETT In NASA. Langley Research Center Recent variables include wing geometry, tail geometry, fuselage size, and Experiences in Multidisciplinary Analysis and Optimization, Part 1 engine size. This iteration continues until the optimum performance 17p 1984 index is found which satisfies all the constraint functions. The Avail: NTlS HC A22/MF A01 CSCL 01C analyst interacts with OPDOT by varying the input parameters to The efficient design of aircraft structure involves a series of either the constraint functions or the design constants. Note that compromises among various engineering disciplines. These the optimization of aircraft geometry parameters is equivalent to compromises are necessary to ensure the best overall design. To finding the ideal aircraft size, but with more degrees of freedom effectively reconcile the various technical constraints requires a than classical design procedures will allow. Author number of design iterations, with the accompanying long elapsed time. Automated procedures can reduce the elapsed time, improve productivity and hold the promise of optimum designs which may N87-11725'# Boeing Commercial Airplane Co.,Seattle, Wash. be missed by batch processing. Several examples are given of PIAS: A PROGRAM FOR AN ITERATIVE AEROELASTIC optimization applications including aeroelastic constraints. Particular SOLUTION attention is given to the success or failure of each example and M. E. MANRO ln NASA. Langley Research Center Recent the lessons learned. The specific applications are shown. The Experiences in Multidisciplinary Analysis and Optimization, Part 1 final two applications were made recently. Author 15p 1984 Avail: NTlS HC A22/MF A01 CSCL 01C N87-11722'# Lockheed-Georgia Co., Marietta. A Program for an Iterative Aeroelastic Solution (PIAS) is APPLICATION OF THE GENERALIZED REDUCED GRADIENT discussed. This will be a modular computer program that combines METHOD TO CONCEPTUAL AIRCRAFT DESIGN the use of a finite-element structural analysis code with any linear G. A. GABRIELE In NASA. Langley Research Center Recent or nonlinear aerodynamic code. At this point in time, PIAS has Experiences in Multidisciplinary Analysis and Optimization, Part 1 been designed but the software has not been written. The idea 21 p 1984 for this development originated with P. J. (Bud) Bobbitt of the Avail: NTlS HC A22/MF A01 CSCL 01C NASA Langley Research Center. There was initial interest in an The complete aircraft design process can be broken into three aeroelastic solution for a separation-induced leading-edge vortex. phases of increasing depth: conceptual design, preliminary design, Some examples of the flow patterns for a low aspect ratio wing and detail design. Conceptual design consists primarily of are shown. The Leading-Edge Vortex Program, which calculates developing general arrangements and selecting the configuration pressure distributions including the effects of a separation-induced that optimally satisfies all mission requirements. The result of the leading-edge vortex, uses an iterative solution method. This led to conceptual phase is a conceptual baseline configuration that serves the concept of an iteration cycle on configuration shape external as the starting point for the preliminary design phase. The to the aerodynamic code. Author

97 N87-11726'# Hughes Helicopters, Culver City, Calif. structure with greater accuracy and less cost. These guidelines OPTIMIZATION PROCESS IN HELICOPTER DESIGN can be useful in an interactive optimization environment and in A. H. LOGAN and D. BANERJEE ln NASA. Langley Research the design of heuristic rules for the development of Center Recent Experiences in Multidisciplinary Analysis and knowledge-based expert optimization systems. Author Optimization, Part 1 19 p 1984 Avail: NTlS HC A22/MF A01 CSCL 01c In optimizing a helicopter configuration, Hughes Helicopters uses a program called Computer Aided Sizing of Helicopters N87-11743'# Kentron International, Inc., Hampton, Va. (CASH), written and updated over the past ten years, and used AIRCRAFT CONFIGURATION OPTIMIZATION INCLUDING as an important part of the preliminary design process of the OPTIMIZED FLIGHT PROFILES AH-64. First, measures of effectiveness must be supplied to define L. A. MCCULLERS ln NASA. Langley Research Center Recent the mission characteristics of the helicopter to be designed. Then Experiences in Multidisciplinary Analysis and Optimization, Part 1 CASH allows the designer to rapidly and automatically develop 18p 1984 the basic size of the helicopter (or other rotorcraft) for the given Avail: NTlS HC A22/MF A01 CSCL 01C mission. This enables the designer and management to assess The Flight Optimization System (FLOPS) is an aircraft the various tradeoffs and to quickly determine the optimum configuration optimization program developed for use in conceptual configuration. Author design of new aircraft and in the assessment of the impact of advanced technology. The modular makeup of the program is N87-11737'# Kansas Univ., Lawrence. Dept. of Aerospace illustrated. It contains modules for preliminary weights estimation, Engineering. preliminary aerodynamics, detailed mission performance, takeoff APPLICATIONS OF CONMIN TO WING DESIGN OPTIMIZATION and landing, and execution control. An optimization module is used WITH VORTEX FLOW EFFECT to drive the overall design and in defining optimized profiles in C. E. LAN ln NASA. Langley Research Center Recent Experiences the mission performance. Propulsion data, usually received from in Multidisciplinary Analysis and Optimization, Part 1 12 p engine manufacturers, are used in both the mission performance 1984 and the takeoff and landing analyses. Although executed as a Avail: NTlS HC A22/MF A01 CSCL 01C single in-core program, the modules are stored separately so that Slender wings on supersonic cruise configurations are expected the user may select the appropriate modules (e.g., fighter weights to be thin and highly swept. As a result, edge-separated vortex versus transport weights) or leave out modules that are not flow is inevitable and must be accounted tor in aerodynamic needed. Author analysis and design. The present method is based on the method of suction analogy to calculate the total aerodynamic characteristics. The method requires the solution of the attached flow problem, the latter being solved by a low-order panel method N87-11747'# Lockheed-CaliforniaCo., Burbank. in subsonic and supersonic flow. In essence, the lifting pressure SOME EXPERIENCES IN AIRCRAFT AEROELASTIC DESIGN is calculated by using a pressure-doublet distribution satisfying USING PRELIMINARY AEROELASTIC DESIGN OF the Prandtl-Glauert equation. From the pressure distribution, the STRUCTURES (PAD) leading-edge suction is calculated. The latter is assumed to be N. A. RADOVCICH In NASA. Langley Research Center Recent the vortex lift through the method of suction analogy. For a Experiences in Multidisciplinary Analysis and Optimization, Part 1 cambered wing, the location of vortex-lift action point is important 49 p 1984 in predicting the aerodynamic characteristics. It is also seen that Avail: NTlS HC A22/MF A01 CSCL 01C the effect of camber shape appears nonlinearly in all aerodynamic The design experience associated with a benchmark aeroelastic expressions. To design the camber shape, the camber slope is design of an out of production transport aircraft is discussed. represented by a cosine Fourier series at each of several spanwise Current work being performed on a high aspect ratio wing design stations. The Fourier coefficients are the design variables. To is reported. The Preliminary Aeroelastic Design of Structures design a leading-edge flap in the vortex flow (i.e., a vortex flap), (PADS) system is briefly summarized and some operational aspects the coordinates of corner points and the deflection angle are the of generating the design in an automated aeroelastic design design variables. The process of wing design is to determine the environment are discussed. Author camber shape and twist distribution such that an objective function, typically the drag, is minimized, subject to various constraints. Author N87-11749'# Northrop Corp., Hawthorne, Calif. Aircraft Div. N87-11739'# Jet Propulsion Lab., California Inst. of Tech., THE AUTOMATED STRENGTH-AEROELASTIC DESIGN OF Pasadena. AEROSPACE STRUCTURES PROGRAM Progress Report INFLUENCE OF ANALYSIS AND DESIGN MODELS ON MINIMUM E. H. JOHNSON and V. B. VENKAYYA (Air Force Wright WEIGHT DESIGN Aeronautical Labs., Wright-PattersonAFB, Ohio) In NASA. Langley M. SALAMA, R. K. RAMANATHAN (Northrop Corp., Hawthorne, Research Center Recent Experiences in Multidisciplinary Analysis Calif.), L. A. SCHMIT (California Univ.. Los Angeles), and I. S. and Optimization, Part 1 11 p 1984 SARMA In NASA. Langley Research Center Recent Experiences Avail: NTlS HC A22/MF A01 CSCL 01C in Multidisciplinary Analysis and Optimization, Part 1 14 p An ongoing program whose goal is to develop an automated 1984 procedure that can assist in the preliminary design of aircraft and (Contract NAS7-918) space structures is described. The approach and capabilities that Avail: NTlS HC A22/MF A01 CSCL 01C are to be included in the final procedures are descussed. By The results of numerical experiments designed to illustrate how using proven engineering software as a basis for the project, a the minimum weight design, accuracy, and cost can be influenced reliable and interdisciplinary procedure is developed. The use of a by: (1) refinement of the finite element analysis model and control language for module sequencing and execution permits associated load path problems, and (2) refinement of the design efficient development of the procedure and gives the user variable linking model are examined. The numerical experiments significant flexibility in altering or enhancing the procedure. The range from simple structures where the modelling decisions are data base system provides reliable and efficient access to the relatively obvious and less costly to the more complex structures large amounts of interrelated data required in an enterprise of where such decisions are less obvious and more costly. All this sort. In addition. the data base allows interfacing with existing numerical experiments used employ the dual formulation in pre- and post-processors in an almost trivial manner. Altogether, ACCESS-3 computer program. Guidelines are suggested for the procedure promises to be of considerable utility to preliminary creating analysis and design models that predict a minimum weight structural design teams. Author

98 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

N87-11750*# National Aeronautics and Space Administration. past experience and data in determining the influence of a design Langley Research Center, Hampton, Va. change on the performance. Author RECENT EXPERIENCES IN MULTIDISCIPLINARY ANALYSIS AND OPTIMIZATION, PART 2 J. SOBIESKI, comp. 1984 509 p Symposium held in Hampton, Va., 24-26 Apr. 1984 N87-11756'# United Technologies Research Center, East (NASA-CP-2327-PT-2; L-15830; NAS 1.55:2327-PT-2) Avail: Hartford, Conn. NTlS HC A22/MF A01 CSCL 01c OPTIMIZATION OF HELICOPTER ROTOR BLADE DESIGN FOR The papers presented at the NASA Symposium on Recent MINIMUM VIBRATION Experiences in Multidisciplinary Analysis and Optimization held at M. W. DAVIS ln NASA. Langley Research Center Recent NASA Langley Research Center, Hampton, Virginia, April 24 to Experiences in Multidisciplinary Analysis and Optimization, Part 2 26, 1984 are given. The purposes of the symposium were to 17p 1984 exchange information about the status of the application of Avail: NTlS HC A22/MF A01 CSCL OlC optimization and the associated analyses in industry or research The optimization approach discussed is part of an ongoing laboratories to real life problems and to examine the directions of effort to develop a general automated procedure for rotor blade future developments. design. This procedure can be used to determine the necessary geometric, structural, and material properties of a rotor system to N87-11751*# National Aeronautics and Space Administration. achieve desired objectives relating to vibration, stress, and Ames Research Center, Moffett Field, Calif. aerodynamic performance. The approach used for helicopter OVERVIEW APPLICATIONS OF NUMERICAL OPTIMIZATION vibration is emphasized. Based on analytical studies performed at METHODS TO HELICOPTER DESIGN PROBLEMS the United Technologies Research Center (UTRC), a simplified H. MIURA In NASA. Langley Research Center Recent Experiences vibration analysis was developed to be used in conjunction with a in Multidisciplinary Analysis and Optimization, Part 2 13 p forced response analysis in the optimization process. This simplified 1984 analysis improves the efficiency of the design process significantly. Avail: NTlS HC A22/MF A01 CSCL 01C Results of applying this approach to the design of an existing There are a number of helicopter design problems that are rotor blade model are presented. Author well suited to applications of numerical design optimization techniques. Adequate implementationof this technology will provide high pay-offs. There are a number of numerical optimization programs available, and there are many excellent N87-11757'# Army Research and Technology Labs., Fort Eustis, response/performance analysis programs developed or being Va. developed. But integration of these programs in a form that is APPLICATION OF NUMERICAL OPTIMIZATION TO ROTOR usable in the design phase should be recognized as important. It AERODYNAMIC DESIGN is also necessary to attract the attention of engineers engaged in W. A. PLEASANTS, 111 and T. J. WIGGINS In NASA. Langley - 2-. --I-----* ..-.,. -r-rhilitinr tn then! aYJlr~ LII~U~VWU~IIIGIIL O: aiialyia--- bapawuuru cannu .V ,,,..-.- ..I.,.1 -..-.- Resea:ch Center Recen! Experie~cesin Mul?irlisciplinaryAnalysis that analysis capabilities are much more powerful if integrated and Optimization, Part 2 15 p 1984 into design oriented codes. Frequently, the shortcoming of analysis Avail: NTlS HC A22/MF A01 CSCL 01C capabilities are revealed by coupling them with an optimization Based on initial results obtained from the performance code. Most of the published work has addressed problems in optimization code, a number of observations can be made regarding preliminary system design, rotor system/blade design or airframe the utility of optimization codes in supporting design of rotors for design. Very few published results were found in acoustics, improved performance. (1) The primary objective of improving the aerodynamics and control system design. Currently major efforts productivity and responsiveness of current design methods can are focused on vibration reduction, and aerodynamics/acoustics be met. (2) The use of optimization allows the designer to consider applications appear to be growing fast. The development of a a wider range of design variables in a greatly compressed time computer program system to integrate the multiple disciplines period. (3) Optimization requires the user to carefully define his required in helicopter design with numerical optimization technique problem to avoid unproductive use of computer resources. (4) is needed. Activities in Britain, Germany and Poland are identified, Optimization will increase the burden on the analyst to validate but no published results from France, Italy, the USSR or Japan designs and to improve the accuracy of analysis methods. (5) were found. Author Direct calculation of finite difference derivatives by the optimizer was not prohibitive for this application but was expensive. Approximate analysis in some form would be considered to improve N87-11753*# National Aeronautics and Space Administration. program response time. (6) Program developement is not complete Langley Research Center, Hampton, Va. and will continue to evolve to integrate new analysis methods, HELICOPTER ROTOR BLADE AERODYNAMIC OPTIMIZATION design problems, and alternate optimizer options. Author BY MATHEMATICAL PROGRAMMING J. L. WALSH, G. J. BINGHAM, and M. F. RILEY (Kentron International, Inc., Hampton, Va.) ln its Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2 12 p 1984 Avail: NTlS HC A22/MF A01 CSCL 01C N87-11758'# Army Research and Technology Labs., Fort Eustis, Formal mathematical programing was applied to the Va. Applied Technology Lab. aerodynamic rotor blade design process. The approach is to couple AEROELASTIC-AERODYNAMIC OPTIMIZATION OF HIGH hover and forward flight analysis programs with the general-purpose SPEED HELICOPTER-COMPOUND ROTOR optimization program CONMIN to determine the blade taper ratio, L. R. SUTTON and R. L. BENNETT In NASA. Langley Research percent taper, twist distribution, and solidity which minimize the Center Recent Experiences in Multidisciplinary Analysis and horsepower required at hover while meeting constraints on forward Optimization, Part 2 20 p 1984 flight performance. Designs obtained using this approach for the Avail: NTlS HC A22/MF A01 CSCL 01C blade of a representative Army helicopter compare well with those Several problems related to the aeroelastic/aerodynamic obtained using a conventional approach involving optimization of a high speed helicopter compound rotor are personnel-intensive parametric studies. Results from the present discussed. The helicopter fuselage vibration problem, the effects method can be obtained in 2 days as compared to 5 weeks of fuselage vibrations, the source of external and periodic air loads, required by the conventional procedure. Also the systematic typical airfoil environments and configurations, rotor dynamics, manipulation of the design variables by the optimization procedure vibration reduction, and requirements for the rotor design minimizes the need for the researcher to have a vast body of optimization analysis are among the topics covered. R.J.F.

99 N87-11759'# Sikorsky Aircraft, Stratford, Conn. N87-12556 ESDU International Ltd., London (England). THE STRUCTURAL OPTIMIZATION OF A SPREADER BAR FOR SIMPLIFIED FORMS OF PERFORMANCE EQUATIONS. TWIN LIFT HELICOPTER OPERATIONS ADDENDUM A EFFECT ON AEROPLANE LEVEL SPEED OF A. DOBYNS In NASA. Langley Research Center Recent SMALL CHANGES IN THRUST, DRAG, WEIGHT, POWER Experiences in Multidisciplinary Analysis and Optimization, Part 2 May 1986 14 p Supersedes ESDU-EG2/1 12 p 1984 (ESDU-86004-ADD-A ISBN-0-85679-556-9;ISSN-0141-4054) Avail: NTlS HC A22/MF A01 CSCL 01C Avail: ESDU An optimization study was performed to develop a minimum This Data Item ESDU 86004 is an addition to the Aircraft weight spreader bar to allow two helicopters to lift the same Performance Sub-series. Equations and curves are given for a payload. With this arrangement, the maximum payload that can method that neglects the effects of any consequential changes in be lifted is almost doubled without the expense of designing and the other independent variables although, at the cost of increased building a new helicopter. The concept has had some limited use complexity, a means of including such effects (in particular, by civil helicopter operators using small helicopters and has been compressibility effects on drag) is provided. Several worked demonstrated in large scale by two CH-54's which successfully examples show how well the simple method compares with actual lifted a total load of 20 ton. To this point, rather heavy available operations data. This document is an Addendum to ESDU 80032, beams or tower structures have been used for the spreader bar. and illustrates how the equations of motion given there combined Since the weight of the bar not only detracts from payload but with a parabolic drag law yield valuable results. ESDU also adds to the logistics problem, there are more than the usual incentives to minimize weight. Since the design requirement is for classic beam column with uniform side loads resulting from bar N87-12557'# National Aeronautics and Space Administration. weight and aerodynamic drag, the design problem is particularly Ames Research Center, Moffett Field, Calif. amenable to optimization. A study has been performed at Sikorsky NASA ROTOR SYSTEMS RESEARCH AIRCRAFT: FIXED-WING to establish the minimum weight for a spreader bar sized to carry CONFIGURATION FLIGHT-TEST RESULTS a load equal to the capacity of two Army BLACK HAWK helicopters. R. E. ERICKSON, J. L. CROSS, R. M. KUFELD, C. W. ACREE, D. Toward this end, a computer program was written to analyze the NGUYEN, and R. W. HODGE (Sikorsky Aircraft, Stratford, Conn.) spreader bar deflections and stresses and coupled to the NASA Feb. 1986 124 p developed CONMIN optimization routines. Author (NASA-TM-86789; A-85363; NAS 1.15236789) Avail: NTlS HC AO6/MF A01 CSCL 01C The fixed-wing, airplane configuration flight-test results of the Rotor System Research Aircraft (RSRA), NASA 740, at AmedDryden Flight Research Center are documented. Fourteen taxi and flight tests were performed from December 1983 to October 1984. This was the first time the RSRA was flown with N87-11781'# National Aeronautics and Space Administration. the main rotor removed; the tail rotor was installed. These tests Ames Research Center, Moffett Field, Calif. confirmed that the RSRA is operable as a fixed-wing aircraft. Data THE PREDICTION OF TRANSONIC LOADING ADVANCING were obtained for various takeoff and landing distances, control HELICOPTER ROTORS sensitivity, trim and dynamics stability characteristics, performance R. STRAWN and C. TUNG Apr. 1986 17 p rotor-hub drag, and acoustics signature. Stability data were obtained (AD-A168217; NASA-TM-88238; A-861 98; NAS 1.1 5~88238; with the rotor hub both installed and removed. The speed envelope AVSCOM-TM-86-A-1) Avail: NTlS HC A02/MF A01 CSCL 01C was developed to 261 knots true airspeed (KTAS), 226 knots Two different schemes are presented for including the effect calibrated airspeed (KCAS) at 10,000 ft density altitude. The of rotor wakes on the finite-difference prediction of rotor loads. airplane was configured at 5 deg. wing incidence with 5 deg. wing The first formulation includes wake effects by means of a flaps as a normal configuration. Level-flight data were acquired at blade-surface inflow specification. This approach is sufficiently 167 KCAS for wing incidence from 0 to 10 deg. Step inputs and simple to permit coupling of a full-potential finite-difference rotor doublet inputs of various magnitudes were utilized to acquire code to a comprehensive integral model for the rotor wake and dynamic stability and control sensitivity data. Sine-wave inputs of blade motion. The coupling involves a transfer of appropriate loads constantly increasing frequency were used to generate parameter and inflow data between the two computer codes. Results are identification data. The maximum load factor attained was 2.34 g compared with experimental data for two advancing rotor cases. at 206 KCAS. Author The second rotor wake modeling scheme in this paper is a split potential formulation for computing unsteady blade-vortex interactions. Discrete vortex fields are introduced into a N87-12558'# National Aeronautics and Space Administration. three-dimensional,conservative, full-potential rotor code. Computer Ames Research Center, Moffett Field, Calif. predictions are compared with two experimental blade-vortex THE HANDLING QUALITIES AND FLIGHT CHARACTERISTICS interaction cases. GRA OF THE GRUMMAN DESIGN 698 SIMULATED TWIN-ENGINE TILT NACELLE V/STOL AIRCRAFT M. A. ESKEY and S. B. WILSON, 111 Jun. 1986 112 p (NASA-TM-86785; A-85361 ; NAS 1.1 5:86785) Avail: NTlS HC AO6/MF A01 CSCL 01C This paper describes three government-conducted,piloted flight N87-11782# National Aerospace Lab., Amsterdam (Netherlands). simulations of the Grumman Design 698 vertical and short takeoff Structures and Materials Div. and landing (V/STOL) aircraft. Emphasis is placed on the aircraft's A CHECK OF CRACK PROPAGATION PREDICTION MODELS handling qualities as rated by various NASA, Navy, and Grumman AGAINST TEST RESULTS GENERATED UNDER TRANSPORT Aerospace Corporating pilots with flight experience ranging from AIRCRAFT FLIGHT SIMULATION LOADING conventional takeoff and landing (CTOL) to V/STOL aircraft. Each H. H. VANDERLINDEN 30 Dec. 1985 112 p Sponsored by successive simulation incorporated modifications to the aircraft in Netherlands Agency for Aerospace Programs order to resolve the flight problems which were of most concern (NLR-TR-84005-U; 88667272; GARTEUR/TP-OOB; ETN-86-98497) to the pilots in the previous simulation. The objective of the first Avail: NTlS HC AO6/MF A01 simulation was to assess the basic handling qualities of the aircraft Thirteen variations of the F-27 transport spectrum were with the noncross-shafted propulsion system. The objective of the evaluated by 7 institutes and companies using in total 13 crack second simulation was to examine the effects of incorporating the propagation prediction methods and models. It is shown that the cross-shafted propulsion system. The objective of the third predictions range from very conservative through accurate to simulation was to examine inoperative single-engine characteristics unconservative. ESA with and without cross-shafted engines. Author

100 06 AIRCRAFT INSTRUMENTATION

N87-12559'# National Aeronautics and Space Administration. A87-13545# Lewis Research Center, Cleveland, Ohio. PRECISION POINT TARGET TRACKING A HEATER MADE FROM GRAPHITE COMPOSITE MATERIAL C. L. RICHARDS, JR. (Technology Concepts Associates, Inc., FOR POTENTIAL DEICING APPLICATION Irvine, CA) IN: ION, National Technical Meeting, Long Beach, C. C. HUNG, M. E. DILLEHAY (Cleveland State Univ., Ohio), and CA, January 21-23, 1986, Proceedings . Washington, DC, Institute M. STAHL 1986 22 p Proposed for presentation at the 25th of Navigation, 1986, p. 105-110. Aerospace Sciences Meeting, Reno, Nev., 12-15 Jan. 1987; Subresolution tracking may be achieved through a combination sponsored by AIAA of proper imaging sensor design and algorithm selection. The (NASA-TM-88888; E-3298; NAS 1.15:88888) Avail: NTlS HC requirement on the sensor for optimum performance is that images AO2/MF A01 CSCL 01C must be sampled by a stable grid which meets the Nyquist sampling A surface heater was developed using a graphite fiber-epoxy criterion. For staring array sensors this requirement leads to a composite as the heating element. This heater can be thin, highly detector size and sample spacing which is quite different from electrically and thermally conductive, and can conform to an the classical design choice. Once the focal plane has been properly irregular surface. Therefore it may be used in an aircraft's thermal designed, there is a selection of tracking algorithms which give deicing system to quickly and uniformly heat the aircraft surface. approximately the same tracking performance. All of these One-ply of unidirectional graphite fiber-epoxy composite was algorithms show a residual single measurement error which is laminated between two plies of fiber glass-epoxy composite, with inversely proportional to the signal to noise ratio. The choice of a nickel foil contacting the end portions of the composite and partly particular algorithm comes primarily from a trade between exposed beyond the composites for electrical contact. The model processing burden and clutter rejection. A system which is heater used brominated P-100 fibers from Amoco. The fiber's optimized for point target tracking will also be optimized, and will electrical resistivity, thermal conductivity and density were 50 micro show improved performance, for extended target tracking and for ohms per centimeter, 270 W/m-K and 2.30 gmlcubic cm, pattern recognition. Author respectively. The electricity was found to penetrate through the composite in the transverse direction to make an acceptably low A87-13912 foil-composite contact resistance. When conducting current, the COMBINED RADAR, ECM FUNCTIONS WILL ENHANCE LAVl heater temperature increase reached 50 percent of the steady SURVIVABILITY state value within 20 sec. There was no overheating at the ends D. A. BROWN Aviation Week and Space Technology (ISSN of the heater provided there was no water corrosion. If the 0005-2179, VOI. 125, AUg. 25, 1986, p. 111, 113. foil-composite bonding failed during storage, liquid water exposure The Israeli Lavi attack fighter will incorporate an avionics system was found to oxidize the foil. Such bonding failure may be avoided that links radar warning and active electronics countermeasures if perforated nickel foil is used, so that the composite plies can functions, as one way of enhancing aircraft survivability and freeing bond to each other through the perforated holes and therefore wing and fuselage stations for additional ordnance. The internal lock the foil in place. Author location of the system created problems with respect to shape, volume and weight constraints, as well as antenna position optimization. A power management concept is used which allows N87-i2716# joint Pubiicaiiuiis iigseaicli Sei~ice,AikfigiGfi, \'a. I*-LIIG J)IaLTIII-.,-+-m +-LV rrmmpmv,---In., i!s U.U;IL~YIe.$,mdmhle ~v..u.'onwor UUVU*..UJ-Yrrlvlrntannn(lclv -.I -..--.I ndnr POSSIBLE MILITARY APPLICATIONS OF STRATOSPHERIC any circumstances. The Lavi's ECM capability will be enhanced AIRSHIP DISCUSSED by an operationally redundant active subsystem which provides J. KIMURA. R. TAKEDA, Y. FUJIMATSU, and T. KAT0 ln its for dynamic location of multiple resources and will allow graceful Japan Report: Science and Technology (JPRS-JST-86-023) p degradation in the event of subsystem unit failures. O.C. 49-62 29 Aug. 1986 Transl. into ENGLISH from Boei Gijutsu (Tokyo, Japan), Nov. 1985 p 48-58 A87-14005# Avail: NTlS HC A04/MF A01 AVIONICS SYSTEMS FOR FUTURE COMMERCIAL The possibilities of a stratospheric airship of the LB (lifting HELICOPTERS body) types are studied from the aspect of operation. The BMFT, Statusseminar ueber Luftfahrtforschung und meteorological conditions that most severly restrict its operation Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, are considered. The advantages that the stratospheric airship has Paper. 23 p. In German. over other aircraft and artificial satellites are discussed. B.G. The state of the art and future developments in avionics for commercial helicopters are discussed. Present systems of cockpit instrumentation with color displays, systems for testing these displays, and central control systems are described. Future sensors, cockpit instrumentation, and central controls are described, stressing the greater levels of control and information about the 06 entire aircraft that will be concentrated in the cockpit. The use of simulators to test these future technologies before their installation AIRCRAFT INSTRUMENTATION in helicopters is discussed, and signal standrdization, bus systems, and software that will be used in future commercial helicopters Includes cockpit and cabin display devices; and flight instruments. are considered. C.D.

A87-14030# A8743469 STALL MARGIN INDICATION MICROELECTRONICS IN AIRCRAFT SYSTEMS A. W. HOADLEY (Western Michigan University, Kalamazoo) and E. H. J. PALLETT (Civil Aviation Authority, Airworthiness Div., R. S. VANDERBOK (Electronic Systems Development Co., Canton, Redhill. England) London, Pitman, 1985, 285 p. MI) AIAA, General Aviation Technology Conference. Anaheim, The design, operating principles, and performance of aircraft CA, Sept. 29-Oct. 1, 1986. 6 p. Research supported by the Western electronic systems based on microelectronic devices are surveyed Michigan University. and illustrated with photographs, diagrams, and graphs. The (AIAA PAPER 86-2595) developmental history of aircraft electronics is traced, and individual The landing and takeoff phases of flight require control of the chapters are devoted to number systems and coding, logic gates aircraft at airspeeds and angles of attack close to stall. This is and circuits, logic devices, displays, CRT displays, logic diagrams particularly true when a wind shear condition has been encountered. and interpretation, computers, aircraft systems, and handling During the recovery from a wind shear, the aircraft must use all procedures to avoid electrostatic damage to microelectronic available energy, the most immediately available being kinetic circuits. T.K. energy in the form of airspeed. This paper covers the concept

101 06 AIRCRAFT INSTRUMENTATION and hardware of a microprocessor based stall margin display with low altitude, all-weather, day/night operational capability by system. The LCD heads up display provides accurate real time means of an FLlR sensor, supporting electronics, and an data to the provides accurate real time data to the pilot allowing environmental control system. Military specifications for realistic the precise use of the available airspeed. The precise use of this environment testing led to emulation of the vibration conditions immediately available, but limited, energy source will increase the experienced by similar stores on F-16 aircraft. Validation data were chance that ground contact can be avoided until the engines can obtained for the vibration test stand with flight tests of mock-ups provide the necessary additional energy for full recovery. Author of the LANTIRN pod. M.S.K.

A87-14352' National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. N87-11783# Science Applications, Inc., Orlando, Fla. ALL-DIGITAL JETS ARE TAKING OFF EVALUATION OF A VISUAL SYSTEM IN ITS SUPPORT OF C. R. SPITZER (NASA, Langley Research Center, Hampton, VA) SIMULATED HELICOPTER FLIGHT Final Report, Sep. 1985 - IEEE Spectrum (ISSN 0018-9235), vol. 23. Sept. 1986, p. 51-56. Feb. 1986 refs W. D. SPEARS and W. E. CORLEY Feb. 1986 113 p Prepared The functions and advantages of second-generation digital in cooperation with Seville Training Systems Corp. avionics systems are described. These digital systems have (Contract N61339-82-D-0006) increased integration, increased reliability and flexibility, and (AD-A168829; TR-86-06) Avail: NTlS HC AO6/MF A01 CSCL improved man-machine interface, and they provide increases in 05H the mean time between removal of line-replacable units and fuel The Visual System Component Development Program O/SCDP) savings. Different redundant processors and software are utilized was developed by GE under contract with PM TRADE and installed to achieve fault-tolerance performance of flight control systems. at Williams AFB in spring 1985. Its purpose was to expand the The improved landing capabilities, front-panel instruments, sidestick state-of-the-art in visual systems by providing the capability to controllers, back-lighted liquid-crystal displays, and fly-by-wire support nap-of-the-earth (NOE) flight simulation, which requires a system possible with digital avionics are examined. The applications high density of visual cues to allow pilots to accurately judge of digital avionics to military and commercial aircraft are discussed vertical and horizontal distances. The GE system was tested with and examples are provided. I.F. the computer generated imagery projected in the dome with a radius of 12 feet. The Field of View (FOV) was 140 degrees A87-15028# horizontal by 60 degrees vertical with an enhanced Area of Interest EXPERIMENTAL CALIBRATION OF AN AIRCRAFT VECTOR (AOI) of 26 degrees horizontal by 20 degrees vertical inserted in ELECTRIC FIELD METER SYSTEM the middle. The imagery centered in pilot's attention regardless of R. V. ANDERSON and J. C. BAILEY (US. Navy, Naval Research where he was looking in the dome; however, the eye tracker was Laboratory, Washington, DC) IN: International Aerospace and not functioning for these tests. Nine experienced helicopter pilots Ground Conference on Lightning and Static Electricity, 11th, participated as subjects. Two kinds of flight mission plans were Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, used: a familiarization flight and a tactical maneuvers flight. The National Interagency Coordination Group, 1986, p. 33-1 to 33-13. results of the experiment showed that the GE system can support refs all aspects of helicopter flight simulation. However, problems were Although numerous aircraft have been instrumented for the found that indicate further work is needed. These included trouble measurement of electrostatic field, and there have been a few with perceived sizes and distances in the visual scene, and a instances of calibration on an absolute basis, the absolute high incidence of simulator sickness, probably due to processing calibration of an airborne system for the measurement of a full of motion cues. GRA three-dimensional vector field has not been reported. This report outlines the problems inherent in such a calibration. The design of field meters which are simultaneously suitable for lightning N87-11784# Deutsche Forschungs- und Versuchsanstalt fuer measurements and for calibration is summarized. A description of Luft- und Raumfahrt, Brunswick (West Germany). Abteilung the calibration accomplished is provided, and the inherent errors Traegheitsortung und Navigation. are estimated. It is concluded that the process described is viable, INVESTIGATION OF MAGNETOMETER ERRORS AND THEIR and possible improvements are suggested. Author COMPENSATION IN THE BO-105 HELICOPTER H. J. HOTOP and N. NAWA Mar. 1986 62 p In GERMAN; A87-15415 ENGLISH summary LAMPS MK 111 - A 'NEW LOOK SUCCESS STORY (DFVLR-FB-86-21; ISSN-0171-1342; ETN-86-98187) Avail: NTlS T. M. GOOD (IBM Corp., Federal Systems Div., Owego, NY) IN: HC A04/MF A01; DFVLR, Cologne, West Germany DM 23.50 1986 Annual Reliability and Maintainability Symposium, Las Vegas, The errors of a magnetometer as a function of helicopter pitch NV, January 28-30. 1986, Proceedings . New York, Institute of and roll angles were investigated using flight test data. An error Electrical and Electronics Engineers, Inc., 1986, p. 151-1 55. model for compensation is presented. The magnetometer was The reliability enhancement elements incorporated into the tested in different locations in the helicopter. Two possibilities of LAMPS MK 111 development program are described. New elements magnetometer error compensation are explained together with their included conservative derating criteria to ensure that a 20-yr service accuracy as a magnetic sensor in an attitude and heading reference life would be available from 99 percent of the 30,000 components system. The use of an on-line algorithm allows compensation during of the integrated system. Other program elements are parts the flight, and hence leads to an improvement of the magnetic selection and a test, analyze, and fix program. A reliability estimate attitude information with increasing flight time. ESA for the SH-GOB helicopter exceeded the reliabilities of other current systems by a factor of 2.5. M.S.K. N87-11785# National Aerospace Lab., Amsterdam (Netherlands). A87-15430# Flight Div. TAILORING A MAJOR WEAPON ENVIRONMENTAL PROGRAM SYSTEMS, AVIONICS AND INSTRUMENTATION OF J. H. WAFFORD (USAF. Aeronautical Systems Div., TRANSPORT CATEGORY HELICOPTERS Wright-Patterson AFB, OH) IN: 1986 Annual Reliability and F. J. ABBINK Aug. 1985 37 p Submitted for publication Maintainability Symposium, Las Vegas, NV, January 28-30, 1986, (NLR-MP-850664; 68667703; ETN-86-98495) Avail: NTlS HC Proceedings . New York, Institute of Electrical and Electronics AOSIMF A01 Engineers, Inc., 1986, p. 383-388. The development of helicopters for passenger transport is The impact of engineering data and consequent design changes reviewed. The systems, avionics, and instrumentation of an S-76 on the vibratinm requirements for environment tests of LANTIRN transport helicopter used for offshore services are described. is described. LANTIRN was devised to provide tactical aircraft Developments in helicopter avionics are discussed. ESA

102 07 AIRCRAFT PROPULSION AND POWER

N87-11786# National Aerospace Lab., Amsterdam (Netherlands). A87-13323 Flight Div. CLOSED LOOP CONTROL OF AN AFTERBURNING F100 GAS A SMALL, FLEXIBLE AND POWERFUL DATA ACQUISITION TURBINE ENGINE SYSTEM FOR THE F16 AIRCRAFT S. A. ElSA and H. P. TYLER (Allied Corp., Bendix Aerospace S. S. VANLEEUWEN 20 Sep. 1985 18 p Sector, South Bend, IN) IN: 1986 American Control Conference, (NLR-MP-85074-U; 88667704; ETN-86-98496) Avail: NTlS HC 5th, Seattle, WA, June 18-20, 1986, Proceedings. Volume 1 . New A02IMF A01 York, Institute of Electrical and Electronics Engineers, 1986, p. Electrical layout, mechanical properties, performance 266-272. refs parameters, and growth facilities of a data acquisition system for The paper describes the development of a nonlinear the F-16 aircraft are described. The system can be used for flight multivariable closed loop control for the F100 augmented tests requiring less than 500 parameters. A selection of avionics (afterburning) engine using transfer function synthesis theory and Muxbus parameters was made, but with modifications the whole a multivariable approach. The study addresses the following issues: Muxbus contents can be recorded. Flight test data is written on (1) development of a control for the augmented FlOO engine which tape during the whole flight, and telemetry to a ground-based controls the complete engine in a closed loop manner, (2) extension station is possible. ESA of controller authority to the entire thrust range, and (3) demonstration of the controller's ability to minimize fan stall problems. A 15th order nonlinear F100 afterburning engine simulation is used as the plant for which a full range nonlinear transfer function controller is generated. Linear feedforward N87-11787 Kansas Univ., Lawrence. elements generated by the synthesis procedure assist the basic DESIGN OF A TAKEOFF PERFORMANCE MONITORING nonlinear closed loop controller to provide desired system response SYSTEM Ph.D. Thesis while maintaining engine input and output variables within physical R. SRIVATSAN 1985 218 p position and rate constraints. Author Avail: Univ. Microfilms Order No. DA8608473 An algorithm was developed to monitor the Performance of the aircraft during the takeoff phase to improve safety in that flight phase. The algorithm is made up of two segments: a pretakeoff segment and a real time segment. One-time inputs of A87-13343 ambient temperature, pressure, runway wind, aircraft gross weight, VARIABLE STRUCTURE CONTROL OF A TURBOJET ENGINE and selected flap and stabilizer setting are utilized by the pretakeoff C.-Y. CHAO (Industrial Technology Research Institute, Hsinchu, segment in generating a set of standard acceleration performance Republic of China), C.-W. CHEN (National Chiao-Tung University, data in an off-line condition. The real-time segment, in addition to Hsinchu, Republic of China), and B.-C. WANG (Chung-Shan the above one-time inputs, requires the runway length available Institute of Science and Technology, Lungtan, Republic of China) for rotation, the runway length available for stopping, and an IN: 1986 American Control Conference, 5th, Seattle, WA, June estimated runway rolling friction coefficient. The algorithm was 16-20, 1986, Proceedings. Volume 1 . New York, Institute of evaluated using a six degree-of-freedom nonlinear aircraft Electrical and Electronics Engineers, 1986, p. 482-487. refs TL - simulation as the plant for several design point test cases and I II~iuei controi probiem of a singie-spooi iurbojei engine is two types of engine malfunctions. Dissert. Abstr. studied. A transfer function approximation method is utilized to identify linear models for operating points. Then, a sliding mode control is developed to regulate the fuel flow so that the engine speed and temperature are within their physical constraints, based on the identified linear models. The resultant variable structure control is evaluated to determine its effectiveness in engine nonlinear simulations. Author 07

AIRCRAFT PROPULSION AND POWER A87-13418' General Electric Co., Lynn, Mass. MULTI-VARIABLE CONTROL OF THE GE T700 ENGINE USING Includes prime propulsion systems and systems components, e.g., THE LQG/LTR DESIGN METHODOLOGY gas turbine engines and compressors; and onboa rd auxiliary power W. H. PFEIL (General Electric Co., Aircraft Engine Business Group, plants for aircraft. Lynn, MA), M. ATHANS (MIT, Cambridge, MA), and H. A. SPANG, 111 (GE Corporate Research and Development Center, Schenectady, NY; MIT, Cambridge, MA) IN 1986 American Control Conference, A87-13318' National Aeronautics and Space Administration. 5th, Seattle, WA, June 18-20, 1986, Proceedings. Volume 2 . New Lewis Research Center, Cleveland, Ohio. York, Institute of Electrical and Electronics Engineers, 1986, p. I A REAL-TIME SIMULATION EVALUATION OF AN ADVANCED 1297-1312. Research supported by the General Electric Co. DETECTION, ISOLATION AND ACCOMMODATION ALGORITHM Previously announced in STAR as N86-29819. refs

I FOR SENSOR FAILURES IN TURBINE ENGINES (Contract NAG2-297) I W. c. MERRILL and J. C. DELAAT (NASA, Lewis Research Center, The design of scalar and multi-variable feedback control Cleveland, OH) IN: 1986 American Control Conference, 5th, systems for the GE T700 turboshaft engine coupled to a helicopter rotor system is examined. A series of linearized models are I Seattle, WA, June 18-20, 1986, Proceedings. Volume 1 . New 1 York, Institute of Electrical and Electronics Engineers, 1986, p. presented and analyzed. Robustness and performance 162-169. Previously announced in STAR as N86-24697. refs specifications are posed in the frequency domain. The An advanced sensor failure detection, isolation, and linear-quadratic-Gaussian with loop-transfer-recovery (LQGILTR) accommodation (ADIA) algorithm has been developed for use with methodology is used to obtain a sequence of three feedback an aircraft turbofan engine control system. In a previous paper designs. Even in the single-input/single-output case, comparison the authors described the ADIA algorithm and its real-time of the current control system with that derived from the LQGILTR I implementation. Subsequent improvements made to the algorithm approach shows significant performance improvement. The and implementation are discussed, and the results of an evaluation multi-variable designs, evaluated using linear and nonlinear 1 presented. The evaluation used a real-time, hybrid computer simulations, show even more potential for performance I simulation of an FlOO turbofan engine. Author improvement. Author I 103 07 AIRCRAFT PROPULSION AND POWER

A87-13647# A87-13990# ON THE IMPROVEMENT...... ~- OF AN EXPENDABLE TURBOJET IMPROVING THE ENERGY EFFICIENCY OF COOLED ENGINE FLIGHT ENVELOPE HIGH-TEMPERATURE TURBINES [STEIGERUNG DER G. LEVIN, S. ARAD, and A. LEVY (Bet Shemesh Engines, Ltd., ENERGIEAUSNUTZUNG IN GEKUEHLTEN Israel) IN: Israel Annual Conference on Aviation and Astronautics, HOCHTEMPERATURTURBINEN] 27th, Haifa, Israel, February 27, 28, 1985, Collection of Papers . H.-J. DlETRlCHS (MTU Motoren- und Turbinen-Union Muenchen Haifa, Israel, Technion - Israel Institute of Technology, 1986, p. GmbH, Munich, West Germany) BMFT, Statusseminar ueber 118-1 24. Luftfahrtforschung und Luftfahrttechnologie, Munich, West The paper describes how it was found possible to change the Germany, Apr. 28-30, 1986, Paper. 28 p. In German. maximum allowed flight speed (M = 0.9) of the SOREK 4 The interaction of supersonic fields, cooling-air flows, and expendable turbojet to a higher value (M = 1.1) at sea level, aperture effects in high-pressure one-stage turbines is examined, after an analysis of burst test results of the first compressor stage, summarizing the results of analytical and experimental its detailed stress calculation, and data about its material. The investigations performed during phase II of a BMFT-sponsored decision to augment the maximum allowed flight seed has been project to improve the efficiency of cooled high-temperature turbine made possible by a relatively inexpensive procedure as compared engines for aircraft. The predictions of two-dimensional and with the conventional method of altitude bench testing. Author three-dimensional time-dependent simulations of inviscid turbine flow are compared with data obtained in a cold-air rig, the DFVLR grid-flow wind tunnel, and under engine conditions in the new-technology gas generator GNTl. The results are presented in graphs, photographs, and drawings, and it is shown that high efficiency can be achieved at high pressures in single-stage transonic turbines. The need for improved simulations which take viscous effects and compression-shock/boundary-layer interactions A87-13658# into account and identify the causes of secondary flows and radial EXPERIMENTAL INVESTIGATION OF A SOLID FUEL RAMJET aperture effects is indicated. T.K. COMBUSTOR R. ZUVLONI, Y. LEVY, and A. GANY (Technion - Israel Institute of Technology, Haifa) IN: Israel Annual Conference on Aviation and Astronautics, 27th, Haifa, Israel, February 27, 28, 1985, Collection of Papers . Haifa, Israel, Technion - Israel Institute of Technology, 1986, p. 205-209. refs A87-13998# An experimental investigation on a small solid fuel ramjet FURTHER DEVELOPMENT OF THE AXIAL-RADIAL combustor employing PMMA (Plexiglas) as a fuel has been COMPRESSOR [ WEITERENTWICKLUNG DES conducted. A static test system, which includes a 20 kW electrical AX1AL-RADIALVERDICHTERS] air heater, simulates the air temperature and pressure encountered U. SCHMIDT-EISENLOHR (MTU Motoren- und Turbinen-Union in at a flight Mach number of 3, and enables the measurements Muenchen GmbH, Munich, West Germany) BMFT, Statusseminar of pressure, air temperature, and motor thrust. Fuel regression ueber Luftfahrtforschung und Luftfahrttechnologie, Munich, West rate is studied by means of video photographs. The results reveal Germany, Apr. 28-30, 1986, Paper. 17 p. In German. refs high combustion efficiency and indicate that average fuel regression Progress made recently in the development of an experimental rate correlation may be different in different motor geometries. axial-radial compressor for medium-performance aircraft engines Author is discussed. The oeprational behavior of the compressor and its insertion in the GNT 1 new technology gas generator are examined. The way the compressor’s adjustable geometry works is described, and the testing of the device is reviewed. It is shown that the compressor requires an improvement in efficiency, and efforts made in that direction are discussed. Author

A87-13989# TECHNICAL/ECONOMIC EVALUATION OF NEW PROPFAN CONCEPTS IN COMPARISON WITH THE TURBOFAN OF THE 1990s [TECHNISCH/WIRTSCHAFLlCHE BEWERTUNG NEUER A87-14000# PROPFAN-KONZEPTE IM VERGLEICH ZUM TURBOFAN DER IMPETUS OF NEW TECHNOLOGIES FOR UTILITY, EXECUTIVE, 90ER JAHRE] AND COMMUTER AIRCRAFT [ANTRIEB NEUER TECHNOLO- D. ECKARDT (MTU Motoren- und Turbinen-Union Muenchen GIE (ANT) FUER UTILITY-, EXECUTIVE- UND COMMUTER- GmbH, Munich, West Germany) BMFT, Statusseminar ueber FLUGZEUGE] Luftfahrtforschung und Luftfahrttechnologie, Munich, West H. KROJER (Dornier GmbH, Friedrichshafen, West Germany) Germany, Apr. 28-30, 1986, Paper. 25 p. In German. refs BMFT, Statusseminar ueber Luftfahrtforschung und The results of a comparative study of advanced propfan and Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, turbofan engines, as applied to a 150-passenger short-distance Paper. 53 p. In German. aircraft (Eckardt et al., 1984) are summarized, and the development The calculative and experimental studies undertaken in the of a counter-rotating integrated shrouded propfan (CRISP) is project Impetus of New Technologies, which proposes an entirely reported. It is shown that the additional noise-reduction structures new design concept for two-engine turboprop aircraft in general required for proposed single-rotation and counter-rotation propfans aviation, are reviewed. The calculative studies were aimed at would negate most of their fuel-economy advantages vis a vis guaranteeing a flow separation-free tail flow and at causing uniform advanced turbofans. The CRISP concept combines the standard flow conditions toward the propellers. Experimental findings mounting position, noise damping, and blade containment of the concerning the installation efficiency, flow conditions toward the turbofan with the higher propulsive efficiency, propeller sweep, propellers, resistance balance and polar curves, and acoustics and thrust-reversal capability of the counter-rotating propfan. The are discussed. Data on the flight efficiency and flight characteristics development of CRISP engines is described and illustrated with that resulted when the project concept was applied in actual drawings and graphs. It is predicted that CRISP will save about engines are reported and discussed, and the propeller and engine 20 percent (relative to a 1986 turbofan) in the total propulsion configurations that resulted from the findings are summarized. The weight (the sum of weights of the engine, the sound insulation, results using the project concept are compared with those from and fuel) for a typical 2300-n mi mission. T.K. conventional designs concepts. C.D.

104 07 AIRCRAFT PROPULSION AND POWER

A87-14123*# Flow Research, Inc., Kent, Wash. A87-15010# PROPELLER DESIGN BY OPTIMIZATION AIRWORTHINESS CONSIDERATIONS OF LIGHTNING STRIKE M. H. RlZK and W.-H. JOU (Flow Research Co., Kent, WA) AlAA PROTECTION FOR HELICOPTER DIGITAL ENGINE Journal (ISSN 0001-1452), vol. 24, Sept. 1986, p. 1554-1556. CONTROLS Previously cited in issue 07, p. 848, Accession no. A86-19678. R. L. VAUGHN (FAA, Fort Worth, TX) IN: International Aerospace refs and Ground Conference on Lightning and Static Electricity, 1lth, (Contract NAS3-24533) Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, National Interagency Coordination Group, 1986, p. 12-1 to 12-5. refs The use of full-authority digital engine control (FADEC) systems A87-14 139# in Category A transport rotorcraft, especially during IFR operations, MATHEMATICAL MODEL AND DIGITAL SIMULATION FOR may lead to catastrophic system failure in the absence of lightning SPEED CONTROL SYSTEM OF TWO-SPOOL TURBOJET strike protection. FAA Advisory Circular 29-2 characterizes the ENGINE lightning environment and recommends test and analysis methods S. FAN (Northwestern Polytechnical University, Xian, People's with which manufacturers can demonstrate adequate protection Republic of China) Acta Aeronautica et Astronautica Sinica, vol. of FADECs against lightning strikes. O.C. 7, June 1986, p. 287-290. In Chinese, with abstract in English. A mathematical model for the speed-control system of a A87-15179 two-spool turbojet engine is derived from component characteristics FOR SMALL AIRLINERS AND EXECUTIVE JETS of the engine and construction parameters of the controller. The I. KINNEAR (Rolls-Royce, Ltd., Civil Engine Group, Derby, discretization-similitudemethod is adopted in the digital simulation England) Exxon Air World, vol. 38, no. 2, 1986, p. 8-11. of the nonlinear control system. The computer program written The design of the Tay engine, which has a take-off thrust in gives the steady-state and dynamic characteristics of the control the 12,000-15,000 range, is described. The use of a wide-chord system at H = 0, V = 0 under standard atmospheric conditions. fan and a large by-pass ratio to reduce the noise generated by Author the engine is examined. A three-stage intermediate-pressure compressor was incorporated into the engine design in order to increase engine efficiency and reduce noise generation. Mechanical changes such as increased fan diameter, improvements in the combustion chamber, and a new HP-turbine are considered. I.F. A87-14364'# General Dynamics Corp., Fort Worth, Tex. TURBINE BYPASS REMOTE AUGMENTOR LIFT SYSTEM FOR A87-15204 V/STOL AIRCRAFT DETERMINATION OF THE THRUST AND NET EFFICIENCY OF A. E. SHERIDAN (General Dynamics Corp., Fort Worth, TX) A PROPELLER AND FLOW PARAMETERS BEHIND THE 1986, p. Journal of Aircraft (ISSN 002143669), vol. 23, Sept. PROPELLER [K VOPROSU OPREDELENIIA TIAGI, 703-710. NASA-supported research. Previously cited in issue 01, EFFEKTIVNOGO KPD VOZDUSHNOGO VINTA I PARAMETROV p. 11, Accession no. A86-10941. refs POTOKA ZA NIM] A. A. BUMWIN kiiztisionnaia Takhnika (ISSN 0579-2975), nc. 2, 1986, p. 19-23. In Russian. The uncertainty of the estimates of the thrust of a propeller A87-14366# under start conditions is demonstrated. A method is proposed for NOISE AND PERFORMANCE OF A COUNTER-ROTATION determining the thrust equivalent of power from the aerodynamic PROPELLER characteristic of a propeller for start and flight conditions. S. FUJII, H. NISHIWAKI, and K. TAKEDA (National Aerospace Expressions are obtained for calculating the propeller airflow rate, Laboratory, Chofu, Japan) Journal of Aircraft (ISSN 0021 -8669), the flow velocity behind the propeller, and the net efficiency of vol. 23, Sept. 1986, p. 719-724. Research supported by the the propeller under various operating conditions of a turboprop Environment Protection Agency of Japan. refs engine. V.L. The noise and aerodynamic performance of a 3 x 3 counter-rotating propeller scale model were quantified A87-15208 experimentally in anechoic environments with a velocity of 68 m/s THE EFFECT OF TURBINE ELEMENTS ON THE GASDYNAMIC incoming flow on. The model diameter was 400 mm and the aft STABILITY MARGIN [VLIIANIE ELEMENTOV TURBINY NA blade rotational speeds and the rotational Mach numbers were ZAPAS GAZODINAMICHESKOI USTOlCHlVOSTl] varied up to 9000 rpm and 0.55, respectively, while the front blades A. M. IDELSON Aviatsionnaia Tekhnika (ISSN 0579-2975), no. were kept at 9000 rpm. The reinforcement of counter-rotating 2, 1986, p. 38-42. In Russian. harmonics was observed even at high blade passage frequencies. The variance of the geometrical dimensions of turbine The axial separation between two rotors had a favorable effect components during their manufacture can noticeably affect the on the noise levels, whereas an adverse effect on the performance stability margin of multishaft gas turbine engines. It is shown here was found for the large spacing with axial velocity acceleration that, during the large-volume production of multishaft gas turbines, attendant. The spike due to the overturning of tangential velocity the effect of the dimensional variance of turbine components on was found near the tip section. A difference of the rotational the gasdynamic stability margin of the gas-turbine engine can be speeds yielded the spinning sound waves with a beat frequency determined by processing statistically the shaft rotation frequency of three times the rps difference. The split frequencies could be ratios, which are commonly measured during bench testing. V.L. identified on the measured spectrum when the two rotors had such nonsynchronous rotational speeds. Author A8745210 USING VIBRATION SPECTRUM CHARACTERISTICS FOR THE FLOW-PATH DIAGNOSTICS OF AIRCRAFT GAS TURBINE ENGINES [ ISPOL'ZOVANIE KHARAKTERISTIK A87-14984# VIBRATSIONNOGO SPEKTRA DLlA DlAGNOSTlKl DEVELOPMENT OF AN ADVANCED VANELESS INLET PROTOCHNOI CHASTI AVIATSIONNYKH GTD] PARTICLE SEPARATOR FOR HELICOPTER ENGINES A. G. MIRONOV and S. M. DOROSHKO Aviatsionnaia Tekhnika B. V. R. VITTAL, D. L. TIPTON, and W. A. BENNETT (General (ISSN 0579-2975), no. 2, 1986, p. 45-49. In Russian. Motors Corp., Indianapolis, IN) Journal of Propulsion and Power An improved vibration spectrum model is presented which allows (ISSN 0748-4658), vol. 2, Sept.-Oct. 1986, p. 438-444. Previously for the presence of combination components. Methods are then cited in issue 18, p. 2622, Accession no. A85-39694. refs examined for evaluating the aerodynamic inhomogeneity of a rotor

105 07 AIRCRAFT PROPULSION AND POWER of a dual-shaft gas turbine engine from the vibration parameters adverse. Kaza and Kielb have studied the effects of two types of based on the combination components. The accuracy of the results mistuning on the flutter and forced response: alternate mistuning obtained is confirmed experimentally. V.L. where alternte blades are identical and random mistuning. The objective is to investigate other patterns of mistuning which A87-15211 maximize the beneficial effects on the flutter and forced response TURBINES WITH COUNTER-ROTATING ROTORS FOR of the cascade. Numerical optimization techniques are employed AIRCRAFT POWER PLANTS [TURBINY S to obtain optimal mistuning patterns. The optimization program PROTIVOPOLOZHNYM NAPRAVLENIEM VRASHCHENIIA seeks to minimize the amount of mistuning required to satisfy ROTOROV DLlA AVIATSIONNYKH SILOVYKH USTANOVOK] constraints on flutter speed and forced response. Author B. A. PONOMAREV and IU. V. SOTSENKO Aviatsionnaia Tekhnika (ISSN 0579-2975), no. 2, 1986, p. 50-53. In Russian. N87-11768'# Pratt and Whitney Aircraft, East Hartford, COnn. A classification of turbines with counter-rotating rotors is OPTIMIZATION APPLICATIONS IN AIRCRAFT ENGINE DESIGN presented, and their applications in aircraft power plants of various AND TEST types are examined. The principal gasdynamic characteristics of T. K. PRATT ln NASA. Langley Research Center Recent the traditional (fixed-stator) and nontraditional (birotational) turbine Experiences in Multidisciplinary Analysis and Optimization, Part 2 designs are discussed. For birotational turbines, characteristic 18p 1984 kinematic relationshipsare obtained, and an expression is proposed Avail: NTlS HC A22/MF A01 CSCL 21E for determining the gasdynamic loading parameter. V.L. Starting with the NASA-sponsored STAEBL program, optimization methods based primarily upon the versatile program N87-11731'# National Aeronautics and Space Administration. COPES/CONMIN were introduced over the past few years to a Lewis Research Center, Cleveland, Ohio. broad spectrum of engineering problems in structural optimization, STAEBL STRUCTURAL TAILORING OF ENGINE BLADES, engine design, engine test, and more recently, manufacturing PHASE 2 processes. By automating design and testing processes, many M. S. HlRSCHBElN and K. W. BROWN (Pratt and Whitney Aircraft, repetitive and costly trade-off studies have been replaced by East Hartford, Conn.) ln NASA. Langley Research Center Recent optimization procedures. Rather than taking engineers and Experiences in Multidisciplinary Analysis and Optimization, Part 1 designers out of the loop, optimization has, in fact, put them more 13p 1984 in control by providing sophisticated search techniques. The Avail: NTlS HC A22/MF A01 CSCL 21E ultimate decision whether to accept or reject an optimal feasible The Structural Tailoring of Engine Blades (STAEBL) program design still rests with the analyst. Feedback obtained from this was initiated at NASA Lewis Research Center in 1980 to introduce decision process has been invaluable since it can be incorporated optimal structural tailoring into the design process for aircraft gas into the optimization procedure to make it more intelligent. On turbine engine blades. The standard procedure for blade design several occasions, optimization procedures have produced novel is highly iterative with the engineer directly providing most of the designs, such as the nonsymmetric placement of rotor case decisions that control the design process. The goal of the STAEBL stiffener rings, not anticipated by engineering designers. In another program has been to develop an automated approach to generate case, a particularly difficult resonance contraint could not be structurally optimal blade designs. The program has evolved as a satisfied using hand iterations for a compressor blade, when the three-phase effort with the developmental work being performed STAEBL program was applied to the problem, a feasible solution contractually by Pratt & Whitney Aircraft. Phase 1 was intended was obtained in just two iterations. Author as a proof of concept in which two fan blades were structurally tailored to meet a full set of structural design constraints while N87-11769'# Michigan Univ., Ann Arbor. minimizing DOC+I (direct operating cost plus interest) for a ON OPTIMAL DESIGN FOR THE BLADE-ROOT/HUB representative aircraft. This phase was successfully completed and INTERFACE IN JET ENGINES was reported in reference 1 and 2. Phase 2 has recently been N. KlKUCHl and J. E. TAYLOR ln NASA. Langley Research completed and is the basis for this discussion. During this phase, Center Recent Experiences in Multidisciplinary Analysis and three tasks were accomplished: (1) a nonproprietary structural Optimization, Part 2 14 p 1984 tailoring computer code was developed; (2) a dedicated (Contract NAG3-388) approximate finite-element analysis was developed; and (3) an Avail: NTlS HC A22/MF A01 CSCL 21E approximate large-deflection analysis was developed to assess Two major problems identified with the design of the local foreign object damage. Phase 3 is just beginning and is blade-root/hub interface are discussed. The first is the so-called designed to incorporated aerodynamic analyses directly into the friction contact problem which has two special features: unilateral structural tailoring system in order to relax current geometric contact and Coulomb's friction. One of the difficulties in this problem constraints. Author is that the portions of contact and sticking/sliding surfaces are not known a priori. The second is the shape optimization problem N87-11732'# Virginia Polytechnic Inst. and State Univ., which is characterized either by the minimization of the maximum Blacksburg. Dept. of Aerospace and Ocean Engineering. contact pressure or by the minimization of the equivalent stress OPTIMIZATION OF CASCADE BLADE MlSTUNlNG UNDER on the boundary. Design variables are the shapes of the blade-root FLUlTER AND FORCED RESPONSE CONSTRAINTS and the hub. It is noted that friction contact and shape optimization D. V. MURTHY and R. T. HAFTKA ln NASA. Langley Research problems are strongly coupled in the present design problem. Center Recent Experiences in Multidisciplinary Analysis and Author Optimization, Part 1 15 p 1984 (Contract NAG3-347) N87-11788'# Transmission Research, Inc., Cleveland, Ohio. Avail: NTlS HC A22/MF A01 CSCL 21E THE 3600 HP SPLIT-TORQUE HELICOPTER TRANSMISSION In the development of modern turbomachinery. problems of G. WHITE 18 Dec. 1985 95 p flutter instabilities and excessive forced response of a cascade of (Contract NAS3-23931) blades that were encountered have often turned out to be extremely (NASA-CR-174932; NAS 1.26:174932) Avail: NTlS HC AO5/MF difficult to eliminate. The study of these instabilities and the forced A01 CSCL21E response is complicated by the presence of mistuning; that is. Final design details of a helicopter transmission that is powered small differences among the individual blades. The theory of by GE twin T 700 engines each rated at 1800 hp are presented. mistuned cascade behavior shows that mistuning can have a It is demonstrated that in comparison with conventional helicopter beneficial effect on the stability of the rotor. This beneficial effect transmission arrangements the split torque design offers: weight is produced by the coupling between the more stable and less reduction of 15%; reduction in drive train losses of 9%; and stable flutter modes introduced by mistuning. The effect of improved reliability resulting from redundant drive paths between mistuning on the forced response can be either beneficial or the two engines and the main shaft. The transmission fits within

106 07 AIRCRAFT PROPULSION AND POWER the NASA LeRC 3000 hp Test Stand and accepts the existing N87-11792# Materials Research Labs., Ascot Vale (Australia). positions for engine inputs, main shaft, connecting drive shafts, INVESTIGATION OF COATING PERFORMANCE AND and the cradle attachment points. One necessary change to the CORROSION OF COMPRESSOR COMPONENTS IN THE test stand involved gear trains of different ratio in the tail drive TF30-P-3 ENGINE OF FlllC AIRCRAFT gearbox. Progressive uprating of engine input power from 3600 to L. V. WAKE and 6. S. SMITH Jan. 1986 32 p 4500 hp twin engine rating is allowed for in the design. In this (AD-A168802; MRL-R-984) Avail: NTlS HC AOWMF A01 CSCL way the test transmission will provide a base for several years of 11c analytical, research, and component development effort targeted This report examines factors involved in the degradation of at improving the performance and reliability of helicopter the protective coating, Chromalloy S-A12, employed on the low transmission. Author pressure compressor stators in the Pratt and Whitney TF30-P-3 engine of an RAAF F111 aircraft. The study is confined to the 7th stage of the engine (4th stage; low pressure compressor). The stator examined had experienced considerable corrosion after only 427 hours operation. Stators on other engines are failing for N87-11789*# Solar Turbines International, San Diego, Calif. similar reasons. Small corrosion nodules were present on specific FABRICATION OF COOLED RADIAL TURBINE ROTOR Final areas of each stator vane coating. Sections on the outer ring or Report shroud were found to be corroded along a geometric arc around A. N. HAMMER, G. G. AIGRET, T. P. PSICHOGIOS, and C. the 6 o’clock position of the stage. These included: (1) both RODGERS Jun. 1986 258 p surfaces of the outer shroud or ring (2) the air seal around the (Contract NAS3-22513; DA PROJ. 1L1-612209-AH-76) shroud and (3) the area underneath the air path seal or rub strip. (NASA-CR-179503; NAS 1.26:179503; SR86-R-4938-39) Avail: The corrosion nodules on the vanes were associated with NTlS HC A12/MF A01 CSCL 21E discontinuities in the coating. These discontinuities resulted in A design and fabrication program was conducted to evaluate breakdown of the diffusion coating in surrounding areas forming a unique concept for constructing a cooled, high temperature radial aluminium, chromium and iron oxides. The elements sulphur and turbine rotor. This concept, called split blade fabrication was chlorine and to a lesser extent calcium and potassium were also developed as an alternative to internal ceramic coring. In this found in the corrosion deposits. These elements are present in technique, the internal cooling cavity is created without flow dividers the local water supply and a detergent used for aircraft washing. or any other detail by a solid (and therefore stronger) ceramic Examination of the compressor washing and drying procedures plate which can be more firmly anchored within the casting shell are recommended. GRA mold than can conventional detailed ceramic cores. Casting is conducted in the conventional manner, except that the finished product, instead of having finished internal cooling passages, is N87-11793# Rolls-Royce Ltd., Derby (England). now a split blade. The internal details of the blade are created CONTROL OF GAS TURBINES. THE FUTURE: IS A RADICAL separately together with a carrier sheet. The inserts are superalloy. APPROACH NEEDED? Both are produced by essentially the same software such that P. H. RILEY 12 Feb. 1986 26 p *-.I- --..*r FT., n,. non. 1, they are a net fit. The carrier assemblies are loaded into the split (rivn-ywya, c I IY-00-JOU14) Avail: KIS HC ?\93/MF AO! blade and the edges sealed by welding. The entire wheel is Hot An engine control system which considers systems as well as Isostatic Pressed (HIPed), braze bonding the internal details to individual component changes is supported. It is argued that by the inside of the blades. During this program, two wheels were moving devices which dissipate a large amount of power away successfully produced by the split blade fabrication technique. from the electronic engine control (EEC) box, inflight shutdown Author rate due to overheating can be reduced. The EEC reliability per actuator can be improved by changing to an on/off rather than a variable current transducer. ESA

N87-11790*# National Aeronautics and Space Administration. N87-12560# Cambridge Univ. (England). Dept. of Engineering. Lewis Research Center, Cleveland, Ohio. VISUALISATION OF AXIAL TURBINE TIP CLEARANCE FLOW COMPOUND CYCLE ENGINE PROGRAM USING A LINEAR CASCADE G. A. BOBULA, W. T. WINTUCKY, and J. G. CASTOR (Garrett J. P. BINDON 1986 66 p Turbine Engine Co., Phoenix, Ariz.) 1986 23 p Presented at (CUED/A-TURBO/TR-l22; ISSN-0309-6521) Avail: NTlS HC the Rotary Wing Propulsion System Specialist Meeting, A04/MF A01 Williamsburg, Va., 12-14 Nov. 1986; sponsored by the American Gas tracer techniques were not successful in revealing anything Helicopter Society except the very generalized movement of fluid from the mainstream (Contract DA PROJ. 1L1-62209-AH-76) into the tip clearance gap. Smoke flow visualization at low Reynolds (NASA-TM-88879; E-3286; NAS 1.26188879; numbers revealed much of the intricate detail of the flow structure USAAVSCOM-TR-86-C-37) Avail: NTlS HC A02/MF A01 CSCL in and around the tip clearance region. Smoke traces were injected 21 E both into the mainstream fluid via a rake and also through holes The Compound Cycle Engine (CCE) is a highly turbocharged, in the blade surface. At low values of clearance, there was no power compounded power plant which combines the lightweight evidence of any separation bubble in the clearance gap and the pressure rise capability of a gas turbine with the high efficiency of flow was attached and well behaved as it moved from pressure a diesel. When optimized for a rotorcraft, the CCE will reduce fuel to suction side. Traces injected on the pressure surface moved burned for a typical 2 hr (plus 30 min reserve) mission by 30 to radially to enter the clearance gap. In passing round the pressure 40 percent when compared to a conventional advanced technology corner, the traces became transparent indicating an acceleration gas turbine. The CCE can provide a 50 percent increase in around the corner. This confirms the measurements elsewhere of range-payload product on this mission. A program to establish the extremely low values of pressure on the pressure surface corner. technology base for a Compound Cycle Engine is presented. The This local high velocity would cause a high heat transfer coefficient goal of this program is to research and develop those technologies on the corner. A test was done to investigate the possibility of which are barriers to demonstrating a multicylinder diesel core in cooling the pressure corner by radially exhausting cooling air from the early 1990’s. The major activity underway is a three-phased the pressure surface near the tip. Qualitative heat transfer studies contract with the Garrett Turbine Engine Company to perform: (1) using a radiantly heated optical film appeared not to be able to a light helicopter feasibility study, (2) component technology resolve the small scale effects near the pressure corner but did development, and (3) lubricant and material research and clearly show the area of low heat transfer where the separation development. Other related activities are also presented. Author bubble flow stagnates and separates. Author

107 07 AIRCRAFT PROPULSION AND POWER

N87-12561# Department of the Air Force, Washington, D.C. of interlocking flanges. A two piece impingement plate which is THRUST REVERSER-EXHAUST NOZZLE ASSEMBLY FOR A positioned adjacent to the air seal controls and meters cooling air GAS TURBINE ENGINE Patent flow that cools ceramic seal. The backside of air seal is thereby E. B. THAYER, inventor (to Air Force) 27 May 1986 8 p fully cooled before heated cooling air is exhausted from the seal Supersedes AD-DO1 1101 through holes at expansion slots and edge holes at the axial (AD-DO12390; US-PATENT-4,591,097; edges of the air seal. GRA US-PATENT-APPL-SN-611041; US-PATENT-CLASS-239-265.29) Avail: US Patent and Trademark Office CSCL 21 E N87-12565# Sverdrup Technology, Inc., Arnold Air Force Station, This patent discloses an improved thrust reverserlexhaust Tenn. nozzle assembly which has a plurality of blocker devices located EFFECTS OF TEST CELL RECIRCULATION ON HIGH-BYPASS in the divergent section of the exhaust nozzle and a plurality of TURBOFAN ENGINES DURING SIMULATED ALTITUDE TESTS deflector devices located in the convergent section of the nozzle. Final Report, Oct. 1984 - May 1985 The blocker and deflector devices are linked together such that R. M. DUGAS Aug. 1986 89 p Prepared in cooperation with they move simultaneously and maintain a substantially constant AEDC, Arnold AFS, Tenn. engine between forward and reverse thrust conditions. GRA (AD-A171418; AEDC-TR-85-55) Avail: NTlS HC AO5/MF A01 CSCL 21E N87-12562# Allied Bendix Aerospace, Utica, N.Y. Fluid Power An experimental and analytical program was conducted to Div. determine the nature of the flow field around a subscale model of COMPONENT IMPROVEMENT PROGRAM TASK 83-01,36E133 a high bypass turbofan engine installed in a representatively scaled AIR TURBINE STARTER altitude test cell. The engine model employed variable geometry L. WILLIAMS Feb. 1986 36 p and flow conditions in order to determine their effects on test cell (Contract NO001 9-80-G-0607) recirculating flows, which can affect engine performance during (AD-A169483; REPT-8720-3173U) Avail: NTlS HC AO3/MF A01 altitude testing. Flow field data were obtained from both two axis CSCL 09c laser Doppler velocimeters, as well as from pressure and The objective of this task was to replace the mechanical cutout temperature instrumentation installed on the model and test cell. switch with a solid-state electronic cutout switch to improve Review of full and 1/10 scale test data and the results of the accuracy and reliability of the automatic start cycle termination in subscale tests indicate that test cell recirculation effects are a the S-3A and F-14A aircraft. The function of the cutout switch is function of cell geometry. Measurement of test cell effects is to terminate the start cycle at a predetermined speed. It was dependent on a baseline test configuration, such as an outdoor determined that the existing electronic circuit can be used for the test, where the effects are not present. GRA 36E133/123 with only a minor resistor change to accommodate the subject unit’s cutout speed. Breadboard testing was successfully completed and satisfactorily demonstrated feasibility. GRA

N87-12563# Dayton Univ., Ohio. Research Inst. AIRCRAFT STABILITY AND CONTROL RESEARCH ON MECHANICAL PROPERTIES FOR ENGINE LIFE PREDICTION Interim Report, 1 Aug. 1984 - 31 Jul. 1985 Includes aircraft handling qualities; piloting; flight controls; and N. E. ASHBAUGH, M. KHOBAIB, G. A. HARTMAN, T. autopilots. WEERASOORIYA, and A. M. RAJENDRAN May 1986 74 p (Contract F33615-84-C-5051) (AD-A169570; UDR-TR-85-132; AFWAL-TR-85-4154) Avail: A87-13341*# National Aeronautics and Space Administration. NTlS HC A04/MF A01 CSCL 20K Flight Research Center, Edwards, Calif. Analytical and experimental investigations have been performed AEROELASTIC CONTROL OF OBLIQUE-WING AIRCRAFT to determine crack growth behavior of metals under conditions J. J. BURKEN, G. B. GILYARD (NASA, Flight Research Center, typical of the service environments of aircraft gas turbine engines. Edwards, CA), and G. S. ALAG (Western Michigan University. To evaluate baseline crack growth behavior, investigations have Kalamazoo, MI) IN: 1986 American Control Conference, 5th, also been conducted at elevated temperature in vacuum. The Seattle, WA, June 18-20, 1986, Proceedings. Volume 1 . New work performed can be divided into three general categories -- York, Institute of Electrical and Electronics Engineers, 1986, p. development of experimental and automation techniques, material 463-471. Previously announced in STAR as N86-26340. refs characterization testing, and analytic studies. An automated laser The U.S. Navy and NASA are currently involved in the design interferometric displacement-measurement system using linear and development of an unsymmetric-skew-wing aircraft capable array cards has been developed. Enhancements of existing system of 65 deg wing sweep and flight at Mach 1.6. A generic skew-wing for the measurement of crack lengths and displacements are aircraft model was developed for 45 deg wing skew at a flight described. A number of computer automation applications are also condition of Mach 0.70 and 3048 m altitude. At this flight condition described. Fatigue and creep crack growth tests and creep rupture the aircraft has a wing flutter mode. An active implementable control and hot corrosion tests were performed. Description of the law was developed using the linear quadratic Gaussian design experimental techniques and the results for these tests are technique. A method of modal residualization was used to reduce included. Results of analytical investigations in both material the order of the controller used for flutter suppression. Author modeling and methodology development are presented, including discussions of applications within the laboratory. GRA A87-13342‘ University of Western Michigan, Kalamazoo. DECOUPLING CONTROL SYNTHESIS FOR AN OBLIQUE-WING N87-12564# Department of the Air Force, Washington, D.C. AIRCRAFT TURBINE AIR SEAL WITH FULL BACKSIDE COOLING Patent G. S. ALAG (Western Michigan University, Kalamazoo, MI), R. W. Appllcatlon KEMPEL, and J. W. PAHLE (NASA, Flight Research Center, G. LIANG, inventor (to Air Force) 12 May 1986 21 p Edwards, CA) IN: 1986 American Control Conference, 5th, Seattle, (AD-DO12405; US-PATENT-APPL-SN-861909) Avail: NTlS HC WA, June 18-20, 1986, Proceedings. Volume 1 . New York, Institute AO2IMF A01 CSCL 11A of Electrical and Electronics Engineers, 1986, p. 472-480. This patent application relates to air seals for use in Previously announced in STAR as N86-26339. refs turbo-machinery and, more particularly relates to an air seal Interest in oblique-wing aircraft has surfaced periodically since assembly with increased cooling that is adapted to withstand the 1940’s. This concept offers some substantial aerodynamic elevated engine operating temperatures. The air seal comprises a performance advantages but also has significant aerodynamic and full 360 degree seal ring that assemblies to the turbine by means inertial cross-coupling between the aircraft longitudinal and

108 08 AIRCRAFT STABILITY AND CONTROL lateral-directional axes. This paper presents a technique for A87-13352 synthesizing a decoupling controller while providing the desired FLIGHT CONTROL DESIGN USING NONLINEAR INVERSE stability augmentation. The proposed synthesis procedure uses DYNAMICS the concept of a real model-following control system. Feedforward R. F. STENGEL (Princeton University, NJ) and S. H. LANE IN: gains are selected on the assumption that perfect model-following 1986 American Control Conference, 5th. Seattle, WA, June 18-20, conditions are satisfied. The feedback gains are obtained by using 1986, Proceedings. Volume 1 . New York, Institute of Electrical eigensystem assignment, and the aircraft is stabilized by using and Electronics Engineers, 1986, p. 587-596. Research sponsored partial state feedback. The effectiveness of the control laws by the Schultz Foundation. refs developed in achieving the desired decoupling is illustrated by Aircraft in extreme flight conditions such as stalls and spins application to linearized equations of motion of an oblique-wing experience nonlinear forces and moments generated from high aircraft for a given flight condition. Author angles of attack and high angular rates. Flight control systems based upon nonlinear inverse dynamics offer the potential for providing improved levels of safety and performance in these flight A87-13344 conditions over the competing designs developed using linearizing AIRCRAFT FLUTTER SUPPRESSION VIA ADAPTIVE LOG assumptions. Inverse dynamics are generated for specific command C0 N T R 0 L variable sets of a 12-state nonlinear aircraft model to develop a A. CHAKRAVARTY (Boeing Commercial Airplane Co., Seattle, WA) control system that provides satisfactory response over the entire and J. B. MOORE (Australian National University, Canberra, flight envelope. Detailed descriptions of the inertial dynamic and Australia) IN: 1986 American Control Conference, 5th, Seattle, aerodynamic models are given, and it is shown how the command WA, June 18-20, 1986, Proceedings. Volume 1 . New York, Institute variable sets are altered as functions of the system state to add of Electrical and Electronics Engineers, 1986, p. 488-493. stall prevention features to the system. Simulation results are An adaptive linear quadratic Gaussian based constant gain presented for various mission objectives over a range of flight controller was implemented for an aircraft with one flutter mode conditions to confirm the effectiveness of the design. Author (at 3.25 hz). The controller scheme was applied in a simulated aircraft experiencing Dryden turbulence. The discrete-time LQG regulator was defined with time-varying recursive Riccati equations and employs a flutter mode estimate to generate the required control to attain stability. The controller has a low sensitivity to the large amounts of spillover dynamics in the flutter estimate A87-13355 because the aileron responses to the estimate is a second-order DYNAMIC OUTPUT FEEDBACK FLIGHT CONTROL LAWS system with the estimate as the primary mode. The controller bandwidth is thereby single-input, single-output functioning in the USING EIGENSTRUCTURE ASSIGNMENT K. M. SOBEL (Lockheed-California Co., Burbank) and E. Y. region of the flutter mode frequency and providing a 180 deg phase margin. M.S.K. SHAPIRO (HR Textron, Inc., Valencia, CA) IN: 1986 American Control Conference, 5th. Seattle, WA, June 18-20, 1986, Proceedings. Volume 1 . New York, Institute of Electrical and Electronics Engineers, 1 Y86, p. 605-610. refs A87-13346 The eigenstructure assignment flight control design BANK-TO-TURN UTILIZING SAMPLED DATA NON-LINEAR methodology is extended to include dynamic compensator CONTROL synthesis. Dynamic compensators may be designed via D. CAUGHLIN (USAF, Edwards AFB, CA) and T. BULLOCK eigenstruc!ure assignment by utilizing a composite system structure. (Florida, University, Gainesville) IN: 1986 American Control The success of this design methodology depends upon proper Conference, 5th. Seattle, WA, June 18-20, 1986, Proceedings. choice of the desired eigenvectors. An example of the lateral Volume 1 . New York, Institute of Electrical and Electronics dynamics of an L-1011 aircraft is presented to illustrate the design Engineers, 1986, p. 507, 508. method. Author Features of a nonlinear control algorithm developed for bank-to-turn homing missiles are outlined. The algorithm was constrained to 5 g acceleration in the z-axis and roling maneuvers of up to 500 deglsec. The problem was decomposed into two models: a body-oriented control law to decouple the pitch and yaw axes and an inertial point-mass model to control inertial accelerations. Methods used to compensate for a 100 g turn A87-13379 capability while only 5 deg was allowed are discussed. The system MULTIVARIABLE FLIGHT CONTROL FOR AN ATTACK estimates a closing velocity with an optimal attitude through a HELICOPTER series of rotations and projections. M.S.K. D. ENNS (Honeywell Systems and Research Center, Minneapolis, MN) IN: 1986 American Control Conference, 5th, Seattle, WA, June 18-20, 1986. Proceedings. Volume 2 . New York, Institute of A87-13347' National Aeronautics and Space Administration. Electrical and Electronics Engineers, 1986, p. 858-863. Langley Research Center, Hampton, Va. This paper discusses advanced flight control laws for the TIME SCALE ANALYSIS OF A DIGITAL FLIGHT CONTROL Apache YAH-64 helicopter. The control laws have been SYSTEM successfully flight tested and were extensively evaluated with fixed D. S. NAIDU and D. B. PRICE (NASA, Langley Research Center, base piloted simulation as part of the Advanced Rotorcraft Hampton, VA) IN: 1986 American Control Conference, 5th, Seattle, Technology Integration Flight Experiment. The control laws employ WA, June 18-20, 1986, Proceedings. Volume 1 . New York, Institute three body rate gyros, and normal and lateral accelerometers as of Electrical and Electronics Engineers, 1986, p. 509, 510. refs sensors and collective, tail rotor, anad lateral and longitudinal cyclic In this paper, consideration is given to the fifth order discrete controls. The control laws were developed to provide decoupling, model of an aircraft (longitudinal) control system which possesses gust attenuation, desensitization, and stability augmentation in the three slow (velocity, pitch angle and altitude) and two fast (angle face of aircraft modelling uncertainty. A multivariable proportional of attack and pitch angular velocity) modes and exhibits a two-time plus integral element is the basic ingredient of the control laws. scale property. Using the recent results of the time scale analysis Various analyses including frequency and time responses are of discrete control systems, the high-order discrete model is presented. Stability robustness properties of the control laws are decoupled into low-order slow and fast subsystems. The results presented using singular value and structured singular value of the decoupled system are found to be in excellent agreement techniques. Responses of the controlled helicopter to pilot and with those of the original system. Author gust inputs are presented using time histones. Author

109 08 AIRCRAFT STABILITY AND CONTROL

A87-13419' Massachusetts Inst. of Tech., Cambridge. ability to meet minimum separation distance requirementes, ability MULTIVARIABLE CONTROL OF A TWIN LIFT HELICOPTER to support large numbers of aircraft, communications requirements, SYSTEM USING THE LQG/LTR DESIGN METHODOLOGY retention of accuracy at horizontal and vertical separation maxima, A. A. RODRIGUEZ and M. ATHANS (MIT, Cambridge, MA) IN: coverage capabilities, range systems compatibility, minimum 1986 American Control Conference, 5th, Seattle, WA, June 18-20, complexity and minimum payload). A system architecture is 1986, Proceedings. Volume 2 . New York, Institute of Electrical identified with three platform options for accuracy enhancement and Electronics Engineers, 1986, p. 1325-1332. Previously and range interoperability. Author announced in STAR as N86-28956. refs (Contract NAG2-297) Guidelines for developing a multivariable centralized automatic flight control system (AFCS) for a twin lift helicopter system (TLHS) A87-13648# are presented. Singular value ideas are used to formulate DIRECT SOLUTION OF FLUTTER EQUATIONS WITH performance and stability robustness specifications. A linear INTERACTIVE GRAPHICS PROCEDURE Quadratic Gaussian with Loop Transfer Recovery (LQG/LTR) I. HERSZBERG (Royal Melbourne Institute of Technology, design is obtained and evaluated. Author Australia) IN: Israel Annual Conference on Aviation and Astronautics, 27th, Haifa, Israel, February 27, 28. 1985, Collection A87-13426 of Papers . Haifa, Israei, Technion - Israel Institute of Technology, RENEWED INTEREST IN HINGE MOMENT MODELS FOR 1986, p. 135-143. refs FAILURE DETECTION AND ISOLATION A direct method for the solution of flutter equations is presented. H. N. GROSS, P. R. CHANDLER, and R. A. ESLINGER (USAF, This method enables the designer to determine the relationship Wright Aeronautical Laboratories, Wright-Patterson AFB. OH) IN: between any two parameters which satisfy the flutter equations. 1986 American Control Conference, 5th, Seattle, WA, June 18-20, The solution procedure is described and some of the computational 1986, Proceedings. Volume 3 . New York, Institute of Electrical considerations are briefly discussed. An example is presented of and Electronics Engineers, 1986, p. 1497-1502. refs the use of this method in the investigation and solution of a flutter A hinge moment model (HMM) was developed for the direct problem on the Jindivik MK 111 B (an RPV). A comparison is made lift flap of the Total In Flight Simulator from data obtained during of the direct and classical methods and a list of some of the a recent flight test. A typical linear trim point hinge HMM did not advantages an disadvantages of the direct method is presented. account for the significant oscillations in differential pressure due Some of the advantages of the direct method are: it is several to nonlinear effects. An algorithm for the synthesis of polynomial orders of magnitude faster for the preparation of plots other than networks was used to construct a nonlinear model of differential the standard V-g-omega plots; it does not relay on any particular pressure. Using readily measurable flight variables, the new model formulation of the flutter equations; and it may be used for residuals are shown to have a smaller mean square error. The determining subcritical response. Author estimate of the hinge moment is thus more accurate, leading to better detection, isolation, and estimation capability. It is concluded that this will help reduce the false alarm rate which has been a chronic problem with HMMs. B.J. A87-13654# A87-13435' Alphatech, Inc., Burlington, Mass. COMBINED GUIDANCE - FLIGHT CONTROL OF ATMOSPHERIC EVALUATION OF DETECTABILITY AND DISTINGUISHABILITY VEHICLES OF AIRCRAFT CONTROL ELEMENT FAILURES USING FLIGHT M. SHEFER (Rafael Armament Development Authority, Haifa, TEST DATA Israel) IN: Israel Annual Conference on Aviation and Astronautics, J. L. WEISS, J. S. ETERNO, and J. Y. HSU (Alphatech, Inc., 27th, Haifa, Israel, February 27, 28, 1985, Collection of Papers . Burlington, MA) IN: 1986 American Control Conference, 5th, Haifa, Israel, Technion - Israel Institute of Technology, 1986, p. Seattle, WA, June 18-20, 1986, Proceedings. Volume 3 . New 180-184. York, Institute of Electrical and Electronics Engineers, 1986, p. Guidance and flight control, traditionally two distinct problems, 1551-1 557. refs are combined here together in a minimal state model. Based on (Contract NASl-18004) classical optimal control, a computerized design procedure is This paper examines the detectability and distinguishability of applied to the overall problem. This yields a fast design cycle as control element failures on the 8-737 aircraft. The results of Weiss well as a simply implemented solution. Author (1 985) are used to define decentralized residuals from analytic redundancy relationships, and the results of Weiss et at. (1984) are used to define the probabilistic distance measures which provide bounds on the minimum achievable probabilities or error. A87- 13991 # The residual signals are then generated using data which were DESIGN CONSIDERATIONS FOR FLY-BY-WIRE CONTROL OF recorded during a landing approach of the NASA-Langley Advanced NEW AIRBUS AIRCRAFT [KONZEPTIONELLE Transport Operations (ATOPS) transportation systems research UEBERLEGUNGEN ZUR FLY-BY-WIRE-STEUERUNG FUER vehicle (TSRV). The distance measures are computed using NEUE AIRBUS-FLUGZEUGE] estimates of the statistics of these residual signals. Author U. CARL (Messerschmitt-Boelkow-Blohm GmbH, Bremen, West Germany) BMFT, Statusseminar ueber Luftfahrtforschung und A87-13536# Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986. MTFCS (MULTIPLE TARGET FORMATION FLIGHT CONTROL Paper. 60 p. In German. refs SYSTEM) FORMATION POSITION SENSOR TRADE-OFF (Contract BMFT-LFL-8360-7) ANALYSIS (MBB-UT-222-86) L. NEWMAN (U.S. Navy, Naval Air Development Center, The development of an experimental triaxial fly-by-wire (FBW) Warminster, PA) IN: ION, National Technical Meeting, Long Beach, primary flight-control system for future Airbus transport aircraft is CA, January 21-23, 1986. Proceedings . Washington, DC, Institute discussed in a status report. The biaxial FBW system used in the of Navigation, 1986, p. 23-32. refs A320 is briefly characterized; and a triaxial system with integrated An analysis is performed to identify a navigation/position sensor active control functions. fiber-optic communications buses, and that best meets the requirements for a multiple target formation quad-redundant fault-tolerant computers and actuators controllers control system (MTFCS). A set of basic alternatives was chosen is described in detail and illustrated with block diagrams. from among all classes of systems. GPS (Global Positioning Consideration is given to the definition and validation of the control System) derivative systems were selected from the basic laws, tests of the FBW system using the A300 simulator, and alternatives through an examination of distinguishing trade-offs (the Planned tests using an integrated simulation system. T.K.

110 08 AIRCRAFT STABILITY AND CONTROL

A87-14013 and concepts for stall/spin technology are identified. Specific REDUNDANT COMPUTER SYSTEM FOR FLY-BY-WIRE results discussed include: (1) development and validation of test CONTROLS [REDUNDANTES RECHNERSYSTEM FUER techniques and analysis methods; (2) studies of airplane spinning FLY-BY-WIRE STEUERUNGEN] and spin recovery characteristics; and (3) concepts designed to R. REICHEL and F. BOOS (Bodenseewerk Geraetetechnik GmbH, increase the spin resistance of general aviation-type vehicles. Ueberlingen, West Germany) BMFT, Statusseminar ueber V.L. Luftfahrtforschung und Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, Paper. 29 p. In German. A87-14 135# A redundant computer system for active flight control in MODELING OF THE AIRCRAFT MECHANICAL CONTROL fly-by-wire (FBW) systems is discussed. The integration of the SYSTEM FBW control system into the general system is summarized, and X. XU, T. YAO, Y. FENG, and S. MU0 (Beijing Institute of different redundant computer systems are intercompared. The Aeronautics and Astronautics, People’s Republic of China) Acta management of computer redundancy is addressed, and the Aeronautica et Astronautica Sinica, vol. 7, June 1986, p. 256-265. coupling of sensors to the FBW control system is considered. In Chinese, with abstract in English. refs C.D. The mode analysis method for multipole-degree-of-freedom systems, model-uncoupling and order-reduction method, digital A87-14021# simulation methods for nonlinear systems, system-identificationand POSSIBILITIES FOR OPTIMIZATION AND HIGHER-HARMONIC parameter-estimation techniques, and various available calculating CONTROL OF HELICOPTER MAIN ROTORS BY BLADE methods are combined in this paper to obtain an engineering FEATHERING [MOEGLICHKEITEN ZUR OPTIMIERUNG UND calculating method for the fundamental frequency. This method is HOEHERHARMONISCHEN STEUERUNG VON HUBSCHRAUBER- used to establish the nonlinear-approach model of the mechanical HAUPTROTOREN DURCH BLAlTVERSTELLSYSTEME] system, analyze the system dynamic characteristics, and give the BLAlTVERSTELLSYSTEMEl equivalent linear model of the mechanical system. The relation P. RICHTER and M. PLATZER (Henschel-Flugzeug-WerkeGmbH, between various major parameters and handling quality is Kassel, West Germany) BMFT, Statusseminar ueber discussed. In reference to the model-uncoupling part, it has been Luftfahrtforschung und Luftfahrttechnologie, Munich, West proved by flight test. Author Germany, Apr. 28-30, 1986, Paper. 23 p. In German. refs The current status of the development of a helicopter-rotor A87-14136# vibration-control system is reported. The system is based on THE METHOD OF CALCULATING THE DESIRED FLIGHT PATH hydraulic actuators mounted between the swash plate and the OF TERRAIN FOLLOWING TECHNIQUE WITH CIRCULAR ARC blade-pitch control arms. Consideration is given to the operating SPLINE principle of the electrical control circuits, the actuator loads, the Y. ZHENG and C. CHEN (Nanjing Aeronautical Institute, People’s time sequence of operations, feedback loops, safety features, and Republic of China) Acta Aeronautica et Astronautica Sinica, vol. the possible extension of the system principles to single-blade 7, June 1986, p. 266-272. In Chinese, with abstract in English. control. Drawings, graphs, diagrams, and photographs are refs provided. T.K. In the algorithm-optimal control algorithm for a terrain-following (TFj sysiem presenied by Funk and Kdiy jiS75j ihe dasiied flight A87-14031*# National Aeronautics and Space Administration. path (DFP) is designed using cubic splines from the sampled data Langley Research Center, Hampton, Va. of terrain contour; then the aircraft is forced to fly along this path EXPLORATORY WIND-TUNNEL INVESTIGATION OF THE by a corresponding optimal controller. This paper presents a STABILITY AND CONTROL CHARACTERISTICSOF ADVANCED method of designing DFP with circular-arc splines. Under forty GENERAL AVIATION CONFIGURATIONS terrain conditions, this method is compared with the DFP of L. P. YIP, P. M. KING, C. B. MUCHMORE, and P. DAVIS (NASA, cubic-spline and proved to be feasible. Author Langley Research Center, Hampton, VA) AIAA, General Aviation Technology Conference, Anaheim, CA, Sept. 29-Oct. 1, 1986. 20 A87-14142# p. refs OPTIMAL DISCRETE DESIGN OF DIGITAL FLIGHT CONTROL (AIAA PAPER 86-2596) SYSTEM Results of low-speed wind-tunnel investigations are presented L. LI (Institute of Automatic Flight Control System, People’s for two general aviation configurations: the AVTEK canard Republic of China) Acta Aeronautica et Astronautica Sinica, vol. configuration and the DeVore conventional configuration. 7, June 1986, p. 305-312. In Chinese, with abstract in English. Cooperative research programs were undertaken by industry and An engineering method of optimal discrete regulator design for NASA to jointly conduct tests in the NASA Langley 12-Foot digital flight control system is described. By using the engineering Low-Speed Wind Tunnel to explore stability and control method proposed here, the continuous quadratic performance characteristics of each configuration. A 1/Bscale AVTEK model criterion can be simply transformed to a discrete version. The and a 1/6-scale DeVore model were tested over an angle-of-attack C-asterisk and D-asterisk criteria and some additional flying quality range of up to 45 deg and an angle-of-sideslip range of up to 20 requirements are used for constituting the quadratic cost function deg. Results from the AVTEK test are presented with an emphasis and to precisely determine the value of the elements of the on the effects of configuration on the stall and poststall weighting matrix without repeated adjustment. An example using characteristics. Results from the DeVore test are presented with this method to synthesize the stability augmentation system and emphasis on the effects of wing leading-edge droop design on autopilot is given. Author spin resistance characteristics. Author A87-14367# A87-14032’# National Aeronautics and Space Administration. COORDINATED TURN RELATIONS - A GRAPHICAL Langley Research Center, Hampton, Va. REPRESENTATION SUMMARY OF NASA STALLBPIN RESEARCH FOR GENERAL C. LIBOVE (Syracuse University, NY) Journal of Aircraft (ISSN AVIATION CONFIGURATIONS 0021-8669), vol. 23, Sept. 1986, p. 725, 726. J. R. CHAMBERS and H. P. STOUGH, 111 (NASA, Langley Research Relationships between the flight parameters involved in a Center, Hampton, VA) AIAA, General Aviation Technology controlled turn are analyzed and used to generate graphic Conference, Anaheim, CA, Sept. 29-Oct. 1, 1986. 13 p. refs representations which are suitable for identifying performance (AIAA PAPER 86-2597) windows. Governing equations are defined for lift at the bank The major milestones of stall/spin research conducted in the angle, the aircraft weight, the load factor, the turn rate and the past under NACAINASA programs are reviewed, and recent results lift. Subsidiary relations are developed among the governing offering promise for further improvements in design methodology parameters. Drag and thrust are absent from the basic parameters,

111 08 AIRCRAFT STABILITY AND CONTROL but can be evaluated separately. The graphs obtained from the performance required by statically unstable aircraft; (3) an relationships provided are useful for delineating sets of operating increasing awareness of and demand for survivability; (4) new conditions for attaining a specified turning performance. M.S.K. hydraulic valve concepts; (5) all electric airplane and electromechanical actuator programs; (6) a new look at energy A87-15212 efficient hydraulics; and (7) innovative combinations of several of THE PRINCIPLE OF OPTlMALlTY IN THE MEAN FOR the above. This paper addresses these issues, the current state FAULT-TOLERANT-SYSTEMS [PRINTSIP OPTIMAL'NOSTI v of the art of actuation system concepts, their benefits and SREDNEM TOLERANTNYKH SISTEM] shortcomings and the factors that influence the selection of a N. E. RODNISHCHEV Aviatsionnaia Tekhnika (ISSN 0579-2975), concept or design. Author no. 2, 1986, p. 54-58. In Russian. refs The problem of the optimization of nonlinear fault-tolerant A87-15479 systems in the presence of stochastic perturbations, such as white ADVANCED FLIGHT CONTROL ACTUATION SYSTEMS AND Gaussian noise, and independent failures of k out of n elements THEIR INTERFACE WITH DIGITAL COMMANDS operating in parallel, that are described by stochastic differential M. J. ANTHONY and F. MAlTOS (Fairey Hydraulics, Ltd., equations, is examined with particular reference to the terminal Hounslow, England) IN: Advanced actuation, controls and guidance systems of flight vehicles. The problem is reduced, after integration for aerospace vehicles; Proceedings of the Symposium, certain assumptions are made, to a deterministic optimization San Diego, CA, October 9, 1985 . Warrendale, PA, Society of problem with constraints. The principle of optimality in the mean Automotive Engineers, Inc., 1986, p. 23-35. is then formulated. V.L. (SAE PAPER 851754) Advanced flight control actuation systems require that the A87-15476 actuator be capable of interfacing with centralized digital computing ADVANCED ACTUATION, CONTROLS AND INTEGRATION FOR systems. The actuation specialists must consider the electro AEROSPACE VEHICLES PROCEEDINGS OF THE SYMPOSIUM, hydraulic system as a whole, including the closed loop servo SAN DIEGO, CA, OCTOBER 9,1985 electronics, from the command distribution databus to the final Symposium sponsored by SAE. Warrendale, PA, Society of output member. This paper discusses the overall approach of a Automotive Engineers, Inc. (SAE P-l70), 1986. 72 p. For individual primary flight control specialist company, with the lateral items see A87-15477 to A87-15482. implications of direct drive and multi redundanat valve (SAE P-170) configurations, higher system pressures and direct rotary The present conference gives attention to the reduction of actuation. Author system complexity in fly-by-wire aircraft flight control actuators, a systems design approach to the various actuation concept alternatives emerging in primary flight control technologies, and A87-15480 the features of advanced flight control actuation systems with ADVANCED DIGITAL OPTICAL CONTROL ACTUATION FOR emphasis on their interface with digital commands. Also considered THE ADOCS are advanced digital optical control actuation, energy-efficient F. E. SHERIF (Allied Corp., Bendix Aerospace Electrodynamics actuation employing variable displacement hydraulic control, and Div.. North Hollywood, CA) IN: Advanced actuation, controls and the preliminary design of electromechanical servosystems. O.C. integration for aerospace vehicles; Proceedings of the Symposium, San Diego, CA, October 9, 1985 . Warrendale, PA, Society of A87-15477 Automotive Engineers, Inc., 1986, p. 37-50. Army-sponsored REDUCING COMPLEXITY IN FLY-BY-WIRE FLIGHT CONTROL research. ACTUATORS (SAE PAPER 851755) B. S. LYLE (General Dynamics Corp., Fort Worth, TX) IN: The digital fly-by-wire control systems currently being developed Advanced actuation, controls and integration for aerospace for next generation aircraft are not immune to lightning, vehicles; Proceedings of the Symposium, San Diego, CA, October electromagnetic interference (EMI), and electromagnetic pulse 9, 1985 . Warrendale, PA, Society of Automotive Engineers, Inc., (EMP). Optical commands signals transmitted via fiber optic links, 1986, p. 1-7. and optical digital transducers to generate feedback signals, provide (SAE PAPER 851752) the means to overcome this hostile environment. This paper Since the inception of fly-by-wire flight control systems on describes the major elements of a Driver Actuation System high-performanceaircraft, the need for highly reliable flight control compatible with an Advanced Digital Optical Control System actuators has been evident. Actuators capable of handling multiple (ADOCS), and demonstrates the feasibility of the design concept failures in electronics and hydraulics have been specified as through presentation of bench and aircraft integration test results. necessary to obtain high mission reliability and safety. With the Author recent advances in several technology areas (namely, magnetic materials, electronics, and software capability), it seems to be A87-15481 time to reassess these stringent actuator requirements for future ENERGY EFFICIENT ACTUATION USING VARIABLE aircraft. Concepts such as control law reconfiguration, new DISPLACEMENT HYDRAULIC CONTROL techniques of actuation, aerodynamic redundancy, and systems D. J. LINTON (Sundstrand Corp., Rockford, IL) IN: Advanced integration offer the control system designer new ways of obtaining actuation, controls and integration for aerospace vehicles; mission reliability with simpler actuators. Author Proceedings of the Symposium, San Diego, CA, October 9, 1985 . Warrendale, PA, Society of Automotive Engineers, Inc., 1986, p. A87-15478 51 -55. A SYSTEM LOOK AT ACTUATION CONCEPTS AND (SAE PAPER 851757) ALTERNATIVES FOR PRIMARY FLIGHT CONTROL The features and performance characteristics of a prospective J. B. LEONARD (JBL Associates, Inc., Northport, NY) IN: variable displacement hydraulic control system for advanced Advanced actuation, controls and integration for aerospace aircraft, which promises to yield a 50-80 percent savings in average vehicles; Proceedings of the Symposium, San Diego, CA, October power consumption over conventional fixed displacement devices, 9, 1985 . Warrendale, PA, Society of Automotive Engineers, Inc., are contrasted with those of alternative advanced control systems 1986, p. 9-22. refs and pressure-profiled hydraulic systems. The pressure profiling and (SAE PAPER 851753) 8000-psi methods discussed improve weight and flow consumption, Flight control engineers and managers are facing a dilemma in but are noted to have very low efficiencies when operated below selection of actuation systems and concepts for new high peak loads. By contrast, variable-displacement hydraulics furnish performance aircraft. The dilemma is created by: (1) a demand great power savings by keeping losses nearly constant at all load for simpler, more reliable actuators; (2) a need for higher levels. O.C.

112 08 AIRCRAFT STABILITY AND CONTROL

A8746182 A87-16185 ADAPTIVE FLUlTER SUPPRESSION APPLICATION OF REGRESSION ANALYSIS TO COUPLED J. B. MOORE, D. GANGSAAS (Australian National University, RESPONSES AT HIGH ANGLES OF AlTACK Canberra, Australia), and A. CHAKRAVARTY (Boeing Co., Seattle, A. J. ROSS (Royal Aircraft Establishment, Farnborough, England) WA) IN: Identification and system parameter estimation 1985; and B. J. HOLOHAN (Kingston Polytechic, England) IN: Proceedings of the Seventh Symposium, York, England, July 3-7, Identification and system parameter estimation 1985; Proceedings 1985. Volume 1 . Oxford and New York, Pergamon Press, 1985, of the Seventh Symposium, York, England, July 3-7, 1985. Volume p. 345-349. 1 . Oxford and New York, Pergamon Press, 1985, p. 493-497. This paper presents the application of adaptive control to flutter refs suppression on a flexible aircraft. The adaptive control law is Some of the responses obtained at high angles of attack with integrated with a nominal constant gain controller and furnishes large-scale, free-flight models of aircraft exhibit coupled longitudinal the equivalent of a 180-deg phase margin at the flutter frequency. and lateral oscillations which are not predicted using mathematical The design approach blends the classical, linear-quadratic models of the aerodynamic forces and moments based on Gaussian, and adaptive-synthesis techniques to achieve a robust wind-tunnel and other free-flight data. Several possible causes control law with good performance characteristics. It is shown have been postulated but not confirmed, so stepwise regression that the adaptive controller stabilizes the flutter in the face of analysis techniques have been applied, to see if additional terms arbitrary initial parameter estimates, unmodeled stochastic inputs, in the mathematical model can be identified. The use of data and significant levels of spillover dynamics. Author from angular accelerometers has also been investigated to compare the information obtained with that from the usual linear accelerometers, angular and attitude gyros, incidence and sideslip vanes and control position transducers. Author

A8746183 AIRCRAFT CONTROL INPUT OPTIMIZATION FOR A87-16186 AERODYNAMIC DERIVATIVE ESTIMATION IN DYNAMIC PARAMETER ESTIMATION OF AIRCRAFT WITH FLY-BY-WIRE MANOEUVRES CONTROL SYSTEMS J. A. MULDER (Delft, Technische Hogeschool, Netherlands) IN: P. MEREAU and S. ABU EL ATA-DOSS (ADERSA, Palaiseau, Identification and system parameter estimation 1985; Proceedings France) IN: Identification and system parameter estimation 1985; of the Seventh Symposium, York, England, July 3-7, 1985. Volume Proceedings of the Seventh Symposium, York, England, July 3-7, 1 . Oxford and New York, Pergamon Press, 1985, p. 481-486. 1985. Volume 1 . Oxford and New York, Pergamon Press, 1985, refs p. 505-51 0. Sponsorship: Service Technique des Programmes Future prototype aircraft will be able to execute automatic flight Aeronautiques. refs test maneuvers for the estimation of aerodynamic derivatives. This (Contract STPA-83,95,009) means that methods for the optimization of input signals will be Fly-by-wire control systems (FBWCS) introduce particular of considerabig piaciicai impoiianee shce ~ptimizedinpu! ~ig~a!~correlations between ine aircraii inputs jdgfiection angles) and can accurately be implemented in flight. The present paper gives outputs which lead to biased parameter estimates in the absence a brief overview of existing methods for input signal optimization. of decorrelating actions such as extra signals. This problem has A new method is proposed which avoids some of the disadvantages been investigated with the aim of finding quickly nonbiased of earlier methods. The method is illustrated with an optimization parameter values from flight data on aircraft inputs, outputs, and of a two-dimensional input signal for a lateral flight test pilot inputs in order to provide an iterative optimization scheme maneuver. Author with good initial values. A methodology including input design, instrumental variable estimation, and automatic estimation strategy was developed, analyzed on simulated cases, and tested with real flight data. Author

A8746184 AIRCRAFT FLIGHT DATA COMPATIBILITY CHECKING USING MAXIMUM LIKELIHOOD AND EXTENDED KALMAN FILTER A87-16192 ESTIMATION MAXIMUM LIKELIHOOD ESTIMATION OF PARAMETERS IN R. J. EVANS, G. C. GOODWIN (Newcastle, University, Australia), NONLINEAR FLIGHT MECHANICS SYSTEMS R. A. FEIK, C. MARTIN (Department of Defence, Aeronautical R. V. JATEGAONKAR (National Aeronautical Laboratory, , Research Laboratories, Melbourne, Australia), and R. Bangalore, India) and E. PLAETSCHKE (DNLR, lnstitut fuer LOZANO-LEAL (Instituto Politecnico Nacional, Mexico City, Flugmechanik, Brunswick, West Germany) IN: Identification and Mexico) IN: Identification and system parameter estimation 1985; system parameter estimation 1985; Proceedings of the Seventh Proceedings of the Seventh Symposium, York, England, July 3-7, Symposium, York, England, July 3-7, 1985. Volume 1 . Oxford 1985. Volume 1 . Oxford and New York, Pergamon Press, 1985, and New York, Pergamon Press, 1985, p. 663-668. refs p. 487-492. refs Two methods for maximum-likelihood estimation of flight The considerable potential benefits of compatibility checking mechanics parameters have been developed. They are applicable of aircraft dynamic flight data has, in the past, not been fully to system models which may be nonlinear in the state and control realized when applied to real data. It is suggested in this paper variables as well as in the parameters to be estimated. The that this is partly due to the presence of errors in the real data optimization problem has been solved by using both I which are not usually accounted for in computer simulation studies. minimum-search methods and the quasi-linearization method. When factors such as instrument offset from center of gravity, Advantages and disadvantages of both methods are discussed. I measurement time delays, sinusoidal disturbances and In the latter case the need for deriving explicit sensitivity equations non-linearities are accounted for, good results can be achieved has been avoided by approximating the sensitivity coefficients by 1 with moderate quality instrumentation. The effect of these factors numerical differences. This results in a computationally attractive on the identified instrument errors are studied in this paper using implementation of the estimation method for routine applications the extended Kalman filter approach and the Maximum Likelihood to general nonlinear systems. These techniques have been applied I method. The relative merits of each approach are also studied. to the problems of kinematic consistency checking of flight test 1 Author data as well as estimation of aerodynamic derivatives. Author

113 08 AIRCRAFT STABILITY AND CONTROL

A87-16193 A87-16197 FREQUENCY DOMAIN PARAMETER ESTIMATION OF ANALYTICAL REDUNDANCY THROUGH NONLINEAR AERONAUTICAL SYSTEMS WITHOUT AND WITH TIME OBSERVERS DELAY R. BROCKHAUS (Braunschweig, Technische Universitaet, M. MARCHAND and K.-H. FU (DFVLR, lnstitut fuer Flugmechanik, Brunswick, West Germany) IN: Identification and system parameter Brunswick, West Germany) IN: Identificationand system parameter estimation 1985; Proceedings of the Seventh Symposium, York, estimation 1985; Proceedings of the Seventh Symposium, York, England, July 3-7, 1985. Volume 1 . Oxford and New York, England, July 3-7, 1985. Volume 1 . Oxford and New York, Pergamon Press, 1985, p. 71 9-724. DFG-supported research. Pergamon Press, 1985, p. 669-674. refs By using analytical redundancy the safety of flight Systems The paper considers the application of frequency domain can be improved without the use of additional measuring equipment, methods to flight test data from rotorcraft and fixed wing aircraft. provided the observer precision is sufficiently high. Nonlinear In particular, a modified frequency domain output error method is reduced observers have proven to be a good compromise between presented which can be applied to linear systems with time delays. accuracy and real time computation problems. The aerodynamic In contrast to existing methods, the new approach enables the variables, angle of sidelsip and angle of attack, are essential for combination of data from several maneuvers for one evaluation, aircraft control as well as for the supervision of a safe flight regime, the use of test records with arbitrary initial state conditions x(t = but they can only be measured by external sensors with low 0), and the direct identification of time delays (instead of using reliability. Therefore they are good example to be used in an Pade-approximation). Results are presented from the identication investigation of the applicability of nonlinear observers for analytical of a six-degrees-of-freedomhelicopter model (Bo-105 Research redundancy. The analysis of the observability structure of the Helicopter of the DFVLR) as well as from the identifiation of an process led to a stepwise syystem decomposition and to subsystem equivalent low order system with time delay (HFB local observers of different complexity. These observers have been 320-In-Flight-Simulatorof the DFVLR). Author optimized in a nonlinear simulation and tested using original flight test data. The resulting accuracy is sufficient for control purposes, even in heavy flight maneuvers (such as the turn initiation or steady sideslip). One type of observer has been implemented into the on-board computer of a DO 28 test aircraft, and the good A87-16 195 flight test results showed that this concept is well suited for on-line SENSOR FAILURE DETECTION IN FLIGHT CONTROL SYSTEMS operation. Author USING DETERMINISTIC OBSERVERS N. STUCKENBERG (DFVLR, lnstitut fuer Flugfuehrung, Brunswick, A87-16202 West Germany) IN: Identification and system parameter estimation DETERMINATION OF NONLINEAR AERODYNAMIC 1985; Proceedings of the Seventh Symposium, York. England, July COEFFICIENTS USING THE ESTIMATION-BEFORE-MODELING 3-7, 1985. Volume 1 . Oxford and New York, Pergamon Press, METHODS 1985, p. 705-710. refs M. SRI-JAYANTHA (IBM Thomas J. Watson Research Center, A sensor failure-detection concept is presented providing a Yorktown Heights, NY) and R. F. STENGEL (Princeton University, duplex sensor configuration with the fail-operational properties of NJ) IN: Identification and system parameter estimation 1985; a conventional triplex sensor configuration. The detection of a Proceedings of the Seventh Symposium, York, England, July 3-7, sensor failure is supported by the internal analytic plant redundancy 1985. Volume 1 . Oxford and New York, Pergamon Press, 1985, made available by deterministic observers. For the analysis of the p. 837-844. refs failure detection problem realistic constraints such as external plant Aerodynamic coefficients of a Schweizer 2-32 sailplane have disturbances and plant parameter variations are taken into account. been estimated from flight test data for angles of attack (alpha) The failure detection performance ultimately achievable by an up to 30 deg and sideslip angles (beta) to + or - 17 deg. The optimal observer is determined. The concept is applied to a flight nonlinear aerodynamic model has been identified by applying the control system of a transport aircraft. The operational feasibility is Estimation-Before-Modeling(EBM) technique to flight data derived demonstrated by flight test results. Author from fifteen maneuvers including seven stalls and 'post-stall gyrations'. An Extended Kalman-Bucy Filter and a Modified Bryson-Frazier smoother were used to estimate the time histories of the forces and moments from a fourteen-element discrete measurement vector. The optimal estimates and the measured A87-16196 control variables were sorted into 50 'subspaces', and the COMPARISON OF TWO TECHNIQUES OF I.F.D. BASED ON A aerodynamic modeling was performed using a multiple regression NON-LINEAR STOCHASTIC MODEL OF AN AIRCRAFT scheme in each subspace. Author R. J. PATTON and S. W. WILLCOX (York. University, England) IN: Identification and system parameter estimation 1985; A87-16209 Proceedings of the Seventh Symposium, York, England, July 3-7, STATE ESTIMATION OF FLYING VEHICLE 1985. Volume 1 . Oxford and New York. Pergamon Press, 1985, W.-C. WU. Y.-F. XIONG, and Z.-Y. LUO (Harbin Institute of p. 711-717. Research supported by the Ministry of Defence. Technology, People's Republic of China) IN: Identification and refs system parameter estimation 1985; Proceedings of the Seventh An analysis of two analytical redundancy methods for sensor Symposium, York. England, July 3-7, 1985. Volume 1 . Oxford fault diagnosis is given. Both methods use observers associated and New York, Pergamon Press, 1985, p. 1061-1065. refs with k measurements. The first employs k observers, each driven This paper discusses the effects of the random noises on the by a single measurement of the process, with failure signaling flight path of the flying vehicle and the application of the state developed from the state estimates of observers with dissimilar estimator to the vehicle control system. According to the given input measurements. This method is found to be sensitive to spectra density of the sea-wave colored noise, a lower order model process parameter variations, and hence unsuited to the general is chosen for approximating the sea-wave random process. Such application of fault analysis. An alternative approach, based on an approximation simplifies greatly the design of the state estimator. matching the estimation errors in the observation space on On the basis of the optimal filtering theory, two state estimators R-squared, is described. A number of two-input observers are are designed for the vehicle system in different noise conditions. designed forcing one mode of the estimation error system to be The simulation results show that the presence of the random unobservable. The design gives low sensitivity to plant parameter noises affects the normal operation of the vehicle and its control, variations and high sensitivity to instrument faults defined in an and the flight path of the vehicle can be maintained at lower appropriate frequency band, and does not require explicit use of altitude relative to the sea level by using the state estimator. the state-space. Author Author

114 08 AIRCRAFT STABILITY AND CONTROL

N87-11730'# Kentron International, Inc., Hampton, Va. expressed as a general class of structural synthesis problems is TRADEOFF METHODS IN MULTIOBJECTIVE INSENSITIVE given. Author DESIGN OF AIRPLANE CONTROL SYSTEMS A. A. SCHY and D. P. GIESY (Kentron International, Inc.. Hampton, N87-11774'# Florida Univ., Gainesville. Dept. of Engineering Va.) In NASA. Langley Research Center Recent Experiences in Sciences. Multidisciplinary Analysis and Optimization, Part 1 15 p 1984 COMMENTS ON GUST RESPONSE CONSTRAINED Avail: NTlS HC A22/MF A01 CSCL 01C OPTIMIZATION The latest results of an ongoing study of computer-aideddesign P. HAJELA ln NASA. Langley Research Center Recent of airplane control systems are given. Constrained minimization Experiences in Multidisciplinary Analysis and Optimization, Part 2 algorithms are used, with the design objectives in the constraint 14p 1984 vector. The concept of Pareto optimiality is briefly reviewed. It is Avail: NTlS HC A22/MF A01 CSCL 01C shown how an experienced designer can use it to find designs Recent research pertaining to optimum structural design with which are well-balanced in all objectives. Then the problem of probabilistic constraints is reviewed. The limitations and finding designs which are insensitive to uncertainty in system complexities introduced in the design as a result of the transition parameters are discussed, introducing a probabilistic vector from deterministic to probabilistic constraints are underscored. A definition of sensitivity which is consistent with the deterministic concise development of the theoretical aspects of optimum design Pareto optimal problem. Insensitivity is important in any practical of aircraft structures subjected to random wind loads is presented design, but it is particularly important in the design of feedback and suggestions for future research are offered. An emphasis is control systems, since it is considered to be the most important placed on the incorporation of recent developments in fracture distinctive property of feedback control. Methods of tradeoff mechanics in the design constraints. Author between deterministic and stochastic-insensitive (SI) design are described, and tradeoff design results are presented for the N87-11794 Stanford Univ., Calif. example of the a Shuttle lateral stability augmentation system. THEORETICAL AND EXPERIMENTAL INVESTIGATIONS OF This example is used because careful studies have been made of SENSOR LOCATION FOR OPTIMAL AEROELASTIC SYSTEM the uncertainty in Shuttle aerodynamics. Finally, since accurate STATE ESTIMATION Ph.D. Thesis statistics of uncertain parameters are usually not available, the G. LIU 1986 184 p effects of crude statistical models on SI designs are examined. Avail: Univ. Microfilms Order No. DA8608180 One of the major concerns in the design of an active control N87-11736*# National Aeronautics and Space Administration. system is obtaining the information needed for effective feedback. Langley Research Center, Hampton, Va. This involves the combination of sensing and estimation. A sensor APPLICATION OF OPTIMIZATION TECHNIQUES TO THE location index is defined as the weighted sum of the mean square DESIGN OF A FLUTTER SUPPRESSION CONTROL LAW FOR estimation error in which the sensor locations can be regarded as THE DAST ARW-2 estimator design parameters. The design goal is to choose these W. M. ADAMS, JR. and S. H. TIFFANY In its Recent Experiences locations to minimize the sensor location index. The gradient of in Multidisciplinary Analysis and Optimization, Part 1 17 p the sensor location index with respect to each individual sensor .nn A I YO4 !cca!icn is !ormv!i?ed and a program using this gradient for Avail: NTlS HC A22/MF A01 CSCL 01C systematic optimal sensor location search is developed. The choice The design of a candidate flutter suppression (FS) control law of the number of sensors is a tradeoff between the estimation for the symmetric degrees of freedom for the DAST ARW-2 aircraft quality based on the same performance index and the total costs is discussed. The results illustrate the application of several of installing and maintaining extra sensors. An experimental study currently employed control law design techniques. Subsequent for choosing the sensor location is conducted on an aeroelastic designs, obtained as the mathematical model of the ARW-2 is system. It is the physical realization of a two degree of freedom updated, are expected to employ similar methods and to provide typical section wing. It consists of a NACA 00t5 typical section a control law whose performance will be flight tested. This study wing with six accelerometers installed inside along the wing chord represents one of the steps necessary to provide an assessment as the estimator measuring instruments, an existing wind tunnel of the validity of applying current control law synthesis and analysis section, and some other accompanying experimental devices. The techniques in the design of actively controlled aircraft. Mathematical system modeling which includes the unsteady aerodynamics model models employed in the control law design and evaluation phases developed by Stephen Rock has been improved. The center of are described. The control problem is specified by presenting the percussion of the rigid two degree of freedom typical section wing flutter boundary predicted for the uncontrolled aircraft and by has been verified as a sensor location for which the system is defining objectives and constraints that the controller should satisfy. unobservable. Experimental results verify the trend of the A full-order controller is obtained by using Linear Quadratic theoretical predictions of the sensor location index for different Gaussian (LQG) techniques. The process of obtaining an sensor locations at various wind speeds. Dissert. Abstr. implementable reduced-order controller is described. One example is also shown in which constrained optimization techniques are N87-11795"# Northrop Corp., Hawthorne, Calif. utilized to explicitly include robustness criteria within the design VORTEX FLAP TECHNOLOGY A STABILITY AND CONTROL algorithm. ASSESSMENT Final Report K. M. CAREY and G. E. ERICKSON Nov. 1984 361 p N87-11752'# California Univ., Los Angeles. (Contract NAS1-17533) APPLICATION OF MODERN STRUCTURAL OPTIMIZATION TO (NASA-CR-172439; NAS 1.26:172439; NOR-84-158) Avail: NTlS VIBRATION REDUCTION IN ROTORCRAFT HC A16/MF A01 CSCL 01C P. P. FRIEDMANN ln NASA. Langley Research Center Recent A comprehensive low-speed wind tunnel investigation was Experiences in Multidisciplinary Analysis and Optimization, Part 2 performed of leading edge vortex flaps applied to representative 14p 1984 aircraft configurations. A determination was made of the effects (Contract NSG-1578; NAG2-226) of analytically- and empirically-designed vortex flaps on the static Avail: NTlS HC A22/MF A01 CSCL 01C longitudinal and lateral-directional aerodynamics, stability, and The helicopter rotor model consists of a four bladed hingeless control characteristics of fighter wings having leading-edge sweep rotor attached to a fuselage. The helicopter is assumed to be in angles of 45 to 76.5 degrees. The sensitivity to several configuration trimmed forward flight. Each blade is assumed to have flap, lag, modifications was assessed, which included the effects of flap and torsional degrees of freedom. The fuselage degrees of freedom planform, leading- and trailing-edge flap deflection angles, wing are not included in the analysis. Thus the aeroelastic stability and location on the fuselage, forebody strakes, canards, and centerline response analysis upon which this study is based is an isolated and outboard vertical tails. Six-component forces and moments, blade analysis. The helicopter rotor vibration reduction problem wing surface static pressure distributions, and surface flow patterns

115 08 AIRCRAFT STABILITY AND CONTROL were obtained using the Northrop 21- by 30-inch low-speed wind parameter C (sub m (sub sigma e squared)). However, the scatter tunnel. Author about the preflight prediction of C (sub m (sub sigma e squared)) was large. Other investigators have suggested that adding nonlinear N87-11796'# National Aeronautics and Space Administration. terms to the mathematical model used to identify C (sub m (sub Ames Research Center, Moffett Field, Calif. sigma e)) could reduce the scatter. The results of this investigation AIRCRAFT AUTOMATIC-FLIGHT-CONTROL SYSTEM WITH show that C (sub m (sub sigma e squared)) is the only identifiable INVERSION OF THE MODEL IN THE FEED-FORWARD PATH nonlinear parameter applicable and that the changes in C (sub m USING A NEWTON-RAPHSON TECHNIQUE FOR THE (sub sigma e)) values when C (sub m (sub sigma e squared)) is INVERSION included are in the order of ten percent for the data estimated. G. A. SMITH, G. MEYER, and M. NORDSTROM (Sterling Software, Author Palo Alto, Calif.) Jul. 1986 96 p (NASA-TM-88209; A-2-86092; NAS 1.1588209) Avail: NTlS HC A05/MF A01 CSCL 01C A new automatic flight control system concept suitable for N87-12568# Princeton Univ., N. J. Dept. of Mechanical and aircraft with highly nonlinear aerodynamic and propulsion Aerospace Engineering. characteristics and which must operate over a wide flight envelope A PROTOTYPE MAINTENANCE EXPERT SYSTEM FOR THE was investigated. This exact model follower inverts a complete CH-47 FLIGHT CONTROL HYDRAULIC SYSTEM nonlinear model of the aircraft as part of the feed-forward path. C. J. LOH 28 Apr. 1986 182 p The inversion is accomplished by a Newton-Raphson trim of the (Contract DAAG29-84-K-0048) model at each digital computer cycle time of 0.05 seconds. The (AD-A169019; MAE-1751; ARO-20155.8-MA) Avail: NTlS HC combination of the inverse model and the actual aircraft in the AO9/MF A01 CSCL 148 feed-forward path alloys the translational and rotational regulators An investigation of the hydraulic flight control system of a Boeing in the feedback path to be easily designed by linear methods. An CH-47 Chinook helicopter using artificial intelligence techniques explanation of the model inversion procedure is presented. An will be undertaken. Specifically, a knowledge based expert system extensive set of simulation data for essentially the full flight will employ situation-action rules (production rules) to diagnose a envelope for a vertical attitude takeoff and landing aircraft (VATOL) failure and subsequently identify specific device@) which caused is presented. These data demonstrate the successful, smooth, that failure. Moreover, because the behavior of the system is directly and precise control that can be achieved with this concept. The responsive to the goals the system is directly attempting to achieve, trajectory includes conventional flight from 200 to 900 ft/sec with the expert system's inference engine performs a backward-chaining path accelerations and decelerations, altitude changes of over process via a goal-driven control strategy. This strategy involves 6000 ft and 29 and 39 turns. Vertical attitude maneuvering as a finding rules that demonstrate the hypothesis and then verifying tail sitter along all axes is demonstrated. A transition trajectory the facts that enable the rule to work. The List Processing Language from 200 ft/sec in conventional flight to stationary hover in the (LIPS) is used to facilitate data processing and symbolic logic vertical attitude includes satisfactory operation through lift-cure expression manipulation. GRA slope reversal as attitude goes from horizontal to vertical at constant altitude. A vertical attitude takeoff from stationary hover to conventional flight is also demonstrated. Author

N87-11797'# Kohlrnan Systems Research, Inc., Lawrence, N87-12569# New Mexico Univ., Albuquerque. Kans. APPLICATION OF THE AlPA (APPROXIMATE ITERATIVE FLIGHT TEST REPORT OF THE NASA ICING RESEARCH PREPROCESSING ALGORITHM) TO F-106 DATA Flnal Report, AIRPLANE: PERFORMANCE, STABILITY, AND CONTROL Jul. 1984 - Jul. 1985 AFTER FLIGHT THROUGH NATURAL ICING CONDITIONS Final S. W. PARK and J. T. CORDARO Jun. 1986 12 p Report (Contract F29601-84-K-0045) J. L. JORDAN, S. J. PLATZ, and W. C. SCHINSTOCK Oct. (AD-A169084; AFWL-TN-85-52) Avail: NTlS HC A02/MF A01 1986 159p CSCL 20N (Contract NAS3-24547) This report covers the application of the AlPA numerical (NASA-CR-179515; NAS 1.26:179515; KSR-86-01) Avail: NTlS algorithm to measured data from the F-106 fly-by electromagnetic HC AOWMF A01 CSCL 01C pulse test conducted at the AFWL in 1984. The algorithm was Flight test results are presented documenting the effect of partially successful at reducing the data. The amplitudes of the airframe icing on performance and stability and control of a NASA normalized coupling coefficients for the first three poles were DHCB icing research aircraft. Kohlman System Research, Inc., determined. GRA provided the data acquisition system and data analysis under contract to NASA. Performance modeling methods and MMLE techniques were used to determine the effects of natural ice on the aircraft. Results showed that ice had a significant effect on N87-12570# Ballistic Research Labs., Aberdeen Proving Ground, the drag coefficient of the aircraft and a modest effect on the Md. MMLE derived longitudinal stability coefficients (code version BLAST GUST LOADING ON A 35 DEGREE SWEPT-BACK WING MMLE). Data is also presented on asymmetric power sign slip Flnal Report maneuvers showing rudder floating characteristics with and without C. L. FISHER May 1986 141 p ice on the vertical stabilizer. Author (AD-A169415; BRL-MR-3519) Avail: NTlS HC A07/MF A01 CSCL 01c N87-12566'# National Aeronautics and Space Administration. The Ballistic Research Lab (BRL) performed shock loading tests Langley Research Center, Hampton, Va. on a generic wing in the 2.44 meter shock tube. This model was EVALUATION OF A NONLINEAR PARAMETER EXTRACTION previously tested on the rocked sled facility at Holloman AFB, MATHEMATICAL MODEL INCLUDING THE TERM C(SUBM(SUB New Mexico, and is documented in report number DNA 5211F. DELTA E SQUARED)) The purpose of the BRL test was to determine if the data gathered W. T. SUIT Oct. 1986 18 p at Holloman AFB on gust loading of the wing could be duplicated (NASA-TM-87731; NAS 1.15:87731) Avail: NTlS HC AO2/MF in the shock tube. On Feb 20 and 25, 1985, tests were conducted A01 CSCLOlC in the BRL shock tube to obtain pressure data on a 35 degree Shuttle flight test data were used to determine values for the sweptback generic wing model. These data are subsequently short-period wameters. The best identified, as judged by its compared with equivalent data taken on the same model at the estimated standard deviation. was the elevon effectiveness Holloman sled track. GRA

116 09 RESEARCH AND SUPPORT FACILITIES (AIR)

N87-12571# Hughes Research Labs., Malibu, Calif. A87-14007# FLIGHT MODEL DISCHARGE SYSTEM Report, Nov. 1984 - Dec. THE DEVELOPMENT OF DMS-SCALES FOR CRYOGENIC WIND 1985 TUNNELS [UEBER DIE ENTWICKLUNG VON DMSWAAGEN R. R. ROBSON, W. S. WILLIAMSON, and J. SANTORU Feb. FUER KRYO-WINDKANAELE] 1986 170p B. EWALD (Darmstadt, Technische Hochschule, West Germany) (Contract F19628-83-C-0143) and E. GRAEWE (Messerschmitt-Boelkow-BlohmGmbH, Bremen, (AD-A169423; AFGL-TR-86-0036; SR-2) Avail: NTlS HC West Germany) BMFT, Statusseminar ueber Luftfahrtforschung AO8/MF A01 CSCL 22A und Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, The viability of the Flight Model Discharge System (FMDS) Paper. 18 p. In German. refs concept has been demonstrated by the successful fabrication and The development of a DMS scale for use in a cryogenic wind testing of a breadboard system. The FMDS is a spacecraft tunnel is discussed. The accuracy of power measurements in wind charge-control system designed to overcome the problem of charge tunnels is reviewed, and attainable accuracies for DMS scales buildup on a space vehicle which occurs during periods of adverse are compared with those required for cryogenic wind tunnels. The space-environmental conditions. Operational characteristics of the main sources of inaccuracy in DMS scales are described, and entire system are presented, including the electrostatic analyzers, methods to overcome them are indicated. C.D. surface potential monitors, transient pulse monitor, plasma source, and microprocessor-based controller, including its software. Results of the breadbhoard demonstration testing and the preliminary flight A87-14009# hardware design are also included. Author (GRA) MEASUREMENTS IN THE HIGH SUBSONIC REGION IN THE TU-BERLIN WIND TUNNEL WITH ADAPTIVE WALLS [UEBER MESSUNGEN IM HOHEN UNTERSCHALL IN DEM WINDKANAL DER TU-BERLIN MIT ADAPTIVEN WAENDEN] U. GANZER (Berlin, Technische Universitaet, West Germany) BMFT, Statusseminar ueber Luftfahrtforschung und Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, Paper. 20 p. In German. 09 The construction and electronic wall regulation, as well as the measurement procedures for wall adaptation, in the flexible-wall RESEARCH AND SUPPORT FACILITIES (AIR) 'Octagon' section of the wind tunnel at the University of Berlin are discussed. Numerical procedures for three-dimensional wall adaptation are addressed along with test results from the Octagon Includes airports, hangars and runways; aircraft repair and overhaul section. Wind tunnels with flexible walls for supersonic flows are facilities; wind tunnels; shock tubes; and aircraft engine test briefly discussed. C.D. stands.

A87-14023# A87-13122 STATUS REPORT ON THE EUROPEAN TRANSONiC WiND REPAIR OF COMPOSITE COMPONENTS - A NAVY TUNNEL (ETW) [STATUSBERICHT ZUM EUROPAEISCHEN APPROACH TRANSSCHALL-WINDKANAL /ETW/] R. E. CARSON (US. Navy, Naval Air Rework Facility, San Diego, F. MAURER (European Transonic Wind Tunnel, Cologne, West CA) IN: International SAMPE Symposium and Exhibition, 31st, Germany) BMFT, Statusseminar ueber Luftfahrtforschung und Los Angeles, CA, April 7-10, 1986, Proceedings . Covina, CA, Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, Society for the Advancement of Material and Process Engineering, Paper. 42 p. In German. refs 1986, p. 1012-1016. The development of ETW during phases 2.2 (the The Naval Air Rework Facility at North Island Naval Air Station functional-design phase begun in Fall 1985) and 3 (the construction in San Diego, CA has recently opened a new facility for the repair phase, still dependent on approval by the participating and overhaul of composite and honeycomb/metal bonded aircraft governments) is discussed in a status report. The emphasis are components. The facility, its equipment and its uses will be on the new ETW organizational structure and on changes adopted discussed. The development of training programs for Depot level in the ETW specifications. Topics examined include the duties of and intermediate/organizational level repairs will be discussed. the industry architect in phases 2.2 and 3, the overall advantages Topics will include X-ray, 'C' scan, honeycomb core carvers, and disadvantages of external insulation (El) and internal insulation automated storage and retreival systems (ASRS), Gerber knife, (II), two proposed II systems, EI/II cost comparisons, breathable autoclaves, heat blank bonding and a vertical process center. atmospheres and breathing devices, the adjustable diffuser, and Author the temperature conditioning of models. T.K.

A87-14024# A87-13988# DFVLR CRYOGENIC-WIND-TUNNEL AND MODEL TECHNOL- DESIGN AND CONSTRUCTION OF A CRYOGENIC-WIND- OGY [KRYO-WINDKANAL- UND MODELLTECHNIK IN DER TUNNEL MODEL [KONSTRUKTION UND BAU EINES KRYO- DFVLR] WINDKANALMODELLS] 0. LAWACZECK BMFT, Statusseminar ueber Luftfahrtfarschung P. ESCH (Dornier GmbH, Friedrichshafen, West Germany) and U. und Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, GROSS (Messerschmitt-Boelkow-Blohm GmbH, Ottobrunn, West Paper. 49 p. In German. refs Germany) BMFT, Statusseminar ueber Luftfahrtforschung und Projects underway in the framework of DNLR programs on Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, cryogenic-wind-tunnel technology, new methods in applied fluid Paper. 19 p. In German. refs mechanics, and separated flows are surveyed, with a focus on The status of efforts to design and fabricate a 1:lO-scale model the status of facilities and results applicable to the planned of the TST, an experimental Alpha-Jet aircraft with a transonic European Transonic Wind Tunnel (ETW). Topics examined include wing, for use in both conventional and cryogenic wind tunnels is high-Reynolds-number profile measurements at ambient and reviewed. Consideration is given to the choice of scale, the cryogenic temperatures, the DNLR cryogenic facilities at simulation of the TST flight envelope, the model load and its Goettingen and Cologne, measurements on the ETW test rig, and implications for the balance measurement range, the strength experiments on droplet evaporation and condensation. properties of the martensitically hardenable 18 Ni 1700 steel Photographs, graphs, diagrams, drawings, and tables are selected for the model, and the model instrumentation. T.K. provided. T.K.

117 09 RESEARCH AND SUPPORT FACILITIES (AIR)

A87-15463 N87-11799# Army Engineer Waterways Experiment Station, A WIND-TUNNEL METHOD FOR V/STOL TESTING Vicksburg, Miss. Geotechnical Lab. W. R. SEARS (Arizona, University, Tucson) IN: Recent advances ADVANCED CONSTRUCTION PROCEDURES CONFINED in aerodynamics . New York, Springer-Verlag, 1986, p. 525-545. BASES FOR AIRPORT PAVEMENTS Final Report, Sep. 1983 - refs Mar. 1986 (Contract NO0014-79-C-0010; AF-AFOSR-82-0185) J. C. POlTER and P. C. LAMBE Sep. 1986 96 p Attention is given to the results of a numerical study in which (Contract DTFAOl -83-Y-30606) the adaptive wall wind tunnel concept was modeled with a powered (FAA/PM-86/9) Avail: NTlS HC A05/MF A01 lift aircraft installed in the tunnel test section, and in which the Airports for light aircraft must often be built in areas where process of iterative tunnel modification was simulated in detail. base course material is inadequate or economically unavailable. Since the adaptive wall scheme allows the operator to choose Sand grids may provide an economical solution in these cases. the simulated undisturbed stream vector in a wind tunnel, it Previous work with sand grids has identified optimum grid-cell becomes possible to eliminate the problem of the wake in high geometry based on ultimate bearing capacity. Past observations lift testing. The numerical simulations presently conducted for the also suggest the nature of sand-grid behavior for small stresses case of tests of a jet-flap wing aircraft appear to confirm this and strains. From these a model was formulated for analyzing the claim. A panel method for jet-flap wing and wake modeling are performance of sand grids in pavement systems and spot-checked developed, and convergence and iteration method details are using field data from a full-scale, accelerated-traffic sand-grid test explored. O.C. section. Author

N87-11800'# National Aeronautics and Space Administration. A87-15464' National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. Ames Research Center, Moffett Field, Calif. METHODS FOR ASSESSING WALL INTERFERENCE IN THE 2- THE EVOLUTION OF ADAPTIVE-WALL WIND TUNNELS BY 2-FOOT ADAPTIVE-WALL WIND TUNNEL S. S. DAVIS (NASA, Arnes Research Center, Moffett Field, CA) E. T. SHAIRER Jun. 1986 61 p IN: Recent advances in aerodynamics . New York, Springer-Verlag, (NASA-TM-88252; A-86249; NAS 1.15:88252) Avail: NTlS HC 1986, p. 547-566. refs A04/MF A01 CSCL 148 Since its inception, adaptive wall wind tunnel design has Discussed are two methods for assessing two-dimensional wall developed three major configurational possibilities: streamlined interference in the adaptive-wall test section of the NASA Ames walls, variable porosity walls, and segmented plenum arrangements. 2 x 2-Foot Transonic Wind Tunnel: (1) a method for predicting All of these methods have demonstrated their feasibility for free-air conditions near the walls of the test section (adaptive-wall transonic flow research; development programs are noted to be methods); and (2) a method for estimating wall-induced velocities underway for three-dimensional adaptive wall tunnels. With the near the model (correction methods), both of which methods are availability of advanced computational procedures, routine based on measurements of either one or two components of flow angle-of-incidence or Mach sweeps may be treated numerically, velocity near the walls of the test section. Each method is while adaptive wall wind tunnels are employed for complementary demonstrated using simulated wind tunnel data and is compared point-design and for testing at flow conditions that are beyond with other methods of the same type. The two-component the capabilities of current numerical modeling. O.C. adaptive-wall and correction methods were found to be preferable to the corresponding one-component methods because: (1) they are more sensitive to, and give a more complete description of, wall interference; (2) they require measurements at fewer locations; A87-15465 (3) they can be used to establish free-stream conditions; and (4) ADVANCES IN ADAPTIVE WALL WIND TUNNEL TECHNIQUE they are independent of a description of the model and constants U. GANZER (Berlin, Technische Universitaet, West Germany) IN: of integration. Author Recent advances in aerodynamics . New York, Springer-Verlag, 1986, p. 567-601. BMFT-DFG-supported research. refs The adaptive wind tunnel wall technique requires: (1) a device N87-11801'# National Aeronautics and Space Administration. that locally adjusts the flow condition near the test section wall; Langley Research Center, Hampton, Va. (2) the means with which to check how far the wall is free of A DESCRIPTION OF THE ACTIVE AND PASSIVE interference; and (3) a strategy by means of which to arrive at SIDEWALL-BOUNDARY-LAYER REMOVAL SYSTEMS OF THE wall interference-free flow conditions. Various adaptive wall wind 0.3-METER TRANSONIC CRYOGENIC TUNNEL tunnel projects are presently discussed. Attention is given to two C. B. JOHNSON, A. V. MURTHY. and E. J. RAY Nov. 1986 different kinds of adaptive wall test section: the type employing 21 P perforated or slotted walls with local control of flow through the (NASA-TM-87764;L-16178; NAS 1.1 587764) Avail: NTlS HC wall, and that using flexible irnprermeable walls with the shape AO2IMF A01 CSCL 148 adjusted to the individual flow condition. Design features are Results are presented for an operational checkout and explored for the NASA Ames, University of Southampton. AEDC, shakedown of the active sidewall-boundary-layer removal system DFVLR, and Technical University of Berlin three-dimensional newly installed in the Langley 0.3-meter Transonic Cryogenic adaptive wall wind tunnel projects. O.C. Tunnel (0.3-m TCT). Prior to the installation of this active removal system, the sidewall-boundary layer was removed passively by exhausting directly to the atmosphere @e., no reinjection). With the active removal system using the reinjection compressor, the N87-11798# Federal Aviation Administration, Washington. D.C. removal capability is greatly expanded to cover the entire operating Program Engineering and Maintenance Service. envelope of the 0.3-m TCT. Details of the active removal system FAA HELICOPTER/HELIPORT RESEARCH, ENGINEERING, are presented including the compressor reinjection circuit, the AND DEVELOPMENT BIBLIOGRAPHY, 1964-1986 compressor pressure ratidsurge control, and the compressor R. D. SMITH Nov. 1986 170 p recirculation loop. The control logic and features of the compressor (FAA/PM-86/47) Avail: NTlS HC AOWMF A01 surge control are explained. Initial tests covering critical operating This report is a bibliography of FAA heliport related documents conditions show mass flow removal rates of about 5 percent at published in the 1964 to 1986 time period. The list is limited to lower Mach numbers can be obtained with the active system. documents in which the research, engineering, and development Measured performance characteristics of the compressor are elements of the FAA were involved as sponsors, participants, or presented. As part of the validation of the active system, limited authors. Author airfoil tests were made using the new system. Author

118 09 RESEARCH AND SUPPORT FACILITIES (AIR)

N87-11802# Toronto Univ. (Ontario). Inst. for Aerospace An expression for the probability distribution of the duration that Studies. dense fog may persist was derived. ESA MOTION CHARACTERISTICS OF THE UTIAS FLIGHT RESEARCH SIMULATOR MOTION-BASE P. R. GRANT Jul. 1986 144 p Sponsored in part by Natural Sciences and Engineering Research Council, and by University of Toronto (UTIAS-TN-261; ISSN-0082-5263) Avail: NTlS HC A07/MF A01 N87-12572# Essex Corp., Orlando, Fla. The motion characteristics of the UTlAS Flight Research SIMULATOR DESIGN FEATURES FOR HELICOPTER LANDING Simulator Motion-Base were experimentally determined. More ON SMALL SHIPS. 1: A PERFORMANCE STUDY Final Report, specifically describing function tests (under various operating 1 Sep. 1981 - 26 Apr. 1985 conditions), 112 Hz noise level tests, signal-to-noise tests, and D. P. WESTRA and G. LINTERN 27 Sep. 1985 63 p hysteresis tests were performed for all six degrees-of-freedom. (Contract N61339-81-C-0105) Dynamic threshold tests were performed for the heave (AD-A16951 4; NAVTRASYSCEN-81-C-01 05-1 3) Avail: NTlS HC degree-of-freedom. The motion-base was found to have a A04/MF A01 CSCL 051 reasonably flat amplitude response up to 10 Hz in all The Visual Technology Research Simulator (VTRS) at the Naval degrees-of-freedom. Motion in the non-dirven degrees-of-freedom Training Systems Center was used to study the effects of six was small compared to the driven channel. The noise of the simulator features on performance for helicopter landings on small motion-base was found to be the sum of braodband background ships. The purpose of the experiment was to obtain information noise and harmonics of the driven frequency, with the amplitude relevant to the design of simulators for skill maintenance and of the noise varying with both the amplitude and frequency of the transition training, and to obtain information for decisions about driving signal. Hysteresis was determined to be neglible. The future transfer-of-training studies. The six simulator factors were dynamic threshold was found to be small and quite acceptable scene detail (high detail ship deck and hangar markings versus for most projected applications involving the motion-base. no deck and hangar markings), field of view (VTRS-wide versus Author reduced SH-GOB operational flight trainer field of view), system visual lab (217 msec versus 117 msec), g-seat acceleration cuing (off versus on), and collective sound cuing (off versus on). These N87-11803# Air Force Systems Command, Wright-Patterson AFB, factors were tested across two levels of seastate and pilot Ohio. Foreign Technology Div. experience. Pilots who participated in the experiment were THE 8 M X 6 M LOW SPEED WIND TUNNEL AT THE CHINESE experienced Navy H-3 rotary wing pilots. Results indicated large AERODYNAMIC RESEARCH AND DEVELOPMENT CENTER effects of scene detail, small to moderate effects for visual lag, M. WANG and R. PAN 30 May 1986 14 p Transl. into small effects for field of view, and no meaningful effects for the ENGLISH from Guoji Hangkong (China), no. 10(260), Oct. 1984 p g-seat factors and collective sound. Performance was better with 2-4 the high-detail ship, the shorter visual lag, and the VTRS-wide (AD-A168448; FTD-ID(RS)T-0257-86) Avail: NTlS HC A02/MF field of view. Transfer-of-training research is recommended as the A01 CSCL 148 next step to further explore these findings and to obtain information The low speed wind tunnel at CARDC is a large scale, double directly relevant to the design of simulators for use by student experimentai section wind iunnei soieiy designed ana buiii in China. pilots. GRA It is primarily used for experiments in the aerodynamic characteristics of aerospace vehicles, Le., ground wind load of guided missiles and space vehicles; large attack angle of airplanes and guided missiles; large prototypes; aerodynamics of helicopters and vertical short takeoff aircraft; and industrial aerodynamics (e.g., architecture, bridges, fans and automobiles). It passed national certification at the end of 1983 and was officially released for N87-12573# Essex Corp., Orlando, Fla. use. This wind tunnel is an open-circuit, closed double experimental SIMULATOR DESIGN AND INSTRUCTIONAL FEATURES FOR section in series, large scale low speed wind tunnel. Its length is CARRIER LANDING: A FIELD TRANSFER STUDY Final Report 237 m with a maximum width of 40 m and a maximum height of D. P. WESTRA, G. LINTERN, D. J. SHEPPARD, K. E. THOMLEY, 20.5 m. It consists of air intake assembly, stabilization section, and R. MAUK 18 Jun. 1986 91 p first convergence section, first experimental section, second (Contract N61339-85-C-0044) experimental section, fan section, second divergence section, and (AD-A169962; NAVTRASYSCEN-85-C-0044-2) Avail: NTlS HC air exhaust assembly. GRA A05/MF A01 CSCL 01B A transfer-of-training experiment was conducted as part of the carrier landing behavioral research program at the Visual N87-11805# Royal Netherlands Meteorological Inst., De Bilt. Technology Research Simulator (VTRS). Experimental results Afdeling Fysische Meteorologie. provide information on the design and use of simulators for training NUMBER AND DURATION OF RUNWAY VISUAL RANGE (RVR) the aircraft carrier landing task and also provide input on design RUNS FOR RVR-VALUES LOWER THAN 225 M issues for the Navy’s new T-45 training system. Two visual display A. H. C. STALENHOEF 1986 25 p In DUTCH; ENGLISH variables and two simulator training variables were selected for summarv- -...... -. inclusion in this experiment: scene detail (day contrasted with night); (KNMI-fR-85(FM); ISSN-0169-1708; ETN-86-98500) Avail: NTlS field of view (wide versus narrow); approach type (circling, modified HC A02/MF A01 straight-in or segmented); and number of simulator trials (20, 40, The number and length of runway visual range (RVR) runs for or 60). 72 student pilots were trained on the VTRS prior to going values of the RVR leass than 225 m were studied in order to through the Field Carrier Landing Practice (FCLP) phase of their obtain a better insight into the appearance of dense fog at pilot training program. Performance of these students at FCLP Amsterdam airport Schiphol. The study was based on 1 m data was contrasted with that of a group of 54 students who did not of transmissometers and matching background luminance meters receive simulator training. Results show that students trained in at several locations in the airport for the period June 1979 till the simulator performed better at FCLP than the control students. May 1985. The percentage of time during each month that the There was no transfer advantage for those trained with a daytime transmissometer data were not available on magnetic tape, the high-detail scene compared to those trained with a lower cost number of runs of specified lengths for each location, the local nighttime low-detail scene. There was also no transfer advantage number of runs in the period, the relative frequencies of runs with for those trained with a wide FOV compared to those trained with several lengths for each location, and information about the total the wide field of view compared to those trained with the lower duration that the RVR does not exceed a certain level are tabulated. cost narrow FOV scene. GRA

119 10 ASTRONAUTICS

10 11 ASTRONAUTICS CHEMISTRY AND MATERIALS

Includes astronautics (general); astrodynamics; ground support Includes chemistry and materials (general); composite materials; systems and facilities (space); launch vehicles and space vehicles; inorganic and physical chemistry; metallic materials; nonmetallic space transportation; space communications; spacecraft materials; propellants and fuels; and materials processing. communications; command and tracking; spacecraftdesign; testing and performance; spacecraft instrumentation: and spacecraft propulsion and power. A87-13092 DEVELOPMENT OF HIGH-ALUMINA CERAMIC MATERIALS SUITABLE FOR MAKING JET ENGINE FIXTURES M. WOOD and S. C. KUO (CEMCOM Corp., Lanham, MD) IN: International SAMPE Symposium and Exhibition, 31 st, Los Angeles, CA, April 7-10. 1986, Proceedings . Covina, CA, Society for the Advancement of Material and Process Engineering, 1986, p. 600-608. refs A calcium-aluminate bonded ceramic material was developed for fabricating low cost vacuum furnace fixtures suitable for the high temperature repair of jet engine components. The material was formulated based on results obtained from a series of statistically designed experiments. The material was refined and the prototype was scaled up to practical sizes. The materials’s A87-15920# thermophysical properties and mechanical strength characteristics RAMJET APPLICATION IN ATMOSPHERES OF DIFFERENT were determined. Preliminary results demonstrate that the furnace CELESTIAL BODIES time necessary for heat treating jet engine components can be D. M. WOLF (DFVLR, lnstitut fuer Chemische Antriebe und reduced from the 13 hours required by graphite fixturing (due to Verfahrenstechnik, Hardthausen am Kocher, West Germany) IAF, outgassing) to six hours of less for ceramic fixtures. Author International Astronautical Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. 8 p. refs (IAF PAPER 86-181) Primarily, this study shall answer the question of ramjet A87-13093 application in the atmospheres of Venus, Mars, Jupiter, Saturn, RESIN-HARDENER SYSTEMS FOR RESIN TRANSFER and Titan. Atmospheric models of the specified celestial bodies MOLDING are presented, describing the chemical composition as well as W. D. WHITE (Dow Chemical Co., Coatings and Resins Technical the temperature and pressure distribution. After selecting suitable Service and Development Dept., Freeport. TX) IN: International propellants and committing to an engine configuration, the load SAMPE Symposium and Exhibition, 31st, Los Angeles, CA, April limits of the engine model are fixed. The engine calculations are 7-10, 1986. Proceedings . Covina, CA, Society for the Advancement pointing out the impact of a few parameters, e.g., Mach number of Material and Process Engineering, 1986, p. 622-634. or mixture ratio, on the specific impulse and the thrust density. Three resin-hardener systems developed for resin transfer The results of the study are showing the ramjet application in all molding, braiding, and filament winding are evaluated as matrix atmospheres mentioned above as being theoretically possible. resins for glass, Kevlar, and graphite fiber reinforcements. It is Author shown that the three systems are suitable for fabricating composite panels with mechanical properties comparable with those of panels made of state-of-the-art 350 F dry/250 F wet epoxy systems. V.L.

A87-13121 COMPOSITE CURING WITH SEMI-PERMEABLE MEMBRANES R. S. KIWAK and J. L. TOUCHETTE (Martin Marietta Corp., Baltimore Aerospace Div., MD) IN: International SAMPE Symposium and Exhibition, 31st. Los Angeles, CA, April 7-10, 1986, Proceedings . Covina, CA, Society for the Advancement of Material and Process Engineering, 1986, p. 999-101 1. refs N87-12577# Texas Univ., Austin. Absorbed moisture has been identified as the major cause of OPTIMAL DESCENDING, HYPERSONIC TURN TO HEADING internal porosity during high temperature, low pressure curing of G. R. EISLER and D. G. HULL 1986 15 p Presented at the epoxy matrix composites needed for composite aircraft repair. Atmospheric Flight Mechanics Conference, Williamsburg, Va., 18 Semi-permeable membranes, thin sheets of polymer that allow Aug. 1986 gases including water vapor to pass through unimpeded while (Contract DE-AC04-76DP-00789) stopping resin, offer a higher level of gas management processing (DE86-010989; SAND-86-2061C; CONF-860882-2) Avail: NTlS than conventional methods. This has allowed the development of HC AO2/MF A01 a simple concept for an improved nonautoclave cure process. Approximations are made to the point-mass equations of motion The composite layup, including a predetermined amount of bleeder for flight within the atmosphere. Optimal controls are formulated ply, is completely surrounded with the gas permeable membrane for a reentry vehicle to execute a maximum-terminal-velocityturn and hydrostatically sealed to contain the liquid resin. The layup is to a specified heading while executing steep, descent trajectories. pressurized through the membrane, while the surrounding effluent A Newton scheme is used repetitively to solve a nonlinear algebraic cavity is under vacuum. Having the liquid phase under pressure system for two parameters in the control equations to provide the at all times increases gas solubility and prevents bubble formation, on-line guidance. Trajectory comparisons from the repetitive thereby allowing volatiles to diffuse to the membrane interface solution of the optimal control problem, pure numerical optimization, and dissipate. Results of experiments conducted on various and simulation of sample-data guidance show good agreement, if membranes and resulting void fraction gradients through the the atmospheric model is accurate. DOE laminates are discussed. Author

120 11 CHEMISTRY AND MATERIALS

A87-1317 1 A87-13985# DIFFUSION BONDING OF CERTAIN REFRACTORY METALS CLARIFICATION OF ADHESIVE BINDING MECHANISMS OF T. G. NlEH (Lockheed Metallurgy Laboratory, Palo Alto, CA) IN: ALUMINUM STRUCTURAL BONDS IN AIRCRAFT FABRICATION International SAMPE Symposium and Exhibition, 31 st, Los Angeles, [ KLAERUNG DER ADHAESIVEN BINDUNGSMECHANISMEN CA, April 7-10, 1986, Proceedings . Covina, CA, Society for the VON STRUKTURELLEN ALUMINIUMKLEBUNGEN IM Advancement of Material and Process Engineering, 1986, p. FLUGZEUGBAU] 1595-1603. Research supported by the Lockheed Independent C. MAT2 (Messerschmitt-Boelkow-Blohm GmbH, Bremen, West Research and Development Program. refs Germany) BMFT, Statusseminar ueber Luftfahrtforschung und Fusion welding or brazing of refractory metals is, in general, Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, not desirable due to the recrystallized, brittle microstructure Paper. 22 p. In German. refs produced in the joint. In view of this, it is preferable to reduce the (Contract BMFT-LFF-8350) bonding temperature by conducting solid-state diffusion bonding (MBB-UT-226-86) at a low temperature to prevent recrystallization. It will be The material characteristics and processing parameters which demonstrated that a number of refractory metals systems, e.g., determine the service life of bonded AI aircraft structures are TZM-Mo (Mo- Ti-Zr) to TZM-Mo, TZM-Mo to C103 (89Nb-10Hf-1Ti) investigated experimentally. Three primary damage mechanisms and W-25Re to W-25Re, can be jointed together by solid-state are identified: the growth of weak zones near boundary layers, diffusion bonding solid-state diffusion bonding at temperatures the alkaline destruction of the oxide layer, and joint corrosion. For below that for the recrystallization of the parent metals by using optimum bonding, it is recommended that the substrate surface either Nb, Ta, Ti, or Ni as interleaf materials. In addition, it will be physicochemically active vis a vis the adhesive, that the also be demonstrated that W-25Re can be self diffusion bonded adhesive-substrate interaction be resistant to hydrolysis, and that without causing a brittle joint. Parameters affecting the quality of the adhesive be designed to keep the chemical environment in the joint, particularly the surface preparation prior to bonding, will the joint within the stability limits of the substrate surface. T.K. be discussed. This particular type of joint has immediate applications in many aerospace structures. Author A87-14001# STRUCTURE-COMPONENT TESTS FOR A CFK FUSELAGE [STRUKTUR-KOMPONENTENVERSUCHE FUER EINEN CFK-RUMPF] M. KOLAX (Messerschmitt-Boelkow-Blohm GmbH, Bremen, West A8743613 Germany) BMFT, Statusseminar ueber Luftfahrtforschung und FIBRE REINFORCED COMPOSITES 1986; PROCEEDINGS OF Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, THE SECOND INTERNATIONAL CONFERENCE, UNIVERSITY Paper. 19 p. In German. OF LIVERPOOL, ENGLAND, APRIL 8-10, 1986 (Contract BMFT-LFK-8350) Conference sponsored by the Institution of Mechanical Engineers, (MBB-UT-223-86) Plastics and Rubber Institute, Institution of Production Engineers, Critical structural components for a future CFK fuselage of a and Royal Aeronautical Society. London, Mechanical Engineering large-capacity aircraft have been studied, and the results are Publications, Ltd., 1986, 269 p. For individual items see A87-13614 discussed. Methods of building such a composite fuselage are to A87-13634. addressed along with the characteristics of individual components. The papers presented include thermoplastic composites in The development and testing of the first critical structural woven fabric form, the preparation of ultrahigh modulus components are reviewed, and the selection of materials and the polyethylene composites, compact disk fracture mechanics testing techniques utilized are described. C.D. of injection-molded short-fiber-reinforced thermoplastics, and injection molding of thick-section-fiber-reinforced thermoplastics. A87-14982# Consideration is given to the flexible manufacturing of composite COMBUSTION STUDIES OF METALLIZED FUELS FOR aerospace structures, the mechanized manufacture of composite SOLID-FUEL RAMJETS rotor-blade spars, and AV-8B/GR Mk 5 airframe composite A. GANY (Technion - Israel Institute of Technology, Haifa) and D. applications. Additional papers include the prediction of the energy W. NETZER (U.S. Naval Postgraduate School, Monterey, CA) absorption of composite structural materials, hovercraft skirt design Journal of Propulsion and Power (ISSN 0748-4658), vol. 2, and manufacture, and low-cost carbon fibers for high-performance Sept.-Oct. 1986, p. 423-427. Research supported by the U.S. applications. IS. National Research Council. Previously cited in issue 18, p. 2653, Accession no. A85-39640. refs (Contract N60530-85-WR-30011)

A87-13659# A87-14986'# United Technologies Research Center, East THERMOCHEMICAL EVALUATION OF FUEL CANDIDATES FOR Hartford, Conn. I RAMJET PROPULSION LONG-TERM DEPOSIT FORMATION IN AVIATION TURBINE A. GANY (Technion - Israel Institute of Technology, Haifa) and D. FUEL AT ELEVATED TEMPERATURE W. NETZER (U.S. Naval Postgraduate School, Monterey, CA) IN: A. J. GlOVANElTl and E. J. SZETELA (United Technologies Israel Annual Conference on Aviation and Astronautics, 27th, Haifa, Research Center, East Hartford, CT) Journal of Propulsion and ' Israel, February 27, 28, 1985, Collection of Papers . Haifa, Israel, Power (ISSN 0748-4658), vol. 2, Sept.-Oct. 1986, p. 450-456. Technion - Israel Institute of Technology, 1986, p. 210-219. refs Previously cited in issue 07, p. 876, Accession no. A86-19929. Thermochemical evaluation of fuel candidates for ramjet refs propulsion is made in terms of the theoretical heat of combustion (Contract NAS3-24091) per unit mass and per unit volume of the fuel. Combustion phenomena and combustion efficiency are not accounted for in A87-15187' National Aeronautics and Space Administration. I this study. Compared with the commonly used hydrocarbons, the Lewis Research Center, Cleveland, Ohio. main advantage of using metals or metal compounds is their much POLYMER, METAL, AND CERAMIC MATRIX COMPOSITES FOR higher energy density, which is of great significance in volume ADVANCED AIRCRAFT ENGINE APPLICATIONS limited systems. For practical use, boron has the highest energy D. L. MCDANELS, T. T. SERAFINI, and J. A. DICARLO (NASA, density of all elements (almost three times higher than that of Lewis Research Center, Cleveland, OH) Journal of Materials I hydrocarbons). However, several boron compounds exhibit similar for Energy Systems (ISSN 01 62-9719), vol. 8, June 1986, p. 80-91. theoretical performance, and it is highly recommended to examine Previously announced in STAR as N86-13407. refs them; especially boron carbide and the high borides of aluminum, Advanced aircraft engine research within NASA Lewis is being magnesium and silicon. Author focused on propulsion systems for subsonic, supersonic, and

121 11 CHEMISTRY AND MATERIALS hypersonic aircraft. Each of these flight regimes requires different N87-11902# Jet Propulsion Lab., California Inst. of Tech., types of engines, but all require advanced materials to meet their Pasadena. goals of performance, thrust-to-weight ratio, and fuel efficiency. ANTIMISTING KEROSENE EVALUATION OF LOW The high strength/weight and stiffnesdweight properties of resin, TEMPERATURE PERFORMANCE Final Report, Mar. 1983 - Dec. metal, and ceramic matrix composites will play an increasingly 1984 key role in meeting these performance requirements. At NASA P. PARIKH, A. YAVROUIAN, R. PETERSEN, and V. SAROHlA Lewis, research is ongoing to apply graphite/polyimide composites Aug. 1986 49 p to engine components and to develop polymer matrices with higher (Contract DTFA3-80-A-00215) operating temperature capabilities. Metal matrix composites, using (DOT/FAA/CT-85/31) Avail: NTlS HC AO3/MF A01 magnesium, aluminum, titanium, and superalloy matrices, are being The low temperature and freezing behavior of Jet A and AMK developed for application to static and rotating engine components, fuels was investigated in a 50-gallon capacity wing tank simulator. as well as for space applications, over a broad temperature range. The fuel in the rectangular simulator was chilled from the top and Ceramic matrix composites are also being examined to increase bottom surfaces while the sides were thermally insulated. The the toughness and reliability of ceramics for application to evolution of a vertical temperature profile in the simulator was high-temperatureengine structures and components. Author studied for Jet A and AMK fuels under nearly identical bottom wall temperature histories. A small but noticeable difference between the bulk fuel thermal response of Jet A and AMK was observed with a slower response for AMK. Holdup measurements A87-15924# for AMK were slightly lower than those for Jet A. Rocking of the PROSPECTIVE, CHARACTERISTICS AND PROBLEMS OF THE simulated wing tank did not significantly alter the cool down and USE OF BORON IN DIFFERENT AIR AUGMENTED PROPULSION freezing behavior. The performance of two boost pumps: one for MODES the DC-10 and the other for the Cessna 441 aircraft, was evaluated A. GANY and Y. M. TIMNAT (Technion - Israel Institute of with AMK fuel. For both pumps the performance deteriorated when Technology, Haifa) IAF, International Astronautical Congress, switching from Jet A to AMK. This performance deterioration was 37th, Innsbruck, Austria, Oct. 4-11, 1986. 11 p. refs far more dramatic for the Cessna 441 boost pump than for the (IAF PAPER 86-191) DC-10 boost pump. At low temperature (-30 C) the performance The theoretical energetic advantages and the practical problems of the DC-10 pump actually improved compared to ambient and characteristics associated with three modes of ramjet-type temperature (20 C) performance. It deteriorated, however, for the propulsion engines are discussed. It is shown that the use of Cessna 441 pump. Author boron results in a remarkable theoretical energy gain compared with hydrocarbon fuels, especially in volume-limited systems. However, the poor combustion characteristics of boron and the high ignition temperature required (1900 K) impose special constraints on the combustor system if high efficiencies are to be N87-11904# Air Force Wright Aeronautical Labs., obtained. Solid fuels and propellants containing high percentage Wright-Patterson AFB, Ohio. of boron tend to exhibit irregular combustion (which may cause FlOO FUEL SAMPLING ANALYSIS FOREIGN SAMPLES Final thrust modulations), while agglomeration of boron particles may Report, Apr. 1984 - Apr. 1985 result in incomplete combustion due to the insufficient residence L. 0. MAURICE Mar. 1986 115 p time in the combustor. Author (AD-A168573; AFWAL-TR-85-2087) Avail: NTlS HC AO6/MF A01 CSCL 21D Fuel pump cavitator problems experienced with the F100 engine used in the F-l5/F-16 aircraft have led to an extensive fuel analysis N87-11877# Amax Materials Research Center, Ann Arbor, program to identify properties that might be contributing to fuel Mich. pump falure. This report analyzes the chemical and physical CARBURIZING STEEL FOR HIGH TEMPERATURE SERVICE properties of 12 JP-4 and 4 JP-8 fuel samples obtained from Final Report, 1982 - Dec. 1984 Foreign National Air Bases. The fuels analyzed met specifications T. B. CAMERON and D. E. DIESBURG Aug. 1985 53 p in all but a few isolated cases, and had no unusual properties. If (Contract DAAG46-82-C-0066) the fuel is causing fuel pump failure, it must be the result of a (AD-A168327; REPT-82-C-66; AMMRC-TR-85-25) Avail: NTlS property not being measured. The fuels are as good or better HC A04/MF A01 CSCL 13H than their specifications prescribed. It is concluded that the FlOO A prime concern in airborne equipment is to avoid a brittle fuel pump cavitation problems are most likely associated with the fracture in gearing or bearings which could lead to catastrophic mechanical complexity built into the design, rather than the results engine or propulsion system failure. Projected requirements for of the fuel used. GRA advanced aircraft and helicopters suggest that currently employed through-hardened materials will no longer be adequate for these applications due to their low fracture toughness. Hence there is an interest in carburized materials which have somewhat similar surface characteristics to the through-hardened materials but N87-11908# IIT Research Inst., Bartlesville, Okla. inherently higher core toughness due to the lower core carbon AVIATION TURBINE FUELS, 1985 levels. Five steels similar in composition to CBSlOOO and a low C. L. DICKSON and P. W. WOODWARD May 1986 15 p carbon M50 composition were evaluated with respect to carburizing (Contract DE-FC22-83FE-60149) characteristics, temper resistance, hot hardness and carburized (DE86-012140; NIPER-144-PPS-86/2) Avail: NTlS HC A02/MF fracture toughness. Si, Mo and Ni levels were varied in an effort A0 1 to identify a composition that would maintain a surface hardness Samples of this report are typical 1985 production and were of 58 HRC minimum at 315 C (600 F) without a deterioration in analyzed in the laboratories of 17 manufacturers of aviation turbine fracture toughness properties. Si and Ni were both shown to retard (jet) fuels. The data were submitted for study, calculation, and carburization but have little influence on hardness retention or compilation under a cooperative agreement between the National fracture toughness. A composition with 2.3% Ni was shown to Institute for Petroleum and Energy Research (NIPER), Bartlesville, have optimum carburizing, hardness and fracture toughness Oklahoma, the American Petroleum Institute (API), and the United properties. The modified steel showed an improvement over States Department of Energy (DOE), Bartlesville Project Off ice. CBSlOOO in case fracture toughness but the core fracture Results for certain properties of 88 samples of aviation turbine toughness was lower than that of CBSlOOO. This steel was tested fuels are included in the report for military grades JP-4 and JP-5, in rolling contact fatigue and found to be similar in performance and commercial type Jet A. Previous aviation fuel survey reports to through-hardened M50. GRA are listed. DOE

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N87-12622# Air Force Systems Command, Wright-PattersonAFB, A87-13074 Ohio. Foreign Technology Div. ADVANCED MANUFACTURING TECHNOLOGY FOR CARBON FIBERS STRUCTURAL AIRCRAFT/AEROSPACE COMPONENTS A. A. KONKIN and N. F. KONNOVA 22 Aug. 1986 35 p N. C. OLSEN (XERKON Co., Minneapolis, MN) IN: International Transl. into ENGLISH from Zhurnal Vsesoyuznogo Khimicheskogo SAMPE Symposium and Exhibition, 31st, Los Angeles, CA, April Obshchestva (USSR), v. 17, no. 6, 1972 p 632-639 7-10, 1986, Proceedings . Covina, CA, Society for the Advancement (AD-A171 370; AD-F250645; FTD-ID(RS)T-0761-86) Avail: NTlS of Material and Process Engineering, 1986, p. 387-395. HC AO3/MF A01 CSCL 11B An integrated semiautomated multiple manufacturing process In connection with development of missile construction, aircraft has been developed to produce composite primary structural parts construction, mastery of space, and also other branches of uniquely shaped to match typical airframe taper and curvature. technology arose acute need for high temperature (oxidation The initial process employs modified textile equipment to process resistant) fibrous materials, reinforced plastics on basis of which knitted fabric broadgoods using carbon, aramid, and fiberglass were intended for exploitation at high temperatures. Common fibers. The knitted fabric broadgoods are then assembled into a natural and synthetic fibers, including thermoresistant, could not fiber form; dry fiber forms are impregnated using the resin film satisfy these requirements. As a result of intensive investigations, infusion process. The pressure molding process uses matched carried out for latter by decade are developed methods of obtaining surface tooling, and the curing process uses temperature, pressure, large number of high temperature (oxidation resistant) fibers and vacuum. The process generates fully cured or staged parts different in properties, predominantly on basis of inorganic allowing the components to be co-cured to other assemblies. compounds. To the important of them relate carbon, boric, carbide, V.L. metallic, on the basis of oxides of the elements and some other compounds. Filamentary crystals (whisker) occupy special position in view of unique mechanical properties. This group of fibers is located on different levels of technical development. GRA

A87-13123 NOVEL COMPOSITE REPAIR METHODS N87-12685# State Univ. of New York, Stony Brook. Dept. of R. L. COLOGNA (Boeing Aerospace Co., Seattle, WA) IN Chemistry. International SAMPE Symposium and Exhibition, 31st, Los Angeles, CHARACTERIZATION AND DYNAMICAL STUDIES OF CA, April 7-10, 1986, Proceedings . Covina, CA, Society for the POLYMERS IN DIPOLAR (APROTIC) LIQUIDS Final Report, 5 Advancement of Material and Process Engineering, 1986, p. Jul. 1982 - 4 Jan. 1986 1017-1022. B. CHU 14 Apr. 1986 7 p Novel composite blind-side repair methods for aircraft are being (Contract DAAG29-82-K-0143) developed which are particularly suitable for use in the field or at (AD-A169243; REPT-6340A; ARO-19251.5-CH) Avail: NTlS HC an operating base under adverse conditions and stringent time A02/MF A01 CSCL 20D constraints. The repairs can be accomplished easiiy wiin simpie The aerodynamic breakup of liquids is an essential mechanism hand tools and require minimum training and skill to perform. The in many processes, e.g., fuel atomization in liquid rocket engine, repairs can be used to provide support to the blind side, provide turbojet afterburners and ramjets, paint spraying, aerial a vacuum seal, and permit near-side repair by conventional dissemination of insecticides, and explosive dissemination of fuels. methods such as scarf or doubler. Two such methods are Only limited studies have been conducted on the aerodynamic considered: flexible-washer and turn-in disk blind-side repair. A breakup of viscoelastic fluids where molecular parameters must blind-side repair validation test on a graphite-epoxy honeycomb necessarily play an important role in the control of both the sandwich panel was carried out. B.J. magnitude of the mean mass diameter of the droplets and the droplet size distribution. The viscoelastic properties of bulk liquid can be altered by using polymer additives whose molecular weight, concentration an dcomposition control the conversion of bulk liquid into specific droplet sizes for a fixed stress and geometry. In this report, we want to summarize the experimental preparations we have made to characterize both static and dynamic properties of polymer additives in dipolar (aprotic) liquids. We have developed a generalized technique to determine the molecular weight, the A87-13164 molecular weight distribution, the polymer composition, the USE OF FILAMENT WINDING IN MANUFACTURING HIGH interaction parameters expressed in terms of the second virial QUALITY AEROSPACE COMPOSITE COMPONENTS coefficients, including both thermodynamic and hydrodynamic A. K. MUNJAL (Aerojet Strategic Propulsion Go., Sacramento, interactions for copolymers by means of laser light scattering. As CA) IN: International SAMPE Symposium and Exhibition, 31st, a specific example, we characterized acryloid k-125, a Los Angeles, CA, April 7-10, 1986, Proceedings . Covina, CA, quasiterpolymer used in aerodynamic breakup tests. GRA Society for the Advancement of Material and Process Engineering, 1986, p. 1504-1518. refs The use of filament winding in aircraft manufacture has been limited due to concerns regarding high void content, resin matrix selection, aerospace resign processing requirements, fiber placement accuracy, resin fiber control, composite quality, in-process inspection method applicability, aerodynamic surface 12 finish requirements, and structural design analysis suitability. These concerns are presently addressed with a view to the improvement ENGINEERING of quality and structural integrity in filament-wound composites. Attention is given to the optimum selection of materials, tooling Includes engineering (general); communications and radar; and design, as well as the quality control of materials, their electronics and electrical engineering; mechanics and heat transfer; processing, and their handling during manufacture. The minimization instrumentation and photography; lasers and masers; mechanical of void content is noted to be the single most important factor in engineering; quality assurance and reliability; and structural the determination of composites’ resin-dominated properties. mechanics. O.C.

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A87-13173 geometry of injection. Such geometrical considerations may be of 7050. - - ALUMINUM..- -.. . - RIVETS FOR MILITARY AIRCRAFT great importance in the design of afterburner wall geometry and E. R. WOOD (Lockheed-CaliforniaCo., Burbank) IN: International in the reduction of wall thermal damage. The injection geometry SAMPE Symposium and Exhibition, 31st, Los Angeles, CA, April may also affect the intensity of the spray distribution which 7-10, 1986, Proceedings . Covina, CA, Society for the Advancement determines the mode of droplet group combustion. The latter plays of Material and Process Engineering, 1986, p. 1619-1630. an important role in improving afterburner combustion efficiency. The use of 7075 alloy aluminum rivets leads to a sharp decline Author in the number of rivets that must be removed due to cracking during aircraft structure assembly, by comparison to experience with the 2024 alloy rivets previously employed. While the 2024 A87-13680 alloy rivets require treatment at subzero temperatures prior to WHOLEFIELD DISPLACEMENT MEASUREMENTS USING installation. the 7075 rivets are driven in place in their final temper SPECKLE IMAGE PROCESSING TECHNIQUES FOR CRASH condition. Attention is given to the results of tension, lap shear TESTS and fatigue testing for 7075 rivets, in light of which a major P. SRIRAM, S. HANAGUD (Georgia Institute of Technology, commercial and military aircraft manufacturer is planning complete Atlanta), and W. F. RANSON (South Carolina, University, conversion to rivets of this type. O.C. Columbia) IN: National Specialist's Meeting on Crashworthy Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, Proceedings . A87-13625 Alexandria, VA, American Helicopter Society, 1986, 6 p. refs MECHANIZED MANUFACTURE OF COMPOSITE MAIN ROTOR (Contract DAAG29-82-K-0094) BLADE SPARS The digital correlation scheme of Peters et al. (1983) was D. HOLT (Westland, PLC, Yeovil, England) IN: Fibre reinforced extended to measure out-of-plane deformations, using a white light composites 1986; Proceedings of the Second International projection speckle technique. A simple ray optic theory and the Conference, Liverpool, England, April 8-10, 1986 . London, digital correlation scheme are outlined. The technique was applied Mechanical Engineering Publications, Ltd., 1986, p. 125-131. successfully to measure out-of-plane displacements of initially flat This paper describes the latest developments in a long-term rotorcraft structures (an acrylic circular plate and a steel cantilever program directed at the integrated design and manufacture of beam), using a low cost video camera and a desktop computer. composite main rotor blades. The availability of high performance The technique can be extended to measurements of composite materials made it possible to design rotor blades with three-dimensional deformations and dynamic deformations. I.S. considerably enhanced performance relative to standard metal blades. The use of prepreg materials called for entirely new A87-13682 methods of manufacture, and mechanization of the process was MECHANISM OF ENERGY ABSORPTION VIA BUCKLING - AN essential if performance and quality standards were to be ANALYTICAL STUDY guaranteed. A close liaison between design and manufacturing S. V. HANAGUD, A. CHATTOPADHYAY, J. ZHANG, and Y. WANG engineers has resulted in a series of mechanization projects (Georgia Institute of Technology, Atlanta) IN: National Specialist's culminating in an FMS cell for the manufacture of main-rotor blade Meeting on Crashworthy Design of Rotorcraft, Atlanta, GA, April spars. Author 7-9, 1986, Proceedings . Alexandria, VA. American Helicopter Society, 1986, 10 p. refs A87-13642# (Contract DAAG29-82-K-0094) THE EFFECT OF MATERIAL COMPRESSIBILITY (POISSON The static postbuckling behavior of energy absorbing structures RATIO) ON THE ELASTO-PLASTIC SOLUTION TO THE has been analyzed in this paper for the purpose of developing a PROBLEM OF A CYLINDER UNDER INTERNAL PRESSURE procedure for optimum design of energy absorbing structures which (COLDWORKING SITUATION) are essential parts of a crashworthy design of rotorcraft. Finite Y. BORTMAN and D. SCHUR (Tel Aviv University, Israel) IN: deformations have been considered and an adapted Lagrangian Israel Annual Conference on Aviation and Astronautics, 27th, Haifa, approach has been used. The numerical analysis consists of Israel, February 27, 28, 1985, Collection of Papers . Haifa, Israel, discrete penalty function based finite element technique. The Technion - Israel Institute of Technology, 1986, p. 61-64. refs iteration procedure uses a constant arc-length method. Results The effect of material compressibility (Poisson ratio) on the have been presented for specific energy absorbing structure. residual elastoplastic stress distribution around a fastener hole Author was investigated. The aim of this study is to estimate the error which could arise in using a close form solution of the stress distribution instead of the exact solution which cannot be A8743683 determined by analytical means. The finite element approach was CORRELATION OF EXPERIMENTAL STATIC AND DYNAMIC used to show that the residual hoop stress is not significantly RESPONSE OF SIMPLE STRUCTURAL COMPONENTS dependent on the Poisson ratio. Author J. 1. CRAIG, S. V. HANAGUD, W. ZHOU, and P. SRIRAM (Georgia Institute of Technology, Atlanta) IN: National Specialist's Meeting A87-13660# on Crashworthy Design of Rotorcraft, Atlanta, GA, April 7-9, 1986, SPRAY CHARACTERISTICS OF TWO COMBINED JET Proceedings . Alexandria, VA, American Helicopter Society, 1986, ATOMIZERS 5 p. refs Y. TAMBOUR and D. PORTNOY (Technion - Israel Institute of (Contract DAAG29-82-K-0094) Technology, Haifa) IN: Israel Annual Conference on Aviation Crashworthy design of rotorcraft involves not only a and Astronautics, 27th, Haifa, Israel, February 27, 28, 1985, systems-oriented approach but also requires that the design and Collection of Papers . Haifa, Israel, Technion - Israel Institute of performance simulation of each system be based on accurate Technology, 1986, p. 220-228. refs component models. To date, much of the structural simulation The downstream changes in droplet volume concentration of work has focused on analytical models, although several programs a vaporizing fuel spray produced by two jet atomizers which form are capable of including force-deformation characteristics derived an overlapping zone of influence is analyzed. One of the atomizers from experimental tests. However, the formulations are based on is located below the other at a certain distance downstream. Such static or quasi-static characteristics and are not capable of handling an injection geometry can be found in afterburners of modern jet time-dependent properties. The reported work is an initial attempt engines. The influence of various vertical and horizontal distances to develop dynamic response characteristics for simple composite between the two atomizers on the downstream spray characteristics structural components that have potential for use in crashworthy is investigated for a vaporizing kerosene spray in a 'cold' (293 K) design. Preliminary results from static and dynamic and a 'hot' !d50 K) environment. The present analysis shows how buckling/post-buckling tests of Kevlar corrugated-web sandwich one can control the downstream spray characteristics via the panels are reported. Author

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A87-13719 A87-13848' National Aeronautics and Space Administration. AUTOMATED INFRARED INSPECTION OF JET ENGINE Marshall Space Flight Center, Huntsville, Ala. TURBINE BLADES LARGE VOLUME WATER SPRAYS FOR DISPERSING WARM T.. BANTEL.-. .. . D. BOWMAN. J. HALASE. S. KENUE. R. KRISHER FOGS (General kectric Co., Aircraft Engine Business Group, Evendale, V. W. KELLER, B. J. ANDERSON, R. A. BURNS (NASA, Marshall OH) et al. IN: International Conference on Thermal Infrared Space Flight Center, Huntsville, AL), G. G. LALA, and M. B. MEYER Sensing for Diagnostics and Control (Thermosense VIII), (New York, State University, Albany) IN: ICLASS-85; Proceedings Cambridge, MA, September 12-20, 1985, Proceedings . Bellingham, of the Third International Conference on Liquid Atomisation and WA, Society of Photo-Optical Instrumentation Engineers, 1986, p. Spray Systems, London, England, July 8-10, 1985. Volume 2 . 18-23. London, Institute of Energy, 1986, p. LP/VIIC/4/1 -LP/VIIC/4/10. (Contract F33615-80-C-5106) NASA-supported research. refs The detection of blocked surface cooling holes in hollow jet A new method for dispersing of warm fogs which impede visibility engine turbine blades and vanes during either manufacture or and alter schedules is described. The method uses large volume overhaul can be crucial to the integrity and longevity of the parts recycled water sprays to create curtains of falling drops through when in service. A fully automated infrared inspection system is which the fog is processed by the ambient wind and spray-induced being established to inspect these surface cooling holes for air flow; the fog droplets are removed by coalescence/rainout. blockages. The method consists of viewing the surface holes of The efficiency of this fog droplet removal process depends on the blade with a scanning infrared radiometer when heated air is the size spectra of the spray drops and optimum spray drop size flushed through the blade. As the airfoil heats up, the resultant is calculated as between 0.3-1.0 mm in diameter. Water spray infrared images are written directly into computer memory where tests were conducted in order to determine the drop size spectra image analysis is performed. The computer then makes a and temperature response of sprays produced by commercially determination of whether or not the holes are open from the available fire-fighting nozzles, and nozzle array tests were utilized inner plenum to the exterior surface, and ultimately makes an to study air flow patterns and the thermal properties of the overall acceptheject decision based on previously programmed criteria. system. The initial test data reveal that the fog-dispersal procedure A semiautomatic version has already been implemented and is is effective. I.F. more cost effective and more reliable than the previous manual inspection methods. Author A87-13872' Boeing Computer Services Co., Tukwila, Wash. AN EXTERIOR POISSON SOLVER USING FAST DIRECT METHODS AND BOUNDARY INTEGRAL EQUATIONS WITH APPLICATIONS TO NONLINEAR POTENTIAL FLOW A87-13828 D. P. YOUNG (Boeing Computer Services Co., Tukwila, WA), A. PERFORMANCE AND OPTlMlSATlON OF AN AIRBLAST C. WOO (NASA, Ames Researh Center, Moffett Field, CA), J. E. NOZZLE - DROP SIZE DISTRIBUTION AND VOLUMETRIC AIR BUSSOLETTI, and F. T. JOHNSON (Boeing Military Airplane Co., FLOW Seattle, WA) SlAM Journal on Scientific and Statistical Computing M. AIGWR arid ??ITT!G :Kar!s:uhe, Uni\vnrsi?rret, West S. jiSSii Oi96-5204j, vdi. 7, duly !386, p. 1OW! 021. re!^ Germany) IN: ICLASS-85; Proceedings of the Third International (Contract NSF MCS-80-12220; NAS2-9830) Conference on Liquid Atomisation and Spray Systems, London, A general method is developed combining fast direct methods England, July 8-10, 1985. Volume 1 . London, Institute of Energy, and boundary integral equation methods to solve Poisson's 1986, p. llC/3/l-llC/3/8. Research supported by the equation on irregular exterior regions. The method requires O(N Forschungsvereinigung fuer Verbrennungskraftmaschinen. refs log N) operations where N is the number of grid points. Error Detailed experimental studies of airblast atomization with its estimates are given that hold for regions with corners and other governing processes were conducted by utilizing various atomizers. boundary irregularities. Computational results are given in the In considering practical design principles, it is shown, that air context of computational aerodynamics for a two-dimensional lifting consumption and drop size distribution depend on various airfoil. Solutions of boundary integral equations for lifting and parameters such as geometry, air swirl and acceleration. The film's nonlifting aerodynamic configurations using preconditioned inlet position and the diameter of the atomization edge are of conjugate gradient are examined for varying degrees of thinness. secondary importance. In contrast to other studies it is found, Author that the film thickness has only an indirect effect on the quality of atomization, due to its roughness effects. Author

A87-13986# INCREASING THE ECONOMY OF DESIGN AND PREPARATION FOR MANUFACTURING BY INTEGRATED AND GRAPHIC DATA A87-13830 PROCESSING CAD/CAM - PHASE 111 [ERHOEHUNG DER PREDICTION OF VELOCITY COEFFICIENT AND SPRAY CONE WIRTSCHAFTLICHKEIT VON KONSTRUKTION UND ANGLE FOR SIMPLEX SWIRL ATOMIZERS FERTIGUNGSVORBEREITUNG DURCH INTEGRIERTE UND N. K. RlZK and A. H. LEFEBVRE (Purdue University, West GRAPHISCHE DATENVERARBEITUNG CAD/CAM - PHASE I111 Lafayette, IN) IN: ICLASS-85; Proceedings of the Third U. GRUPE (Messerschmitt-Boelkow-Blohm GmbH, Bremen, West International Conference on Liquid Atomisation and Spray Systems, Germany) BMFT, Statusseminar ueber Luftfahrtforschung und London, England, July 8-10, 1985. Volume 1 . London, Insliute of Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, Energy, 1986, p. lllC/2/1-lllC/2/16. refs Paper. 39 p. In German. The effects of atomizer dimensions and operating conditions (Contract BMFT-LVS-8305) on spray cone angle and velocity coefficient are examined. A (MBB-UT-225-86) theoretical approach is adopted to determine the liquid film The development of CADICAM techniques and equipment for thickness in the final discharge orifice and to relate this thickness aircraft production at Dornier and MBB during the period 1983-1986 to cone angle and velocity coefficient. The calculated results are is reviewed. The topics discussed include geometry processing, shown to compare satisfactorily with the experimental data reported structural mechanics, design of fabrication equipment, NC in the literature. Equations are presented for predicting cone angle techniques, production planning, and processing of production and velocity coefficient in terms of the nozzle pressure differential orders. Consideration is given to the increased use of color and the nozzle constant K, which is defined as the ratio of inlet graphics, the change from vector to scanning screens, and ports area to the product of discharge orifice diameter and swirl software-related problems encountered in shifting functions from chamber diameter. Author the mainframe computer to terminals. T.K.

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A87-13999# A87-15006# TECHNOLOGIES FOR A MECHANIZED CARBON FIBER STATE-OF-THE-ART TECHNIQUES FOR LIGHTNING CONSTRUCTION ELEMENT FOR COMMERCIAL AIRCRAFT SUSCEPTIBILITYNULNERABILITY ASSESSMENTS PRODUCTION [TECHNOLOGIEN FUER ElNE MECHANISIERTE J. G. SCHNEIDER, M. D. RISLEY, M. J. REAZER, A. V. SERRANO KOHLEFASERBAUTEILFERTIGUNG IM ZIVILFLUGZEUGBAU] (Technology/Scientific Services, Inc., Dayton, OH), and J. L. R. OBERFRANZ (Messerschmitt-Boelkow-Blohm GmbH, Hamburg, HEBERT (USAF, Wright Aeronautical Laboratories, West Germany) BMFT, Statusseminar ueber Luftfahrtforschung Wright-Patterson AFB, OH) IN: International Aerospace and und Luftfahrttechnologie, Munich, West Germany, Apr. 28-30, 1986, Ground Conference on Lightning and Static Electricity, llth, Paper. 24 p. In German. Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, (Contract BMFT-LFK-8351-4) National Interagency Coordination Group, 1986, p. 8-1 to 8-8. (MBB-UT-005-86) refs Technological steps taken to improve the economicality and The vulnerability of current and future aircraft to reproducibility of carbon fiber-reinforced elements for commercial lightning-induced EMP and electrostatic discharges can be aircraft construction are reviewed. The characterization and assessed by the techniques developed at Wright Aeronautical handling of blanks are discussed, and alloying techniques for cubic Laboratories. The methods are presently noted to possess bodies are reviewed. Processing and binding techniques for thicker cost-effective data acquisition, processing and storage systems, laminates and shaping and boring techniques for CFK structures and software of exceptionally high productivity. The and laminates are described. Quality control and the preparation microcomputer-controlled minicomputers used are capable of of production materials are addressed. C.D. transient as well as CW measurements, and analog fiber data links that are pneumatically controlled for use in the high EM noise environment of high voltage/current simulators are incorporated. O.C. A87-14006# NEW-TECHNOLOGY GAS GENERATOR (GNT 1) - THE ACTUAL A87-15007# STATE OF DEVELOPMENT [GASGENERATOR NEUER TECH- COMPARISON OF LOW LEVEL FREQUENCY DOMAIN NOLOGIE /GNT 1/ - AKTUELLER ENTWICKLUNGSSTAND] LIGHTNING SIMULATION TEST TO PULSE MEASUREMENTS W. WEILER (MTU Motoren- und Turbinen-Union Muenchen GmbH, D. B. WALEN (Boeing Military Airplane Co., Seattle, WA) IN: Munich, West Germany) BMFT, Statusseminar ueber International Aerospace and Ground Conference on Lightning and Luftfahrtforschung und Luftfahrttechnologie, Munich, West Static Electricity, 1lth. Dayton, OH, June 24-26, 1986, Technical Germany, Apr. 28-30, 1986, Paper. 46 p. In German. refs Papers . Fairborn, OH, National Interagency Coordination Group, An advanced gas generator for aircraft gas turbines of the 1986, p. 9-1 to 9-8. 1000-kW class, called the new-technology generator (GNT l), is (Contract F33615-82-C-3406) discussed. The main components of the generator are described, Three lightning test techniques were used to measure induced and test results giving its present state of development are transients on a modified F-14A airplane. The F-14A was modified reviewed. C.D. by adding graphitelepoxy skin panels and by installing special avionics equipment. Test techniques demonstrated on the F-14A A87-14423 included low current (less than 20A) swept frequency transfer APPLICATION OF A MIXED VARIATIONAL APPROACH TO function measurements, moderate current (28 kA) pulse tests and AEROELASTIC STABILITY ANALYSIS OF A NONUNIFORM high current (200 kA) pulse tests. The results of the measurements BLADE were compared using Fourier transformations and linear M. NATORI and S. NEMAT-NASSER (Northwestern University, extrapolation. Responses measured at lower current levels and Evanston, IL) Journal of Structural Mechanics (ISSN 0360-121 8), extrapolated to higher current levels were 23 percent lower to 32 vol. 14, no. 1, 1986, p. 5-31. refs percent higher than the responses measured at high levels. (Contract DAAG29-79-C-0168) Author A mixed variational approach is used to investigate the coupled flap-lagtorsional aeroelastic stability of a nonuniform helicopter A87- 15023# blade. This approach is particularly suited to treating rotating blades EXPERIMENTAL STUDY OF THE INTERACTION BETWEEN AN with sharp variations or discontinuous changes in their properties ARC AND AN ELECTRICALLY FLOATING STRUCTURE or cross-sectional dimensions. Numerical results by this approach G. LABAUNE, J. P. MOREAU, J. C. ALLIOT. V. GOBIN (ONERA, are presented in hovering conditions, for both uniform and Chatillon-sous-Bagneux, France), B. HUTZLER (Electricite de nonuniform blades with low torsional stiffness, and compared with France, Moret-sur-Loing) et al. IN: International Aerospace and the results by the usual Rayleigh-Ritz method. It is shown that Ground Conference on Lightning and Static Electricity, 1lth, the present approach has good convergence properties for both Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, static equilibrium position and critical collective pitch angles. National Interagency Coordination Group, 1986, p. 27-1 to 27-9. Author DRET-supported research. refs The relationship between an arc and an electrically floating structure is investigated with a high-voltage apparatus. An analysis A87-14683 is conducted of the phase of the arc-structure connection when METHODS FOR THE ASSEMBLY AND TESTING OF THE the plasma on each side of the structure is of high resistivity; it is BEARING SUPPORTS OF GAS TURBINE ENGINES shown that the structure is in electric equilibrium between impulsive [TEKHNOLOGIIA SBOAKI I KONTROLIA PODSHIPNIKOVYKH positive and negative streamers that induce fast and strong OPOR GTD] variations of the electric field at its surface. O.C. V. A. ZAKHAROV Moscow, Izdatel’stvo Mashinostroenie, 1985, 128 p. In Russian. refs A87- 15029# The general design and the principal geometrical and force LIGHTNING RETURN STROKE CURRENT COMPUTATION characteristics of the rolling bearings and bearing supports of gas P. R. P. HOOLE and J. E. ALLEN (Oxford University, England) turbine engines are summarized with reference to the results of IN: International Aerospace and Ground Conference on Lightning recent studies in this field. Particular attention is given to the and Static Electricity, llth, Dayton, OH, June 24-26, 1986, organization and optimization of the bearing assembly process. Technical Papers . Fairborn, OH, National Interagency Coordination Theoretical relationships are presented for calculating the initial Group, 1986. p. 34-1 to 34-10. Research supported by the Culham data required for the assembly process design; the nature and Lightning Club and ORS Committee of British Universities. refs sequence of individiual assembly operations are examined, and The paper briefly reviews the lightning return stroke models, ways of improving the assembly precision are discussed. V.L. currently in use and highlights some weaknesses of these models

126 12 ENGINEERING in relation to basic principles of physics and observed reported. A method for generalizing experimental data is proposed characteristics of the return stroke. The solution of diffusion which makes it possible to obtain a unified similarity equation equation for a distributed line is given. Then a simple distributed allowing for the effect of the curvature of flow lines, for the LCR model of the return stroke, with all the elements calculated three-dimensional nature of the flow, for flow acceleration along from known data is given. The return stroke currents along the the channel, and for the laminar transition of the flow. The equation channel are calculated and its implications to current measurements can be used for calculating local heat transfer coefficients at and applications of the model are discussed. Author arbitrary points of the face surface. V.L.

A87-15039# A87-15218 IMPROVED ELECTROSTATIC DISCHARGE WICKS FOR A STUDY OF THE EFFECT OF THE TEMPERATURE FACTOR AIRCRAFT ON PRESSURE LOSSES IN THE COOLING SYSTEM OF THE R. V. ANDERSON and J. C. BAILEY (US. Navy, Naval Research LEADING EDGE OF A DEFLECTOR VANE [ISSLEDOVANIE Laboratory, Washington, DC) IN: International Aerospace and VLllANllA TEMPERATURNOGO FAKTORA NA POTERI Ground Conference on Lightning and Static Electricity, 1lth, DAVLENllA V SISTEME OKHLAZHDENIIA VKHODNOI KROMKI Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, DEFLEKTORNOI LOPATKI] National Interagency Coordination Group, 1986, p. 49-1 to 49-5. A. I. ARKHIPOV, A. S. LIMANSKII, V. V. RUMIANTSEV, and M. refs M. KHASBIULLIN Aviatsionnaia Tekhnika (ISSN 0579-2975), no. After presenting a development history for the static discharge 2, 1986, p. 81-83. In Russian. refs wicks used in reducing the static potential of aircraft employed in Reference is made to several earlier studies in which pressure measurements of small, fair weather electric fields, attention is losses associated with the use of single-row and multiple-row jet given to the results of the 1985 tests in which the dependencies cooling of the leading edge of nozzle vanes of gas turbine engines of aircraft potential were observed for the number of wicks used, have been estimated using independent models of the leading their length, and their diameters. Theoretical studies of corona edge. Here, experiments are carried out on a specially designed discharge are reviewed, and their applicability to the aircraft high-temperature gasdynamic test bench in order to verify the discharge problem is discussed. It is concluded that a significant validity of the earlier results and also to determine the effect of reduction in aircraft potential is obtainable through the use of process nonisothermality on pressure losses. V.L. metallic wicks. O.C. A87- 15226 A87-15193# ANALYSIS OF A COMPOSITE THIN-WALLED AIRCRAFT FINITE ELEMENT CONTACT ANALYSIS OF RING GEAR AND STRUCTURE [K RASCHETU SOSTAVNOI TONKOSTENNOI SUPPORT AVIAKONSTRUKTSII] S. SUNDARARAJAN and R. BLANCHElTE (Pratt and Whitney V. A. PAVLOV and A. S. SAFONOV Aviatsionnaia Tekhnika Canada, Inc.. Longueuil, Canada) Canadian Aeronautics and (ISSN 0579-2975), no. 2, 1986, p. 102-104. In Russian. Space Journal (ISSN 0008-2821), vol. 32, June 1986, p. 148-154. A numerical method is proposed for analyzing the stress-strain refs state of composite thin-walled lifting surfaces, such as tail surfaces !R !he PE!nrhnprnp ensines of Pratt and Whitnev. Canada, and !he ~ing!oge!hor with !he lift-increasing devices. The approach the turbine-to-propeller speed reduction is obtained using a used here is based on a refined discrete-continuous model and two-stage planetary gearbox. This paper describes a method of makes it possible to determine the stress-strain state of irregular analyzing the ring gear torque reacted by six steel pins. In-house structures under any conditions of external loading, including large finite element contact analysis computer program was developed concentrated force factors and a temperature field. As an example, and used to analyse in detail and optimize the geometry of the a stress-strain analysis is carried out for tail surfaces of various ring gear. The development of the computer program and the types. V.L. interplay of the different geometric parameters of the ring gear are discussed. The need for analysing gears as structures rather than as pairs of teeth in mesh is emphasized. Author A87-15403 ENVIRONMENTAL STRESS SCREENING (ESS) A87-15203 DEMONSTRATES ITS VALUE IN THE FIELD THE EFFECT OF LUBRICANT CAVITATION ON THE J. L. CAPITANO (Gould, Inc., Arlington, VA) and J. H. FElNSTElN CHARACTERISTICS OF A SHORT HYDRODYNAMIC DAMPER (Gould, Inc., Defense Electronics Div., Glen Burnie, MD) IN: [VLIIANIE KAVlTATSll SMAZKI NA KHARAKTERlSTlKl 1986 Annual Reliability and Maintainability Symposium, Las Vegas, 'KOROTKOGO' GIDRODINAMICHESKOGO DEMPFERA] NV, January 28-30, 1986, Proceedings . New York, Institute of A. I. BELOUSOV and V. B. BALlAKlN Aviatsionnaia Tekhnika Electrical and Electronics Engineers, Inc., 1986, p. 31-35. (ISSN 0579-2975), no. 2, 1986, p. 15-19. In Russian. The failure rate of systems in the field is often much higher Analytical relationships are presented for calculating the than planned; thereby negatively impacting support cost and components of a hydrodynamic reaction with allowance for the availability. This paper explores the cause and presents a true discontinuity region of a lubricant film. It is shown that the demonstrated solution for this unacceptably high field failure rate. rupture of a lubricant film reduces the tangential component and A concept (ESS) is presented as not only a significant contributor gives rise to a radial component of the hydrodynamic force. to the solution of this problem but as a demonstrated cost effective Therefore, in a short hydrodynamic damper, the true size of the one. Author cavitation region of the working fluid must be taken into account to improve the accuracy of the calculated dynamic characteristics A87-15412# of the damper. V.L. RELIABILITY GROWTH DURING FLIGHT TEST J. N. BOWER (USAF, Edwards AFB, CA) IN: 1986 Annual A87-15215 Reliability and Maintainability Symposium, Las Vegas, NV, January A STUDY OF LOCAL HEAT TRANSFER ON THE FACE 28-30, 1986, Proceedings . New York, Institute of Electrical and SURFACE OF A NOZZLE RING MODEL [ISSLEDOVANIE Electronics Engineers, Inc., 1986, p. 101-1 06. LOKAL'NOGO TEPLOOBMENA NA TORTSEVOI 6-52 Offensive Avionics System (OAS), F-16 XL avionics POVERKHNOSTI MODEL1 SOPLAVOGO APPARATA] system, and F-16 Multinational Staged Improvement Program A. A. KHALATOV, K. I. KAPITANCHUK. A. S. KOVALENKO, and (MSIP) avionics flight-test data are discussed in terms of reliability. A. N. TRUFANOV Aviatsionnaia Tekhnika (ISSN 0579-2975). The Duane model was used to predict reliability growth by plotting no. 2, 1986, p. 68-72. In Russian. refs weighted linear regression values for the cumulative failure rate Results of an experimental study of local heat transfer on the (MTBF) in log-log form. The method avoids the controversial face surface of a model of the nozzle ring of a gas turbine are aspects of MIL-STD-l635(EC), Reliability Growth Testing, which

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assumes independence between data points, an inaccurate figurations and redundancies. BIT capabilities are identified as the technique for cumulative statistics. M.S.K. most effective for fail-safe system operation. M.S.K.

A87-154 17 RADC AUTOMATED R&M PACKAGE (RAMP) F. WINTER and G. W. LYNE (USAF, Rome Air Development Center, Griffiss AFB, NY) IN: 1986 Annual Reliability and Maintainability A87-15432 Symposium, Las Vegas, NV, January 28-30, 1986, Proceedings . REVERSE TAILORING FOR REALISTIC RELIABILITY TESTS New York, Institute of Electrical and Electronics Engineers, Inc., H. CARUSO (Westinghouse Product Qualification Laboratory, 1986, p. 177-182. refs Baltimore, MD) IN: 1986 Annual Reliability and Maintainability As electronic systems become increasingly complex, more Symposium, Las Vegas, NV, January 28-30, 1986, Proceedings . efficient and cost effective means of predicting reliability and New York, Institute of Electrical and Electronics Engineers, Inc., maintainability to fulfill DOD procurement requirements are needed. 1986, p. 397-402. refs Because of the increased demand for automated R&M prediction, Reverse tailoring is proposed as an analytical process whereby RADC RAMP has been developed as an interface between various the environmental engineering specialist can evaluate the validity RADC R&M computer programs. RAMP provides a structured of specified environmental design and test criteria. Detailed approach to R&M analysis, eliminating the need for certain examples are presented for traditionally specified high- and subjective judgments and hand calculations. The computer low-temperature values for airborne electronics. Mission-use programs made available through RAMP are discussed: the RADC considerations and basic physics, combined with published Optimized Reliability and component Life Estimator (ORACLE), the literature and interviews with the equipment operators, can be ORACLE Stress Analysis Program (OSAP), the ORACLE Thermal used to establish realistic environmental criteria in the absence of Analysis Program (OTAP), the computer-Aided Maintainability specific measured data. Author Predictor (CAMP), and the Derivative Truncated Sequential Test Plan (DTSTP) Program. Author

A87-15423 VLSl IMPACT ON RAMS STRATEGIES IN AVIONICS DESIGN L. R. WEBSTER and J. M. MADER (Harris Corp., Melbourne, FL) A87-15433 IN: 1986 Annual Reliability and Maintainability Symposium, Las SIZING HYBRID PACKAGES FOR OPTIMUM RELIABILITY Vegas, NV, January 28-30. 1986, Proceedings. New York, Institute H. S. GOEDEKE (Westinghouse Electric Corp., Baltimore, MD) of Electrical and Electronics Engineers, Inc., 1986, p. 303-306. IN: 1986 Annual Reliability and Maintainability Symposium, Las Although VLSl will improve the reliabilityof electronics-dominated Vegas. NV, January 28-30, 1986, Proceedings . New York, Institute avionics, off-chip interconnections will still limit reliability. The reli- of Electrical and Electronics Engineers, Inc., 1986, p. 403-407. ability of a VLSl chip is expected to be nearly 20 times that of LSI refs chips. The control over the system MTBF by the MTBFof the intercon- An analytical technique is defined for quantifying the package nections can be lessened by increasing the complexity of the VLSl size at which a minimum hybrid failure rate will occur in devices, thus decreasing the number of interconnections on a microelectronics avionics packages for aircraft. The method was board. M.S.K. devised specifically to satisfy the requirements of MIL-HDBK-2170 and the failure rate equation it contains. The FORTRAN code A87-15425 HYBRID was written to identify a minimum failure rate package DEVELOPMENT OF A MAINTENANCE AUTOMATION SYSTEM size. The results of sample calculations are provided for a hybrid R. LOH (Mitre Corp., McLean, VA) and J. NAGER (FAA, electronics package, showing the failure rate as a function of Washington, DC) IN: 1986 Annual Reliability and Maintainability temperature and package size. The code is considered valuable Symposium, Las Vegas, NV, January 28-30, 1986, Proceedings . whenever an electronics package must have a minimal size and New York, Institute of Electrical and Electronics Engineers, Inc., operate over a specified temperature range. M.S.K. 1986, p. 332-337. refs Given the ever increasing costs for personnel, the advent of stable and reliable albeit more complex modern equipment, the lowering of costs for computers, and the improvements in communications multiplexing technology, it is now cost-effective A87-15435 to implement maintenance automation systems (MAS). The APPLICATION OF MARKOV MODELS FOR RMA objective of this paper is to define a generic MAS for a large and ASSESSMENT dispersed maintenance organization, to propose a management J. V. JOSSELYN, R. E. FLEMING, J. A. FRENSTER, and R. L. model for the development and implementation of such a MAS, DE HOFF (Systems Control Technology, Inc., Palo Alto, CA) IN: and to cite examples from the Federal Aviation Administration’s 1986 Annual Reliability and Maintainability Symposium, Las Vegas, (FAA) Remote Maintenance Monitoring System (RMMS) and NV, January 28-30, 1986, Proceedings . New York, Institute of Maintenance Control Center (MCC) programs (hereafter referred Electrical and Electronics Engineers, Inc., 1986, p. 427-432. refs to as the FAA’s MAS in this paper) that are being implemented Low cost methodologies for accurately evaluating designs, as part of the FAA’s modernization of its maintenance operations. predicting reliability, and comparing maintenance strategies are Author critical to the optimization of cost-effective design, production, and support policy decisions. Both the government and contractor require effective prediction tools to monitor and compare A87-15428 performance at the beginning phases of a program. This ensures BUILT-IN-TEST FOR FAIL-SAFE DESIGN maximum RMA growth during later design, test, and production D. E. HARRIS (Westinghouse Electric Corp., Baltimore, MD) IN: phases. The ideal tool needs to accurately represent the system, 1986 Annual Reliability and Maintainability Symposium. Las Vegas, incorporating the necessary resolution to the component level, NV, January 28-30, 1986, Proceedings . New York, Institute of thus allowing sensitivity analysis and low-cost run repetitions to Electrical and Electronics Engineers, Inc., 1986, p. 361-366. evaluate design trade-offs. This paper presents a procedure for Several analytical design approaches are examined for their the general development and solution of complex problems using effectiveness in producing components with mean-time-between- Markov models. Practical application of these techniques is made hazards (catastrophicfailure) of 100,000 hr or more. Attention is given with three case studies. These studies demonstrate the application to systems (such as aircraft) with identical control circuits and across- to complex architectures common in today’s highly reliable compare capability, and to equipment with all available control con- operational configurations. Author

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A87-15482 optimizer is used in POSTOP although other options such as those PRELIMINARY DESIGN OF ELECTROMECHANICAL in the ADS system could be substituted with relative ease. The SERVOSYSTEMS basic elements of POSTOP are shown. Some of these elements S. A. ROWE (AiResearch Manufacturing Co., Torrance, CA) IN: and usage of the program are described. Author Advanced actuation, controls and integration for aerospace vehicles; Proceedings of the Symposium, San Diego, CA, October 9, 1985 . Warrendale, PA, Society of Automotive Engineers, Inc., N87-11910# Texas ABM Univ., College Station. Texas 1986, p. 57-68. refs Transportation Inst. (SAE PAPER 851759) CRITERIA FOR ASPHALT-RUBBER CONCRETE IN CIVIL The preliminary design of electromechanical (EM) servosystems AIRPORT PAVEMENTS MIXTURE DESIGN Final Report, Sep. is a complex engineering problem due to the numerous parameters, 1983 - Aug. 1986 constraints, and performance requirements which must be satisfied. F. L. ROBERTS, R. L. LYTTON, and D. HOYT Jul. 1986 74 p When this is coupled with optimization, the task becomes even (Contract DTFAOl-83-C-30076) more difficult. This paper discusses: (1) the variables that must (DOT/FAA/PM-86/39) Avail: NTlS HC A04/MF A01 be considered in the design phase of an EM servosystem, (2) the A mixture design procedure is developed to allow the use of main constraints that must be addressed during preliminary design, asphalt-rubber binders in concrete for flexible airport pavement. and (3) a reasonable strategy for designing and optimizing an EM The asphalt-rubber is produced by reacting asphalt with ground, servosystem. Also, a computer program developed by AiResearch scrap tire rubber to produce the binder for the asphalt-rubber for the preliminary design of EM servosystems (EMSYS) and concrete. Procedures for laboratory preparation of alsphalt-rubber methods used by EMSYS to address the above are briefly binders using an equipment setup that was found by researchers described. Author to produce laboratory binders with similar properties to field processes are included. The rubber-asphalt concrete mixture design A87-16 160 procedure includes adjustments to the aggregate gradation to permit space for the rubber particles in the asphalt-rubber binder SOME EFFECTS OF MOISTURE ON ADHESIVE-BONDED CFRP-CFRP JOINTS as well as suggested mixing and compaction temperatures, and B. M. PARKER (Royal Aircraft Establishment, Materials and compaction efforts. While the procedure was used in the laboratory Structures Dept., Farnborough, England) (Imperial College of to successfully produce asphalt-rubber concrete mixtures, it should Science and Technology and Ciba-Geigy Plastics, International be evaluated in the field to ensure that consistent results can be Symposium on Joining and Repair of Fibre-Reinforced Plastics, achieved in a production environment. Author London, England, Sept. 10, 11, 1986) Composite Structures (ISSN 0263-8223), vol. 6, no. 1-3, 1986, p. 123-139. refs N87-11992# ESDU International Ltd.. London (England). Investigations have been carried out into the effect of long-term VERTICAL DEFLECTION CHARACTERISTICS OF AIRCRAFT exposure to a hot, humid environment on the strength and mode TYRES of failure of CFRP-CFRP joints bonded with structural epoxy May 1986 6 p adhesives. Strengths of joints have been shown to be reduced (ESDU-86005; ISBN-0-85679-557-7; ISSN-0141-4054) Avail: Seth by abserp!ien n! mnistgre and by increased test temperature. ESD!! There is some evidence that, with certain adhesives, the This Data Item ESDU 86005 is an addition to the Aircraft composite-adhesive interface may be weakened at long exposure Performance Sub-series. The characteristics are given for times. Investigations have also been made into the effect of aircraft-type cross-ply tires under load normal to the runway moisture in the composite on subsequent bonding with epoxy surfaces. Equations for tire deflection are primarily for establishing adhesives, with reference to the repair of composite components. aircraft pitch attitude on the ground. Equations for footprint It has been shown that considerable drying may be required to dimensions and areas are required in calculations related to tire obtain good bonds with some 120 C-cured adhesives. The 175 behavior on wet or flooded runways. The equations are found to C-cured adhesive tested was less susceptible. Author represent load-deflection characteristics and contact area length well and some data were verified for speeds up to 100 knots. N87-11733’# Lockheed-Georgia Co., Marietta. ESDU SIZING-STIFFENED COMPOSITE PANELS LOADED IN THE POSTBUCKLING RANGE S. 8. BIGGERS and J. N. DICKSON In NASA. Langley Research N87-11993’# National Aeronautics and Space Administration. Center Recent Experiences in Multidisciplinary Analysis and Lewis Research Center, Cleveland, Ohio. Optimization, Part 1 15 p 1984 SELECTION OF ROLLING-ELEMENT BEARING STEELS FOR Avail: NTlS HC A22/MF A01 CSCL 20K LONG-LIFE APPLICATION Stiffened panels are widely used in aircraft structures such as E. V. ZARETSKY 1986 76 p Presented at International wing covers, fuselages, control surfaces, spar webs, bulkheads, Symposium on the Effect of Steel Manufacturing Processes on and floors. The detailed sizing of minimum-weight stiffened panels the Quality of Bearing Steels, Phoenix, Ariz., 4-6 Nov. 1986; involves many considerations. Use of composite materials sponsored by American Society for Testing and Materials introduces additional complexities. Many potential modes of failure (NASA-TM-88881; E-3288; NAS 1.15:88881) Avail: NTlS HC exist. Analyses for these modes are often not trivial, especially AOWMF A01 CSCL 131 for those involving large out-of-plane displacements. Accurate Nearly four decades of research in bearing steel metallurgy analyses of all potential failure modes are essential. Numerous and processing have resulted in improvements in bearing life by a practical constraints arise from manufacturing/cost considerations factor of 100 over that obtained in the early 1940’s. For critical and from damage tolerance, durability, and stiffness requirements. applications such as aircraft, these improvements have resulted The number of design variables can be large when lamina in longer lived, more reliable commercial aircraft engines. Material thicknesses and stacking sequence are being optimized. A factors such as hardness, retained austenite, grain size and carbide significant burden is placed on the sizing code due to the complex size, number, and area can influence rolling-element fatigue life. analyses, practical constraints, and number of design variables. Bearing steel processing such as double vacuum melting can have On the other hand, sizing weight-efficient panels without the aid a greater efect on bearing life than material chemistry. The selection of an automated procedure is almost out of the question. The and specification of a bearing steel is dependent on the integration sizing code postbuckled Open-Stiffener Optimum Panels (POSTOP) of all these considerations into the bearing design and application. has been developed to aid in the design of minimum-weight panels The paper reviews rolling-element fatigue data and analysis which subject to the considerations mentioned above. Developed for can enable the engineer or metallurgist to select a rolling-element postbuckled composite panels, POSTOP may be used for buckling bearing steel for critical applications where long life is required. resistant panels and metallic panels as well. The COPES/CONMIN Author

129 N87-11995*# General Motors Corp., Indianapolis, Ind. Gas projected 33.1 % and 36.3% savings, respectively, over an Trubine Div. equivalent 3000 psi system. A study of simulator operating ADVANCED GAS TURBINE (AGT) TECHNOLOGY PROJECT experience indicated a 23% improvement in reliability over a Final Annual Report, 1985 comparable 3000 psi system. An additional 600 hours of simulator 1 Sep. 1986 160 p endurance cycling are scheduled for completion in FY '86. GRA (Contract DEN3-168) (NASA-CR-179484; DOE/NASA/O168-10; NAS 1.26:179484; EDR-12344) Avail: NTlS HC AOWMF A01 CSCL 21A Engine testing, ceramic component fabrication and evaluation, component performance rig testing, and analytical studies N87-12729# Princeton Univ., N. J. Dept. of Mechanical and comprised AGT 100 activities during the 1985 year. Ten Aerospace Engineering. experimental assemblies (builds) were evaluated using two engines. A TEST ON THE RELIABILITY AND PERFORMANCE OF THE Accrued operating time was 120 hr of burning and 170 hr total, VERBEX SERIES 4000 VOICE RECOGNIZER bringing cumulative total operating time to 395 hr, all devoid of P. SUNTHARALINGAM Sep. 1985 21 p major failures. Tests identified the generator seals as the primary (Contract DAAG29-84-K-0048) working fluid leakage sources. Power transfer clutch operation was (AD-A169066; MAE-1748; ARO-20155.6-MA) Avail: NTlS HC demonstrated. An alpha Sic gasifier rotor engine test resulted in AO2/MF A01 CSCL 17B blade tip failures. Recurring case vibration and shaft whip have Voice recognition systems are becoming increasingly limited gasifier shaft speeds to 84%. Ceramic components widespread as forms of data entry. One such use of speech input successfully engine tested now include the Sic scroll assembly, would be as an aid to pilot communication in the cockpit. The Si3N3 turbine rotor, combustor assembly, regenerator disk Verbex Series 4000 Voice Recognizer (WR) was chosen as the bulkhead, turbine vanes, piston rings, and couplings. A compressor input channel for a forthcoming flight simulation system. The VVR shroud design change to reduce heat recirculation back to the is a speaker dependent unit with the ability to recognize continuous inlet was executed. Ceramic components activity continues to focus speech. An additional feature of the WR is its use of structured on the development of state-of-the-art material strength grammars in defining the speech format. Tests were run to characteristics in full-scale engine hardware. Fiber reinforced determine the WR's reliability, and also to investigate the variations glass-ceramic composite turbine (inner) backplates were fabricated in performance for different grammar structures. Author (GRA) by Corning Glass Works. The BMAS/III material performed well in engine testing. Backplates of MAS material have not been engine tested. Author

N87-12017*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. N87-12766# Energy Research Corp., Danbury, Conn. CONCENTRATED MASS EFFECTS ON THE FLUlTER OF A AIRCRAFT BATTERY STATE OF CHARGE AND CHARGE COMPOSITE ADVANCED TURBOPROP MODEL CONTROL SYSTEM Interim Report, 1 Jul. 1984 - 30 Jun. 1985 J. K. RAMSEY and K. R. V. KAZA Oct. 1986 22 p S. VISWANATHAN and A. CHARKEY Feb. 1986 60 p (NASA-TM-88854; E-3247; NAS 1.15:88854) Avail: NTlS HC (Contract F33615-83-(2-2435) AO2/MF A01 CSCL 20K (AD-A16941 1; AFWAL-TR-85-2104) Avail: NTlS HC A04/MF The effects on bending-torsion flutter due to the addition of a A01 CSCL 1OB concentrated mass to an advanced turboprop model blade with This Interim Report describes work done in developing an rigid hub are studied. Specifically the effects of the magnitude aircraft battery state of charge and charge control system. The and location of added mass on the natural frequencies, mode basis for this system developed by ERC is a nickel-oxygen (Ni02) shapes, critical interblade phase angle, and flutter Mach number Pilot cell (0.374 Ah). This pilot cell is cycled in tandem with a are analytically investigated. The flutter of a propfan model is nickel-cadmium battery. The oxygen pressure of the pilot cell is shown to be sensitive to the change in mass distribution. Static utilized to determine and control the state of charge of the unbalance effects, like those for fixed wings, were shown to occur nickel-cadmium battery. The Ni02 pilot cell baseline performance as the concentrated mass was moved from the leading edge to was determined during this period. The effect of using different the trailing edge with the exception of one mass location. Mass nickel electrodes (ERC, SAFT, MARATHON) was also performed. balancing is also inferred to be a feasible method for increasing GRA the flutter speed. Author

N87-12711# Rockwell International Corp., Columbus, Ohio. North American Aircraft Operations. FABRICATION AND TESTING OF LIGHTWEIGHT HYDRAULIC N87-12768# Department of the Air Force, Washington, D.C. SYSTEM SIMULATOR HARDWARE Final Report, 15 May 1980 CRYOGENIC WOUND ROTOR FOR LIGHTWEIGHT, HIGH - 15 Nov. 1985 VOLTAGE GENERATORS Patent Application W. N. BICKEL and R. K. HANING Jan. 1986 279 p C. E. OBERLY, inventor (to Air Force) 23 Apr. 1986 28 p (Contract N62269-80-(2-0261) (AD-DO12370; US-PATENT-APPL-SN-855047) Avail: NTlS HC (AD-A169884; NA-85-0134; NADC-79024-60) Avail: NTlS HC AO3/MF A01 CSCL 1OB A13/MF A01 CSCL 13G Liquid hydrogen is used to completely cool all elements of the The Lightweight Hydraulic System (LHS) Advanced generator including bearings, stator conductor, rotor conductor, Development Program is a multi-phase investigation of the concept magnetic flux shield, and excitation mechanisms. By essentially of using an 8000 psi operating pressure level to achieve smaller immersing the generator in liquid hydrogen, cryogenic interface and lighter weight hydraulic components than those used in aircraft problems are minimized. The conductor windings will utilize pure with conventional 3000 psi systems. This report presents the results metals such as aluminum to minimize the weight and the ohmic of Phase II in which a full scale A-7E 8000 psi dual system hydraulic heat loss in the machine. Complication of liquid helium cooling for simulator was fabricated and tested. Tests conducted were proof superconducting windings and quench phenomena due to thermal pressure, system integration, baseline, dynamic performance, and instabilities in the superconductors are eliminated. The use of 600 hours of endurance cycling. No major technological problems extremely low resistance of liquid hydrogen cooled aluminum were encountered. Four flight control actuators accumulated over permits heat removal in the confined space of the rotor field winding 3,000,000 cycles; one pump accumulated over 1000 hours of at magnetic field and current density that can exceed that of operation (Phase I and Phase 11). Hydraulic system math models superconductors. Because iron is not required in the generator, were corroborated by test data. A weight and space analysis update very high voltages can be generated. GRA

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N87-12816# Dayton Univ., Ohio. Research Inst. N87-12869'# National Aeronautics and Space Administration. COMPUTATIONAL FLUID DYNAMIC STUDIES OF CERTAIN Ames Research Center, Moffett Field, Calif. DUCTED BLUFF-BODY FLOWFIELDS RELEVANT TO THE EVALUATION OF A NUMBER OF PROTOTYPES FOR THE TURBOJET COMBUSTORS. VOLUME 1: TIME-DEPENDENT FREE-TIP ROTOR CONSTANT-MOMENT CONTROLLER CALCULATIONS WITH THE K-EPSILON TURBULENCE MODEL L. A. YOUNG Feb. 1986 76 p FOR AN EXISTING CENTERBODY COMBUSTOR Final Report, (NASA-TM-86664; A-85059; NAS 1.1 5:86664) Avail: NTlS HC 16 Aug. 1984 - 30 Sep. 1985 A05/MF A01 CSCL 01C M. S. RAJU and L. KRISHNAMURTHY Jul. 1986 53 p The development of several prototypes of a constant moment (Contract F22615-84-(3-2411) controller, a critical component of the free-tip rotor (FTR) concept, (AD-A171 434: UDR-TR-85-82-VOL-1:AFWAL-TR-86-2004-VOL-1) is described. Also presented are the experimental results of a Avail: NTlS HC A04/MF A01 CSCL 218 whirl test designed to select a final controller configuration to be A numerical investigation of the near-wake region in a ducted included in a future wind-tunnel test of this innovative rotor system. bluff-body combustor by finite-difference computations is reported. A brief explanation of the FTR concept and its history are included. The numerical predictions are based upon the time-dependent, The paper documents the controller design constraints, each compressible Navier-Stokes equations and the k-epsilon turbulence prototype's operating principle, the evaluation test, and the model. The standard k-epsilon turbulence model was modified to individual prototype test results. A recommended design is account for the nonstationary terms. The time-dependent identified, along with the selection rationale. Author calculations predictions addressed the nonreacting near-wake flow field of the centerbody combustor with only the annular air stream N87-12881# Department of the Air Force, Washington, D.C. present. Flowfield predictions for a combustor inlet mass flow of IMPROVED VANE PLATFORM SEALING AND RETENTION 2 kg/s with the time-dependent formulation incorporating the MEANS Patent Application k-epsilon turbulence model show the attainment of a steady-state G. A. BONNER, inventor (to Air Force) 12 May 1986 16 p recirculating flow in the near wake. The slow axial migration of (AD-DO12407; US-PATENT-APPL-SN-861905) Avail: NTlS HC the recirculation vortex towards the exit boundary which was A02/MF A01 CSCL 11A noticed in the earlier time-dependent calculations without a This patent application describes improved vane platform turbulence model is not longer present. Present results have thus feather seal is disclosed for use in turbine engines. This feather eliminated the appearance of reverse flow at the exit boundary seal contains a flat, thin feather seal, which is attached by adhesive with the consequent incompatibility of the boundary conditions, to ease assembly to an L-shaped retainer plate to result in a and thereby the spu rious shedding-like behavior observed combined thickness of 0.032 inches. This new seal may be used previously. The steady-state results in the present study to replace the inner vane platform seals which are currently used demonstrate internal consistency with the time-averaged in F-100 turbine engines, which have a history of not bending measurements and predictions for the locations of the vortex center easily to conform to seal slots. The new seal provides improved and the centerline rear stagnation point. GRA platform sealing without loss of platform retention in the event of vane burn through. GRA

N87-12915'# Case Western Reserve Univ.. Cleveland, Ohio. Dep!. of Civil Engineering. N87-12830'# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. ANALYSIS OF MIXED-MODE CRACK PROPAGATION USING SUPPLEMENTARY CALIBRATION TEST OF THE THE BOUNDARY INTEGRAL METHOD Final Report TIP-AERODYNAMICS- AND ACOUSTICS-TEST PRESSURE A. MENDELSON and L. J. GHOSN Sep. 1986 194 p TRANSDUCERS (Contract NAG3-396) (NASA-CR-179518; NAS 1.26:179518) Avail: NTlS HC AO9/MF M. WATTS Jul. 1986 44 p E. A01 CSCL20K (NASA-TM-88312; A-86273; NAS 1.15:88312) Avail: NTlS HC AOWMF A01 CSCL 148 Crack propagation in a rotating inner raceway of a high speed A calibration test is described that was performed to supplement roller bearing is analyzed using the boundary integral equation the normal calibration of the 188 pressure transducers used in method. The method consists of an edge crack in a plate under the Tip Aerodynamics and Acoustics Test. This calibration led to tension, upon which varying Hertzian stress fields are the identification of 15 transducers which had a slope change of superimposed. A computer program for the boundary integral greater than 7% from the initial calibration. The calibration equation method was written using quadratic elements to determine procedure is described and the results presented. The effect of the stress and displacement fields for discrete roller positions. the slope changes on the pressure distributions are described, Mode I and Mode II stress intensity factors and crack extension followed by a method to compensate for these changes., Author forces G sub 00 (energy release rate due to tensile opening mode) and G sub r0 (energy release rate due to shear displacement mode) were computed. These calculations permit determination of that crack growth angle for which the change in the crack extension forces is maximum. The crack driving force was found N87-12868 ESDU International Ltd., London (England). to be the alternating mixed-mode loading that occurs with each FRICTIONAL AND RETARDING FORCES ON AIRCRAFT TYRES. passage of the most heavily loaded roller. The crack is predicted PART 4 ESTIMATION OF EFFECTS OF YAW to propagate in a step-like fashion alternating between radial and Sep. 1986 29 p inclined segments, and this pattern was observed experimentally. (ESDU-86016-PT-4; ISBN-0-85679-568-2 ISSN-0141-4054) The maximum changes DeltaG sub 00 and DeltaG sub r0 of the Avail: ESDU crack extension forces are found to be good measures of the Available as part of the ESDU Sub-series on Aircraft crack propagation rate and direction. Author Performance, this ESDU gives expressions and data for calculating the forces and moments acting on the tire-ground contact area N87-12924'# National Aeronautics and Space Administration. during unbraked and braked yawed rolling. The methods have Lewis Research Center, Cleveland, Ohio. been verified against experimental data drawn from a wide range A CONSTITUTIVE LAW FOR FINITE ELEMENT CONTACT of sources in the literature for speeds up to 100 knots, for a wide PROBLEMS WITH UNCLASSICAL FRICTION range of tire sizes, inflation pressures, vertical loads and runway M. E. PLESHA and B. M. STEINETZ Nov. 1986 19 p surface conditions. Applications include estimation of minimum (NASA-TM-88838; E-3181 ; NAS 1.15:88838; ICOMP-86-1) Avail: control speed on the ground and investigation of stopping NTlS HC AO2/MF A01 CSCL 20K performance with asymmetric reverse thrust and/or asymmetric Techniques for modeling complex, unclassical contact-friction braking and/or cross winds and/or low friction surface. ESDU problems arising in solid and structural mechanics are discussed.

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A constitutive modeling concept is employed whereby analytic 13 relations between increments of contact surface stress (Le., traction) and contact surface deformation (Le., relative displacement) are developed. Because of the incremental form of GEOSCIENCES these relations, they are valid for arbitrary load-deformation histories. The motivation for the development of such a constitutive Includes geosciences (general); earth resources and remote law is that more realistic friction idealizations can be implemented sensing; energy production and conversion; environment pollution; in finite element analysis software in a consistent, straightforward geophysics; meteorology and climatology; and oceanography. manner. Of particular interest is modeling of two-body (i.e., unlubricated) metal-metal, ceramic-ceramic, and metal-ceramic contact. Interfaces involving ceramics are of engineering A87-13584 importance and are being considered for advanced turbine engines IMPACT OF AVIATION ON THE ENVIRONMENT in which higher temperature materials offer potential for higher S. NEEL (Texas, University, San Antonio) IN: Fundamentals of engine fuel efficiency. Author aerospace medicine . Philadelphia, PA, Lea and Febiger, 1985, p. 941-957. refs The ways in which the aviation industry has a negative impact on the environment are summarized, along with possible ameliorative action. Attention is given to potential and proven adverse effects of aircraft and airport noise, RF emissions, atmospheric contaminations, contrails, ozone depletion, and Shuttle launches. Noise is identified as the major pollutant, and several joint industry-airport-communityefforts to lessen the effects of noise N87-12939# Fairchild Republic Co.. Farmingdale, N.Y. pollution are described. M.S.K. ASSESSMENT OF DAMAGE TOLERANCE REQUIREMENTSAND ANALYSES A USERS MANUAL FOR CRACK GROWTH AND A87-15002# CRACK INITIATION ANALYSIS DAMGRO Final Report, Sep. A REVIEW OF AEROSPACE AND GROUND LIGHTNING 1982 - May 1986 THREAT CHARACTERISTICS AND APPLICATIONS M. LEVY and A. KUO 31 May 1986 142 p P. L. RUSTAN, JR. (USAF, Wright Aeronautical Laboratory, (Contract F33615-82-C-3215) Wright-Patterson AFB, OH) IN: International Aerospace and (AD-A171 209; AFWAL-TR-86-3028) Avail: NTlS HC A07/MF Ground Conference on Lightning and Static Electricity, 11th, A01 CSCLOlC Dayton, OH, June 24-26, 1986, Technical Papers . Fairborn, OH, A structural test program of typical aircraft structural National Interagency Coordination Group, 1986, p. 1-1 to 1-8. configurations was conducted to assess the current Air Force refs damage tolerance design requirements defined in MIL-A-83444. A development history and a comprehensive evaluation are The specimens, made of 2024-T3XX and 7075-T6XX, were presented for research in the fields of ground and aerospace subjected to randomized flight-by-flight spectra, representative of lightning strike protection and lightning strike threat fighterltrainer and bomber/cargo type loading spectra, respectively, characterization. Attention is given to the results obtained to date and to a constant amplitude loading spectrum. A total of by research programs conducted with the NASA F-106 and FAA two-hundred fifty-six specimens were tested. The test results were CV-580 aircraft. It is noted that successful simulations of aircraft correlated with analytical predictions using crack growth and crack strike data have been demonstrated for the cases of crowbarred initiation methods. As a result of this study, recommendation is switching, peaking capacitor, and UV laser methods, all of which provided to the validity of MIL-A-83444, to develop guidelines for yield currents with high rates-of-rise. O.C. selection of critical crack locations, and to assess the state-of-the art analytical capabilities in predicting crack growth and crack N87-12082'# South Dakota School of Mines and Technology, initiation time. This report presents the user's manual of the Rapid City. Inst. of Atmospheric Sciences. computer program DAMGRO. This program has been developed ATMOSPHERIC ELECTRICAL MODELING IN SUPPORT OF THE in conjunction with this contract, and used to predict the crack NASA F106 STORM HAZARDS PROJECT Annual Report, 15 growth and crack initiation of the structural test specimens. Mar. 1984 - 14 Mar. 1986 Author (GRA) J. H. HELSDON Sep. 1986 40 p (Contract NAG1-463) (NASA-CR-179801; NAS 1.26:179801; SDSMT/IAS/R-86/07) Avail: NTIS HC A03/MF A01 CSCL 048 With the use of composite (nonmetallic) and microelectronics becoming more prevalent in the construction of both military and commercial aircraft, the control systems have become more susceptible to damage or failure from electromagnetic transients. One source of such transients is the lightning discharge. In order N87-13149# AEG-Telefunken, Ulm (West Germany). Abteilung to study the effects of the lightning discharge on the vital H14E27. components of an aircraft, NASA Langley Research Center has OBSTACLE-WARNING RADAR FOR HELICOPTERS [DAS undertaken a Storm Hazards Program in which a specially HINDERNISWARN-RADAR FUER HUBSCHRAUBER - ElNE instrumented F106B jet aircraft is flown into active thunderstorms ANTHROPOTECHNISCHE PROBLEMSTELLUNG] with the intention of being struck by lightning. One of the specific G. M. OCH In DGLR Proceedings of a Symposium on the purposes of the program is to quantify the environmental conditions Evaluation of Man-Machine Systems: Methods and Problems p which are conductive to aircraft lightning strikes. Author 25-33 1985 In GERMAN Avail: NTlS HC Al3/MF A01 N87-13064'# Mississippi Univ., University. An obstacle warning radar concept for helicopters is described MOBILE INTERCEPT OF STORMS in both the test and operational phases. A radar sonde is mounted R. T. ARNOLD In NASA. Marshall Space Flight Center on the front of the helicopter under a radome and senses the NASAIMSFC FY-85 Atmospheric Processes Research Review 2 atmosphere forward over a range of 180 deg azimuth and 32 deg p Oct. 1985 elevation. The ray is directed by a fast-rotating mirror, resulting in Avail: NTlS HC A07/MF A01 CSCL 048 an image-renewal rate of two per second. Obstacles can be The primary goal was to acquire lightning data to serve as detected to a distance of 800 m. depending on atmospheric ground truth for U2 overflights. Researchers were successful in conditions and obstacle size. ESA instrumenting the Univ. of Mississippi/National Severe Storms Lab.

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(UMINSSL) mobile laboratory and in coordinating storm intercept N87-13110# Air Force Inst. of Tech., Wright-Patterson AFB, through communication to the U2 provided by airplane guidance Ohio. at NSSL and through direct communication with the U2 pilot from A REVIEW OF MICROBURSTS AND THEIR ANALYSIS AND a portable transceiver in the mobile lab. A demonstration showed DETECTION WITH DOPPLER RADAR M.S. Thesis that a mobile laboratory can be directed within a large geographical G. L. FREEMAN 1986 75 p area and used to collect ground truth data for comparison with (AD-A170458; AFIT/CI/NR-86-98T) Avail: NTlS HC A04/MF airborne data on a routine basis with proper utilization of forecasts, A01 CSCLO4B nowcasts, and communication among all participants. After the Microbursts are small downbursts, less than 4km in outflow U2 flights, researchers turned their attention solely to intercepting size, with peak winds lasting only 2 to 5 minutes. They can be severe storms within the area of Oklahoma with good Doppler classified as either midair or surface microbursts and also either radar coverage. They incorporated a second vehicle, which followed wet or dry microbursts. All microbursts are characterized by a the mobile lab and from which they released instrumented balloons. vertical downrush of air with a divergent outflow at its base. The This project utilized a standard meteorological rawinsonde and a parent clouds associated with microbursts are: Cumulonimbus; balloon-borne electric field meter. They were successful in flying, Towering Cumulus; and Anvil Cirrus. Most origin theories credit tracking, and receiving data from mobily launched balloons on thermodynamic factors with microburst creation. Wolfson (1983) several days. Researchers believe that they have demonstrated contends that microbursts result from dynamically induced vertical the ability to obtain meteorological and electrical data in severe pressure gradients that are intrinsic characteristics of strong storms using instrumented balloons. This also includes the mesocyclone circulation. Doppler radar is the primary tool for capability to launch into the mesocyclone region and for multiple detecting and observing microbursts. Wind field mapping is launches in the same storm. Author accomplished by either a single, dual or triple radar configuration. Single radar analysis methods require the most external assumptions but are the least expensive. Multiple radar techniques provide more accuracy but are more costly. Wilson and Roberts (1983) propose a number of alternatives for realtime operational N87-13099# Federal Aviation Administration, Atlantic City, N.J. detection of microbursts in an airport environment. Of these Technical Center. alternatives they chose a single radar, on airport configuration as THE SITING, INSTALLATION AND OPERATIONAL SUITABILITY the optimum choice when considering economic feasibility as well OF THE AUTOMATED WEATHER OBSERVING SYSTEM (AWOS) as technical performance. Author (GRA) AT HELIPORTS Final Report, Feb. 1985- Apr. 1986 R. A. MATOS, J. R. SACKETT, P. M. SHUSTER, and R. M. WElSS Aug. 1986 70 p (DOT/FAA/PM-86/30; DOT/FAA/CT-85/9) Avail: NTlS HC A04/MF A01 The Federal Aviation Administration (FAA) Technical Center MATHEMATICAL AND COMPUTER SCIENCES was tasked to site, install, and evaluate an Automated Weather Observing System (AWOS) at a heliport. The conclusions of the Includes mathematical and computer sciences (general); computer nvq!ni!ion o! !he 4.WOS at the Technical Center’s Interim Concept operations and hardware; computer programming and software; Development Heliport are given. By using the AWOS equipment computer systems; cybernetics; numerical analysis; statistics and installed at the Interim Concept Development Heliport, in probability; systems analysis; and theoretical mathematics. conjunction with literature research, the following test objectives were addressed: (1) locations in the vicinity of the heliport in which helicopter operations could influence the environment A87-13200 causing transient AWOS sensor performance were identified; (2) BEYOND FTMP AND SIFT - ADVANCED FAULT-TOLERANT areas for sensor location near the heliport that provided the most COMPUTERS AS SUCCESSORS TO FTMP AND SIFT beneficial information to the pilot were identified; (3) optimal sensor K. N. LEVITT, P. M. MELLIAR-SMITH, and R. L. SCHWARTZ location in relationship to predominant approach and departure (SRI International, Menlo Park, CA) IN: The fault-tolerant paths was determined; (4) siting criteria and recommendations for multiprocessor computer . Park Ridge, NJ, Noyes Publications, AWOS equipment installation at heliports were developed; (5) the 1986, p. 733-782. Previously announced in STAR as NU-10769. operational suitability of the AWOS equipment for heliport refs installations was determined; and (6) additional maintenance Work into possible architectures for future flight control requirements for the AWOS as the result of heliport installation computer systems is described. Ada for Fault-Tolerant Systems, were identified. the NETS Network Error-Tolerant System architecture, and voting in asynchronous systems are covered. Author

A87-13301 1986 AMERICAN CONTROL CONFERENCE, 5TH, SEAlTLE, WA, N87-13105# Air Force Environmental Technical Applications JUNE 16-20, 1986, PROCEEDINGS. VOLUMES 1,2, & 3 Center, Scott AFB, 111. Conference sponsored by the American Automatic Control Council. I REVISED UNIFORM SUMMARY OF SURFACE WEATHER New York, Institute of Electrical and Electronics Engineers, 1986. I , OBSERVATIONS (RUSSWO). PARTS A-F ELLINGTON ANGB, Vol. 1, 678 p.; vol. 2, 757 p.; vol. 3, 807 p. For individual items TEXAS Data Summary Report, Jul. 1941 - Feb. 1986 see A87-13302 to A87-13460. I 21 May 1986 298 p Papers are presented on robustness and modeling issued in (AD-A169389; USAFETAC/DS-86/024) Avail: NTlS HC A1 3/MF process control, stochastic control, stability theory for adaptive A01 CSCLO4B control, robotics, artificial intelligence in process control, direct-drive 1 A six-part statistical data summary of surface weather robot arms, and estimation and tracking. Also considered are I observations for: Ellington ANGB FL. Summary consists of PART performance/robustness tradeoffs inc ontroller design, linear and I A, Weather Conditions and Atmospheric Phenomena; PART B, nonlinear systems, advances in model predictive control, simulation I Precipitation; PART C, Surface Winds; PART D, Ceiling and tools for control systems, control of flexible spacecraft, missile Visibility; PART E, Psychrometric Summaries; PART F, Pressure navigation, guidance and control, and aerospace and aircraft control I Summaries. See USAFETAWTN-83/001 (AD-A1321 86), An Aid applications. Other topics include real-time applications of parallel I for Using the Revised Uniform Summary of Surface Weather processing technology, identification, control in mechanical and Observations (RUSSWOs) for complete descriptions of contents optical systems, web handling, and reconfiguration strategies for j and instructions for use. Author (GRA) flight control systems. R.R. I 133 15 MATHEMATICAL AND COMPUTER SCIENCES

A87-133 19 A87-13365 METHODS FOR OBTAINING ROBUST TRACKING CONTROL MULTIVARIABLE HIGH-GAIN CONTROL WITH FEEDFORWARD LAWS COMPENSATION - A DESIGN TECHNIQUE W. E. SCHMITENDORF (Northwestern University, Evanston, IL) A. HEMAMI (Concordia University, Montreal, Canada) IN: 1986 IN: 1986 American Control Conference, 5th, SeatZle, WA, June American Control Conference, 5th. Seattle, WA, June 18-20,1986, 18-20,1986, Proceedings. Volume 1 . New York, Institute of Proceedings. Volume 2 . New York, Institute of Electrical and Electrical and Electronics Engineers, 1986, p. 21 2-216. refs Electronics Engineers, 1986, p. 751 -758. refs (Contract NSF ECS-84-15591;AF-AFOSR-ISSA-85-00051) State space analysis of linear time-invariant multivariable This paper treats the problem of determining a tracking control systems has been the subject of many researches in the past 2-3 law for linear systems with uncertain parameters. The tracking decades. Trying to find an analogy between single-input, control is robust in the sense that it achieves asymptotic tracking single-output and multiinput and multioutput systems, so that the of the command reference input for all admissible parameter values. successful classical methods can be applied to multivariable Based on the available theoretical results for determining tracking systems, is more recent. Each individual research contributes in controllers, numerical methods for obtaining the feedback gains part to find a better solution to the main, still not completely for a robust control law are presented. The efficacy of these solved, problem of designing a good controller for this class of methods is demonstrated by applying them to two aircraft systems. In this paper, results of several works on multivariable examples. Author systems are combined to give an easy to use design technique for robust high-gain controllers by output feedback, inner-loop feedback and feedforward. An illustrative example is included. A87-13326 Author REACHABLE OUTPUTS IN SYSTEMS WITH BOUNDED PARAMETER UNCERTAINTIES - APPLICATION TO FAILURE DETECTION A87-13385 D. T. HORAK and D. M. GOBLIRSCH (Bendix Aerospace EIGENSTRUCTURE ASSIGNMENT BY DYNAMIC OUTPUT Technology Center, Columbia, MD) IN: 1986 American Control FEEDBACK Conference, 5th, Seattle, WA, June 18-20, 1986. Proceedings. F. L. LEWIS (Georgia Institute of Technology, Atlanta), B. L. Volume 1 . New York, Institute of Electrical and Electronics STEVENS, R. S. KEMP, and R. D. MARSHALL (Lockheed-Georgia Engineers, 1986, p. 301-308. refs Co., Marietta) IN: 1986 American Control Conference, 5th, Seattle, A method for computing the intervals in which the outputs of WA, June 18-20,1986, Proceedings. Volume 2 . New York, Institute a linear multivariable dynamic system with bounded parameter of Electrical and Electronics Engineers, 1986, p. 963-969. refs uncertainties and noise must lie has been developed. It utilizes A design method is proposed for low order regulators which Pontryagin’s Maximum Principle and is recursive. Because of its assign desired closed-loop eigenvalues and eigenvectors. It is computational efficiency it can be executed in real time and used shown that, even if all poles are to be assigned, the regulator for system and sensor failure detection in systems with parameter may have degree less than that of a minimal order state observer. uncertainties. Failures are detected by testing if the measured Connections with the generalized dynamic cover problem are outputs lie outside the computed intervals, indicating that the pointed out, and a simple algorithm is given to solve that problem system cannot be described by the given model and the specified for the special case. An example of eigenstructure assignment parameter uncertainty bounds. The method is illustrated by with dynamic output feedback for a relaxed static stability (RSS) application to the longitudinal dynamics of the AFT1 F-16 aircraft. fighter aircraft completes this paper. Author Author A87-13399 EXTENSIONS OF A SIMPLIFIED CONTINUOUS-TIME A8743353 MULTIVARIABLE ADAPTIVE CONTROL ALGORITHM A DIRECT METHOD FOR ENFORCING EQUALITY I. BAR-KANA (Rafael Armament Development Authority, Haifa, CONSTRAINTS IN OPTIMAL OUTPUT FEEDBACK Israel) IN: 1986 American Control Conference, 5th, Seattle, WA, K. V. RAMAN (RCA, Astro-Electronics Div., Princeton, NJ) and A. June 18-20,1986, Proceedings. Volume 2 . New York, Institute of J. CALISE (Georgia Institute of Technology, Atlanta) IN: 1986 Electrical and Electronics Engineers, 1986, p. 1081 -1086. refs American Control Conference, 5th, Seattle, WA, June 18-20,1986, A simplified adaptive control algorithm was recently shown to Proceedings. Volume 1 . New York, Institute of Electrical and guarantee robustness with parasitic dynamics and disturbances. Electronics Engineers, 1986, p. 597-601. refs The algorithm uses parallel feedforward in order to satisfy This paper presents an algorithm that can be used to calculate necessary positive realness conditions. On the other hand, the optimal output feedback gains subject to a linear constraint on order of the plant and the pole excess may be very large and the gain matrix. This method is direct in that it does not rely on a unknown, while the model reference may be of a very low order. penalty function approach. The algorithm is proven to converge This paper presents an attempt to reduce the prior knowledge to a local minimum. As an application, the lateral dynamics of an needed for implementation of the adaptive algorithm. It is only L-1011 aircraft are considered both for static gain output feedback assumed that a necessary feedforward of a known order exists and dynamic compensator design. Author and the eigenvalues of this configuration are calculated adaptively. Although the stability analysis still presents some difficulties, the A87-13359 proposed algorithm seems to perform very well in difficult COMPUTATIONAL ENHANCEMENTS TO A 4D ALGORITHM environments, including nonminimum-phase plants with rapidly C. A. BUCKHAM (Boeing Commercial Airplane Co., Seattle, WA) changing parameters. Author IN: 1986 American Control Conference, 5th, Seattle, WA, June 18-20,1986, Proceedings. Volume 2 . New York, Institute of A87-13436 Electrical and Electronics Engineers, 1986, p. 676-680. SELECTION OF MEDIA ACCESS PROTOCOL FOR An implementation of a cost-optimal four-dimensional aircraft DISTRIBUTED DIGITAL AVIONICS trajectory computation algorithm was enhanced. The enhancements A. RAY (Pennsylvania State University, University Park) and J. were aimed at providing onboard capability, and included minimizing MCGOUGH (Bendix Corp., Flight Systems Div., Teterboro, NJ) execution time, and providing robustness and portability. The IN: 1986 American Control Conference, 5th. Seattle, WA, June techniques discussed include creating a favorable programming 18-20, 1986, Proceedings. Volume 3 . New York, Institute of environment, structuring code based on a data flow analysis, saving Electrical and Electronics Engineers, 1986, p. 1558-1562. refs intermediate results for reuse, and sticking to a standard The paper presents the results of an ongoing research project programming language. These techniques resulted in portable code where the objectives are to evaluate avionic network topologies which executes six times faster than the original. Some ideas for and media access protocols in view of the distributed digital flight further time reduction are presented. Author control systems (DDFCS) of high performance aircraft and to

134 15 MATHEMATICAL AND COMPUTER SCIENCES recommend a specific protocol for its prototype development. The A87-14682 selection of an appropriate protocol is critical for the stability of INTEGRATED ACTIVE CONTROL SYSTEMS: METHODS OF an aircraft because the DDFCS, in addition to the sampling time ALGORITHMIC INTEGRATION [INTEGRIROVANNYE SISTEMY delay, is subject to the transport delay due to media access and AKTIVNOGO UPRAVLENIIA METODY ALGORITMICHESKOI message transmission in the network. The MIL-STD-1553B and INTEGRATSII] SAE token ring protocols were analyzed and the analytical results I. S. UKOLOV, V. V. BEK, and A. R. MAKHLIN Moscow, have been verified by use of discrete event simulation Izdatel’stvo Nauka, 1986, 184 p. In Russian. refs techniques. Author Design principles and algorithmic support methods are developed in a general systems framework for integrated active control systems. Algorithms are obtained for the state estimation, parameter identification, and control of dynamic plants operating A87-13689 under significant nonlinear and nonstationary variations of the PARAMETER ESTIMATION AND IN-PLANE DISTORTION motion parameters. The proposed approach is applied to a number INVARIANT CHORD PROCESSING of problems involving the control of flight vehicles. B.J. D. CASASENT (Carnegie-Mellon University, Pittsburgh, PA) and W.-T. CHANG (Eastman Kodak Research Laboratory, Rochester, A87-14957 NY) IN: Intelligent robots and computer vision; Proceedings of the Fourth Meeting, Cambridge, MA, September 16-20, 1985 . IMPLEMENTATION OF CDFM GENERATOR CONTROL Bellingham, WA, Society of Photo-Optical Instrumentation T. H. ORTMEYER (Clarkson University, Potsdam, NY) and J. A. Engineers, 1985, p. 2-10. refs WEIMER (USAF, Aero Propulsion Laboratory, Wright-Patterson (Contract AF-AFOSR-84-0293) AFB, OH) IEEE Transactions on Aerospace and Electronic An attractive feature space (chord distributions) for pattern Systems (ISSN 0018-9251), vol. AES-22, July 1986, p. 349-355. recognition is discussed. New advancements presented are: (Contract F33615-81-C-2011) extensions to 3-D in-plane and out-of-plane distortion-invariant The control of a cascaded doubly fed machine (CDFM) to be object recognition; new techniques to allow estimation of in-plane used for aircraft power generation is investigated. The controller distortion parameters; and a new technique to achieve class employs a resistance simulator in the generator exciter to provide estimation in the presence of multiple distortions. Quantitative machine damping. Excitation is provided by a six step inverter fed results are provided for a ship data base (for out-of-plane from a controlled rectifier. Delays due to the dc link time constant distortions) and for an aircraft data base (for in-plane distortions). cause the resistance simulation to be nonideal. An investigation Author into the ability of resistance simulation to provide damping under these conditions is described. Author

A87-16176 A87-13703’ National Aeronautics and Space Administration. IDENTIFICATION AND SYSTEM PARAMETER ESTIMATION Ames Research Center, Moffett Field, Calif. 1985; PROCEEDINGS OF THE SEVENTH SYMPOSIUM, GRUNDY - PARALLEL PROCESSOR ARCHITECTURE MAKES UNIVERSITY OF YORK, ENGLAND, JULY 3-7, 1985. VOLUMES PROGRAMMING EASY 1&2 R. J. MEIER, JR. (NASA, Ames Research Center, Moffett Field, H. A. BARKER, ED. (Swansea, University College, Wales) and P. CA) IN: Intelligent robots and computer vision; Proceedings of C. YOUNG, ED. (Lancaster. University, England) Symposium the Fourth Meeting, Cambridge, MA, September 16-20, 1985 . organized by IEE; Sponsored by IFAC and International Federation Bellingham, WA, Society of Photo-Optical Instrumentation of Operational Research Societies. Oxford and New York, Engineers, 1985, p. 284-288. NASA-supported research. Pergamon Press (IFAC Proceedings Series, No. 7), 1985. Vol. 1, The hardware, software, and firmware of the parallel processor, 1171 p.; vol. 2, 891 p. For individual items see A87-16177 to Grundy, are examined. The Grundy processor uses a simple A87-16224. processor that has a totally orthogonal three-address instruction A collection of papers is presented covering identification and set. The system contains a relative and indirect processing mode system parameter estimation from many different areas of scientific to support the high-level language, and uses pseudoprocessors investigation, including control and system engineering, and read-only memory. The system supports high-level language environmental science and agriculture, biomedicine, aeronautics in which arbitrary degrees of algorithmic parallelism is expressed. and astronautics, statistics and time-series analysis, economics, The functions of the compiler and invocation frame are described. business forecasting, and education. A large number of the papers Grundy uses an operating system that can be accessed by an describe results of the latest research and development in arbitrary number of processes simultaneously, and the access time applications of identifications and system parameter estimation to grows only as the logarithm of the number of active processes. a wide variety of dynamic systems, including 54 papers on Applications for the parallel processor are discussed. I.F. self-adaptive and self-tuning control. Practical implementation of the techniques is also extensively addressed. C.D.

A87-14019# A87-16179 CAD AS A PREREQUISITE FOR COMPUTER-INTEGRATED PARAMETRIC IDENTIFICATION OF DISCONTINUOUS MANUFACTURING [CAD ALS VORAUSSETZUNG FUER DIE NONLlNEARlTlES COMPUTER-INTEGRIERTE FERTIGUNG] R. V. JATEGAONKAR (National Aeronautical Laboratory, J. NAGEL (Dornier GmbH, Friedrichshafen, West Germany) BMFT, Bangalore, India) IN: Identification and system parameter Statusseminar ueber Luftfahrtforschung und Luftfahrttechnologie, estimation 1985; Proceedings of the Seventh Symposium, York, Munich, West Germany, Apr. 28-30, 1986, Paper. 17 p. In England, July 3-7, 1985. Volume 1 . Oxford and New York, German. Pergamon Press, 1985, p. 167-172. refs Techniques for coordinating the CAD of aircraft components The present paper proposes a technique to identify systems with their fabrication by conventional NC machining and with discontinuous nonlinearities. A well-established maximum measurement tools are discussed. The relatively straightfornard likelihood estimation method has been suitably extended for this use of CADAM programs for sheet-metal components comprising purpose. The technique enjoys the desired properties of plane panels is contrasted with the difficulties of translating consistency, efficiency, and unbiased estimates associated with drawings of complex three-dimensional components into the maximum likelihood estimation. The estimation method has milling-machine instructions, combining parts lists with geometrical been illustrated using a second-order dynamic system which data, or specifying the layer and ply orientations of laminated incorporates specific nonlinear elements viz.: hysteresis and composites. Diagrams, drawings, photographs, and sample deadband plus saturation. Effects of additive noise on the printouts are included. T.K. parameter estimates have also been presented. Practical utility of

135 15 MATHEMATICAL AND COMPUTER SCIENCES

the technique has been demonstrated in identifying from flight to be selected and supplied by the user to meet his specific test data the discontinuous nonlinear effects in the control surface needs and preferences. The one exception to this is a fully stressed actuator system of an aircraft. Author design (FSD) based on simple scaling. The gradients are currently I supplied by various design sensitivity options now existing in A87-16189 MSC/NASTRAN's design sensitivity analysis (DSA). Author AN EFFICIENT DECISION-MAKING-FREE FILTER FOR PROCESSES WITH ABRUPT CHANGES N87-11754'# Kaman Aerospace Corp., Bloomfield, Conn. H. A. P. BLOM (Nationaal Lucht- en Ruimtevaartlaboratorium, REGRESSION ANALYSIS AS A DESIGN OPTIMIZATION TOOL Amsterdam, Netherlands) IN: Identification and system parameter R. PERLEY ln NASA. Langley Research Center Recent estimation 1985; Proceedings of the Seventh Symposium, York, Experiences in Multidisciplinary Analysis and Optimization, Part 2 England, July 3-7, 1985. Volume 1 . Oxford and New York, 15p 1984 Pergamon Press, 1985, p. 631-636. refs Avail: NTlS HC A22/MF A01 CSCL 12A The well known system of linear stochastic difference equations The optimization concepts are described in relation to an overall with Markovian coefficients has been generalized to cover design process as opposed to a detailed, part-design process processes which jump simultaneously with the coefficients. where the requirements are firmly stated, the optimization criteria Examples are given to illustrate the additional modeling potential are well established, and a design is known to be feasible. The of this generalized system for filtering partial observations of the overall design process starts with the stated requirements. Some generalized system, a new algorithm, called the Interacting Multiple of the design criteria are derived directly from the requirements, Model (IMM) algorithm, is given. It consists of a bank of N but others are affected by the design concept. It is these design interacting Kalman-like filters which cooperate with a filter for the criteria that define the performance index, or objective function, N state Markov process and is free of any decision making that is to be minimized within some constraints. In general, there I mechanism. Comparisons with other advanced algorithms for will be multiple objectives, some mutually exclusive, with no clear processes with abrupt changes show that the IMM algorithm statement of their relative importance. The optimization loop that performs very well at the cost of a relatively low computational is given adjusts the design variables and analyzes the resulting load. Due to the generalization the IMM algorithm is a serious design, in an iterative fashion, until the objective function is competitor of the well known decision directed filters for processes minimized within the constraints. This provides a solution, but it is with additive jumps. Author only the beginning. In effect, the problem definition evolves as information is derived from the results. It becomes a learning N87-11740'# National Aeronautics and Space Administration. process as we determine what the physics of the system can Langley Research Center, Hampton, Va. deliver in relation to the desirable system characteristics. As with MULTIDISCIPLINARY SYSTEMS OPTIMIZATION BY LINEAR any learning process, an interactive capability is a real attriubute DECOMPOSITION for investigating the many alternatives that will be suggested as J. SOBlESKl In its Recent Experiences in MultidisciplinaryAnalysis learning progresses. Author and Optimization, Part 1 24 p 1984 Avail: NTlS HC A22/MF A01 CSCL 128 N87-11755'# Kaman Aerospace Corp., Bloomfield, Conn. In a typical design process major decisions are made A ROTOR OPTIMIZATION USING REGRESSION ANALYSIS sequentially. An illustrated example is given for an aircraft design N. GIANSANTE In NASA. Langley Research Center Recent in which the aerodynamic shape is usually decided first, then the Experiences in Multidisciplinary Analysis and Optimization, Part 2 airframe is sized for strength and so forth. An analogous sequence 13 p 1984 could be laid out for any other major industrial product, for instance, Avail: NTlS HC A22/MF A01 CSCL 12A a ship. The loops in the discipline boxes symbolize iterative design The design and development of helicopter rotors is subject to improvements carried out within the confines of a single engineering the many design variables and their interactions that effect rotor discipline, or subsystem. The loops spanning several boxes depict operation. Until recently, selection of rotor design variables to multidisciplinary design improvement iterations. Omitted for achieve specified rotor operational qualities has been a costly, graphical simplicity is parallelism of the disciplinary subtasks. The time consuming, repetitive task. For the past several years, Kaman parallelism is important in order to develop a broad workfront Aerospace Corporation has successfully applied multiple linear necessary to shorten the design time. If all the intradisciplinary regression analysis, coupled with optimization and sensitivity and interdisciplinary iterations were carried out to convergence, procedures, in the analytical design of rotor systems. It is concluded the process could yield a numerically optimal design. However, it that approximating equations can be developed rapidly for a usually stops short of that because of time and money limitations. multiplicity of objective and constraint functions and optimizations This is especially true for the interdisciplinary iterations. Author can be performed in a rapid and cost effective manner; the number and/or range of design variables can be increased by expanding I N87-11748*# MacNeal-Schwendler Corp., Los Angeles, Calif. the data base and developing approximating functions to reflect DESIGN ENHANCEMENT TOOLS IN MSC/NASTRAN the expanded design space; the order of the approximating D. V. WALLERSTEIN In NASA. Langley Research Center Recent equations can be expanded easily to improve correlation between Experiences in Multidisciplinary Analysis and Optimization, Part 1 analyzer results and the approximating equations; gradients of the 22 p 1984 approximating equations can be calculated easily and these Avail: NTlS HC A22/MF A01 CSCL 09B gradients are smooth functions reducing the risk of numerical Design sensitivity is the calculation of derivatives of constraint problems in the optimization; the use of approximating functions functions with respect to design variables. While a knowledge of allows the problem to be started easily and rapidly from various these derivatives is useful in its own right, the derivatives are initial designs to enhance the probability of finding a global optimum; required in many efficient optimization methods. Constraint and the approximating equations are independent of the analysis derivatives are also required in some reanalysis methods. It is Or optimization codes used. Author shown where the sensitivity coefficients fit into the scheme of a basic organization of an optimization procedure. The analyzer is N87-11775*# Boeing Computer Services Co.,Seattle, Wash. to be taken as MSCINASTRAN. The terminator program monitors APPLYING OPTIMIZATION SOFTWARE LIBRARIES TO the termination criteria and ends the optimization procedure when ENGINEERING PROBLEMS the criteria are satisfied. This program can reside in several plances: M. J. HEALY ln NASA. Langley Research Center Recent in the optimizer itself, in a user written code, or as part of the Experiences in Multidisciplinary Analysis and Optimization, Part 2 MSUEOS (Engineering Operating System) MSCIEOS currently 21 p 1984 under development. Since several excellent optimization codes Avail: NTlS HC A22/MF A01 CSCL 09B exist and since they require such very specialized technical Nonlinear programming, preliminary design problems, knowledge, the optimizer under the new MSC/EOS is considered performance simulation problems trajectory optimization, flight

136 16 PHYSICS computer optimization, and linear least squares problems are in FORTRAN language, is described. This tool can be seen as an among the topics covered. The nonlinear programming applications environment to simulate the operation of all subsystems of the encountered in a large aerospace company are a real challenge simulated system, except one: the subsystem under test. The to those who provide mathematical software libraries and documentation of each subsystem is attached to it. Simulation consultation services. Typical applications include preliminary results are presented by means of tables and curves. The tool design studies, data fitting and filtering, jet engine simulations, was used in perfecting the flight simulator for the Empresa Brasileira control system analysis, and trajectory optimization and optimal de Aeronautica (EMBRAER) T-27 airplane, developed at the Centro control. Problem sizes range from single-variable unconstrained tecnico Aeroespacial - CTA (IPD-PEA). Accompanying the report minimization to constrained problems with highly nonlinear functions are printouts regarding the results of a simulation and and hundreds of variables. Most of the applications can be posed documentation for the atmosphere subsystem which is part of the as nonlinearly constrained minimization problems. Highly complex simulator described above. Author optimization problems with many variables were formulated in the early days of computing. At the time, many problems had to be reformulated or bypassed entirely, and solution methods often relied on problem-specific strategies. Problems with more than ten variables usually went unsolved. Author 16 N87-12265'# Virginia Univ., Charlottesville. Dept. of Computer Science. THE IMPLEMENTATION AND USE OF ADA ON DISTRIBUTED PHYSICS SYSTEMS WITH HIGH RELIABILITY REQUIREMENTS Semiannual Progress Report, 5 Mar. 1982 - 31 Dec. 1986 Includes physics (general); acoustics; atomic and molecular J. C. KNIGHT Aug. 1986 73 p physics; nuclear and high-energy physics; optics; plasma physics; (NASA-CR-179842; NAS 1.26:179842; UVA/528213/CS87/109) solid-state physics; and thermodynamics and statistical physics. Avail: NTlS HC A04/MF A01 CSCL 09B The general inadequacy of Ada for programming systems that must survive processor loss was shown. A solution to the problem A87-13585 was proposed in which there are no syntatic changes to Ada. AERO- AND HYDRO-ACOUSTICS; PROCEEDINGS OF THE The approach was evaluated using a full-scale, realistic application. SYMPOSIUM, ECOLE CENTRALE DE LYON, ECULLY, FRANCE, The application used was the Advanced Transport Operating JULY 3-6, 1985 System (ATOPS), an experimental computer control system G. COMTE-BELLOT, ED. (Lyon, Ecole Centrale, Ecully, France) developed for a modified Boeing 737 aircraft. The ATOPS system and J. E. FFOWCS WILLIAMS, ED. (Cambridge University, is a full authority, real-time avionics system providing a large variety England) Symposium sponsored by IUTAM, DRET, CNRS, et al. of advanced features. Methods of building fault tolerance into Berlin and New York, Springer-Verlag, 1986, 567 p. In English concurrent systems were explored. A set of criteria by which the and French. For individual items see A87-13586 to A87-13612. p;opoe& -n+k111-,1 A wi!! be judged WBB examined. Extensive Topics discussed include diffraction, active noise control, source interaction with personnel from Computer Sciences Corporation mechanisms, rotor noise, thermoacoustics, computational and NASA Langley occurred to determine the requirements of the acoustics, flow noise, the acoustics of unstable flows, and ATOPS software. Backward error recovery in concurrent systems flow-acoustic interaction. Particular attention is given to the was assessed. B.G. influence of airfoil mean loading on convected gust interaction noise; an experimental study of unsteady flow over a trailing edge; N87-12273'# National Aeronautics and Space Administration. acoustic pressure and intensity distributions in finite-length active Ames Research Center, Moffett Field, Calif. noise control systems; a comparison of two propeller source models RAPID PROTOTYPING FACILITY FOR FLIGHT RESEARCH IN for aircraft interior noise studies; and the acoustoelasticity of a ARTIFICIAL-INTELLIGENCE-BASED FLIGHT SYSTEMS panel backed by a rectangular cavity. Also considered are a wind CONCEPTS tunnel study of aeolian tones from rough-surface cylinders, E. L. DUKE, V. A. REGENIE, and D. A. DEETS Oct. 1986 19 wake-induced shear excitation in a basic annular jet, and the P response of a flat-plate turbulent boundary layer to intense sound (NASA-TM-88268; H-1367; NAS 1.1 5:88268) Avail: NTlS HC waves moving in the upstream direction. B.J. A02/MF A01 CSCL 09B The Dryden Flight Research Facility of the NASA Ames Research Facility of the NASA Ames Research Center is developing A87-13587' Arizona Univ., Tucson. a rapid prototyping facility for flight research in flight systems INFLUENCE OF AIRFOIL MEAN LOADING ON CONVECTED concepts that are based on artificial intelligence (AI). The facility GUST INTERACTION NOISE will include real-time high-fidelity aircraft simulators, conventional E. J. KERSCHEN and M. R. MYERS (Arizona, University, Tucson) and symbolic processors, and a high-performance research aircraft IN: Aero- and hydro-acoustics; Proceedings of the Symposium, specially modified to accept commands from the ground-based AI Ecully, France, July 3-6, 1985 . Berlin and New York, computers. This facility is being developed as part of the Springer-Verlag, 1986, p. 13-20. refs NASA-DARPA automated wingman program. This document (Contract NAG3-357) discusses the need for flight research and for a national flight A theoretical model is developed for the noise generated when research facility for the rapid prototyping of AI-based avionics a convected vortical or entropic gust encounters an airfoil at systems and the NASA response to those needs. Author nonzero angle of attack. The analysis is based on Rapid Distortion Theory. High frequency gusts, whose wavelengths are short N87-13179# lnstituto de Pesquisas Espaciais, Sao Jose dos compared to the airfoil chord, are considered. The noise generation Campos (Brazil). is shown to be concentrated near the airfoil leading edge. The TOOL TO DEVELOP REAL TIME SIMULATION SYSTEMS M.S. level of the generated noise is increased by airfoil mean loading, Thesis [FERRAMENTA PARA DESENVOLVIMENTO DE with the appropriate scaling parameter being the local leading SISTEMAS DE SIMULACAO EM TEMPO REAL] edge incidence angle. The trailing edge simply scatters the leading C. L. RUYBALDOSSANTOS Aug. 1986 196 p In PORTUGUESE; edge sound field, and here the mean loading effects scale on the ENGLISH summary airfoil total lift. Calculations are presented which illustrate that, at (INPE-3979-TDL1233) Avail: NTlS HC AO9/MF A01 high frequencies, moderate levels of airfoil steady loading can The development of a tool for testing and documenting the dramatically increase the noise produced by airfoil convected gust constituent subsystems of a real time simulation system, written interactions. Author

137 16 PHYSICS

A87-13593 A87-15582 THE ACTIVE MINIMIZATION OF HARMONIC ENCLOSED NONLINEAR ACOUSTICS - ACHIEVEMENTS, PROSPECTS, SOUND FIELDS PROBLEMS [NELINEINAIA AKUSTIKA - DOSTIZHENIIA, P. A. NELSON, A. R. D. CURTIS, and S.J. ELLIOTT (So,uthampton, PERSPEKTIVY, PROBLEMY] University, England) IN: Aero- and hydro-acoustics; Proceedings 0. V. RUDENKO (Moskovskii GosudarstvennyiUniversitet, MOSCOW, of the Symposium, Ecully, France, July 3-6, 1985 . Berlin and USSR) Priroda (ISSN 0032-874)0, July 1986, p. 16-26. In New York, Springer-Verlag, 1986, p. 87-92. refs Russian. refs The total time averaged acoustic potential energy in a steady The current state of theory and technology in nonlinear harmonic sound field can be expressed as a positive definite acoustics is examined with particular emphasis on the use of quadratic function of the complex strengths of a number of parametric antennas to detect nonlinear acoustic waves, techniques ’secondary sources’ of sound introduced into the enclosure. For a for controlling the interaction of acoustic waves, and analogies given number and location of secondary sources, there is a unique between nonlinear acoustics and nonlinear optics. Applications of set of complex source strengths which minimizes this potential nonlinear acoustics to nondestructive testing, noise control, aircraft energy. This analysis is applied to the case of a lightly damped noise, and hydroacoustics are mentioned. B.J. enclosure excited by a point primary source at a frequency well above the Schroeder large room frequency. It is demonstrated N87-12322’# Lockheed-CaliforniaCo., Burbank. that in this case, the maximum reduction that can be achieved in WINDOW ACOUSTIC STUDY FOR ADVANCED TURBOPROP the potential energy of the sound field is critically dependent on AIRCRAFT Flnal Report the relative locations of primary and secondary sources. Author R. A. PRYDZ and F. J. BALENA Aug. 1984 48 p (Contract NAS1-16441) (NASA-CR-172391; NAS 1.26:172391; LR-30727) Avail: NTIS HC A03/MF A01 CSCL 20A A87-13595 An acoustic analysis was performed to establish window designs NOISE OF HIGH SPEED SURFACES for advanced turboprop powered aircraft. The window transmission A. R. GEORGE (Cornell University, Ithaca, NY) IN: Aero- and loss requirements were based on A-weighted interior noise goals hydro-acoustics; Proceedings of the Symposium, Ecully, France, of 80 and 75 dBA. The analytical results showed that a triple July 3-6, 1985 . Berlin and New York, Springer-Verlag, 1986, p. pane window consisting of two glass outer panes and an inner 119-1 33. refs pane of acrylic would provide the required transmission loss and Aerodynamic noise radiated by surfaces moving with respect meet the sidewall space limits. Two window test articles were to the fluid are discussed. Particular attention is given to sonic fabricated for laboratory evaluation and verification of the predicted boom due to supersonic motion, rotor noise due to the acceleration transmission loss. Procedures for performing laboratory tests are of rotor volumes, steady forces and nonlinear effects, and noise presented. Author due to various unsteady force effects on rotors. The unsteady forces include effects from harmonically varying inflow, impulsive N87-12323*# Douglas Aircraft Co., Inc., Long Beach, Calif. blade-vortex interaction loading (including transonic effects), and LIGHTWEIGHT SIDEWALLS FOR AIRCRAFT INTERIOR NOISE broadband noise due to loading from inflow turbulence and CONTROL Final Report self-generated turbulence. The state-of-the-art of predicting noise D. N. MAY, K. J. PLOTKIN, R. G. SELDEN, and B. H. SHARP from practical configurations is considered. B.J. Feb. 1985 154 p (Contract NAS1-17263) (NASA-CR-172490; NAS 1.26:172490) Avail: NTlS HC A08/MF A01 CSCL20A A87-13605 A theoretical and experimental study was performed to devise EXPERIMENTAL INVESTIGATION OF NEAR AND FAR lightweight sidewalls for turboprop aircraft. Seven concepts for ACOUSTIC FIELD OF A SMALL TURBOJET new sidewalls were analyzed and tested for noise reduction using J. HAERTIG and C. JOHE (Saint-Louis, lnstitut Franco-Allemand flat panels of 1.2 m x 1.8 m (4 ft x 6 ft), some of which were de Recherches, France) IN: Aero- and hydro-acoustics; aircraft-type constructions and some of which were simpler, Proceedings of the Symposium, Ecully, France, July 3-6, 1985 . easier-to-construct panels to test the functioning of an acoustic Berlin and New York, Springer-Verlag, 1986, p. 41 1-417. principle. Aircraft-application sidewalls were then conceived for Experimental results concerning the near and far acoustic field each of the seven concepts, and were subjectively evaluated for of a small turbojet are presented. At idle speed (subsonic jet) the their ability to meet aircraft nonacoustic design requirements. As acoustic field of the engine is similar to the one of a strongly a result of the above, the following sidewall concepts were excited free jet model (tone noise with high azimuthal coherence). recommended for further investigation: a sidewall in which the At maximum speed (supersonic subcritical jet) tone noise is more interior cavity is vented to ceiling and underfloor areas; sidewalls or less covered by jet noise and the far field is similar to the one with wall-mounted resonators, one having a conventional trim panel of quiet jet model. Author and one a limp one; and a sidewall with a stiff outer wall and a limp trim panel. These sidewalls appear to promise lower weights than conventional sidewalls adjusted to meet similar acoustic requirements, and further development may prove them to be A87-15458* Brown Univ., Providence, R. I. practical. Author LARGE-SCALE COHERENT STRUCTURES IN FREE TURBULENT FLOWS AND THEIR AERODYNAMIC SOUND N87-12326# European Space Agency, Paris (France). J. T. C. LIU (Brown University, Providence, RI) IN: Recent ON SOUND PROPAGATION IN CENTRIFUGAL FAN CASINGS advances in aerodynamics . New York, Springer-Verlag. 1986, p. M. BARTENWERFER and T. GlKADl Dec. 1985 44 p Transl. 297-334. refs into ENGLISH from “Zur Schallausbreitung in Gehaeusen von (Contract NSF MEA-78-22127; NAG1-379) Radialventilatoren” (Berlin, West Germany) Original language After interpreting the observed physical features of large-scale document was announced at N86-16053 coherent structures in free shear flows on the basis of conservation (ESA-TT-957; DFVLR-FB-85-32; ETN-86-98244) Avail: NTlS HC principles, the role of such structures in sources of turbulent jet A03/MF A01; original German version avail. at DFVLR, Cologne, sound is discussed. It is found that the lower-frequency sound, West Germany DM 11 which comes from lower-frequency coherent structures peaking Sound propagation in radial fan hollow casings was studied further downstream, radiates preferentially nearer the jet axis; the for cylindrical and spiral-shaped casings of the same volume and peak radiation moves away from the jet axis as the frequency width. After measurement of the sound reflection through the increases. O.C. different casings a monopole or dipole sound source of reduced

138 17 SOCIAL SCIENCES expansion at the casing cut-off was introduced and the frequency 17 responses in the intake and outflow canals determined. The influence of casing geometry and the flow in the casing on the SOCIAL SCIENCES rejection level and on the system frequency responses was determined. The applicability of the one-mode approximation for description of the frequency responses was verified. Torsional Includes social sciences (general); administration and management; sound in the outflow canal can be reduced with a phase-variable documentation and information science; economics and cost sound source synchronous with the rotation frequency at the analysis; law, political science, and space policy; and urban cut-off. ESA technology and transportation.

A87-13636# PARAMETRIC SIZING OF AERIAL APPLICATION AIRPLANES N87-12327# lnstitut Franco-Allemand de Recherches, St. Louis BASED ON VARYING LEVELS OF TECHNOLOGY (France). A. SIGAL (Technion - Israel Institute of Technology, Haifa) and R. INTRODUCTION TO HELICOPTER NOISE [INTRODUCTION AU YOELI IN: Israel Annual Conference on Aviation and Astronautics, BRUIT DES HELICOPTERES] 27th, Haifa, Israel, February 27, 28, 1985, Collection of Papers . J. HAERTIG 7 Feb. 1984 25 p In FRENCH Haifa, Israel, Technion - Israel Institute of Technology, 1986, p. (ISL-NB-401/84; ETN-86-98405) Avail: NTlS HC A02/MF A01 1-6. refs Literature on the intensity and characteristics of the external A computer program was used to size current advanced noise produced by helicopters was reviewed. Several types of technology configurations to given payload and performance noise are described and illustrated by measurements and constraints. The configurations were compared mainly from a cost calculations. ESA point of view based on a simulation mission run by the program. The most dominant design parameter for agricultural aircraft is the wing aspect ratio. The incorporation of advanced technologies tended to reduce the size and weight of the aircraft and to improve the ratio of the payload/gross wt. Mission cost was only modestly N87-13252*# National Aeronautics and Space Administration. influenced, especially due to the reduction in aircraft size, which Lewis Research Center, Cleveland, Ohio. tended to increase the number of spray passes and thus have an CRUISE NOISE OF COUNTERROTATION PROPELLER AT adverse effect on total mission time. It is concluded that, as long ANGLE OF ATTACK IN WIND TUNNEL as the basis for comparison is mission cost only, there seems J. H. DllTMAR Oct. 1986 35 p little justification for the incorporation of advanced technologies in (NASA-TM-88869; E-3275; NAS 1.1 588869) Avail: NTlS HC agricultural-aircraft design. B.J. A03/MF A01 CSCL 20A The noise of a counterrotation propeller at angle of attack A87-14037# was measured in the NASA Lewis 8- by 6-Foot Supersonic Wind GENERAL AVIATION COST EFFECTIVENESS Tunnel at cruise conditions. Noise increases of as much as 4 dB R. E. ET!-!ER!NGTnN (Gates Leajet Cnrp, Wichita, KS) AIAA, were measured at positive angles of attack on the tunnel side General Aviation Technology Conference, Anaheim, CA, Sept. wall, which represented an airplane fuselage. These noise 29-Oct. 1, 1986. 8 p. increases could be minimized or eliminated by operating the (AIAA PAPER 86-2607) counterrotation propeller with the front propeller turning up-inboard. The General Aviation Industry has not recovered from the last This would require oppositely rotating propellers on opposite sides economic recession. This paper is an update of AIAA Paper of the airplane. Noise analyses at different bandwidths enabled 86-4029, 'General Aviation Cost Effectiveness', presented in the separate front- and rear-propeller tones, as well as the total Colorado Springs on October 15, 1985. This paper re-examines noise, at each harmonic to be determined. A simplified noise model the areas of cost effectiveness and model changes. Both cost was explored to show how the observed circumferential noise effectiveness and model changes play an important part in the patterns of the separate propeller tones might have occurred. The past history of general aviation growth. This paper examines these total noise pattern, which represented the sum of the front- and areas in greater depth and makes some recommendations for rear-propeller tones at a particular harmonic, showed trends that future recovery of aircraft sales. Author would be hard to interpret without the separate-tone results. Therefore it is important that counterrotation angle-of-attack noise N87-13352# Orlando Technology, Inc., Shalimar, Fla. data be taken in such a manner that the front- and rear-propeller TSAR (THEATER SIMULATION OF AIRBASE RESOURCES) tones can be separated. Author DATABASE DICTIONARY F-4E Flnal Report, 1 Aug. 1985 - 31 Jul. 1986 D. ROBINSON and C. GORNTO 28 Mar. 1986 257 p (AD-A169575) Avail: NTlS HC A12/MF A01 CSCL 058 A significant problem for analysts and simulation model users N87-13347# Air Force Systems Command, Wright-Patterson AFB, is the availability of complete documentation of input databases. Ohio. Foreign Technology Div. The Theater Simulation of Airbase Resources (TSAR) model is JOURNAL OF ENGINEERING THERMOPHYSICS (SELECTED no exception. This TSAR dictionary documents the F-4E database ARTICLES) by translating the database codes to their English equivalents, L. DUAN, B. DONG, Z. WANG, Y. GAO, and K. LI 24 Jun. 1986 presents graphic network models for the decision logic networks 51 p Transl. into ENGLISH from Gongcheng Rewuli Xuebao for aircraft repair tasks, and a cross-reference index to facilitate China), v. 3, no. 2, May 1982 p 123-130, 135-137, 183-189 its use by modelers and analysts. GRA (AD-A169452; FTD-ID(RS)T-0312-86) Avail: NTlS HC AO4/MF A01 CSCL 13G The Journal of Engineering Thermophysics, vo1.3, no.2, May 1982, contains articles on the following topics: Effect of Part Span Shroud on Performance of a Single Stage Compressor; Effect of the Rear Stage Casing Treatment on the Overall Performance of a Multistage Axial flow Compressor; Investigations on Performance of Swept Wing Aircraft; Cascade of Axial Flow Compressor; and Thermal Performance of Turbine Vane with Ceramic Coatings with Enhanced Cooling. GRA

139 SUBJECT INDEX

~ AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 217) March 1987

Typical Subject Index Listing

Integrated active control systems: Methods of Axisymmetric vortex lattice method applied to parachute AERODYNAMIC BALANCE algorithmic integration --- Russian book shapes Low speed rotary aerodynamics of F-18 configuration p 135 A87-14682 [AIAA PAPER 86-24561 p68 A87-13796 For 0 deg to 90 deg angle of attack Test results and Application of optimization techniques to the design of Aerodynamic characteristics and flow round cross analvsis a flutter suppression control law lor the DAST ARW-2 parachutes in steady motion INASA-CR-3608) o 15 N87-10836 p 115 N87-11736 [AIAA PAPER 86-24581 p 68 A87-13798 ACTUATION Theoretical studies of the ETW diffuser and of the Advanced actuation, controls and integration for second throat p 69 A87-14022 aerospace vehicles; Proceedings of the Symposium. San Wind-tunnel investigation of the OMAC canard Diego, CA. October 9, 1985 configuration I [SAE P-1701 p 112 A87-15476 [AIM PAPER 86-26081 p 69 A87-14038 Advanced digital optical control actuation for the NUMBER ADOCS Impact of airfoil profile on the supersonic aerodynamics [SAE PAPER 8517551 p 112 A87-15480 of delta wngs p 71 A87-14363 dgq Energy efficient actuation using variable displacement A study of the effect of surface roughness on the head hydraulic control resistance of an aircraft D 94 A87-14717 Using vibration spectrum charactensticsfor the flow-path The subject heading is a key to the subject content [SAE PAPER 8517571 p 112 A87-15481 ACTUATORS diagnostics of aircraft gas turbine engines of the document title used to provide The is a Optimal stochastic observers applied to hydraulic p 105 A87-15210 description of the subject matter When the title is actuation systems p 87 A87-13354 The induced aerodynamics of jet and fan powered V/STOL aircraft p 73 A87-15459 insufficiently descriptive of the document content Actuating system with digital signal converters and An experimental study of the aerodynamics of a NACA the title extension is added separated from the title fiber-optic control p 93 A87-14018 A redundant actuating system with servo valves of low 0012 airfoil with a simulated glaze ice accretion by three hyphens The (NASA or AIAA) accession hydraulic loss p 93 A87-14025 [NASA-CR-179897] p 75 N87-11701 number and the page number are included in each Reducing complexity in fly-by-wire flight control The 8 m x 6 m low speed wind tunnel at the Chinese Aerodynamic Research and Development Center entry to assist the user in locating the abstract in actuatom [SAE PAPER 8517521 p 112 A87-15477 [ AD-A1684481 p 119 N87-11803 the abstract section If applicable. a report number NASA rotor systems research aircraft: Fixed-wing A system Iwk at actuation concepts and alternatives configuration flight-test results is also included as an aid in identifying the for primary flight control [NASA-TM-86789] p 100 N87-12557 document Under any one subject heading. the [SAE PAPER 8517531 p 112 A87-15478 The handling qualities and flight characteristics of the accession numbers are arranged in sequence with Advanced flight control actuation systems and their Grumman design 698 simulated twin-engine tilt Nacelle the AIAA accession numbers appearing first interface with digital commands V/STOL aircraft [SAE PAPER 8517541 p 112 A87-15479 [ NASA-TM-867851 p 100 N87-12558 Fabrication and testing of lightweight hydraulic system AERODYNAMIC COEFFICIENTS simulator hardware Aerodynamic coefficients of a circular wing in steady [ AD-A1698841 p 130 N87-12711 subsonic flw p 67 A87-13653 ADA (PROGRAMMING LANGUAGE) Calculation of aerodynamic force cwfficients The implementation and use of Ada on distributed p 73 A87-15229 systems with high reliability requirements Determination of the regime coefficients in the local [ NASA-CR-1798421 p 137 N87-12265 theory of interaction from plate data p 74 A87-15561 ADAPTIVE CONTROL Parameter estimation of aircraft with fly-by-wire wntrol A Aircraft flutter suppression via adaptive LOG control systems p 113 A87-16186 p 109 A87-13344 Determination of nonlinear aerodynamic coefficients A-320 AIRCRAFT Extensions of a simplified continuous-time multivariable using the estimation-before-modelingmethods p 114 A87-16202 A320 - Flyby-wire airliner p 96 A87-16394 adaptive control algonthm p 134 A87-13399 Supplementary calibration test of the tipaerodynamics- ABSTRACTS Adaptive flutter suppression p 113 A87-16182 and acoustics-test pressure transducers FAA helicopterfheliport research, engineering, and Methods for assessing wall interference in the 2- by [NASA-TM-88312I p 131 N87-12830 development bibliography, 1964-1986 2-foot adaptive-wallwind tunnel AERODYNAMIC CONFIGURATIONS [ NASA-TM-882521 p 118 N87-11800 [FAA/PM-86/47] p 118 N87-11798 A review of the technical devekqment of Concorde ACCELERATION (PHYSICS) ADHESIVE BONDING p96 A87-16408 Acceleration to a steady state for the Euler equations Clarification of adhesive binding mechanisms of Forward-swept wing configuration designed for high p70 A87-14096 aluminum structural bonds in aircraft fabrication maneuverability by use of a transonic computational ACCELEROMETERS [MBB-UT-226-86] p 121 A87-13985 method Theoretical and experimental investigations of sensor Some effects of moisture on adhesive-bonded [ NASA-TP-26281 p 75 N87-11702 lwation for optimal aeroelastic system state estimation CFRP-CFRP joints p 129 A87-16160 Assessment of damage tolerance requirements and p 115 N87-11794 AEROACOUSTICS analyses: A user's manual for crack growth and crack ACCIDENT PREVENTION Aero- and hydro-acoustics; Proceedings of the initiation analysis: DAMGRO Impact severity and potential injury prevention in general Symposium. Ecole Centrale de Lyon. Ecully. France, July [AD-A171209] p 132 N87-12939 aviation accidents p 79 A87-13687 3-8. 1985 p 137 A87-13585 AERODYNAMIC DRAG Obstacle-warningradar for helicopters Analytical model for investigation of interior noise Draa and stabilitv.. imorovements of a sauare p 132 N87-13149 characteristics in aircraft with multiple propellers including parachute ACOUSTIC ATTENUATION synchrophasing p 94 A87-14925 [AIAA PAPER 86-2471 I p68 A87-13805 The active minimization of harmonic enclosed sound Large-scak coherent structures in tree turbulent flom Prooellarfbodv interacbn for thNSt and draa fields p 138 A87-13593 and their aerodynamic sound p 138 A87-15458 [ESDU-86017] . p 76 i87-12537 ACOUSTIC MEASUREMENT Length adjustable strut link with low aerodynamic drag Supplementary calibration test of the tip-aerodynamics- An analysis of blade vortex interaction aerodynamics and acoustics p 77 N87-12547 [AD-D0122791 D 77 N87-12543 and acoustics-test pressure transducers AERODYNAMIC FORCES AERODYNAMIC BALANCE [ NASA-TM-883121 p 131 N87-12830 An aerodynamic analysis and the subsequent motion The 8 m x 6 m low speed wind tunnel at the Chinese ACOUSTIC PROPERTIES of external store p 66 A87-13501 Aerodynamic Research and Development Center Window acoustic study for advanced turboprop aircraft Aerodynamic force calculations of an elliptical circulation [AD-AlW448] p 119 N87-11803 [NASA-CR-172391] p 138 N87-12322 control airfoil p71 A87-14360 Lightweight sidewalls for aircraft interior noise control AERODYNAMIC CHARACTERISTICS Lower-side normal force characteristics of delta wings [NASA-CR-172490] p 138 N87-12323 Turbulent buoyant flow and pressure variations around at supersonic speeds p 72 A87-14372 ACOUSTICS an aircraft luselage in a cross wind near the ground --- Calculation of aerodynamic force coefficients Nonlinear acoustics ~ Achievements. prowts. simulated fire in cabin p 78 A87-13187 p 73 A87-15229 problems p 138 A87-15582 Automatic variable reefing of parachutes by application The effect of a winglet on the spatial vortex of a slender ACTIVE CONTROL of inflation forces body at high angle of attack The active minimization of harmonic enclosed sound [AIM PAPER 8624341 p 79 A87-13784 IAD-Al699251 p 65 N87-12533 fields p 138 A87-13593 On the utilization of vortex methods for parachute A summary of the development of integral aerodynamic Redundant computer system for fly-by-wire controls aerodynamic predictions methods for the Computation of rotor wake interactions p 111 A87-14013 [AIAA PAPER 86.24551 p 68 A87-13795 [ AD-A1692541 p 77 N87-12545

A- 1 AERODYNAMIC HEATING SUBJECT INDEX

AERODYNAMIC HEATING The podfolio model of technological development in the Analysis of U.S. civil rotorcraftaccidents for development Determination of dynamic stresses in the heat-insulating aircraft industry Of improved design criteria p78 A87-13685 coatings of fliht vehicles during aerodynamic heating [ AD-A1708321 p66 N87-12534 Acquisition and use of data for crashworthiness p 72 A87-15223 AEROSPACE INDUSTRY improvements in U.S. Army aircraft p 78 A87-13686 AERODYNAMIC INTERFERENCE Impact of aviation on the environment Impact severity and potential injury prevention in general Special opportunities in helicopter aerodynamics p 132 A87-13584 aviation accidents p79 A87-13687 p 74 A87-15469 AEROS,PACE VEHICLES Aircraft accident reports: Brief format, US civil and Methods for assessing wall interference in the 2- by Advanced actuation. controls and integration for foreign aviation. issue number 5 of 1985 accidents 2-fwl adaptive-wall wind tunnel aerospace vehicles; Proceedings of the Symposium, San [PB86-916919] p83 N87-11710 [ NASA-TM-882521 p 118 N87-11800 Diego. CA. October 9. 1985 Aircraft accident/incident summary reports: Erie. An approximate method of estimating the aerodynamic [SAE P-1701 p 112 A87-15476 Pennsylvania, October 14, 1984; Albuquerque, New interference between two parallel bodies in a supersonic AEROSPACEPLANES Mexico. February 11, 1985 flow (axial force) Aerospace plane - Fact or fantasy? [PB86-910407] p 84 N87-12549 [BR-1002711 p 76 N87-12540 p 65 A87-16396 Aircraft accident report: Bar Harbor Airlines Flight 1808, AERODYNAMIC LOADS AFTERBURNING Beech BE-99. N3OOWP. Auburn-Lewiston Municipal Influence of airfoil mean loading on convected gust Closed loop control 01 an afterburning FlOO gas turbine Airport. Auburn, Maine, August 25. 1985 interaction noise p 137 A87-13587 engine p 103 A87-13323 [PB86-910408] p 84 N87-12550 Improved measurement of the dynamic loads acting on AGRICULTURALAIRCRAFT AIRCRAFT ACCIDENTS rotating parachutes Parametric sizing of aerial application airplanes based Turbulent buoyant flow and pressure variations around [AIAA PAPER 86-24731 p68 A87-13807 on varying levels of technology p 139 A87-13636 an aircraft fuselage in a cross wind near the ground ..- Introduction to aerodynamics derivitives, equations 01 AH44 HELICOPTER simulated fire in cabin p 78 A87-13187 motion and stability Multivanable flight control lor an attack helicopter Aircraft accident reports: Brief format, US civil and [ESDU-86021I p 76 N87-12536 p 109 A87-13379 foreign aviation. issue number 4 01 1985 accidents AERODYNAMIC NOISE Optimization process in helicopter design [ PB86-9169181 p 84 N87-11712 Noise of high speed surfaces p 138 A87-13595 p 98 N87-11726 Aircraft accident reports: Brief format, US civil and Noise and performance of a counter-rotation propeller AILERONS foreign aviation. issue number 3 of 1985 accidents p 105 A87-14366 A redundant actuating system with servo valves of low [ PB86-9169171 p 84 N87-11713 Large-scale coherent structures in free turbulent flows hydraulic loss p 93 A87-14025 Review of accident data: US general aviation calendar and their aerodynamic sound p 138 A87-15458 AIR BREATHING ENGINES year 1982 AERODYNAMIC STABILITY Prospective. characteristics and problems of the use [ PB86-2019101 p 84 N87-11714 Application of time-domain unsteady aerodynamics to of boron in different air augmented propulsion modes AIRCRAFT APPROACH SPACING rotary-wing aeroelasticity p 94 A87-14103 [IAF PAPER 86-191 I p 122 A87-15924 Sensitivity studies of 4D descent strategies in an The effect of random wind gusts on the stability of e AIR COOLING advanced metering environment p 88 A87-13361 parachute system p 72 A87-15216 Fabrication of cooled radial turbine rotor Runway incursions at controlled airports in the United Vortex flap technology: A stability and control [ NASA-CR-1795031 p 107 N87-11789 States assessment AIR FLOW [PB86-9170031 p84 N87-11711 [ NASA-CR-1724391 p 115 N87-11795 Performance and optimisation of an airblast nozzle - AIRCRAFT CARRIERS AERODYNAMIC STALLING Drop size distribution and volumelric air flow Simulator design and instructional features for carrier Stall margin indication --- aircraft accident prevention p 125 A87-13828 landing: A field transfer study [AIAA PAPER 86-25951 p 101 A87-14030 AIR NAVIGATION [AD-A1699621 p 119 N87-12573 Summary of NASA stalllspin research for general ION, National Technical Meeting. Long Beach, CA. AIRCRAFT CONFIGURATIONS aviation configurations January 21-23. 1986. Proceedings p 85 A87-13532 Exploratory wind-tunnel investigation of the stability and [AIAA PAPER 86-25971 p 111 A87-14032 MTFCS (multiple target formation flight control system) control characteristics of advanced general aviation AERODYNAMICS Formation position sensor trade-off analysis configurations Questions and problems in aerodynamics --- Russian p 110 A87-13536 [AIAA PAPER 86.25961 p 111 A87-14031 book p66 A87-13050 Weather safety aspects in future civil air navigation Experiences perlorming conceptual design optimization Aerodynamic Decelerator and Balloon Technology p 85 A87-13540 of transport aircraft p 97 N87-11723 Conference, 9th. Albuquerque. NM. October 7-9. 1986. Improving Loran coverage a1 minimum cost PIAS A program lor an iterative aeroelastic solution Technical Papers p 79 A87-13776 p 86 A87-13543 p 97 N87-11725 The use of mathematical models in aerodynamics Vhe Combining Loran and GPS - The best of both worlds Helicopter rotor blade aerodynamic optimization by W. Rupert Turnbull Lecture) p 72 A87-15189 p 86 A87-13544 mathematical programming p 99 N87-11753 Recent advances in aerodynamics p 73 A87-15451 Development and testing of new technologies for flight NASA rotor systems research aircraft: Fixed-wing Applications of CONMIN lowing design optimization with operation and safety p 86 A87-14004 configurationflight-test results vortex flow effect p 98 N87-11737 Tailoring a malor weapon environmental program --- for [ NASA-TM-867891 p 100 N87-12557 Aircraft configuration optimization including optimized Low Altilude Navigation and Targeting Infrared System for AIRCRAFT CONSTRUCTION MATERIALS flight profiles p 98 N87-11743 Night p 102 A87-15430 Advanced composites applications for the 6-1B bomber Aeroelastic-aerodynamic optimization of high speed Synthesis of devices for the optimal processing of pulsed - An overview p 87 A87-13101 helicopter-compound rotor p 99 N87-11758 radio signals in LORAN systems p 86 A87-15563 Use of filament winding in manufacturing high quality Analysis and verification of the icing scaling equations. Mobile communications, navigation and surveillance aerospace composite components p 123 A87-13164 Volume 1: Revision [IAF PAPER 86-3331 p 86 A87-16027 Testing of fiber-reinforced construction elements - [AD-A167976] p 85 N87-12551 AIR TRAFFIC CONTROL Simulation of mechanical loads and environmental Characterization and dynamical studies of polymers in Time-based air traffic management using expert influences p 92 A87-14012 dipolar (aprotic) liquids systems p 85 A87-13362 Results of research on materials and construction [ AD-A 169243 1 p 123 N87-12685 Fault-tolerant C31 system A(O), A(l], MTBF allocations methods by the DFVLR p 64 A87-I4015 AEROELASTIC RESEARCH WINGS p 86 A87-15427 AIRCRAFT CONTROL Theoretical and experimental investigations 01 sensor Runway incursions a1 controlled airports in the United Decoupling control synthesis for an oblique-wing location for optimal aeroelastic system state estimation States aircraft p 108 A87-13342 p 115 N87-11794 [ PB86-9170031 p84 N87-11711 Aircraft fluner suppression via adaptive LOG control AEROELASTICITY Mode S beacom system: Functional description p 109 A87-13344 Application of time-domain unsteady aerodynamics to [ WTIFAA/PM-86/19] p 87 N87-11715 Bank-to-turnutilizing sampled data non-linear control rotary-wing aeroelasticity p 94 A87-14103 Aircraft accident report: Bar Harbor Airlines Flight 1808, p 109 A87-13346 Aeroelastic divergence of trimmed aircraft Beech BE-99, N300WP. Auburn-Lewiston Municipal Computational enhancements to a 4D algorithm --- for p 94 A87-14368 Airport. Auburn, Maine. August 25. 1985 aircraft trajectory optimization p 134 A87-13359 Application of a mixed variatlonal approach lo [PB86-910408] p 84 N87-12550 Impact of mismodeled idle engine performance on aeroelastic stability analysis of a nonuniform blade AIR TRANSPORTATION calculation and tracking of optimal 4-D descent p 126 A87-14423 US air transport technology - Where next? trajectories p 88 A87-13360 Unsteady transonic aerodynamics and aeroelasticity p 65 A87-16398 Eigenstructure assignment by dynamic output p 73 A87-15453 AIRBORNE EQUIPMENT feedback p 134 A87-13385 The aerodynamics and dynamics of rotors - Problems LOW COS1 aerial testing of parachutes Renewed interest in hinge moment models for failure and perspectives p 74 A87-15468 (AIM PAPER 86-24721 p 79 A87-13806 detection and isolation p 110 A87-13426 Adaptive fluner suppression p 113 A87-16182 ATTAS - The new lest bed p 92 A87-14003 Evaluation of detectability and distinguishability of Calculated effects of varying Reynolds Number and Effect of E-field mill location on accuracy of electric field aircraft control element failures using flight test data dynamic pressure on flexible wings at transonic speeds measurements with instrumented airplane p 110 A87-13435 p 75 N87-11738 p 95 A87-15027 Microelectronicsin aircraft systems Book Some expenences in aircraft aeroelastic design using --- Experimentalcalibration of an aircraft vector electric field p 101 A87-I3469 Preliminary Aeroelastic Design of Structures (PAD) meter system p 102 A87-15026 D 98 N87-11747 Combined guidance - Flight control of atmospheric Radio-navigation meters based on the K588 series vehicles p 110 A87-13654 On sound propagation in centrifugal fan casings microprocessor unit p 86 A87-15569 Design considerations for fly-by-wire control of new IESA-TT-957I D 138 N87-12326 Mobile intercept of storms p 132 N87-13064 AERONAUTICS AIRCRAFT Airbus aircraft [ MBB-UT-222-861 p 110 A87-13991 Israel Annual Conference on Aviation and Astronautics. Parameter estimation and in-plane distortion invariant ATTAS The new test bed p 92 A87-14003 27th. Haifa. Israel. February 27. 28. 1985. Collection of chord processing p 135 A87-13689 - Papers p64 A87-13635 AIRCRAFT ACCIDENT INVESTIGATION ESSY . An electromechanical adjustment system lor AEROSPACE ENGINEERING Aircraft accident investigation p 78 A87-13578 aircraft control surfaces p 92 A87-14014 Automated flexible assembly of aerospace structures Aircraft accidents, survival, and rescue Actuating system with digital signal converters and p 63 A87-13063 p 78 A87-13581 fiber-optic control p 93 A87-14018

A-2 SUBJECT INDEX AIRCRAFT LANDING

Stall margin indication --- aircraft accident prevention Experiences performingconceptual design optimization TSAR (Theater Simulation of Airbase Resources) [AIAA PAPER 86-25951 p 101 A87-14030 of transport aircraft p 97 N87-11723 database dictionary F-4E Modeling of the aircraft mechanical control system PIAS A program for an iterative aeroelastic solution [ AD-A1695751 p 139 N87-13352 p 111 A87-14135 p 97 N87-11725 AIRCRAFT FUEL SYSTEMS Optimal guidance law with first order lag loop and normal Optimization process in helicopter design Minimum ignition levels of aircraft fuel constituents to constraint p 86 A87-14140 p 98 N87-117% lightning related ignition sources p 83 A87-15038 Alldigital jets are taking off p 102 A87-14352 Sizing-stiffened composite panels loaded in the AIRCRAFT FUELS Integrated active control systems: Methods of postbuckling range p 129 N87-11733 Long-term deposit formation in aviation turbine fuel at algorithmic integration --- Russian book Application of optimization techniques to the design of elevated temperature p 121 A87-14986 p 135 A87-14682 a flutter suppression control law for the DAST ARW-2 Antimisting kerosene: Evaluation of low temperature p 115 N87-11736 Implementation01 CDFM generator control --.cascaded performance doubly fed machine p 135 A87-14957 Applicationsof CONMlNto wing design optimizationwith [DOT/FAAICT-85/31] p 122 N87-11902 The principle of optimality in the mean for fault-tolerant vortex flow effect p 98 N87-11737 Aviation turbine fuels, 1985 systems --- for aircraft terminal guidance Influence of analysis and design models on minimum p 112 A87-15212 weight design p 98 N87-11739 [ DE86-0121401 p 122 N87-11908 Reducing complexity in fly-by-wire flight control Multidisciplinary systems optimization by linear AIRCRAFT HAZARDS actuators decomposition p 136 N87-11740 Ground-based detection of aircraft icing conditions using [SAE PAPER 8517521 p 112 A87-15477 Aircraft configuration optimization including optimized microwave radiometers p 80 A67-14861 A system look at actuation concepts and alternatives flight profiles p 98 N87-11743 A review of aerospace and ground lightning threat lor primary flight control Multidisciplinary optimization applied to a transport characteristics and applications p 132 A87-15002 [ SAE PAPER 8517531 p 112 A87-15478 aircraft p 84 N87-11746 F-106 data summary and model results relative to threat Adaptive flutter suppression p 113 A87-16182 Some experiences in aircraft aeroelastic design using criteria and protection design analysis Aircraft control input optimization for aerodynamic Preliminary Aeroelastic Design of Structures (PAD) p 81 A87-15004 derivative estimation in dynamic manoeuvres p 98 N87-11747 Interpretation of a class of in-flight lightning signatures p 113 A87-16183 Design enhancement 1wIs in MSUNASTRAN p 81 A87-15005 Parameter estimation of aircraft with fly-by-wire control p 136 N87-11748 State-ol-the-art techniques for lightning systems p 113 A87-16186 The automated strength-aeroelastic design of susceptibililylvulnerabilily assessments Frequency domain parameter estimation of aeronautical aerospace structures program p 98 N87-11749 p 126 A87-15006 systems without and with time delay Recent Expenences in Multidisciplinary Analysis and Cornparison of low level frequency domain lightning p 114 A87-16193 Optimization, part 2 simulation test to pulse measurements --- on modified Analytical redundancy through nonlinear observers --_ [ NASA-CP-2327-PT-21 p 99 N87-11750 F-14A aircraft p 126 A87-15007 of aircraft motion p 114 A87-16197 Comments on gust response constrained optimization Lightning strikes10 aircraft of the German Federal Armed Tradeoff methods in multiobjective insensitive design p 115 N87-11774 Forces p 81 A87-15008 of airplane control systems p 115 N87-11730 Applying optimization software libraries to engineering Simulated lightning current tests on a Lynx helicopter Application of optimization techniques to the design of problems p 136 N87-11775 p 95 A87-15011 a flutter suppression control law for the DAST ARW-2 Design of a takeoff performance monitoring system Spatial and temporal description of strikes to the FAA p 115 N87-11736 p 103 N87-11787 CV-580 aircraft p 81 A87-15013 The implementation and use of Ada on distributed AIRCRAFT ENGINES Simultaneous airborne and ground measurement of low systems with high reliability requirements Vanable structure control of a turbojet engine altitude cloud-to-ground lightning strike on CV-580 [NASA-CR-1798421 p 137 N87-12265 p 103 A87-13343 aircraft p 81 A87-15014 AIRCRAFT DESIGN Multi-variable control of the GE T700 engine using the Comparison of electromagnetic measurements on an Design considerations for superplastically formed LQGILTR design methodology --- Linear Quadratic aircraft from direct lightning attachment and simulated P complex aircraft structures p 87 A87-13151 GaussianlLoop Transfer Recovery method nuclear electromagnetic pulse p 81 A87-15015 Cost drivers and design methodology lor automated p 103 A87-13418 Analysis of the first milliseconds of aircraft lightning airframe assembly p 63 A87-13157 Technicalleconomic evaluation of new propfan attachment p 81 A87-15016 Utilization of 3-0 programs for aircraft design and concepts in comparison with the turbofan of the 1990s Current levels and distributions on an aircraft during development p 86 A87-13646 p 104 A87-13989 ground lightning simulation tests and in-flight lightning National Specialist's Meeting on Crashworthy Design Improving the energy efficiency of cooled attachments p 82 A87-15017 of Rotorcraft.Georgia Institute of Technology, Atlanta. April high-temperature turbines p 104 A87-13990 Aircraft lightning-induced transient test and protection ! 7-9. 1986, Proceedings p89 A87-13662 Further development 01 the axial-radial compressor comparison p 82 A87-15022 State-of-the-art crashworthy cargo restraint systems lor p 104 A87-13998 Experimental study of the interaction between an arc military aircraft p89 A87-13667 Polymer, metal. and ceramic matrix composites for and an electrically floating structure p 126 A87-15023 Mechanism of energy absorption via buckling - An advanced aircraft engine applications Minimum ignition levels of aircraft fuel constituents to I analytical study p 124 A87-13682 p 121 A87-15187 lightning related ignition sources p 83 A87-15038 Correlationof experimentalstatic and dynamic response Finite element contact analysis of ring gear and Atmospheric electrical modeling in support of the NASA of simple structural components p 124 A87-13683 support p 127 A87-15193 F106 Storm Hazards Project Increasing the economy of design and preparation for The effect of lubricant cavitation on the characteristics [NASA-CR-1798011 p 132 N87-12082 manufacturingby integrated and graphic data processing: of a short hydrodynamic damper p 127 A87-15203 AIRCRAFT HYDRAULIC SYSTEMS CADICAM - Phase 111 Determination of the thrust and net efficiency of a Optimal stochastic Observers applied lo hydraulic [MBB-UT-225-86] p 125 A87-13986 propeller and flow parameters behind the propeller actuation systems p 87 A87-13354 The amphibian technology test vehicle - Summary and p 105 A87-15204 Fabrication and testing of lightweight hydraulic system results p 91 A87-13992 The effect of turbine elements on the gasdynamic simulator hardware Development of a GFRP wing in accordance with FAR stability margin p 105 A87-15208 [AD-AI 698841 p 130 N87-12711 Part 23 p 92 A87-13993 Using vibrationspectrum characteristicsfor the flow-path AIRCRAFT INDUSTRY Impetus of new technologies for utility. executive, and diagnostics of aircraft gas turbine engines The portfolio model of technological development in the commuter aircraft p 104 A87-14000 p 105 A67-15210 aircraft industry New fuselage technologies for general-aviation aircraft Turbines with counter-rotatingrotors for aircraft power [AD-AI708321 p 66 N87-12534 p 93 A87-14027 plants p 106 A87-15211 AIRCRAFT INSTRUMENTS Static test of an ultralight airplane STAEBL Structural tailoring of engine blades, phase 2 Precision point target tracking p 101 A87-13545 [AIAA PAPER 86-26001 p 64 A87-14034 p 106 N87-11731 Development and testing of new technologies for flight General aviation cost effectiveness Optimization applications in aircraft engine design and operation and safely p 86 A87-14004 [AIM PAPER 86-26071 p 139 A87-14037 test p 106 N87-11768 Avionics systems for future commercial helicopters Propeller design by optimization p 105 A87-14123 Control of gas turbines. The future: Is a radical approach p 101 A87-14005 Direct-inverse transonic wing analysis-design method needed? --- aircraft engines Stall margin indication --- aircraft accident prevention with viscous interaction p 71 A87-14365 [PNR-90295] p 107 N87-11793 [AIM PAPER 86-25951 p 101 A87-14030 Aeroelastic divergence of trimmed aircraft Carburizing steel for high temperalure service Experimental calibration of an aircraft vector electric field p94 A87-14368 [ AD-A1683271 p 122 N87-11877 meter system p 102 A87-15028 Computation of optimum-optimorum wing-fuselage Research on mechanical properties for engine life Comparison of two techniques of I.F.D. based on a configuration for future generation of supersonic aircraft prediction non-linear stochastic model of an aircraft --- Instrument p 74 A87-15761 [ AD-A1695701 p 108 N87-12563 Fault Detection p 114 A87-16196 A320 - Fly-by-wire airliner p96 A87-16394 Analysis of mixed-mode crack propagation using the A320 . Fly-by-wireairliner p96 A87-16394 V-22 Osprey - Multi-service workhorse boundary integral method AIRCRAFT LANDING p96 A87-16400 [ NASA-CR-1795181 p 131 N87-12915 The equivalent masses at nose landing-gears during A review of the technical development of Concorde landingimpacts and when taxiing over runway AIRCRAFT EQUIPMENT p96 A87-16408 perturbations p 86 A87-13637 Carburizing steel for high temperature service Recent Expenences in Multidisciplinary Analysis and Airplane flight through wind-shear turbulence [AD-A168327l p 122 N67-11877 Optimization. part 1 p 80 A87-14371 [NASA-CP-2327-PT-l] p96 N87-11717 A heater made from graphite composite matenal for Electroluminescent (EL) remotely-controlled landing Optimization in the systems engineering process potential deicing application zone marker light system p96 N87-11719 [NASA-TM-888881 p 101 N87-12559 [AD-W123861 p 87 N87-11716 Practical considerations in aeroelastic design Fabncation and testing of lightweight hydraulic system Simulator design features for helicopter landing on small p 97 N87-11720 simulator hardware ships. 1: A performance study Flutter optimization in fighter aircraft design [ AD-A1698841 p 130 N87-12711 [AD-A169514] p 119 N87-12572 p 97 N87-11721 Aircraft battery state of charge and charge control Simulator design and instructional features for carrier Application of the generalized reduced gradient method system landing: A field transfer study to conceptual aircraft design p 97 N87-11722 [AD-A169411] p 130 N87-12766 [AD-AI 699621 p 119 N87-12573

A-3 AIRCRAFT MAINTENANCE SUBJECT INDEX

Fnctional and retarding forces on aircraft tyres. Part 4: AIRCRAFT POWER SUPPLIES Aircraft accident reports: Brief format, US civil and Estimation of effects of yaw Implementation of CDFM generator control ---cascaded foreign aviation, issue number 5 of 1985 accidents [ESDU-86016-PT-41 p 131 N87-12868 doubly fed machine p 135 A87-14957 [PB86-916919] p 83 N87-11710 AIRCRAFT MAINTENANCE AIRCRAFT PRODUCTION Flight test report of the NASA icing research airplane: Development of high-alumina ceramic materials suitable Implementation of a robotic assembly cell Performance, stability. and control after flight through for making jet engine fixtures p 120 A87-13092 p63 A87-13062 natural icing conditions Repair of composite components. A Navy approach Automated flexible assembly of aerospace structures [NASA-CR-179515] p 116 N87-11797 p 117 A87-13122 p 63 A87-13063 AIRCRAFT SPIN Novel composite repair methods p 123 A67-13123 Clarification of adhesive binding mechanisms of Summary of NASA stalllspin research for general aviation configurations Multi-Echelon Repair Level Analysis - MERLA aluminum structural bonds in aircraft fabrication [AIM PAPER 86-25971 p 111 A87-14032 p64 A87-15414 [ MBB-UT-226-861 p 121 A87-13985 AIRCRAFT STABILITY Development of a maintenance automation system Automation of support processes for aircraft production p 128 A87-15425 Application of modern structural optimization to vibration using computers and numerical control --- Russian book reduction in rotorcraft p 115 N87-11752 Demonstration of combat damage repair estimator p64 A87-14687 p65 A87-15436 Introduction to aerodynamics derivitives. equations of The inspectable Structure p 65 A87-16397 AIRCRAFT RELIABILITY motion and stability TSAR (Theater Simulation of Airbase Resources) Airworthiness of composite structures - Some [ESDU-86021] p 76 N87-12536 experiences from civil certification p 78 A87-13627 database dictionary F-4E NASA rotor systems research aircraft: Fixed-wing [ AD-A1695751 p 139 N87-13352 All-digital jets are taking off p 102 A87-14352 configuration flight-test results AIRCRAFT MANEUVERS Airworthiness considerations of lightning strike [ NASA-TM-867891 p 100 N87-12557 Gust and maneuver spectra for general aviation protection for helicopter digital engine controls AIRCRAFT STRUCTURES aircraft p 105 A87-15010 Automated flexible assembly of aerospace structures [AIAA PAPER 86-25991 p 93 A87-14033 Environmental Stress Screening (ESS) demonstrates its p 63 A87-13063 Coordinated turn relations - A graphical representation value in the field p 127 A87-15403 Advanced manufacturing technology for structural ... of aircraft maneuver p 111 A87-14367 Reliability growth during flight test p 127 A87-15412 aircraft/aerospace components p 123 A87-13074 Aircraft control input optimization for aerodynamic RADC automated RaM package (RAMP) Repair of Composite Components - A Navy approach derivative estimation in dynamic manoeuvres p 128 A87-15417 p 117 A87-13122 p 113 A87-16183 MD-80 service maturity program p 64 A87-15418 Design considerations for superplastically formed Aircraft flight data compatibility checking using maximum FIA-18 Hornet reliability program - Status report complex aircraft structures p 87 A87-13151 likelihood and extended Kalman filter estimation p 64 A87-15419 Use of filament winding in manufacturing high quality p 113 A87-16184 VLSl impact on RAMS strategies in avionics design aerospace composite components p 123 A87-13164 AIRCRAFT MODELS p 128 A87-15423 Modelling strategies for finite element crash simulation Modeling of the aircraft mechanical control system Assessing the RaM attributes of advanced structures of complete vehicles p 90 A87-13673 p 111 A87-14135 --- Reliability a Maintainability of composite helicopters Correlation of experimental static and dynamic response Application of regression analysis to coupled responses p 96 A87-15424 of simple structural components p 124 A87-13683 at high angles of attack p 113 A87-16185 Reverse tailoring for realistic reliability tests Structure-component tests for a CFK fuselage Comparison of two techniques of I.F.D. based on a p 128 A87-15432 [MBB-UT-223-86] p 121 A87-14001 non-linear stochastic model of an aircraft --- Instrument Sizing hybrid packages for optimum reliability Corona from simulated aircraft surfaces and their Fault Detection p 114 A87-16196 p 128 A87-15433 contribution to the triggered discharge Determination of nonlinear aerodynamic coefficients AIRCRAFT SAFETY p 82 A87-15024 using the estimation-before-modelingmethods National Specialist's Meeting on Crashworthy Design Analysis of a composite thin-walled aircraft structure p 114 A87-16202 of Rotorcraft.Georgia Instituteof Technology. Atlanta, April p 127 A87-15226 AIRCRAFT NOISE 7-9. 1986. Proceedings p 89 A87-13662 Assessing the RaM attributes of advanced structures Influence of airfoil mean loading on convected gust Evolution of MIL-STD-1290A.light fixed and rotary-wing --- Reliability 8 Maintainability of composite helicopters interaction noise p 137 A87-13587 aircraft crashworthiness p 89 A87-13663 p 96 A87-15424 Companson of two propeller source models for aircraft The status of crashworthiness design criteria The inspectable structure p 65 A87-16397 interior noise studies p 88 A87-13596 p 89 A87-13664 Flutter optimization in fighter aircraft design Noise and performance of a counter-rotation propeller Survivability and crashworthiness design criteria p 97 N87-11721 p 105 A87-14366 p 89 A87-13665 Sizingsliflened composite panels loaded in the Analytical model for investigation of intenor noise The development of dynamic performance standards postbuckling range p 129 N87-11733 characteristics in aircraft with multiple propellers including for civil rotorcraft seats p 89 A87-13666 Comments on gust response constrained optimization synchrophasing p 94 A87-14925 Design of airframe Structures for crash impact p 115 N87-11774 Lightweight sidewalls for aircraft intenor noise control p 90 A87-13668 Carbon fibers [ NASA-CR-1724901 p 138 N87-12323 Crew seat stroke requirements for helicopter rolled [ AD-AI 71 3701 p 123 N87-12622 On sound propagation in centrifugal fan casings attitude impact crashworthiness p 90 A87-13669 AIRCRAFT SURVIVABILITY [ ESA-TT-9571 p 138 N87-12326 Program KRASH . The evolution of an analyiical tool survivability and crashworthiness design criteria Introduction to helicopter noise lo evaluate aircraft structural crash dynamics response p 89 A87-13665 [ ISL-NB-401/84] p 139 N87-12327 p 90 A87-13672 Combined radar, ECM functions will enhance Lavi An analysis of blade vortex interaction aerodynamics Crashworthy crewseat limit load optimization through survivability p 101 A87-13912 and acoustics p 77 N87-12547 dynamic testing p 91 A87-13675 Crash dynamics program transport seat performance Cruise noise of counterrotation propeller a1 angle of The design and qualification testing of an and cost benefit study attack in wind tunnel energy-absorbing seat for the Navy's H-53 AID [DOT/FAAICT-85/361 p 83 N87-11708 [NASA-TM-88869] p 139 N87-13252 helicopters p 91 A87-13679 AIRCRAFT PARTS Realistic civil helicopter crash safety AIRCRAFT TIRES CAD as a prerequisite for computer-integrated p 78 A87-13684 Vertical deflection characteristics of aircraft tyres manufacturing p 135 A87-14019 Impact severity and potential injury preventionin general [ESDU-86005] p 129 N87-11992 Design and manufacturing of a CFRP tail fin for the aviation accidents p 79 A87-13687 Frictional and retarding forces on aircraft tyres. Part 4: A300 Development and testing of new technologies for flight Estimation of effects of yaw [ MBB-UT-006-86] p 93 A87-14026 operation and safety p 86 A87-14004 [ESDU-86016-PT-4I p 131 N87-12868 AIRCRAFT PERFORMANCE Stall margin indication --- aircraft accident prevention AIRDROPS Parametric sizing of aerial application airplanes based [AIM PAPER 86-25951 p 101 A87-14030 Design and development of a two-stage parachute on varying levels of technology p 139 A87-13636 Summary of NASA stall/spin research for general system for delivery of troops from a high-speed aircraft Combined guidance - Flight control of atmospheric aviation configurations [AlAA PAPER 86-24481 p 80 A87-13818 vehicles p 110 A87-13654 [AIAA PAPER 86.25971 p 111 A87-14032 AIRFOIL PROFILES Potential influences of heavy rain on general aviation Now hear this --- sound warnings to aircrews Shock boundary layer interactions in laminar transonic airplane performance p 80 A87-14620 flow over airfoils using a hybrid method [AIAA PAPER 86-26061 p 94 A87-14036 International Aerospace and Ground Conference on p 66 A87-13503 Lightning and Static Electricity. 1Ith. Dayton. OH, June Coordinated turn relations - A graphical representation An exterior Poisson solver using fast direct methods 24-26. 1986. Technical Papers p 80 A87-15001 --- of aircraft maneuver p 11 1 A87-14367 and boundary integral equations with applications to Zoning of aircraft for lightning attachment and current nonlinear potential flow p 125 A87-13872 Flight test report of the NASA icing research airplane: transfer p 94 A87-15009 Performance. stability. and control after flight through Impact of airfoil profile on the supersonic aerodynamics Airworthiness considerations of lightning strike of delta wings p 71 A87-14363 natural icing conditions protection for helicopter digital engine controls NASA-CR-1795151 p 116 N87-11797 Vortex shedding of a square cylinder in front a slender 1 p 105 A87-15010 of Simplified forms of performance equations. Addendum Effect of E-field mill location on accuracy of electric field airfoil at high Reynolds numbers. Part 2: Compressibility A Effect on aeroplane level speed of small changes in measurements with instrumented airplane effect [MPIS-24/1985] p 75 N87-11704 thrust, drag, weight. power p 95 A87-15027 [ ESDU-86004-ADD-AI p 100 N87-12556 Implementation of GEMACS for lightning interactions AIRFOILS NASA rotor systems research aircraft: Fixed-wing analysis --- general electromagnetic model for analysis of Influence of airfoil mean loading on convected gust configuration flight-test results complex systems p 82 A87-15033 interaction noise p 137 A87-13587 INASA-TM-867891 p 100 N87-12557 Companson of absorption and radiation boundary Comparison of numerical solutions of lower order and AIRCRAFT PILOTS conditions in a time-domain three-dimensional higher order integralequation methods for two-dimensional Average landing force dependence on length and finite-diflerence code p 82 A87-15034 aerofoils direction of landing, parachute velocity components and The inspectable structure p 65 A87-16397 [AIAA PAPER 86-2591 1 p 69 A87-14028 wind speed National Transportation Safety Board safety Acceleration to a steady state for the Euler equations [AIAA PAPER 86-2452) p 79 A87-13794 recommendation p 83 N87-11706 p 70 A87-14096

A-4 SUBJECT INDEX AVIONICS

An experimental study of the aerodynamics of a NACA Mach 6 experimental and theoretical stability and Effectof E-fieldmilt location on accuracy of electnc field 0012 airfoil with a simulated glaze ice accretion performanceof a finnedcylindrical body at angles of attack measurements with instrumented airplane [NASA-CR-1798971 p 75 N87-11701 up to 65 deg p 95 A87-15027 Viscous-inviscidinteraction in transonic separated flow [ NASA-TM-890501 p 76 N87-12538 Implementation of GEMACS lor lightning interactions over solid and porous airfoils and cascades Cruise no& of counterrotation propeller at angle of analysis .-.general electromagnetic model for analysis of p 76 N87-12535 attack in wind tunnel complex systems p 82 A87-15033 AIRFRAME MATERIALS [NASA-TM-88869] p 139 N87-13252 Comparison of absorption and radiation boundary AV-8B/GR Mk 5 airframe composite applications ANGULAR VELOCITY conditions in a time-domain three-dimensional p 88 A87-13628 Motion characteristics of the UTlAS flight research finite-difference code p 82 A87-15034 AIRFRAMES simulator motion-base Improved electrostatic discharge wicks for aircraft Cost drivers and design methodology for automated [ UTIAS-TN-261I p 119 N87-11802 p 127 A87-15039 airframe assembly p 63 A87-13157 ANNULAR FLOW ATMOSPHERIC MODELS Effect of endwall contours on the performance of Design of airframe structures for crash impact two Atmospheric electrical modeling in support of the NASA an annular nozzle cascade p 71 A87-14119 p90 A87-13668 F106 Storm Hazards Project Computational fluid dynamic studies 01 certain ducted [NASA-CR-179801 p 132 N87-12082 Assessment of damage tolerance requirements and 1 bluff-body flowfields relevant to turbojet combustors. ATMOSPHERIC TURBULENCE analyses: A user's manual for crack growth and crack Volume 1: Timedependent calculationswith the k-epsilon Airplane flight through wind-shear turbulence initiation analysis: DAMGRO turbulence model for an existing centerbody combustor [AD-A1712091 p 132 N87-12939 p 80 A87-14371 [AD-A171434] p 131 N87-12816 A review of microburstsand their analysis and detection AIRLINE OPERATIONS ANTIFRICTION BEARINGS with Doppler radar Airlines look at 150-seaters p 83 A87-15180 Selection of rolling-element bearing steels for long-life [AD-A170458] p 133 N87-13110 Systems, avionics and instrumentation of transport application ATOMIZERS category helicopters [ NASA-TM-88881I p 129 N87-11993 Spray characteristics of two combined jet atomizers [NLR-MP-85066-U] p 102 N87-11785 ANTIMISTING FUELS p 124 A87-13660 AIRPORTS Antimisting kerosene: Evaluation of low temperature Performance and optimisation of an aitblast nozzle - Runway incursions at controlled airports in the United performance Drop size distribution and volumetric air flow States [DoT/FAAICT-85/31 I p 122 N87-11902 p 125 A87-13828 [PB86-917003] p 84 N87-11711 ANTISUBMARINE WARFARE Prediction of velocity coefficient and spray cone angle Advanced construction procedures: Confined bases for LAMPS MK 111 -A 'New Look' success story _-- reliability for simplex swirl atomizers p 125 A87-13830 airport pavements engineering of ship/helicopter system for antisubmarine AlTlTUDE (INCLINATION) [ FAA/PM-86/9] p 118 N87-11799 warfare p 102 A87-15415 The handling qualities and flight characteristics of the Number and duration of Runway Visual Range (RVR) APPLICATIONS PROGRAMS (COMPUTERS) Grumman design 698 simulated twin-engine tilt Nacelle runs for RVR-values lower than 225 m Design of a takeoff performance monitoring system V/STOL aircraft [ KNMI-TR-85(FM)I p 119 N87-11805 p 103 N87-11787 [ NASA-TM-867851 p 100 N87-12558 APPROACH A review of microbursts and their analysis and detection AlTlTUDE INDICATORS Guidance law simulation studies lor complex approaches with Doppler radar Investigation of magnetometer errors and their using the Microwave Landing System (MLS) [ AD-A1704581 p 133 N87-13110 compensation in the BO-105 helicopter [NASA-CR-l78182] p 87 N87-12552 [DNLR-FB-86-21] p 102 N87-11784 TSAR (Theater Simulation of Airbase Resources) Simulator design and instructional features for carrier AUTOMATED EN ROUTE ATC database dictionary F-4E landing: A field transfer study Sensitivity studies of 4D descent strategies in an [ADA1695751 p 139 N87-13352 [AD-A1699621 p 119 N87-12573 advanced metering environment p 88 A87-13361 AIRSHIPS APPROXIMATION AUTOMATIC CONTROL Possible military applications of stratospheric airship An approximate method of estimating the aerodynamic Decoupling control synthesis for an oblique-wing discussed p 101 N87-12716 interference between two parallel bodies in a supersonic aircraft p 108 A87-13342 AIRSPEED flow (axial force) Automatic variable reefing of parachutes by application Simplified forms of performance equations. Addendum [BR-1002711 p 76 N87-12540 of inflation forces A: Effect on aeroplane level speed of small changes in ARCHITECTURE (COMPUTERS) [AIM PAPER 86-24341 p79 A87-13784 thrust. drag, weight, power Beyond FTMP and SIFT - Advanced fault-tolerant The siting. installation and operational suitability of the [ESDU-86004-ADD-A] p 100 N87-12556 computers as successors to FTMP and SIFT Automated Weather Observing System (AWOS) at ALGORITHMS p 133 A87-13200 heliports A real-time simulation evaluation of an advanced Grundy - Parallel processor architecture makes [DOT/FAA/PM-86/30] p 133 N87-13099 detection. ikolation and accommodation algorithm for programming easy p 135 A87-13703 AUTOMATIC FLIGHT CONTROL sensor failures in turbine engines p 103 A87-13318 ARMED FORCES (UNITED STATES) A320 - Fly-by-wireairliner p 96 A87-16394 Computational enhancements to a 4D algorithm --- for Revised Uniform Summary of Surface Weather Aircraft automatic-flight-controlsystem with inversion of aircraft trajectory optimization p 134 A87-13359 Observations (RUSSWO). Parts A-F Ellington ANGB. the model in the feed-forward path using a Design of a takeoff performance monitoring system Texas Newton-Raphsontechnique for the inversion p 103 N87-11787 [AD-A169389] p 133 N87-13105 [ NASA-TM-882091 p 116 N87-11796 Guidance law simulationstudies for complex approaches ARTIFICIAL INTELLIGENCE AUTOMATIC TEST EQUIPMENT using the Microwave Landing System (MLS) 1986 American Control Conference. 5th. Seattle, WA. Automated infrared inspection of jet engine turbine [ NASA-CR-1781821 p 87 N87-12552 June 18-20, 1986. Proceedings. Volumes 1, 2. 8 3 blades p 125 A87-13719 Application of the AlPA (Approximate Iterative p 133 A87-I3301 AUTOMATION PreprocessingAlgorithm) to F-106 data Automated flexible assembly of aerospace structures Rapid prototyping facility for flight research in [ AD-A1690841 p 116 N87-12569 p63 A87-13063 artificial-intelligence-basedflight systems concepts ALIGNMENT Automated assembly-trends. concepts and [ NASA-TM-882681 p 137 N87-12273 In-flight transfer alignment/calibration of a strapdown requirements p 63 A87-13105 INS that employs carouseled instruments and IMU A prototype maintenance expert system for the CH-47 Cost drivers and design methodology for automated indexing p 85 A87-13438 flight control hydraulic system airframe assembly p 63 A87-13157 ALTITUDE SIMULATION [ADA1690191 p 116 N87-12568 Automation of support processes for aircraft production Effects of test cell recirculation on high-bypassturbofan ASPHALT using computers and numerical control --- Russian book engines during simulated altitude tests Criteria for asphalt-rubber concrete in civil airport p64 A87-14687 [AD-A1714181 p 108 N87-12565 pavements: Mixture design Development of a maintenance automation system ALTITUDE TESTS [DOT/FAA/PM-86/391 p 129 N87-11910 p 128 A87-15425 On the improvement of an expendable turbojet engine ASSEMBLING AUTOMOBILE ENGINES flight envelope p 104 A87-13647 Cost drivers and design methodology for automated Advanced Gas Turbine (AGT) Technology Project ALUMINUM ALLOYS airframe assembly p 63 A87-13157 [ NASA-CR-1794841 p 130 N87-11995 7050 aluminum rivets for military aircraft ASSEMBLY AVIONICS p 124 A87-13173 Implementationof a robotic assembly cell Selection of media access protocol for distributed digital Clarification of adhesive binding mechanisms of p 63 A87-13062 avionics p 134 A87-13436 aluminum structural bonds in aircraft fabrication Automated flexible assembly of aerospace structures Microelectronics in aircraft systems --- Book [ MBB-UT-226-861 p 121 A87-13985 p 63 A87-13063 p 101 A87-13469 ALUMINUM OXIDES Automated assembly-trends. concepts and Navstar Global Positioning Systems Collins user Developmentof high-aluminaceramic materials suitable requirements p 63 A87-13105 equipment - An evolutionary assessment for making jet engine fixtures p 120 A87-13092 p 85 A87-13533 AMPHIBIOUS AIRCRAFT ASTRONAUTICS Combined radar, ECM functions will enhance Lavi Israel Annual Conference on Aviation and Astronautics. The amphibian technology test vehicle - Summary and survivability p 101 A87-13912 27th. Haifa, Israel, February 27. 28. 1985. Collection of results p 91 A87-13992 Avionics Systems for future commercial helicopters Papers p64 A87-13635 ANGLE OF ATTACK p 101 A87-14005 A split canard configuraion for improved control at high ASYMMETRY All-digital jets are taking off p 102 A87-14352 angles of attack p67 A87-13643 Decoupling control synthesis for an oblique-wing A system model, a logic design diagram, and a general Experimental investigation of vortex flow over aircraft p 108 A87-13342 synthesis algorithm for optimal systems of onboard double-delta wing at high alpha p 67 A87-13652 ATMOSPHERIC EFFECTS electrical equipment in computer-aideddesign Application of regression analysis to coupled responses Combined guidance . Flight control of atmospheric p 96 A87-15214 at high angles of attack p 113 A87-16185 vehicles p 110 A87-13654 RAE€ automated R8M package (RAMP) The effect of a winglet on the spatial vortex of a slender ATMOSPHERIC ELECTRICITY p 128 A87-15417 body at high angle of attack Atmospheric Electncity Hazards Protection (AEHP) VLSl impact on RAMS strategies in avionics design [ADA1699251 p 65 N87-12533 demonstration p 82 A87-15021 p 128 A87-15423

A-5 AXIAL FLOW SUBJECT INDEX

Sizing hybnd packages for Optimum reliability Cornputation of optimum-optimorum wing-fuselage Carbon libers p 128 A87-15433 configuration lor future generation of supersonic aircraft [ AD-AI 71370 ] p 123 N87-12622 General aviation activity and avionics survey p 74 A87-15761 CARBURIZING [AD-A168582] p 65 N87-11686 BORON Carburizing steel for high temperature service Systems. avionics and instrumentation of transport Prospective. characteristics and problems of the use [ AD-AI 68327 ] p 122 N87-11877 category helicopters 01 boron in different air augmented propulsion modes CARGO AIRCRAFT [NLR-MP-85066-UI p 102 N87-11785 [IAF PAPER 86-1911 p 122 A87-15924 State-of-the-artcrashworthy cargo restraint systems lor AXIAL FLOW BOUNDARYINTEGRALMETHOD military aircraft p 89 A87-13667 Journal of engineering thermophysics (selected Shock boundary layer interactions in laminar transonic Aircraft accident reports: Brie1 format. US civil and articles) flow over airfoils using a hybrid method foreign aviation. issue number 5 of 1985 accidents [ AD-AI 694521 p 139 N87-13347 p66 A87-13503 [ PB86-9169191 p 83 N87-11710 AXIAL FLOW TURBINES An exterior Poisson solver using fast direct methods CASCADE CONTROL GsuaIisation of axial turbine tip clearance flow using a and boundary integral equations with applications lo Implementation 01 CDFM generator control --- cascaded linear cascade nonlinear potential flow p 125 A87-13872 doubly fed machine p 135 A87-14957 [CUED/A-TURBO/TR-1221 p 107 N87-12560 CASCADE FLOW BOUNDARYLAYERCONTROL AXISYMMETRIC BODIES Effect of two endwall contours on the performance of Combination of suction and tangential blowing in Application 01 viscous-inviscid interaction methods lo an annular nozzle cascade p 71 A87-14119 boundary layer control p 67 A87-13641 transonic turbulent flows Performance evaluation of an inverse integral equation [ NASA-CR-I799001 p 75 N87-11700 BOUNDARY LAYER SEPARATION method applied to turbomachine cascades A summary of the development of integral aerodynamic p 72 A87-14771 methods for the computation of rotor wake interactions Viscous-inviscid interaction in transonic separated flow B [AD-A169254] p 77 N87-12545 over solid and porous airfoils and cascades BOUNDARY LAYER TRANSITION p 76 N87-12535 6-1 AIRCRAFT Pitot and static errors in Steady level fltght CASTING Advanced composites applications lor the 6-1B bomber [ESDU-860061 p 74 N87-11691 Resin-hardener systems lor resin transfer molding - An OVeNleW p 87 A87-13101 BOUNDARY VALUE PROBLEMS p 120 A87-13093 BALANCE Reachable outputs in systems with bounded parameler Fabrication 01 cooled radial turbine rotor The development 01 balance tubes for Dowty ROIol uncertainties - Application to failure detection [ NASA-CR-1795031 p 107 N87-11789 composite bladed propellers p 63 A87-13630 p 134 A87-13326 CAVITATION FLOW BALLOON-BORNE INSTRUMENTS Analysis 01 mixed-mode crack propagation using the The effect 01 lubricant cavilation on the characteristics Mobile intercept of storms p 132 N87-13064 boundary integral method of a short hydrodynamic damper p 127 A87-15203 BALLOONS [ NASA-CR-1795181 p 131 N87-12915 CELESTIAL BODIES Aerodynamic Decelerator and Balloon Technology BRITTLENESS Ramjet application in atmospheres of different celestial Conference. 9th. Albuquerque. NM. October 7-9. 1986, bodies Technical Papers p 79 A87-13776 Carburizing steel for high temperalure service [ AD-A168327 I p 122 N87-11877 [IAF PAPER 86-1811 p 120 A87-15920 BATTERY CHARGERS CENTRIFUGAL COMPRESSORS Aircraft battery state of charge and charge control BUBBLES Spanwise variation of laminar separation bubbles on Further development of the axial-radial compressor system p 104 A87-13998 [AD-A169411] p 130 N87-12766 wings at low Reynolds number p 71 A87-14362 BUCKLING CERAMIC COATINGS BEAMS (SUPPORTS) Investigation of coaling performance and corrosion 01 The structural optimization 01 a spreader bar lor twin Mechanism of energy absorption via buckling - An analytical study p 124 A87-13682 cornpressor components in the TF30-P-3 engine of F1I IC lift helicopter operations p 100 N87-11759 aircraft BEARING ALLOYS [AD-A168802] p 107 N87-11792 Selection of rollina-element bearing steels lor Ions-life C Advanced Gas Turbine (AGT) Technology Project application [ NASA-CR-1794841 p 130 N87-11995 NASA-TM-888811 D 129 N87-11993 r C-130 AIRCRAFT Journal of engineering thermophysics (selected BEARINGLESS ROTORS Electrostatic field measurements in a foam filled C-130 articles) Testing a tail rotor system in fiber-reinforcedconstruction fuel tank during fuel sloshing p 95 A87-15037 [AD-A169452I p 139 N87-13347 manner p 92 A87-14016 CALIBRATING Development 01 a new type of beanngless rotor CERAMIC MATRIX COMPOSITES In-flight transfer alignmentlcalibration of a strapdown system p 93 A87-14017 Polymer, metal, and ceramic matrix composites for INS that employs carouseled instruments and IMU advanced aircraft engine applications BEARINGS indexing p 85 A87-13438 Carburizing steel for high temperature service p 121 A87-15187 Experimentalcalibration of an aircraft vector electric field Advanced Gas Turbine (AGT) Technology Project [ AD-AI 683271 p 122 N87-11877 meter system p 102 A87-15028 BENDING THEORY [ NASA-CR-179484 I p 130 N87-11995 Improved electrostatic discharge wicks for aircraft Someobservationsonthe behavior 01 the Langley model CERAMICS p 127 A87-15039 rotor blade Development of high-alumina ceramic materials suitable Motion characteristics of the UTlAS flight research [NASA-CR-179880] p 74 N87-11695 lor making jet engine fixtures p 120 A87-13092 simulator motion-base BIBLIOGRAPHIES A constitutive law for finite element contact problems [ UTIAS-TN-2611 p 119 N87-I 1802 FAA helicopterlheliport research engineering, and Supplementary calibration test of the tip-aerodynamics- with unclassical friction development bibliography. 1964-1986 and acoustics-testpressure transducers [ NASA-TM-888381 p 131 N87-12924 [FAA/PM-86/47 1 p 118 N87-11798 [NASA-TM-883121 p 131 N87-I2830 CERTIFICATION BLADE SLAP NOISE CANARD CONFIGURATIONS Airworthiness of composite Structures - Some An analysis of blade vortex interaction aerodynamics A split canard configuraion for improved control at high experiences from civil certification p 78 A87-13627 and acoustics p 77 N87-12547 angles of altack p 67 A87-13643 CESSNA AIRCRAFT BLADE TIPS Exploratory wind-tunnel investigation 01 the stability and National Transportation Safety Board safety Two-dimensional blade-vortex flow visualization control characteristics of advanced general aviation recommendation p 83 N87-11706 investigation p 70 A87-14111 configurations CH-47 HELICOPTER Special opportunities in helicopter aerodynamics [AIAA PAPER 86-25961 p 11 1 A87-14031 A prototype maintenance expert System for the CH-47 p 74 A87-15469 Wind-tunnel investigation of the OMAC canard flight control hydraulic system An analysis 01 blade vortex interaction aerodynamics configuration [ AD-AI69019 ] p 116 N87-12568 and acoustics p 77 N87-12547 [AIAA PAPER 86-26081 p 69 A87-I4038 The evaluation of a number of prototypes for the free tip CH-54 HELICOPTER CANOPIES rotor constant-moment controller The structural optimization of a spreader bar for twin Performance prediction for fully-deployed parachute [ NASA-TM-866641 p 131 N87-12869 lift helicopter operations p 100 N87-11759 canopies BLAST LOADS CHANNEL FLOW [AIAA PAPER 86-24751 p 79 A87-13809 Blast gust loading on a 35 degree swept-back wing Numerical solution of transonic potential flows with finite A comparison of measuredand calculated Stress in solid [AD-A1694151 p 116 N87-12570 elements method using multigrid technique and ribbon parachute canopies BLOWING p 68 A87-13900 [AlAA PAPER 86.24881 p A87-13815 80 CHEMICAL COMPOSITION Combination of suction and tangential blowing in CARBON FIBER REINFORCED PLASTICS boundary layer control p 67 A87-13641 Criteria lor asphalt-rubber concrete in civil airport The development of balance tubes lor Do* Roto1 BLUNT BODIES pavemenis: Mixture design composite bladed propellers p 63 A87-13630 Computational fluid dynamic studies of certain ducted 1 DOT/FAA/PM-86/39) Development and testing 01 critical components for the p 129 N87-11910 bluff body flowfields relevanl to turbojet combustors technological preparation of a CFK outer wing CHEMICAL PROPERTIES Volume 1 Time-dependent calcutatlons with the h-epsilon IMBB-UT-224-861 p 92 A87-13997 FlOO fuel sampling analysis: Foreign samples turbulence model for an existing centerbody combustor Structure-component tests for a CFK luselage IAD-AI685731 p 122 N87-11904 [ AD-AI 71434 p 131 N87-12816 1 I MBB-UT-223.861 p 121 A87-14001 CHEMICAL REACTIONS 80-105 HELICOPTER Design and manufacturing of a CFRP tail fin lor the Spectral methods lor modeling supersonic chemically Investigation of magnetometer errors and their A300 reacting flowfields p 70 A87-14110 compensation in the BO-105 helicopter IMBB-UT-006.861 p 93 A87-I4026 CHOKES IDFVLR-FB-86-21I p 102 N87-11784 Some effects of moislure on adhesive-bonded Comment on 'Computation of choked and supersonic BODY-WING CONFIGURATIONS CFRP-CFRP joints p 129 A87-16160 turbomachinery flows by a modified potential method Turbulent flow around a winglfuselage-type juncture CARBON FIBERS p 71 A87-14129 p70 A8714108 Technologies for a mechanized carbon fiber CIRCUIT RELIABILITY Advances in adaptive wall wind tunnel technique construction element for commercial aircraft production VLSl impact on RAMS strategies in avionics design p 118 A87-15465 [ MBB-UT-005-861 p 126 A87-13999 p 128 A87-15423

A-6 SUBJECT INDEX COMPUTER AIDED DESIGN

CIRCULAR PLATES COMPENSATORS Convergence acceleration lor a three-dmensional Aerodynamic coefficients of a circular wing in steady Multivariable high-gain control with feedforward EulerlNavier-Stokes zonal approach p 70 A87-14105 subsonic flow p 67 A87-13653 compensation - A design technique p 134 A87-13365 Cornpanson of finite volume flux vector splmgs for tne CIRCULATION CONTROL AIRFOILS COMPOSITE MATERIALS Euler equations p 70 A87-14109 Aerodynamic force calculations of an ellipticalcirculation Advanced manufacturing technology for structural Experimental and numerical invest8gation of supersonic control airfoil p 71 A87-14360 aircraft/aerospacecomponents p 123 A87-13074 turbulent flow through a square duct p 70 A87-14117 Composite curing with semi-permeable membranes CIVIL AVIATION An implicit time-marching scheme for transonic flow p 120 A87-13121 Weather safety aspects in future civil air navigation p 71 A87-14261 p 85 A87-13540 Polymer. metal, and ceramic matrix composites for advanced aircraft engine applications Study of a bounded jet flow considering the initial Airworthiness of composite structures - Some turbulence II . In the case of relatively large nozzle aspect experiences from civil certification p 78 A87-13627 p 121 A87-15187 COMPOSITE STRUCTURES ratio p 71 A87-14263 The development of dynamic performance standards Advanced composites applicationsfor the 6-1 bomber Aerodynamic force calculations of an ellipticalcirculation for civil rotorcraft seats p89 A87-13666 - An overview p 87 A87-13101 control airfoil p 71 A87-14380 Summary of NASA staWspin research for general Automated assembly-trends. concepts and Vectonzable multigrid algorithms for transonic-flow aviation configurations requirements p 63 A87-13105 calculations p 72 A87-14652 p 111 A87-14032 [AIM PAPER 86.25971 Repair of composite components - A Navy approach Performance evaluation of an inverse integral equation General aviation cost effectiveness p 117 A87-13122 method applied to lurbomachine cascades [AIM PAPER 86.26071 p 139 A87-14037 Novel Composite repair methods p 123 A87-13123 p72 A87 14771 General aviation activity and avionics survey Fibre reinforced composites 1986; Proceedings of the Calculation of aerodynamic force Coefficients [ AD-A1685821 p65 N87-11686 Second International Conference, University of Liverpool. p 73 A87 15229 Aircraft accident reports: Brief format, US civil and England, April 8-10, 1986 p 121 A87-13613 Advances in the understanding and computation of foreign aviation, issue number 5 of 1985 accidents Mechanized manufacture of composite main rotor blade unsteady transonic flow p 73 A87-15452 [ PB86-9169191 p83 N87-11710 spars p 124 A87-13625 Unsteady transonic aerodynamics and aeroelaslicity Aimorthiness of composite Structures - Some Aircraft accident reports: Brief format. US civil and p 73 A87-15453 foreign aviation. issue number 4 of 1985 accidents experiences from civil certification p 78 A87-13627 AV8BIGR Mk 5 airframe composite applications Some asymptotic types 01 transonic vortex flows [ PB86-9169181 p84 N87-11712 p 74 A87-15553 Aircraft accident reports: Brief format, US civil and p 88 A87-13628 The development of balance tubes for Dowty Rotol Determination of the regime coefficlents in the local foreign aviation, issue number 3 of 1985 accidents theory of interaction from plate data p 74 A87-15561 [ PB86-9169171 p84 N87-11713 composite bladed propellers p 63 A87-13630 Technologies for a mechanized carbon fiber Computation of optimum-optimorum wing fuselage Review of accident data: US general aviation calendar construction element for commercial aircraft production configuration for future generation of supersonic aircraft year 1982 [MBB-UT-005-86] p 126 A87-13999 p 74 A87-15761 [ PB88-201910] p84 N87-11714 Analysis of a composite thin-walled aircraft structure Calculated effects of varying Reynolds Number and CLOUD GLACIATION p 127 A87-15226 dynamic pressure on flexible wings at transonic speeds Comparative flight measurement icing parameters for of Assessing the RBM anributes of advanced Structures p 75 N87-11738 the DO 28 D2 propeller-drivenaircraft of the German Army --- Reliability B Maintainability of composite helicopters The predictionof transonic loading advancing helicopter Testing Office 61 and for DFVLR's Falcon 20 E jet aircraft p96 A87-15424 in stratus clouds rotors COMPRESSIBILITY EFFECTS AD-A168217 p 100 N87-11781 [ ESA-TT-9411 p 83 N87-11709 I I Vortex shedding of a square cylinder in front of a slender Computational fluid dynamic studies of certain ducted COCKPITS airfoil at high Reynolds numbers. Part 2 Compressibility bluff body flowfields relevant to turbojet combustors Now hear this sound warnings to aircrews --- effect Volume 1 Time-dependent calculabons mth the k-epsilon p 80 A87-14620 [ MPIS-24/1985] p 75 N87-11704 turbulence model for an existing centerbody combustor A test on the reliability and performance of the verbex COMPRESSIBLE FLOW [AD A1714341 p 131 N87-12816 series 4000 voice recognizer Computation of two-dimensional supersonic turbulent COMPUTATIONAL GRIDS [AD-A169066] p 130 N87-12729 flow over a wmpresson corner p 66 A87-13502 An analytical parametric investigation of numerical COEFFICIENT OF FRICTION Numerical calculation of viscous internal flows nonlinear vortex lanice methods p 67 A87-13638 Frictional and retarding forces on aircraft lyres. Part 4: p 69 A87-14010 Numencal solution of transonic potential flows with finite Estimation of effects of yaw Numerical solution of the Euler equation for elements method using multignd technique [ ESDU-86016-PT-41 p 131 N87-12868 compressible inviscid fluids p 69 A87-14095 p 88 A87-13900 COLD WEATHER TESTS Modeling of turbulent separated flows for aerodynamic influence of trailing-edge meshes on skin fnction in Antimisting kerosene: Evaluation of low temperature applications p 73 A87-15454 Navier-Stokescalculations p 71 A87-14125 performance COMPRESSOR EFFICIENCY Vectonzable multigrid algorithms lor transonic-flow [DOT/FAA/CT-85/31] p 122 N87-11902 Further development of the axial-radial compressor calculations p 72 A87 14852 COLD WORKING p 104 A87-13998 COMPUTER AIDED DESIGN The effect of material compressibility (Poisson ratio) on COMPRESSORS Mechanized manufacture of composite main rotor blade the elasto-plastic solution to the problem of a cylinder under Investigation of coating performance and corrosion of spars p 124 A87.13825 internal pressure (coldworking situation) compressor components in the TF30-P-3 engine of F111C Utilization of 3-0 programs for aircraft design and p 124 A87-13642 aircraft development p88 A87-13648 COLLISION AVOIDANCE [ADA1688021 p 107 N87-11792 Increasing (he economy of design and preparation for Runway incursions at controlled airports in the United COMPUTATIONAL FLUID DYNAMICS manufacturing by integrated and graphic data processing States Interaction of decaying trailing vortices in ground CADICAM Phase Ill [PB86-917003] p84 N87-11711 shear p 66 A87-13499 IMBB LIT 225-861 p 125 A87-13986 Obstacle-warning radar for helicopters Computation of two-dimensional supersonic turbulent CAD as a prerequisite for computer-integrated p 132 N87-13149 flow over a compression corner p 66 A87-13502 manufacturing p 135 A87-14019 COMBUSTIBLE FLOW Numerical calculation of three-dimensional inviscid A system model, a logic design diagram. and a general Spectral methods for modeling supersonic chemically supersonic flows p 66 A87-13504 synthesis algorithm for optimal systems of onboard reacting flowfields p 70 A87-14110 On the utilization of vortex methods for parachute electrical equipment in computer-aided design COMBUSTION CHAMBERS aerodynamic predictions p 96 A87-15214 Experimental investigation of a solid fuel ramjet [AIM PAPER 86-24551 p68 A87-13795 Recent Experiences in Multidisciplinary Analysis and combustor p 104 A87-13658 Axisymmetric vortex lanice method applied to parachute Optimization. part I Computational fluid dynamic studies of certain ducted shapes [ NASA-CP-2327-PT-1J p 96 N87-11717 bluff-body flowfields relevant to turbojet combustors. [AIM PAPER 86-24561 p68 A87-13796 Practical considerations in aeroelastic design Volume 1: Time-dependent calculations with the k-epsilon An exterior Poisson solver using fast direct methods p 97 N87-11720 turbulence model for an existing centerbody combustor and boundary integral equations with applications to Flutter optimization in fighter aircraft design [AD-A1714341 p 131 N87-12816 nonlinear potential flow p 125 A87-13872 p 97 N87-11721 COMBUSTION EFFICIENCY Numerical solution of transonic potential flows with finite Application of the generalized reduced gradient method Spray characteristics of two combined jet atomizers elements method using multigrid technique to conceptual aircraft design p 97 N87-11722 p124 A87-13660 p 68 A87-13900 Experiences performing conceptual design optimization COMBUSTION PHYSICS Numerical calculation of viscous internal flows of transport aircraft p 97 N87-11723 Further shock tunnel studies of scramjet phenomena p 69 A87-14010 PlAS A program for an iterative aeroelastic solution [NASA-CR-l79937] p 77 N87-12542 Comparison of numerical solutions of lower order and p 97 N87-11725 COMMERCIAL AIRCRAFT higher order integral equation methods for two-dimensional Optlmization process in helicopter design Technologies for a mechanized carbon fiber aerofoils p 98 N87-11726 COnStrUCtion element for commercial aircraft production [AIM PAPER 86-2591I p 69 A87-14028 Tradeofl methods in multioblective insensitive design [MBB-UT-005-86] p 126 A87-13999 Effect of an upstream wake on a pusher propeller oi airplane control systems p 115 N87-11730 Avionics systems for future commercial helicopters [AIM PAPER 86-28021 p 69 A87-14035 STAEBL Structural tailonng of englne blaoes. phase 2 p 101 A87-14005 Numerical solution oi the Euler equation for p 106 N87 11731 Airlines look at 150-seaters p 83 A87-15180 compressible inviscid fluids p 69 A87-14095 Sizing-stiffened composite panels loaded in the Manufacturers plan new long-range aircraft Vortex-sheet capturing in numerical solutions of the postbuckling range p 129 N87-11733 p 95 A87-15181 incompressible Euler equations p 70 A87-14099 Influence of analysis and design models on minimum Us air transport technology - Where next? Finite element Navier-Stokes calculation of welght design p 98 N87-11739 p 65 A87-16398 three-dimensional turbulent flow near a propeller Aircraft configuration optimization including optimized COMMUNICATION NETWORKS p 70 A87-14101 flight profiles p 98 N87 11743 Improving Loran coverage at minimum cost Computation of sharpfin-induced shock wave/turbulenl Multidisciplinary optimization applied to a transport D 86 A87-13543 boundary-layer interactions p 70 A87-14104 aircraft p84 N87 11746

A-7 COMPUTER AIDED MANUFACTURING SUBJECT INDEX

Some experiences in aircraft aeroelastic design using CONCURRENT PROCESSING A direct method for enforcing equality constraints in Preliminary Aeroelastic Design of Structures (PAD) The implementation and use of Ada on distributed optimal output feedback p 134 A87-13353 p 98 N87-11747 systems with high reliability requirements Dynamic output feedback flight control laws using Design enhancement tools in MSCINASTRAN [ NASA-CR-1798421 p 137 N87-12265 eigenstructure assignment p 109 A87-13355 p 136 N87-11748 CONFERENCES Multivariable high-gain control with feedforward The automated strength-aeroelastic design of Fire safety science; Proceedingsof the First International Compensation - A design technique p 134 A87-13365 aerospace structures program p 98 N87-11749 Symposium. Gaithersburg. MD. October 7-11, 1985 Multivariable flight control for an attack helicopter Recent Experiences in Multidisciplinary Analysis and p 78 A87-13186 p 109 A87-13379 Optimization. part 2 1986 American Control Conference. 5th. Seattle. WA. Eigenstructure assignment by dynamic output [ NASA-CP-2327-PT-21 p 99 N87-11750 June 18-20, 1986. Proceedings. Volumes 1, 2, 8 3 feedback p 134 A87-13385 Overview: Applications of numerical optimization p 133 A87-13301 Multi-variable control of the GE T700 engine using the methods to helicopter design problems ION. National Technical Meeting. Long Beach, CA. LQGILTR design methodology --- Linear Quadratic p 99 N87-11751 January 21-23. 1986. Proceedings p 85 A87-13532 Gaussian/Loop Transfer Recovery method Helicopter rotor blade aerodynamic optimization by Aero- and hydro-acoustics; Proceedings of the p 103 A87-13418 mathematical programming p 99 N87-11753 Symposium, Ecole Centrale de Lyon. Ecully, France, July Design considerations for fly-by-wire control of new Regression analysis as a design optimization tool 3-6, 1985 p 137 A67-13585 Airbus aircraft p 136 N87-11754 Fibre reinforced composites 1966 Proceedings of the [ MBB-UT-222-861 p 110 A87-13991 A rotor optimization using regression analysis Second International Conference, University of Liverpool. Actuating system with digital signal converters and p 136 N87-11755 England. April 6-10, 1986 p 121 A87-13613 fiber-optic control p 93 A87-14018 Optimization of helicopter rotor blade design for Israel Annual Conference on Aviation and Astronautics. Modeling of the aircraft mechanical control system minimum vibration p 99 N87-11756 27th, Haifa. Israel. February 27. 28, 1985. Collection of p 111 A87-14135 Application of numerical optimization to rotor Papers p 64 A87-13635 Mathematical model and digital simulation for speed aerodynamic design p 99 N87-11757 National Specialist's Meeting on Crashworthy Design control system of two-spool turbojet engine Aeroelastic-aerodynamic optimization of high speed of Rotorcraft.Georgia Institute of Technology, Atlanta. April p 105 A67-14139 helicopter-compoundrotor p 99 N87-11758 7-9. 1986, Proceedings p89 A87-13662 Optimal discrete design of digital flight control system The structural optimization of a spreader bar for twin Aerodynamic Decelerator and Balloon Technology p 111 A67-14142 lift helicopter operations p 100 N87-11759 Conference, 9th, Albuquerque, NM. October 7-9. 1986. Advanced actuation. controls and integration for Optimization applications in aircraft engine design and Technical Papers p 79 A87-13776 aerospace vehicles; Proceedings of the Symposium, San test p 106 N87-11768 International Aerospace and Ground Conference on Diego. CA. October 9. 1985 On optimal design for the blade-root/hub interface in Lightning and Static Electricity, 1lth, Dayton, OH, June [ SAE P-1701 p 112 A87-15476 jet engines p 106 N87-11769 24-26, 1986. Technical Papers p 80 A87-15001 Reducing complexity in fly-by-wire flight control Comments on gust response constrained optimization Recent advances in aerodynamics p 73 A87-15451 actuators p 115 N87-11774 Advanced actuation, controls and integration for [SAE PAPER 8517521 p 112 A87-15477 COMPUTER AIDED MANUFACTURING aerospace vehicles; Proceedings of the Symposium. San A system look at actuation concepts and alternatives Automated assembly-trends. concepts and Diego. CA. October 9, 1985 for primary flight control requirements p63 A87-13105 [SAE P-1701 p 112 A87-15476 [SAE PAPER 8517531 p 112 A87-15478 Increasing the economy of design and preparation for Identification and system parameter estimation 1985; Advanced digital optical control actuation for the manufacturing by integrated and graphic data processing: Proceedings of the Seventh Symposium, University of ADOCS CAD/CAM - Phase 111 York. England, July 3-7, 1985. Volumes 1 8 2 [SAE PAPER 8517551 p 112 A87-15480 [ MBB-UT-225-661 p 125 A67-13986 p 135 A87-16176 Preliminary design of electromechanical servosystems [SAE PAPER 8517591 p 129 A87-15482 CAD as a prerequisite for computer-integrated Recent Experiences in Multidisciplinary Analysis and Identification and system parameter estimation 1985; manufacturing p 135 A87-14019 Optimization. part 1 [ NASA-CP-2327-PT-11 p 96 N87-11717 Proceedings of the Seventh Symposium, University of Automation of support processes for aircraft production CONICAL FLOW York. England, July 3-7. 1965. Volumes 1 8 2 using computers and numerical control Russian book ._- Constant-density approximation to Taylor-Maccoll p 135 A87-16176 p64 A87-14687 solution p 71 A87-14127 Adaptive flutter suppression p 113 A87-16182 COMPUTER GRAPHICS CONICAL NOZZLES Sensor failure detection in flight control systems using Direct solution of flutter equations with interactive Prediction of velocity coefficient and spray cone angle deterministic observers p 114 A87-16195 graphics procedure p 110 A87-13648 for simplex swirl atomizers p 125 A87-13830 Aircraft autometic-flight-controlsystem with inversion of Increasing the economy of design and preparation for CONSTRAINTS the model in the feed-fomard path using a manufacturing by integrated and graphic data processing: A direct method for enforcing equality constraints in Newton-Raphson technique for the inversion CAD/CAM - Phase Ill optimal output feedback p 134 A87-13353 [ NASA-TM-882091 p 116 N87-11796 [ MBB-UT-225-861 p 125 A87-13986 CONSTRUCTION CONTROL THEORY On optimal design for the blade-rootlhub interlace in Advanced construction procedures: Confined bases for Methods for obtaining robust tracking control laws jet engines p 106 N87-11769 airport pavements p 134 A87-13319 Evaluation of a visual system in its support of simulated [FAA/PM-66/9] p 116 N87-11799 Optimal guidance law with first order lag loop and normal helicopter flight CONTRAROTATING PROPELLERS constraint p 86 A87-14140 [ AD-A1688291 p 102 N87-11783 Noise and performance of a counter-rotationpropeller Integrated active control systems: Methods of COMPUTER PROGRAMMING p 105 A87-14366 algorithmic integration --- Russian book Computational enhancements to a 4D algorithm --.for Cruise noise of counterrotation propeller at angle of p 135 A87-14662 aircraft trajectory optimization p 134 A87-13359 attack in wind tunnel CONTROLLERS Applying optimization software libraries to engineenng [ NASA-TM-66869] p 139 N87-13252 1986 American Control Conference. 5th. Seattle. WA. June 16-20, 1986. Proceedings. Volumes 1. 2, 8 3 problems p 136 N87-11775 CONTROL 1966 American Control Conference, 5th. Seattle. WA. p 133 A87-13301 COMPUTER PROGRAMS June 18-20, 1986. Proceedinas. Volumes 1. 2. 8 3 Evaluation of detectability and distinguishability of Implementation of GEMACS for lightning interactions p 133 A87-13301 aircraft control element failures using flight test data analysis --- general electromagnetic model for analysis of CONTROL EQUIPMENT p 110 A87-13435 complex systems p 82 A87-15033 MTFCS (multiDle target formation flight control svstem) Tradeoff methods in multiobjective insensitive design COMPUTER SYSTEMS PROGRAMS Formation position sensor trade-off analysis of airplane control systems p 115 N87-11730 Grundy - Parallel processor architecture makes p 110 A87-13536 Application of optimization techniques to the design of programming easy p 135 A87-13703 Integrated active control systems Methods of a flutter suppression control law for the DAST ARW-2 COMPUTER TECHNIQUES algonthmic integration --- Russian book p 115 N87-11736 Development of a maintenance automation system p 135 A87-14682 Flight model discharge system p 128 A87-15425 CONTROL SIMULATION [AD-A169423] p 117 N87-12571 COMPUTERIZED SIMULATION ATTAS - The new test bed p 92 A87-14003 Aircraft battery state of charge and charge control A real-time simulation evaluation of an advanced CONTROL STABILITY system detection. ikolation and accommodation algorithm for Flight test report of the NASA icing research airplane [AD-A169411] p 130 N87-12766 sensor failures in turbine engines p 103 A87.13318 Performance. stability. and control after flight through The evaluation of a number of prototypes for the free-tip Landing gear performance simulation by KRASH natural icing conditions rotor constantmoment controller program p 90 A87-13670 [NASA-CR-1795151 p 116 N87-11797 1 NASA-TM-866641 p 131 N87-12869 Computer modeling of crashworthy seating systems CONTROL SURFACES COOLING SYSTEMS p 90 A87-13671 A split canard configuraion for improved control at high A study of the effect of the temperature factor on Modelling strategies for finite element crash simulation angles of attack p 67 A87-13643 pressure losses in the cooling system of the leading edge of complete vehicles p 90 A87-13673 Load lightening and flutter damping for future Airbus of a deflector vane --- for gas turbine engines projects p 127 A87-15218 A simulation of the dynamics of the mechanisms of the MBB-UT-004.861 p 92 A87-14002 CORNER FLOW aircraft landing gear p 96 A87.15220 1 ESSY - An electromechanical adjustment system for Computation of two-dimensional supersonic turbulent Tool to develop real time simulation systems aircraft control surfaces p 92 A87-14014 flow Over a compression corner p 66 A87-13502 [ INPE-3979-TDL/233] p 137 N87-13179 A System look at actuation concepts and alternatives Effect of port corner geometry on the internal CONCORDE AIRCRAFT for pnmary flight control performance of a rotating-vane-typethrust reverser A review of the technical development of Concorde [ SAE PAPER 851 753 ] p 112 A87-15478 INASA-TP-26241 p 77 N87-12541 p96 A87-16408 CONTROL SYSTEMS DESIGN CORROSION CONCRETES Time scale analysis of e digital flight control system Investigation of coating performance end corrosion of Criteria for asphalt-rubber concrete in civil airport p 109 A87-13347 compressor components in the TF30-P-3 engine of FlllC pavements: Mixture design Flight control design using nonlinear inverse dynamics aircraft [DOT/FAA/PM-86/39] p 129 N67-11910 p 109 A87 13352 IAD-At 686021 p 107 N87-11792 A-a SUBJECT INDEX DIFFUSERS

COST ANALYSIS CREEP TESTS DATA SAMPLING A dynamic model for airframe cost estimation Research on mechanical propertles for engine life Bank-to-turn utilizing sampled data non-linear control [ ADA168842 ] p65 N87-11687 prediction p 109 A87-13346 COST EFFECTIVENESS [ ADA1 695701 p 108 N87-12563 DECELERATION Parametric sizing of aerial application airplanes based CROSS COUPLING Aerodynamic Decelerator and Balloon Technology on varying levels of technology p 139 A87-13636 Decoupling control synthesis for an oblique-wing Conference. 91h, Albuquerque, NM. October 7-9, 1986. General aviation cost effectiveness aircraft p 108 A87-13342 Technical Papers p 79 A87-13776 [AIAA PAPER 86.26071 p 139 A87-14037 CROSS FLOW DECISION MAKING For small airliners and executive jets Interaction of decaying trailing vortices in ground An efficientdecision-making-free filter for processes with p 105 A87-15179 shear p66 A87-13499 abrupt changes p 136 A87-16189 COUNTER ROTATION CRUISING FLIGHT Optimization in the systems engineering process Turbines with counter-rotating rotors for aircraft power Cruise noise of counterrotation propeller at angle of p 96 N87-11719 plants p 106 A87-15211 attack in mnd tunnel Influence of analysis and design models on minimum 1 COUPLING COEFFICIENTS INASA-TM-888691 p 139 N87-13252 weight design p 98 N87-11739 Application of the AlPA (Approximate Iterative CRYOGENIC COOLING Munidisciplinary systems optimization by linear Preprocessing Algorithm) to F-106 data Clyogenic wound rotor for lightweight, high voltage decomposition p 136 N87-11740 [ ADA1 690841 p 116 N87-12569 generators DECOUPLING CRACK PROPAGATION [AD-W12370] p 130 N87-12768 Decoupling control synthesis for an oblique-wing A check of crack propagation prediction models against CRYOGENIC WIND TUNNELS aircraft p 108 A87-13342 test results generated under transport aircraft flight Design and construction of a cryogenic-wind-tunnel DEFENSE PROGRAM simulation loading model p 117 A87-13986 Possible military applications of stratospheric airship [ NLR-TR-84005-Ul p 100 N87-11782 The development of DMS-scales for cryogenic wind discussed p 101 N87-12716 Research on mechanical properties for engine life tunnels p 117 A87-14007 DEFLECTION prediction Status report on the European Transonic Wind Tunnel Calculated effects of varying Reynolds Number and [ AD-A1695701 p 108 N87-12563 (EW p 11 7 A87-14023 dynamic pressure on flexible wings at transonic speeds Analysis of mixed-mode crack propagation using the DNLR cryogenic-wind-tunneland model technology p 75 N87-11738 boundary integral method p 117 A87-14024 Vertical deflection characteristics of aircraft lyres [NASA-CR-179518] p 131 N87-12915 A description of the active and passive [ESDU-86005] p 129 N87-11992 Assessment of damage tolerance requirements and sidewall-boundary-layerremoval systems of the 0.3-meter DEFLECTORS analyses: A user's manual for crack growth and crack transonic cryogenic tunnel A study of the effect of the temperature factor on initiation analysis: DAMGRO [NASA-TM-87764] p 118 N87-11801 pressure losses in the cooling system of the leading edge [ AD-A171 2091 p 132 N87-12939 CURING of a deflector vane -__for gas turbine engines CRASH LANDING Composite curing with semi-permeable membranes p 127 A87-15218 Program KRASH - The evolution of an analytical tool p 120 A87-13121 DEICING to evaluate aircraft structural crash dynamics response CURRENT DISTRIBUTION Ground aircraft deicing technology review p 90 A87-13672 Zoning of aircraft for lightning attachment and current [DOTIFAA/CT-85/21] p 83 N87-11707 KRASH analysis correlation with full scale YAH-63 transfer p94 A87-15009 A heater made from graphite composite material for helicopter crash test p 90 A87-13674 Current levels and distributions on an aircraft during potential deicing application Full scale crash test of a BK117 helicopter ground lightning simulation tests and in-flight lightning [ NASA-TM-888881 p 101 N87-12559 p 91 A87-13678 attachments p 82 A87-15017 DELTA WINGS Wholefield displacement measurements using speckle CYLINDRICAL BODIES Experimental investigation of vortex flow over image processing techniques for crash tests Vortex shedding of a square cylinder in front of a slender double-delta wing at high alpha p 67 A87-13652 p 124 A87-13680 airfoil at high Reynolds numbers. Part 2 Compressibility Impact of airfoil profile on the supersonic aerodynamics Analysis of US. civil rotorcraftaccidents for development effect I of delta wings p 71 A87-14363 of improved design criteria p78 A87-13685 [ MPIS-24/1985] p 75 N87-11704 Lower-side normal force charactensltcs of delta mngs Aircraft accident/incident summary reports: Erie, Mach 6 experimental and theoretical stability and at supersonic speeds p 72 A87-14372 i Pennsylvania. October 14, 1984; Albuquerque, New performance of a finned cylindrical body at angles of attack Mathematical modeling of the motion of a statically Mexico, February 11, 1985 up to 65 deg deformed delta-shaped glider p 95 A87-15205 [ PB86-9104071 p 84 N87-12549 [ NASA-TM-890501 p 76 N87-12538 DEPOSITS Aircraft accident report: Bar Harbor Airlines Flight 1808, CYLINDRICAL SHELLS Long-term deposit formation in aviation turbine fuel at Beech BE-99, N300WP. Auburn-Lewiston Municipal The effect of material compressibility (Poisson ratio) on elevated temperature p 121 A87-14986 Airport. Auburn. Maine, August 25, 1985 the elasto-plasticsolution lo the problem of a cylinder under Investigation of coating performance and corrosion of I [PB86-910408] p 84 N87-12550 internal pressure (coldworking situation) compressor components in the TF30-P-3 engine of F111C CRASHWORTHINESS p 124 A87-13642 aircraft I National Specialist's Meeting on Crashworthy Design [ AD-A1688021 p 107 N87-11792 of Rotorcraft,Georgia Instituteof Technology, Atlanta, April DESCENT TRAJECTORIES 7-9. 1986, Proceedings p89 A87-13662 D !mpact of mismodeled idle engine performance on Evolution of MIL-STD-1290A. light fixed and rotary-wing calculation and tracking of optimal 4-D descent DAMAGE ASSESSMENT aircraft crashworthiness p 89 A87-13663 trajectories pBB A87-13360 Demonstration of combat damage repair estimator The status of crashworthiness design criteria Sensitivity studies of 4D descent strategies in an p65 A87-15436 p 89 A87-13664 advanced metering environment p 88 A87-13361 Assessment of damage tolerance requirements and Survivability and crashworthiness design criteria DESIGN ANALYSIS analyses: A user's manual for crack growth and crack p 89 A87-13665 Increasing the economy of design and preparation for initiation analysis: DAMGRO State-of-the-art crashworthy cargo restraint systems for manufacturing by integrated and graphic data processing: [ AD-A171 2091 p 132 N87-12939 military aircraft p89 A87-13667 CAD/CAM - Phase 111 Design of airframe structures for crash impact DATA ACOUlSlTlON [ MBB-UT-225-861 p 125 A87-13986 p 90 A87-13668 Acquisition and use of data for crashworthiness Propeller design by optimization p 105 A87-14123 Crew seat stroke requirements for helicopter rolled improvements in US. Army aircraft p 78 A87-13686 Turbine bypass remote augmentor lift system for attitude impact crashworthiness p 90 A87-13669 A small, flexible and powerful data acquisition system V/STOL aircraft p 105 A87-14364 Landing gear performance simulation by KRASH for the F16 aircraft Recent Experiences in Multidisciplinary Analysis and program p90 A87-13670 [NLR-MP-85074-U] p 103 N87-11786 Optimization, part 1 Computer modeling of crashworthy seating systems DATA BASES [ NASA-CP-2327-PT-11 p96 N87-11717 p90 A87-13671 Parameter estimation and in-plane distortion invanant Regression analysis as a design optimization tool Program KRASH ~ The evolution of an analytical tool chord processing p 135 A87-13689 p 136 N87-11754 to evaluate aircraft structural crash dynamics response Practical considerations in aeroelastic design DESIGN TO COST p 90 A87-13672 p 97 N87-11720 Cost drivers and design methodology for automated KRASH analysis correlation with full scale YAH-63 DATAMANAGEMENT airframe assembly p 63 A87-13157 helicopter crash test p90 A87-13674 Optimization in the systems engineering process DETECTION Crashworthy crewseat limit load optimization through p 96 N87-11719 A real-time simulation evaluation of an advanced dynamic testing p 91 A87-13675 Practical considerations in aeroelastic design detection. isolation and accommodation algorithm for Full scale crash test of a BK117 helicopter p 97 N87-11720 sensor failures in turbine engines p 103 A87-13318 p 91 A87-13678 DICTIONARIES DATA PROCESSING The design and qualification testing of an TSAR (Theater Simulation of Airbase Resources) Increasing the economy of design and preparation for energy-absorbing seat for the Navy's H-53 AID database dictionary F-4E manufacturing by integrated and graphic data processing: helicopters p 91 A87-13679 [ADA1695751 p 139 N87-13352 CAD/CAM Phase Ill Correlation of experimentalstatic and dynamic response - DIESEL ENGINES [MBB-UT-225-86] p 125 A87-13986 Of simple structural components p 124 A87-13683 Compound cycle engine program Realistic civil helicopter crash safety Evaluation of a nonlinear parameter extraction [NASA-TM-88879] p 107 N87-11790 p78 A87-13684 mathematical model including the term C(subm(sub delta DIFFERENCE EOUATIONS Acquisition and use of data for crashworthiness e squared)) An efficient decision-making-freefilter for processes with improvements in US. Army aircraft p 78 A87-13686 [NASA-TM-87731] p 116 N87-12566 abrupt changes p 136 A87-16189 Impact severity and potential injury prevention in general A prototype maintenance expert system for the CH-47 DIFFUSERS aviation accidents p79 A87-13687 flight control hydraulic system Theoretical studies of the ETW diffuser and of the Crash dynamics program transport seat performance [ ADA1 6901 91 p 116 N87-12568 second throat p 69 A87-14022 and cost benefit study Tool lo develop real time simulation systems Start-up of a wind tunnel with a multichannel diffuser [ DOT/FAA/CT-85/36] p 83 N87-11708 [ INPE-3979-TDL12331 p 137 N87-13179 p 72 A87-15206

A-9 DIFFUSION SUBJECT INDEX

DIFFUSION DROPS (LIQUIDS) ELECTRIC CONTROL Investigation of coating performance and corrosion of Large volume water sprays for dispersing warm logs Design considerations for fly-by-wire Control of new compressor components in the TF30-P-3 engine of F111C p 125 A87-13848 Airbus aircraft aircraft DUCTED BODIES [ MBB-UT-222-861 p 110 A87-13991 [AD-A1688021 p 107 N87-11792 Computational fluid dynamic studies of certain ducted ESSY - An electromechanical adjustment SyStem for DIFFUSION WELDING bluff-body flowfields relevant to turbojet combustors. aircraft control surfaces p 92 A87-14014 Diffusion bonding of certain refractory metals Volume 4: Time-dependent calculationswith the k-epsilon ELECTRIC CORONA D 121 A87-13171 turbulence model for an existing centerbody combustor Corona from simulated aircraft surfaces and their DIGITAL COMMAND SYSTEMS [AD-AI 714341 p 131 N87-12816 contribution to the triggered discharge Advanced flight control actuation systems and their DUCTED FLOW p 82 A87-15024 interface with digital commands Experimental and numerical investigation of supersonic ELECTRIC CURRENT I [SAE PAPER 8517541 p 112 A87-15479 tutulent flow through a square duct p 70 A87-14117 Prediction of skin currents flowing on a Lynx helicopter Advanced digital optical control actuation lor the DUST COLLECTORS due to a simulated lightning strike p 95 A87-15012 ADOCS Development of an advanced vaneless inlet particle Current levels and distributions on an aircraft during [SAE PAPER 8517551 p 112 A87-15480 separator for helicopter engines p 105 A87-14984 ground lightning simulation tests and in-flight lightning DIGITAL DATA DYNAMIC CHARACTERISTICS attachments p 82 A87-15017 Time scale analysis of a digital flight control system A dynamic model for airframe cost estimation Lightning return stroke current computation p 109 A87-13347 [ AD-At 688421 p 65 N87-11687 p 126 A87-15029 DIGITAL RADAR SYSTEMS Crash dynamics program transport seat performance A heater made from graphite composite material for Mode S beacom system: Functional description and cost benefit study potential deicing application [ DOT/FAA/PM-86/19] p 87 N87-11715 [ NASA-TM-888881 p 101 N87-12559 [ DOT/FAA/CT-85/36 I p 83 N87-11708 DIGITAL SIMULATION Characterization and dynamical studies 01 polymers in ELECTRIC DISCHARGES State-of-the-art techniques for lightning Modeling of the aircraft mechanical control system dipolar (aprotic) liquids susceptibilitylvulnerabilityassessments p 111 A87-14135 [AD-A169243] p 123 N87-12685 p 126 A87-15006 Mathematical model and digital simulation for speed DYNAMIC CONTROL Corona from simulated aircraft surfaces and their control system of two-spool turbojet engine Reachable outputs in systems with bounded parameter p 105 A87-14139 contribution to the triggered discharge uncertainties - Application to failure detection p A87-15024 DIGITAL SYSTEMS p 134 A87-13326 82 Selection of media access protocol for distributed digital Dynamic output feedback flight control laws using Improved electrostatic discharge wicks for aircraft avionics p 134 A87-13436 eigenstructure assignment p 109 A87-13355 p 127 A87-15039 Optimal discrete design of digital flight control system Eigenstructure assignment by dynamic output Atmospheric electrical modeling in support of the NASA p 111 A87-14142 feedback p 134 A87-13385 F106 Storm Hazards Project All-digital jets are taking off p 102 A87-14352 DYNAMIC LOADS [NASA-CR-179801] p 132 N87-12082 DIGITAL TECHNIQUES Dynamic loads on twin jet exhaust nozzles due to shock ELECTRIC FIELDS Actuating system with digital signal converters and noise p 94 A87-14369 Effect of E-field mill location on accuracy of electric field fiber-optic control p 93 A87-14018 DYNAMIC MODELS measurements with instrumented airplane DIRECTIONAL CONTROL A simulation of the dynamics of the mechanisms of the p 95 A87-15027 Methods for obtaining robust tracking control laws aircraft landing gear p 96 A87-15220 Experimentalcalibration of an aircraft vector electric field p 134 A87-13319 DYNAMIC RESPONSE DISPLACEMENTMEASUREMENT meter system p 102 A87-15028 Correlation of experimental static and dynamic response Wholefield displacement measurements using speckle Electrostatic field measurements in a foam filled C-130 of simple structural components p 124 A87-13683 image processing techniques for crash tests fuel tank during fuel sloshing p 95 A87-15037 Application of regression analysis to coupled responses p 124 A87-13680 ELECTRIC GENERATORS at high angles 01 attack p 113 A87-16185 Implementation of CDFM generator control ---cascaded DISPLAY DEVICES DYNAMIC STABILITY Microelectronics in aircraft systems Book doubly led machine p 135 A87-14957 --- Drag and stability improvements of a square p 101 A87-13469 parachute ELECTRIC PULSES Simulated lightning current tests on a Lynx helicopter Simulator design and instructional leatures lor carrier [ AIAA PAPER 86-2471] p 68 A87-13805 landing: A field transfer study The effect 01 turbine elements on the gasdynamic p 95 A87-15011 [ AD-A1699621 p 119 N87-12573 stability margin p 105 A87-15208 ELECTRODES DISTORTION NASA rotor systems research aircraft: Fixed-wing Aircraft battery state of charge and charge control Parameter estimation and in-plane distortion invariant configuration flight-test results system chord processing p 135 A87-13689 [ NASA-TM-867891 p 100 N87-12557 [AD-A1694111 p 130 N87-12766 I DISTRIBUTED PROCESSING DYNAMIC STRUCTURAL ANALYSIS ELECTROLUMINESCENCE Selection of media access protocol lor distributed digital Landing gear performance simulation by KRASH Electroluminescent (EL) remotely-controlled landing avionics p 134 A87-13436 program p 90 A87-13670 zone marker light system The implementation and use 01 Ada on distributed Program KRASH - The evolution of an analytical tool [AD-D012386] p87 N87-11716 systems with high reliability requirements to evaluate aircraft structural crash dynamics response ELECTROMAGNETICINTERACTIONS [NASA-CR-1798421 p 137 N87-12265 p90 A87-13672 Implementation of GEMACS for lightning interactions DOCUMENTS Modelling strategies for finite element crash simulation analysis --- general electromagnetic model for analysis of I FAA helicopterlheliport research, engineering. and of complete vehicles p 90 A87-13673 complex systems p 82 A87-15033 development bibliography, 1964-1986 KRASH analysis correlation with full scale YAH-63 ELECTROMAGNETICPULSES IFAA/PM-86/47] p 118 N87-11798 helicopter crash test p 90 A87-13674 Comparison of electromagnetic measurements on an DOPPLER RADAR Mechanism 01 energy absorption via buckling - An aircraft from direct lightning attachment and simulated Mobile intercept of storms p 132 NP7-13064 analytical study p 124 A87-13682 nuclear electromagnetic pulse p81 A87-15015 DYNAMIC TESTS A review 01 microbursts and their analysis and detection Analysis of the first milliseconds of aircraft lightning Crashworthy crewseat limit load Optimization through with Doppler radar attachment p 81 A87-15016 dynamic testing p 91 A87-13675 [ AD-A 170458] p 133 N87-13110 Application 01 the AlPA (Approximate Iterative DYNAMICAL SYSTEMS Preprocessing Algorithm) to F-106 data DRAG Parametric identification of discontinuous [ AD-A1690841 p 116 N87-12569 I Simplified forms of performance equations. Addendum nonlinearities p 135 A87-16179 A Effect on aeroplane level speed 01 small changes in ELECTROMECHANICALDEVICES thrust. drag, weight. power ESSY - An electromechanical adjustment system for [ ESDU-86004-ADD-Al P 100 N87-12556 E aircraft control surfaces p 92 A87-14014 DRAGCHUTES Preliminary design of electromechanical servosystems Status report of a new recovery parachute system for EARLY WARNING SYSTEMS [SAE PAPER 8517591 p 129 A87-15482 the F111 aircraft crew escape module Combined radar, ECM functions will enhance Lavi ELECTRONIC COUNTERMEASURES [AIAA PAPER 86.24371 p 91 A87-13821 survivability p 101 A87-13912 Combined radar, ECM functions will enhance Lavi The Annular Parachute - An approach to a low altitude EIGENVALUES SuNiVability p 101 A87-13912 personnel parachute Decoupling control synthesis lor an oblique-wing ELECTROSTATICCHARGE [AIM PAPER 86.24491 p 80 A87-13823 aircraft p 108 A87-13342 Electrostatic field measurements in a foam filled C-130 I DRAG REDUCTION Dynamic output feedback flight control laws using fuel tank during fuel sloshing p 95 A87-15037 eigenstructure assignment p 109 A87-13355 Length adjustable strut link with low aerodynamic drag Improved electrostatic discharge wicks for aircraft Eigenstructure assignment by dynamic output [AD-D0122791 p 77 N87-12543 p 127 A87-15039 DROP SIZE feedback p 134 A87-13385 EJECTION SEATS ELECTROSTATICPROBES Performance and optimisation 01 an airblast nozzle - Status report 01 a new recovery parachute system lor Flight model discharge system Drop size distribution and volumetric air flow the F111 aircraft crew escape module IAD-Al694231 p 117 N87-12571 I p 125 A87-13828 [AIAA PAPER 86-2437 I p 91 A87-13821 EMBEDDED COMPUTER SYSTEMS DROP TESTS ELASTOPLASTICITY The implementation and use 01 Ada on distributed Landing gear performance simulation by KRASH The effect 01 material compressibility (Poisson ratio) on systems with high reliability requirements program p 90 A87-13670 the elasto-plastic Solution to the problemof a cylinder under INASA-CR-1798421 p 137 N87-12265 KRASH analysis correlation with lull scale YAH-63 internal pressure (coldworking situation) ENERGY ABSORPTION helicopter crash test p 90 A87-13674 p 124 A87-13642 Crashworthy crewseat limit load optimization through Wholefield displacement measurements using speckle ELECTRIC ARCS dynamic testing p 91 A87-13675 image processing techniques for crash tests Expenmental study of the interaction between an arc Mechanism of energy absorption via buckling - An p 124 A87-13680 and an electrically floating structure p 126 A87-15023 analytical study p 124 A87-13682 I I A-10 SUBJECT INDEX FEEDBACK CONTROL

ENERGY CONSERVATION EQUATIONS OF MOTION F-14 AIRCRAFT Polymer, metal, and ceramic matrix composites for Direct solution of flutter equations with interactive Comparison of low level frequency domain lightning advanced aircraft engine applications graphics procedure p 110 A87-13648 simulation test to pulse measurements -_- on modified p 121 A87-15187 Mathematical modeling of the motion of a statically F-14A aircraft p 126 A87-15007 ENERGY CONSUMPTION deformed delta-shaped glider p 95 A87-15205 Atmospheric Electricity Hazards Protection (AEHP) Energy efficient actuation using variable displacement Introduction to aerodynamics derivitives, equations of demonstration p 82 A87-15021 hydraulic control motion and stability Aircraft lightninginduced transient test and protection [SAE PAPER 8517571 p 112 A87-15481 [ESDU-86021] p 76 N87-12536 companson p 82 A87-15022 Simplified forms of perlormance equations. Addendum ENERGY CONVERSION EFFICIENCY F-16 AIRCRAFT A Effect on aeroplane level speed of small changes in Improving the energy efficiency of cooled A small, flexible and powerful data acquisition system high-temperature turbines p 104 A87-13990 thrust, drag, weight, power for the F16 aircraft [ ESDU-86004-ADD-A] p 100 N87-12556 [ NLR-MP-85074-Ul p 103 N87-11786 ENGINE CONTROL ERRORS F-18 AIRCRAFT Closed loop control of an afterburning FlOO gas turbine Pitot and static errors in steady level flight FIA-18 Hornet reliability program Status report engine p 103 A87-13323 - [ESDU-86006] p 74 N87-11691 p 64 A87-15419 Variable structure control of a turbojet engine ESTIMATING F-27 AIRCRAFT p 103 A87-13343 An approximate method of estimating the aerodynamic A check of crack propagation prediction models against Impact of mismodeled idle engine performance on interference between two parallel bodies in a supersonic test results generated under transport aircraft flight calculation and tracking of optimal 4-D descent flow (axial force) simulation loading trajectories p88 A87-13360 [ BR-100271] p 76 N87-12540 [NLR-TR-84005-U] p 100 N87-11782 Mathematical model and digital simulation for speed EULER EQUATIONS OF MOTION F-4 AIRCRAFT control system of two-spool turbojet engine Numerical solution of the Euler equation for A dynamic model for airframe cost estimation p 105 A87-14139 compressible inviscid fluids p 69 A87-14095 [AD-A168842] p 65 N87-11687 Airworthiness considerations of lightning strike Acceleration to a steady state for the Euler equations TSAR vheater Simulation of Airbase Resources) protection for helicopter digital engine controls p 70 A87-14096 database dictionary F-4E p 105 A87-15010 Vortex-sheet capturing in numerical solutions of the [AD-A169575] p 139 N87-13352 Control of gas turbines. The future: Is a radicalapproach incompressible Euler equations p 70 A87-14099 FABRICATION needed? --- aircraft engines Convergence acceleration for a three-dimensional Microelectronicsin aircraft systems --- Book [PNR-90295] p 107 N87-11793 Euler/Navier-Stokes zonal approach p 70 A87-14105 p 101 A87-13469 ENGINE DESIGN Comparison of finite volume flux vector splittings for the FACTORIZATION Mechanized manufacture of composite main rotor blade Euler equations p 70 A87-14109 Application of viscous-inviscid interaction methods to spars p 124 A87-13625 Numerical simulation of tip vortices of wings in subsonic transonic turbulent flows On the improvement of an expendable turbojet engine and transonic flows [ NASA-CR-1799001 p 75 N87-11700 flight envelope p 104 A87-13647 [ AD-A1691 161 p 77 N87-12544 FAIL-SAFE SYSTEMS Further development of the axial-radial compressor EUROPEAN AIRBUS Built-In-Testfor fail-safe design p 128 A87-15428 p 104 A87-13998 Design considerations for fly-by-wire control of new FAILURE ANALYSIS New-technology gas generator (GNT 1) - The actual Airbus aircraft Reachable outputs in systems with bounded parameter state of development p 126 A87-14006 [ MBB-UT-222-861 p 110 A87-13991 uncertainties - Application to failure detection Turbine bypass remote augmentor lift System for Development and testmg of critical components for the p 134 A87-13326 V/STOL aircraft p 105 A87-14364 technological preparation of a CFK outer wing FAILURE MODES For small airliners and executive jets [ MBB-UT-224-861 p 92 A87-13997 A real-time Simulation evaluation of an advanced p 105 A87-15179 Load lightening and flutter damping for future Airbus detection, isolation and accommodation algorithm for Optimization applications in aircraft engine design and projects sensor failures in turbine engines p 103 A87-13318 test p 106 N87-11768 [MBB-UT-004-86] p 92 A87-14002 Clanfication of adhesive binding mechanisms of On optimal design for the blade-rootlhub interface in Design and manufacturing of a CFRP tail fin for the aluminum structural bonds in aircraft fabrication jet engines p 106 N87-11769 A300 [ MBB-UT-226-861 p 121 A87-13985 ENGINE NOISE [ MBB-UT-006-861 p 93 A87-14026 Some effects of moisture on adhesive-bonded CFRP-CFRP joints p 129 A87-16160 Dynamic loads on twin jet exhaust nozzles due to shock EVALUATION noise p 94 A87-14369 A real-time simulation evaluation of an advanced Sizing-stiffened composite panels loaded in the postbuckling range p 129 N87-11733 Analytical model for investigation of interior noise detection, isolation and accommodation algorithm for characteristics in aircraft with multiple propellers including sensor failures in turbine engines p 103 A87-13318 FAIRINGS Length adjustable strut link with low aerodynamic drag synchrophasing p 94 A87-14925 EXHAUST NOZZLES ENGINE PARTS (AD-Wl22791 p 77 N87-12543 Dynamic loads on twin jet exhaust nozzles due to shock FAR FIELDS Development of high-alumina ceramic materials suitable noise p 94 A87-14369 for making jet engine fixtures p 120 A87-13092 Experimental investigation of near and far acoustic field Thrust reverser-exhaust nozzle assembly for a gas Methods for the assembly and testing of the bearing of a small turbojet p 138 A87-13605 turbine engine FATIGUE TESTS supports of gas turbine engines --- Russian book [AD-D012390] p 108 N87-12561 p 126 A87-14683 Development of a GFRP wing in accordance with FAR The effect of turbine elements on the gasdynamic Effects of test cell recirculationon high-bypass turbofan Part 23 p 92 A87-13993 stability margin p 105 A87-15208 engines during Simulated altitude tests A check of crack propagation prediction models against [AD-A171418] p 108 N87-12565 Component improvement program task 83-01, 36E133 test results generated under transport aircraft flight air turbine starter EXPERT SYSTEMS simulation loading [ AD-A1694831 p 108 N87-12562 Time-based air traffic management using expert [ NLR-TR-84005-UI p 100 N87-11782 ENGINE STARTERS systems p 85 A87-13362 Research on mechanical DroDerties for enaine life Component improvement program task 83-01, 36E133 A prototype maintenance expert system for the CH-47 prediction air turbine starter flight control hydraulic system [AD-A169570] p 108 N87-12563 [AD-A1694831 p 108 N87-12562 [ AD-A16901 91 p 116 N87-12568 FAULT TOLERANCE ENGINE TESTS EXTERNAL STORE SEPARATION Beyond FTMP and SIFT - Advanced fault-tolerant Experimental investigation of a solid fuel ramjet An aerodynamic analysis and the subsequent motion computers as successors to FTMP and SIFT combustor p 104 A87-13658 of external store p 66 A87-13501 p 133 A87-13200 Renewed interest in hinge moment models for failure Methods for the assembly and testing of the bearing EXTERNALSURFACECURRENTS detection and isolation p 110 A87-13426 supports of gas turbine engines --- Russian book Comparison of absorption and radiation boundary The principle of optimality in the mean for fault-tolerant p 126 A87-14683 conditions in a time-domain three-dimensional Using vibration spectrum charactenstics for the flow-path finite-difference code p 82 A87-15034 systems --- for aircraft terminal guidance p 112 A87-15212 diagnostics of aircraft gas turbine engines EXTERNAL TANKS p 105 A87-15210 Fault-tolerant C31 system A(0). A(I), MTBF allocations Electrostatic field measurements in a foam filled C-130 p 86 A87-15427 ENVIRONMENT EFFECTS fuel tank during fuel sloshing p 95 A87-15037 Impact of aviation on the environment The implementation and use of Ada on distributed p 132 A87-13584 systems with high reliability requirements Environmental Stress Screening (ESS) demonstrates its F [NASA-CR-1798421 p 137 N87-12265 VdllR.-. -. ..in . the.. .. field. . . .- D 177 -AA7-15403 .- FEASIBILITY ANALYSIS 1 Tailoring a major weapon environmental program --- for Aerospace plane - Fact or fantasy? F-106 'IRCRAFT p 65 A87-16396 Low Altitude Navigation and Targeting InfraredSystem for F-106 data summary and model results relative to threat I Night 5430 FEEDBACK CONTROL criteria and protection design analysis Closed loop control of an afterburning FlOO gas turbine Reverse tailoring for realistic reliability tests p 81 A87-15004 p 128 A87-15432 p 103 A87-13323 ENVIRONMENT POLLUTION Joint thunderstorm operations using the NASA F-1066 A direct method for enforcing equality constraints in Impact of aviation on the environment and FAATClAFWALConvair 580 airplanes optimal output feedback p 134 A87-13353 1 p 132 A87-13584 p 95 A87-15018 Dynamic output feedback flight control laws using ENVIRONMENTALTESTS Application of the AlPA (Approximate Iterative eigenstructure assignment p 109 A87-13355 Testing of fiber-reinforced construction elements - Preprocessing Algorithm) to F-106 data Multivariable high-gain control with feedfomard simulation of mechanical loads and environmental [AD-A1690841 p 116 N87-12569 compensation - A design technique p 134 A87-13365 influences p 92 A87-14012 F-111 AIRCRAFT Eigenstructure assignment by dynamic output I EPOXY RESINS Status report of a new recovery parachute system for feedback p 134 A87-13385 Resin-hardener systems for resin transfer molding the F111 aircraft crew escape module Extensions of a simplified continuous-time multivariable : p 120 A87-13093 [AIAA PAPER 86-24371 p 91 A87-13821 adaptive control algorithm p 134 A87-13399 I A-1 1

- SUBJECT INDEX

Multi-variablecontrol of the GE T700 engine using the Mach 6 experimental and theoretical stability and Simulator design features for helicopter landing on small LQGILTR design methodology --- Linear Quadratic performanceof a finned cylindrical body at angles of attack ships. 1: A performance study GaussianlLoop Transfer Recovery method up to 65 deg [AD-AI 695141 p 119 N87-12572 p 103 A87-13418 [NASA-TM-89050] p 76 N87-12538 Fabrication and testing of lightweight hydraulic system Optimal guidance law with first order lag loop and normal FINS Simulator hardware constraint p 86 A87-14140 Design and manufacturing of a CFRP tail fin for the [AD-A169884] p 130 N87-12711 FEEDFORWARD CONTROL A300 ’ FLIGHT CREWS Decoupling control synthesis for an oblique-wing [ MBB-UT-006-861 p 93 A87-14026 Crew seal stroke requirements for helicopter rolled aircraft p 108 A87-13342 FIRE PREVENTION attitude impact crashworthiness p 90 A87-13669 Multivariable high-gain control with feedforward Antimisting kerosene: Evaluation of low temperature Now hear this --- sound warnings lo aircrews compensation - A design technique p 134 A87-13365 performance p 80 A87-14620 Extensions of a simplified continuous-time multivariable [ DOTlFAA/CT-85/31] p 122 N87-11902 FLIGHT HAZARDS adaptive control algorithm p 134 A87-13399 FIRES Turbulent buoyant flow and pressure variations around Aircraft automatic-flight-controlsystem with inversion of Fire safety science; Proceedings of the First International an aircraft fuselage in a cross wind near the ground --- the model in the feed-forward path using a Symposium, Gaithersburg, MD. October 7-11. 1985 simulated fire in cabin p 78 A87-13187 Newton-Raphsontechnique for the inversion p 78 A87-13186 Summary of NASA storm hazards lightning research, [ NASA-TM-882091 p 116 N87-11796 Turbulent buoyant flow and pressure variations around 1980-1985 p 80 A87-15003 FIBER COMPOSITES an aircraft fuselage in a cross wind near the ground --- Joint thunderstorm operations using the NASA F-106B A healer made from graphite composite material for simulated fire in cabin p 78 A87-13187 and FAATClAFWAL Convair 580 airplanes potential deicing application FIXED WINGS p 95 A87-15018 [ NASA-TM-888881 p 101 N87-12559 NASA rotor systems research aircraft: Fixed-wing Atmospheric Electricity Hazards Protection (AEHP) FIBER OPTICS configuration flight-test results demonstration p 82 A87-15021 Actuating system with digital signal converters and [ NASA-TM-867891 p 100 N87-12557 Implementation of GEMACS for lightning interactions fiber-optic control p 93 A87-14018 FLIGHT CHARACTERISTICS analysis --- general electromagnetic model for analysis of FIBER REINFORCED COMPOSITES Questions and problems in aerodynamics --.Russian complex systems p 82 A87-15033 Fibre reinforced composites 1986; Proceedings of the book p 66 A87-13050 Runway incursions at controlled airports in the United Second International Conference. University of Liverpool. Polymer, metal. and ceramic matrix composites for States England, April 8-10, 1986 p 121 A87-13613 advanced aircraft engine applications [PB86-917003] p 84 N87-11711 Testing of fiber-reinforced construction elements - p 121 A87-15187 FLIGHT MANAGEMENT SYSTEMS Simulation of mechanical loads and environmental NASA rotor systems research aircraft: Fixed-wing Impact of mismodeled idle engine performance on influences p 92 A87-14012 configuration flight-test results calculation and tracking of optimal 4-0 descent Testing a tail rotor system in fiber-reinforcedconstruction [ NASA-TM-867891 p 100 N87-12557 trajectories p 88 A87-13360 manner p 92 A87-14016 FLIGHT CONDITIONS Rapid prototyping facility for flight research in FIGHTER AIRCRAFT Gust and maneuver spectra for general aviation artificial-intelligence-basedflight systems concepts Combined radar, ECM functions will enhance Lavi aircraft [ NASA-TM-882681 p 137 N87-12273 survivability p 101 A87-13912 [AIAA PAPER 86-2599I p 93 A87-14033 FLIGHT MECHANICS Demonstration of combat damage repair estimator Airplane flight through wind-shear turbulence Maximum likelihood estimation of parameters in p 65 A87-15436 p 80 A87-I4371 nonlinear flight mechanics systems p 113 A87-16192 Frequency domain parameter estimation of aeronautical Vortex flap technology: A stability and control Summary of NASA storm hazards lightning research, systems without and with lime delay assessment 1980-1985 p 80 A87-15003 p 114 A87-16193 [ NASA-CR-172439I p 115 N87-11795 FLIGHT CONTROL Beyond FTMP and SIFT . Advanced fault-tolerant State estimation of flying vehicle p 114 A87-16209 TSAR (Theater Simulation of Airbase Resources) computers as successors to FTMP and SIFT FLIGHT OPERATIONS database dictionary F-4E p 133 A87-13200 Development and testing of new technologies for flight [ AD-At 69575 ] p 139 N87-13352 Decoupling control synthesis for an oblique-wing operation and safely p 86 A87-14004 FILAMENT WINDING aircraft p 108 A87-13342 FLIGHT OPTIMIZATION Use of filament winding in manufacturing high quality Time scale analysis of a digital flight control system Sensitivity studies of 40 descent strategies in an aerospace composite components p 123 A87-13164 p 109 A87-13347 advanced metering environment p 88 A87-13361 FILM COOLING Flight control design using nonlinear inverse dynamics Manufacturers plan new long-range aircraft Automaled infrared inspection of let engine turbine p 109 A87-13352 p 95 A87-15181 blades p 125 A87-13719 A direct method for enforcing equality constraints in Optimal descending, hypersonic turn to heading Further shock tunnel studies of scramjet phenomena optimal output feedback p 134 A87-13353 [DE86-010989] p 120 N87-12577 [ NASA-CR-1799371 p 77 N87-12542 Dynamic output feedback flight control laws using FLIGHT PATHS FINITE DIFFERENCE THEORY eigenstructure assignment p 109 A87-13355 The method of calculating the desired flight path of An implicit lime-marching scheme for transonic flow Multivariable flight control for an attack helicopter terrain following technique with circular arc spline p 71 A87-14261 p 109 A87-13379 p 11 1 A87-14136 Comparison of absorption and radiation boundary Multivariable control of a twin lift helicopter system using State estimation of flying vehicle p 114 A87-16209 conditions in a time-domain three-dimensional the LQGILTR design methodology --- Linear Quadratic FLIGHT SAFETY finite-difference code p 82 A87-15034 Gaussian/Loop Transfer Recovery method Fire safety science; Proceedings of the First International Application of viscous-inviscid interaction methods lo p 110 A87-13419 Symposium, Gaithersburg, MD. October 7-11. 1985 transonic turbulent flows MTFCS (multiple target formation flight control system) p 78 A87-13186 Formation position sensor trade-off analysis [NASA-CR-1799OOJ p 75 N87-11700 Weather safety aspects in future civil air navigation p 110 A87-13536 The prediction of transonic loading advancing helicopter p 85 A87-13540 Combined guidance - Flight control of atmospheric rotors vehicles p 110 A87-13654 Large volume water sprays for dispersing warm fogs [AD-A168217] p 100 N87-11781 Design considerations for fly-by-wire control of new p 125 A87-13848 Computational fluid dynamic studies of certain ducted Airbus aircraft Design of a takeoff performance monitoring system bluff-body flowfields relevant to turbojet combustors. [MBB-UT-222-86] p 110 A87-13991 p 103 N87-11787 Volume 1: Time-dependent calculations with the k-epsilon Actuating system with digital signal converters and FLIGHT SIMULATION turbulence model for an existing centerbody combustor fiber-optic control p 93 A87-14018 ATTAS - The new test bed p 92 A87-14003 [ AD-At 71434) p 131 N87-12816 Optimal discrete design of digital flight control system Development and testing of new technologies for flight FINITE ELEMENT METHOD p 11 1 A87-14142 operation and safety p 86 A87-14004 Modelling strategies for finite element crash simulation Reducing complexity in fly-by-wire flight control A check of crack propagation prediction models against of complete vehicles p 90 A87-13673 actuators test results generated under transport aircraft flight Numerical solution of transonic potential flows with finite [SAE PAPER 8517521 p 112 A87-I5477 simulation loading elements method using multigrid technique A system look a1 actuation concepts and alternatives [ NLR-TR-84005-UI p 100 N87-11782 p 68 A87-13900 for primary flight control Evaluation of a visual system in its support of simulated Some observations on the behavior of the Langley model [SA€ PAPER 8517531 p 112 A87-I5478 helicopter flight rotor blade Advanced flight control actuation systems and their I AD-Al688291 p 102 N87-11783 [NASA-CR-1798801 p 74 N87-11695 interface with digital commands Design of a takeoff performance monitoring system [ SAE PAPER 851 754 I p 112 A87-15479 PIAS: A program for an iterative aeroelastic solution p 103 N87-11787 p 97 N87-11725 Sensor failure detection in flight control systems using deterministic obseivers p 114 A87-16195 The handling qualities and flight characteristics of the Influence of analysis and design models on minimum Grumman design 698 simulated twin-engine tilt Nacelle weight design p 98 N87-I 1739 State estimation of flying vehicle p 114 A87-16209 Pitot and static errors in steady level flight V/STOL aircraft On optimal design for the blade-roollhub interface in [ ESDU-86006 I p 74 N87-11691 I NASA-TM-867851 p 100 N87-12558 jet engines p 106 N87-11769 National Transportation Safety Board safety A test on the reliability and performance of the verbex A constitutive law for finite element contact problems recommendation p 83 N87-11706 series 4000 voice recognizer with unclassical friction Introduction to aerodynamics derivitives. equations of IAD-At 690661 p 130 N87-12729 I NASA-TM-88838) p 131 N87-12924 motion and stability FLIGHT SIMULATORS FINITE VOLUME METHOD [ESDU-86021I p 76 N87-12536 Motion characteristics of the UTlAS flight research Comparison of finite volume flux vector splillings for the A prototype maintenance expert system for the CH-47 simulator motion-base Euler equations p 70 A87-I4109 flight control hydraulic system IUTIAS-TN-2611 p 119 N87-11802 FINNED BODIES [ AD-A169019) p 116 N87-12568 Simulator design features for helicopter landing on small Computation of sharp-fin-inducedshock wavelturbulent Flight model discharge system ships. 1: A performance study boundary-layer interactions p 70 A87-14104 [AD-A1694231 p 117 N87-12571 IAD-At 695141 p 119 N87-12572

A-12 SUBJECT INDEX GEARS

Simulator design and instructional features for carrier FLOW RESISTANCE FUEL PUMPS landing: A field transfer study A study of the effect of surface roughness on the head FlOO fuel sampling analysis Foreign samples [ AD-At 699621 p 119 N87-12573 resistance of an aircraft p 94 A87-14717 [AD-A168573] p 122 N87-11904 FLIGHT STABILITY TESTS FLOW VELOCITY FUEL SPRAYS The handling qualities and flight characteristics of the Thrust reverser-exhaust nozzle assembly for a gas Spray charactenstics of two combined let atomizers Grumman design 698 simulated twin-engine tilt Nacelle turbine engine p 124 A87-13660 V/STOL aircraft [ AD-Wl23901 p 108 N87-12561 Performance and optimisation of an airblast nozzle . [ NASA-TM-867851 p 100 N87-12558 FLOW VISUALIZATIDN Drop size distnbution and volumetric air flow Aerodynamic characteristics and flow round cross FLIGHT TEST INSTRUMENTS p 125 A87-13828 parachutes in steady motion A small, flexible and powerful data acquisition system FUEL TANKS [AIM PAPER 86.24581 p68 A87-13798 for the F16 aircraft Electrostatic field measurements in a foam filled C-130 [NLR-MP-85074-U] p 103 N87-11786 Two-dimensional blade-vortex flow visualization fuel tank dunng fuel sloshing p 95 A87-15037 FLIGHT TESTS investigation p70 A87-14111 FUEL TESTS Aeroelastic control of oblique-wing aircraft Visualization of wing tip vortices in accelerating and Thermochemicalevaluation of fuel candidates for ramjet p 108 A87-13341 steady flow p 72 A87-14370 Evaluation of detectability and distinguishability of Visualisation of axial turbine tip clearance flow using a propulsion p 121 A87-13659 aircraft control element failures using flight test data linear cascade FULL SCALE TESTS p 110 A87-13435 [CUED/A-TURBO/TR-122] p 107 N87-12560 KRASH analysis correlation with full scale YAH-63 Low cost aerial testing of parachutes FLUID DYNAMICS helicopter crash test p 90 A87-13674 [AIAA PAPER 86-24721 p79 A87-13806 Characterizationand dynamical studies of polymers in The design and qualification testing of an The amphibian technology test vehicle - Summary and dipolar (aprotic) liquids energy-absorbtng seat for the Navy's H-53 AID results p 91 A87-13992 [ADA1692431 p 123 N87-12685 helicopters p 91 A87-13679 Testing a tail rotor system in fiber-reinforcedconstruction FLUID FILMS FUSELAGES manner p 92 A87-14016 The effect of lubncant cavitation on the characteristics Structure-componenttests for a CFK fuselage Reliability growth dunng flight test p 127 A87-15412 of a short hydrodynamic damper p 127 A87-15203 [ MBB-UT-223.861 p 121 A87-14001 Flight test report of the NASA icing research airplane: FLUIDSOLID INTERACTIONS New fuselage technologies for general-aviationaircraft Performance. stability. and control after flight through Noise of high speed surfaces p 138 A87-13595 p 93 A87-14027 natural icing conditions FLUTTER Turbulent flow around a wing/fuselage-typeluncture [ NASA-CR-1795151 p 116 N87-11797 Aircraft fluner suppression via adaptive LQG control p 70 A87-14108 p 109 A87-13344 NASA rotor systems research aircraft: Fixed-wing A study of the effect of surface roughness on the head Load lightening and fluner damping for future Airbus configuration flight-test results resistance of an aircraft p 94 A87-14717 [ NASA-TM-867891 p 100 N87-12557 projects Computation of optimum-optimorum wing-fuselage Evaluation of a nonlinear parameter exlraction [MBB-UT-004-86] p 92 A87-14002 configuration for future generabon of supersonic aircraft mathematical model including the term C(subm(sub delta Adaptive fluner suppresson p 113 A87-16182 p 74 A87-15761 e squared)) Optimization of cascade blade mistuning under fluner [ NASA-TM-877311 p 116 N87-12566 and forced response constraints p 106 N87-11732 FLIGHT TIME Application of optimization techniques lo the design of General aviation activity and avionics survey a fluner Suppression control law for the DAST ARW-2 G [[email protected]] p65 N87-11686 p 115 N87-11736 FLOATS FLUTTER ANALYSIS GAS DYNAMICS Experimental study of the interactin between an arc Aeroelastic control of oblique-wing aircraft Numerical solution of the Euler equation for and an electrically floating Structure p 126 A87-15023 p 108 A87-13341 compressible inviscid fluids p 69 A87-14095 FLOW CHARACTERISTICS Direct solution of flutter equations with interactive Some asymptotic types of transonic vortex flows Vectorizable multigrid algorithms for transonic-flow graphics procedure p 110 A87-13648 p 74 A87-15553 calculations p 72 A87-14652 Concentrated mass effects on the fluner of a composite Further shock tunnel studies of scramjet phenomena The use of mathematical models in aerodynamics (The advanced turboprop model [ NASA-CR-1799371 p 77 N87-12542 W. Rupert Turnbull Lecture) p 72 A87-15189 [NASA-TM-68854] p 130 N87-12017 GASGENERATORS The prediction of transonic loading advancing helicopter FLY BY TUBE CONTROL Further development of the axial-radial compressor rotors Optimal stochastic ObSeNerS applied to hydraulic p 104 A87-13998 [AD-A168217] p :00 N87-11781 actuation systems p 87 A87-13354 New-technology gas generator (GNT 1) - The actual FLOW DEFLECTION FLY BY WIRE CONTROL state of development p 126 A87-14006 Effect of an upstream wake on a pusher propeller Design considerations for fly-by-wire control of new GAS TURBINE ENGINES [AIM PAPER 86-26021 p 69 A87-14035 Airbus aircraft Closed loop control of an afterburning F100 gas turbine FLOW DISTRIBUTION [ MBB-UT-222-861 p 110 A87-13991 engine p 103 A87-13323 Turbulent flow around a wing/fuselage-type juncture Redundant computer system for fly-by-wire controls Improving the energy efficiency of cooled p 70 A87-14108 p 111 A87-14013 high-temperatureturbines p 104 A87-13990 Special Opportunities in helicopter aerodynamics Reducing complexity in fly-by-wire flight control New-technology gas generator (GNT 1) ~ The actual p 74 A87-15469 ac 1 u a to r s state of development p126 A87-14006 An experimental study of the aerodynamics of a NACA [SAE PAPER 8517521 p 112 A87-15477 Methods for the assembly and testing of the bearing 0012 airfoil with a simulated glaze ice accretion Parameter estimation of aircraft with fly-by-wire control supports of gas turbine engines --- Russian book [ NASA-CR-1798971 p 75 N87-11701 systems p 113 A87-16186 p 126 A87-14683 Viscous-inviscid interaction in transonic separated flow Development of an advanced vaneless inlet particle A320 Fly-by-wireairliner p 96 A87-16394 over solid and porous airfoils and cascades - separator for helicopter engines p 105 A87-14984 p 76 N87-12535 FOG DISPERSAL Usingvibration spectrum characteristicsforthe flow-path Analysis and verification of the icing scaling equations. Large volume water sprays for dispersing warm fogs diagnostics of aircraft gas turbine engines Volume 1: Revision p 125 A87-13848 p 105 A87-15210 [ AD-A1679761 p 85 N87-12551 FORMAT Turbines with counter-rotating rotors for aircraft power Effectsof test cell recirculation on high-bypassturbofan A test on the reliability and performance of the verbex plants p 106 A87-15211 engines dunng simulated altitude tests series 4000 voice recognizer A study of local heat transfer on the face surface of a [AD-A171418] p 108 N87-12565 [ADA1690661 p 130 N87-12729 nozzle ring model p 127 A87-15215 Computational fluid dynamic studies of certain ducted FRACTURE MECHANICS A study of the effect of the temperature factor on bluff-body flowfields relevant lo turbojet combustors. Carburizing steel for high temperature service pressure losses in the cooling system of the leading edge Volume 1: Timedependent calculations with the k-epsilon [ AD-A1683271 p 122 N87-11877 of a deflector vane -.-for gas turbine engines turbulence model for an existing centerbody combustor Analysis of mixed-mode crack propagation using the p 127 A87-15218 [AD-A171434] p 131 N87-12816 boundary integral method STAEBL Structural tailoring of engine blades, phase 2 FLOW EQUATIONS [NASA-CR-l79518] p 131 N87-12915 p 106 N87-11731 Constant-density approximation lo Taylor-Maccoll FREE FLOW Control of gas turbines. The future: Is a radical approach solution p 71 A87-14127 Large-scale coherent structures in free turbulent flows needed? --- aircraft engines Modeling of turbulent separated flows for aerodynamic and their aercdynamic sound p 138 A87-15458 [PNR-90295] p 107 N87-11793 applications p 73 A87-15454 FRICTION Advanced Gas Turbine (AGT) Technology Project FLOW GEOMETRY A constitutive law for finite element contact problems [ NASA-CR-1794841 p 130 N87-11995 Spray characteristics of two combined let atomizers with unclassical friction Thrust reverser-exhaust nozzle assembly for a gas p 124 A87-13660 [NASA-TM-88838I p 131 N87-12924 turbine engine Theoretical studies of the ETW diffuser and of the [AD-D012390] p 108 N87-12561 second throat p 69 A87-14022 FUEL COMBUSTION GAS TURBINES Combustion studies of metallized fuels for solid-fuel Experimentaland numerical investigation of supersonic The effect of turbine elements on the gasdynamic ramjets p 121 A87-14982 turbulent flow through a square duct p 70 A87-14117 stability margin p 105 A87-15208 Effect Of two endwall contours on the performance of FUEL CONSUMPTION Research on mechanical properties for engine life an annular nozzle cascade p 71 A87-14119 Sensitivity studies of 4D descent strategies in an prediction Start-up of a wind tunnel with a multichannel diffuser advanced metering environment p 88 A87-13361 [AD-A1695701 p 108 N87-12563 p 72 A87-15206 FUEL CONTROL GAUSS EQUATION FLOW MEASUREMENT Variable structure control of a turbojet engine Aeroelastic control of oblique-wing aircraft Experimental and numerical investigation of supersonic p 103 A87-13343 p 108 A87-13341 turbulent flow through a square duct p 70 A87-14117 Polymer, metal. and ceramic matrix composites for GEARS Laser velocimetry for transonic aerodynamics advanced aircraft engine applications Finite element contact analysis of ring gear and p 74 A87-15467 p 121 A87-15187 support p 127 A87-15193

A-13 GENERAL AVIATION AIRCRAFT SUBJECT INDEX

GENERAL AVIATION AIRCRAFT HARDENERS HELICOPTERS Impact severity and potential injury prevention in general Resin-hardenersystems for resin transfer molding Multi-variable control of the GE T700 engine using the aviation accidents p 79 A87-13687 p 120 A87-13093 LQGILTR design methodology --- Linear Quadratic Impetus of new technologies for utility, executive. and HARDNESS GaussianlLoop Transfer Recovery method commuter aircraft p 104 A87-14000 Carburizing steel for high temperature service p 103 A87-13418 N~Wfuselage technologies for general-aviationaircraft [ AD-A1683271 p 122 N87-11877 Multivariablecontrol of a twin lie helicopter system using p 93 A87-14027 HARMONICS the LQG/LTR design methodology --- Linear Quadratic Gust and maneuver spectra for general aviation Cruise noise of counterrotation propeller at angle of Gaussian/Loop Transfer Recovery method aircraft attack in wind tunnel p 110 A87-13419 [AIAA PAPER 86-25991 p 93 A87-14033 [ NASA-TM-888691 p 139 N87-13252 Landing gear performance simulation by KRASH program p 90 A87-13670 Potential influences of heavy rain on general aviation HARRIER AIRCRAFT airplane performance AV-8BIGR Mk airframe composite applications Computer modeling of crashworthy seating systems 5 p 90 A87-13671 [AIAA PAPER 86-26061 p 94 A87-14036 p 88 A87-13628 General aviation cost eff8CtNeneSS KRASH analysis correlation with full scale YAH-63 HEATTRANSFER [AIAA PAPER 86-26071 p 139 A87-14037 helicopter crash test p 90 A87-13674 A study of local heat transfer on the face surface of a General aviation activity and avionics survey Realistic civil helicopter crash safety noale ring model p 127 A87-15215 [AD-A1685821 p65 N87-11686 p 78 A87-13684 Aircraft accident reports: Brief format. US civil and Further shock tunnel studies of scramjet phenomena Simulated lightning current tests on a Lynx helicopter foreign aviation. issue number 5 of 1985 accidents [ NASA-CR-1799371 p 77 N87-12542 p 95 A87-15011 [ PB86-9169191 p83 N87-11710 Visualisation of axial turbine tip clearance flow using a Prediction of skin currents flowing on a Lynx helicopter Aircraft accident reports: Brief format, US civil and linear cascade due to a simulated lightning strike p 95 A87-15012 foreign aviation, issue number 4 of 1985 accidents [CUEDIA-TURBO/TR-1221 p 107 N87-12560 Assessing the RBM attributes of advanced StrUCtUreS [PB86-916918] p 84 N87-11712 HEATERS --- Reliability 8 Maintainability of composite helicopters Aircraft accident reports: Brief format, US civil and A heater made from graphite composite material for p 96 A87-15424 foreign aviation. issue number 3 of 1985 accidents potential deicing application Special opportunities in helicopter aerodynamics [PB86-916917] p 84 N87-11713 [ NASA-TM-888881 p 101 N87-12559 p 74 A87-15469 Review of accident data: US general aviation calendar HELICOPTER CONTROL A brief introduction to the helicopter year 1982 Multivariable flight control for an attack helicopter (NLR-MP-85062-UI p 65 N87-11688 [ PB86-201910] p84 N87-11714 p 109 A87-13379 Recent Experiences in Multidisciplinary Analysis and GEOMETRY Possibilitiesfor Optimizationand higher-harmoniccontrol Optimization. part 2 Vertical deflection characteristics of aircraft tyres of helicopter main rotors by blade feathering [ NASA-CP-2327-PT-21 p 99 N87-11750 [ ESDU-860051 p 129 N87-11992 p 111 A87-14021 Application of modernstructural optimizationto vibration reduction in rotorcraft p 115 N87-11752 GLASS FIBER RZINFORCED PLASTICS A brief introduction to the helicopter The hp split-torque helicopter transmission Development of a GFRP wing in accordance with FAR [ NLR-MP-85062-UI p 65 N87-11688 3600 Part 23 p 92 A87-13993 [NASA-CR-174932] p 106 N87-11788 Obstacle-warning radar for helicopters GLIDE PATHS Compound cycle engine program p 132 N87-13149 Guidance law simulationstudies for complex approaches [ NASA-TM-88879I p 107 N87-11790 using the Microwave Landing System (MLS) HELICOPTER DESIGN FAA helicopterlheliport research. engineering, and [NASA-CR-178182] p 87 N87-12552 Evolution of MIL-STD-l29OA,light fixed and rotary-wing development bibliography, 1964-1986 GLIDERS aircraft crashworthiness p 89 A87-13663 [FAAIPM-86/47] p 118 N87-11798 Mathematical modeling of the motion of a statically The status of crashworthinessdesign criteria The 8 m x 6 m low speed wind tunnel at the Chinese deformed delta-shaped glider p 95 A87-15205 p 89 A87-13664 Aerodynamic Research and Development Center GLOBAL POSITIONING SYSTEM Survivability and crashworthiness design criteria [AD-A168448] p 119 N87-11803 ION, National Technical Meeting. Long Beach. CA. p 89 A87-13665 Introduction to helicopter noise January 21-23. 1986. Proceedings p 85 A87-13532 Design of airframe structures for crash impact [ISL-NB-401/84] p 139 N87-12327 Navstar Global Positioning Systems Collins user p 90 A87-13668 Simulator design features for helicopter landing on small equipment - An evolutionary assessment Crew seat stroke requirements for helicopter rolled ships. 1: A performance study p 85 A87-13533 attitude impact crashworthiness p 90 A87-13669 [ AD-A16951 41 p 119 N87-12572 The siting. installation and operational suitability of the Combining Loran and GPS . The best of both worlds Analysis of U.S. civil rotorcraft accidentsfor development p A87-13544 Automated Weather Observing System (AWOS) at 86 of improved design criteria p 78 A87-13685 GRAMMARS heliports Results of helicopter research at DFVLR A test on the reliability and performance of the verbex [DOT/FAA/PM-86/30] p 133 N87-13099 p 91 A87-13987 series 4000 voice recognizer HELIPORTS [ AD-A169066 I p 130 N87-12729 Improvement of mathematical models of helicopters by FAA helicopterlheliport research. engineering. and GRAPHITE-EPOXY COMPOSITES analytical presentation of nonlinear aerodynamics development bibliography, 1964-1986 A heater made from graphite composite material for p 69 A87-13995 FAAIPM-86/47] p 118 N87-11798 potential deicing application Avionics systems for future commercial helicopters The siting. installation and operational suitability of the [NASA-TM-88888] p 101 N87-12559 p 101 A87-14005 Automated Weather observing System (AWOS) at GROUND EFFECT (AERODYNAMICS) Models for rotor and helicopter design heliports Interaction of decaying trailing vortices in ground p 92 A87-14008 [ DOT/FAAIPM-86/30I p 133 N87-13099 shear p 66 A87-13499 Development of a new type of bearingless rotor HEURISTIC METHODS The induced aerodynamics of jet and fan powered system p 93 A87-14017 Influence of analysis and design models on minimum V/STOL aircraft p 73 A87-15459 A brief introduction to the helicopter weight design p 98 N87-11739 Multiple jet impingement flowfields p 73 A87-15461 [NLR-MP-85062-U] p 65 N87-11688 HIGH ASPECT RATIO GROUND SUPPORT EQUIPMENT Overview: Applications of numerical Optimization Study of a bounded jet flow considering the initial Ground aircraft deicing technology review methods to helicopter design problems turbulence. II - In the case of relatively large nozzle aspect [DOT/FAA/CT-85/21 I p 83 N87-11707 p 99 N87-11751 ratio p 71 A87-14263 GROUND TESTS Helicopter rotor blade aerodynamic Optimization by HIGH LEVEL LANGUAGES Testing a tail rotor system in fiber-reinforced construction mathematical programming p 99 N87-11753 Grundy - Parallel processor architecture makes manner p 92 A87-14016 A rotor optimization using regression analysis programming easy p 135 A87-13703 GROUNDTRUTH p 136 N87-11755 HIGH REYNOLDS NUMBER Ground-baseddetection of aircrafl icing conditions using Application of numerical optimization to rotor Vortex shedding of a square cylinder in front of a slender microwave radiometers p 80 A87-I4861 aerodynamic design p 99 N87-11757 airfoil at high Reynolds numbers. Part 2: Compressibility GROUND WIND Aeroelaslic-aerodynamic optimization of high speed effect Turbulent buoyant flow and pressure variations around helicopter-compound rotor p 99 N87-11758 [ MPIS-24/1985] p 75 N87-11704 an aircraft fuselage in a cross wind near the ground --- HELICOPTER ENGINES HIGH TEMPERATURE GASES simulated fire in cabin p 78 A87-13187 Development of an advanced vaneless inlet particle Improving the energy efficiency of cooled GUST LOADS separator for helicopter engines p 105 A87-14984 high-temperatureturbines p 104 A87-13990 The effect of random wind gusts on the stability of a Compound cycle engine program HIGHLY MANEUVERABLE AIRCRAFT parachute system p 72 A87-15216 [ NASA-TM-888791 p 107 N87-11790 Forward-swept wing configuration designed for high Blast gust loading on a 35 degree swept-back wing HELICOPTER PERFORMANCE maneuverability by use of a transonic computational [ ADA1 6941 5 I p 116 N87-12570 Full scale crash test of a BK117 helicopter method GUSTS p 91 A87-13678 I NASA-TP-26281 p 75 N87-11702 Influence of airfoil mean loading on convected gust Airworthiness considerations of lightning strike HINGES interaction noise p 137 A87-13587 protection for helicopter digital engine controls Renewed interest in hinge moment models for failure Gust and maneuver spectra for general aviation p 105 A87-15010 detection and isolation p 110 A87-13426 aircraft The 3600 hp split-torque helicopter transmission HISTORIES [AIAA PAPER 86-25991 p 93 A87-14033 [ NASA-CR-174932I p 106 N87-11788 Technical-historical development of parachutes and HELICOPTER TAIL ROTORS their applications since World War I Testing a tail rotor system in fiber-reinforcedconstruction LAIAA PAPER 86-2423I p 79 A87-13777 H manner p 92 A87-14016 HONEYCOMBCORES HELICOPTER WAKES Repair of composite components - A Navy approach H-53 HELICOPTER Vortex panel calculation of wake rollup behind a large p 117 A87-13122 The design and qualification testing of an aspect ratio wing p 70 A87-14102 HOT ISOSTATIC PRESSING energy-absorbing seat lor the Navy's H-53 AID Two-dimensional blade-vortex flow visualization Fabrication of cooled radial turbine rotor helicopters p 91 A87-13679 investigation p 70 A87-14111 1 NASA-CR-1795031 p 107 N87-11789

A-14 SUBJECT INDEX LANDING

HOVERING INDEPENDENT VARIABLES ITERATIVE SOLUTION Multiple let impingement flowfields p 73 A87-15461 Reachable outputs in systems with bounded parameter PIAS: A program for an iterative aerwlastic solution

Recent advances in prediction methods for jet-induced uncertainties ~ Application to (allure detection D 97 N87-11725 effects on V/STOL aircraft p 73 A87-15462 p 134 A87-13326 HOVERING STABILITY INDICATING INSTRUMENTS Application of time-domain unsteady aerodynamics lo Theoretical and experimental investigations of sensor J rotary-wing aeroelasticily p 94 A87-14103 location for optimal aeroelastic system state estimation HUBS p 115 N87-11794 JACKS (LIFTS) INERTIAL PLATFORMS On optimal design for the blade-rootlhub interface in Multivariable control of a twin lift helicopter system using jet engines p 106 N87-11769 In-flight transfer alignmentlcalibration of a strapdown the LQGILTR design methodology --- Linear Quadratic HUMAN TOLERANCES INS that employs carouseled instruments and IMU GaussianlLoop Transfer Recovery method Crashworthy crewseat limit load optimization through indexing p 85 A87-13438 p 110 A87-13419 dynamic testing p 91 A87-13675 INFLATING JAPAN HYDRAULIC CONTROL Automatic variable reefing of parachutes by application Possible military applications of stratospheric airship of inflation forces A redundant actuating system with servo valves of low discussed p 101 N87-12716 hydraulic loss p 93 A87-14025 [AIM PAPER 86-24341 p 79 A87-13784 JET AIRCRAFT Notes on a generic parachute opening force analysis Energy efficient actuation using variable displacement All-digital jets are taking off p 102 A87-14352 hydraulic control [AIM PAPER 86-24401 p 67 A87-13788 INFORMATION DISSEMINATION TSAR (Theater Simulation of Airbase Resources) [SA€ PAPER 8517571 p 112 A87-15481 database dictionary F-4E HYDROCARBON COMBUSTION Optimization in the systems engineering process p96 N87-11719 [AD-A169575] p 139 N87-13352 Long-term deposit formation in aviation turbine fuel at JET AIRCRAFT NOISE elevated temperature p 121 A87-14986 INFRARED IMAGERY Automated infrared inspection of jet engine turbine For small airliners and executive jets HYDRODYNAMICS p 105 A87-15179 The effect of lubricant cavitation on the characteristics blades p 125 A87-13719 INFRARED INSPECTION JET ENGINE FUELS of a short hydrodynamic damper p 127 A87-15203 Automated infrared inspection of jet engine turbine FlOO fuel sampling analysis: Foreign samples Characterization and dynamical studies of polymers in [AD-A168573] p 122 N87-11904 dipolar (aprotic) liquids blades p 125 A87-13719 INJURIES Aviation turbine fuels, 1985 [ AD-A1 69243 ] p 123 N87-12685 [ DE86-0121401 p 122 N87-11908 HYPERSONIC AIRCRAFT Impact severity and potential injury preventionin general aviation accidents p 79 A87-13687 JET ENGINES Ames accelerates research on hypersonic technology Development of high-alumina ceramic materials suitable p 64 A87-13911 INSTRUMENT COMPENSATION Investigation of magnetometer enors and their for making jet engine fixtures p 120 A87-13092 HYPERSONIC FLIGHT On optimal design for the blade-rootlhub interface in Optimal descending, hypersonic turn lo heading cornpensation in the 80-105 helicopter [DFVLR-FB-86-21] p 102 N87-11784 jet engines p 106 N87-11769 [ DE86-0109891 p 120 N87-12577 JET FLOW HYPERSONIC FLOW INSTRUMENT ERRORS Investigation of magnetometer errors and their Spray characteristics of two combined jet atomizers Constant-density approximation to Taylor-Maccoll p 124 A87-13660 solution p 71 A87-14127 compensation in the 60-105 helicopter [DFVLR-FB-86-21] p 102 N87-11784 The induced aerodynamics of jet and fan powered HYPERSONIC VEHICLES V/STOL aircraft p 73 A87-15459 Ames accelerates research on hypersonic technology INSTRUMENT LANDING SYSTEMS Aircraft accidentlincident summary reports: Erie, JET IMPINGEMENT p 64 A87-13911 Multiple ]et impingement flowfields p 73 A87-15461 HYSTERESIS Pennsylvania, October 14, 1984; Albuquerque, New Mexico, February 11, 1985 Recent advances in prediction methods for jet-induced Motion characteristics 01 the UTlAS flight research [ PB86-9104071 p 84 N87-12549 effects on V/STOL aircraft p 73 A87-15462 simulator motion-base JET PROPULSION [UTIAS-TN-261] p 119 N87-11802 INTAKE SYSTEMS Journal 01 engineenng thermophysics (selected Prospective, characteristics and problems of the use articles) of boron in different air augmented propulsion modes I [ AD-A1894521 p 139 N87-13347 [IAF PAPER 86.1911 p 122 A87-15924 INTEGRAL EOUATIONS JOINTS (JUNCTIONS) ICE Comparison of numerical solutions of lower order and Some effects of moisture on adhesive-bonded An experimental study of the aerodynamics of a NACA higher order integral equation methods for two-dimensional CFRP-CFRP joints p 129 A87-16160 0012 airfoil with a simulated glaze ice accretion aerofoils JP-4 JET FUEL [ NASA-CR-1798971 p 75 N87-11701 [AIM PAPER 86-25911 p 69 A87-14028 F100 fuel sampling analysis: Foreign samples Analysis and verification of the icing scaling equations. Performance evaluation of an inverse integral equation [ AD-A1685731 p 122 N87-11904 Volume 1: Revision method applied to turbomachine cascades JP-8 JET FUEL FlOO fuel sampling analysis: Foreign samples [AD-A167976] p 85 N87-12551 p 72 A87-14771 ICE FORMATION INTERACTIONALAERODYNAMICS [ AD-A1685731 p 122 N87-11904 Ground-baseddetection of aircraft icing conditions using Interaction of decaying trailing vortices in ground microwave radiometers p 80 A87-14861 shear p 66 A87-13499 K Flight test report of the NASA icing research airplane: Computation of sharpfin-inducedshock wave/turbulent Performance, stability. and control alter flight through boundary-layer interactions p 70 A87-14104 KALMAN FILTERS natural icing conditions Two-dimensional blade-vortex flow visualization Aircraft flight data compatibility checking using maximum [ NASA-CR-1795151 p 116 N87-11797 investigation p 70 A87-14111 likelihood and extended Kalman filter estimation Analysis and verification of the icing scaling equations. Direct-inverse transonic wing analysis-design method p 113 A87-16184 Volume 1: Revision with viscous interaction p 71 A87-14365 KAWASAKI AIRCRAFT [ AD-A1679761 p 85 N87-12551 Recent advances in prediction methods for jet-induced Full scale crash test of a BK117 helicopter ICE PREVENTION effects on V/STOL aircraft p 73 A87-15462 p 91 A87-13678 Ground aircraft deicing technology review Propellarlbody interactbn for IhNSt and drag KEROSENE [DOT/FAA/CT-85121] p 83 N87-11707 [ ESDU-860171 p 76 N87-12537 Antimisting kerosene: Evaluation of low temperature IGNITION LIMITS INTERFACES performance Minimum ignition levels of aircraft fuel constituents to On optimal design for the blade-rootlhub interface in [ DOTIFAAICT-85/31 I p 122 N87-11902 lightning related ignition sources p 83 A87-15038 jet engines p 106 N87-11769 KINEMATICS IGNITION TEMPERATURE INTERLAYERS Introduction to aerodynamics derivitives. equations of Prospective, characteristics and problems of the use Diffusion bonding of certain refractory metals motion and stability of boron in different air augmented propulsion modes p 121 A87-13171 [ ESDU-860211 p 76 N87-12536 [IAF PAPER 86-1911 p 122 A87-15924 INTERNAL COMBUSTION ENGINES KINETIC FRICTION IMAGE PROCESSING Advanced Gas Turbine (AGT) Technology Project Frictional and retarding forces on aircraft lyres. Part 4: [ NASA-CR-1794841 p 130 N87-11995 Wholefield displacement measurements using speckle Estimation of effects 01 yaw image processing techniques for crash tests INVISCID FLOW [ESDU-86016-PT-4] p 131 N87-12868 p 124 A87-13680 Shock boundary layer interactions in laminar transonic KNUDSEN FLOW IMPACT DAMAGE flow over airfoils using a hybrid method Determination 01 the regime coefficients in the local Crash dynamics program transport seat performance p 66 A87-13503 theory of interaction from plate data p 74 A87-15561 and cost benefit study Numerical calculation of three-dimensional inviscid [ DOT/FAA/CT-85/36] p 83 N87-11708 supersonic flows p 66 A87-13504 IMPACT TESTS Numerical solution of the Euler equation for L Full scale crash test of a BK117 helicopter compressible inviscid fluids p 69 A87-14095 p 91 A87-13678 An implicit time-marching scheme for transonic flow LAMINAR BOUNDARY LAVER Crash dynamics program transport seat performance p 71 A87-14261 Shock boundary layer interactions in laminar transonic and cost benefit study Viscous-inviscid interaction in transonic separated flow flow over airfoils using a hybrid method [DOT/FAA/CT-85/36] p 83 N87-11708 over solid and porous airfoils and cascades p 86 A87-13503 IN-FLIGHT MONITORING p 76 N87-12535 LAMINAR FLOW In-flight transfer alignmentlcalibration of a strapdown ITERATION Spanwise variation of laminar separation bubbles on INS that employs carouseled instruments and IMU Application of viscous-inviscid interaction methods lo wings at low Reynolds number p 71 A87-14362 indexing p 85 A87-13438 transonic turbulent flows LANDING INCOMPRESSIBLE FLOW [NASA-CR-179900] p 75 N87-11700 Guidance law simulation studies for complex approaches Vortex-sheet capturing in numerical solutions of the Multidisciplinary systems optimization by linear using the Microwave Landing System (MLS) incompressible Euler equations p 70 A87-14099 decomposition p 136 N87-11740 [ NASA-CR-1781821 p 87 N87-12552

A-15 LANDING GEAR SUBJECT INDEX

LANDING GEAR Comparison of electromagnetic measurements on an Synthesis of devicesfor the optimal processing of pulsed Landing gear performance smulation by KRASH aircraft horn direct lightning anachment and simulated radio signals in LORAN systems p 86 A87-15563 program p 90 A87-13670 nuclear electromagnetic pulse p81 A87-15015 LORAN C A simulation of the dynamics of the mechanisms of the Analysis of the first milliseconds of aircraft lightning Improving Loran coverage at minimum cost aircraft landing gear p 96 A87-15220 attachment p 81 A87-15016 p 86 A87-13543 LANDING LOADS Current levels and distributions on an aircraft during LOW ALTITUDE The equivalent masses at nose landing-gears during ground lightning simulation tests and in-flight lightning The Annular Parachute - An approach to a low altitude landing-impacts and when taxiing over runway attachments p 82 A87-15017 personnel parachute perturbations p 88 A87-13637 Joint thunderstorm operations using the NASA F-106B [AIAA PAPER 86-24491 p 80 A87-13823 Average landing force dependence on length and and FAATCIAFWAL Convair 580 airplanes LOW NOISE direction of landing, parachute velocity components and p 95 A87-15018 For small airliners and executive lets wind speed p 105 A87-15179 [AIAA PAPER 86-24521 p 79 A87-13794 Experimental study of the interaction between an arc and an electrically floating structure p 126 A87-15023 LANDING SIMULATION LOW REYNOLDS NUMBER Guidance law simulation studies for complex approaches Corona from simulated aircraft surfaces and their Spanwise variation of laminar separation bubbles on using the Microwave Landing System (MLS) contribution to the triggered discharge wings at low Reynolds number p 71 A87-14362 [NASA-CR-1781821 p 87 N87.12552 p 82 A87-15024 LOW SPEED WIND TUNNELS LANDING SITES Expenmental calibration of an aircraft vectorelectric field Exploratory wind-tunnel investigation of the stability and Electroluminescent (EL) remotely-controlled landing meter system p 102 A87-15028 control Characteristics of advanced general aviation zone marker light system Lightning return stroke current computation configurations [AD-DO1 23861 p87 N87-11716 p 126 A87-15029 [AIAA PAPER 86-25961 p 111 A87-14031 LASER DOPPLER VELOCIMETERS Implementation of GEMACS lor lightning interactions Wind-tunnel investigation of the OMAC canard Laser velocimetry for transonic aerodynamics analysis --- general electromagnetic model for analysis of configuration , p 74 A87-15467 complex systems p 82 A87-15033 (AIM PAPER 86-26081 p 69 A87-14038 LASER INTERFEROMETRY Comparison of absorption and radiation boundary The 8 m x 6 m low speed wind tunnel a1 the Chinese Research on mechanical properties for engine life conditions in a time-domain three-dimensional Aerodynamic Research and Development Center prediction finite-differencecode p 82 A87-15034 [ AD-A1684481 p 119 N87-11803 [ AD-AI 695701 p 108 N87-12563 Minimum ignition levels of aircraft fuel constituents to LOW TEMPERATURE ENVIRONMENTS LATERAL CONTROL lightning related ignition sources p 83 A87-15038 Ground aircraft deicing technology review Decoupling control synthesis for an oblique-wing Atmospheric electrical modeling in support of the NASA [DOT/FAA/CT-85/21 I p 83 N87-11707 aircraft p 108 A87-13342 F106 Storm Hazards Project LOW TEMPERATURE TESTS LEADING EDGES [NASA-CR-179801I p 132 N87-12082 DNLR cryogenic-wind-tunnel and model technology Exploratory wind-tunnel investigationof the stability and LIGHTNING SUPPRESSION D 117 A87-14024 control characteristics of advanced general aviation F-106 data summary and model results relative to threat LUBRICANTS configurations criteria and protection design analysis The effect of lubricant cavitation on the characteristics [AIAA PAPER 86.25961 p 111 A87-14031 p 81 A87-15004 of a short hydrodynamic damper p 127 A87-15203 Wind-tunnel investigation of the OMAC canard Comparison of low level frequency domain lightning configuration simulation test lo pulse measurements --- on modified i [AlAA PAPER 86-26081 p 69 A87-14038 F-14A aircraft p 126 A87-15007 M An experimental study 01 the aerodynamics of a NACA Zoning of aircraft for lightning anachment and current 0012 airfoil with a simulated glaze ice accretion transfer p94 A87-15009 MACH NUMBER [NASA-CR-179897] p 75 N87-11701 Airworthiness considerations of lightning strike Mach 6 experimental and theoretical stability and PIAS A program for an iterative aeroelastic solution protection for helicopter digital engine controls p 97 N87-11725 performance of a finned cylindrical body at angles of attack p 105 A87-15010 up to 65 deg LEARNING THEORY Atmospheric Electricity Hazards Protection (AEHP) [ NASA-TM-890501 p 76 N87-12538 A dynamic model for airframe cost estimation demonstration p 82 A87-15021 [AD-A168842] p 65 N87-11687 Aircraft lightning-induced transient test and protection MAGNETOMETERS Investigation of magnetometer errors and their LIFE (DURABILITY) comparison p 82 A87-15022 Selection of rolling-element bearing steels for long-life LINEAR EQUATIONS compensation in the BO-105 helicopter [ DNLR-FB-86-21 ] p 102 N87-11784 application Aeroelastic control of oblique-wing aircraft (NASA-TM-888811 p 129 N87-11993 p 108 A87-13341 MAINTAINABILITY Research on mechanical properties for engine life LINEAR SYSTEMS Novel composite repair methods p 123 A87-13123 prediction Aircraft fluner suppression via adaptive LQG control RAM) automated RBM package (RAMP) (AD-Al695701 p 108 N87-12563 p 109 A87-13344 p 128 A87-15417 LIFT LiauiD ATOMIZATION Assessing the RBM anributes of advanced slructures Combination of suction and tangential blowing in Large volume water sprays for dispersing warm fogs --- Reliability 8 Maintainability of composite helicopters boundary layer control p67 A87-13641 p 125 A87-13848 p 96 A87-15424 Aerodynamic coefficients of a circular wing in steady Characterization and dynamical studies of polymers in Application of Markov models for RMA assessment --- subsonic flow p 67 A87-13653 dipolar (aprotic) liquids Reliability, Maintainability and Availability LIFT AUGMENTATION [AD-A169243] p 123 N87-12685 p 128 A87-15435 Turbine bypass remote augmentor lift system for LiamSLOSHING MANCOMPUTER INTERFACE V/STOL aircraft p 105 A87-14364 Electrostaticfield measurements in a foam filled C-130 A test on the reliability and performance of the verber LIFTING BODIES fuel tank during fuel sloshing p 95 A87-15037 series 4000 voice recognizer Analysis of a composite thin-walled aircrall structure LOAD TESTS [AD-A169066] p 130 N87-12729 p 127 A87-15226 Development and testing of critical components for the MANUFACTURING LIGHT AIRCRAFT technological preparation of a CFK outer wing Evolutionof MIL-STD-l290A, light fixed and rotary-wing Advanced manufacturing technology for Structural [ MBB-UT-224.861 p 92 A87-13997 aircraft/aerospace components p 123 A87-13074 aircraft crashworthiness p 89 A87-13663 Testing of fiber-reinforced construction elements - LIGHTING EQUIPMENT Simulation of mechanical loads and environmental Resin-hardener systems for resin transfer molding p 120 A87-13093 Electroluminescent (EL) remotely-controlled landing influences p 92 A87-14012 zone marker light system LOADS (FORCES) Use of filament winding in manufacturing high quality [ AD-DO1 23861 p 87 N87-11716 Vertical deflection characteristics of aircraft lyres aerospace composite components p 123 A87-13164 LIGHTNING [ ESDU-860051 p 129 N87-11992 MAPPING International Aerospace and Ground Conference on Analysis of mixed-mode crack propagation using the A review of microbursts and their analysis and detection Lightning and Static Electricity. 1lth. Dayton, OH, June boundary integral method with Doppler radar 24-26. 1986. Technical Paprs p 80 A87-15001 [ NASA-CR-1795181 p 131 N87-12915 [ AD-At 704581 p 133 N87-13110 A review of aerospace and ground lightning threat LOGIC CIRCUITS MARKOV PROCESSES characteristics and applications p 132 A87-15002 Microelectronicsin aircraft systems --- Book Application of Markov models for RMA assessment -.. Summary of NASA storm hazards lightning research, p I01 A87-13469 Reliability. Maintainability and Availability 1980-1985 p 80 A87-15003 LOGIC DESIGN p 128 A87-15435 Interpretationof a class of in-flight lightning signatures A System model. a logic design diagram, and a general An efficientdecision-making-free filter for processeswith p 81 A87-15005 synthesis algorithm for optimal Systems of onboard abrupt changes p 136 A87-16189 State-of-the-art techniques lor lightning electrical equipment in computer-aided design MASS DISTRIBUTION susceptibility/vulnerability assessments P96 A87-15214 p 126 A87-15006 LOGISTICS MANAGEMENT Concentrated mass effects on the fluner of a composite Lightning strikestoaircraft 01 the German Federal Armed Multi-EchelonRepair Level Analysis - MERLA advanced turboprop model [NASA-TM-88854] p 130 N87-12017 Forces p 81 A87-15008 p64 A87-15414 Simulated lightning current tests on a Lynx helicopter LONG TERM EFFECTS Characterization and dynamical studies of polymers in p 95 A87-15011 Long-term deposit formation in aviation turbine fuel at dipolar (aprotic) liquids Prediction of skin currents flowing on a Lynx helicopter elevated temperature p 121 A87-14986 [AD-A169243] p 123 N87-12685 due to a simulated lightning strike p 95 A87-15012 LONGITUDINAL CONTROL MASS FLOW Spatial and temporal description of strikes to the FAA Decoupling control synthesis for an oblique-wing Computational fluid dynamic studies of certain ducted CV-580 aircraft p 81 A87-15013 aircraft p 108 A87-13342 bluff-body flowfields relevant to turbojet combustors. Simultaneous airborne and ground measurement of low LORAN Volume 1: Time-dependent calculations with the k-epsilon altitude cloud-to-ground lightning strike on CV-580 Combining Loran and GPS - The best of both worlds turbulence model for an existing centerbdy combustor aircraft D 81 A87-15014 p 88 A87-13544 [ AD-A171 4341 p 131 N87-12816 SUBJECT INDEX NOISE REDUCTION

MATERIALS HANDLING METEOROLOGICAL PARAMETERS MOLECUIAR INTERACTIONS Multivariablecontrol of a twin lift helicopter system using Possible military applications of stratospheric airship Characterization and dynamical studies of polymers in the LQG/LTR design methodology --- Linear Quadratic discussed p 101 N87-12716 dipolar laprotic) liquids GaussiadLoop Transfer Recovery method Revised Uniform Summary of Surface Weather [ AD-A1692431 p 123 N87-12685 p 110 A87-13419 Observations (RUSSWO). Parts A-F Ellington ANGB. MOTION STABILITY MATERIALS TESTS Texas Application of time-domain unsteady aerodynamics to 7050 aluminum rivets for military aircraft [ AD-A1693891 p 133 N87-13105 rotary-wing aeroelasticity p 94 A87-14103 o 124 A87-13173 METEOROLOGICAL RADAR r .- -...... -_.- ._. review of microbursts and their analysis and detection Testing of fiber-reinforced construction elements - A Fault-tolerant C31 system A(O), A(l). MTBF allocations with Doppler radar Simulation of mechanical loads and environmental D 86 A87-15427 influences p 92 A87-14012 [AD-A170458] p 133 N87-13110 Results of research on materials and construction METEOROLOGICAL SERVICES methods by the DFVLR p64 A87-14015 Weather safety aspects in future civil air navigation N MATHEMATICAL MODELS p85 A87-13540 METEOROLOGY Improvement of mathematical models of helicopters by NACELLES analytical presentation of nonlinear aerodynamics Analyvs and verilication of the icing scaling equations. The handling qualities and flight characteristics of the p 69 A87-13995 Volume 1: Revision Grumman design 698 simulated twin-engine tilt Nacelle [AD-A1679761 p 85 N87-12551 Analytical model for investigation of interior noise V/STOL aircraft characteristics in aircraft with multiple pcopellers including MICROELECTRONICS [ NASA-TM-867851 p 100 N87-12558 synchrophasing p 94 A87-14925 Microelectronics in aircraft systems .-.Book The use of mathematical models in aerodynamics (The p 101 A87-13469 NASA PROGRAMS Summary of NASA stall/spin research for general W. Rupert Tumbull Lecture) p 72 A87-15189 Sizing hybrid packages for optimum reliability A dynamic model for airframe cost estimation p 128 A87-15433 aviation configurations [ AD-A1686421 p65 N87-11687 MICROPROCESSORS [AIAA PAPER 86.25971 p 111 A87-14032 Numerical simulation of tip vortices of wings in subsonic Radio-navigation meters based on the K588 series Summary of NASA storm hazards lightning research, and transonic flows microprocessor unit p86 A87-15569 1980-1985 p 80 A87-15003 [AD-A169116] p 77 N87-12544 Flight model discharge system NASA SPACE PROGRAMS A summary of the development of integral aerodynamic [AD-AI 694231 p 117 N87-12571 Ames accelerates research on hypersonic technolcgy methods for the computation of rotor wake interactions MICROWAVE LANDING SYSTEMS p 64 A87-13911 [AD-A1692541 p 77 N87-12545 Guidance law simulation studies for complex approaches Aerospace plane - Fact or fantasy? Analysis and verification 01 the icing scaling equations. using the Microwave Landing System [MLS) p65 A87-16396 Volume 1: Revision [NASA-CR-178182] p 87 N87-12552 NASTRAN [ AD-A1679761 p 85 N87-12551 MICROWAVE RADIOMETERS Design enhancement tools in MSUNASTRAN Simplified forms of performance equations. Addendum Ground-baseddetection of aircraft icingconditions using p 136 N87-11748 A: Effect on aeroplane level speed 01 small changes in microwave radiometers p 80 A87-14861 NAVIER-STOKES EQUATION thrust, drag, weight. power MILITARY AIR FACILITIES Finite element Navier-Stokes calculation of [ESDU-86004-ADD-A] p 100 N87-12556 Design and development of a two-stage parachute three-dimensionalturbulent flow near a propeller Evaluation of a nonlinear parameter extraction system for delivery of troops from a high-speed aircraft p 70 A87-14101 mathematical model including the term C[subm(sub delta [AIM PAPER 86-24481 p 80 A87-13818 Convergence acceleration for a three-dimensional e squared)) Revised Uniform Summary of Surface Weather EulerINavier-Stokes zonal approach p 70 A87-14105 [NASA-TM-87731] p 116 N87-12566 Observations (RUSSWO). Parts A-F Ellington ANGB. Influence of trailing-edge meshes on skin friction in MATRICES (MATHEMATICS) Texas Navier-Stokes calculations p 71 A87-14125 Motion characteristics of the UTlAS flight research [ AD-A1693891 p 133 N87-13105 Numerical simulation of tip vortices of wings in subsonic simulator motion-base and transonic flows MILITARY AIRCRAFT [UTlAS-TN-261] PI19 N87-11802 [AD-A169116] p 77 N87-12544 7050 aluminum rivets for military aircraft MAXIMUM LIKELIHOOD ESTIMATES NAVIGATION AIDS p 124 A87-13173 Aircraft flight data compatibilitychecking using maximum ION, National Technical Meeting, Long Beach, CA. likelihood and extended Kalman filter estimation State-of-the-artcrashworthy cargo restraint systems lor January 21-23, 1986, Proceedings p 85 A87-13532 p 113 A87-16184 military aircraft p89 A87-13667 Weather safety aspects in future civil air navigation Maximum likelihood estimation of parameters in Acquisition and use of data for crashworthiness p 85 A87-13540 nonlinear flight mechanics systems p 113 A87-16192 improvements in U.S. Army aircraft p 78 A87-13686 Improving Loran coverage at minimum cost MCDONNELL DOUGLAS AIRCRAFT Lightningstrikes toaircraft of the German Federal Armed p 86 A87-13543 MD-80 service maturity program p 64 A87-15418 Forces p 81 A87-15008 Radio-navigation meters based on the K588 series MEASURING INSTRUMENTS Reliability growth during flight test p 127 A87-15412 microprocessor unit p 86 A87-15569 Experimental calibration of an aircraft vector electric field Multi-Echelon Repair Level Analysis - MERLA NAVIGATION SATELLITES meter system p 102 A87-15028 p64 A87-15414 Mobile communications. navigation and surveillance MECHANICAL ENGINEERING RAW automated RBM package (RAMP) [IAF PAPER 86.3331 p 86 A87-16027 Modeling of the aircraft mechanical control system p 128 A87-15417 NAVSTAR SATELLITES p 111 A87-14135 Navstar Global Positioning Systems Collins user Tailoring a major weapon environmental program ---for MEMBRANE STRUCTURES equipment - An evolutionary assessment Low Altitude Navigationand Targeting Infrared System for Composite curing with semi-permeable membranes p 85 A87-13533 p 120 A87-13121 Night p 102 A87-15430 NAVY MESH MILITARY OPERATIONS Repair of composite components - A Navy approach Advanced construction procedures: Confined bases for Design and development of a two-stage parachute p 117 A87-13122 airport pavements system for delivery of troops from a high-speed aircraft NEAR FIELDS [FAA/PM-86/9] p 118 N87-11799 [AIAA PAPER 86-24481 p 80 A87-13818 Experimental investigationof near and far acoustic field METAL BONDING MILITARY TECHNOLOGY of a small turbojet p 138 A87-13605 Diffusion bonding of certain refractory metals Navstar Global Positioning Systems Collins user NETWORK SYNTHESIS p 121 A87-13171 equipment - An evolutionary assessment A system model, a logic design diagram, and a general Clarification of adhesive binding mechanisms of p 85 A87-13533 synthesis algorithm for optimal systems of onboard

aluminum structural bonds in aircraft fabrication LAMPS MK 111 ~ A 'New Look' success story --- reliability electrical equipment in computer-aideddesign [MBB-UT-226-86] p 121 A87-13985 engineering of ship/helicopter system for antisubmarine p96 A87-15214 METAL FOILS ~ warfare p 102 A87-15415 NEWTON-RAPHSON METHOD A heater made from graphite composite material for MISSILE COMPONENTS Aircraft automatic-flight-controlsystem with inversion of 1 potential deicing application Carbon fibers the model in the feed-foruard path using a [ NASA-TM-888881 P 101 N87-12559 [ AD-A171 3701 p 123 N87-12622 Newton-Raphson technique for the inversion METAL MATRIX COMPOSITES MISSILE CONTROL [ NASA-TM-882091 p 116 N87-11796 Polymer, metal, and ceramic matrix composites for A split canard configuraion for improved control at high NICKEL CADMIUM BAITERIES advanced aircraft engine applications angles of attack p67 A87-13643 Aircraft battery state of charge and charge control P 121 A87-15187 The 8 m x 6 m low speed wind tunnel at the Chinese system METAL PROPELLANTS [AD-A169411] p 130 N87-12766 Aerodynamic Research and Development Center 1 Combustion studies of metallized fuels for solid-fuel I [ AD-AI 684481 p 119 N87-11803 NOISE GENERATORS ramjets p 121 A87-14982 Noise of high speed surfaces p 138 A87-13595 Prospective. characteristics and problems of the use MOBILE COMMUNICATION SYSTEMS NOISE MEASUREMENT Mobile communications, navigation and surveillance I of boron in different air augmented propulsion modes Introduction to helicopter noise I [IAF PAPER 861911 p 122 A87-15924 [IAF PAPER 86-3331 p 86 A87-16027 [ISL-NB-401/84] p 139 N87-12327 METAL SURFACES MODELS NOISE PREDICTION (AIRCRAFT) A constitutive law for finite element contact problems 1986 American Control Conference, 5th, Seattle, WA. Noise and performance of a counter-rotation propeller with unclassical friction June 18-20. 1986, Proceedings. Volumes 1. 2. 8 3 p 105 A87-14366 [NASA-TM-88838] p 131 N87-12924 p 133 A87-13301 NOISE PROPAGATION I METEOROLOGICAL FLIGHT TSAR (Theater Simulation of Airbase Resources) Analytical model for investigation of interior noise Comparative flight measurement of icing parametersfor database dictionary F.4E characteristics in aircraft with multiple propellers including the DO 28 D2 propeller-drivenaircraft of the German Army [ AD-A1695751 p 139 N87-13352 synchrophasing p 94 A87-14925 Testing Office 61 and for DFVLR's Falcon 20 E jet aircraft MOISTURE CONTENT NOISE REDUCTION in stratus clouds Some effects of moisture on adhesive-bonded Companson of two propeller source models for aircraft [ESA-TT-941J p 83 N87-11709 CFRP-CFRP joints p 129 A87-16160 interior noise studies p 88 A87-13596

A-17 NONDESTRUCTIVE TESTS SUBJECT INDEX

Lightweight Sidewalls for aircraft interior noise control Automation of support processes for aircraft production Application of optimization techniques to the design of [NASA-CR-172490] p 138 N87-12323 using computers and numerical control .--Russian book a flutter suppression control law for the DAST ARW-2 on sound propagation in centrifugal fan casings p64 A87-14687 p 115 N87-11736 [ ESA-lT-957I p 138 N87-12326 NUMERICAL FLOW VISUALIZATION Influence of analysis and design models on minimum Application of the AlPA (Approximate Iterative An analytical parametric investigation of numerical weight design p 98 N87-11739 Preprocessing Algorithm) to F-106 data nonlinear vortex-lattice methods p 67 A87-13638 Aircraft configuration optimization including optimized [AD-A1690841 p 116 N87-12569 Experimentaland numencal investigation of supersonic flight profiles p 98 N87-11743 Cruise noise of counterrotation propeller at angle of turbulent flow through a square duct p 70 A87-14117 Multidisciplinary optimization applied to a transport attack in wind tunnel aircraft p 84 N87-11746 [ NASA-TM-888691 p 139 N87-13252 Design enhancement tools in MSCINASTRAN NONDESTRUCTIVE TESTS 0 p 136 N87-11748 Automated infrared inspection of jet engine turbine Recent Experiences in Multidisciplinary Analysis and blades p 125 A87-13719 OBLIOUE WINGS Optimizabon. part 2 [ NASA-CP-2327-PT-2 p 99 N87-11750 NONLINEAR EQUATIONS Aerwlastic control of oblique-wing aircraft I An analytical parametric investigation of numerical p 108 A87-13341 Overview: Applications of numencal Optimization nonlinear vortex-lattice methods p 67 A87-13638 methods to helicopter design problems Decoupling control synthesis for an oblique-wing NONLINEAR FILTERS p 99 N87-11751 aircraft p 108 A87-13342 An efficientdecision-making-free filter for processeswith Regression analysis as a design optimization tool abrupt changes p 136 A87-16189 OBSERVABILITY (SYSTEMS) p 136 N87-11754 Analytical redundancy through nonlinear Observers --- Sensor failure detection in flight control systems using A rotor optimization using regression BnalYSiS of aircraft motion p 114 A87-16197 deterministic observers p 114 A87-16195 p 136 N87-11755 NONLINEAR SYSTEMS Comparison of two techniques of I.F.D. based on a Optimization of helicopter rotor blade design for Bank-to-turn utilizing sampled data non-linear control non-linear stochastic model of an aircraft _-- Instrument minimum vibration p 99 N87-11756 p 109 A87-13346 Fault Detection p 114 A87-16196 Application of numerical optimization to rotor Flight control design using nonlinear inverse dynamics Analytical redundancy through nonlinear Observers --- aerodynamic design p 99 N87-11757 p 109 A87-13352 of aircraft motion p 114 A87-16197 Aeroelastic-aerodynamic optimization of high speed Improvement of mathematicalmodels of helicopters by OFFSHORE PLATFORMS helicopter-compoundrotor p 99 N87-11758 analytical presentation of nonlinear aerodynamics Systems, avionics and instrumentation of transport The structural optimization of a spreader bar for twin p 69 A87-13995 category helicopters lift helicopter operations p 100 N87-11759 Special opportunities in helicopter aercdynamics [NLR-MP-85066-U] p 102 N87-11785 Optimization applications in aircraft engine design and p 74 A87-15469 ONBOARD DATA PROCESSING test p 106 N87-11768 Nonlinear acoustics - Achievements, prospects, Computational enhancements to a 4D algorithm --- for On optimal design for the blade-rootlhub interface in problems p 138 A87-15582 aircraft trajectory optimization p 134 A87-13359 jet engines p 106 N87-11769 Parametric identification of discontinuous Redundant computer system for fly-by-wire controls Comments on gust response constrained optimization nonlinearities p 135 A87-16179 p 111 A87-14013 p 115 N87-11774 Maximum likelihood estimation of parameters in ONBOARD EOUIPMENT Applying optimization software libraries to engineering nonlinear flight mechanics systems p 113 A87-16192 A system model. a logic design diagram, and a general problems p 136 N87-11775 Comparison of two techniques of I.F.D. based on a synthesis algorithm for optimal systems of onboard Carburizing steel for high temperature service non-linear stochastic model of an aircraft --- Instrument electrical equipment in computer-aideddesign [ AD-A1683271 p 122 N87-11877 Fault Detection p 114 A87-16196 p 96 A87-15214 OSCILLATIONS Determination of nonlinear aerodynamic coefficients A small, flexible and powerful data acquisition system An experimental investigation of free-tip response to a using the estimation-before-modelingmethods for the F16 aircraft jet p 114 A87-16202 [NLR-MP-85074-U] p 103 N87-11786 [ NASA-TM-882501 p 76 N87-12539 NONLINEARITY OPTICAL RELAY SYSTEMS OUTPUT Evaluation of a nonlinear parameter extraction Advanced digital optical control actuation for the Reachable outputs in systems with bounded parameter mathematical model including the term C(subm(sub delta ADOCS uncertainties - Application to failure detection e squared)) [SAE PAPER 8517551 p 112 A87-15480 p 134 A87-13326 [ NASA-TM-877311 p 116 N87-12566 OPTIMAL CONTROL NOSE WHEELS A direct method for enforcing equality constraints in The equivalent masses at nose landing-gears during optimal output feedback p 134 A87-13353 P landing-impacts and when taxiing over runway Combined guidance - Flight control of atmospheric perturbations p 88 A87-13637 vehicles p 110 A87-13654 PANEL METHOD (FLUID DYNAMICS) An aerodynamic analysis and the subsequent motion NOZZLE DESIGN The method of calculating the desired flight path of of external store p 66 A87-13501 Performance and optimisation of an airblast noale - terrain following technique with circular arc spline On the utilization of vortex methods for parachute Drop size distribution and volumetric air flow D 111 A87-14136 aerodynamic predictions p 125 A87-13828 Optimal guidance law with first order lag loop and normal [AIM PAPER 86-24551 p 68 A87-13795 Prediction of velocity cwfficient and spray cone angle constraint p 86 A87-14140 Vortex panel calculation of wake rollup behind a large for simplex swirl atomizers p 125 A87-13830 Optimal discrete design of digital flight control system aspect ratio wing p 70 A87-14102 NOZZLE FLOW p 111 A87-14142 Effect of two endwall contours on the performance of Aircraft control input optimization for aerodynamic PANELS Sizing-stiffened composite panels loaded in the an annular nozzle cascade p 71 A87-14119 denvative estimation in dynamic manoeuvres postbuckling range p 129 N87-11733 Study of a bounded jet flow considering the initial p 113 A87-16183 Carbon fibers turbulence. I1 - In the case of relatively large nozzle aspect Optimal descending. hypersonic turn to heading [ AD-A171 3701 p 123 N87-12622 ratio p 71 A87-14263 [DE86-010989] p 120 N87-12577 A study of local heat transfer on the face surface of a OPTIMIZATION PARACHUTEDESCENT nozzle ring model p 127 A87-15215 Optimal stochastic observers applied to hydraulic The effect of random wind gusts on the stability of a Effectsof test cell recirculation on high-bypassturbofan actuation systems p 87 A87-13354 parachute system p 72 A87-15216 engines dunng simulated altitude tests Performance and optimisation of an airblast nozzle - PARACHUTES [ AD-A1714181 p 108 N87-12565 Drop size distnbution and volumetnc air flow Aerodynamic Decelerator and Balloon Technology NOZZLE GEOMETRY p 125 A87-13828 Conference, 9th. Albuquerque, NM. October 7-9, 1986. Effect of port corner geometry on the internal Propeller design by optimization p 105 A87-14123 Technical Papers p 79 A87-13776 performance of a rotating-vane-typethrust reverser A system model. a logic design diagram. and a general Technical-historical development of parachutes and [ NASA-TP-26241 p 77 N87-12541 synthesis algorithm for optimal systems of onboard their applications since World War I NUMERICAL ANALYSIS electncal equipment in computer aided design [AIAA PAPER 86-24231 p 79 A87-13777 1986 American Control Conference. 5th. Seattle. WA, p96 A87-15214 Automatic vanable reefing of parachutes by application June 18-20, 1986. Proceedings. Volumes 1. 2. 8 3 Recent Experiences in Multidisciplinary Analysis and of inflation forces p 133 A87-13301 Optimization. part 1 [AIAA PAPER 86-24341 p 79 A87-13784 Comparison of numerical solutions of lower order and [NASA-CP-2327-PT-l] p 96 N87-11717 Notes on a generic parachute opening force analysis higher order integral equationmethods for two-dimensional Optimization in the systems engineering process [AIM PAPER 86-24401 p 67 A87-13788 aerofoils p 96 N87-11719 Average landing force dependence on length and Practical considerations in aeroelastic design [AIAA PAPER 86-2591 1 p 69 A87-14028 direction of landing. parachute velocity components and Numerical simulation of tip vortices of wings in subsonic p97 N87 11720 wind speed and transonic flows Flutter optimization in fighter aircraft design [AIAA PAPER 86-24521 p 79 A87-13794 [AD-A1691161 p 77 N87-12544 p 97 N87-11721 Application of the generalized reduced gradient method On the utilization of vortex methods for parachute A summary of the development of integral aerodynamic aerodynamic predictions methods for the computation of rotor wake interactions to conceptual aircraft design p 97 N87-11722 p 68 A87-13795 Experiences performing conceptual design optimization [AIM PAPER 86-24551 [AD-A169254] p 77 N87-12545 of transport aircraft p 97 N87-11723 Axisymmetric vortex lattice method applied to parachute Application of the AlPA (Approximate Iterative Optimization process in helicopter design shapes Preprocessing Algorithm) to F-106 data [AlAA PAPER 86-24561 p68 A87-13796 p 98 N87-11726 [AD-A169084] p 116 N87-12569 STAEBL Structural tailoring of engine blades, phase 2 Aerodynamic characteristics and flow round cross NUMERICAL CONTROL P 106 N87-11731 parachutes in steady motion Time scale analysis of a digital flight control system Optimization of cascade blade mistuning under flutter [AIAA PAPER 86-24581 p 68 A87-13798 p 109 A87-13347 and forced response constraints p 106 N87-11732 Drag and stability improvements of a square Time-based air traffic management using expert Sizing-stiffened composite panels loaded in the parachute systems p 85 A87-13362 postbuckling range P 129 N87-11733 [AIM PAPER 86-2471I p 68 A87-13805 SUBJECT INDEX PROTOTYPES

LOW cost aerial testing of parachutes PERTURBATION POWER EFFICIENCY [AIM PAPER 86-24721 p79 A87-13806 Introduction to aerodynamics derivitives. equations of Improving the energy efficiency 01 cooled Improved measurement of the dynamic loads acting on motion and stability high-temperatureturbines p 104 A87-13990 rotating parachutes [ESDU-86021 I p 76 N87-12536 PREDICTION ANALYSIS TECHNIQUES [AIAA PAPER 86-24731 p68 A87-13807 PILOT ERROR Recent advances in prediction methods for jet-induced Performance prediction lor fully-deployed parachute Aircraft accident report: Bar Harbor Airlines Flight 1808, effects on V/STOL aircraft p 73 A87-15462 canopies Beach BE-99, NBOOWP, Auburn-Lewiston Municipal PREDICTIONS [ AIAA PAPER 86-24751 p 79 A87-13809 Airport. Auburn, Maine, August 25. 1985 1986 American Control Conlerence. 5th. Seattle. WA, [ PB86-9104081 p 84 N87-12550 A comparisonof measured and calculated stress in solid June 18-20, 1986, Proceedings. Volumes 1. 2. 8 3 PILOT PERFORMANCE p 133 A87-13301 and ribbon parachute canopies Evaluation of a visual system in its support 01 simulated [AIAA PAPER 86-24881 p 80 A87-13815 Special oppoltunities in helicopter aerodynamics helicopter flight p 74 A87-15469 Design and development 01 a two-stage parachute [ AD-A1688291 p 102 N87-11783 Research on mechanical properties for engine life system for delivery of troops from a high-speed aircraft Simulator design and instructional features for canier prediction [AIAA PAPER 86-24481 p 80 A87-13818 landing: A field transfer study [AD-A1695701 p 108 N87-12563 PARALLEL FLOW [AD-A169962] p 119 N87-12573 Some asymptotic types of transonic vortex flows PILOT TRAINING PREFLIGHT OPERATIONS p 74 A87-15553 Simulator design featuresfor helicopter landing on small Ground aircraft deicing technology review An approximate method of estimating the aerodynamic ships. 1: A performance study [DOT/FAA/CT-85/21 I p 83 N87-11707 interference between two parallel bodies in a supersonic [AD-A1695141 p 119 N87-12572 PREPREGS flow (axial force) Simulator design and instructional features lor carrier Mechanizedmanufacture of composite main rotor blade [BR-1002711 p 76 N87-12540 landing: A field transfer study spars p 124 A87-13625 PARALLEL PROCESSING (COMPUTERS) [AD-A169962] p 119 N87-12573 PRESSURE EFFECTS Grundy - Parallel processor architecture makes PIPES (TUBES) Pitot and static errors in steady level flight programming easy p 135 A87-13703 The development of balance tubes for Dowty Rotol [ ESDU-860061 p 74 N87-11691 PARAMETER IDENTIFICATION composite bladed propellers p 63 A87-13630 PRESSURE REDUCTION Parameter estimation and in-plane distortion invariant PLANETARY ATMOSPHERES A study 01 the effect of the temperature factor on chord processing p 135 A87-13689 Ramjet application in atmospheres of different celestial pressure losses in the cooling system of the leading edge Identification and System parameter estimation 1985: bodies of a deflector vane --- lor gas turbine engines [IAF PAPER 86-1811 p 120 A87-15920 Proceedings of the Seventh Symposium, University 01 p 127 A87-15218 York. England, July 3-7, 1985. Volumes 1 8 2 PLASTIC AIRCRAFT STRUCTURES PRESSURE SENSORS p 135 A87-16178 Resin-hardener systems for resin transfer molding Supplementary calibration test 01 the tipaerodynamics- p 120 A87-13093 Parametric identification 01 discontinuous and acoustics-test pressure transducers Advanced composites applications for the 6-1B bomber nonlinearities p 135 A87-16179 [NASA-TM-88312] p 131 N87-12830 - An overview p 87 A87-13101 PRODUCT DEVELOPMENT Parameter estimation 01 aircraft with fly-by-wire control Automated assembly-trends, concepts and systems p 113 A87-16186 Design considerations lor superplastically formed requirements p 83 A87-13105 complex aircraft structures p 87 A87-13151 Maximum likelihood estimation 01 parameters in Developmentand testing of critical components lor the PRODUCTION COSTS nonlinear flight mechanics systems p 113 A87-16192 technological preparation of a CFK outer wing A dynamic model lor airframe cost estimation Frequency domain parameter estimation of aeronautical [MBB-UT-224-86] p 92 A87-13997 [ AD-A1688421 p65 N87-11687 systems without and with time delay Technologies for a mechanized carbon fiber p 114 A87-16193 construction element for commercial aircraft production PRODUCTION ENGINEERING A dynamic model lor airframe cost estimation Evaluation 01 a nonlinear parameter extraction [ MBB-UT-005-861 p 126 A87-13999 [AD-A168842] p 65 N87-11687 mathematical model including the term C(subm(sub delta Structure-componenttests for a CFK fuselage e squared)) [ MBB-UT-223-861 p 121 A87-14001 PROJECT PLANNING [NASA-TM-87731] p 116 N87-12566 Testing of fiber-reinforced construction elements - Repair of Composite components - A Navy approach p 117 A87-13122 . PARAMETERIZATION Simulation of mechanical loads and environmental An analytical parametric investigation of numerical influences p 92 A87-14012 PROP-FAN TECHNOLOGY nonlinear vortex-lattice methods p 67 A87-13638 PLASTICS Technicalleconomic evaluation 01 new propfan concepts in comparison with the turbofan of the 1990s PARTICLE TRAJECTORIES Carbon fibers p 104 A87-13989 Development 01 an advanced vaneless inlet particle [AD-A1713701 p 123 N87-12622 separator for helicopter engines p 105 A87-14984 PLATE THEORY PROPELLER BLADES Determination 01 the regime coefficients in the local Comparison of two propeller source models lor aircraft PASSENGER AIRCRAFT theory of interaction from plate data p 74 A87-15561 interior noise studies p 88 A87-13596 New fuselage technologies for general-aviationaircraft PLY ORIENTATION The development of balance tubes for Dowty Rotol p A87-14027 93 Vertical deflection characteristics 01 aircraft tyres composite bladed propellers p 63 A87-13630 MD-80 service maturity program p 64 A87-15418 [ESDU-86005] p 129 N87-11992 Finite element Navier-Stokes calculation of Systems, avionics and instrumentation of transport POISSON EQUATION threedimensionalturbulent flow near a propeller category helicopters An exterior Poisson solver using fast direct methods p 70 A87-14101 [ NLR-MP-85066-UI p 102 N87-11785 and boundary integral equations with applications to PROPELLER EFFICIENCY PAlTERN RECOGNITION nonlinear potential flow p 125 A87-13872 Effect of an upstream wake on a pusher propeller Parameter estimation and in-plane distortion invariant POISSON RATIO [AIM PAPER 86-26021 p 69 A87-14035 chord processing p 135 A87-13689 The effect 01 material compressibility (Poisson ratio) on Determination of the thrust and net efficiency of a PAVEMENTS the elasto-plasticsolution lo the problemof a cylinder under propeller and flow parameters behind the propeller Advanced construction procedures: Confined bases for internal pressure (coldworking situation) p 105 A87-15204 airport pavements p 124 A87-13642 Propellarlbodyinteraction lor thrust and drag [FAA/PM-86/9] p 118 N87-11799 POLYMERIC FILMS [ ESDU-860171 p 76 N87-12537 Criteria for asphalt-rubber concrete in civil airport Composite curing with semi-permeable membranes PROPELLERS pavements: Mixture design p 120 A87-13121 Propeller design by optimization p 105 A87-14123 [ DOT/FAAIPM-86/391 p 129 N87-11910 POROSITY Propellarlbody interaction lor thrust and drag PAYLOADS Viscous-inviscidinteraction in transonic separated flow [ESDU-86017] p 76 N87-12537 The structural optimization of a spreader bar for twin over solid and porous airfoils and cascades PROPULSION SYSTEM PERFORMANCE lift helicopter operations p 100 N87-11759 p 76 N87-12535 Thermochemicalevaluation of fuel candidatesfor ramjet PERFORMANCE PREDICTION PORTS (OPENINGS) propulsion p 121 A87-13659 Performance prediction for fully-deployed parachute Effect of port comer geometry on the internal Propeller design by optimization p 105 A87-14123 canopies performance of a rotating-vane-typethrust reverser PROTECTIVE COATINGS [AIAA PAPER 86-24751 p 79 A87-13809 [ NASA-TP-26241 p 77 N87-12541 Determinationof dynamic stresses in the heat-insulating Design 01 a takeoff performance monitoring system POSITION INDICATORS coatings 01 flight vehicles during aerodynamic heating p 103 N87-11787 MTFCS (multiple target formation flight control system) p 72 A87-15223 PERFORMANCE TESTS Formation position Sensor trade-off analysis Investigation 01 coating performance and corrosion of Noise and performance of a counter-rotation propeller p 110 A87-13536 compressor components in the TF30-P-3 engine of F111C p 105 A87-14366 POTENTIAL FLOW aircraff F/A-18 Hornet reliability program - Status report An exterior Poisson solver using fast direct methods [AD-A168802] p 107 N87-11792 p64 A87-15419 and boundary integral equations with applications to PROTOCOL (COMPUTERS) Built-ln-Test for fail-safe design p 128 A87-15428 nonlinear potential flow p 125 A87-13872 Selection of media access protocol lor distnbuted digital Reverse tailoring lor realistic reliability tests Numerical solution of transonic potential flows with finite avionics p 134 A87-13436 p 128 A87-15432 elements method using multigrid technique PROTOTYPES Motion characteristics of the UTlAS flight research p68 A87-13900 The 8 m x 6 m low speed wind tunnel at the Chinese simulator motion-base POTENTIAL THEORY Aerodynamc Research and Development Center [UTIAS-TN-261] p 119 N87-11802 Comment on 'Computation of choked and supersonic [ AD-A168448 I p 119 N87-11803 Fabrication and testing of lightweight hydraulic system turbomachinery flows by a modified potential method' Rapid prototyping lacility lor flight rewarch in simulator hardware p 71 A87-14129 artificialmtelligence-basedflight systems concepts [ AD-Al698841 p 130 N87-12711 POWER CONDITIONING I NASA-TM-882681 p 137 N87.12273 PERMEABILITY I 986 American Control Conference, 51h, Seattle. WA, The evaluation of a number 01 prototypes lor the free-tip Composite curing with semi-permeable membranes June 18-20, 1986, Proceedings. Volumes 1. 2, 8 3 rotor constant-moment controller p 120 A87-13121 D 133 A87-13301 INASA-TM-866641 p 131 N87-12869

A-19 QUADRATIC EQUATIONS SUBJECT INDEX

Q RELlABlLlTV ENGINEERING ROBUSTNESS (MATHEMATICS) Renewed interest in hinge moment models for failure 1986 Amencan Control Conference. 5th. Seattle. WA. QUADRATIC EOUATIONS detection and isolation p 110 A87-13426 June 18-20. 1986. Proceedings. Volumes 1. 2. 8 3 Aeroelastic control of obliquewing aircraft Environmental Stress Screening (ESS) demonstratesits p 133 A87-13301 p 108 A87-13341 value in the field p 127 A87-15403 Methods for obtaining robust tracking control laws Reliability growth during flight test p 127 A87-15412 p 134 A87-13319 R LAMPS MK Ill - A 'New Look' success story --- reliability Multivariable high-gain control with feedforward engineering of ship/helicopter system for antisubmarine compensation - A design technique p 134 A87-13365 warfare p 102 A87-15415 Multwariablecontrol of a twin lift helicopter system using RADARBEACONS the LQGlLTR design methodology Linear Quadratic F/A-16 Hornet reliability program - Status report --- Mode S beacom system: Functional description Gaussian/ Loop Transfer Recovery method p64 A87-15419 [ DOT/FAA/PM-86/19] p 87 N87-11715 p 110 A87-13419 RADAR DETECTION Built-In-Test for fail-safe design p 128 A87-15428 ROLLER BEARINGS Obstacle-warningradar for helicopters Sizing hybrid packages for optimum reliability Methods for the assembly and testing 01 the bearing p 132 N87-13149 p 128 A87-15433 supports of gas turbine engines --- Russian book RADIAL FLOW REMOTE CONTROL p 126 A87-14683 On sound propagation in centrifugal fan casings Electroluminescent (EL) remotely-controlled landing Selection of rolling-element bearing steels for long-life [ ESA-l-r-957I p 138 N87-12326 zone marker light system application RADIO NAVIGATION [ AD-DO1 23861 p 87 N87-11716 [NASA-TM-88881I p 129 N87-11993 Radio-navigation meters based on the K588 series REMOTE SENSORS Analysis of mixed-mode crack propagation using the microprocessor unit p 86 A87-15569 Ground-based detection of aircraft icingconditions using boundary integral method RADIO RECEIVERS microwave radiometers p 80 A87-14861 [ NASA-CR-1795181 p 131 N87-12915 Synthesis of devices for the optimal processingof pulsed ROLLING CONTACT LOADS radio signals in LORAN systems p 86 A87-15563 REMOTELY PILOTED VEHICLES On the improvement of an expendable turbojet engine Frictional and retarding forces on aircraft tyres. Part 4: RAIN IMPACT DAMAGE Estimation of effects of yaw Potential influences of heavy rain on general aviation flight envelope p 104 A87-13647 RESCUE OPERATIONS [ESDU-86015PT-4] p 131 N87-12868 airplane performance ROTARY STABILITY [AIM PAPER 86-26061 p 94 A87-14036 Aircraft accidents, survival, and rescue p 78 A87-13581 Application of time-domain unsteady aerodynamics to RAMJET ENGINES rotary-wing aeroelasticity p 94 A87-14103 Technical-historical development of parachutes and Thermochemicalevaluation of fuel candidates for ramjet ROTARY WING AIRCRAFT their applications since World War I pfopulsion p 121 A87-13659 Evolution of MIL-STD-129OA. light fixed and rotary-wing [AIAA PAPER 86-24231 p 79 A87-13777 Combustion studies of metallized fuels for solid-fuel aircraft crashworthiness p 89 A87-13663 ramjets p 121 A87-14982 RESEARCH AIRCRAFT Compound cycle engine program Ramjet application in atmospheres of different celestial Low cost aerial testing 01 parachutes [NASA-TM-88879] p 107 N87-11790 bodies [AIM PAPER 86.24721 p 79 A87-13606 An experimental investigation of free-tip response to a [IAF PAPER 86-181 1 p 120 A87-15920 Summary of NASA stall/spin research for general jet Prospective, charactenstics and problems of the use aviation configurations (NASA-TM-882501 p 76 N87-12539 of boron in different air augmented propulsion modes [AIAA PAPER 86.25971 p 111 A87-14032 ROTARY WINGS [IAF PAPER 86-1911 p 122 A87-15924 F-106 data summary and model results relative to threat Mechanized manufactureof composite main rotor blade RANDOM NOISE criteria and protection design analysis spars p 124 A87-13625 State estimation of flying vehicle p 114 A87-16209 p 81 A87-15004 Theoretical investigations of transonic rotor-blade READ-ONLY MEMORY DEVICES Interpretation of a class of in-flight lightning signatures aerodynamics p68 A87-13994 Grundy - Parallel processor architecture makes p 81 A87-15005 Models for rotor and helicopter design programming easy p 135 A87-13703 Spatial and temporal description of strikes lo the FAA p 92 A87-14008 REAL TIME OPERATION CV-580 aircraft p 81 A87-15013 Development of a new type of bearingless rotor A real-time simulation evaluation of an advanced Simultaneous airborne and ground measurement of low system p 93 A87-14017 detection. isolation and accommodation algorithm for altitude cloud-to-ground lightning strike on CV-580 Possibilitiesfor optimization and higher-harmoniccontrol sensor failures in turbine engines p 103 A87-13318 aircraft p 81 A87-15014 of helicopter main rotors by blade feathering Tool to develop real time simulation systems Joint thunderstorm operations using the NASA F-1066 p 111 A87-14021 INPE-3979-TDL/233] p 137 N87-13179 and FAATClAWAL Convair 580 airplanes Application of a mixed variational approach to RECOVERY PARACHUTES p 95 A87-15018 aeroelastic stability analysis 01 a nonuniform blade Status report of a new recovery parachute system for Improved electrostatic discharge wicks for aircraft p 126 A87-14423 the F111 aircraft crew escape module p 127 A87-15039 Application of modern structural optimization to vibration [AIAA PAPER 86-24371 p 91 A87-13821 Flight test report of the NASA icing research airplane: reduction in rotorcraft p 115 N87-11752 RECTANGULAR WINGS Performance, stability. and control after flight through Helicopter rotor blade aerodynamic optimization by Spanwise variation of laminar separation bubbles on natural icing conditions mathematical programming p 99 N87-11753 wings a1 low Reynolds number p 71 A87-14362 [ NASA-CR-1795151 p 116 N87-11797 A rotor optimization using regression analysis Numerical simulationof tip vortices of wings in subsonic RESEARCH AND DEVELOPMENT p 136 N87-11755 and transonic flows Mechanized manufactureof composite main rotor blade Optimization of helicopter rotor blade design for [AD-A169116] p 77 N87-12544 spars p 124 A87-13625 minimum vibration p 99 N87-11756 REDUCED ORDER FILTERS Results of helicopter research a1 DFVLR Aeroelastic-aerodynamic optimization of high speed Aeroelastic control of oblique-wing aircraft p 91 A87-13987 helicopter-compound rotor p 99 N87-11758 p 108 A87-13341 Results of research on materials and construction The prediction of transonic loading advancing helicopter REDUNDANCY methods by the DFVLR p64 A87-14015 rotors Redundant computer system for fly-by-wire controls RESEARCH FACILITIES [ AD-A1 682171 p 100 N87-11781 p 111 A87-14013 Rapid prototyping facility for flight research in A summary of the development of integral aerodynamic Analytical redundancy through nonlinear observers --- artaicial-intelligence-based flight systems concepts methods for the computation of rotor wake interactions of aircraft motion p 114 A87-16197 [AD-A169254] p 77 N87-12545 REENTRY GUIDANCE [ NASA-TM-882681 p 137 N87-12273 RESIN MATRIX COMPOSITES An analysis of blade vortex interaction aerodynamics Optimal descending. hypersonic turn lo heading Resin-hardener systems for resin transfer molding and acoustics p 77 N87-12547 [ DE86-0109891 p 120 N87-12577 The evaluationof a number of prototypes for the free-tip REFRACTORY MATERIALS p 120 A87-13093 Polymer. metal. and ceramic matrix composites for rotor constant-moment controller Diffusion bonding of certain refractory metals advanced aircraft engine applications [ NASA-TM-866641 p 131 N87-12869 p 121 A87-13171 Carbon fibers p 121 A87-15187 ROTATING BODIES RING STRUCTURES [ AD-A1713701 p 123 N87-12622 Improved measurement of the dynamic loads acting on The Annular Parachute An approach to a low altitude REQRESSIONANALYSIS - rotating parachutes personnel parachute Application of regressionanalysis lo coupled responses [AIAA PAPER 86.24731 p 68 A87-13807 at high angles of attack p 113 A87-16185 [AiAA PAPER 86.24491 p 80 A87-13823 Effect of port corner geometry on the internal Finite element contact analysis of nng gear and A rotor optimization using regression analysis performance of a rotating-vane-typethrust reverser p 136 N87-11755 support p 127 A87-15193 [ NASA-TP-26241 p 77 N87-12541 Turbine air seal with full backside cooling REQULATORS ROTOR AERODYNAMICS Eigenstructure assignment by dynamic output [AD-DO124051 p 108 N87-12564 Theoretical investigations of transonic rotor-blade RIVETS feedback p 134 A87-13385 aerodynamics p 68 A87-13994 7050 aluminum rivets for military aircraft RELIABILITY ANALYSIS Improvement of mathematical models of helicopters by MD-80 service maturity program p 64 A87-15418 p 124 A87-13173 RLC CIRCUITS analytical presentation of nonlinear aerodynamics Tailonng a major weapon environmental program --- for p 69 A87-13995 Lightning return stroke current computation Low Altitude Navigation and Targeting Infrared System for Models for rotor and helicopter design Night p 102 A87-15430 p 126 A87-15029 ROBOTICS p 92 A87-14008 Reverse tailoring for realistic reliability tests Implementation of a robotic assembly cell Application of time-domain unsteady aerodynamics to p 128 A87-15432 p 63 A87-13062 rotary-wing aeroelasticity p 94 A87-14103 Application of Markov models for RMA assessment --- Automated flexible assembly of aerospace structures The aerodynamics and dynamics of rotors. Problems Reliability. Maintainabilityand Availability p 63 A87-13063 and perspectives p 74 A87-15468 p 128 A87-15435 1986 American Control Conference. 5th. Seattle. WA. The prediction of transonic loading advancing helicopter Sensor failure detection in flight control systems using June 18-20, 1986, Proceedings. Volumes 1, 2. B 3 rotors deterministic observers p 114 A87-16195 p 133 A87-13301 [AD-A168217] p 100 N87-11781 A-20 SUBJECT INDEX SOFTWARE TOOLS

An analysis of blade vortex interaction aerodynamics SANDWICH STRUCTURES Computation of sharpfin-inducedshock wave/turbuIent and acoustics p77 N87-12547 Development of a GFRP wing in accordance with FAR boundary-layerinteractions p 70 A87-14104 ROTORBLADES Part 23 P 92 ~87-13993 SHOCK WAVES Theoretical investigations of transonic rotor-blade SCALING LAWS Numerical calculation of three-dimensional inviscid aerodvnamics~, D68 A87-13994 Analysis and verification of the icing scaling equations. suwrsonic flows 066 A87-13504 Models for rotor and helicopter design Volume 1: Revision Dynamic loads on twin jet exhaust noales due to shock p 92 A87-14008 [ AD-A1 679761 p 85 N87-12551 noise p 94 A87-14369 SEALS (STOPPERS) The aerodynamics and dynamics of rotors. Problems SHORT HAUL AIRCRAFT Turbine air seal with full backside cooling and perspectives p74 A87-15468 Technicalleconomic evaluation of new propfan [AD-W12405] p 108 N87-12561 concepts in comparison with the turbofan of the 1990s The evaluation of a number of prototypes for the free-tip Improved vane platform sealing and retention means p 104 A87-13989 rotor constant-moment controller [AD-W12407] p 131 N87-12881 [ NASA-TM-866641 p 131 N87-12869 SEATS Impetus of new technologies for utility, executive, and ROTOR BLADES (TURBOMACHINERY) The development of dynamic performance standards commuter aircraft p104 A87-14000 Some observationson the behaviorof the Langley model for civil rotorcraft seats p89 A87-13666 SHORT TAKEOFF AIRCRAFT rotor blade Crew seat stroke requirements for helicopter rolled Combination of Suction and tangential blowing in [NASA-CR-179880] p 74 N87-11695 attitude impact crashworthiness p 90 A87-13669 boundary layer control p67 A87-13641 A Summary of the development of integral aerodynamic Computer modeling of crashworthy seating systems The 8 m x 6 m low speed wind tunnel at the Chinese methods lor the computation of rotor wake interactions p 90 A87-13671 Aerodynamic Research and Development Center [ AD-AI 692541 p77 N87-12545 Crashworthy crewseat limit load optimization through [ AD-AI68448 I p 119 N87-11803 Visualisation of axial turbine tip clearance flow using a dynamic testing p 91 A87-13675 The handling qualities and flight characteristics of the linear cascade The design and qualification testing of an Grumman design 698 simulated twin-engine tilt Nacelle [CUED/A-TURBO/TR-122] p107 N87-12560 energy-absorbing seat for the Navy's H-53 AID V/STOL aircrafl ROTOR BODY INTERACTIONS helicopters p 91 A87-13679 [NASA-TM-86785] p 100 N87-12558 Possibilitiesfor optimization and higher-harmonic control Crash dynamics program transport seat performance SHROUDS of helicopter main rotors by blade feathering and cost beneffl study Journal of engineering thermophysics (selected p 11 1 A87-14021 [ DOT/FAAICT-85/36] p 83 N87-11708 articles) PropellarIbody interaction for thrust and drag SECONDARY FLOW [ AD-A1 694521 p 139 N87-13347 [ESDU-86017] p 76 N87-12537 Study of a bounded jet flow considering the initial SIGNAL PROCESSING turbulence. II .In the case of relatively large nonle aspect ROTORSYSTEMSRESEARCHAIRCRAFT Synthesis 01 devices for the optimal processingof pulsed ratio p 71 A87-14263 NASA rotor systems research aircraft: Fixed-wing radio signals in LORAN systems p 86 A87-15563 SELECTION configuration flight-test results SIKORSKY AIRCRAFT Selection 01 rolling-element bearing steels for long-life [ NASA-TM-867891 p 100 N87-12557 Systems, avionics and instrumentation of transport application category helicopters ROTORCRAFT AIRCRAFT [NASA-TM-88881J p 129 N87-11993 [NLR-MP-85066-U] p 102 N87-11785 National Specialist's Meeting on Crashworthy Design SEPARATED FLOW SILANES of Rotorcraft, Georgia Institute 01 Technology,Atlanta, April Spanwise variition of laminar separation bubbles on Further shock tunnel studies of scramjet phenomena 7-9, 1986, Proceedings p89 A87-13662 wings at low Reynolds number p 71 A87-14362 [NASA-CR-179937] p77 N87-12542 The development of dynamic performance standards Modeling of turbulent separated flows for aerodynamic SIMPLIFICATION for civil rotorcraft seats p89 A87-13666 applications p 73 A87-15454 Reducing complexity in fly-by-wire flight control Mechanism of energy absorption via buckling ~ An Application of viscous-inviscid interaction methods to actuators analytical study p 124 A87-13682 transonic turbulent flows [SAE PAPER 8517521 p 112 A87-15477 Correlation of experimentalstatic and dynamic response [NASA-CR-179900] p75 N87-11700 SIMULATION of simple structural components p 124 A87-13683 Viscous-inviscidinteraction in transonic separated flow State-of-the-art techniques for lightning ROTORS over solid and porous airfoils and cascades susceptibilitylvulnerabilityassessments Multi-variablecontrol of the GE T700 engine using the p 76 N87-12535 PI26 A87-15006 LQG/LTR design methodology --- Linear Quadratic A summary of the development of integral aerodynamic Comparison of low level frequency domain lightning GaussianILoop Transfer Recovery method methods for the computation of rotor wake interactions simulation test to pulse measurements --.on modified I p 103 A87-13418 [AD-A169254] p77 N87-12545 F-14A aircraft p 126 A87-15007 Turbines with counter-rctating rotors for aircraft power Visualisation of axial turbine tip clearance flow using a Simulated lightning current tests on a Lynx helicopter plants p 106 A87-15211 linear cascade p 95 A87-15011 [CUEDIA-TURBOITR-1221 p 107 N87-12560 Optimization of cascade blade mistuning under flutter Prediction of skin currents flowing on a Lynx helicopter SEPARATORS and forced response constraints p 106 N87-11732 due to a simulated lightning strike p 95 A87-15012 Development of an advanced vaneless inlet particle Fabrication of cooled radial turbine rotor Comparison of electromagnetic measurements on an separator for helicopter engines p 105 A87-14984 [ NASA-CR-1795031 p 107 N87-11789 aircraft from direct lightning attachment and simulated An experimental investigation of free-tip response to a SEQUENCING nuclear electromagnetic pulse p 81 A87-15015 jet Multidisciplinary systems optimization by linear Current levels and distributions on an airnafl during decomposition p 136 N87-11740 [NASA-TM-R3250] p 76 N87-12539 ground lightning Simulation tests and in-flight lightning SEQUENTIAL CONTROL Cryogenic wound rotor for lightweight, high voltage attachments p 82 A87-15017 Electroluminescent (EL) remotely-controlled landing generators TSAR (Theater Simulation of Airbase Resources) zone marker light system [AD-W12370] p 130 N87-12768 database dictionary F-4E [ AD-DO123861 p 87 N87-11716 RUBBER [ AD-A1695751 p 139 N87-13352 Criteria for asphalt-rubber concrete in civil airport SERVICE LIFE SIMULATORS pavements: Mixture design Development of a GFRP wing in accordance with FAR Fabrication and testing of lightweight hydraulic system Part 23 p 92 A87-13993 [M)TIFAA/PM-86/39] p 129 N87-11910 simulator hardware RUN TIME (COMPUTERS) SERVOMECHANISMS [AD-A1698841 p 130 N87-12711 A redundant actuating system with servo valves of low Computational enhancements to a 4D algorithm for SITE SELECTION --. hydraulic loss p 93 A87-14025 aircraft trajectory optimization p 134 A87-13359 The siting, installation and operational suitability of the RUNGE-KUlTA METHOD Preliminary design of electromechanicalservosystems Automated Weather Observing System (AWOS) at [SAE PAPER 8517591 p 129 A87-15482 Acceleration to a steady state for the Euler equations heliports j SHEAR FLOW [ DOT/FAA/PM46/30] p 133 N87-13099 p70 A87-14096 I Spectral methods lor modeling supersonic chemically Finite element Navier-Stokes calculation of SIZE (DIMENSIONS) reacting flowfields p 70 A87-14110 three-dimensional turbulent flow near a propeller Sizing hybrid packages for optimum reliability I RUNWAY CONDITIONS p 70 A87-14101 p 128 A87-15433 I Runway incursions at controlled airports in the United Large-scale coherent structures in free turbulent flows SKIN FRICTION States and their aerodynamic sound p 138 A87-15458 Influence of trailing-edge meshes on skin friction in ~ I [ PB86-9170031 p84 N87-11711 SHIPS Navier-Stokescalculations p 71 A87-14125 1 Number and duration of Runway Visual Range (RVR) Parameter estimation and in-plane distortion invariant SLENDER BODIES runs for RVR-values lower than 225 m chord processing p 135 A87-13689 Vortex shedding of a square cylinder in front of a slender airfoil at high Reynolds numbers. Part 2: Compressibility [ KNMI-TR-85(FM)] p 119 N87-11805 Simulator design features for helicopter landing on small effect RUNWAYS ships. 1: A performance study [ MPIS-24/1985] p75 N87-11704 Advanced construction procedures: Confined bases for [ AD-A1695141 p 119 N87-12572 The effect of a winglet on the spatial vortex of a slender airport pavements SHOCK LOADS [FAA/PM-86/9] p 118 N87-11799 body at high angle of attack Notes on a generic parachute opening force analysis [AD-AI 699251 p 65 N87-12533 I Vertical deflection characteristics of aircraft tyres [AlAA PAPER 86-24401 p 67 A87-13788 [ESDU-86005] p 129 N87-11992 SLENDER WINGS SHOCK TESTS Vortex panel calculation of wake rollup behind a large Blast gust loading on a 35 degree swept-back wing aspect ratio wing p 70 A87-14102 S [ AD-A16941 51 p 116 N87-12570 Applicationsof CONMIN to wing design optimizationwith I SHOCK TUNNELS vortex flow effect p 98 N87-11737 SAFETY FACTORS Further shock tunnel studies of scramjet phenomena Some experiences in aircraft aeroelastic design using Built-In-Test for fail-safe design p 128 A87-15428 [ NASA-CR-179937) p 77 N87-12542 Preliminary Aeroelastic Design of Structures (PAD) SANDS SHOCK WAVE INTERACTION p 98 N87-11747 Advanced construction procedures: Confined bases for Shock boundary layer interactions in laminar transonic SOFTWARE TOOLS airport pavements flow over airfoils using a hybrid method Tml to develop real time simulation systems [ FAA/PM-86/9] p 118 N87-11799 p66 A87-13503 [INPE-3979-TDL/233I p 137 N87-13179

A-2 1 SOLID PROPELLANTCOMBUSTION SUBJECT INDEX

SOLID PROPELLANTCOMBUSTION STAGNATION FLOW Environmental Stress Screening (ESS) demonstrates its Experimental investigation Of a solid fuel ramjet Visualisation of axial turbine tip clearance flow using a value in the field p 127 A87-15403 combustor p 104 A87-13658 linear cascade STRESS CONCENTRATION SONIC BOOMS [CUED/A-TURBO/TR-1221 p 107 N87-12560 The effect of material compressibility (Poisson ratio) on Noise of high speed surfaces p 138 A87-13595 STANDARDS the elasto-plastic solution to the problem of a cylinder under SOUND FIELDS The development of dynamic performance standards internal pressure (coldworking situation) The active minimization of harmonic enClOSed sound for civil rotorcraft seats p 89 A87-13666 p 124 A87-13642 fields p 138 A87-13593 STARTERS STRESS INTENSITY FACTORS Experimental investigation of near and far acoustic field Component improvement program task 83-01, 36E133 Analysis of mixed-mode crack propagation using the of a small turbojet p 138 A87-13605 air turbine starter boundary integral method SOUND PROPAGATION [AD-AI 694831 p 108 N87-12562 [NASA-CR-179518] p 131 N87-12915 On sound propagation in centrifugal fan casings STARTING STRUCTURAL ANALYSIS [ ESA-lT-9571 p 138 N87-12326 Start-up of a wind tunnel with a multichannel diffuser PIAS A program for an iterative aeroelastic SOIulion SPACECHARGE p 72 A87-15206 p 97 N87-11725 Flight model discharge system STATE ESTIMATION STAEEL Structural tailoring of engine blades. phase 2 [ AD-A1694231 p 117 N87-12571 Aircraft flight data compatibility checking using maximum p 106 N87-11731 SPACE NAVIGATION likelihood and extended Kalman filter estimation Application of modern structural optimization lovibration ION, National Technical Meeting, Long Beach, CA. p 113 A87-16184 reduction in rotorcraft p 115 N87-11752 January 21-23. 1986. Proceedings p 85 A87-13532 Comparison of two techniques of I.F.D. based on a Optimization of helicopter rotor blade design for SPACESHUTTLES non-linear stochastic model of an aircraft --- Instrument minimum vibration p 99 N87-11756 Tradeoff methods in multiobjective insensitive design Fault Detection p 114 A87-16196 Optimization applications in aircraft engine design and of airplane control systems p 115 N87-11730 State estimation of flying vehicle p 114 A87-16209 test p 106 N87-11768 Evaluation of a nonlinear parameter extraction STATIC ELECTRICITY STRUCTURAL DESIGN mathematical model including the term C(subm(sub delta International Aerospace and Ground Conference on Mechanism of energy absorption via buckling - An e squared)) Lightning and Static Electricity. 1Ith, Dayton, OH, June analytical study p 124 A87-13682 [ NASA-TM-87731I p 116 N87-12566 24-26. 1986. Technical Papers p 80 A87-15001 Recent Expenences in Multidisciplinary Analysis and SPACECRAFT DESIGN A review of aerospace and ground lightning threat Optimization. part 1 Ames accelerates research on hypersonic technology charactenstics and applications p 132 A87-15002 [ NASA-CP-2327-PT-1I p 96 N87-11717 p64 A87-13911 STATIC LOADS Practical considerations in aeroelastic design SPACECRAFT MODELS Some observations on the behavior of the Langley model p 97 N87-11720 Flight model discharge system rotor blade Flutter optimization in fighter aircraft design [AD-A1694231 p 117 N87-12571 [NASA-CR-179880] p 74 N87-11695 p 97 N87-11721 SPACECRAFT STABILITY STATIC PRESSURE The automated strength-aeroelastic design of Tradeoff methods in multiobjective insensitive design Pitot and static errors in steady level flight aerospace structures program p 98 N87-11749 of airplane control systems p 115 N87-11730 [ESDU-86006] p 74 N87-11691 Optimization of helicopter rotor blade design for SPACECRAFTSTRUCTURES STATIC TESTS minimum vibration p 99 N87-11756 Advanced manufacturing technology for structural Correlation of experimental static and dynamic response Application of numerical optimization to rotor aircraftlaerospace components p 123 A87-13074 of simple structural components p 124 A87-13683 aerodynamic design p 99 N87-11757 Polymer, metal. and ceramic matrix composites for Static test of an ultralight airplane The structural optimization of a spreader bar for twin advanced aircraft engine applications [AIAA PAPER 86-26001 p 64 A87-14034 lift helicopter operations p 100 N87-11759 p 121 A87-15187 STATORS Comments on gust response constrained optimization The automated strength-aeroelastic design of Investigation of coating performance and corrosion of p 115 N87-11774 aerospace structures program p 98 N87-11749 compressor components in the TF30-P-3engine of F111C STRUCTURAL DESIGN CRITERIA SPANWISE BLOWING aircraft The status of crashworthiness design criteria Spanwise variation of laminar separation bubbles on [ AD-At 688021 p 107 N87-11792 p89 A87-13664 wings at low Reynolds number p 71 A87-14362 STEADY FLOW Survivability and crashworthiness design criteria SPATIAL DISTRIBUTION Aerodynamic coefficients of a circular wing in steady p 89 A87-13665 Atmospheric electrical modeling in support of the NASA subsonic flow p 67 A87-13653 Analysis of U.S. civil rotorcraftaccidents for development F106 Storm Hazards Project Visualization of wing lip vortices in accelerating and of improved design criteria p 78 A87-13685 [ NASA-CR-I79801 ] p 132 N87-12082 steady flow p 72 A87-14370 The 3600 hp split-torque helicopter transmission SPECKLE PATTERNS Application of viscous-inviscid interaction methods to [ NASA-CR-174932I p 106 N87-11788 Wholefield displacement measurements using speckle transonic turbulent flows STRUCTURAL FAILURE image processing techniques for crash tests [NASA-CR-l799001 p 75 N87-11700 The inspectable structure p 65 A87-16397 p 124 A87-13680 STEELS STRUCTURAL STABILITY SPECTRAL METHODS Carburizing steel for high temperature service Application of a mixed variational approach to Spectral methods for modeling supersonic chemically [ AD-At 683271 p 122 N87-11877 aeroelastic stability analysis of a nonuniform blade reacting flowfields p 70 A87-I4110 Selection of rolling-elementbearing steels for long-life p 126 A87-14423 SPEECH RECOGNITION application STRUTS A test on the reliability and performance of the verbex [ NASA-TM-88881] p 129 N87-11993 Length adjustable strut link with low aerodynamic drag series 4000 voice recognizer STOCHASTIC PROCESSES [ AD-DO12279 I p 77 N87-12543 [AD-At 69066 1 p 130 N87-12729 1986 American Control Conference. 5th. Seanle. WA. SUBSONIC FLOW SPEED CONTROL June 18-20. 1986. Proceedings. Volumes 1, 2, 8 3 Aerodynamic coefficients of a circular wing in steady Mathematical model and digital simulation for speed p 133 A87-13301 subsonic flow p 67 A87-13653 control system of two-spool turbojet engine Optimal stochastic ObSeNerS applied lo hydraulic Tip vortices of wings in subsonic and transonic flow: A p 105 A87-14139 actuation systems p 87 A87-13354 numerical simulation SPIN DYNAMICS An efficient decision-making-freefilter for processes with [ NASA-TM-883341 p 75 N87-11699 Flight control design using nonlinear inverse dynamics abrupt changes p 136 A87-16189 SUBSONIC WIND TUNNELS p 109 A87-13352 Comparison of two techniques of I.F.D. based on a Measurements in the high subsonic region in the SPIN TESTS non-linear stochastic model of an aircraft --- Instrument TU-Berlin wind tunnel with adaptive walls An experimental investigation of free-tip response to a Fault Detection p 114 A87-16196 p 117 A87-14009 jet STOPPING SUCTION [ NASA-TM-882501 p 76 N87-12539 Frictional and retarding forces on aircraft lyres. Part 4: Combination of suction and tangential blowing in SPLINE FUNCTIONS Estimation of effects of yaw boundary layer control p 67 A87-13641 The method of calculating the desired flight path of [ ESDU-86016-PT-41 p 131 N87-12868 Applications of CONMIN lo wing design optimization with terrain following technique with circular arc spline STRAPDOWN INERTIAL GUIDANCE vortex flow effect p 98 N87-11737 p 111 A87-14136 In-flight transfer alignment/calibration of a strapdown SUPERPLASTICITY SPRAY CHARACTERISTICS INS that employs carouseled instruments and IMU Design considerations for superplastically formed Spray characteristics of two combined jet atomizers indexing p 85 A87-13438 complex aircraft structures p 87 A87-I3151 p 124 A87-13660 STRATOSPHERE SUPERSONIC AIRCRAFT SPRAYERS Possible military applications of stratospheric airship Computation of optimum-optimorum wing-fuselage Prediction of velocity coefficient and spray cone angle discussed p 101 N87-12716 configuration for future generation of supersonic aircraft for simplex swirl atomizers p 125 A87-13830 STRATUSCLOUDS p 74 A87-15761 STABILITY AUGMENTATION Comparative flight measurement of icing parameters for A review of the technical development of Concorde Multivariable flight control for an attack helicopter the DO 28 D2 propeller-driven aircraft of the German Army p 96 A87-16408 p 109 A87-13379 Testing Office 61 and for DFVLR's Falcon 20 E jet aircraft Applications of CONMIN to wing design optimization with Tradeoff methods in multiobjective insensitive design in stratus clouds vortex flow effect p 98 N87-11737 of airplane control systems p 115 N87-11730 [ ESA-TT-9411 p 83 N87-11709 SUPERSONIC COMBUSTION RAMJET ENGINES STABILITY DERIVATIVES STRESS ANALYSIS Experimental investigation of e solid fuel ramjet Aircrall control input Optimization for aerodynamic A comparison of measured and calculatedstress in solid combustor p 104 A87-13658 derivative estimation in dynamic manoeuvres and ribbon parachute canopies Spectral methods for modeling supersonic chemically p 113 A87-16183 [AIAA PAPER 86-24881 p 80 A87-13815 reacting flowfields p 70 A87-14110 STABILITY TESTS Determination of dynamic stresses in the heat-insulating Further shock tunnel studies of scramjet phenomena Mach 6 experimental and theoretical stability and coatings of flight vehicles during aerodynamic heating [ NASA-CR-1799371 p 77 N87-I2542 performanceof a finned cylindrical body at angles of attack p 72 A87-15223 SUPERSONIC CRUISE AIRCRAFT RESEARCH up to 65 deg Analysis of a composite thin-walled aircraft structure Applicationsof CONMIN lowing design optimization with [ NASA-TM-890501 p 76 N87-12538 p 127 A87-15226 vortex flow effect p 98 N87-11737

A-22 SUBJECT INDEX THUNDERSTORMS

SUPERSONIC FLOW SYSTEMS ANALYSIS Guidance law simulation studies for complex approaches Cornputation of two-dimensional supersonic turbulent Reachable outputs in systems with bounded parameter using the Microwave Landing System (MLS) flow over a compression corner p 66 A87-13502 uncertainties - Application to failure detecbon [NASA-CR-1751821 p 87 N87-12552 Numerical calculation of three-dimensional inviscid p 134 A87-13326 TERRAIN FOLLOWING AIRCRAFT supersonic flows p66 A87-13504 Application of Markov models for RMA assessment .- The method of calculating the desired flight path of Spectral methods for modeling supersonic chemically Reliability, Maintainability and Availability terrain following technique with circular arc spline reacting flowfields p 70 A87-14110 p 128 A87-15435 p 111 A87-14136 Theoretical and expenmental investigations of sensor Experimental and numerical investigation of supersonic TEST FACILITIES location for oplmal aeroelasbc system slate estimation turbulent flow through a square duct p 70 A87-14117 ATAS - The new test bed p 92 A87-14003 p 115 N87-11794 Constant-density approximation to Taylor-Maccoll TEXAS SYSTEMS ENGINEERING Revised Uniform Summary of Surface Weather solution p 71 A87-14127 Tool to develop real time simulation systems Observations (RUSSWO). Parts A-F Ellington ANGB. Comment on 'Computation of choked and supersonic tINPE-3979-TDLI2331 p 137 N87-13179 turbomachinery flows by a modified potential method' Texas SYSTEMS INTEGRATION [ AD-A1693891 p 133 N87-13105 p 71 A87-14129 Turbine bypass remote augmentor lift system for Impact of airfoil profile on the supersonic aerodynamics V/STOL aircraft p 105 A87-14364 THERMAL INSTABILITY of delta wings p 71 A87-14363 Integrated active control systems Methods of Cryogenic wound rotor for lightweight. high voltage generators An approximate method of estimating the aerodynamic alaonthmic intearation --- Russran book [AD-DO12370] p 130 N87-12768 interference between two parallel bodies in a supersonic p 135 A87-14682 flow (axial force) Fault-tolerant C31 system A(0). A(I). MTBF allocations THERMAL INSULATION [BR-100271] p 76 N87-12540 p 86 A87-15427 Determination of dynamic stresses in the heat-insulating coatings of flight vehicles during aerodynamic heating SUPERSONIC NOZZLES p 72 A87-15223 Fnamic loads on twin jet exhaust nozzles due to shock noise p 94 A87-14369 T THERMOCHEMICAL PROPERTIES SUPERSONIC SPEED Thermochemical evaluation of fuel candidatesfor ramjet TAIL ASSEMBLIES Lower-side normal force characteristics of delta wings propulsion p 121 A87-13659 Design and manufactunng of a CFRP tail fin for the at supersonic speeds p 72 A87-14372 THERMODYNAMIC PROPERTIES A300 SUPERSONIC WIND TUNNELS Analysis and verification of the icing scaling equations. [ MBB-UT-006-861 p 93 A87-14026 Start-up of a wind tunnel with a multichannel diffuser Volume 1: Revision Length adiustable strut link with low aerodynamic drag p 72 A87-15206 [AD-A167976] p 85 N87-12551 [ AD-DO1 22791 p77 N87-12543 SURFACE PROPERTIES THERMODYNAMICS TAKEOFF Carburizing steel for high temperature service Characterization and dynamical studies of polymers in Airplane flight through wind shear turbulence [ AD-AI68327 I p 122 N87-11877 dipolar (aprotic) liquids p A87-14371 A constitutive law for finite element contact problems 80 [ AD-A1 692431 p 123 N87-12685 TARGET ACQUISITION with unclassical friction THERMOELASTICITY Precision point target tracking p 101 A87-13545 [ NASA-TM-888381 p 131 N87-12924 Determination of dvnamic stresses in the heat-insulating TAXIING SURFACE ROUGHNESS EFFECTS coatings of flight vehicles during aerodynamic heating The equivalent masses at nose landing-gears during A study of the effect of surface roughness on the head p 72 A87-15223 landing-impacts and when taxiing over runway resistance of an aircraft p 94 A87-14717 THICK WALLS perturbations p 88 A87-13637 SURFACES Lightweight sidewalls for aircraft interior noise control TAYLOR INSTABILITY Analysis of a composite thin-walled aircraft structure [ NASA-CR-1724901 p 138 N87-12323 Constant-density approximation to Taylor-Maccoll p 127 A87-15226 THIN WALLS solution p 71 A87-14127 SURVEILLANCE Analysis of a composite thin-walled aircraft structure TECHNOLOGICAL FORECASTING Mobile communications. navigation and surveillance p 127 A87-15226 Technlcal/economic evaluation of new propfan [IAF PAPER 863331 p86 A87-16027 THREE DIMENSIONAL BODIES concepts in cornpanson wth the turbofan of the 1990s SURVEILLANCE RADAR Utilization of 3-D programs for aircraft design and p 104 A87-13989 Mode beacom system: Functional description development p88 A87-13646 S Ramiet aDDliCahOn in atmosDheres of different celestial [ DOT/FAA/PM-86/19] p 87 N67-11715 . .. THREE DIMENSIONAL FLOW SURVEYS bodies Numerical calculation of three-dimensional inviscid [IAF PAPER 86-181 I p 120 A87-15920 General aviation activity and avionics survey supersonic flows p 66 A87-13504 Mobile communications. naviaation and surveillance [ AD-A1685821 p 65 N87-11666 Theoretical investigations of transonic rotor-blade [IAF PAPER 8-33] p86 A87-16027 SURVIVAL EQUIPMENT aerodynamics p68 A87-13994 US air transport technology Where next? Aircraft accidents, survival. and rescue - Finite element Navier-Stokes calculation of p65 A87-16398 p 78 A87-13581 three-dimensional turbulent flow near a propeller SWEPT FORWARD WINGS The portfolio model of technological development in the p 70 A87-14101 Aeroelastic divergence of trimmed aircraft aircraft industry Vortex panel calculation of wake rollup behind a large [ AD-A1708321 p N87-12534 p94 A67-14368 66 aspect ratio wing p 70 A87-14102 TECHNOLOGY ASSESSMENT Forward-swept wing configuration designed for high Convergence acceleration for a three-dimensional maneuverability by use of a transonic computational Advanced manufacturing technology for structural EulerlNavier-Stokes zonal approach p 70 A87-14105 method aircraft/aerospace components p 123 A87-13074 THREE DIMENSIONAL MOTION Ames accelerates research on hypersonic technology [ NASA-TP-26281 p 75 N87-11702 Mathematical modeling of the motion of a statically p A87-13911 SWEPT WINGS 64 deformed delta-shaped glider p 95 A87-15205 Applicationsof CONMIN to wing design optimizationwith State-of-the-art techniques for lightning THROATS susceptibility/vulnerability assessments vortex flow effect p 98 N67-11737 Theoretical studies of the ETW diffuser and of the p 126 A67-15006 SWEPTBACK WINGS second throat p 69 A87-14022 Nonlinear acousbcs Achievements. prospects. Blast gust loading on a 35 degree swept-back wing - THRUST problems p 138 A87-15582 [AD-A169415] p 116 N87-12570 Determination of the thrust and net efficiency of a SWIRLING The portfoliomodel of technological development in the propeller and flow parameters behind the propeller Prediction of velocity coefficient and spray cone angle aircraft industry p 105 A87-15204 [ AD-A1 708321 p N67-12534 for simplex swirl atomizers p 125 A87-13830 66 Propellarlbody interaction for thrust and drag SWITCHING CIRCUITS Assessment of damage tolerance requirements and [ ESDU-860171 p 76 N87-12537 Component improvement program task 83-01. 36E133 analyses: A user's manual for crack growth and crack THRUST CONTROL air turbine starter initiation analysis: DAMGRO Thrust reverser-exhaust nozzle assembly lor a gas [!."-A!?! 20sj p 132 N87-12939 [AD-A169483] p 108 N87-12562 turbine engine SYNCHROPHASING TECHNOLOGY UTILIZATION [AD-D012390] p 108 N87-12561 AV-BB/GR Mk 5 airframe composite applications Comparison of two propeller source models for aircraft THRUSTREVERSAL p 88 A87-13628 interior noise studies p88 A87-13596 Effect of port comer geometry on the internal Technical-historical development of parachutes and Analytical model for investigation of interior noise performance of a rotating-vane-typethrust reverser characteristics in aircraft wth multiple propellers including their applications since World War I [NASA-TP-2624] p 77 N87-12541 [AIAA PAPER 86-24231 p 79 A87-13777 synchrophasing p 94 A87-14925 Thrust reverser-exhaust nozzle assembly for a gas SYSTEM FAILURES Ramjet application in atmospheres of different celestial turbine engine Evaluation of detectability and distinguishability of bodies [AD-D0123901 p 106 N87-12561 [IAF PAPER 86-1811 p 120 A87-15920 aircraft control element failures using flight test data THRUST-WEIGHT RATIO TEMPERATURE EFFECTS p 110 A87-13435 Polymer, metal, and ceramic matrix composites for EnvironmentalStress Screening (ESS) demonstrates its Diffusion bonding of certain refractory metals advanced aircraft engine applications p 121 A87-13171 value in the field p 127 A87-15403 p 121 A87-15187 Sensor failure detection in flight control systems using A study of the eflect of the temperalure factor on THUNDERSTORMS deterministic observers p 114 A87-16195 pressure losses in the cooling system of the leading edge Summary of NASA storm hazards lightning research, SYSTEM IDENTIFICATION of a deflector vane --- for gas turbine engines 1980-1985 p 80 A87-15003 Identification and system parameter estimation 1985; p 127 A87-15218 Joint thunderstorm operations using the NASA F-106B Proceedings of the Seventh Symposium. University of TERMINAL GUIDANCE and FAATC/AFWAL Convair 580 airplanes York. England, July 3-7. 1985. Volumes 1 8 2 Time-based air traffic management using expert p 95 A87-15018 p 135 A87-16176 systems p 85 A87-13362 Effect of E-field mill locationon accuracy of electric field Determination of nonlinear aerodynamic coefficients The principle of optimality in the mean for fault-tolerant measurements wth instrumented airplane using the estimation-beforemodelingmethods systems -.-for aircraft terminal guidance p 95 A87-15027 p 114 A87-16202 p 112 A87-15212 Mobile intercept of storms p132 N87-13064

A-23 TILT ROTOR AIRCRAFT SUBJECT INDEX

TILT ROTOR AIRCRAFT Numerical solution of transonic potential flows with finite TURBINE ENGINES v-22 Osprey - Multi-SBNiCe workhorse elements method using multigrid technique A real-time Simulation evaluation of an advanced p96 A87-16400 p68 A87-13900 detection, isolation and accommodation algorithm for TILT ROTOR RESEARCH AIRCRAFT PROGRAM Theoretical investigations of transonic rotor-blade sensor failures in turbine engines p 103 A87-13318 V-22 Osprey - Mulb-SBNiCe workhorse aerodynamics p 68 A87-13994 Turbine bypass remote augmentor lift system for p96 A87-16400 Acceleration to a steady state for the Euler equations V/STOL aircraft p 105 A87-14364 TIME LAG p 70 A87-14096 Long-term deposit formation in aviation turbine fuel at elevated temperature p 121 A87-14986 Frequency domain parameter estimationof aeronautical Comment on 'Computation of choked and supersonic systems without and with time delay turbomachinery flows by a modified potential method' Compound cycle engine program [ NASA-TM-888791 p 107 N87-11790 p 114 A87-16193 p 71 A87-14129 TIME MARCHING Aviation turbine fuels, 1985 An implicit time-marching scheme for transonic flow [ DE86-012140] p 122 N87-11908 An implicit time-marching scheme for transonic flow p 71 A87-14261 p 71 A87-14261 Component improvement program task 63-01, 36E133 Direct-inverse transonic wing analysis-design method TIME RESPONSE air turbine starter Time scale analysis of a dQiW flight control System with viscous interaction p 71 A87-14365 [AD- A169483 I p 108 N87-12562 p 109 A87-13347 Vectorizable multigrid algorithms for transonic-flow Turbine air seal with full backside cooling TIPS calculations p 72 A87-14652 [AD-W124051 p 108 N87-12564 An experimental investigation 01 free-lip response to a Advances in the understanding and computation of Improved vane platform sealing and retention means jet unsteady transonic flow p 73 A87-15452 [ AD-DO124071 p 131 N87-12681 [ NASA-TM-882501 p 76 N87-12539 Unsteady transonic aerodynamics and aeroelasticity TURBINES Supplementary calibration test of the tipaerodynamics- p 73 A87-15453 Turbine air seal with full backside cooling and acoustics-test pressure transducers Laser velocimetry for transonic aerodynamics [ AD-DO124051 p 108 N87-12564 [ NASA-TM-883121 p 131 N87-12830 p 74 A87-15467 TURBOCOMPRESSORS TOLERANCES (MECHANICS) Further development of the axial-radial compressor Some asymptotic types of transonic vortex flows p 104 A87-13998 Assessment of damage tolerance requirements and p 74 A87-15553 analyses: A user's manual for crack growth and crack Compound cycle engine program Tip vortices 01 wings in subsonic and transonic flow: A initiation analysis: DAMGRO [ NASA-TM-88879I p 107 N87-11790 numerical simulation [ AD-A171 2091 p 132 N87-12939 Journal of engineering thermophysics (selected [NASA-TM-88334I p 75 N87-11699 TORQUE articles) Finite element contact analysis 01 ring gear and Application 01 viscous-inviscid interaction methods lo [AD-A169452] p 139 N87-13347 support p 127 A87-15193 transonic turbulent llows TURBOFAN ENQINES TOROUECONVERTERS [NASA-CR-179900] p 75 N87-11700 A real-time simulation evaluation of an advanced The 3600 hp split-torque helicopter transmission Calculated effects of varying Reynolds Number and detection, isolation and accommodation algorithm for [NASA-CR-1749321 p 106 N87-11788 dynamic pressure on flexible wings a1 transonic speeds sensor failures in turbine engines p 103 A87-I3318 TORSIONAL VIBRATION p 75 N87-11736 Technicalleconomic evaluation of new propfan Application 01 a mixed variational approach to The prediction of transonic loading advancing helicopter concepts in comparison with the turbofan 01 the 1990s aeroelastic stability analysis of a nonuniform blade rotors p 104 A87-13989 p 126 A87-14423 [AD-A166217] p 100 N87-11781 For small airliners and executive jets TOUGHNESS Viscous-inviscidinteraction in transonic separated flow p 105 A87-15179 Carburizing steel for high temperature service over solid and porous airfoils and cascades FlOO fuel sampling analysis: Foreign samples [ AD-A1683271 p 122 N87-11877 p 76 N87-12535 [AD-A168573] p 122 N67-11904 TOWED BODIES TRANSONIC SPEED Length adjustable strut link with low aerodynamic drag The structural optimization of a spreader bar for twin Forward-swept wing configuration designed for high [ AD-DO1 22791 p 77 N87-12543 lift helicopter operations p 100 N87-11759 maneuverability by use of a transonic computational Simplified forms 01 performance equations. Addendum TOXIC HAZARDS method A Effect on aeroplane level speed 01 small changes in Fire safety science; Proceedingsot the First International [NASA-TP-26281 p 75 N87-11702 thrust. drag, weight. power Symposium. Gaithersburg, MD. October 7-11. 1985 TRANSONIC WIND TUNNELS [ ESDU-86004-ADD-A1 p 100 N87-12556 p 78 A87-13186 Theoretical studies 01 the ETW diffuser and of the Effects 01 test cell recirculation on high-bypass turbofan TRACKING (POSITION) second throat p 69 A87-14022 engines during simulated altitude tests Methods lor obtaining robust tracking control laws Status report on the European Transonic Wind Tunnel [AD-A171418] p 108 N87-12565 p 134 A87-13319 (Em) p 117 A87-14023 TURBOFANS Precision point target tracking p 101 A87-13545 Calculated eflects 01 varying Reynolds Number and On sound propagation in centrifugal Ian casings TRADEOFFS dynamic pressure on flexible wings at transonic speeds [ ESA-lT-9571 p 138 N87-12326 MTFCS (multiple target formation flight control system] p 75 N87-11738 TURBOJET ENGINES Formation position sensor trade-ofl analysis Methods for assessing wall interference in the 2- by Variable structure control 01 a turbojet engine p 110 A87-13536 2-loot adaptive-wall wind tunnel p 103 A87-13343 TRAILING EDGES [ NASA-TM-882521 p 118 N87-11600 Experimental investigation of near and Iar acoustic field Influence of trailing-edge meshes skin friction on in A description of the active and passive of a small turbojet p 138 A87-13605 Navier-Stokes calculations p 71 A87-14125 sidewall-boundary-layerremoval systems of the 0.3-meter On the improvement of an expendable turbojet engine TRAINING AIRCRAFT transonic cryogenic tunnel flight envelope p 104 A87-13647 Exploratorywind-tunnel investigation of the stability and NASA-TM-877641 p 118 N87-11601 control characteristics 01 advanced general aviation TRANSPORT AIRCRAFT Mathematical model and digital simulation for speed configurations Impact of mismodeled idle engine perlormance on control system of two-spool turbojet engine [AIAA PAPER 86.25961 p 111 A87-14031 calculation and tracking of optimal 4-D descent p 105 A87-14139 TRAJECTORY ANALYSIS trajectories p 88 A87-13360 Computational fluid dynamic studies of certain ducted An aerodynamic analysis and the subsequent motion A redundant actuating system with servo valves of low bluff-body flowfields relevant to turbojet combustors. of external store p66 A87-13501 hydraulic loss p 93 A87-14025 Volume 1: Time-dependentcalculations with the k-epsilon TRAJECTORY OPTIMIZATION Airlines look at 150-seaters p 83 A87-15180 turbulence model for an existing centerbody combustor Computational enhancements to a 4D algorithm --.for Manufacturers plan new long-range aircraft [AD-A1714341 p 131 N87-12816 aircraft trajectory optimization p 134 A87-13359 p 95 A87-15181 TURBOMACHINERY Impact 01 mismodeled idle engine performance on Practical considerations in aeroelastic design Comment on 'Computation of choked and supersonic calculation and tracking 01 optimal 4-0 descent p 97 N87-11720 turbomachinery flows by a modilied potential method' trajectories p 88 A87-13360 Experiences performing conceptual design Optimization p 71 A87-14129 TRANSFER OF TRAINING of transport aircraft p 97 N87-11723 Performance evaluation 01 an inverse integral equation Simulator design features lor helicopter landing on small Multidisciplinary optimization applied to a transport method applied lo turbomachine cascades ships. 1: A performance study aircraft p 84 N87-11746 p 72 A87-14771 IAD-Al69514) P 119 N87-12572 Some experiences in aircraft aeroelastic design using TURBOPROP AIRCRAFT Simulator design and instructional features for carrier Preliminary Aeroalastic Design of Structures (PAD) Wind-tunnel investigation of the OMAC canard landing: A field transler study p 98 N87-11747 configuration [ AD-A1699621 119 N87-12573 P TUNING [AIAA PAPER 86-26081 p 69 A87-14038 TRANSIENT RESPONSE Optimization of cascade blade mistuning under flutter Concentrated mass effects on the flutter of a composite Aircraft lightning-induced transient test and protection and forced response constraints p 106 N87-11732 advanced turboprop model comparison p 82 A87-15022 TURBINE BLADES [ NASA-TM-888541 p 130 N87-12017 TRANSMISSION LOSS Automated infrared inspection of jet engine turbine Window acoustic study lor advanced turboprop aircraft Window acoustic study lor advanced turboprop aircraft blades p 125 A87-13719 [NASA-CR-1723911 p 138 N87-12322 [ NASA-CR-172391] p 138 N87-12322 STAEBL: Structural tailoring of engine blades, phase 2 TRANSMISSIONS(MACHINE ELEMENTS) p 106 N87-I1731 Lightweight sidewalls lor aircraft interior noise control The 3600 hp split-torque helicopter transmission Optimization of cascade blade mistuning under flutter [ NASA-CR-172490I p 138 N87-12323 [NASA-CR-174932) p 106 N87-11788 and forced response constraints p 106 N87-11732 TURBOPROP ENGINES TRANSONIC FLOW On optimal design lor the blade-rootlhub interlace in Finite element contact analysis 01 ring gear and Shock boundary layer interactions in laminar transonic jet engines p 106 N87-11769 support p 127 A87-15193 flow over airfoils using a hybrid method Fabrication 01 cooled radial turbine rotor TURBOSHAFTS p66 A87-13503 [NASA-CR-179503] p 107 N67-11789 Multi-variable control 01 the GE T700 engine using the An exterior Poisson solver using fast direct methods Journal of engineering thermophysics (selected LQGILTR design methodology --- Linear Quadratic and boundary integral equations with applications to articles) Gaussian/ Loop Transfer Recovery method nonlinear potential flow p 125 A87-13872 [AD-A1694521 p 139 N87-13347 p 103 A87-13418

A-24 SUBJECT INDEX WALL FLOW

TURBULENTBOUNDARYLAYER v VISUAL FLIGHT Computation of sharpfin-inducedshock wavelturbulent Evaluation of a visual system in its support of simulated boundary-layer interactions p 70 A87-14104 V/STOL AIRCRAFT helicopter flight Direct-inverse transonic wing analysisdesgn method Turbine bypass remote augmentor lift system for [AD-A168829] p 102 N87-11783 with viscous interaction p 71 A87-14365 V/STOL aircraft p 105 A87-14364 Number and duration of Runway Visual Range (RVR) TURBULENT FLOW The induced aerodynamics of jet and fan powered runs for RVR-values lower than 225 m Turbulent buoyant flow and pressure variations around V/STOL aircraft p 73 A87-15459 [ KNMI-TR-B5(FM)] p 119 N87-11805 an aircraft fuselage in a cross wind near the ground --_ Recent advances in prediction methods for jet-induced VISUAL PERCEPTION simulated fire in cabin p 78 A87-13187 effects on V/STOL aircraft p 73 A87-15462 Evaluationof a visual system in its support of simulated A wind-tunnel method for V/STOL testing Computation of two-dimensional supersonic turbulent helicopter flight p 118 A87-15463 [AD-A168829] p 102 N87-11783 flow over a compression corner p 66 A87-13502 VALVES Number and duration of Runway Visual Range (RVR) Combination of suction and tangential blowing in A redundant actuating system with servo valves of low boundary layer control p67 A87-13641 runs for RVR-values lower than 225 m hydraulic loss p 93 A87-14025 [ KNMI-TR-B5(FM)] p 119 N87-11605 Experimental investigation of vortex flow over VANELESS DIFFUSERS doubledelta wing at high alpha p 67 A87-13652 VOICE COMMUNICATION Development of an advanced vaneless inlet particle A test on the reliablity and performance of the verbex Finite element Navier-Stokes calculation of separator for helicopter engines p 105 A87-14984 series 4000 voice recognizer three-dimensional turbulent flow near a propeller VANES [ AD-A16soSsl p 130 N87-12729 p 70 A87-14101 Effect of port corner geometry on the internal VOLTAGEGENERATORS Turbulent flow around a winglfuselage-type juncture performance of a rotatingvane-type thrust reverser Cryogenic wound rotor for lightweight, high voltage [ NASA-TP-26241 p 77 N87-12541 p 70 A87-14108 generators Influence of trailing-edge meshes on skin friction in Improved vane platform sealing and retention means [ AD-DO1 23701 p 130 N87-12768 Navier-Stokes calculations p 71 A87-14125 [AD-DO12407] p 131 N87-12881 VORTEX BREAKDOWN Modeling of turbulent separated flows for aerodynamic VARIABLE GEOMETRY STRUCTURES Vortex flm technoloav A stabilitv and control I, applications p 73 A87-15454 Design considerations for superplastically formed assessment complex aircraft structures p 87 A87-13151 Application of viscous-inviscid interaction methods to [NASA-CR-1724391 p 115 N87-11795 The evolution of adaptive-wall wind tunnels transonic turbulent flows VORTEX FILAMENTS pll8 A87-15464 [NASA-CR-179900] p75 N87-11700 Two-dimensional blade-vortex flow visualization Advances in adaptive wall wind tunnel technique investigation p 70 A87-14111 Computational fluid dynamic studies of certain ducted p 116 A87-15465 bluff-body flowfields relevant to turbojet combustors. VORTEX FLAPS VARIATIONAL PRINCIPLES Vortex flap technology: A stability and control Volume 1: Time-dependentcalculations with the k-epsilon Application of a mixed variational approach to turbulence model for an existing centerbody combustor assessment aeroelastic stabiliky analysis of a nonuniform blade [NASA-CR-172439] p 115 N87-11795 [ AD-A171 4341 p 131 N87-12816 p 126 A87-14423 TURBULENTJETS VORTEX RINGS VECTORS (MATHEMATICS) Axisymmetric vortex lattice method applied to parachute Study of a bounded jet flow considering the initial Vectorizable multigrid algorithms for transonic-flow shapes turbulence. II .In the case of relatively large nozzle aspect calculations p 72 A87-14652 ratio p 71 A87-14263 [AIAA PAPER 86-24561 p 68 A87-13796 VELOCITY DISTRIBUTION VORTEX SHEDDING Large-scale coherent structures in free turbulent flows Prediction of velocity coefficient and spray cone angle On the utilization of vortex methods for parachute and their aerodynamic sound p 138 A87-15458 for simplex swirl atomizers p 125 A87-13830 aerodynamic predictions TURBULENT WAKES VELOCITY MEASUREMENT [AIAA PAPER 86-24551 p68 A87-13795 Vortex panel calculation of wake rollup behind a large Laser velocimetry for transonic aerodynamics Vortex shedding of a square cylinder in front of a slender aspect ratio wing p 70 A87-14102 p 74 A87-15467 airfoil at high Reynolds numbers. Part 2 Compressibility TURNING FLIGHT VERTICAL TAKEOFF AIRCRAFT effect Bank-to-turn utilizing sampled data non-linear control Multiple jet impingement flowfields p 73 A87-15461 [ MPIS-24/1985] p 75 N87-11704 p 109 A87-13346 Aircraft automatic-flight-controlsystem with inversion of Computational fluid dynamic studies of certain ducted Coordinated turn relations - A graphical representation the model in the feed-forward path using a bluff-body flowfields relevant to turbojet combustors. __-of aircraft maneuver p 111 A87-14367 Newton-Raphsontechnique for the inversion Volume 1: Time-dependent calculations with the k-epsilon [NASA-TM-88209] p 116 N87-11796 Optimal descending, hypersonic turn to heading turbulence model for an existing centerbody combustor The 8 m x 6 m low speed wind tunnel at the Chinese [DE86-010989] p 120 N87-12577 [ AD-A1714341 p 131 N87-12816 Aerodynamic Research and Development Center TWO DIMENSIONAL FLOW VORTEX SHEETS [AD-A!68448] p 119 N87-11803 Computation of two-dimensional supersonic turbulent Vortex-sheet capturing in numerical solutions of the The handling qualities and flight characteristics of the flow over a compression corner p 66 A87-13502 incompressible Euler equations p 70 A87-14099 Grumman design 696 simulated twin-engine tilt Nacelle Comparison of numerical solutions of lower order and Vortex panel calculation of wake rollup behind a large V/STOL aircraft higher order integral equationmethods for twodimensional aspect ratio wing p 70 A87-14102 [NASA-TM-86785] p 100 N87-12558 aerofoils VORTICES VERY LARGE SCALE INTEGRATION [AIAA PAPER 66-25911 p 69 A87-14028 Interaction of decaying trailing vortices in ground Grundy Parallel processor architecture makes Two-dimensional blade-vortex flow visualization - shear p66 A87-13499 programming easy p 135 A87-13703 investigation p 70 A87-14111 Experimental investigation of vortex flow over VLSl impact on RAMS strategies in avionics design An implicit time-marching scheme for transonic flow double-delta wing at high alpha p 67 A87-13652 D 128 A87-15423 p 71 A87-14261 Some asymptotic types of transonic vortex flows VIBRATION DAMPING Aerodynamic force calculations of an elliptical circulation p 74 A87-15553 control airfoil p 71 A67-14360 Aeroelastic control of oblique-wing aircraft PIAS A program for an iterative aeroelastic solution D 106 A87-13341 p 97 N87-11725 Aircraft flutter suppression via adapive LOG control Applicationsof CONMIN to wing design optimization with U p 109 A87-13344 vortex flow effect p 98 N87-11737 Load lightening and flutter damping for future Airbus The prediction of transonic loading advancing helicopter ULTRALIGHT AIRCRAFT projects rotors Static test of an ultralight airplane [MBB-UT-004-86] p92 A87-14002 [ AD-A16821 71 p 100 N87-11781 [AIM PAPER 8626001 p64 A87-14034 Possibilitiesfor ODtimization and hiaher-harmoniccontrol The effect of a winglet on the spatial vortex of a slender UNDERWATER ACOUSTICS of helicopter main rotors by blade feathering body at high angle of attack Aero- and hydro-acoustics; Proceedings of the p 111 A87-14021 [AD-A169925] p 65 N87-12533 Symposium. Ecole Centrale de Lyon, Ecully. France. July The effect of lubricant cavitation on the characteristics A summary of the development of integral aerodynamic 3-6, 1985 p 137 A87-13585 of a short hydrodynamic damper p 127 A87-15203 methods for the computation of rotor wake interactions UNSTEADY FLOW Adaptive flutter suppression p 113 A87-16182 [ AD-A1692541 p 77 N87-12545 Visualization of wing tip vortices in accelerating and Application of modern structural optimizationto vibration An analysis of blade vortex interaction aerodynamics steady flow p 72 A87-14370 reduction in rotorcraft p 115 N87-11752 and acoustics p 77 N87-12547 Advances in the understanding and computation of VIBRATIONAL SPECTRA Visualisation of axial turbine tip clearance flow using a unsteady transonic flow p 73 A87-15452 Usina vibrationspectrum characteristics for the flow-path linear cascade Unsteady transonic aerodynamics and aeroelasticity diagnostics of aircraft gas turbine engines [CUED/A-TURBO/TR-1221 p 107 N87-12560 p 73 A87-15453 D 105 A67-15210 VORTICITY Special opportunities in helicopter aerodynamics VISCOELASTICITY An analytical parametric investigation of numerical p74 A87-15469 Charactenzation and dynamical studies of polymers in nonlinear vortex-lattice methods p 67 A87-13638 Computational fluid dynamic studies of certain ducted dipolar (aprobc) liquids bluff-body flowfields relevant to turbojet combustors. [AD-A1692431 p 123 N87-12685 Volume 1: Time-dependentcalculations with the k-epsilon VISCOUS FLOW W turbulence model for an existing centerbody combustor Shock boundaw layer interactions in laminar transonic [AD-A1714341 p 131 N87-12816 flow over airfoils us86 a hybnd method WAKES USER MANUALS (COMPUTER PROGRAMS) D66 A87-13503 Effect of an upstream wake on a pusher propeller Assessment of damage tolerance requirements and Numerical calculation of viscous internal flows [AIAA PAPER 66-26021 p 69 A87-14035 analyses: A user's manual for crack growth and crack p 69 A87-14010 The prediction of transonic loading advancing helicopter initiation analysis: DAMGRO Direct-inverse transonic wing analysis-design method rotors [AD-A171209] p 132 N87-12939 with viscous interaction p 71 A67-14365 [ AD-A16821 71 p 100 N87-11781 UTILITY AIRCRAFT Viscous-inviscid interaction in transonic separated flow WALL FLOW Impetus of new technologies for utility. executive, and over solid and porous airfoils and cascades Effect of two endwall contours on the performance of commuter aircraft p 104 A87-14000 p 76 N87-12535 an annular node cascade p 71 A87-14119

A-25 WARNING SYSTEMS SUBJECT INDEX

WARNING SYSTEMS Theoretical studies of the ETW diffuser and of the Tip vortices of wings in subsonic and transonic flow A Now hear this ... sound warnings lo aircrews second throat p 69 A87-14022 numencal simulation p 80 A87.14620 Exploratory wind-tunnel investigation of the stability and [NASA-TM-88334] p 75 N87-11699 Obstacle-warningradar for helicopters control characteristics of advanced general aviation Numerical simulation of tip vortices of wings in subsonic P 132 N87-13149 configurations and transonic flows WATER [AlAA PAPER 86-25961 p 111 A87-14031 [ AD-A1691 161 p 77 N87-12544 Large volume water sprays for dispersing warm fogs Potential influences of heavy rain on general aviation WINGLETS p 125 A87-13848 airplane performance The effect of a winglet on the spatial vortex of a slender WATER LANDING [AIAA PAPER 86-26061 p 94 A87-14036 body at high angle of attack The amphibian technology test vehicle - Summary and Wind-tunnel investigation of the OMAC canard [AD-AI 699251 p 65 N87-12533 results p 91 A87-13992 configuration WINGS WEAPON SYSTEMS [AIAA PAPER 86-28081 p 69 A87-14038 Aerodynamic coefficients of a circular wing in steady LAMPS MK Ill - A 'New Lwk' success story --- reliability A wind-tunnel method for V/STOL testing subsonic flow p 67 A87-13653 engineering of shipthelicopter system for antisubmarine p 118 A87-15463 Development of a GFRP wing in accordance with FAR warfare p 102 A87-15415 An expenmental study of the aerodynamics of a NACA Part 23 p 92 A87-13993 Tailoring a major weapon environmental program --- for 0012 airfoil with a simulated glaze ice accretion Development and testing of critical components for the Low Altitude Navigation and Targeting Infrared System for [NASA-CR-1798971 p 75 N87-11701 technological preparation of a CFK outer wing Night p 102 A87-15430 Calculated effects of varying Reynolds Number and [ MBB-UT-224-861 p 92 A87-13997 WEATHER dynamic pressure on flexible wings a1 transonic speeds Calculated effects of varying Reynolds Number and Aircraft accidenttincident Summary reports: Erie, p 75 N87-11738 dynamic pressure on flexible wings at transonic speeds Pennsylvania, October 14. 1984; Albuquerque, New Vortex flap technology: A stability and control p 75 N87 11738 Mexico, February 11, 1985 assessment Multidisciplinary optimization applied to a transport [ PB86-9104071 p 84 N87-12549 [ NASA-CR-1724391 p 115 N87-11795 aircraft p 84 N87-11746 Aircraft accident report: Bar Harbor Airlines Flight 1808, Methods for assessing wall interference in the 2- by WIRE Beech BE-99. NSOOWP. Auburn-Lewiston Municipal 2-foot adaptive-wall wind tunnel National Transportation Safety Board safety Airport, Auburn, Maine, August 25, 1985 [ NASA-TM-882521 p 118 N87-11800 recommendation p 83 N87-11706 [PB86-9104081 p 84 N87-12550 A description of the active and passive WEATHER DATA RECORDERS sidewall-boundary-layerremoval systems of the 0.3-meter The siting, installation and operational suitability of the transonic cryogenic tunnel X Automated Weather Observina Svstem (AWOS) at [ NASA-TM-877641 p 118 N87-11801 -. XV-I5 AIRCRAFT heliports The 8 m x 6 m low speed wind tunnel at the Chinese IDOT/FAA/PM-86/301 P 133 N87-13099 V-22 Osprey - Multi-service workhorse Aerodynamic Research and Development Center p 96 A87-16400 WEATHER STATIONS . [AD-A168448] p 119 N87-11803 Revised Uniform Summary of Surface Weather The effect of a winglet on the spatial vortex of a slender Observations (RUSSWO). Parts A-F Ellington ANGB. body at high angle of attack Y Texas [AD-A1699251 p 65 N87-12533 [ AD-At 693891 p 133 N87-13105 Mach 6 experimental and theoretical stability and YAW WEIGHT INDICATORS Derformanceof a finned cvlindrical bodv.~ at anales of attack Fnctional and retarding forces on aircraft tyres Part 4 The development of OMS-scales for wyogenic wind up to 65 deg Estimation of effects of yaw tunnels p 117 A87-14007 [ NASA-TM-890501 p 76 N87-12538 [ ESDU-86016-PT-41 p 131 N87-12868 WEIGHT REDUCTION Effect of mrt corner aeometw on the internal Sizing hybrid packages for optimum reliability performanceof a rotating-vane-typeihrust reverser p 128 A87-15433 [ NASA-TP-26241 p 77 N87-12541 z The structural Optimization of a spreader bar for twin Cruise noise of counterrotation propeller at angle of lift helicopter operations p 100 N87-11759 attack in wind tunnel ZONAL HARMONICS Fabrication and testing of lightweight hydraulic system [ NASA-TM-888691 p 139 N87-I3252 Tip vortices of wings in subsonic and transonic flow A Simulator hardware WIND TUNNEL WALLS numerical simulation [AD-A169884] p 130 N87-12711 Measurements in the high subsonic region in the [ NASA-TM-88334I p 75 N87-11699 WHISKERS (CRYSTALS) TU-Berlin wind tunnel with adaptive walls Carbon fibers p 117 A87-14009 [ ADA1 713701 p 123 N87-12622 The evolution of adaptive-wall wind tunnels WICKS p 118 A87-15464 Improved electrostatic discharge wicks for aircraft Advances in adaptive wall wind tunnel technique p 127 A87-15039 p 118 A87-15465 WIND (METEOROLOGY) Methods for assessing wall interference in the 2- by Comments on gust response constrained optimization 2-foot adaptive-wall wind tunnel p 115 N87-11774 [ NASA-TM-882521 p 118 N87-11800 A review of microbursts and their analysis and detection A description of the active and passive with Doppler radar sidewall-boundary-layerremoval systems of the 0 3-meter [AD-A170458] p 133 N87-13110 transonic cryogenic tunnel WIND EFFECTS [NASA-TM-877641 p 118 N87-11801 The effect of random wind gusts on the stability of a WINDING~- parachute system p 72 A87-15216 Cryogenic wound rotor for lightweight. high voltage WIND SHEAR generators Interaction of decaying trailing vortices in ground [AD-D012370] p 130 N87-12768 shear p 66 A87-13499 WINDOWS (APERTURES) Aimlane flight through wind-shear turbulence Window acoustic study for advanced turboprop aircraft p 80 A87-14371 INASA-CR-172391 I p 138 N87-12322 WINDTUNNEL APPARATUS WING FLOW METHOD TESTS Improved measurement of the dynamic loads acting on Turbulent flow around a wingtfuselage.type juncture rotating parachutes p 70 A87.14108 [AIM PAPER 86-24731 p 68 A87-13807 WING LOADING The development of OMS-scales for cryogenic wind Load lightening and fluner damping for future Airbus tunnels p 117 A87-14007 projects Status report on the European Transonic Wind Tunnel I MBBUT-004.861 p 92 A87-14002 (EW) p 117 A87-14023 Aeroelastic divergence 01 trimmed aiicraft Start-up of a wind tunnel with a multichannel diffuser p 94 A87.14368 p 72 A87-15206 The predction of transonic loadmg advancing hellcopter WIND TUNNEL CALIBRATION rotors The development of DMS scales for cryogenic wind IAD-AI682171 p 100 N87-11781 tunnels p 117 A87-14007 Blast gust loading on a 35 degree swept-back wing WIND TUNNEL MODELS IAD-At694151 p 116 N87-12570 Design and construction of a cryogenic-wind-tunnel WING OSCILLATIONS model p 117 A87-13988 Aeroelaslic contro of oblique-wmg aircraft DFVLR cryogenic-wind-tunneland model technology p 108 A87-13341 p 117 A87-14024 Load lightening and flutter damping for future Alrbus WIND TUNNEL TESTS proIects Aerodynamic characteristics and flow round cross 1 MBB-UT-004-86I p 92 A87-14002 parachutes in steady motion Two-dimensional blade-vortex flow visualization [AlAA PAPER 86.24581 p 68 A87-13798 investigation p 70 A87-14111 Drag and stability improvements of a square WING PROFILES parachute Direct-inverse transonic wing analysis-design method [AIM PAPER 86-2471 ] p 68 A87-13805 with viscous interaction p 71 A87-14365 Measurements in the high subsonic region in the WING TIP VORTICES TU-Berlin wind tunnel with adaptive walls V~sualization01 wing tip vortices in accelerating and P 117 A87-14009 steady flow p 72 A87-I4370

A-26 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 211) March 1987

Typical Personal Author Index Listing

PERSONAL AUTHOR Experimental study of the interaction between an arc BARKER, H. A. and an electrically floating structure p 126 A87-15023 Identification and system parameter estimation 1985; ANDERSON, 8. J. Proceedings of the Seventh Symposium, University of Large volume water sprays for dispersing warm fogs York. England, July 3-7. 1985. Volumes 1 8 2 p 125 A87-13848 p 135 A87-16176 BERNER,,-Air Force W. E. technical oblective document fiscal year ANDERSON. R. v. BARTENWERFER, M. LF Experimentalcalibration of an aircraft vector electric field On sound propagation in centrifugal fan casings [ADA1673241 P 62 N87-1G779 meter system p 102 A87-15028 [ESA-lT-957] p 138 N87-12326 7- 7 Improved electrostatic discharge wicks for aircraft BASTEW, W. G., JR. p 127 A87-15039 Spanwise variation of laminar separation bubbles on ANDERSON, W. K. wings at low Reynolds number p 71 A87-14362 BEAVIN. R. C. Comparison of finite volume flux vector splinings for the Atmospheric Electricity Hazards Protection (AEHP) Euler equations p 70 A87-14109 NUMBER NUPER ACCESS~ONNUMBER ANNESER, TH. demonstration p 82 A87-15021 BEERS, K. N. Actuating system with digital signal converters and Aircraft accidents. survival. and rescue fiber-odic control D 93 A87-14018 --- ~ -- p 78 A87-13581 ANTHONY, M. J. BEK, V. V. Advanced flight control actuation systems and their Integrated active control systems: Methods of Listings in this index are arranged alphabetically by interface with digital commands algorithmic integration p 135 A87-14682 personal author The title of the document provides [SAE PAPER 8517541 p 112 A87-15479 BELIAEV, V. IA. ARAD, S. A study of the effect of surface roughness on the head the user with a brief description of the subject On the improvement of an expendable turbojet engine resistance of an aircraft p 94 A87-14717 matter The report number helps to indicate the flight envelope p 104 A87-13647 BELOUSOV, A. 1. type of document listed (eg , NASA report, ARBUCKLE, P. D. The effect of lubricant cavitation on the characteristics translation. NASA contractor report) The page and Experiences performing conceptual design optimization of a short hydrodynamic damper p 127 A87-15203 of transport aircraft p 97 N87-11723 BENNET, R. L accession numbers are located beneath and to the ARKHIPOV, A. 1. Aeroelastic-aerodynamic optimization of high speed right of the title Under any one author's name the A study of the effect of the temperature factor on helicopter-compound rotor p 99 N87-11758 accession numbers are arranged in sequence with pressure losses in the cooling system of the leading edge BENNET, W. A. the AlAA accession numbers appearing first of a deflector vane p 127 A87-15218 Development of an advanced vaneless inlet particle ARNOLD, R. T. separator for helicopter engines p 105 A87-14984 Mobile intercept of storms p 132 N87-13064 BERDNIKOV, V. V. ASHBAUGH, N. E. A simulation of the dynamics of the mechanisms of the Research on mechanical properties for engine life aircraft landing gear p 96 A87-15220 BERRIER, 8. L A prediction Effect of port corner geometry on the internal [ ADA1695701 p 108 N87-12563 ABBINK, F. J. performance of a rotating-vane-type thrust reverser ATHANS, M. Systems, avionics and instrumentation of transport [ NASA-TP-26241 p 77 N87-12541 Multi-variable control of the GE T700 engine using the category helicopters BERRY, V. L. LQGILTR design methodology p 103 A87-13418 [NLR-MP-85066-U] p 102 N87-11785 KRASH analysis correlation with full scale YAH-63 ABU EL ATA-DOSS, S. Multivariable control of a twin lift helicopter system using helicopter crash test p 90 A87-13674 the LQGILTR design methodology p 110 A87-13419 Parameter estimation of aircraft with fly-by-wire control BICKEL, W. N. systems p 113 A87-16186 ATILGAN, A. R. Fabncation and testing of lightweight hydraulic system Some ObseNations on the behavior of the Langley model ACREE, C. W. simulator hardware rotor blade NASA rotor systems research aircraft: Fixed-wing [ AD-A1698841 p 130 N87-12711 configurationflight-test results [ NASA-CR-1798801 p 74 N87-11695 BICKNELL, J. A. Corona from simulated aircraft surfaces and their [ NASA-TM-867891 p 100 N87-12557 contribution to the triggered discharge ADAMS, B. H. p A87-15024 Acquisition and use of data for crashworthiness B 82 BIGELOW, A. R. improvements in U.S. Army atrcraft p 78 A87-13686 BAEDER, J. D. Electrostatic field measurements in a foam filled C130 ADAMS, W. M., JR. Numerical simulation of tip vortices of wings in subsonic fuel tank during fuel sloshing p 95 A87-15037 Application of optimization techniques lo the design of and transonic flows BIGGERS, S. B. a fluner suppression control law for the DAST ARW-2 [ AD-AI 691 161 p 77 N87-12544 Sizing-stiened composite panels loaded in the p 115 N87-11736 BAILEY, J. C. postbuckling range p 129 N87-11733 ADAMSON, T. C., JR. Experimental calibration of an aircraft vector electric field BINDON, J. P. Comment on 'Computation of choked and supersonic meter system p 102 A87-15028 Visualisation of axial turbine tip clearance flow using a turbomachinery flows by a modified potential method' Improved electrostatic discharge wicks for aircraft linear cascade p 71 A87-14129 p 127 A87-15039 [CUED/A-TURBO/TR-122] p 107 N87-12560 AGARWAL, R. K. BAKUMSKII, A. N. BINGHAM, G. J. Recent advances in prediction methods for jet-induced Automation of support processes for aircraft production Helicopter rotor blade aerodynamic optimization by effects on V/STOL aircraft P 73 A87-15462 using computers and nurnencal control mathematical programming p 99 N87-11753 AIGNER, M. p 64 A87-14687 BLACKMORE, D. M. Performance and optimisation of an airblast noale - BALENA, F. J. MD-80 service maturity program p 64 A87-15418 Window acoustic study for advanced turboprop aircraft Drop size distribution and volumetric air flow BLANCHElTE, R. [NASA-CR-172391I p 138 N87-12322 P 125 A87-13828 Finite element contact analysis of ring gear and BALIAKIN, V. B. AIGRET, 0. 0. support p 127 A87-15193 Fabrication of cooled radial turbine rotor The effect of lubricant cavitation on the characteristics of a short hydrodynamic damper p 127 A87-15203 BLOM, H. A. P. [ NASA-CR-1795031 p 107 N87-11789 An efficient decision-making-freefilter for processes with ALAG, G. S. BANERJEE. D. Optimization process in helicopter design abrupt changes p 136 A87-16189 Aeroelastic control of oblique-wing aircraft p 98 N87-11726 BLOUNT. A. p 108 A87-13341 BANK, W. Electroluminescent (EL) remotely-controlled landing Decoupling control synthesis for an oblique-wing Visualization of wing tip vortices in accelerating and zone marker light system aircraft p 108 A87-13342 steady flow p 72 A87-14370 [AD-D012386] p87 N87-11716 ALLEN, J. E. BANTEL, T. BOASSON, M. Lightning return stroke current computation Automated infrared inspection of jet engine turbine Combination of suction and tangential blowing in p 126 A87-15029 blades p 125 A87-13719 boundary layer control p 67 A87-13641 ALLIOT, J. C. BAR-KANA, 1. BOBULA, 0. A. Analysis of the first milliseconds of aircraft lightning Extensions of a simplified continuous-time multivariable Compound cycle engine program attachment p 81 A87-15016 adaptive control algorithm p 134 A87-13399 [NASA-TM-88879] p 107 N87-11790

6-1 BOLUKBASI, A. 0. PERSONAL AUTHOR INDEX

BOLUKBASI, A. 0. C CHENG, 0. R. Cornpuler modeling of crashworthy seating systems Comparison of numerical solutions of lower order and p 90 A87-13671 CALIANNO, C. T. higher order integralequation methods for two-dimensional Drag and stability improvements of a square aerofoils BONNER, 0. A. parachute [AlAA PAPER 86-2591 ] p 69 A87-14028 Improved vane platform sealing and retention means [ AD-00124071 p 131 N87-12881 [AIM PAPER 8624711 p68 A87-13805 CHESTER, D. H. CALISE, A: J. The equivalent masses at nose landing-gears during BOOS, F. A direct method for enforcing equality constraints in landingimpacts and when taxiing over runway Redundant computer system for fly-by-wire controls optimal wtput feedback p 134 A87-13353 perturbations p 88 A87-13637 p 111 A87-14013 CAMERON, T. B. CHOPRA, 1. BOOTH, E. R., JR. Carburizing steel for high temperature service Aerodynamic force calculationsof an ellipticalcirculation Two-dimensional blade-vortex flow visualization [ AD-A1683271 p 122 N87-11877 control airfoil p 71 A87-14360 investigation p 70 A87-14111 CAMPBELL, R. F. CHRISTOPOULOS. C. BOROVSKII. E. E. State-of-the-artcrashworthy cargo restraint systems for Prediction of skin currents flowing on a Lynx helicopter Questions and problems in aerodynamics military aircraft p 89 A87-13667 due to a simulated lightning strike p 95 A87-15012 p 66 A87-13050 CAMPBELL, R. L. CHU. B. Calculated effects of varying Reynolds Number and BORTMAN, Y. Characterization and dynamical studies of polymers in dynamic pressure on flexible wings at transonic speeds dipolar (aprotic) liquids The effect of material compressibility(Poisson ratio) on p 75 N87-11738 the elasto-plasticsolution to the problem of a cylinder under [ AD-A1692431 p 123 N87-12685 CANNON, M. R. CHURKIN, V. M. internal pressure [coldworking situation) Crash dynamics program transport seat performance p 124 A87-13642 The effect of random wind gusts on the stability of a and cost benefit study parachute system p 72 A87-15216 BOWER, J. N. [ DOT/FAA/CT-85/361 p 83 N87-11708 COCKRELL, D. J. Reliability growth during flight test p 127 A87-15412 CAPITANO. J. L. Aerodynamic characteristics and flow round cross BOWMAN, D. Environmental Stress Screening (ESS) demonstrates its parachutes in steady motion Automated infrared inspection of jet engine turbine value in the field p 127 A87-15403 [AIM PAPER 86-24581 p 68 A87-13798 blades p 125 A87-13719 CAPONE, F. J. COFFEY, E. L BRAGG, M. B. Effect of port corner geometry on the internal Implementation of GEMACS for lightning interactions An experimental study of the aerodynamics of a NACA performanceof a rotating-vane-typethrust reverser analysis p 82 A87-15033 0012 airfoil with a simulated glaze ice accretion [ NASA-TP-2624 I p 77 N87-12541 COLOGNA, R. L. [NASA-CR-1798971 p 75 N87-11701 CAREY, K. M. Novel composite repair methods p 123 A87-13123 BRAISTED, P. Vortex flap technology: A stability and control COLTMAN, J. W. Combining Loran and GPS - The best of both worlds assessment Crashworthy crewseat limit load optimization through p 86 A87-13544 [NASA-CR-l72439] p 115 N87-11795 dynamic testing p 91 A87-13675 Analysis of US.civil rotorcraftaccidents for development BRISTOW, J. W. CARL, U. Design considerations for fly-by-wire control of new of improved design criteria p 78 A87-13685 Airworthiness of composite structures . Some COMTE-BELLOT, G. experiences from civil certification p 78 A87-13627 Airbus aircraft [ MBB-UT-222-861 p 110 A87-13991 Aero- and hydro-acoustics; Proceedings of the BRITTON, G. L CARLSON, L. A. Symposium, Ecole Centrale de Lyon. Ecully. France. July Electroluminescent (EL) remotely-controlled landing 3-6. 1985 p 137 A87-13585 Direct-inverse transonic wing analysis-design method zone marker light system with viscous interaction p 71 A87-14365 CONDOM, P. [AD-D012386] p 87 N87-11716 Manufacturers plan new long-range aircraft CARNELL, B. L. p 95 A87-15181 BROCKHAUS, R. Landing gear performance simulation by KRASH CONDON. T. E. Analytical redundancy through nonlinear observers program p 90 A87-13670 p 114 A87-16197 Assessing the RBM attnbutes of advanced structures The design and qualification testing of an p 96 A87-15424 BROWN. D. A. energy-absorbing seat for the Navy's H-53 AID COOK, E. L. Combined radar, ECM functions will enhance Lavi helicopters p 91 A87-13679 Wind-tunnel investigation of the OMAC canard survivability p 101 A87-13912 CARSON, R. E. configuration BROWN, K. W. Repair of composite components - A Navy approach [AlAA PAPER 88-26081 p 69 A87-14038 STAEBL: Structural tailoring of engine blades. phase 2 p 117 A87-13122 COOK, T. N. p 106 N87-11731 CARUSO. H. Assessing the RBM attributes of advanced structures BROWN. P. W. Reverse tailoring for realistic reliability tests p 96 A87-15424 Summary of NASA storm hazards lightning research. p 128 A87-15432 CORDARO. J. T. 1980-1985 p 80 A87-15003 CASASENT, D. Application of the AlPA [Approximate Iterative Joint thunderstorm operations using the NASA F-1066 Parameter estimation and in-plane distortion invariant Preprocessing Algorithm) to F-106 data and FAATC/AFWAL Convair 580 airplanes chord processing p 135 A87-13689 [AD-A169084] p 116 N87-12569 p 95 A87-15018 CASTOR, J. G. CORLEY, W. E. Evaluation of a visual system in its support of simulated BROWN, R. L. Compound cycle engine program helicopter flight A dynamic model for airframe cost estimation [NASA-TM-888791 p 107 N87-11790 [ AD-A1688291 p 102 N87-11783 [AD-A1688421 p 65 N87-11687 CAUGHLIN. 0. CRAIG, J. 1. BUCKHAM. C. A. Bank-to-turnutilizing sampled data non-linear control p 109 A87-13346 Correlation of experimental static and dynamic response Computational enhancements to a 4D algorithm of simple structural components p 124 A87-13683 p 134 A87-13359 CHAKRAVARTY. A. CRONKHITE. J. D. Aircraft flutter suppression via adaptive LQG control BUKHTOIAROV, 1.1. Design of airframe structures for crash impact Mathematical modeling of the motion of a statically p 109 A87-13344 p 90 A87-13668 deformed delta-shapedglider p 95 A87-15205 Adaptive flutter suppression p 113 A87-16182 KRASH analysis correlation with full scale YAH-63 BULAVKIN. A. A. CHAMBERS, J. R. helicopter crash test p 90 A87-13674 Determination of the thrust and net efficiency of a Summary of NASA stalllspin research for general CROSS, J. L. propeller and flow parameters behind the propeller aviation configurations NASA rotor systems research aircraft: Fixed-wing p 105 A87-15204 [AIAA PAPER 86-25971 p 111 A87-14032 configuration flight-test results BULLOCK. T. CHANDLER, P. R. [ NASA-TM-86789I p 100 N87-12557 Bank-to-turn utilizing sampled data non-linear control Renewed interest in hinge moment models for failure CROUCH, K. E. p 109 A87-13346 detection and isolation p 110 A87-13426 Minimum ignition levels of aircraft fuel constituents to BURKEN. J. J. CHANG. W.-T. lightning related ignition sources p 83 A87-15038 Aeroelastic control of oblique-wing aircraft Parameter estimation and in-plane distortion invariant CROWLEY. J. A. p 108 A87-13341 chord processing p 135 A87-13689 Length adjustable strut link with low aerodynamic drag BURKET, H. D. CHAO, C.-Y. [AD-D012279] p 77 N87-12543 Companson of electromagnetic measurements on an Variable structure control of a turbojet engine CURTIS. A. R. D. aircraft from direct lightning attachment and simulated p 103 A87-13343 The. active minimization Of harmonic enclosed sound nuclear electromagnetic pulse p 81 A87-15015 CHARKEY, A. fields p 138 A87-13593 Joint thunderstorm operations using the NASA F-1068 Aircraft battery state of charge and charge control and FAATCIAFWAL Convair 580 airplanes system D p 95 A87-15018 [AD-A169411] p 130 N87-12766 BURNS, R. A. CHATTOPADHYAY,A. DAIGUJI. H. Large volume water sprays for dispersing warm fogs Mechanism of energy absorption via buckling - An An implicit time-marching scheme lot transonic flow p 125 A87-13848 analytical study p 124 A87-13682 p 71 A87-14261 BURROWS, L. T. CHEN. C. DANEK, V. Evolution of MIL-STD-129OA.light fixed and rotary-wing The method of Calculating the desired flight path of Numerical solution of transonic potential flows with finite aircraft crashworthiness p 89 A87-13663 terrain following technique with circular arc spline elements method using multigrid technique BUSSOLETTI, J. E. p 111 A87-14136 p68 A87-13900 An exterior Poisson solver using fast direct methods CHEN, C.-W. DANILOV. A. N. and boundary integral equations with applications to Variable structure control Of a turbojet engine Questions and problems in aerodynamics nonlinear potential flow p 125 A87-13872 p 103 A87-13343 p 66 A87-13050

6-2 PERSONAL A U THOR INDEX FROMMLET, H.

DAVIDOVITCH. A. DOWELL, E. H. EVANS, R. H. A split canard configuraion for improved control at high Unsteady transonic aerodynamics and aeroelasticity Simulated lightning current tests on a Lynx helicopter angles of attack p67 A87-13643 p 73 A87-15453 p 95 A87-15011 DAVIS, 0. 0. DROUILHET. P. R. EVANS, R. J. Experimental and numerical investigation of supersonic Mode S beacom system Functional descnption Aircraft flight data compatibility checking using maximum turbulent flow through a square duct p 70 A87-14117 [ DOT/FAA/PM-86/19] p 87 N87-11715 likelihood and extended Kalman filter estimation DAVIS, M. W. DROZDOV, R. V. p 113 A87-16184 Optimization of helicopter rotor blade design for Radio-navigation meters based on the K588 senes EWALD, 8. minimum vibration p 99 N87-11756 microprocessor unit p 86 A87-15569 The development of DMS-scales for cryogenic wind DAVIS, P. DRUMMOND, J. P. tunnels p 117 A87-14007 Exploratory wind-tunnel investigationof the stability and Spectral methods for modeling supersonic chemically EWALD, J. control characteristics of advanced general aviation reacting flowfields p 70 A87-14110 Models for rotor and helicopter design configurations DUAN. p 92 A87-14008 [AIAA PAPER 86-25961 p 111 A87-14031 L Journal engineenng thermophysics (selected DAVIS, S. S. of articles) The evolution of adaptive-wall wind tunnels F p 118 A87-15464 [ AD-A1694521 p 139 N87-13347 DE HOFF, R. L DUGAS. R. M. FALLON, E. J. Application of Markov models for RMA assessment Effects of test cell recirculation on high-bypass turbofan The Annular Parachute - An approach lo a low altitude p 128 A87-15435 engines dunng simulated altitude tests personnel parachute DEAN, W. N. [AD-A171418] p 108 N87-12565 [AIM PAPER 86.24491 p 80 A87-13823 Improving Loran coverage at minimum cost DUKE, E. L FAN, S. p 86 A87-13543 Rapid prototyping facility for flight research in Mathematical model and digital simulation for speed DECKER, M. T. artificial-intelligence-based flight systems concepts control system of two-spool turbojet engine Ground-based detectionof aircraft icing conditions using [NASA-TM-88268] p 137 N87-12273 p 105 A87-14139 microwave radiometers p 80 A87-14861 DUNHAM, R. E., JR. FEATHER, J. B. DEETS, 0. A. Potential influences of heavy rain on general aviation Guidance law sirnulation studies for complex approaches Rapid prototyping facility for flight research in airplane performance using the Microwave Landing System (MLS) artificial-intelligence-basedflight systems concepts [AIM PAPER 86-26061 p 94 A87-14036 [NASA-CR-178182] p 87 N87-12552 [ NASA-TM-882681 p 137 N87-12273 DUNKLEY, V. P. FEDCHEV, A. F. DEHART, R. L Simulated lightning current tests on a Lynx helicopter Determination of dynamic stresses in the heat-insulating Aircraft accidents, survival. and rescue p 95 A87-15011 coatinqs-- of fliqht vehicles dunnq-. aerodynamic heatina p 78 A87-13581 p 72 A87-1<223 DEHOFF, R. FEIK. R. A. Fault-tolerantC31 system A(O), A(I), MTBF allocations E Aircraft flight data compatibility checking using maximum p 86 A87-15427 likelihood and extended Kalman filler estimation p 113 A87-16184 DELAAT, J. C. ECKARDT, 0. FEINSTEIN, J. H. A real-time simulation evaluation of an advanced Technicalleconomic evaluation of new propfan Environmental Stress Screening (ESS) demonstrates its detection, isolation and accommodation algorithm for concepts in comparison with the turbofan of the 1990s value in the field p 127 A87-15403 sensor failures in turbine engines p 103 A87-13318 p 104 A87-13989 DESJARDINS. S. P. FENG, Y. EDWARDS, T. A. The status of crashworthiness design criteria Modeling of the aircraft mechanical control system Numerical simulation of lip vortices of wings in subsonic p89 A87-13664 p 111 A87-14135 and transonic flows DEVRIES. S. FFOWCS WILLIAMS, J. E. L. [AD-A169116] p 77 N87-12544 Multi-Echelon Repair Level Analysis - MERIA Aero- and hydro-acoustics; Proceedings of the p64 A87-15414 EISA, S. A. Symposium. Ecole Centrale de Lyon, Ecully. France, July DICARLO. J. A. Closed loop control of an afterburning F100 gas turbine 3-6,1985 p 137 A87-13585 Polymer, metal, and ceramic matrix composites for engine p 103 A87-13323 FILATOV, P. P. advanced aircraft engine applications EISLER, 0. R. Synthesis of devices for the optimal processing of pulsed p 121 A87-15187 Optimal descending. hypersonic turn to heading radio signals in LORAN systems p 86 A87-15563 DICKSON, C. L [ DE86-0109891 p 120 N87-12577 FINAISH. F. Aviation turbine fuels, 1985 ELCHIBEKOV. V. IA. Visualization of wing tip vortices in accelerating and [ DE86-012140] p 122 N87-11908 Automation of support processes for aircraft production steady flow p 72 A87-14370 DICKSON, J. N. using computers and numerical control FINELLI, G. 8. Sizing-stiffened composite panels loaded in the p 64 A87-14687 F-106 data summary and model results relative to threat postbuckling range p 129 N87-11733 ELLIOlT. S. J. criteria and protection design analysis DIESBURG, 0. E. The active minimization of harmonic enclosed sound p81 A87-15004 Carburizing steel for high temperature service fields p 138 A87-13593 FISHER, B. 0. [ AD-A1683271 p 122 N87-11877 ENENKL, B. Summary of NASA storm hazards lightning research, DIESEL, 0. Testing a tail rotor system in fiber-reinforced construction 1980-1985 p80 A87-15003 A redundant actuating system with servo valves of low manner p 92 A87-14016 Joint thunderstorm operations using the NASA F-106B hydraulic loss p 93 A87-14025 ENNS, 0. and FAATC/AFWAL Convair 580 airplanes DIETRICHS, H.4. Multivariable flight control for an attack helicopter p95 A87-15018 Improving the energy efficiency of cooled p 109 A87-13379 FISHER, C. L high-temperature turbines p 104 A87-13990 ERICKSON, 0. E. Blast gust loading on a 35 degree swept-back wing DILLEHAY, M. E. Vortex flap technology: A stability and control [AD-A169415] p 116 N87-12570 A healer made from graphite composite material for assessment FLEMING, R. potential deicing application [NASA-CR-172439] p 115 N87-11795 Fault-tolerantC31 system A(0). A(I). MTBF allocations [ NASA-TM-888881 p 101 N87-12559 ERICKSON, R. E. p 86 A87-15427 FLEMING, R. E. DINYAVARI, M. A. H. NASA rotor systems research aircraft: Fixed-wing Application of lime-domain unsteady aerodynamics to configurationflight-test results Application of Markov models for RMA assessment rotary-wingaeroelasticity p 94 A87-14103 [NASA-TM-86789] p 100 N87-12557 p 128 A87-15435 DIlTMAR. J. H. ERIKSSON. L-E. FLORES, F. Cruise noise of counterrotation propeller at angle of Vortex-sheet capturing in numerical Solutions of the Convergence acceleration for a three-dimensional attack in wind tunnel incompressible Euler equations p 70 A87-14099 EulerINavier-Stokeszonal approach p 70 A87-14105 FOX, R. 0. [ NASA-TM-888891 p 139 N87-13252 ESCH, P. DOBYNS, A. Design and construction of a cryogenic-wind-tunnel Realistic civil helicopter crash safety The structural optimization of a spreader bar for twin model p 117 A87-13988 p78 A87-13684 lift helicopter operations p 100 N87-11759 ESCHENBACH, R. FREEMAN, 0. L. DODO, A. J. Combining Loran and GPS - The best of both worlds A review of microbursts and their analysis and detection Practical considerations in aeroelastic design p 86 A87-13544 with Doppler radar p 97 N87-11720 ESKEY, M. A. [AD-A1704581 p 133 N87-13110 DONG, 8. The handling qualities and flight characteristics of the FRENSTER, J. A. Journal of engineering thermophysics (selected GNmman design 698 simulated twin-engine tilt Nacelle Application of Markov models for RMA assessment articles) V/STOL aircraft p 128 A87-15435 FREYMUTH, P. [AD-A169452] p 139 N87-13347 [ NASA-TM-867851 p 100 N87-12558 DOROSHKO. S. M. ESLINGER, R. A. Visualization of wing tip vortices in accelerating and Using vibration spectrum characteristics forthe flow-path Renewed interest in hinge moment models for failure steady flow p 72 A87-14370 diagnostics of aircraft gas turbine engines detection and isolation p 110 A87-13426 FRIEDMANN, P. P. p 105 A87-15210 ETERNO. J. S. Application of time-domain unsteady aerodynamics to DORTMANN. K. Evaluation of detectability and distinguishability of rotary-wing aeroelasticity p 94 A87-14103 Numerical calculation of viscous internal flows aircraft control element failures using flight test data Application of modern structural Optimization to vibration p 69 A87-14010 p 110 A87-13435 reduction in rotorcraft p 115 N87-11752 DOST, K. H. ETHERINGTON, R. E. FROMMLET, H. New fuselage technologies for general-aviation aircraft General aviation cost effectiveness Development of a new type of bearingless rotor D 93 A87-14027 [AIAA PAPER 88-26071 p 139 A87-14037 system p 93 A87-14017 FU, K.-H. PERSONAL AUTHOR INDEX

FU, K.-H. GOBIN, V. HANING, R. K. Frequency domain parameter estimation of aerOnautiCal Expenmental study of the interaction between an arc Fabrication and testing of lightweight hydraulic system systems without and with time delay and an electrically floating structure p 126 A87-15023 Simulator hardware p 114 A87-16193 GOBLIRSCH, D. M. [ AD-A169864 ] p 130 N87-12711 FUJII, S. Reachable outputs in systems with bounded parameter HANSEN, L 0. Noise and performance of a counter-rotation propeller uncertainties - Application to failure detection Advanced composites applications for the 8-1B bomber p 105 A87-14366 p 134 A87-13326 - An overview p 87 A87-13101 FUJIMATSU, Y. GOEDEKE. H. S. HANSON, A. W. Possible military applications of stratospheric airship Sizing hybrid packages for optimum reliability Zoning of aircraft for lightning attachment and current discussed p 101 N87-12716 p 128 A87-15433 transfer p 94 A87-15009 GOOD, T. M. FULLER, C. R. HARDWICK, C. J. LAMPS MK 111 A 'New Look' success story Comparison of two propeller source models for aircraft - Simulated lightning current tests on a Lynx helicopter intenor noise studies p 88 A87-13596 p 102 A87-15415 p 95 A87-15011 GOODWIN, G. C. Analytical model for investigation of interior noise HARDY, J. S. P. Aircraft flight data compatibilitychecking using maximum characteristics in aircraft with multiple propellers including Simulated lightning current tests on a Lynx helicopter likelihood and extended Kalman filter estimation synchrophasing p 94 A87-14925 p 95 A87-15011 p 113 A87-16184 HARRIS, D. E. FUNG. K. Y. GORDON, T. W. Built-In-Test for fail-safe design p 128 A87-15428 Advances in the understanding and computation of FIA 18 Hornet reliability program - Status report HARTMAN, E. R. unsteady transonic flow p 73 A87-15452 p64 A87-15419 Mach 6 experimental and theoretical stability and GORNTO, C. performance of a finned cylindrical body at angles of attack TSAR (Theater Simulation of Airbase Resources) up to 65 deg G database dictionary F-4E [ NASA-TM-89050l p 76 N87-12538 [AD-A169575] p 139 N87-13352 HARTMAN, G. A. GABRIELE, G. A. GRAEWE, E. Research on mechanical properties for engine life Application of the generalized reduced gradient method The development of OMS-scales for cryogenic wind prediction to conceptual aircraft design p 97 N87-11722 tunnels p 117 A87-14007 [AD-AI 69570 I p 108 N87-12563 GANGSAAS. D. GRANT, C. E. HATE, R. L. Adaptive flutter suppression p 113 A87-16182 Fire safetyscience. Proceedingsof the First International State-of-the-art crashworthy cargo restraint systems for GANY. A. Symposium. Gaithersburg. MD. October 7 11. 1985 military aircraft p 89 A87-13667 Experimental investigation of a solid fuel ramjet p 78 A87-13186 HAlTA, K. combustor p 104 A87-13658 GRANT, P. R. Study of a bounded jet flow considering the initial Thermochemical evaluationof fuel candidates for ramjet Motion characteristics of the UTlAS flight research turbulence. II - In the case of relatively large nozzle aspect propulsion p 121 A87-13659 simulator motion-base ratio p 71 A87-14263 Combustion studies of metallized fuels for solid-fuel [UTIAS-TN-261] p 119 N87-11802 HAUPTMAN,A. ramjets p 121 A87-14982 GROMOV, 0. N. Aerodynamic coefficients of a circular wing in steady Radio-navigation meters based on the K588 series Prospective, characteristics and problems of the use subsonic flow p 67 A87-13653 microprocessor unit p 86 A87-15569 HEALY. M. J. of boron in different air augmented propulsion modes GROSS. H. N. [IAF PAPER 86-1911 p 122 A87-15924 Applying optimization software libraries to engineering Renewed interest in hinge moment models for failure problems p 136 N87-11775 GANZER, U. detection and isolation p 110 A87-13426 HEBERT, J. L. Measurements in the high subsonic region in the GROSS, U. State-of-the-art techniques for lightning TU-Berlin wind tunnel with adaptive walls Design and construction of a cryogenic-wind-tunnel susceptibility/vulnerability assessments p 117 A87-14009 model p 117 A87-13988 p 126 A87-15006 Advances in adaptive wall wind tunnel technique GRUPE, U. Current levels and distributions on an aircraft during p 118 A87-15465 Increasing the economy of design and preparation for ground lightning simulation tests and in-flight lightning GAO, Y. manufacturingby integrated and graphic data processing attachments p 82 A87-15017 Journal of engineering thermophysics (selected CADICAM - Phase 111 Implementation of GEMACS for lightning interactions articles) [ MBB-UT-225-861 p 125 A67-13986 analysis p 82 A87-15033 [ AD-A169452 ] p 139 N87-13347 Comparison of absorption and radiation boundary GARRARD, W. L. conditions in a time-domain three-dimensional A comparison of measured and calculated stress in solid H finite-difference code p 82 A87-15034 and ribbon parachute canopies HEBERT. M. HAASE. W. P. [AIAA PAPER 86.24881 p 80 A87-13815 Atmospheric Electricity Hazards Protection (AEHP) Theoretical studies of the ETW diffuser and of the GAVRISHCHUK,V. V. demonstration p 82 A87-15021 second throat p 69 A87-14022 Radio-navigation meters based on the K588 series Electrostatic field measurements in a foam filled C-130 Influence of trailing-edge meshes on skin friction in microprocessor unit p 86 A87-15569 fuel lank during fuel sloshing p 95 A87-15037 GENXING, W. Navier-Stokes calculations p 71 A87-14125 HEIDTMANN, K.-H. HAENEL, D. The effect of a winglet on the spatial vortex of a slender Design and manufacturing of a CFRP tail fin for the Numerical calculation of viscous internal flows body a1 high angle of attack A300 p 69 A87-14010 [AD-A169925] p 65 N87-12533 [ MBB-UT-006-661 p 93 A87-14026 HAERTIG, J. GEORGE, A. R. HELLER, H. Expenmental investigation of near and far acoustic field Noise of high speed surfaces p 138 A67-I3595 Results of helicopter research a1 DFVLR of a small turbojet p 138 A87-13605 GEORGE, H. L p 91 AB7-13987 Introduction to helicopter noise State-of-the-artcrashworthy cargo restraint systems for HELSDON, J. H. [ISL-NB-401/84] p 139 N67-12327 military aircraft p 89 A87-13667 Atmospheric electrical modeling in support of the NASA GEORGIADES, M. S. HAFTKA. R. T. F106 Storm Hazards Project MD-80 service maturity program p 64 A87-15418 Optimization of cascade blade mistuning under flutter [ NASA-CR-l79801] p 132 N87-12082 GESSNER, F. B. and forced response constraints p 106 N87-11732 HEMAMI. A. Experimental and numerical investigation of supersonic HAJELA, P. Multivariable high-gain control with feedforward turbulent flow through a square duct p 70 A87-14117 Comments on gust response constrained optimization compensation - A design technique p 134 A87-13365 GHOSN. L. J. p 115 N87 11774 HERSZBERG, 1. Analysis of mixed-mode crack propagation using the HALASE, J. Direct solution of flutter equations with interactive boundary integral method Automated infrared inspection of le1 engine turbine graphics procedure p 110 A87-13648 [ NASA-CR-1795181 p 131 N87-12915 blades p 125 A87-13719 HERTEL, J. GIANSANTE. N. HALL, T. F. W. Theoretical investigations of transonic rotor-blade A rotor optimization using regression analysis Automated assembly-trends, concepts and aerodynamics p 68 A87-13994 p 136 N87-11755 requirements p 63 A87-13105 HIRSCHBEIN, M. S. GIESY, D. P. HAMEL, P. STAEBL: Structural tailoring of engine blades, phase 2 Tradeoft methods in multiobjective insensitive design ATTAS The new test bed p92 A87 14003 p 106 N87-11731 of airplane control systems p 115 N87-11730 - HAMMER, A. N. HO, W.C. GIKADI. T. Fabrication of cooled radial turbine rotor Numerical calculation of three-dimensional inviscid On sound propagation in centrilugal fan casings supersonic flows p 66 A87-13504 1 NASA-CR 179503 I p 107 N87-11789 [ ESA-TT-9571 p 138 N87-12326 HOADLEY, A. W. GILES, 0. L HANAGUD, S. Wholefield displacement measurements using speckle Stall margin indication Multidisciplinary optimization applied to a transport [AIAA PAPER 86-25951 p 101 A67-14030 image Processing techniques for crash tests aircraft p 84 N87-11746 HOBBS, R. A. p 124 A87-13680 GILYARD. 0. B. Simulated lightning current tests on a Lynx helicopter Aeroelastic control of oblique-wing aircraft HANAGUD. S. V. p 95 A87-15011 p 108 A87-13341 National Specialist s Meeting on Crashworthy Design HODGE, R. W. GIOVANElTI. A. J. Of Rotorcraft. Georgia Institute of Technology, Atlanta. April NASA rotor systems research aircraft: Fixed-wing 7-9. 1986, Proceedings Long-term deposit formation in aviation turbine fuel at p 89 A87 13662 configuration flight-test results elevated temperalure p 121 A87-14986 Mechanism Of energy absorption via buckling An [NASA-TM-867891 p 100 N87-12557 GMELIN, 8. analytical study p 124 A87-13682 HOGAN, J. V. Results of helicopter research at DFVLR Correlation of experimentalstatic and dynamic response Low cost aerial testing of parachutes p 91 A87-13987 of simple StNctural components p 124 A87-13683 [AIAA PAPER 86-24721 p 79 A87-13806 PERSONAL AUTHOR INDEX KROJER, H.

HOLOHAN, E. J. JOHNSON, C. KHOLIABIN, 1.1. Application of regression analysis to coupled responses In-flight transfer alignment/calibration of a strapdown Determination of the regime coefficients in the local at high angles of attack p 113 A87-16185 INS that employs carouseled instruments and IMU theory of interaction from plate data p 74 A87-15561 HOLT, D. indexing p 85 A87-13438 KIKUCHI. N. Mechanized manufacture of composite main rotor blade JOHNSON, C. E. On optimal design for the blade-rootlhub interface in spars p 124 A87-13625 A description of the active and passive jet engines p 106 N87-11769 HOOLE, P. R. P. sidewall-boundary-layerremoval systems of the 0.3-meter KIMURA, J. Lightning return stroke current Computation transonic cryogenic tunnel Possible military applications of stratospheric airship p 126 A87-15029 [NASA-TM-87764J p 118 N87-11801 discussed p 101 N87-12716 HOPKINS, H. JOHNSON, D. A. KING, P. M. Now hear this p 80 A87-14620 Laser velocimetry for transonic aerodynamics Exploratory wind-tunnel investigation of the stability and HORAK, D. T. p 74 A87-15467 control characteristics of advanced general aviation Reachable outputs in systems with bounded parameter JOHNSON, D. W. configurations [AIAA PAPER 86-25961 p 111 A87-14031 uncertainties - Application to failure detection Status report of a new recovery parachute system for p 134 A87-13326 the F11I aircraft crew exape module KINNEAR, 1. For small airliners and executive jets HORSTMAN, C. C. [AIAA PAPER 86-24371 p 91 A87-13821 Computation of sharp-fin-inducedshock wave/turbulent p 105 A87-15179 JOHNSON. E. boundary-layer interactions p 70 A87-14104 H. KIWAK, R. S. The automated strength-aeroelastic design of HOTOP, H. J. Composite curing with semi-permeable membranes aerospace structures program p 98 N87-11749 Investigation of magnetometer errors and their p 120 A87-13121 compensation in the 80-105 helicopter JOHNSON, F. T. KLOEPPEL, V. [DFVLR-FB-86-21] p 102 N87-11784 An exterior Poisson solver using fast direct methods Testing a tail rotor system in fiber-reinforcedconstruction HOYT, D. and boundary integral equations with applications to manner p 92 A67-14016 Criteria for asphalt-rubber concrete in civil airport nonlinear potential flow p 125 A87-13872 KNACKE, T. W. pavements: Mixture design JOHNSTON, P. J. Technical-historical development of parachutes and [ DOT/FAA/PM-86/39] p 129 N87-11910 Mach 6 experimental and theoretical stability and their applications since World War I HSIEH, S.-J. performance of a finned cylindncal body at angles of attack [AIM PAPER 86-24231 p 79 A87-13777 An aerodynamic analysis and the subsequent motion up to 65 deg KNIGHT, J. C. of external store p66 A87-13501 [ NASA-TM-890501 p 76 N87-12538 The implementation and use of Ada on distributed HSU, J. Y. JONES, C. C. R. systems with high reliability requirements Evaluation of detectability and distinguishability of Zoning of aircraft for lightning attachment and current [NASA-CR-1798421 p 137 N87-12265 aircraft control element failures using flight test data transfer p 94 A87-15009 KOLANDER, W. p 110 A87-13435 JORDAN, J. L. Load lightening and flutter damping for future Airbus HUBBARlT, J. E. Flight test report of the NASA icing research airplane: projects Turbulent flow around a winglfuselage-type juncture Performance, stability, and control after flight through [ MBB-UT-004-861 p92 A87-14002 p 70 A87-14108 natural icing conditions KOLAX, M. HUDAK, 0. J. [NASA-CR-179515] p 116 N67-11797 Structure-component tests for a CFK fuselage Navstar Global Positioning Systems Collins user JOSSELYN, J. [MBB-UT-223-86] p 121 A87-14001 equipment - An evolutionary assessment Fault-tolerant C31 system A(O), A(I). MTBF allocations KONDO, H. p 85 A67-13533 p 86 A87-15427 An approximate method of estimating the aerodynamic interference between two parallel bodies in a supersonic HULL, D. G. JOSSELYN, J. V. flow (axial force) Optimal descending, hypersonic turn to heading Application of Markov models for RMA assessment [BR-1002711 p 76 N87-12540 [ DE86-0109891 p 120 N87-12577 p 128 A87-15435 KONICKE, M. L HUNG, C. C. JOST. R. A heater made from graphite composite material for A comparison of measured and calculated stress in solid Comparison of absorption and radiation boundary and ribbon parachute canopies potential deicing application conditions in a time-domain three-dimensional [ NASA-TM-888881 p 101 N87-12559 [AIAA PAPER 86-24881 p 60 A87-13815 finite-difference code p 82 A87-15034 KONKIN, A. A. HUSSAINI, M. Y. JOU, W.-H. Carbon fibers Spectral methods for modeling supersonic chemically Propeller design by optimization p 105 A87-14123 [ AD-A171 3701 p 123 N87-12622 reacting flowfields p 70 A87-14110 KONNOVA, N. F. HUTZLER, 8. Carbon fibers Experimental study of the interaction between an arc K [ AD-A171 3701 p 123 N87-12622 and an electrically floating structure p 126 A87-15023 KOSHEVOI, V. N. KAPITANCHUK. K. I. Questions and problems in aerodynamics A study of local heat transfer on the face surface of a p 66 A87-13050 I nozzle ring model p 127 A87-15215 KOTANSKY, D. R. KATO. T. Multiple jet impingement flowfields p 73 A67-15461 IAKUPOVA, 1. P. Possible military applications of stratospheric airship KOU, H. S. A Simulation of the dynamics of the mechanisms of the discussed p 101 N87-12716 Turbulent buoyant flow and pressure variations around aircraft landing gear p 96 A87-15220 KATZ, A. an aircraft fuselage in a cross wind near the ground IDELSON, A. M. A split canard configuraion for improved control at high p 78 A87-13187 The effect of turbine elements on the gasdynamic angles of attack p67 A67-13643 KOVALENKO, A. S. stability margin p 105 A67-15208 KAZA, K. R. V. A study of local heat transfer on the face surface of a ILLARIONOV, A. M. Concentrated mass effects on the flutter of a composite nozzle ring model p 127 A87-15215 A study of the effect of surface roughness on the head advanced turboprop model KOVATCH, D. H. resistance of an aircraft p 94 A87-14717 [ NASA-TM-668541 p 130 N87-12017 Demonstration of combat damage repair estimator INGRAM, W. C. KELLER, V. W. p65 A87-15436 Wind-tunnel investigation of the OMAC canard Large volume water sprays for dispersing warm fogs KRAEMER, E. configuration p 125 A67-13846 Theoretical investigations of transonic rotor-blade [AIM PAPER 86-26081 p 69 A67-14038 KEMP, R. S. aerodynamics p68 A87-13994 IVANOV, E. S. Eigenstructure assignment by dynamic output KRASNOV, N. F. Start-up of a wnd tunnel with a multichannel diffuser feedback p 134 A87-13385 Questions and problems in aerodynamics p 72 A87-15206 KEMPEL, R. W. p66 A87-13050 KRIECHBAUM, G. IZUMI, K. H. Decoupling control synthesis for an oblique-wing aircraft p 108 A87-13342 The amphibian technology test vehicle - Summary and Sensitivity studies of 4D descent strategies in an results p 91 A87-13992 advanced metering environment p 88 A87-13361 KENUE, S. Automated infrared inspection of jet engine turbine KRILE, D. J. blades p 125 A67-13719 Electroluminescent (EL) remotely-controlled landing J KERLICK, G. D. zone marker light system Experimental and numerical investigation of supersonic [AD-DO123861 p87 N87-11716 turbulent flow through a square duct p 70 A87-14117 KRISHER, R. JAMESON, A. Automated infrared inspection of jet engine turbine Numerical solution of the Euler equation for KERXHEN, E. J. Influence of airfoil mean loading on convected gust blades p 125 A87-13719 compressible inviscid fluids p 69 A87-14095 interaction noise p 137 A67-13587 KRISHNAMURTHY, L JATEGAONKAR, R. V. KHALATOV, A. A. Computational fluid dynamic studies of certain ducted Parametric identification of discontinuous A study of local heat transfer on the face surface of a bluff-body flowfields relevant to turbojet combustors. nonlinearities p 135 A87-16179 nozzle ring model p 127 A87-15215 Volume 1: Time-dependent calculations with the k-epsilon Maximum likelihood estimation of parameters in KHASBIULLIN, M. M. turbulence model for an existing centerbody combustor nonlinear flight mechanics systems p 113 A87-16192 A study of the effect of the temperature factor on [AD-AI 714341 p 131 N87-12816 JIBILIAN, H. pressure losses in the cooling system of the leading edge KRIVORUCHKO. IU. T. Electrostatic field measurements in a foam fllled C-130 of a deflector vane p 127 A87-15218 Radio-navigation meters based on the K586 series fuel tank during fuel sloshing p 95 A87-15037 KHOBAIB, M. microprocessor unit p 86 A87-15569 JOHE, C. Research on mechanical properties for engine life KROJER, H. Experimental investigationof near and far acoustic field prediction Impetus of new technologies for utility, executive, and of a small turbojet p 138 A87-13605 [AD-A1695701 p 108 N87-12563 commuter aircraft p 104 A87-14000

B-5 KROTHAPALLI. A. PERSONAL AUTHOR INDEX

KROTHAPALLI, A. LEVIN, 0. LOZANO-LEAL, R. Recent advances in aerodynamics p 73 A87-15451 A split canard confguraion for improved control at high Aircraft flight data compabbility checking using maximum KRUEGER. H. angles of anack p67 A87-13643 likelihood and extended Kalman filter estimation

AlTAS ~ The new test bed p92 A87-14003 Improved measurement of the dynamic loads acting on p 113 A87-16184 KUBENDRAN. L R. rotating parachutes LUCAS, H. Turbulent flow around a wing/fuselage-typejuncture [AIAA PAPER 86-24731 p 68 A87-13807 Development of a GFRP wing in accordance with FAR p 70 A87-14108 LEVIN, G. Part 23 p 92 A87-13993 On the improvement of an expendable turbojet engine KUDRIASHEV, L 1. LUDTKE, W. P. Determinationof dynamic stresses in the heat-insulating flight envelope p 104 A87-13647 Notes on a genenc parachute opening force analysis LEVllT, K. N. coatings of flight vehicles dunng aerodynamic heating [AIAA PAPER 86-24401 p 67 A87-13788 Beyond FTMP and SIFT ~ Advanced fault-tolerant p 72 A87-15223 LUO, 2.-Y. computers as successors to FTMP and SIFT KUFELD, R. M. State estimation of flying vehicle p 114 A87-16209 p 133 A87-13200 NASA rotor systems research aircraft Fixed-wing LYLE, B. S. configuration flight-test results LEVY, A. On the improvement of an expendable turbojet engine Reducing complexity in fly-by-wire flight control [ NASA-TM-867891 p 100 N87-12557 actuators KUHN, R. E. flight envelope p 104 A87-13647 LEVY, M. [SAE PAPER 8517521 p 112 A87-15477 The induced aerodynamics of jet and fan powered LYNE. G. W. V/STOL aircraft p 73 A87-15459 Assessment of damage tolerance requirements and analyses: A user's manual for crack growth and crack RADC automated RAM package [RAMP) KUO. A. p 128 A87-15417 Assessment of damage tolerance requirements and initiation analysis: DAMGRO LYlTON, R. L analyses A user's manual for crack growth and crack [ ADA1 71 2091 p 132 N87-12939 Cntena for asphalt-rubber concrete in civil airport initiation analysis DAMGRO LEVY, Y. pavements Mixture design [ ADA1 712091 p 132 N87-12939 Experimental investigation of a solid fuel ramjet [DOT/FAA/PM-86/39] p 129 N87-11910 KUO. S. C. combustor p 104 A87-13658 Development of high-alumina ceramic materials suitable LEWIS, F. L for making let engine fixtures p 120 A87-13092 Eigenstructure assignment by dynamic output KULMIN. A. 0. feedback p 134 A87-13385 M Some asymptotic types of transonic vortex flows LEYMAN, C. S. p 74 A87-15553 A review of the technical development of Concorde MACE, J. KULUHARA. M. p96 A87-16408 Comment on 'Computation of choked and supersonic An implicit time-marching scheme for transonic flow LI, K. turbomachinery flows by a modified potential method' p 71 A87-14261 Journal of engineering thermophysics (selected p 71 A87-14129 articles) MADER, J. M. [ AD-A1694521 p 139 N87-13347 VLSl impact on RAMS strategies in avionics design L LI. L p 128 A87-15423 Optimal discrete design of digital flight control system MAHAN, J. R. LABAUNE, G. p 111 A87-14142 comparison of two propeller source models for aircraft Experimental study of the interaction between an arc LIANG, 0. interior noise studies p 88 A87-13596 Turbine air seal with full backside cooling and an electrically floating structure p 126 A87-15023 MAHAPATRA, P. R. [ AD-W12405) p 108 N87-12564 LALA. G. 0. Weather safety aspects in future civil air navigation LIBOVE, C. Large volume water sprays for dispersing warm fogs p 85 A87-13540 p 125 A87-13848 Coordinated turn relations .A graphical representation LAMBE. P. C. p 111 A87-14367 MAJOR, J. H. The development of dynamic performance standards Advanced construction procedures: Confined bases for LIESE, K. for civil rotorcraft seats p 89 A87-13666 airport pavements Models for rotor and helicopter design [ FAA/PM-86/9] p 118 N87-11799 p92 A87-14008 MAKHLIN, A. R. LAMBORN. L C. LIMANSKII, A. S. Integrated active control systems: Methods of Crew seat stroke requirements for helicopter rolled A study of the effect of the temperature factor on algorithmic integration p 135 A87-14682 anitude impact crashworthiness p 90 A87-13669 pressure losses in the cooling system of the leading edge MALLIK, A. LAN, C. E. of a deflector vane p 127 A87-15218 Prediction of skin currents flowing on a Lynx helicopter Applicationsof CONMIN to wing designoptimizationwith LINTERN. 0. due to a simulated lightning stnke p 95 A87-15012 vortex flow effect p 98 N87-11737 Simulator design features for helicopter landing on small MANDL, P. LANE, S. H. ships. 1: A performance study The use of mathematical models in aerodynamics (The Flight control design using nonlinear inverse dynamics [ADA1695141 p 119 N87-12572 W. Rupert Turnbull Lecture) p 72 A87-15189 p 109 A87-13352 Simulator design and instructional features for carrier MANG, H. LARSON, E. S. landing: A field transfer study Actuating system with digital signal converters and Lower-side normal force characteristics of delta wings [ AD-A1 699621 p 119 N87-12573 fiber-optic control p 93 A87-14018 at supersonic speeds p 72 A87-14372 LINTON. D. J. MANN, M. J. LAWACZECK, 0. Energy efficient actuation using variable displacement Forward-swept wing configuration designed for high DFVLR cryogenic-wind-tunneland model technology hydraulic control maneuverability by use of a transonic computational p 117 A87-14024 [SAE PAPER 8517571 p 112 A87-15481 method LEARMOUNT, 0. LIOU. M.-S. [ NASA-TP-26281 p 75 N87-11702 US air transport technology - Where next? Computation of two-dimensional supersonic turbulent MANOR, D. flow over a compression corner p 66 A87-13502 p 65 A87-16398 Experimental investigation of vortex flow over Numerical calculation of three-dimensional inviscid LEE, C.4. double-delta wing at high alpha p 67 A87-13652 An aerodynamic analysis and the subsequent motion supersonic flows p 66 A87-13504 MANRO. M. E. of external store p66 A87-13501 LIU. C. H. LEE, 0. Interaction of decaying trailing vortices in ground PIAS A program for an iterative aeroelastic solution p 97 N87-11725 Application of viscous-inviscid interaction methods to shear p 66 A87-13499 transonic turbulent flows LIU, 0. MARCHAND, M. [NASA-CR-179900] p 75 N87-11700 Theoretical and experimental investigations of sensor Frequency domain parameter estimation of aeronautical LEE, 0. J. location for optimal aeroelastic system state estimation systems without and with time delay An analysis of blade vortex interaction aerodynamics p 115 N87-11794 p 114 A87-16193 and acoustics p 77 N87-12547 LIU. J. T. C. MARSHALL, R. 0. LEFEBVRE, A. H. Large-scale coherent structures in free turbulent flows Eigenstructure assignment by dynamic output Prediction of velocity coefficient and spray cone angle and their aerodynamic sound p 138 A87-15458 feedback p 134 A87-13385 for simplex swirl atomizers p 125 A87-13830 LLOYD, J. R. MARTIN, C. LEICHER. S. Turbulent buoyant flow and pressure variations around Aircraft flight data compatibilitychecking using maximum Theoretical studies of the ETW diffuser and of the an aircraft fuselage in a cross wind near the ground likelihood and extended Kalman filter estimation second throat p 69 A87-14022 p 78 A87-13187 p 113 A87-16184 LEISS. u. LOGAN, A. H. MARTIN, D. Improvement of mathematical models of helicopters by Optimization process in helicopter design Performance evaluation of an inverse integral equation analytical presentation of nonlinear aerodynamics p 98 N87-11726 method applied to turbomachine cascades p 69 A87-13995 LOH, C. J. p 72 A87-14771 LEMMERMAN. L A. A prototype maintenance expert system for the CH-47 MARVIN, J. 0. Optimization in the systems engineering process flight control hydraulic system Modeling of turbulent separated flows for aerodynamic p 96 N87-11719 [ AD-AI6901 91 p 116 N87-12568 applications p 73 A87-15454 LENT, ti. M. LOH, R. MATOS. R. A. Vortex shedding of a square cylinder in front of a slender Development of a maintenance automation system The siting. installation and operational suitability of the airfoil at high Reynolds numbers. Part 2: Compressibility p 128 A87-15425 Automated Weather Observing System (AWOS) at effect LOSSEE. D. heliports [ MPIS-24/ 1985] p 75 N87-11704 Advanced Composites applications for the 8-1B bomber [ DOT/FAA/PM-86/30] p 133 N87-13099 LEONARD, J. 8. - An overview p 87 A87-13101 MAlTOS. F. A system look at actuation concepts and alternatives LOTH, J. L. Advanced flight control actuation Systems and their for primary flight control Combination of Suction and tangential blowing in interface with digital commands [SAE PAPER 8517531 p 112 A87-15478 boundary layer control p67 A87-13641 [SAE PAPER 8517541 p 112 A87-15479 PERSONAL AUTHOR INDEX NORDSTROM, M.

MAT& C. MESSITER. A. F. MUO, S. Clarification of adhesive binding mechanisms of Comment on 'Computation of choked and supersonic Modeling of the aircraft mechanical control system aluminum structural bonds in aircraft fabrication turbomachinery flows by a modified potential method' p 111 A87-14135 [ MBB-UT-226-861 p 121 A87-13985 p 71 A87-14129 MURTHY, A. V. MAUK, R. MEYER, G. A description of the active and passive Simulator design and instructional features lor carrier Aircraft automatic-flight-controlsystem with inversion of sidewall-boundary-layer removal systems of the 0.3-meter landing: A field transfer study the model in the feed-forward path using a transonic cryogenic tunnel [AD-A169962] p 119 N87-12573 Newton-Raphson technique for the inversion [NASA-TM-87764] p 118 N87-11801 MAURER, F. [ NASA-TM-882091 p 116 N87-11796 MURTHY, D. V. Status report on the European Transonic Wind Tunnel MEYER, J. Optimization of cascade blade mistuning under flutter (ETW) p 117 A87-14023 Average landing force dependence on length and and forced response constraints p 106 N87-11732 MAURICE, L 0. direction 01 landing, parachute velocity components and MYERS, M. R. FlOO fuel sampling analysis: Foreign samples wind speed Influence of airfoil mean loading on convected gust [AD-A168573] p 122 N87-11904 [AIM PAPER 86-24521 p 79 A87-13794 interaction noise p 137 A87-13587 MAY, D. N. MEYER, M. B. Lightweight sidewalls for aircraft interior noise COntrOl Large volume water sprays for dispersing warm fogs N [NASA-CR-172490] p 138 N87-12323 p 125 A87-13848 MAYER, D. MEYER, S. NAGEL, J. Ground aircraft deicing technology review A. National Specialist's Meeting on Crashworthy Design CAD as a prerequisite for computer-integrated [WT/FAA/CT-85/21] p 83 N87-11707 of Rotorcralt, Georgia Instituteof Technology. Atlanta. April manufacturing p 135 A87-14019 MAZUR. V. 7-9. 1986. Proceedings p89 A87-13662 NAGER, J. Effect of E-fieldmill locationon accuracy of electric field MICHITSCH, J. Development of a maintenance automation system measurements with instrumented airplane p 128 A87-15425 p 95 A87-15027 Ground aircraft deicing technology review NAIDU, D. S. MCCOY, H. H. [DOT/FAA/CT-85/21I p 83 N87-11707 Time scale analysis of a digital flight control system Axisymmetric vortex lattice method applied to parachute MIKHAELIAN, 0. M. p 109 A87-13347 shapes Automation of support processes for aircraft production [AIAA PAPER 8624561 p63 A87-13796 using computers and numerical control NAKAGAWA, T. Vortex shedding of a square cylinder in front of a slender MCCROSKEY, W. J. p 64 A87-14637 airfoil at high Reynolds numbers. Part 2: Compressibility Special opportunities in helicopter aerodynamics MILLER, D. S. p 74 A87-15469 Impact of airfoil profile on the supersonic aerodynamics effect [ MPIS-24/1985] p 75 N87-11704 Tip vortices of wings in subsonic and transonic flow: A of delta wings p 71 A87-14363 NAKASHIMA, M. numerical simulation MILLER, R. H. Study 01 a bounded jet flow considering the initial [NASA-TM-88334] p 75 N87-11699 The aerodynamics and dynamics of rotors - Problems turbulence. II - In the case of relatively large noale aspect Numerical simulation01 tip vortices of wings in subsonic ana parspeclives p 74 A87-15468 ratio p71 A87-14263 and transonic flows MILOH, T. [ADA1691 161 p 77 N87-12544 Aerodynamic coefficients of a circular wing in steady NASH. D. 0. MCCULLERS. L A. subsonic flow p 67 A87-13653 Length adjustable strut link with low aerodynamic drag [ AD-DO1 22791 p77 N87-12543 Aircraft configuration optimization including optimized MIRONOV, A. 0. flight profiles p 98 N87-11743 Usingvibration spectrum characteristicslor the flow-path NASTASE, A. MCDANELS. D. L diagnostics of aircraft gas turbine engines Computation of optimum-optimorum wing-fuselage Polymer, metal, and ceramic matrix composites for p 105 A87-15210 configuration for future generation of supersonic aircraft advanced aircraft engine applications MIURA, H. p 74 A87-15761 0 121 A87-15187 Overview: Applications of numerical optimization NATORI, M. MCGOUGH, J. methods to helicopter design problems Application of a mixed variational approach to Selection of media access protocolfor distributed digital p 99 N67-11751 aeroelastic stability analysis of a nonuniform blade avionics p 134 A67-13436 MOU, R. J. p 126 A87-14423 MCMAHON, H. M. Implementationof a robotic assembly cell NAWA, N. Turbulent flow around a wing/fuselage-type juncture p 63 A87-13062 Investigation of magnetometer errors and their p 70 A87-14108 MOORE. J. 8. compensation in the 80-105 helicopter Aircraft flutter suppression via adaptive LOG control [DFVLR-FB-8621] p 102 N87-11784 MCMEEKIN, R. R. p 109 A87-13344 Aircraft accident investigation p 78 A87-13578 NEEL, S. Adaptive flutter suppression p 113 A87-16182 Impact of aviation on the environment MEDVEDEV, 8. A. MOORTHY, C. S. p132 A87-13584 Automation of support processes for aircraft production Constant-density approximation lo Taylor-Maccoll NELSON. P. A. using computers and numerical control solution p 71 A87-14127 p64 A87-14687 The active minimization of harmonic enclosed sound MOREAU, J. P. fields p 138 A87-13593 MEIER, 0. E. A. Analysis of the first milliseconds of aircraft lightning NEMAT-NASSER, S. Vortex shedding of a square cylinder in front of a slender attachment p 81 A87-15016 Application of a mixed variational approach to airfoil at high Reynolds numbers. Part 2: Compressibility Experimental study of the interaction between an arc effect aeroelastic stability analysis of a nonuniform blade and an electrically floating structure p 126 A87-15023 p 126 A87-14423 [MPIS24/1985] p 75 N87-11704 MORGAN, R. 0. MEIER. R. J., JR. Further shock tunnel studies of scramjet phenomena NERI, L M. GNndy - Parallel processor architecture makes [NASA-CR-179937] p77 N87-12542 Analysis of US.civil rotorcraftaccidents for development of improved design criteria p78 A87-13685 programming easy p 135 A87-13703 MOROZOV, V. I. MELLIARSMITH, P. M. Mathematical modeling of the motion of a statically NERER, D. W. Beyond FTMP and SIFT - Advanced fault-tolerant deformed delta-shapd glider p 95 A87-15205 Thermochemical evaluation of fuel candidatesfor ramjet propulsion p 121 A87-13659 computers as successors to FTMP and SIFT MORRIS, N. A. p133 A87-13200 Furlher shock tunnel studies 01 scramjet phenomena Combustion studies of metallized fuels for solid-fuel MELSON, N. D. [NASA-CR-179937] p 77 N87-12542 ramjets p 121 A87-14982 Vectorizable multigrid algorithms for transonic-flow MOUSTAPHA, S. H. NEWMAN, L calculations p 72 A87-14652 Effect of two endwall contours on the performance of MTFCS (multiple target formation flight control system) MENDELSON, A. an annular noale cascade p 71 A87-14119 Formation position sensor trade-off analysis Analysis of mixed-mode crack propagation using the MOXON, J. p 110 A87-13536 boundary integral method Aerospace plane - Fact or fantasfl NGUYEN, D. p65 A87-16396 [ NASA-CR-1795181 p 131 N87-12915 NASA rotor systems research aircraft: Fixed-wing MENSHIKH, N. L V-22 Osprey - Multi-service workhorse configuration flight-test results p96 A87-16400 Determinationof dynamic Stresses in the heat-insulating [NASA-TM-86789] p 100 N87-12557 coatings of flight vehicles during aerodynamic heating MUCHMORE, C. 8. NIBLETT, L T. Exploratorywind-tunnel investigation of the stability and p 72 A87-15223 Aeroelastic divergence of trimmed aircraft control characteristics 01 advanced general aviation p94 A87-14368 MERCER, C. E. configurations NIEH, T. G. Forward-swept wing configuration designed for high [AIAA PAPER 86-25961 p 111 A87-14031 maneuverability by use of a transonic computational Diffusion bonding of certain refractory metals MUELLER, H. p 121 A87-13171 method A redundant actuating system with servo valves of low [NASA-TP-2628] p 75 N87-11702 hydraulic loss p 93 A87-14025 NIKOLENKO, V. IU. MEREAU, P. Start-up of a wind tunnel with a multichannel diffuser MUELLER, T. J. p 72 A87-15206 Parameter estimation of aircraft wth fly-by-wire control Spanwise variation of laminar separation bubbles on systems p 113 A87-16186 wings at low Reynolds number p 71 A87-14362 NISHIWAKI, H. MERRIFIELD. J. T. MULDER, J. A. Noise and performance of a counter-rotation propeller Ames accelerates research on hypersonic technology Aircraft control input optimization for aerodynamic p 105 A87-14366 D64 A87-13911 denvalive estimation in dynamic manoeuvres NORDSTROM. M. MERRILL, W. C. p 113 A87-16183 Aircraft automatic-flight-controlsystem with inversion of A real-time simulation evaluation of an advanced MUNJAL, A. K. the model in the feed-forward path using a detection. isolation and accommodation algorithm lor Use of filament winding in manufacturing high quality Newton-Raphsontechnique for the inversion sensor failures in turbine engines p 103 A87-13318 aerospace composite components p 123 A87-13164 [ NASA-TM-882091 p 116 N87-11796 8-7 NORUM, 1. D. PERSONAL AUTHOR INDEX

NORUM, T. D. PELLETIER, D. H. PRAVOTOROV, A. E. Dynamic loads on twin jet exhaust nozzles due to shock Finite element Navier-Stokes calculation of The effect of random wind gusts on the stability of a noise p 94 A87-14369 three-dimensional turbulent flow near a propeller Parachute system p 72 A87-15216 NOTON, 8. R. p 70 A87-14101 PRICE, D. B. Cost drivers and design methodology for automated PERALA, R. A. Time scale analysis of a digital flight control system airframe assembly p63 A87-13157 F-106data summary and model results relative to threat p 109 A87-13347 NOUKI, T. criteria and protection design analysis PRYDS R. A. Study 01 a bounded jet flow considering the initial p 81 A87-15004 Window acoustic study lor advanced turboprop aircraft turbulence. II - In the case of relatively large nozzle aspect PERLEY, R. [NASA-CR-172391] p 138 N87-12322 Regression analysis as a design optimization tool ratio p 71 A87-14263 PRZYBYTKOWSKI,S. p 136 N87-11754 M. PETERSEN, R. Advances in the understanding and computation of unsteady transonic flow p 73 A87-15452 0 Antimisting kerosene: Evaluation of low temperature performance PSICHOGIOS, T. P. [DOT/FAA/CT-85/31] p 122 N87-11902 Fabncation of cooled radial turbine rotor OBERFRANZ, R. [NASA-CR-179503] p 107 N87-11789 Technologies for a mechanized carbon fiber PETERSON, R. construction element for commercial aircraft production Implementation of a robotic assembly cell [ MBB-UT-005-861 p 126 A87-13999 p63 A87-13062 Q OBERLY. C. E. PFEIL, W. H. Multi-variable control of the GE T700 engine using the Cryogenic wound rotor for lightweight. high voltage QUANDT, 0. generators LQGILTR design methodology p 103 A87-13418 PICHKOV, K. N. ESSY - An electromechanical adjustment system for [AD-DO12370] p 130 N87-12768 aircraft control surfaces p 92 A87-14014 OBRIEN. W. L Start-up 01 a wind tunnel with a multichannel diffuser Advanced composites applications for the B-1B bomber p 72 A87-15206 - An overview p 87 A87-13101 PIEPKA, E. R OCH. 0. M. ESSY - An electromechanical adjustment system for Obstacle-warningradar lor helicopters aircraft control surfaces p 92 A87-14014 RADOVCICH, N. A. p 132 N87-13149 PIEROWAY. C. S. Some experiences in aircraft aeroelastic design using ODAM. 0. A. M. Electroluminescent (EL) remotely-controlled landing Preliminary Aeroelastic Design of Structures (PAD) Zoning of aircraft lor lightning anachment and current zone marker light system p 98 N87-11747 transfer p 94 A87-15009 [ AD-DO123861 p87 N87-11716 OGG, J. PIFKO, A. B. RAJENDRAN, A. M. Gust and maneuver spectra for general aviation Modelling strategies lor finlte element crash simulation Research on mechanical properties for engine life aircraft of complete vehicles p 90 A87-13673 prediction [AIAA PAPER 86-25991 p 93 A87-14033 PIlTS, F. L. [AD-A169570] p 108 N87-12563 OLLING, C. R. F-106 data summary and model results relative lo threat RAJU, M. S. Viscous-inviscidinteraction in transonic separated flow cntena and protection design analysis Computational fluid dynamic studies of certain ducted over solid and porous airfoils and cascades p81 A87-15004 bluff-body flowfields relevant to turbojet combustors. p 76 N87-12535 PLAETSCHKE. E. Volume 1: Time-dependentcalculations with the k-epsilon OLSEN, N. C. Maximum likelihood estimation of parameters in turbulence model for an existing centerbody combustor Advanced manufacturing technology for structural nonlinear flight mechanics systems p 113 A87-18192 [ AD-A171 4341 p 131 N87-12816 aircraft/aerospace components p 123 A87-13074 PLATZ. S. J. RAM, R. B. ONISHI, M. Flight test report of the NASA icing research airplane Shock boundary layer interactions in laminar transonic Full scale crash test of a BK117 helicopter Performance, stability, and control after flight through flow over airfoils using a hybrid method p 91 A87-13678 natural icing conditions p 66 A87-13503 ORLANDO, V. A. [NASA-CR-179515] p 118 N87-11797 RAMAN, K. V. PLATZER, M. Mode S beacom system Functional description A direct method for enforcing equality constraints in Possibilitiesfor optimizationand higher-harmoniccontrol [DOT/FAA/PM-86/19] p 87 N87-11715 optimal output feedback p 134 A87-13353 ORTMEYER. T. H. of helicooter main rotors bv blade leatherina p Ill- A87-14021 RAMANATHAN, R. K. Implementationof CDFM generator control Influence of analysis and design models on minimum p 135 A87-14957 PLEASANTS. W. A., 111 Application 01 numerical optimization lo rotor weight design p 98 N87-11739 aerodynamic design p 99 N87-11757 RAMSDEN. J. M. P PLESHA, M. E. The inspectable structure p 65 A87-16397 A constitutive law lor finite element contact problems RAMSEY, J. K. PAGNI, P. J. with unclassical friction Concentrated mass effects on the flutter of a composite Fire salety science, Proceedingsolthe First International [ NASA-TM-888381 p 131 N87-12924 advanced turboprop model Symposium. Gaithersburg. MD, October 7-11. 1985 PLETCHER. R. H. [ NASA-TM-888541 p 130 N87-12017 p 78 A87-13186 Application of viscous-inviscid interaction methods to RANSOM. W. F. PAHLE. J. W. transonic turbulent flows Wholefield displacement measurements using speckle Decoupling control synthesis for an oblique-wing [NASA-CR-179900] p 75 N87-11700 image processing techniques for crash tests aircraft p 108 A87-13342 PLOTKIN, A. p 124 A87-13680 PAI. S. I. Vortex panel calculation of wake rollup behind a large RATWANI, M. M. Aerodynamic force calculations of an elliptical circulation aspect ratio wing p 70 A87-14102 Design considerations lor superplastically formed control airfoil p7l A87-14360 PLOTKIN, K. J. complex aircraft structures p 87 A87-13151 PALLElT. E. H. J. Lightweight sidewalls for aircraft interior noise control RAY, A. Micr&lectronics in aircraft systems [NASA-CR-172490] p 138 N87-12323 Selection of media access protocol for distributed digital p 101 A87-13469 PLUMER, J. A. avionics p 134 A87-13436 PAN, R. Summary of NASA storm hazards lightning research, RAY, E. J. The 8 m x 6 m low speed wind tunnel at the Chinese 1980-1985 p 80 A87-15003 A description 01 the active and passive Aerodynamic Research and Development Center PONOMARENKO, 8. V. sidewall-boundary-layerremoval systems of the 0.3-meter [ AD-AI 684481 p 119 N87-11803 Radio-navigation meters based on the K588 series transonic cryogenic tunnel PANOSSIAN, H. V. microprocessor unit p 86 A87-15569 [ NASA-TM-877641 p 118 N87-11801 Optimal stochastic observers aDDli9d.. to hvdraulic PONOMAREV. A. 1. REAZER. J. S. actuation systems p 87 nei-13354 Mathematical modeling 01 the motion of a statically Spatial and temporal description 01 strikes lo the FAA PARIKH. P. deformed delta-shaped glider p 95 A87-15205 CV-580 aircraft p 81 A87-15013 Antimisting kerosene Evaluation of low temperature PONOMAREV. B. A. Simultaneous airborne and ground measurement of low performance Turbines with counter-rotating rotors lor aircraft power altitude cloud-to-ground lightning strike on CV-580 [DOTIFAA/CT-85/31] p 122 N87-11902 plants p 106 A87-15211 aircraft p 81 A87-15014 PARK, S. W. POPA FOTINO. I. A. Current levels and distributions on an aircraft during Application of the AlPA (Approximate Iterative Ground-baseddetection 01 aircraft icingconditions using ground lightning Simulation tests and in-flight lightning Preprocessing Algorithm) to F.106 data anachments p 82 A87-15017 microwave radiometers p 80 A87-14861 [ AD-A169084 1 p 116 N87-12569 Electrostatic field measurements in a loam filled C-130 PARKER, 8. M. PORTNOY. D. spray characteristics of two combined jet atomizers fuel lank during fuel sloshing p 95 A87-15037 Some effects of moisture on adhesive-bonded REAZER, M. J. CFRP-CFRP joints p 129 A87-16160 p 124 A87-13860 State-of-the-art techniques for lightning POTTER, J. C. PATTON, R. J. susceptibility/vulnerability assessments Companson of two techniques 01 I F D based on a Advanced construction procedures: Confined bases for p 126 A87-15006 airport pavements non-linear stochastic model of an aircraft REGENIE, V. A. p 114 A87-16196 [FAA/PM-86/9] p 118 N87-11799 Rapid prototyping facility for flight research in PAULL, A. PRAMANIK. M. B. artificial-intelligence-basedflight systems concepts Further shock tunnel studies of scramjet phenomena Landing gear performance simulation by KRASH [NASA-TM-882681 p 137 N87-12273 [ NASA-CR-1799371 p 77 N87-12542 program p90 A87-13670 REHFIELD, L W. PAVLOV, V. A. PRATT, T. K. Someobservationsonthe behavior of the Langley model Analysis of a composite thin-walled aircraft structure Optimization applications in aircraft engine design and rotor blade p 127 A87-15226 test p 106 rw-117~8 [NASA-CR-1798801 p 74 N87-11695 8-8 PERSONAL AUTHOR INDEX SHEU, M. J.

REICHEL, R. RUFF, 0. A. SCHWANE. R. Redundant computer system for flyby-wire controls Analysis and verification of the icing scaling equations. Numerical calculation of viscous internal flows p 111 A87-14013 Volume 1: Revision p 69 A87-14010 REICHERT, 0. [AD-A167976] p 85 N87-12551 SCHWARTZ. R. L Models for rotor and helicopter design RUHNKE, L H. Beyond FTMP and SIFT - Advanced fault-tolerant p 92 A87-14008 Effect of E-fieldmill location on accuracy of electnc field computers as successors to FTMP and SIFT REYER, W. M. measurements with instrumented airplane p 133 A87-13200 Gust and maneuver smtra for aeneral aviation p 95 A87-15027 SCHY, A. A. aircraft RUMIANTSEV. V. V. Tradeoff methods in multiobjective insensitive design [AIAA PAPER 86-25991 p 93 A87-14033 A study of the effect of the temperature factor on of airplane control systems p 115 N87-11730 RIBAUT. M. pressure losses in the cooling system of the leading edge SCOGGINS, J. L Perfbrmance evaluation of an inverse integral equation of a deflector vane p 127 A87-15218 Time-based air traffic management using expert method applied to turbomachine cascades RUSAK. Z. systems p 85 A87-13362 p 72 A87-14771 An analytical parametric investigation of numerical SEARS, W. R. RICHARDS, C. L. JR. nonlinear vortex-lattice methods p 67 A87-13638 A wind-tunnel method for V/STOL testing Precision point target tracking p 101 A87-13545 RUSTAN, P. L, JR. p 118 A87-15463 RICHMOND, R. D. A review of aerospace and ground lightning threat SEEBASS, A. R. Simultaneous airborne and ground measurement of low characteristics and applications p 132 A87-15002 Advances in the understanding and computation of altitude cloud-tc-ground lightning strike on CV-580 RUYBALDOSSANTOS, C. L unsteady transonic flow p 73 A87-15452 aircraft p 81 A87-15014 Tool to develop real time simulation systems SEGINER, A. An analytical parametric investigation of numerical RICHTER, P. [ INPE-3979-TDLI2331 p 137 N87-13179 Possibilitiesfor optimizationand higher-harmonic control nonlinear vortex-lanice methods p 67 A87-13638 of helicopter main rotors by blade feathering SEIBERT. W. p 11 1 A87-14021 S Theoretical studies of the ETW diffuser and of the RILEY, B. L second throat p 69 A87-14022 AV-BB/GR Mk 5 airframe composite applications SACKElT, J. R. SELDEN, R. 0. p 88 A87-13628 The siting, installation and operational suitability of the Lghtweight sidewalls for aircraft interior noise control RILEY, M. F. Automated Weather Observing System [AWOS) at [NASA-CR-172490] p 138 N87-12323 Helicopter rotor blade aerodynamic optimization by heliports SEN, J. K. mathematical programming p 99 N87-11753 [ DOT/FAA/PM-86/30] p 133 N87-13099 Survivability and crashworthinessdesign criteria RILEY, P. H. SAFONOV, A. S. p89 A87-13665 Control of gas turbines. The future: Is a radical approach Analysis of a composite thin-walled aircraft structure SERAFINI, T. T. needed? p 127 A87-15226 Polymer, metal. and ceramic matrix composites for [PNR-S0295] p 107 N87-11793 SALAMA, M. advanced aircraft engine applications RISLEY, M. D. Influence of analysis and design models on minimum p 121 A87-15187 State-of-the-art techniques for lightning weight design p 98 N87-11739 SERRANO, A. V. susceptibility/vulnerability assessments SANTORU, J. State-of-the-art techniques for lightning p 126 A87-15W Flight model discharge system susceptibility/vulnerabilityassessments Current levels and distributions on an aircraft during [AD-A169423] p 117 N87-12571 pi26 A87-15006 ground lightning simulation tests and in-flight lightning SARMA, 1. S. Spatial and temporal description of strikes to the FAA attachments p 82 A87-15017 Influence of analysis and design models on minimum CV-580 aircraft p 81 A87-15013 RIZK, M. H. weight design p 98 N87-11739 Current levels and distributions on an aircraft during Propeller design by optimization p 105 A87-14123 SAROHIA, V. ground lightning simulation tests and in-flight lightning RIZK, N. K. Antimisting kerosene: Evaluation of low temperature attachments p 82 A87-15017 Prediction of velocity coefficient and spray cone angle performance SHAIRER, E. T. for simplex swirl atomizers p 125 A87-13830 [DOT/FAA/CT-85/31] p 122 N87-11902 Methods for assessing wall interference in the 2- by RIZZI, A. SCHETZ, J. A. 2-foot adaptive-wallwind tunnel Vortex-sheet capturing in numerical solutions of the Finite element Navier-Stokes calculation of [ NASA-TM-882521 p 118 N87-11800 incompressible Euler equations p 70 A87-14099 three-dimensionalturbulent flow near a propeller SHANE, S. J. ROBERTS, F. L p 70 A87-14101 The design and qualification testing of an Criteria for asphalt-rubber concrete in civil airport SCHICKEL, K. P. energy-absorbing seat for the Navy's H-53 A/D pavements: Mixture design Comparative flight measurement of icing parameters for helicopters p 91 A87-13679 [ DOT/FAA/PM-86/39] p 129 N87-11910 the DO 28 D2 propeller-driven aircraft of the German Army ROBINSON, D. SHAPIRO, E. Y. Testing Office 61 and for DNLR's Falcon 20 E jet aircraft Dynamic output feedback flight control laws using TSAR (Theater Simulation of Airbase Resources) in stratus clouds eigenstructure assignment p 109 A87-13355 database dictionary F-4E [ ESA-l7-9411 p 83 N87-11709 SHARP, B. H. [AD-A169575] p 139 N87-13352 SCHINSTOCK, W. C. Lightweight sidewalls for aircraft interior noise control ROBSON, R. R. Flight test report of the NASA icing research airplane: [NASA-CR-172490] p 138 N87-12323 Flight model discharge system Performance. stability. and control after flight through [AD-A169423] p 117 N87-12571 natural icing conditions SHEARIN, J. G. RODGERS, C. [ NASA-CR-1795151 p 116 N87-11797 pynamic loads on twin jet exhaust nozzles due to shock Fabrication of cooled radial turbine rotor SCHMIDT-EISENLOHR, U. noise p 94 A87-14369 [ NASA-CR-1795031 p 107 N87-11789 Further development of the axial-radial compressor SHEFER, M.

RODNISHCHEV, N. E. p 104 A87-13998 Combined guidance ~ Flight control of atmospheric The principle of optimality in the mean for fault-tolerant SCHMIT, L A. vehicles p 110 A87-13654 systems p 112 A87-15212 Influence of analysis and design models on minimum SHEFRIN, J. RODRIGUEZ, A. A. weight design p 98 N87-11739 State-of-the-artcrashworthy cargo restraint systems for Multivariablecontrol of a twin lift helicopter system using SCHMITENDORF, W. E. military aircraft p 89 A87-13667 the LOGILTR design methodology p 110 A87-13419 Methods for obtaining robust tracking control laws SHELTON, R. W. ROMMEL, B. A. p 134 A87-13319 Corona from simulated aircraft surfaces and their Practical considerations in aeroelastic design SCHNEIDER, J. G. contribution to the triggered discharge p 97 N87-11720 State-of-the-art techniques for lightning p 82 A87-15024 ROSElTI, C. susceptibility/vulnerabililyassessments SHEN, c. a. Mobile communications. navigation and surveillance p 126 A87-15006 Aerodynamic characteristics and flow round cross [IAF PAPER 86-3331 p 86 A87-16027 Cunent levels and distributions on an aircraft during parachutes in steady motion ROSS, A. J. ground lightning simulation tests and in-flight lightning [AIAA PAPER 86-24581 p 68 A87-13798 Application of regression analysis to coupled responses attachments p 82 A87-15017 SHEPPARD, D. J. at high angles of attack p 113 A87-16185 SCHNELL, H. Simulator design and instructional features for carrier ROSS, H. Development and testing of critical components for the landing: A field transfer study Utilization of 3-0 programs for aircraft design and technological preparation of a CFK outer wing [ AD-A1699621 p 119 N87-12573 [ MBB-UT-224.861 p 92 A87-13997 development p86 A87-13646 SHERERTZ, A. SCHRAGE, D. P. F. ROWE, S. A. Impact severity and potential injury prevention in general National Specialist's Meeting on Crashworthy Design Preliminary design of electromechanical servosystems aviation accidents p 79 A87-13687 of Rotorcrali. Georgia Instituteof Technology,Atlanta. April [SAE PAPER 8517591 p 129 A87-15482 7-9, 1986, Proceedings p89 A87-13662 SHERIDAN. A. E. RUDENKO, 0. V. SCHROEDER. J. A. Turbine bypass remote augmentor lift system for Nonlinear acoustics - 4chievements, prospects. Ground-based detection of aircraft icing conditions using V/STOL aircraft p 105 A87-14364 problems p 138 A87-15582 microwave radiometers p 80 A87-14861 SHERIF. F. E. RUDOLPH, T. SCHROEDER, W. Advanced digital optical control actuation for the Eftect of E-fieldmill location on accuracy of electric field Numerical calculation of viscous internal flows ADOCS measurements with instrumented airplane p 69 A87-14010 [SAE PAPER 8517551 p 112 A87-15480 p 95 A87-15027 SCHUR, D. SHEU, M. J. RUDOLPH, T. H. The effect of material compressibility (Poisson ratio) on Comparison of numerical solutions of lower order and

F-106 data summary and model results relative to threat the elasto-plasticsolution to the problem of a cylinder under hiaher order inteoral1.eauation methods for two-dimensional criteria and protection design analysis internal pressure [coldworking situation) airofoils p 81 A87-15004 p 124 A87-13642 [AIAA PAPER 86-25911 p 69 A67-14028

B-9 SHPUND, Z. PERSONAL AUTHOR INDEX

SHPUND, 2. STAHL, M. TERESHCHUK, V. S. Improved measurement of the dynamic loads acting on A heater made from graphite composite material for A system model. a logic design diagram, and a general rotating parachutes potential deicing application synthesis algorithm for optimal systems of onboard [AIM PAPER 86-24731 p68 A87-13807 [NASA-TM-888881 p 101 N87-12559 electrical equipment in computer-aided design SHUSTER, P. M. STALENHOEF, A. H. C. p 96 A87-15214 The siting, installation and operational suitability of the Number and duration of Runway Visual Range (RVR) TERRY, J. S. Automated Weather Observing System (AWOS) at runs for RVR-values lower than 225 m Joint thunderstorm operations using the NASA F-1066 heliports [KNMI-TR-85(FM)] p 119 N87-11805 and FAATWAFWAL Convair 580 airplanes [DOT/FAA/PM-86/30] p 133 N87-13099 STALKER, R. J. p 95 A87-15018 SIDOROV, 0. P. Further shock tunnel studies of scramjet phenomena THAYER, E. B. Calculation of aerodynamic force coefficients [NASA-CR-179937] p 77 N87-12542 Thrust reverser-exhaust nozzle assembly for a gas p 73 A87-15229 STEINETZ, 8. M. turbine engine SIGAL, A. A constitutive law for finite element contact problems [AD-W12390] p 108 N87-12561 with unclassical friction Parametric sizing of aerial application airplanes based THOMAS, J. L. on varying levels of technology p 139 A87-13636 [ NASA-TM-888381 p 131 N87-12924 STENGEL, R. F. Comparison of finite volume flux vector splittings for the SIMPSON. M. M. Euler equations p 70 A87-14109 Fight control design using nonlinear inverse dynamics Aircraft lightning-induced transient lest and protection THOMLEY. K. E. p 109 A87-13352 comparison p 82 A87-15022 Simulator design and instructional features for carrier Determination of nonlinear aerodynamic coefficients SLIWA. S. M. landing: A field transfer study using the estimation-before-modelingmethods Experiences performing conceptual design optimization [ AD-AI 699621 p 119 N87-12573 p 114 A87-16202 of transport aircraft p 97 N87-11723 THOMSON, J. M. STEVENS, 8. L. SMITH, 8. S. Prediction of skin currents flowing on a Lynx helicopter Eienstructure assignment by dynamic output Investigation of coating performance and corrosion of due to a simulated lightning strike p 95 A87-15012 feedback p 134 A87-13385 compressor components in the TF30-P-3 engine of Fl11C TIFFANY, S. H. aircraft STOCK. H. W. Application of optimization techniques to the design of [ AD-AI 688021 p 107 N87-11792 Theoretical studies of the ETW diffuser and of the a flutter suppression control law for the DAST ARW-2 second throat p 69 A87-14022 p 1 15 N87-11736 SMITH, C. A. TIMM, R. Recent advances in aerodynamics p 73 A87-15451 STOUGH, H. P.. 111 Summary of NASA stalllspin research for general Vortex shedding of a square cylinder in front of a slender SMITH, 0. A. aviation configurations airfoil at high Reynolds numbers. Part 2 Compressibility Aircraft automatic-flight-controlsystem with inversion of [AIM PAPER 86.25971 p 111 A87-14032 effect the model in the feed-forward path using a STRAWN, R. [ MPIS-24/1985] p 75 N87-11704 Newton-Raphsontechnique for the inversion TIMMS, R. D. [ NASA-TM-882091 p 116 N87-11796 The prediction of transonic loading advancing helicopter rotors The development of balance tubes for Dowty Rotol SMITH, H. W. [ADA1682171 p 100 N87-11781 composite bladed propellers p 63 A87-13630 Static test of an ultralight airplane STREHLOW. H. TIMNAT, Y. M. [AIAA PAPER 86-26001 p64 A87-14034 Prospective, characteristics and problems of the use SMITH, K. F. Development of a new type of bearingless rotor system p 93 A87-14017 of boron in different air augmented propulsion modes Crashworthy crewseat limit load optimization through STRICKLAND, J. H. [IAF PAPER 86-1911 p 122 A87-15924 dynamic testing p 91 A87-13675 TING, On the utilization of vortex methods for parachute L SMITH, R. D. Interaction of decaying trailing vortices in ground aerodynamic predictions FAA helicopterlheliport research. engineering. and shear p 66 A87-13499 [AIAA PAPER 86.24551 p68 A87-13795 development bibliography, 1964-1986 TIPTON, D. L [FAA/PM-86/47] p 118 N87-11798 STUCKENBERG, N. Development of an advanced vaneless inlet particle Sensor failure detection in flight control systems using SNYDER, D. M. separator for helicopter engines p 105 A87-14984 deterministic observers p 114 A87-16195 The porifolio model of technological development in the TIWARI, A. aircran industry SUIT, W. T. Combining Loran and GPS - The best of both worlds [AD-A1708321 p66 N87-12534 Evaluation of a nonlinear parameter extraction p 86 A87-13544 mathematical model including the term C(subm(sub delta SOBEL, K. M. TIWARI, S. N. e squared)) Dynamic output feedback flight control laws using Shock boundary layer interactions in laminar transonic [ NASA-TM-877311 p 116 N87-12566 eigenstructure assignment p 109 A87-13355 flow over airfoils using a hybrid method SUMMA, J. M. SOBIESKI, J. p 66 A87-13503 A summary of the development of integral aerodynamic Recent Experiences in Multidisciplinary Analysis and TOBIAS, L. methods for the computation of rotor wake interactions Optimization. part 1 Time-based air traffic management using expert [AD-A169254] p 77 N87-12545 [ NASA-CP-2327-PT-I ] p 96 N87-11717 systems p 85 A87-13362 SUN, M. TOUCHETTE, J. L Multidisciplinary systems optimization by linear Aerodynamic force calculationsof an elliptical circulation Composite curing with semi-permeable membranes decomposition p 136 N87-11740 control airfoil p 71 A87-14360 p 120 A87-I3121 Recent Experiences in MUltidiSCiDlinaN... Analvsis and TREVINO, G. Optimization, part 2 SUNDARARAJAN, S. Airplane flight through wind-shear turbulence [ NASA-CP-2327-PT-21 p 99 N87-11750 Finite element contact analysis of ring gear and support p 127 A87-15193 p 80 A87-14371 SOLTIS. S. J. TRIPLETT, W. E. The development of dynamic performance standards SUNTHARALINGAM. P. A test on the reliability and performance of the verbex Flutter Optimization in fighter aircraft design for civil rotorcran seats p 89 A87-13666 p97 N87-11721 SOTSENKO, IU. V. series 4000 voice recognizer TROST, T. F. Turbines with counter-rotating rotors for aircraft power [AD-A169066] p 130 N87-12729 Interpretation of a class of in-flight lightning signatures SUTTON, L R. plants p 106 A87-15211 p 81 A87-15005 SPANG, H. A,. 111 Aeroelastic-aerodynamic optimization of high speed TRUFANOV, A. N. Multi-vanablecontrol of the GE T700 engine using the helicopter-compound rotor p 99 N87-11758 A study of local heat transfer on the face surface of a LOGlLTR design methodology p 103 A87-13418 SWEETMAN, B. nozzle ring model SPEARS, W. D. p 127 A87-15215 Airlines look at 150-seaters p 83 A87-15180 TUNG, C. Evaluation of a visual system in its support of simulated Manufacturers plan new long-range aircran The prediction of transonic loading advancing helicopter helicopter flight p 95 A87-15181 rotors [ AD-AI 688291 p 102 N87-11783 SZETELA, E. J. SPITZER, C. R. [AD-A168217] p 100 N87-11781 Long-term deposit formation in aviation turbine fuel at TURKEL, E. All-dgital lets are taking off p 102 A87 14352 elevated temperature p 121 A87-14986 SRIJAYANTHA. M. Acceleration to a steady state for the Euler equations Determination of nonlinear aerodynamic coefficients p70 A87-14096 TUSS, J. using the estimation-before-modelingmethods Design considerations for superplastically formed p 114 A87-16202 T SRINIVASAN. 0. R. complex aircraft structures p 87 A87-13151 TAKALLU. M. A. Tip vortices of wings in subsonic and transonic flow A TYLER, H. P. numerical simulation Effect of an upstream wake on e pusher propeller Closed loop control of an afterburning FIOO gas turbine [AIAA PAPER 86-26021 p 69 A87-14035 engine p 103 A87-13323 [ NASA-TM-883341 p 75 N87-11699 Numerical simulation of tip vortices of wings in subsonic TAKEDA, K. and transonic flows Noise and performance of a counter-rotation propeller U IADA1 691 161 p77 NE712544 p 105 A87-14366 TAKEDA, R. SRIRAM. P. UKOLOV. I. S. Possible military applications of stratospheric airship Wholefield displacement measurements using speckle Integrated active control Systems Methods of discussed p 101 N87-12716 image processing techniques for crash tests algonthmic integration p 135 A87-14682 p 124 A87-13680 TAMBOUR, Y. UWIRA. K. Correlation of experimentalstatic and dynamic response Spray Characteristics of two combined jet atomizers Comparative flight measurement of icing parameters for of simple structural components p 124 A87-13683 p 124 A87-13660 the DO 28 D2 propeller-drivenaircran of the German Army SRIVATSAN, R. TAYLOR. J. E. Testing Office 61 and for DFVLR's Falcon 20 E let aircraft Design of a takeoff performance monitoring system On optimal design for the blade-rootlhub interface in in stratus clouds p 103 N87-11787 jet engines p 106 N87-11769 [ESA-TT-941] p 83 N87-11709 B-10 PERSONAL AUTHOR INDEX xu, x.

v WANG, Y. WILLIAMS, L Mechanism of energy absorption via buckling - An Component improvement program task 83-01, 36E133 VAISBURG. V. A. analytical study p 124 A87-13682 air turbine starter Automatton of support processes for aircraft productm WANG, 2. [ADA1694831 PI08 N87-12562 using computers and numencal control Jwrnal of engineering thermophysics (selected WILLIAMSON, R. G. p64 A87-14687 articles) Effect of two endwall contours on the performance of VAN INGEN, C. [ AD-A1694521 p 139 N87-13347 an annular nozzle cascade p 71 A87-14119 Crashworthy crewseat limit load optimization through WARRICK, J. C. WILLIAMSON. W. S. dynamic tesbng p 91 A87-13675 The status of crashworthiness design criteria Flight model discharge system VAN LEER, B. p89 A87-13664 [ AD-A1694231 p 117 N87-12571 Cornpanson of finite volume flux vector splittings for the WARWICK, 0. WILLIFORD, C. F. Euler equations p 70 A87-14109 A320 . Fly-by-wire airliner p96 A87-16394 Comparison of absorption and radiation boundary VANDERBOK. R. S. WATKINS, J. conditions in a timedomain three-dimensional Stall margin indication The Annular Parachute An approach to a low altitude [AIM PAPER 86-25951 p 101 A87-14030 - finite-difference code p 82 A87-15034 personnel parachute VANDERLINDEN. H. H. WILSON, S. E., 111 A check of crack propagation prediction models agaInst [AIM PAPER 8624491 p 80 A87-13823 The handling qualities and flight characteristics of the test results aenerated under transDort aircraft fliaht WATKINS, J. W. Grumman design 698 simulated twin-engine tilt Nacelle simulation 1oa;ling Design and development of a two-stage parachute V/STOL aircraft [ NLR-TR-84005-UI p 100 N87-11782 system for delivery of troops from a high-speed aircraft [NASA-TM-86785] p 100 N87-12558 VANLEEUWEN. S. S. [AIAA PAPER 86-24481 p 80 A87-13818 WINTER, C.J. A small, flexible and powerful data acquisition system WATTS, M. E. Results of research on materials and construction for the F16 aircraft Supplementary calibration test of the tipaerodynamics- methods by the DNLR p64 A87-14015 [NLR-MP-85074-U] p 103 N87-11786 and acoustics-test pressure transducers WINTER, F. VASILEV, 1. IU. [ NASA-TM-883121 p 131 N87-12830 RADC automated RBM package (RAMP) Start-up of a wind tunnel wth a multlchannel diffuser WEBB, D. B. p 128 A87-15417 p 72 A87-15206 Automatic variable reefing of parachutes by application WINTER, H. VASTAVA, R. of inflation forces Development and testing of new technologies for flight Design considerations for superplastically formed [AIAA PAPER 86-24341 p 79 A87-13784 operation and safety p 86 A87-14004 complex aircraft structures p 87 A87-13151 WEBSTER, L R. WINTER, R. VAUGHN, R. L VLSl impact on RAMS strategies in avionics design Modelling strategies for finite element crash simulation Airworthiness considerations of lightning stnke p 128 A87-15423 of complete vehicles p90 A87-13673 protection for helicopter digital engine controls WEED, R. A. WINTUCKY. W. T. p f05 AR7-15010 Direct-inverse transonic mng analysisdesign method Compound cycle engine program VEMURU, C. S with viscous interaction p 71 A87-14365 [ NASA-TM-88879j p I07 N87-11790 Shock boundary layer interactions in laminar transonic WEERASOORIYA. 1. flow over airfoils using a hybnd method WIlTIG, S. Research on mechanical properties for engine life p66 A87-13503 Performance and optimisation of an airblast nozzle ~ prediction VENKAYYA, V. 8. Drop size distribution and volumetric air flow [AD-A169570] p 108 N87-12563 The automated strength-aeroelastic design of p 125 A87-13820 aerospace structures program p 98 N87-11749 WEILER, W. WIlTLIN. 0. VICKERY, E. D. New-technology gas generator (GNT 1) - The actual Program KRASH - The evolution of an analytical tool The Annular Parachute - An approach to a low alstude state of development p 126 A87-14006 to evaluate aircraft structural crash dynamics response personnel parachute WEIMER, J. A. p 90 A87-13672 Implementation of CDFM generator control [AIM PAPER 86-24491 p80 A87-13823 WOITHE, K. p 135 A87-14957 VISWANATHAN, S. Testing of fiber-reinforced construction elements - Aircraft battery state of charge and charge control WEINGART. 0. Simulation of mechanical loads and environmental system Automated flexible assembly of aerospace structures influences p 92 A87-14012 [AD-A169411] p 130 N87-I2766 p63 A87-13063 WOLF, D. M. VllTAL, V. R. WEISENBACH, M. E. Ramjet application in atmospheres of different celestial Development of an advanced vaneless inlet particle Demonstration of combat damage repair estimator bodies separator for helicopter engines p 105 A87-14984 p 65 A87-15436 [IAF PAPER 86-181] p 120 A87-15920 VODEGEL, H. J. 0. C. WEISS, J. L A brief introduction to the helicopter Evaluation of detectability and distinguishability of WOO, A. C. [NLR-MP-85062-U] p65 N87-11688 aircraft control element failures using flight test data An exterior Poisson solver using fast direct methods p 110 A87-13435 and boundary integral equations with applications to nonlinear potential flow p 125 A87-13872 WEISS, R. M. W The siting, installation and operational suitability of the WOOD, E. R. Automated Weather Observing System (AWOS) at 7050 aluminum rivets for military aircraft WAFFORD, J. H. p 124 A87-13173 Tailoring a major weapon environmental program heliports [DOT/FAA/PM-86/30] p 133 N87-13099 WOOD. p 102 A87-15430 M. WAGNER. 8. WELTE. D. Development of high-alumina ceramic materials suitable New fuselage technologies for general-aviationaircraft New fuselage technologies for general-aviationaircraft for making jet engine fixtures p 120 A87-13092 p 93 A87-14027 p 93 A87-14027 WOOD, R. M. WAGNER. S. WERME, T. D. Impact of airfoil profileon the supersonic aerodynamics Theoretical investigations of transonic rotor-blade Axisymmetric vortex lattice method applied to parachute of delta wings p 71 A87-14363 aerodynamics p 68 A87-13994 shapes WOODWARD, P. W. Improvement of mathematical models of helicopters by [AIAA PAPER 86.24561 p68 A87-13796 Aviation turbine fuels. 1985 analytical presentation of nonlinear aerodvnamics WESTRA, D. P. [DE86-012140] p 122 N87-11908 p 69 A87-13995 Simulator design features for helicopter landingon small WOOLLEY, 0. WAKE. L. V. ships. 1: A performance study Airlines look at 150-seaters p 83 A87-15180 Investigation of coating performance and corrosion of [ AD-A16951 41 p 119 N87-12572 compressor components in the TF30-P-3 engine of F11IC Simulator design and instructional features for carrier WRENN, G. A. Multidisciplinary optimization applied to a transport aircraft landing: A field transfer study [AD-A168802] p 107 N87-11792 [ AD-A1699621 p 119 N87-12573 aircraft p 84 N87-11746 WALEN, 0. B. WHITE, G. WU, K. S. Comparison Of low level frequency domain lightning The 3600 hp split-torque helicopter transmission A comparison of measured and calculated stress in solid simulation test to pulse measurements [NASA-CR-174932] p 106 N87-11788 and ribbon parachute canopies p 126 A87-15007 [AIAA PAPER 86-24881 p 80 A87-13815 WALLERSTEIN, 0. V. WHITE, W. D. Resin-hardener systems for resin transfer molding wu, W.C. Design enhancement tools in MSC/NASTRAN p 120 A87-13093 State estimation of flying vehicle p 114 A87-16209 p 136 N87-11748 WALSH, J. L WICKER, S. A. WUNSCHEL, A. J., JR. Multi-Echelon Repair Level Analysis MERLA Helicopter rotor blade aerodynamic optimization by - Joint thunderstorm operations using the NASA F-1066 p64 A87-15414 and FAATC/AFWAL Convair 580 airplanes mathematical programming p 99 N87-11753 WIGGINS, T. J. p 95 A87-15018 WANG, B.C. Application of numerical optimization to rotor Variable structure control of a turbojet engine aerodynamic design p 99 N87-11757 p 103 A87-13343 WILLCOX, s. w. WANG. D.4. Comparison of two techniques of I.F.D. based on a X Computation of two-dimensional supersonic turbulent non-linear stochastic model of an aircraft flow over a Compression comer p 66 A87-13502 p 114 A87-16196 XIONG, Y.-F. WANG, M. WILLIAMS, D. H. State estimation of flying vehicle p 114 A87-16209 The 8 m x 6 m low speed wind tunnel at the Chinese Impact of mismodeled idle engine performance on xu, x. Aerodynamic Research and Development Center calculation and tracking of optimal 4-D descent Modeling of the aircraft mechanical control system [AD-A168448] p 119 N87-11803 trajectories p88 A87-13360 p 111 A87-14135

B-11 YANG, K. T. PERSONAL AUTHOR INDEX

Y ZIMMERMANN, R. E. Crash dynamics program transport seat performance YANG, K. T. and cost benefit study Turbulent buoyant flow and pressure variations around [DOT/FAA/CT-65/36] p 83 N87-11708 an aircraft fuselage in a cross wind near the ground ZIXING, W. p 78 A87-13187 The effect of a winglet on the spatial vortex of a slender YAO. T. body at high angle of anack Modeling of the aircraft mechanical control system [AD-A169925] p 65 N87-12533 p 111 A87-14135 ZRNIC, D. S. YAVROUIAN, A. Weather safety aspects in future civil air navigation Antimisting kerosene: Evaluation of low temperature p 85 A87-13540 performance ZUKAKISHVILI, R. 1. [DOT/FAA/CT-85/31] p 122 N67-11902 A study of the effect of surface roughness on the head resistance of an aircraft p 94 A87-14717 YAVUZ, T. ZUVLONI, R. Performance prediction for fully-deployed parachute Experimental investigation of a solid fuel ramjet canopies combustor p 104 A87-13658 [AIAA PAPER 86-24751 p 79 A87-13809 YEH. 0. T. Vortex panel calculation of wake rollup behind a large aspect ratio wing p 70 A87-14102 YIP, L. P. Exploratorywind-tunnel investigation of the stability and control characteristics of advanced general aviation configurations [AIAA PAPER 86.25981 p 111 A87-14031 Wind-tunnel investigation of the OMAC canard configuration [AIAA PAPER 86.26081 p 69 A87-14038 YOELI. R. Parametric sizing of aerial application airplanes based on varying levels of technology p 139 A87-13636 YOSHIMURA, T. Full scale crash test of a BKI 17 helicopter p 91 A87-13676 YOUNG, 0. P. An exterior Poisson solver using fast direct methods and boundary integral equations with applications to nonlinear potential flow p 125 A87-13872 YOUNG, L. A. An experimental investigation of free-tip response lo a jet [ NASA-TM-882501 p 76 N87-12539 The evaluation of a number of prototypes for the free-tip rotor constant-moment controller [ NASA-TM-866641 p 131 N87-12869 YOUNG, P. C. Identification and system parameter estimation 1985; Proceedings of the Seventh Symposium, University of York. England, July 3-7. 1985. Volumes 1 8 2 p 135 A67-16176 YU. J. C. Two-dimensional blade-vortex flow visualization investigation p70 A67-14111 YU, R. Ground aircraft deicing technology review [DOT/FAA/CT-85/21] p 83 N87-11707 z ZAKHARCHENKO, V. F. Questions and problems in aerodynamics p 66 A87-13050 ZAKHAROV. N. N. Start-up of a wind tunnel wilh a multichannel diffuser p 72 A87-15206 ZAKHAROV, V. A. Methods for the assembly and testing of the bearing supports of gas turbine engines p 126 A87-14663 ZAMANI. H. Design considerations for superplastically formed complex aircraft structures p 87 A87-13151 ZANG. T. A. Spectral methods for modeling supersonic chemically reacting flowfields p 70 A87-14110 ZARETSKY. E. V. Selection of rolling-element bearing steels for long-life application [NASA-TM-888811 p 129 N87-11993 ZHAN, Z. Optimal guidance law with first order lag loop and normal constraint p 86 A87-14140 ZHANG. J. Mechanism of energy absorption via buckling - An analytical study p 124 A87-13682 ZHENG, Y. The method of calculating the desired flight path of terrain following technique with circular arc spline p 111 A67-14136 ZHOU. W. Correlation of experimentalstatic and dynamic response of simple structural components p 124 A87-13683 ZIEGLER. W. Lightningstrikes lo aircraft of the German Federal Armed Forces p 81 A87-15008

6-12 CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 277) March 1987

Typical Corporate Source Index Listing Allled Bendlx Aerospace, Utica. N.Y. D Component improvement program task 83-01, 36E133 air turbine starter Dayton Unlv., Ohio. [ AD-A1694831 p 108 N87-12562 Research on mechanical properties for engine life CORPORATE SOURCE Alphatech, Inc., Burlington, Ma-. prediction Evaluation of detectability and distinguishability of [AD-A169570] p 108 N87-12563 aircraft control elernant failures using flight test data Computational fluid dynamic studies of certain ducted p 110 A87-13435 bluff-body flowfields relevant to turbojet combustors. Amax Materials Research Center, Ann Arbor, Mlch. Volume 1: Time-dependentcalculations with the k-epsilon Army Aviation Systems Command, SI. Louls, Mo. Carburizing steel for high temperature service turbulence model for an existing centerbody combustor [AD-A168327] p 122 N87-11877 Summary of artificial and natural icing tests conducted [ AD-A171 4341 p 131 N87-12818 Analytlcal Methods, Inc.. Redmond, Wash. Ion US Armv aircraft from 1974 to 1985 Department of the Alr Force, Washlngton, D.C. r A summary of the development of integral aerodynamic I I FAAlCT-85/26 I p 25 N87-10064 Electroluminescent (EL] remotely-controlled landing methods for the computation of rotor wake interactions zone marker light system [ AD-A1692541 p 77 N87-12545 f AD-DO1 23861 D 87 N87-11716 I-i- 7T Arlnc Research Corp., Annapolis, Md. Length adjustable strut link with low aerodynamic drag Ground aircraft deicing technology review [AD-D012279] p 77 N87-12543 [ DOT/FAA/CT-85/21] p 83 N87-11707 Thrust reverser-exhaust nozzle assembly for a gas Arito~Unlv., Tucaon. turbine engine Influence of airfoil mean loading on convected gust p 108 N87-12561 interaction noise p 137 A87-13587 [AD-W123901 Army Engineer W-atemays Expsrlmen?Statlon. Turbine air seal with full backside cooling Vlckaburg, MIS. [AL3-MJ12405j p 108 N87-12564 Advanced construction procedures: Confined bases for Cryogenic wound rotor for lightweight. high voltage airport pavements generators [FAA/PM-86/9] p 118 N87-11799 [AD-W12370] p 130 N87-12768 Listings in this index are arranged alphabetically by Army Research and Technology Labs., Fort Eustla, Va. Improved vane platform sealing and retention means corporate source The title of the document is used Application of numerical optimization to rotor [AD-DO12407] p 131 N87-12881 to provide a brief description of the subject matter aerodynamic design p 99 N87-11757 Department of the Alr Force, Wrlght-Patteraon AFB, Aeroelastic-aerodynamic optimization of high speed The page number and the accession number are Ohlo. helicopter-compoundrotor p 99 N87-11758 Joint thunderstorm operations using the NASA F-1066 included in each entry to assist the user in locating Arnold Englneerlng Development Center. Arnold Air and FAATCIAFWAL Convair 580 airplanes the abstract in the abstract section If applicable. Force Statlon, Tenn. D 95 A87-15018 a report number is also included as an aid in Analysis and verification of the icing scaling equations. Deutsche Forschungs- und Versuchsanstalt fuer Luft- Volume 1: Revision identifying the document und Raumfahrt, Brunawlck (West Germany). [AD-A167976] p 85 N87-12551 Investigation of magnetometer errors and their Effects of test cell recirculationon high-bypass turbofan Compensation in the 80-105 helicopter engines during simulated altitude tests [DWLR-FB-86-21] p 102 N87-11784 [AD-A171418] p 108 N87-12565 Douglas Aircraft Co., Inc., Long Beach, Callf. Lightweight sidewalls for aircraft intenor noise COntrOl A B [NASA-CR-1724901 p 138 N87-12323 Guidance law simulationstudies for complex approaches AEG-Telefunken, Ulm (West Germany). Balllstlc Research Labs., Aberdeen Provlng Ground, using the Microwave Landing System (MLS) p 87 N87-12552 Obstacle-warningradar for helicopters Md. [ NASA-CR-1781821 p 132 N87-13149 Blast gust loading on a 35 degree swept-back mng Douglas Alrcraft Co., Inc., St Louls, Mo. [AD-A1694151 p 116 N87-12570 Practical considerations in aeroelastic design Alr Force Environmental Technlcal Appllcatlons p 97 N87-11720 Center, Scott AFB, 111. Boelng Commercial Alrplane Co., Seattle, Wash. Revised Uniform Summary of Surface Weather Sensitivity studies of 4D descent strategies in an Observations (RUSSWO) Parts A-F Ellington ANGB. advanced metenng environment p 88 A87-13361 Texas PlAS A program for an iterative aeroelastic solution E p 97 N87-11725 [AD-A1693891 p 133 N87-13105 Boelng Computer Services Co., Seattle, Wash. Alr Force Inst. of Tech., Wright-Pattenon AFB. Ohlo. Energy Research Corp., Danbury, Conn. Applying optimization software libranes to engineenng Aircraft battery state of charge and charge control The portfolio model of technological development in the problems p 136 N87-11775 aircraft industry system Boelng Computer Services Co., Tukwlla, Wash. [AD-A1694111 p 130 N87-12766 [ AD-A1 708321 p 66 N87-12534 An extenor Poisson solver using fast direct methods A review of microbursts and their analysis and detection and boundary integral equations mth applications to ESDU lnternstlonal Ltd., London (England). with Doppler radar nonlinear potential flow p 125 A87-13872 Pitot and static errors in steady level flight [ESDU-86006] p 74 N87-11691 [AD-A1704581 p 133 N87-13110 Boelng Mllltary Alrplane Development, Seattle, Wash. AIr Force Systems Command, Andrews AFB, Md. An extenor Poisson solver using fast direct methods Vertical deflection characteristics of aircraft tyres p 129 N87-11992 Joint thunderstorm operations using the NASA F-106B and boundary integral equations with applications to [ ESDU-860051 and FAATUAFWAL Convair 580 airplanes nonlinear potential flow p 125 A87-13872 Introduction to aerodynamics derivitives. equations of p 95 A87-15018 Brown Unlv., Provldence, R. 1. motion and stability Large-scale coherent structures in free turbulent flows [ESDU-86021I p 76 N87-12536 Alr Force Systems Command, Wright-Patterson AFB. and their aerodynamic sound p 138 A87-15458 Ohio. Propellarlbody interaction for thNst and drag The 8 m x 6 m low speed mnd tunnel at the Chinese [ESDU-86017] p 76 N87-12537 Aerodynamic Research and Development Center C Simplified forms of performance equations. Addendum [AD-A168448] p 119 N87-11803 A Effect on aeroplane level speed of small changes in The effect of a winglet on the spatial vortex of a slender Calltornla Unlv.. Lo8 Angelea. thrust, drag, weight, power body at high angle of attack Application of time-domain unsteady aerodynamics to [ ESDU-86004-ADD-A] p 100 N87-12556 [ AD-A169925) p 65 N87-12533 rotary-wing aeroelasticily p 94 A87-14103 Frictional and retarding forces on aircraft tyres. Part 4 Carbon fibers Application of modern structural optimizationto vibration Estimation of effects of yaw reduction in rotorcraft p 115 N87-11752 [ AD-A171 3701 p 123 N87-12622 [ESDU-86016-PT-4] p 131 N87-12868 Cambridge Unlv. (England). Journal of engineenng thermophysics (selected Visualisation of axial turbine tip clearance flow using a ESKX Corp., Orlando, Fla. Simulator design features for helicopter landing small articles) linear cascade on [AD-A1694521 p 139 N87-13347 [CUED/A-TURBO/TR-1221 p 107 N87-12560 ships. 1: A performance study [ AD-A16951 4 I p 119 N87-12572 Alr Force Wright Aeronautical Labs., Wrlght-Patterson Case Western Reserve Unlv.. Cleveland, Ohio. AFB, Ohlo. Analysis of mixed-mode crack propagation using the Simulator design and instructional features for carrier FIOO fuel sampling analysis Foreign samples boundary integral method landing: A field transfer study [AD-A168573] p 122 N87-11904 [ NASA-CR-1795181 p 131 N87-12915 [ AD-A1699621 p 119 N87-12573 c- 1 European Space Agency, Paris (France). CORPORA TE SOURCE

European Space Agency, Parla (France). J Mlchlgan Unlv.. Ann Arbor. Comparative flight measurement of icing parameters for On optimal design for the blade-rootlhub interlace in the DO 28 D2 propeller-dnvenaircraft of the German Army JAI AssocIatea, Mountain View, Callf. jet engines p 106 N87-11769 Testing Oftice 61 and for DNLR's Falcon 20 E let aircraft Numerical simulation of tip vortices of wings in subsonic Mllltary Academy, West Point, N. Y. in stratus clouds and transonic flows Interpretation01 a class of in-flight lightning signatures [ESA-lT-941] p 83 N87-11709 [ADA1691 161 p 77 N87-12544 p 81 A87-15005 On sound propagation in centrifugal fan casings Jet Propulalon Lab., Callfornla Inst. of Tech., Mlsslsslppl Unlv., Unlvenlty. Pa d Uta. [ESA-TT-957] p 138 N87-12326 M Mobile intercept of storms p 132 N87-13064 Influence of analysis and design models on minimum weight design p 98 N87-11739 Antimisting kerosene: Evaluation of low temperature N F performance [DOT/FAA/CT-85/31] p 122 N87-11902 Natlonal Aeronautlca and Space Admlnlatratlon. Amas Falrchlld Republlc Co., Fannlngdale, N.Y. Jolnt Publlcatlons Research Service, Arlington. Va. Research Center, Moffett Fleld, Callf. Assessment of damage tolerance requirements and Possible military applications of stratospheric airship Time-based air traffic management using expert analyses A user's manual for crack growth and crack discussed p 101 N87-12716 systems p 85 A87-13362 initiation analysis DAMGRO Grundy - Parallel processor architecture makes [ AD-A1 712091 p 132 N87-12939 programming easy p 135 A87-13703 Federal Avbtlon Admlnlatratlon, Atlantlc Clty, N.J. K An exterior Poisson solver using fast direct methods Joint thunderstorm operations using the NASA F-1066 and boundary integral equations with applications to Kaman Aerospace Corp., Bloomfleld, Conn. and FAATC/AFWAL Convair 580 airplanes nonlinear potential flow p 125 A87-13872 Regression analysis as a design optimization tool p 95 A87-15018 Computation of sharp-fin-induced shock wave/turbulent p 136 N87-11754 boundary-layer interactions p 70 A87-14104 The siting. installation and operational suitability of the A rotor optimization using regression analysis Convergence acceleration for a three-dimensional Automated Weather Observing System (AWOS) a1 p 136 N87-11755 EulerlNavier-Stokeszonal approach p 70 A87-14105 heliports KatIMS Unlv., Lawrence. Experimental and numerical investigationof supersonic [DOT/FAA/PM-86/30] p 133 N87-13099 Static test of an ultralight airplane turbulent flow through a square duct p 70 A87-14117 Foderal Avlatlon Admlnlatretlon. Waahlngton. D.C. [AIAA PAPER 86-26001 p 64 A87-14034 Recent advances in aerodynamics p 73 A87-15451 FAA helicopterlheliport research, engineering. and Applications of CONMIN to wing design optimization with Modeling of turbulent separated flows for aerodynamic development bibliography. 1964-1986 vortex flow effect p 98 N87-11737 applications p 73 A87-15454 [ FAA/PM-86/47] p 118 N87-11798 Design of a lakeofl performance monitoring system The evolution of adaptive-wall wind tunnels p 103 N87-11787 Florlda State Unlv.. Tallahassee. p 118 A87-15464 Kentron Internatlonal. Inc., Hampton, Va. Recent advances in aerodynamics p 73 A87-15451 Laser velocimetry for transonic aerodynamics Tradeoff methods in multiobjective insensitive design Florlda Unlv., Galnesvllle. p 74 A87-15467 of airplane control systems p 115 N87-11730 Comments on gust response constrained optimization Special opportunities in helicopter aerodynamics Aircraft configuration optimization including optimized p 115 N87-11774 p 74 A87-15469 flight profiles p 98 N87-11743 Tip vortices of wings in subsonic and transonic flow: A Flow Rewarch. Inc., Kent, Wash. Multidisciplinary optimization applied to a transport numerical simulation Propeller design by optimizalion p 105 A87-14123 aircraft p 84 N87-11746 [ NASA-TM-883341 p 75 N87-11899 Kohlman Systems Research, Inc., Lawrence, Kana. Overview: Applications of numerical optimization Flight test report of the NASA icing research airplane: methods to helicopter design problems Performance. stability, and control after flight through p 99 N87-11751 G natural icing conditions The predictionof transonic loading advancing helicopter [NASA-CR-179515] p 116 N87-11797 General Dynamlca Corp., Fort Worth, Tax. rotors Turbine bypass remote augmentor lift system for [AD-A168217] p 100 N87-11781 V/STOL aircraft p 105 A87-14364 L Aircraft automatic-flight-controlsystem with inversion of General Eleclrlc Co., Lynn, Mass. the model in the feed-forward path using a Multi-vanable control of the GE T700 engine using the Llghtnlng Technologlea. Inc., Plrtafleld, Mau. Newton-Raphson technique for the inversion LOGlLTR design methodology p 103 A87-13418 Summary of NASA storm hazards lightning research. [NASA-TM-88209] p 116 N87-11796 General Electrlc Co., Schenectady, N. Y. 1980-1985 0 80 A87-15003 Methods for assessing wall interference in the 2- by Multi-vanable control of the GE T700 engine using the Lockheed-Callfornla Co., Burbank. 2-foot adaptive-wall wind tunnel [ NASA-TM-882521 p 118 N87-11800 LOGlLTR design methodology p 103 A87-13418 Some experiences in aircraft aeroelastic design using Preliminary Aeroelastic Design of Structures (PAD) Rapid prototyping facility for flight research in General Motors Corp.. Indlanapolla, Ind. p 98 N87-11747 artificial-intelligence-based flight systems concepts Advanced Gas Turbine (AGT) Technology Project Window acoustic study for advanced turboprop aircraft [ NASA-TM-882681 p 137 N87-12273 [NASA-CR-179484] p 130 N87-11995 [NASA-CR-172391] p 138 N87-12322 An experimental investigation of free-tip response to a Gwrgla Inat. of Tech.. Atlanta. Lockheed-Georgla Co.. Marletta. jet Turbulent flow around a winglfuselage-type luncture Optimization in the systems engineering process [ NASA-TM-882501 p 76 N87-12539 p 70 A87-14108 p96 N87 11719 NASA rotor systems research aircraft: Fixed-wing Some ObSeNallOllS on the behavior Of the Langley model Application of the generalized reduced gradient method configuration flight-test results rotor blade to conceptual aircraft design p 97 N87-11722 L NASA-TM-867891 p 100 N87-12557 [NASA-CR-l79880] p 74 N87-11695 Sizing-stiffened composite panels loaded in the The handling qualities and flight characteristics of the postbuckling range p 129 N87-11733 Grumman design 698 simulated twin-engine tilt Nacelle V/STOL aircraft [ NASA-TM-867851 p 100 N87-12558 H M Supplementary calibration test of the tip-aerodynamics- and acoustics-test pressure transducers Hughes HellCoptera, Culver Clty, Callf. MacNeaCSchwendler Corp.. Loa Angeles, Callf. [ NASA-TM-883121 p 131 N87-12830 Optimization process in helicopter design Design enhancement Iools in MSCINASTRAN The evaluation of a number of prototypes for the free-tip p 98 N87-11726 p 136 N87-11748 rotor constant-moment controller Hughea Rewarch Labs., Mallbu. Csllf. Massachuwtta Inat. of Tech., Cambrldgo. [ NASA-TM-866641 p 131 N87-12869 Flight model discharge system Multi-venable control 01 the GE T700 engine using the Natlonal Aeronautlca and Space Admlnlatratlon. Fllght [ AD-A169423 1 p 117 N87-12571 LOGlLTR design methodology p 103 A87-13418 Rewarch Center, Edwards, Callf. Multrvariablecontrol of a twin lift helicopler system usmg Aeroelastic control of oblique-wing aircraft the LOGlLTR design methodology p 110 A87-13419 p 108 A87-13341 I Yassachuwtta Inat. of Tech.. Lexlngton. Decoupling control synthesis for an oblique-wing Mode S beacom system Functional description aircraft p 108 A87-13342 IIT Research Inat.. Bartleavllle. Okla. [DOTlFAAlPM-86/19] p87 N87-11715 Natlonal Aeronautlca and Space Admlnlatratlon. Aviation turbine fuels. 1985 Materlala Rewerch Labs., Ascot Vale (Auatralla). Langley Reaearch Center. Hampton. Va. [ DE86-0121401 p 122 N87-11908 Investigation 01 coating performance and corrosion 01 Time scale analysis of a digital flight control system Infomutlca Qenml Corp., Moffen Fleld, Callf. compressor componenls in the TF30-P.3 engine 01 F 11 1C p 109 A87-13347 Experimental and numencal investigation of supersonic aircrah Impact of mismodeled idle engine performance on turbulent flow through a square duct p 70 A87-14117 IAD-Al688021 p 107 N87-11792 calculation and tracking of optimal 4-D descent Mar-Planck-lnatltutfuer Stroemungafonchung. trajectories p 88 A87-13360 Inetltut Fnnco-Allemand de Recherchea. St. Loula Gwnlngen (Weat Germany). (France). Interaction of decaying trailing vortices in ground Vortex shedding of a square cylmder in front of a slender Introductionto helicopter noise shear p 66 A87-13499 airloil at high Reynolds numbers Part 2 Compresslbility Exploratory wind-tunnel investigation the stability and [ISL-NB-401/84] p 139 N87-12327 of effect control characteristics of advanced general aviation InatltutO de Pemqulua Eapaclala. Jose doa Lo IMPIS-24/1985] p 75 N87-I I704 configurations Campoa (Brazll). McDonnoll Alrcrafl Co.. St. Loula. Yo. [AIAA PAPER 86-25961 p 11 1 A87-14031 Tool to develop real time simulation systems Multiple let impingement flowfields p 73 A87-I 5461 Summary of NASA stalllspin research for general [ INPE-3979-TDL/2331 p 137 N87-13179 Fluner optimization in fighler aircraft design aviation configurations Iowa State Unlv. of Sclence and Technology, Amen. p 97 N87-1I721 [AIAA PAPER 86-25971 p 11 1 A87-14032 Application of viscous-inviscid interaction methods to Mlchlgan Technologlcal Unlv.. Houghton. Potential influences of heavy rain on general aviation transonic turbulent flows Airplane flight through wind-shear lurbulence airplane performance [ NASA-CR-1799001 p 75 N87-11700 p 80 A87-14371 [AIAA PAPER 86-26061 p 94 A87-14036 c-2 CORPORA TE SOURCE Toronto Univ. (Ontario).

Wind-tunnel investigation of the OMAC canard Natlonal Aerospace Lab., Amsterdam (Netherlands). R configuration A brief introduction lo the helicopter [AIM PAPER 86.26081 p 69 A67-14038 [ NLR-MP-85062-U1 p65 N87-11688 RMS Technologles, Inc., Trevoae. Pa. Acceleration lo a steady state for the Euler equations A check of crack propagation prediction models against Crash dynamics program transport seat performance p70 A87-14096 test results generated under transport aircraft flight and cost benefit study Turbulent llow around a wing/fuselage-type juncture simulation loading DOT/FAA/CT-85/36] p 83 N87-11708 p 70 A87-14108 [NLR-TR-84005-U1 p to0 N67-11782 Rockwell lnternatlonal Corp., Columbus, Ohlo. Comparison of finite volume flux vector splittings for the Systems. avionics and instrumentation of transport Fabrication and testing of lightweight hydraulic system Euler equations p 70 A87-14109 category helicopters simulator hardware Spectral methods lor modeling supersonic chemically [ NLR-MP-85066-UI p 102 N87-11785 [AD-A169884] p 130 N87-12711 reacting flowfields p 70 A87-14110 A small, flexible and powerful data acquisition system Rolls-Royce Ltd., Derby (England). Two-dimensional blade-vortex flow visualization for the F16 aircraft Control of aas turbines. The future: Is a radical amroach investigation p 70 A87-14111 needed? [ NLR-MP-85074-Ul p 103 N87-11786 All-digital jets are taking off p 102 A87-14352 [PNR-90295] p 107 N87-11793 National Tranaportatlon Safety Board, Washlngton, D. Impact of airfoil profile on the supersonic aerodynamics Roval Alrcraft Establlshmcnt Farnborough (England). C. of delta wings p7t A87-14363 .An approximate method of estimating theaerodinamic National Transportation Safety Board safety Dynamic loads on twin jet exhaust nozzles due to shock interference between two parallel bodies in a supersonic noise p 94 A87-14369 recommendation p 83 N87-11706 llow (axial force) Vectorizable multigrid algorithms for transonic-flow Aircraft accident r6ports: Brief format, US civil and [ BR-1002711 p 76 N87-12540 calculations p 72 A87-14652 foreign aviation. issue number 5 of 1985 accidents Royal Netherlands Meteorologlcal Inst., Do Bllt. Summary of NASA storm hazards lightning research, [PB86-916919] p 83 N87-11710 Number and duration of Runway Visual Range (RVR) 1980-1985 p80 A87-15003 Runway imursions at controlled airports in the United runs for RVR-values lower than 225 m F-106 data summary and model results relative to threat States [KNMI-TR-85(FM)I p 119 N87-11805 criteria and protection design analysis [PB86-917003] p 84 N67-11711 p81 A87-15004 Aircraft accident reports: Brief format, US civil and Joint thunderstorm operations using the NASA F-1066 foreign aviation. issue number 4 of 1985 accidents S and FAATClAFWAL Convair 580 airplanes [ PB86-9169181 p 84 N87-11712 p 95 A87-15018 Aircraft accident reports: Brief format, US civil and Science Appllcatlons, Inc., Orlando, Fla. Evaluation of a visual system in its support of simulated Forward-swept wing configuration designed for high foreign aviation, issue number 3 of 1985 accidents helicopter flight maneuverability by use of a transonic computational [ PB86-9169171 p 84 N87-11713 [ AD-At 688291 p 102 N87-11783 method Review of accident data: US general aviation calendar [ NASA-TP-26281 p 75 N87-11702 Sevllle Tralnlng Systems Corp., Penaacola, Fla. year 1982 Evaluation of a visual system in its support of simulated Recent Experiences in Multidisciplinary Analysis and [ PB86-2019101 p 84 N87-11714 Optimization. part 1 helicopter flight Aircraft accidentlincident summary reports: Erie, [ NASA-CP-2327-PT-11 p 96 N87-11717 [AD-A168829] p 102 N87-11783 Pennsylvania, October 14, 1984; Albuquerque, New Experiences performing conceptual design optimization Slkorsky Alrcraft, Stratford, Conn. Mexico, February It, 1985 of transport aircraft p 97 N87-11723 The st:uc!ura! optimization of a spreader bar for twin [ PB86-9104071 p84 N87-12549 Application of optimization techniques to the design of lifl helicopter operations p 100 NBi-li758 a fluner suppression control law lor the DAST ARW-2 Aircraft accident report: Bar Harbor Airlines Flight 1808. Slmula, Inc., Tempe, Arlz. p 115 N87-11736 Beech BE-99. NBOOWP. Auburn-Lewiston Municipal Crash dynamics program transport seat performance Airport. Auburn, Maine, August 25. 1985 Calculated effects of varying Reynolds Number and and cost benefit study dynamic pressure on flexible wings at transonic speeds [ PB86-9104081 p 84 N87-12550 [ DOT/FAA/CT-85/36] p 83 N87-11708 p 75 N87-11738 Naval Postgraduate School, Monterey, Callf. Solar Turbines lnternatlonal, San Dlego, Callf. Multidisciplinary systems optimization by linear A dynamic model for airframe cost estimation Fabrication of cooled radial turbine rotor decomposition p 136 N87-11740 [ AD-A1 688421 p 65 N87-11687 [NASA-CR-l795031 p 107 N87-11789 Recent Experiences in Multidisciplinary Analysis and New Mexlco Unlv., Albuquerque. South Dakota School of Mlnes and Technology, Rapld Optimization. part 2 Application of the AlPA (Approximate Iterative city. [ NASA-CP-2327-PT-21 p 99 N87-11750 Preprocessing Algorithm) lo F-106 data Atmospheric electrical modeling in support of the NASA Helicopter rotor blade aerodynamic Optimization by [ AD-A1690841 p 116 N87-12569 F106 Storm Hazards Project mathematical programming p 99 N87-11753 New York Unlv., New York. [NASA-CR-179801I p 132 N87-12082 A description of the active and passive Interaction of decaying trailing vortices in ground Stanford Unlv., Callf. sidewall-boundary-layer removal systems of the 0.3-meter shear p 66 A87-13499 Theoretical and expenmental investigations of sensor loCalion for optimal aeroelastic system state estimation transonic cryogenic tunnel Northrop Corp., Hawthorn, Callf. p 115 N87-11794 [NASA-TM-87764] p 118 N87-11801 The automated strength-aeroelastic design of An analysis of blade vortex interaction aerodynamics Mach 6 experimental and theoretical stability and aerospace structures program p 98 N87-t 1749 and acoustics p 77 N87-12547 performanceof a finned cylindrical body at angles of anack Vortex flap technology: A stability and control State Unlv. of New York, Albany. up to 65 deg assessment Large volume water sprays for dispersing warm fogs [ NASA-TM-890501 p 76 N87-12538 [NASA-CR-1724391 p 115 N87-11795 Effect of port corner geometry on the internal p 125 A87-13848 performance of a rotating-vane-typethrust reverser State Unlv. of New York. Stony Brook. [ NASA-TP-26241 p 77 N87-12541 0 Characterization and dynamical studies of polymers in Evaluation of a nonlinear parameter extraction dipolar (aprotic) liquids mathematical model including the term C(subm(sub delta [AD-A1692431 p 123 N87-12685 Ohlo State Unlv., Columbus. e squared)) An experimental study of the aerodynamics of a NACA Sverdrup Technology, Inc., Arnold Air Force Statlon, [NASA-TM-87731] p 116 N87-12566 0012 airfoil with a simulated glaze ice accretion Tenn. National Aeronautlcs and Space Admlnlstratlon. LewIs [ NASA-CR-1798971 p 75 N87-11701 Analysis and verification of the icing scaling equations. Research Center, Cleveland, Ohlo. Volume 1: Revision Orlando Technology, Inc., Shallmar, FIa. A real-time simulation evaluation 01 an advanced [AD-A1679761 p 85 N87-12551 TSAR (Theater Simulation of Airbase Resources) detection. isolation and accommodation algorithm for Effects of test cell recirculation on high-bypassturbofan sensor failures in turbine engines p 103 A87-13318 database dictionary F-4E [AD-A169575] p 139 N87-13352 engines during simulated altitude tests Polymer. metal. and ceramic matrix composites lor [ AD-A171 41 61 p 108 N87-12565 advanced aircraft engine applications p 121 A87-15187 P STAEBL: Structural tailoring of engine blades, phase 2 T p 106 N87-11731 Pratt Whltney Alrcraft, East Hartford, Conn. Compound cycle engine program and Ophmization applicaltons in aircraft engine design and Technlsche Hogeschool, Delft (Netharlands). [NASA-TM-88879I p 107 N87-11790 test p106 N87-11768 Comparison of finite volume flux vector splinings for the Selection of rolling-element bearing steels for long-life PRC Ksntron, Inc., Hampton, Va. Euler equations p 70 A87-14109 application Effect of an upstream wake on a pusher propeller Tel-Avlv Unlv. (Israel). [NASA-TM-88881] p 129 N87-11993 [AIAA PAPER 86-26021 p 69 A87-14035 Concentrated mass effects on the flutter of a composite Acceleration to a steady state for the Euler equations Prlnceton Unlv., N. J. p70 A87-14096 advanced turboprop model Numerical solution of the Euler equation for Texas AIM Unlv., College Station. [NASA-TM-88854] p 130 N87-12017 compressible inviscid fluids p 69 A87-14095 A heater made from graphite composite material for Criteria for asphalt-rubber concrete in civil airport A prototype maintenance expert system for the CH-47 potential deicing application pavements: Mixture design flight control hydraulic system [ DOT/FAA/PM-86/39] p 129 N87-11910 [ NASA-TM-888881 p 101 N87-12559 [AD-A169019] p 116 N87-12568 A constitutwe law for finite element contact problems Texas Unlv., Austin. A test on the reliability and performance of the verbex with unclassical friction Viscous-inviscidinteraction in transonic separated flow series 4000 voice recognizer over solid and porous airfoils and cascades [ NASA-TM-888381 p 131 N87-12924 [ AD-A1690661 p 130 N87-12729 Cruise noise of counterrotation propeller at angle of p 76 N87-12535 anack in wind tunnel Optimal descending, hypersonic turn to heading [ NASA-TM-888691 p 139 N87-13252 Q [DE86-010989] p 120 N87-12577 Natlonal Aeronautlcs and Space Admlnlstratlon. Toronto Unlv. (Ontarlo). Marshall Space Flight Center, Huntsvllle, Ala. Queensland Unlv., St. Lucla (Australla). Motion characteristics of the UTIAS flight research Large volume water sprays for dispersing warm fogs Further shock tunnel studies of scramjet phenomena simulator motion-base p 125 A87-13848 [NASA-CR-t79937] p 77 N87-12542 [ UTIAS-TN-261] p 119 N87-11802

c-3 Transmission Research, Inc., Cleveland, Ohio. CORPORA TE SOURCE

Transmlaslon Research, Inc., Cleveland, Ohlo. The 3600 hp split-torque helicopter transmission [ NASA-CR-174932J p 106 N87-11788 Transportation Systems Center, Carnbrldge, Mass. General aviation activity and avionics survey [ AD-A1685821 p 65 N87-11686 U

United Technologlea Research Center. East Hartford. Conn. Long-term deposit formation in aviation turbine fuel at elevated temperature p 121 A87-14986 Optimization of helicopter rotor blade design for minimum vibration p 99 N87-11756 Unlverslty of Wedern Mlchlgan, Kalarnazw. Aeroelastic control of oblique-wng aircraft p 108 A87-13341 Decoupling control synthesis for an oblique-wing aircraft p 108 A87-13342

Vlrglnla Polytechnlc Inst. and State Unlv., Blacksburg. Comparison of two propeller source models for aircraft interior noise studies p 88 A87-13596 Analytical model for investigation of interior noise characteristics in aircraft with multiple propellers including synchrophasing p 94 AB?-14925 Optimization of cascade blade mistuning under flutter and forced response constraints p 106 N87-11732 Vlrglnla Unlv., Charlottesvllle. The implementation and us of Ada on distributed systems with high reliability requirements [NASA-CR-179842] p 137 N87-12265 W

Washlngton Unlv., Seattle. Expenmental and numerical investigation of supersonic turbulent flow through a square duct p 70 A87-14117

c-4 FOREIGN TECHNOLOGY INDEX

AERONAUTICAL ENGINEERING /A Continuing Sibliogfaphy (Supplement 211) March 1987

Typical Foreign Technology Finite element contact analysis of ring gear and Theoretical investigations of transonic rotor-blade Index Listing support p 127 A87-15193 aerodynamics p 68 A87-13994 Motion characteristics of the UTlAS flight research Improvement of mathematical models of helicopters by simulator motion-base analytical presentation of nonlinear aerodynamics [UTIAS-TN-261] p 119 N87-11802 p 69 A87-13995 CHINA, PEOPLES REPUBLIC OF Development and testing of critical components for the Aerodynamic characteristics and flow round cross technological preparation of a CFK outer wing COUNTRY OF parachutes in steady motion INTELLECTUAL [MBB-UT-224-66] p 92 A87-13997 [AIAA PAPER 86-24581 p68 A87-13798 Further development of the axial-radial compressor Modeling of the aircraft mechanical control system p 104 A87-13998 p 111 A87-14135 The method of calculating the desired flight path of Technologies for a mechanized carbon fiber terrain following technique with circular arc spline construction element for commercial aircraft production AUSTRALIA p 111 A87-14136 [ MBB-UT-005-861 p 126 A87-13999 Reaction to aircraft noise in residential areas around Mathematical model and digital simulation for speed Impetus of new technologies for utility, executive, and Australian airports )%l A87-,0116 control system of two-spool turbojet engine commuter aircraft p 104 A87-14000 p 105 A87-14139 Structure-component tests for a CFK fuselage Optimal guidance law with first order lag loop and normal [ MBB-UT-223-861 p 121 A87-14001 constraint p 86 A87-14140 Load lightening and flutter damping for future Airbus Optimal discrete design of digital flight control system projects p 111 A87-14142 [ MBB-UT-004.861 p92 A87-14002 State estimation of flying vehicle p 114 A87-16209 ATTAS - The new test bed p92 A87-14003 The 8 m x 6 m low speed wind tunnel at the Chinese Development and testing of new technologies for flght Aerodynamic Research and Development Center operation and safely p 86 A87-14004 [AD-A168448] p 119 N87-11803 Avionics systems for future commercial helicopters Journal of engineering thermophysics (selected p 101 A67-14005 articles) [AD-A169452) p 139 N87-13347 New-technology gas generator (GNT 1) - The actual CZECHOSLOVAKIA state of development p126 A87-14006 The development of DMS-scales for cryogenic wind Listings in this index are arranged alphabetically by Numerical solution of transonic potential flows with finite elements method using multigrid technique tunnels p 117 A87-14007 country of intellectual origin. The title of the p 68 A87-13900 Models for rotor and helicopter design document is used to provide a brief description of p 92 A87-14008 Measurements in the high subsonic region in the the subject matter. The page number and the F TU-Berlin wind tunnel with adaptive walls accession number are included in each entry to p 117 A87-14009 assist the user in locating the citation in the abstract FRANCE Numerical calculation of viscous internal flows section. Experinmntal investigationof near and far acoustic field p 69 A87-14010 of a small turbojet p 138 A67-13605 Testing of fiber-reinforced construction elements - Analysis of the first milliseconds of aircraft lightning Simulation of mechanical loads and environmental allachment p 81 A87-15016 influences p 92 A87-14012 Expenmental study of the interaction between an arc Redundant computer system for fly-by-wirecontrols A and an electrically floating structure p 126 A87-15023 p 111 A87-14013 Parameter estimation of aircraft with fly-by-wire control ESSY . An electromechanical adjustment system for AUSTRALIA systems p 113 A87-16186 aircraft control surfaces p 92 A87-14014 Direct solution of flutter equations with interactive Introduction lo helicopter noise Results of research on materials and construction methods by the DFVLR p 64 A87-14015 graphics procedure p 110 A87-13648 [ISL-NB-4011841 p 139 N87-12327 Testing a tail rotor system in fiber-reinforcedconstruction Adaptive fluller suppression p 113 A87-16182 Aircraft flight data compatibility checking using maximum manner p 92 A87-14016 Development of a new type of bearingless rotor likelihood and extended Kalman filter estimation G system p 93 A87-14017 p 113 A87-16184 GERMANY.FEDERAL REPUBLIC OF Investigation of coaling performance and corrosion of Actuating system with digital signal converters and Aero- and hydro-acoustics; Proceedings of the fiber-optic control p 93 A67-14018 compressor components in the TF30-P-3 engine of F111C Symposium, Ecole Centrale de Lyon. Ecully, France, July aircraft CAD as a prerequisite for computer-integrated 3-6, 1985 p 137 A67-13585 manufacturing p 135 A87-14019 [AD-A168802] p 107 N87-11792 Utilization of 3-D programs for aircraft design and Possibilitiesfor optimization and higher-harmoniccontrol Further shock tunnel studies of scramjet phenomena development p88 A87-13646 of helicopter main rotors by blade feathering [ NASA-CR-1799371 p 77 N87-12542 Performance and optimisation of an airblast noale - p 11 1 A87-14021 Drop size distribution and volumetric air flow Theoretical studies of the ETW diffuser and of the B p 125 A87-13826 second throat p 69 A87-14022 Clanficalion of adhesive binding mechanisms of Status report on the European Transonic Wind Tunnel BRAZIL aluminum structural bonds in aircraft fabrication (EW p 117 A87-14023 Tool lo develop real lime simulation systems [ MBB-UT-226-861 p 121 A87-13985 DFVLR cryogenic-wind-tunnel and model technology [ INPE-3979-TDLl2331 p 137 N87-13179 Increasing the economy of design and preparation for p 117 A87-14024 manufacturing by integrated and graphic data processing: A redundant actuating system with servo valves of low CADICAM - Phase 111 hydraulic loss p 93 A87-14025 C [MBB-UT-225-86] p 125 A87-13986 Design and manufacturing of a CFRP tail fin for the Results of helicopter research at DFVLR A300 CANADA p 91 A87-13967 [ MBB-UT-006-861 p 93 A87-14026 Multivariable high-gain control with feedforward Design and construction of a cryogenic-wind-tunnel New fuselage technologies for general-aviation aircraft compensation - A design technique p 134 A87-13365 model p 117 A87-13988 p 93 A87-14027 Automatic variable reefing of parachutes by application Technicalleconomic evaluation of new propfan Influence of trailing-edge meshes on skin friction in of inflation forces concepts in comparison with the turbofan of the 1990s Navier-Stokes calculations p 71 A87-14125 [AIAA PAPER 86.24341 p 79 A87-13784 p 104 A87-13989 Lightning strikes toaircraft ofthe German Federal Armed Low cost aerial testing of parachutes Improving the energy efficiency of cooled Forces p 81 A87-15008 [AIAA PAPER 86-24721 p 79 A87-13806 high-temperature turbines p 104 A87-13990 Advances in adaptive wall wind tunnel technique Finite element Navier-Stokes calculation of Design considerations for fly-by-wire control of new p 118 A87-15465 three-dimensional turbulent flow near a propeller Airbus aircraft Computation of optimum-optimorum wing-fuselage p 70 A87-14101 [ MBB-UT-222-861 p 110 A87-13991 configuration for future generation of supersonic aircraft Effect of two endwall contours on the performance of The amphibian technology lest vehicle - Summary and p 74 A87-15761 an annular nozzle cascade p 71 A87-14119 results p 91 A87-13992 Ramjet application in atmospheres of different celestial The use of mathematical models in aerodynamics (The Development of a GFRP wing in accordance with FAR bodies W. Rupert Turnbull Lecture) p 72 A87-15189 Part 23 p 92 A87-13993 [IAF PAPER 86.1811 p 120 A87-15920

D- 1 FOREIGN TECHNOLOGY INDEX

Frequency domain parameter estimation of aerOnaUtiCal The effect of a winglet on the spatial vortex of a slender The principle of optimality in the mean for fault-tolerant systems without and with tlme delay body at high angle of attack Systems p 112 A87-15212 p 114 A87-16193 [AD-A1699251 p 65 N87-12533 A system model, a logic design diagram, and a general Sensor failure detection in flight control Systems using Possible military applications of stratospheric airship Synthesis algorithm for optimal systems of onboard deterministic ObseNerS p 114 A87-16195 discussed p 101 N87-12716 electncal equipment in computer-aided design Analytical redundancy through nonlinear ObSeNerS p 96 A87-15214 p 114 A87-16197 A study of local heat transfer on the face Surface of a Vortex shedding of a square cylinder in front of a slender N nozzle ring model p 127 A87-15215 airfoil at high Reynolds numbers Part 2 Compressibility The effect of random wind gusts on the stability of a effect NETHERLANDS parachute system p 72 A87-15216 [ MPIS-24/1985] p 75 N87-11704 Aircraft control input optimization for aerodynamic A study of the effect of the temperalure factor on Comparative flight measurement of icing parameters for denVatNe estimation in dynamic manoeuvres pressure losses in the cooling system of the leading edge the DO 28 D2 propeller-driven aircraft of the German Army p 113 A87-16183 of a deflector vane p 127 A87-15218 Testing Office 61 and for DFVLR’s Falcon 20 E let aircraft An efficient decision-makingfreefilter for processes mth A Simulation of the dynamics of the mechanisms of the in stratus clouds abrupt changes p 136 A87-16189 aircraft landing gear p 96 A87-15220 [ ESA-TT-941 I p 83 N87-11709 Determination of dynamic stresses in the heat-insulating A brief introduction to the helicopter Investigation of magnetometer errors and their coatings of flight vehicles during aerodynamic heating compensation in the 80-105 helicopter [ NLR-MP-85062-Ul p 65 N87-11688 p 72 A87-15223 [ DFVLR-FB-86-21I p 102 N87-11784 A check of crack propagation prediction models against Analysis of a composite thin-walled aircraft structure On sound propagation in centrifugal fan casings test results generated under transport aircraft flight p 127 A87-15226 IESA-TT-9571 D 138 N87-12326 simulation loading Calculation of aerodynamic force coefficients Obstacle-warning radar for helicopters [ NLR-TR-84005-Ul p 100 N87-11782 p 73 A87-15229 p 132 N87-13149 Systems. avionics and instrumentation of transport Some asymptotic types of transonic vortex flows category helicopters p 74 A87-15553 [NLR-MP-85066-U] p 102 N87-11785 Determination of the regime coefficients in the local I A small, flexible and powerlul data acquisition system theory of interaction from plate data p 74 A87-15561 for the F16 aircraft Synthesis of devices for the optimal processing of pulsed INDIA [NLR-MP-85074-U] p 103 N87-11786 radio signals in LORAN systems p 86 A87-15563 Weather safety aspects in future civil air navigation Number and duration of Runway Visual Range (RVR) Radio-navigation meters based on the K588 series p 85 A87-13540 runs for RVR-values lower than 225 m microprocessor unit p 88 A87-15569 Constant-density approximation to Taylor-Maccoll [KNMI-TR-B5(FM)I p 119 N87-11805 Nonlinear acoustics - Achievements. prospects. solution p 71 A87-14127 problems p 138 A87-15582 Parametric identification of discontinuous Carbon fibers nonlinearities p 135 A87-16179 S [ AD-A171 3701 p 123 N87-12622 Maximum likelihood estimation of parameters in UNITED KINGDOM nonlinear flight mechanics systems p 113 A87-16192 SWEDEN Micrmlectronics in aircraft systems INTERNATIONALORGANIZATION Vortex-sheet capturing in numerical solutions of the p 101 A87-13469 Mobile communications, navigation and surveillance incompressible Euler equations p 70 A87-14099 The active minimization of harmonic enclosed sound r IAF PAPER 86-3331 D 86 A87-16027 Lower-side normal force charactenstics of delta wings fields p 138 A87-13593 ISRAEL at supersonic speeds p 72 A87-14372 Fibre reinforced composites 1986; Proceedings of the Extensions of a simplified continuous-timemultivariable SWITZERLAND Second International Conference. University of Liverpool. adaptive control algonthm p 134 A87-13399 Performance evaluation of an inverse integral equation England, April 8-10, 1986 p 121 A87-13613 Israel Annual Conference on Aviation and Astronautics. method applied to turbomachine cascades Mechanized manufacture of composite main rotor blade 27th, Haifa. Israel. February 27, 28 1985. Collection of p 72 A87-14771 spars p 124 A87-13625 Papers p64 A87-13835 Airworthiness of composite structures - Some Parametric sizing of aerial application airplanes based experiences from civil certification p 78 A87-13627 on varying levels of technology p 139 A87 13636 T The development of balance tubes for Do* Rotol The equivalent masses at nose landing-gears during TAIWAN composite bladed propellers p 63 A87-13630 landing-impacts and when taxiing over runway Aermlastic divergence of trimmed aircraft perturbations p 88 A87 13637 Variable structure control of a turbojet engine p 103 A87-13343 p 94 A87-14368 An analytical parametric investigation of numerical Now hear this p 80 A87-14620 nonlinear vortex-lattice methods p 67 A87-13638 An aerodynamic analysis and the subsequent motion of external store p 66 A87-13501 Zoning of aircraft for lightning attachment and current Combination of suction and tangential blowing in Computation of two-dimensional supersonic turbulent transfer p 94 A87-15009 boundary layer control p67 A87 13641 flow over a compression corner p 88 A87-13502 Simulated lightning current tests on a Lynx helicopter The effect of material compressibility (Poisson ratio) on Numencal calculation of three-dimensional inviscid p 95 A87-15011 Prediction of skin currents flowing on a Lynx helicopter the elasto-plastic solution to the problem of a cylinder under supersonic flows p 66 A87-13504 internal pressure (coldworking situation) Companson of numerical solutions of lower order and due to a simulated lightning strike p 95 A87-15012 p 124 A87-13642 higher order integralequation methods for two-dimensional Corona from simulated aircraft surfaces and their A split canard configuraion for improved control at high aerofoils contribution lo the tnggered discharge angles of attack p67 A87 13643 [AIM PAPER 86-25911 p 69 A87-14028 p 82 A87-15024 On the improvement of an expendable turbojet engine TURKEY Lightning return stroke current computation flight envelope p 104 A87-13647 Performance prediction for fully-deployed parachute p 126 A87-15029 For small airliners and executive jets Aerodynamic coefficients of a circular wing in steady canopies p 105 A87-15179 subsonic flow p 67 A87-13653 [AIM PAPER 86-24751 p 79 A87-t 3809 Advanced flight control actuation systems and their Combined guidance Flight control of atmospheric interface with digital commands vehicles p 110 A87-13654 U [SAE PAPER 8517541 p 112 A87-15479 Expenmental investigation of a solid fuel ramjet Some effects of moisture on adheswe-bonded combustor p 104 A87-13658 U.S.S.R. CFRP-CFRP joints p 129 A87-16160 Thermochemical evaluation of fuel candidates for ramjet Questions and problems in aerodynamics Identification and system parameter estimation 1985; propulsion p 121 A87-13659 p 66 A87-13050 Proceedings of the Seventh Symposium, University of Spray charactenstics of two combined let atomizers Integrated active control systems Methods of York. England, July 3-7, 1985. Volumes 1 8 2 p 124 A87 13660 algorithmic integration p 135 A87-14682 p 135 A87-16176 Improved measurement of the dynamic loads acting on Methods for the assembly and testing of the bearing Application of regression analysis to coupled responses rotating parachutes supports of gas turbine engines p 126 A87-14683 at high angles of atlack p 113 A87-16185 [AIM PAPER 86.24731 p 68 A87-13807 Automation of support processes for aircraft production Comparison of two techniques of I.F.D. based on a Combustion studies of metallized luels for solid fuel using computers and numerical control non-linear stochastic model of an aircraft ramlets p 121 A87-14982 p 64 A87-14687 p 114 A87-18196 Prospective. characteristics and problems of the use A study of the effect of surface roughness on the head A320 - Fly-by-wireairliner p 98 A87-16394 of boron in different air augmented propulsion modes resistance of an aircraft p94 A87-14717 Aerospace plane - Fact or fantasy? [IAF PAPER 86-191) p 122 A87-15924 The effect of lubricant cavitation on the characteristics p 65 A87-16396 of a short hydrodynamic damper p 127 A87-15203 The inspectable structure p 65 A87-16397 Determination of the thrust and net efficiency of a US air transport technology - Where next? J propeller and flow parameters behind the propeller p 65 A87-16398 p 105 A87-15204 V-22 Osprey Multi-serviceworkhorse Mathematical modeling of the motion of a statically - JAPAN p 96 A87-16400 deformed deltashaped glider p 95 A87-15205 Full scale crash test of a BK117 helicopter Start-up of a wind tunnel with a multichannel diffuser A review of the technical development of Concorde p 91 A87-13678 p 72 A87-15206 p 96 A87-16408 An implicit time-marching scheme lor transonic flow The effect Of turbine elements on the gasdynamic Pitot and static errors in steady level flight p 71 A87-14261 stability margin p 105 A87-15208 [ESDU-86006] p 74 N87-11691 Study of a bounded jet flow considering the initial Using vibration spectrum characteristicsfor the flow-path Control of gas turbines. The future: Is a radical approach turbulence II .In the case of relatively large nozzle aspect diagnostics of aircraft gas turbine engines needed? ratio p 71 A87-14263 p 105 A87-15210 [PNR-90295] p 107 N87-11793 Noise and performance of a counter-rotation propeller Turbines with counter-rotatingrotors for aircraft power Vertical deflection characteristics of aircraft tyres p 105 A87-14366 plants p 106 A87-15211 [ ESDU-860051 p 129 N87-11992

D-2 FOREIGN TECHNOLOGY INDEX UNITED KINGDOM

Introduction to aerodynamics derivitNeS, equations of motion and stability [ESDU-86021I p 76 N87-12536 Propellarlbody interaction for thrust and drag [ESDU-860171 p 76 N87-12537 An approximate method of estimating the aerodynamic interference betwaen two parallel bodies in a supersonic flow (axial force) [ BR-lOO27II p 76 N87-12540 Simplified forms of performance equations. Addendum A Effect on aeroplane level speed of small changes in thrust, drag, weight, power [ ESDU-86004-ADDAI p 100 N87-12556 Visualisatin of axial turbine tip clearance flow using a linear cascade [CUED/A-TURBO/TR-122] p 107 N87-12560 Frictional and retarding forces on aircraft lyres. Part 4: Estimation of effects of yaw [ESDUdM)16-PT-4] p 131 N87-12868

D-3 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 277) March 1987

vplcal Contract Number Index Listing F33615-83-C-2435 ...... p130 N87-12766 505-66-11 ...... p137 N87-12273 F33615-84-C-5051 ...... p108 N87-12563 505-68-11 ...... p116 N87-11797 NAGW-674 ...... p77 N87-12542 p101 N87-12559 NAG1-186 ...... p69 A87-14095 505-83-11 ...... p131 N87-12915 NAG1472 ...... p22 N87-10854 NAG1-28 ...... p81 A87-15005 506-46-21-01 ...... p116 N87-12566 NAG1-345 ...... p64 A87-14034 535-03-01 ...... p130 N87-12017 NAG1-379 ...... p138 A87-15458 p139 N87-13252 NAG1-390 ...... p88 A87-13596 535-05-01 ...... D107 N87-11789 p94 A87-14925 T NAG1-40 ...... p70 A87-14108 NAG1-463 ...... p132 N87-12082 NAG1-493 ...... NAG1-638 ...... NAGP-152 ...... p75 N87-11700 NAG2-209 ...... p94 A87-14103 NAG2-226 ...... p 115 N87-11752 NAG2-297 ...... p103 A87-13418 Listings in this index are arranged alpha- p 110 A87-13419 numerically by contract number. Under each NAG3-28 ...... p 75 N87-11701 contract number. the accession numbers denoting NAG3447 ...... p106 N87-11732 NAG3-357 ...... p137 A87-13587 documents that have been produced as a result of NAG3-388 ...... p 106 N87-11769 research done under that contract are arranged in NAG3-396 ...... p131 N87-12915 ascending order with the AlAA accession numbers NAS1-16394 ...... p70 A87-14096 appearing first . The accession number denotes the NAS1-16441 ...... p138 N87-12322 NAS1-17:30 ...... p70 A87-14096 number by which the citation is identified in the ...... p138 N87-12323 abstract section. Preceding the accession number NAS1-17533 ...... p115 N87-11795 is the page number on which the citation may be NAS1-17635 ...... p88 A87-13361 found . NASl-17993 ...... p 69 A87-14035 NAS1-18004 ...... NAS1-18028 ...... p87 N87-12552 AF PROJECT 84-1OA-71 ...... p 91 A87-13821 NAS2-10184 ...... p73 A87-15461 AF-AFOSR-ISSA-85-00051 ...... p 134 A87-13319 NAS2-9646 ...... p73 A87-15461 AF-AFOSR-81-0213A ...... p 73 A87-15453 NAS2-9830 ...... p125 A87-13872 AF-AFOSR-82-0185 ...... p 118 A87-15463 NAS3-22513 ...... p107 N87-11789 NAS3-23931 ...... p106 N87-11788 AF-AFOSR-83-0083 ...... p 82 A87-15024 ...... NAS3-24091 ...... p 121 A87-14986 AF-AFOSR-84-0293 ...... p 135 A87-13689 NAS3-24533 ...... p105 A87-14123 BMFT-LFF-8350 ...... p 121 A87-13985 NAS3-24547 ...... p 116 N87-11797 BMFT-LFK-8350 ...... p 121 A87-14001 NAS7-918 ...... p98 N87-11739 BMFT-LFK-8351-4 ...... p 126 A87-13999 NBS-NE-81-NADA-2000 ...... p78 A87-13187 BMFT-LFK-8360 ...... p 92 A87-14002 NCA2-IR-850-401 ...... p70 A87-14117 BMFT-LFK-8531 ...... p 92 A87-13993 NCC1-58 ...... p66 A87-13499 BMFT-LFK-85508 ...... p 92 A87-13997 ...... p134 A87-13319 BMFT-LFL-8360-7 ...... p 110 A87-13991 ...... P125 A87-13872 BMFT-LFL-8571-0 ...... p 92 A87-14014 NSF MEA-78-22127 ...... p138 A87-15458 BMFT-LVS-8305 p 125 A87-13986 ...... NSG-1578 ...... p115 N87-11752 BMVG-T/R41/W007/D1407 ...... p 71 A87-14125 N00014-79-C-0010 ...... p118 A87-15463 DA PROJ. 1L1-612209-AH-76 ...... p 107 N87-11789 NOO014-79-GO130 ...... p73 A87-15461 DA PROJ. 1L1-62209-AH-76 ...... p 107 N87-11790 N00014-80-C-0324 ...... p66 A87-13499 DAAG29-79-C-0168 ...... p 126 A87-14423 N00014-81-K-0379 ...... p69 A87-14095 DAAG29-81-GO032 ...... p 77 N87-12545 N00014-83-K-0239 ...... p71 A87-14362 DAAG29-82-K-0094 ...... p 124 A87-13680 NOO019-80-G-0607 ...... p108 N87-12562 p 124 A87-13682 N00167-81-C-0078-P00004 ...... p71 A87-14365 p 124 A87-13683 N00167-85-C-0077 ...... DAAG29-82-K-0143 ...... p 123 N87-12685 N60530-85-WR-30011 ...... DAAG29-84-K-0048 p 116 N87-12568 ...... N61339-81-C-0105 ...... p 130 N87-12729 N61339-82-D-0006 ...... p102 N87-11783 DAAG29-85-COO02 p 75 N87-11699 ...... N61339-85-C-0044 ...... p77 N87-12544 N62269-76C-0086 ...... DAAG46-82-C-0066 ...... p 122 N87-11877 N62269-80-C-0261 ...... DE-AC04-76DP-00789 ...... p 66 A87-13795 N62269-81-C-0717 ...... p73 A87-15461 p 120 N87-12577 PROJ. E16668 ...... p74 N87-11695 DE-FC22-83FE-60149 ...... p 122 N87-11908 RF PROJ . 712620/762009 ...... p75 N87-11701 DEN3-168 ...... p 130 N87-11995 STPA-83,95,009 ...... p113 A87-16186 DOT-FA01-84-2-02021 ...... p 80 A87-14861 505-33-53-12 ...... p99 N87-11750 DOT-FA72WAI-261 ...... p 87 N87-11715 505-33-53 ...... p138 N87-12323 DTFA01-83-C-30076 ...... p 129 N87-11910 505-34-01 ...... p 116 N87-11796 DTFA01-83-Y-30606 ...... p 118 N87-11799 505-42-11 ...... p131 N87-12869 DTFA03-81-C-00040 ...... p 83 N87-11708 505-42-32 ...... p106 N87-11788 DTFA03-84-C-00086 ...... p 83 N87-11707 505-42-51 ...... p 100 N87-12557 DTFA3-80-A-00215 ...... p 122 N87-11902 505-43-01 ...... p100 N87-12558 FMV-AU-2154 ...... p 72 A87-14372 505-45-35-56 ...... p87 N87-12552 F19628-83-C-0143 ...... p 117 N87-12571 505-60 ...... p75 N87-11699 F19628-85-C-0002 ...... p 87 N87-11715 505-61-01-02 ...... p118 N87-11801 F22615-84-C-2411 ...... p 131 N87-12816 505-61-51 ...... p76 N87-12539 F29601-84-K-0045 ...... p 131 N87-12830 F33615-80-C5106 ...... p 125 A87-13719 505-61-71-03 ...... F33615-81-C-2011 ...... p 135 A87-14957 ...... p132 N87-12939 505-62-81-07 ...... p76 N87-12538 F33615-82-C-3406 ...... p 126 A87-15007 50563-1 1 ...... p 129 N87-11993 p 82 A87-15021 p 131 N87-12924 D 82 A87-15022 505-65-01 ...... p118 N87-11800

E- 1 REPORT NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 277) March 1987

-pica1 Report Number Index Listing

AFGL-TR-860036 ...... p 117 N87-12571 # DOT/FAA/PM-86/19 ...... p 87 N87-11715 # DOT/FAA/PM-86/30 ...... p 133 N87-13099 # AFIT/CI/NR-8684T ...... p 66 N87-12534 # DOT/FAA/PM-86/39 ...... p 129 N87-11910 # NUMBER AFIT/CI/NR-86-98T ...... p 133 N87-13110 # E-3181 ...... p 131 N87-12924 * # AFWAL-TR-85-2087 ...... p 122 N87-11904 # E-3247 ...... p 130 N87-12017 * # AFWAL-TR-85.2104 .... p 130 N87-12766 # E-3275 ...... p 139 N87-13252 * # A-m ...... p 15 N87-10841 * t AFWAL-TR-85-4154 ...... p 108 N87-12563 # E-3286 ...... p 107 N87-11790 * # T AFWAL-TR-86-2004-VOL-1 ...... p 131 N87-12816 # I E-3288 ...... p 129 N87-11993 * # AFWAL-TR-863028 ...... p 132 N87-12939 # E-3298 ...... p 101 N87-12559 * # AWL-TN-85-52 ...... p 116 N87-12569 # EDR-12344 ...... p 130 N87-11995 * # AlAA PAPER 86-2423 ...... p 79 A87-13777 # ESA-TT-941 ...... p 83 N87-11709 # AlAA PAPER 862434 ...... p 79 A87-13784 # ESA-TT-957 ...... p 138 N87-12326 # AlAA PAPER 86-2437 ...... p 91 A87-13821 # LMings in this index are arranged alpha- ...... p 67 A87-13788 # p 100 N87-12556 # numericslly by report number. The page number ...... p80 A87-13818 # ESDU-86004-ADD-A ...... ESDU-86005 ...... p129 N87-11992 # AlAA PAPER 86-2449 ...... p 80 A87-13823 # indicates the page on which the citation is located. p 74 N87-11691 # AlAA PAPER 86.2452 ...... p 79 A87-13794 # ESDU-86006 ...... The auxssion number denotes the number by ESDU-86016PT-4 ...... p 131 N87-12868 # AlAA PAPER 862455 ...... p 68 A87-13795 # ESDU-86017 ...... which the citation is identified. An asterisk (*) AlAA PAPER 86-2456 ...... p 68 A87-13796 # ESDU-86021 ...... p 76 N87-12536 # indicates that the item is a NASA report. A pound AlAA PAPER 86-2458 ...... p 68 A87-13798 # sign (#) indicates that the item is available on ETN-8698014 ...... p 107 N87-11793 # microfiche. ETN-86-98187 ...... p 102 N87-11784 # AlAA PAPER 86.2473 ...... p 68 A87-13807 # ETN-86-98222 ...... p 75 N87-11704 # AlAA PAPER 86.2475 ...... p 79 A87-13809 # ETN-86-98240 p 83 N87-11709 # AlAA PAPER 86-2488 ...... p 80 A87-13815 # ...... ETN-86-98244 ...... p 138 N87-12326 # A-2-86092 ...... p 116 N87-11796 * # AlAA PAPER 86-2591 ...... p 69 A87-14028 # ETN-8698405 ...... p 139 N87-12327 # A-85059 ...... p 131 N87-12869 * # AlAA PAPER 86.2595 ...... p 101 A87-14030 # ETN-86-98494 p 65 N87-11688 # AlAA PAPER 86.2596 ...... p 111 A87-14031 * # ...... A-85361 ...... p 100 N87-12558 * # ETN-86-98495 _._.. ._._.p 102 N87-11785 # AlAA PAPER 86-2597 ...... p 111 A87-14032 * # A-85363 ...... ETN-86-98496 ...... p 103 N87-11786 # AlAA PAPER 86-2599 ...... p 93 A87-14033 # A-86198 ...... p 100 N87-11781 * # ETN-8698497 ...... p 100 N87-11782 # AlAA PAPER 86-2600 ...... p 64 A87-14034 * # A46234 p 76 N87-12539 * # ETN-86-98500 ...... p 119 N87-11805 # ...... AlAA PAPER 86-2M)Z ...... p 69 A87-14035 * # A-86249 ...... p 118 N87-11800 ' # AlAA PAPER 862606 ...... p 94 A87-14036 ' # FAA-MS-85-5 ...... p 65 N87-11686 # A-86273 ...... p 131 N87-12830 ' # AlAA PAPER 86-2607 ...... p 139 A87-14037 # A-86415 p 75 N87-11699 * ...... # AlAA PAPER 86-2608 ...... p 69 A87-14038 * # FAA/PM-86/47 ...... p 118 N87-11798 # FAA/PM-86/9 ...... p 118 N87-11799 # AD-A167976 ...... AMI-8605 ...... p77 N87-12545 # AD-A168217 ...... p FTD-ID(RS)T-0257-86 ...... p 119 N87-11803 # AD-A168327 ...... 122 N87-11877 # AMMRC-TR-85-25 ...... p 122 N87-11877 # AD-A168448 ...... p119 N87-11803 # FTD-ID(RS)T-0267-86 ...... p 65 N87-12533 # FTD-ID(RS)T-0312-86 ...... p 139 N87-13347 # ADA168573 ...... p 122 N87-11904 # p 77 N87-12545 # ARO-18391.3-EG-S ...... FTD-ID(RS)T-0761-86 ...... N87-12622 # AD-A168582 ...... p 65 N87-11686 # ARO-19251.XH ...... p 123 N87-12685 # AD-A168802 p 107 N87-11792 # ...... ARO-20155.6-MA ...... p130 N87-12729 # AD-A168829 p 102 N87-11783 # GARTEUR/TP-008 ...... p 100 N87-11782 # ...... P116 N87-12568 # AD-A168842 ...... p 65 N87-11687 # ARO-21731.1-EG ...... p 77 N87-12544 # AD-A169019 ...... p 116 N87-12568 # H-1367 ...... p 137 N87-12273 '# AD-A169066 ...... p 130 N87-12729 # ATC-42-REV-D ...... p 87 N87-11715 # AD-A169084 ...... p 116 N87-12569 # HTL-42 ...... p 75 N87-11700 '# AD-A169116 ...... p 77 N87-12544 # AVSCOM-TM-86-A-1 ...... p 100 N87-11781 * # AD-A169243 ...... p 123 N87-12685 # IAF PAPER 86-181 ...... p 120 A87-15920 # IAF PAPER 86191 ...... p 122 A87-15924 # AD-A169254 ...... p 77 N87-12545 # BR-100271 ...... p76 N87-12540 # AD-A169389 ...... p 133 N87-13105 # IAF PAPER 86-333 ...... p 86 A87-16027 # AD-A169411 ...... p 130 N87-12766 # BRL-MR-3519 ...... p 116 N87-12570 # AD-A169415 ...... p 116 N87-12570 # ICOMP-86-1 ...... p 131 N87-12924 '# ADA169423 p 117 N87-12571 ...... # 68667019 ...... INPE-3979-TDL1233 ...... p 137 N87-13179 # AD-A169452 ...... p139 N87-13347 # 68667272 ...... ADA169483 ...... p 108 N87-12562 # 68667703 ...... AD-A169514 p 119 N87-12572 ISBN-0-85679-5569 ...... p 100 N87-12556 # ...... # 88667704 ...... p 103 N87-11786 # AD-A169570 ...... p 108 N87-12563 # ISBN-0-85679-557-7 ...... p 129 N87-11992 # ISBN-0-85679-558-5 ...... p 74 N87-11691 # AD-A169575 ...... p 139 N87-13352 # CFD-16 ...... p 75 N87-11700 ' # AD-Al69864 ...... p 130 N87-12711 # ISBN-0-85679-568-2 ...... p 131 N87-12868 # p 76 N87-12537 # AD-A169925 ...... p 65 N87-12533 # CONF-860882-2 ...... p 120 N87-12577 # ISBN-0-85679-569-0 ...... AD-A169962 ...... p 119 N87-12573 # ISBN-0-85679-573-9 ...... p 76 N87-12536 # AD-A170458 ...... p 133 N87-13110 # CUED/A-TURBO/TR-122 ...... p 107 N87-12560 # AD-A170832 ...... p 66 N87-12534 # ISL-NB-401/84 ...... p 139 N87-12327 # AD-A171209 ...... p 132 N87-12939 # ...... p120 N87-12577 # ISSN-0082-5263 ...... p 119 N87-11802 # AD-A171370 ...... p 123 N87-12622 # ...... p122 N87-11908 # AD-A171418 ...... p 108 N87-12565 # ISSN-0141-397X ...... p 76 N87-12536 # ISSN-0141-397X ...... p 76 N87-12537 # AD-A171434 ...... p 131 N87-12816 # DFVLR-FB-85-16 ...... p 83 N87-11709 # ISSN-0141-4054 p 74 N87-11691 # p 138 N87-12326 # ...... DFVLR-FB-85-32 ...... p129 N87-11992 # AD-DO12279 ...... p 77 N87-12543 # DFVLR-FB-86-21 ...... p 102 N87-11784 # AD-DO12370 ...... p130 N87-12768 # ...... p100 N87-12556 # ISSN-0141-4054 ...... p 131 N87-12868 # AD-W12386 ...... p 87 N87-11716 # DOE/NASA/0168-10 ...... p 130 N87-11995 * # AD-DO12390 ...... p108 N87-12561 # ISSN-0169-1708 ...... p 119 N87-11805 # ISSN-0171-1342 ...... p 102 N87-11784 # AD-DO12405 ...... p 108 N87-12564 # DOT-TSC-FAA-85-3 ...... p 65 N87-11686 # AD-DO12407 ...... p131 N87-12881 # ISSN-0309-6521 ...... p 107 N87-12560 # lSSN-04361199 ...... p 75 N87-11704 # AD-F250645 ...... p 123 N87-12622 # DOT/FAA/CT-85/21 ...... p 83 N87-11707 # DOT/FAA/CT-85/31 ...... p 122 N87-11902 # ISU-ERI-AMES-87055 ... p 75 N87-11700 * # ...... p85 N87-12551 # ...... p 108 N87-12565 # KNMI-TR-85(FM) ...... p 119 N87-11805 #

F- 1 KSR-86-01 REPORT NUMBER INDEX

KSR-86-01 ...... p 116 N87-11797 * # NASA-TM-88268 ...... P 137 N87-12273 * # USAAVSCOM-TR-86-C-37 ...... p 107 N87-11790 * # NASA-TM-88312 ...... p 131 N87-12830 * # L-15830 ...... p 99 N87-11750 * # NASA-TM-88334 ...... p 75 N87-11699 * # USAFETAC/DS-86/024 ...... p 133 N87-13105 # L-16120 ...... p 75 N87-11702 ' # NASA-TM-88838 ...... p 131 N87-12924 * # L-16135 ...... p 77 N87-12541 * # NASA-TM-88854 ...... p 130 N87-12017 * # UTIAS-TN-261 ...... p 119 N87-11802 # L-16178 ...... p 118 N87-11801 * # NASA-TM-88869 ...... p 139 N87-13252 * # NASA-TM-88879 ...... p 107 N87-11790 * # UVA1528213/CS87/109 ...... p 137 N87-12265 * # LR-30727 ...... p 138 N87-12322 * # NASA-TM-88881 ...... p 129 N87-11993 * # NASA-TM-88888 ...... p 101 N87-12559 ' # ...... p130 N87-12729 # NASA-TM-89050 ...... p 76 N87-12538 * # ...... p116 N87-12568 # NASA-TP-2624 ...... p 77 N87-12541 * # MBB-UT-004-86 ...... p 92 A87-14002 # NASA-TP-2628 ...... p 75 N87-11702 * # MBB-UT-005-86 ...... p 126 A87-13999 # MBB-UT-006-86 ...... p 93 A87-14026 # NAVTRASYSCEN-81-C-0105.13.. p 119 N87-12572 # MBB-UT-222-86 ...... p 110 A87-13991 # NAVTRASYSCEN-85-C-0044-2 .... p 119 N87-12573 # MBB-UT-223-86 ...... p 121 A87-14001 # MBB-UT-224-86 ...... p 92 A87-13997 # NIPER-144-PPS-BWZ ...... p 122 N87-11908 # MBB-UT-225-86 ...... p 125 A87-13986 # MBB-UT-226-86 ...... p 121 A87-13985 # NLR-MP-85062-U ...... p 65 N87-11688 # NLR-MP-850664 ...... p 102 N87-11785 # MPIS-24/ 1985 ...... p 75 N87-11704 # NLR-MP-85074-U ...... p 103 N87-11786 #

MRL-R-984 ...... p107 N87-11792 # NLR-TR-84005-U ...... p 100 N87-11782 #

NA-85-0134 ...... p 130 N87-12711 # NOR-84-158 ...... p 115 N87-11795 * #

NADC-79024-60 ...... p 130 N87-12711 # NTSB-AAR-86-02-SUM ...... p 84 N87-12549 # NTSB-AAR-86-06 ...... p 84 N87-12550 # NAS 1.15:86664 ...... p 131 N87-12869 # NAS 1.I 5:86785 ...... p 100 N87-12558 * # NTSB/AAB-86/17 ...... p 84 N87-11713 # NAS 1.15:86789 ...... p 100 N87-12557 * # NTSB/AAB-86/18 ...... p 84 N87-11712 # NAS 1.15:87731 ...... p 116 N87-12566 * # NTSB/AAB-86/19 ...... p 83 N87-11710 # 87764 ...... p 118 N87-11801 * # 88209 ...... p 116 N87-11796 * # NTSB/ARG-86/01 ...... p 84 N87-11714 # 88238 ...... p 100 N87-11781 * # 88250 ...... p 76 N87-12539 * # NTSB/SIR-86/01 ...... p 84 N87-11711 # 88252 ...... p 118 N87-11800 * # NAS 1.15:88268 ...... p 137 N87-12273 * # ...... p84 N87-11714 # NAS 1.15:88312 ...... p 131 N87-12830 * # PB86-910407 ...... p 84 N87-12549 # NAS 1.15:88334 ...... p 75 N87-11699 * # PB86-910408 ...... p 84 N87-12550 # NAS 1.15:88838 ...... p 131 N87-12924 * # PB86-916917 ...... p84 N87-11713 # NAS 1.15:88854 ...... p 130 N87-12017 * # PB86-916918 ...... p84 N87-11712 # NAS 1.15:88869 ...... p 139 N87-13252 * # PB86-916919 ...... p 83 N87-11710 # NAS 1.15:88881 ...... p 129 N87-11993 * # PB86-917003 ...... p 84 N87-1 171 1 # NAS 1.15:88888 ...... p 101 N87-12559 * # NAS 1.15:89050 ...... p 76 N87-12538 * # PNR-90295 ...... p107 N87-11793 # NAS 1.26:172391 ...... p 138 N87-12322 * # NAS 1.26:172439 ...... p 115 N87-11795 * # RAE-TRANS-2131 ...... p 76 N87-12540 # NAS 1.26:172490 ...... p 138 N87-12323 * # NAS 1.26:174932 ...... p 106 N87-11788 * # REPT-3038-01-1-3985 ...... p 83 N87-11707 # NAS 1.26:178182 ...... p 87 N87-12552 * # REPT-6340A ...... p 123 N87-12685 # NAS 1.26:179484 ...... p 130 N87-11995 * # REPT-82-C-66 ...... p 122 N87-11677 # NAS 1.26:179503 ...... p 107 N87-11789 * # REPT-8720-3173U ...... p 108 N87-12562 # NAS 1.26:179515 ...... p 116 N87-11797 * # NAS 1.26:179518 ...... p 131 N87-12915 * # RR-10-86 ...... p 77 N87-12542 * # NAS 1.26:179801 ...... p 132 N87-12082 * # NAS 1.26:179842 ...... p 137 N87-12265 * # SAEP-170 ...... p112 A87-15476 # NAS 1.26:179880 ...... p 74 N87-11695 * # NAS 1.26:179897 ...... p75 N87-11701 * # SAE PAPER 851752 ...... p 112 A87-15477 # NAS 1.26:179900 ...... p 75 N87-11700 * # SAE PAPER 851753 ...... p 112 A87-15478 # NAS 1.26179937 ...... p 77 N87-12542 * # SAE PAPER 851754 ...... p 112 A87-15479 # NAS 1.26:88879 ...... p 107 N87-11790 * # SAE PAPER 851755 ...... p 112 A87-15480 # NAS 1.55:2327-PT-l ...... p 96 N87-11717 * # SAE PAPER 851757 ...... p 112 A87-15481 # NAS 1.55:2327-PT-2 ...... p 99 N87-11750 * # SAE PAPER 851759 ...... p 129 A87-15482 # NAS 1.60:2624 ...... p 77 N87-12541 * # NAS 1.60:2628 ...... p 75 N87-11702 * # SAND-86-2061C ...... p 120 N87-12577 #

NASA-CP-2327-PT-1 ...... p 96 N87-11717 * # SDSMT/lAS/R-86/07 ...... p 132 N87-12082 * # NASA-CP-2327-PT-2 ...... p 99 N87-11750 * # SR-2 ...... p 117 N87-12571 # NASA-CR-172391 ...... p 138 N87-12322 * # NASA-CR-172439 ...... p 115 N87-11795 * # SR86-R-4938-39 ...... p 107 N87-11789 * # NASA-CR-172490 ...... p 138 N87-12323 * # NASA-CR-174932 ...... p 106 N87-11788 * # TR-85433 ...... p83 N87-11708 # NASA-CR-178182 ...... p 87 N87-12552 * # TR-86-06 ...... p 102 N87-11783 # NASA-CR-179484 ...... p 130 N87-11995 * # NASA-CR-179503 ...... p 107 N87-11789 * # UDR-TR-85-132 ...... p 108 N87-12563 # NASA-CR-179515 ...... p 116 N87-11797 # UDR-TR-85-82-VOL-1 ...... p 131 N87-12816 # NASA-CR-179518 ...... p 131 N87-12915 # NASA-CR-179801 ...... p 132 N87-12082 * # US-PATENT-APPL-SN-566351 ..... p 87 N87-11716 # NASA-CR-179842 ...... p 137 N87.12265 * # US-PATENT-APPL-SN-611041 ..... p 108 N87-12561 # NASA-CR-179880 ...... p 74 N87-11695 * # US-PATENT-APPL-SN-753462 ..... p 77 N87-12543 # NASA-CR-179897 ...... p 75 N87-11701 * # US-PATENT-APPL-SN-855047 ..... p 130 N87-12768 # NASA-CR-179900 ...... p 75 N87-11700 * # US-PATENT-APPL-SN-861905 .... p 131 N87-12881 # NASA-CR-179937 ...... p 77 N87-12542 * # US-PATENT-APPL-SN-861909 ..... p 108 N87-12564 #

NASA-TM-86664 ...... p 131 N87-12869 * # US-PATENT-CLASS-239-265.29.. p 108 N87-12561 # NASA-TM-86785 ...... p 100 N87-12558 * # US-PATENT-CLASS-340-825.69 . p 87 N87-11716 # NASA-TM-86789 ...... p 100 N87-12557 * # US-PATENT-CLASS-60.39.31 ..... p 77 N87-12543 # NASA-TM-87731 ...... p 116 N87-12566 * # NASA-TM-87764 ...... p 1I8 N87-11801 * # US-PATENT-4.571.936 ...... p 77 N87-12543 # NASA-TM-88209 ...... p 116 N87-11796 * # US-PATENT-4.590.471 ...... p 87 N87-11716 # NASA-TM-88238 ...... p 100 N87-11781 * # US-PATENT-4.591.097 ...... p 108 N87-12561 # NASA-TM-88250 ...... p 76 N87-12539 * # NASA-TM-88252 ...... p 118 N87-11800 * # USAAVSCOM-TM-86-A-4 ...... p 75 N87-11699 * #

F-2 ACCESSION NUMBER INDEX

March 1987 AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 277)

Typical Accession Number Index Listing

A87-13684 # p 78 A87-14101 # p70 A87-15189 # p72 A87-15193 # PI27 A87-10524 '# P 4 A87-13685 # p 78 A87-14102 # p70 A87-15203 # P 127 A87-13686 # p78 A87-14103 * # p 94 A87-15204 # PI05 A87-13687 # p79 A87-14104 * # p 70 A87-13889 # p 135 A87-15205 # p95 A87-14105 '# P 70 A87-15206 # p72 A87-13703 '# p 135 A87714108 '# P 70 A87-13719 # p125 A87-15208 # P 105 A87-14109 '# P 70 A87-15210 # P 105 A87-13776 # p79 A87-14110 '# p70 A87-15211 # P 106 A87-13777 # p79 NUMBER SPONSORED MICROFICHE NUMBER A87-14111 '# P70 A87-15212 # P 112 A87-13784 # p79 Fl Fl Fl A87-14117 '# P70 A87-15214 # p96 A87-13788 # p67 A87-14119 # p71 A87-15215 # p127 A87-13794 # p79 A87-14123 '# p 105 A87-13795 # p68 A87-15216 # p72 A87-14125 # p71 A87-15218 # p127 A87-13796 # p88 A87-14127 # p71 A87-13798 # p88 A87-15220 # p 96 A87-14129 # p71 A87-15223 # p 72 A87-13805 # p68 A87-14135 # PI11 A87-15226 # PI27 Listings In this index are arranged alphanumerically A87-13806 # P 79 A87-14136 # PI11 A87-15229 # p 73 by accession number. The page number listed to A87-13807 # p 68 A87-14139 # P 105 A87-15403 # PI27 A87-13809 # P 79 the right indicates the page on which the citation A87-14140 # p86 A87-15412 # PI27 A87-13815 # p80 A87-14142 # plll is located. An asterisk (*) indicates that the item is A87-13818 # p80 A87-15414 # p64 A87-14261 # p71 A87-15415 # PI02 a NASA report. A pound sign (X) indicates that the A87-13821 # p91 A87-14263 # P71 A87-15417 # PI28 item is available on microfiche. A87-13823 # p80 A87-14352 '# P 102 A87-15418 # p64 A87-13828 # p 125 A87-14360 # P 71 A87-13830 # PI25 A87-15419 # p 64 A87-14362 # P71 A87-15423 # P 128 A87-13848 *# p 125 A87-14363 '# P 71 A87-13872 '# p 125 A87-15424 # p 96 A87-14364 '# P 105 A87-15425 # P 128 A87-13900 # p68 A87-14365 # P71 A87-15427 # p 86 A87-13050 # P 66 A87-13533 # p85 A87-13911 # p64 A87-14386 # P 105 A87-13912 # p101 A87-15428 # p 128 A87-13062 # P63 A87-13536 # PI10 A87-14387 # P 111 A87-13985 # p 121 A87-15430 # PI02 A87-13063 # P 63 A87-13540 # p85 A87-14388 # P94 A87-15432 # p 128 A87-13986 # p 125 A87-13074 # PI23 A87-13543 # p86 A87-14369 '# P 94 A87-15433 # P 128 A87-13092 # p 120 A87-13987 # p 91 A87-13544 # p86 A87-14370 # P72 A87-15435 # P 128 A87-13093 # p120 A87-13988 # p 117 A87-13545 # PI01 A87-14371 '# P 80 A87-15436 # p 65 A87-13101 # p87 A87-13989 # P 104 A87-14372 # P 72 A87-13578 # P78 A87-13990 # p 104 A87-15451 '# p 73 A87-13105 # p63 A87-14423 # p 126 A87-15452 # p73 A87-13121 # p120 A87-13581 # P78 A87-13991 # pll0 A87-13584 # p 132 A87-14620 # P80 A87-15453 # p73 A87-13122 # PI17 A87-13992 # P91 A87-13585 # p 137 A87-14652 '# P 72 A87-15454 * # P 73 A87-13123 # p 123 A87-13993 # p92 A87-14682 # PI35 A87-13587 *# p 137 A87-15458 '# p 138 A87-13151 # p87 A87-13994 # p68 A87-I4683 # P 126 A87-13593 # p 138 A87-15459 # P 73 A87-13157 p63 A87-13995 # p69 A87-14687 # p 64 # A87-13595 # PI38 A87-15461 * # p 73 A87-13164 # PI23 A87-13997 # p 92 A87-14717 # P94 A87-13596 * # p 88 A87-13998 # p 104 A87-15462 # p 73 A87-13171 # PI21 A87-14771 # p72 A87-15463 # PI18 A87-13605 # P 138 A87-13999 # p 126 A87-13173 # p124 A87-14861 # P80 A87-15464 '# P 118 A87-13813 # PI21 A87-14000 # p104 A87-13186 # p78 A87-14925 * # P 94 A87-15465 # PI18 A87-13825 # P 124 A87-14001 # P 121 A87-13187 # p78 A87-14957 # P 135 A87-15487 * # p 74 A87-13627 # p 78 A87-14002 # P 92 A87-13200 # p 133 A87-14982 # PI21 A87-15468 # P 74 A87-13828 # p88 A87-14003 # P 92 A87-13301 # p 133 A87-14984 # PI05 A87-15469 p 74 A87-13630 # p63 A87-14004 # p86 '# A87-13318 '# p 103 A87-14986 '# P 121 A87-15476 # P 112 A87-13635 # P64 A87-14005 # p 101 A87-13319 # PI34 A87-15001 # P80 A87-15477 # p 112 A87-13636 # P 139 A87-14006 # P 126 A87-13323 # P 103 A87-15002 # P 132 A87-15478 # p 112 A87-13637 # p88 A87-14007 # p 117 A87-13326 # P134 A87-15003 *# p 80 A87-15479 # p 112 A87-13638 # p67 A87-14008 # p 92 A87-13341 '# P 108 A87-15004 * # p 81 A87-15480 # p 112 A87-13641 # p 67 A87-14009 # p 117 A87-13342 '# p 108 A87-15005 * # P 81 A87-15481 # p 112 A87-13642 # p124 A87-14010 # P69 A87-13343 # PI03 A87-15006 # P 126 A87-15482 # p 129 A87-13643 # p67 A87-14012 # P92 A87-13344 # p 109 A87-15007 # P 126 A87-15553 # A87-13646 # p88 A87-14013 # Plll P 74 A87-13346 # P 109 A87-15008 # P 81 A87-15561 # A87-13647 # P 104 A87-14014 # P92 P 74 A87-13347 '# P 109 A87-15009 # p 94 A87-I5563 # A87-13648 # PI10 A87-14015 # P64 P 88 A87-13352 # P 109 A87-15010 # PI05 A87-15569 # A87-13652 # p67 A87-14016 # P92 P 86 A87-13353 # P 134 A87-15011 # P95 A87-15582 # p 138 A87-13653 # p67 A87-14017 # P93 A87-13354 # P87 A87-15012 # P95 A87-15761 # A87-13654 # PllO A87-14018 # P93 P 74 A87-13355 # p 109 A87-15013 # p81 A87-15920 # p 120 A87-13658 # PI04 A87-14019 # PI35 A87-13359 # p 134 A87-15014 # P81 A87-15924 # p 122 A87-13659 # P 121 A87-14021 # P 111 A87-13360 * # p 88 A87-15015 # P81 A87-16027 A87-13660 # P 124 A87-14022 # p89 # P 88 A87-13361 * # p 88 A87-15016 # P81 A87-16160 p 129 A87-13682 # 089 A87-14023 # PI17 # A87-13362 * # p 85 A87-15017 # P82 A87-16176 p 135 A87-13663 # p89 A87-14024 # p 117 # A87-13365 # p 134 A87-15018 '# P95 A87-16179 # p 135 A87-13664 # p89 A87-14025 # p 93 A87-13379 # p 109 A87-15021 # P 82 A87-16182 P 113 A87-13665 # P 89 A87-14026 # p 93 # A87-13385 # p 134 A87-15022 # P82 A87-16183 # p 113 A87-13666 # p89 A87-14027 # P 93 A87-13399 # p 134 A87-15023 # PI26 A87-16184 # p113 A87-13667 # p89 A87-14028 # p 69 A87-13418 '# p 103 A87-15024 # p82 A87-18185 # PI13 A87-13668 # P90 A87-14030 # P 101 A87-13419 '# p 110 A87-15027 # p95 A87-16186 # p113 A87-13669 # p90 A87-14031 * # P 111 A87-13428 # PI10 A87-15028 # p102 A87-16189 # PI38 A87-13670 # p90 A87-14032 * # P 111 A87-13435 '# p 110 A87-15029 # p 126 A87-16192 # PI13 A87-13671 # p90 A87-14033 # p 93 A87-13436 # p 134 A87-15033 # P 82 A87-16193 # p 114 A87-13872 # p 90 A87-14034 * # p A87-13438 # p85 64 A87-15034 # P 82 A87-16195 # PI14 A87-13673 # p90 A87-14035 '# p 69 A87-13469 # p 101 A87-15037 # P95 A87-16196 # p114 A87-13674 # P90 A87-14036 * # p 94 A87-13499 * # p 66 A87-15038 # P 83 A87-18197 # PI14 A87-13675 # p91 A87-14037 # P 139 A87-13501 # p66 A87-15039 # P 127 A87-16202 # p114 A87-13678 # p91 A87-14038 '# p 69 A87-15179 # p105 A87-13502 # p66 A87-13679 # p91 A87-16209 # PI14 A87-14095 * # p 69 A87-15180 # p83 A87-13503 # p 66 A87-13680 # PI24 A87-16394 # p96 A87-14096 * # p 70 A87-15181 # p95 A87-13504 # P66 A87-13682 # PI24 A87-16396 # D65 A87-14099 # p 70 A87-15187 '# P 121 A87-13532 # p85 A87-13683 # PI24 G- 1 ACCESSION NUMBER INDEX A87-16397

A87-16397 # P65 N87-12273 '# P 137 N87-12322 '# P 138 A87-16398 # P65 N87-12323 '# P 138 A87-16400 # p96 N87-12326 # P 138 A87-16408 # P96 N87-12327 W P 139 N87-12533 # P65 N87-11686 # p65 N87-12534 # P66 N87-11687 # p65 N87-12535 # P76 N87-11688 # p65 N87-12536 # p 76 N87-11691 # p 74 N87-12537 # p 76 N87-11695 * # p 74 N87-12538 * # p 76 N87-11699 ' # p 75 N87-12539 * # p 76 N87-11700 '# P 75 N87-12540 # P76 N87-11701 * # P 75 N87-12541 '# p 77 N87-11702 * # p 75 N87-12542 * # P 77 N87-11704 # P 75 N87-12543 # P 77 N87-11706 # p 83 N87-12544 # p 77 N87-11707 # P83 N87-12545 # p77 N87-11708 # P83 N87-12547 # p 77 N87-11709 # P 83 N87-12549 # p64 N87-11710 # P83 N87-12550 # p84 N87-11711 # P 84 N87-12551 # P85 N87-11712 # P84 N87-12552 * # p 87 N87-11713 # P84 N87-12556 # PlOO N87-11714 # P84 N87-12557 '# p 100 N87-11715 # p87 N87-12558 ' W P 100 N87-11716 # P87 N87-12559 ' W P 101 N87-11717 '# p96 N87-12560 W PI07 N87-11719 '# P 98 N87-12561 # P 108 N87-11720 * # P 97 N87-12562 # P 108 N87-11721 * # p 97 N87-12563 W p 108 N87-11722 ' # p 97 N87-12564 W P 108 N87-11723 * # p 97 N87-12565 # P 108 N87-11725 * # p 97 N87-12566 '# P 116 N87-11726 * # p 98 N87-12568 # p 116 N87-11730 '# p 115 N87-12569 # p 116 N87-11731 '# p 106 N87-12570 # p116 N87-11732 '# p 106 N87-12571 # P 117 N87-11733 '# p 129 N87-12572 # p119 N87-11736 '# p 115 N87-12573 # p119 N87-11737 * # p 98 N87-12577 # p 120 N87-11738 * # p 75 N87-12622 # p 123 N87-11739 * W p 98 N87-12685 # P 123 N87-11740 '# p 136 N87-12711 # p 130 N87-11743 ' # p 98 N87-12716 # PlOl N87-11746 * # p 84 N87-12729 W p 130 N87-11747 * # p 98 N87-12766 # p 130 N87-11748 '# p 136 N87-12768 # p130 N87-11749 * # p 98 N87-12816 # p131 N87-11750 * # p 99 N87-12830 '# p 131 N87-11751 * # p 99 N87-12868 # p 131 N87-11752 '# p 115 N87-12869 '# p 131 N87-11753 * # p 99 N87-12881 # p 131 N87-11754 '# p 136 N87-12915 '# p 131 N87-11755 '# p 136 N87-12924 '# p 131 N87-11756 * # p 99 N87-12939 # p132 N87-11757 * # p 99 N87-13064 '# p 132 N87-11758 * # p 99 N87-13099 # p133 N87-11759 '# p 100 N87-13105 # PI33 N87-11768 * # p 106 N87-13110 # P133 N87-11769 * # p 106 N87-13149 # p132 N87-11774 '# p 115 N87-13179 # p137 N87-11775 '# p 136 N87-13252 '# p 139 N87-11781 '# p 100 N87-13347 # p139 N87-11782 # p 100 N87-13352 # p139 N87-11783 # p 102 N87-11784 # p 102 N87-11785 # p 102 N87-11786 W p103 N87-11787 W p 103 N87-11788 '# p 106 N87-11789 '# p 107 N87-11790 '# p 107 N87-11792 # p107 N87-11793 # p107 N87-11794 # p115 N87-11795 '# p 115 N87-11796 '# p 116 N87-11797 '# p 116 N87-11798 # pll8 N87-11799 # pll8 N87-11800 '# p 118 N87-11801 '# p 118 N87-11802 # pll9 N87-11803 # p119 N87-11805 # p119 N87-11877 # p 122 N87-11902 W p 122 N87-11904 W p 122 N87-11908 W p122 N87-11910 W p 129 N87-11992 # p129 N87-11993 '# p 129 N87-11995 'I p 130 N87-12017 '# p 130 N87-12082 '# p 132 N87-12265 '# p 137

6-2 AVAILABILITY OF CITED PUBLICATIONS

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NORTH PRICE AMERICAN FOREIGN CODE PRICE PRICE E01 $ 7.50 15.00 E02 10.00 20.00 E03 11.00 22.00 EO4 13.50 27.00 E05 15.50 31.00 EO6 18.00 36.00 E07 20.50 41.00 E08 23.00 46.00 EO9 25.50 51.00 El0 28.00 56.00 Ell 30.50 61.00 E12 33.00 66.00 E13 35.50 71.00 E14 38.50 77.00 E15 42.00 84.00 E16 46.00 92.00 E17 50.00 100.00 E18 54.00 108.00 E19 60.00 120.00 E20 70.00 140.00 E99

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IMPORTANT NOTICE NTlS Shipping and Handling Charges U.S., Canada, Mexico - ADD $3.00 per TOTAL ORDER All Other Countries - ADD $4.00 per TOTAL ORDER Exceptions - Does NOT apply to: ORDERS REQUESTING NTIS RUSH HANDLING ORDERS FOR SUBSCRIPTION OR STANDING 0RDE.R PRODUCTS ONLY NOTE: Each additional delivery address on an order requires a separate shipping and handling charge. 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037 (21 1) 4. Title and Subtitle 5. Report Date Aeronaut1 cal Engineering March, 1987 1) A Continuing Bibl iography (Supplement 21 6. Performing Organization Code

7. Authorb) 8. Performing Organization Report No.

10. Work Unit No. 9. Performing Organization Name and Address

National Aeronautics and Space Administration 11. Contract or Grant No. Washington, DC 20546

13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address

14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract This bibliography lists 519 reports, articles and other documents introduced into the NASA scientific and technical information system in February, 1987.

17. Key Words (Suggested by Author(s) ) 18. Distribution Statement Aem naut I ca 1 Engineering Aeronautics Bibl iographies

19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Rice' Unclassified Unclassified 144 AO7/HC

NASA-Langley, 1987