Aeronautical Engineering

NASA SP-7037(238)

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

(Supplement 238)

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 March 1989 in

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

National Aeronautics and Space Administration Office of Management NASA scientific and Technical Information Division Washington, DC 1989 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 458 reports, journal articles and other documents originally announced in March 1989 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 IAA 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) 141

Category 02 Aerodynamics 143 Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 155 Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation 157 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 161 Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 169 Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 175 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 178 Includes aircraft handling qualities; piloting; flight controls; and autopilots.

Category 09 Research and Support Facilities (Air) 182 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.

Category 10 Astronautics 184 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 185 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing.

V Category 12 Engineering 186 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 195 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; mankystem technology and life support; and space biology.

Category 15 Mathematical and Computer Sciences 197 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 203 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 204 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 204

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 TYPICAL REPORT CITATION AND ABSTRACT

NASASPONSORED 1[-.ON MICROFICHE

ACCESSION NUMBER- N89-10029'# North Carolina State Univ.. Raleigh. Dept. of -CORPORATE SOURCE Mechanical and Aerospace Engineering. TITLE- A TRANSONIC INTERACTIVE BOUNDARY-LAYER THEORY FOR LAMINAR AND TURBULENT FLOW OVER SWEPT WINGS Final Report AUTHORS- SHAWN H. WOODSON and FRED R. DEJARNETTE Washington Oct. 1988 82 p CONTRACT NUMBER- (Contract NCCl-22) PUBLICATION DATE REPORT NUMBERS- (NASA-CR-4185; NAS 1.26:4185) Avail: NTlS HC A05/MF A01 -PRICE CODE COSATI CODE -CSCL 01A \ AVAILABILITY SOURCE A 3-0 laminar and turbulent boundary-layer method is developed for compressible flow over swept wings. The governing equations and curvature terms are derived in detail for a nonorthogonal, curvilinear coordinate system. Reynolds shear-stress terms are modeled by the Cebeci-Smith eddy-viscosity formulation. The governing equations are descretized using the second-order accurate, predictor-corrector finite-differencetechnique of Matsuno. which has the advantage that the crossflow difference formulas are formed independent of the sign of the crossflow velocity component. The method is coupled with a full potential wing/body inviscid code (FLO-30) and the inviscid-viscous interaction is performed by updating the original wing surface with the viscous displacement surface calculated by the boundary-layer code. The number of these global iterations ranged from five to twelve depending on Mach number, sweep angle, and angle of attack. Several test cases are computed by this method and the results are compared with another inviscid-viscous interaction method (TAWFIVE) and with experimental data. Author

TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT

NASA SPONSORED 1r ON MICROFICHE ACCESSION NUMBER -A89-12562'# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. TITLE -EFFICIENT VIBRATION MODE ANALYSIS OF AIRCRAFT WITH MULTIPLE EXTERNAL STORE CONFIGURATIONS AUTHOR -M. KARPEL (NASA, Langley Research Center, Hampton. VA; Israel Aircraft Industries, Ltd., Lod) Journal of Aircraft (ISSN 0021-8669).- JOURNAL TITLE vol. 25, Aug. 1988, p. 747-751. refs A coupling method for efficient vibration mode analysis of aircraft with multiple external store configurations is presented. A set of low-frequency vibration modes, including rigid-body modes, represent the aircraft. Each external store is represented by its vibration modes with clamped boundary conditions, and by its rigid-body inertial properties. The aircraft modes are obtained from a finite-element model loaded by dummy rigid external stores with fictitious masses. The coupling procedure unloads the dummy stores and loads the actual stores instead. The analytical development is presented, the effects of the fictitious mass magnitudes are discussed, and a numerical example is given for a combat aircraft with external wing stores. Comparison with vibration modes obtained by a direct (full-size) eigensolution shows very accurate coupling results. Once the aircraft and stores data bases are constructed, the computer time for analyzing any external store configuration is two to three orders of magnitude less than that of a direct solution. Author

vii AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 238)

APRIL 1989

01 duplicate (CND), and retest OK (RTOK) events are identified, and their adverse impact assessed using both historical data and analytical examples. Corrective approaches are identified and their AERONAUTICS (GENERAL) potential effectiveness examined. Criteria for evaluating ID tradeoffs in this milieu are identified. I.E.

A09- 10053# MODULAR AVIONICS SYSTEMS ARCHITECTURE (MASA) - A8918011 SEEDS OF DESTRUCTION OR SEEDS OF PROGRESS? AVIONICS TESTING IN THE MILITARY BARE-BASE ROBERT P. LAVOIE IN: AIAAAEEE Digital Avionics Systems ENVIRONMENT Conference, 8th. San Jose, CA, Oct. 17-20, 1988, Technical Papers. A. PADGElT PETERSON (Martin Marietta Electronic Systems Part 1. Washington, DC, American Institute of Aeronautics and Center, Orlando, FL) IN: AUTOTESTCON '88; Proceedings of Astronautics, 1988, p. 8-15. the IEEE International Automatic Testing Conference, Minneapolis, (AIAA PAPER 88-3851) MN, Oct. 4-6, 1988. New York, Institute of Electrical and Electronics This paper identifies payoffs, risks, and some negative business Engineers, Inc., 1988, p. 103-106. implications involved in the adoption of standard electronics and The bare-base support environment for avionics is examined avionics modules. The potential impact on the technical base that with emphasis on the units to be tested, operator sheltering, has permitted conventional avionics products to come far in the unsupplied duration, portable vs. semiportable equipment, and the last two decades is explored. A course of action that would focus criteria necessary for testing current and developing avionics. The the standard module concept, critically examine the payoffs, identify current multisquadron intermediate-level test equipment is offsetting cost penalties, and limit damage to current product lines compared with the requirements arising from the deployment of is proposed. C.D. small numbers (6-10) of aircraft in forward areas. Data derived from the Air Force Coronet Warrior exercise is presented to A89-18347 demonstrate actual testing requirements for avionics equipment, DOWN WITH DRAG as projected onto the bare-base support task. LE. CHRIS DREWER Flight International (ISSN 0015-3710), vol. 134. OCt. 22, 1988, p. 26-28. A8918023 Current research into LFC benefits from novel manufacturing INTEGRATED DIAGNOSTIC CONCEPTS FOR ADVANCED techniques that allow boundary layer suction to be accomplished TECHNOLOGY ROTORCRAFT through the electron beam or laser drilling of microscopic holes JAN-DAVID MARCUS, JAMES MAHANNA, and ROBERT on wing surfaces. Additional techniques under investigation by such GRUESSNER (United Technologies Corp., Sikorsky Aircraft Div., agencies as NASA for near-term implementation are large Stratford, CT) IN: AUTOTESTCON '88; Proceedings of the IEEE eddy-breakup devices, noise reduction on aerodynamic surfaces International Automatic Testing Conference, Minneapolis, MN, Oct. near engines, and 'riblet' V-grooves aligned with the flow. The 4-6, 1988. New York, Institute of Electrical and Electronics intriguing sonic-boom and surface temperature-reduction Engineers, Inc., 1988, p. 171-177. consequences of LFC for SSTs are noted. O.C. It is proposed to achieve integrated diagnostic systems for advanced rotorcraft by melding together design-for-testability (DFf), A89-18851 expert systems, advanced maintenance architectures, portable AHS, ANNUAL FORUM, 44TH, WASHINGTON, DC, JUNE maintenance aids, and electronic publications. Mechanical and 16-18, 1988, PROCEEDINGS avionic systems of the rotorcraft would both be covered by the Forum sponsored by AHS. Alexandria, VA, American Helicopter diagnostic system. The problem is broken down into mechanical Society, 1988, 910 p. For individual items see A89-18852 to diagnostics, in-flight diagnostics, and ground-based diagnostics. A89-18930. LE. The present conference discusses topics in helicopter and tilt-rotor vehicle aerodynamics, military operations, avionics and A8918025 systems, product-support, structural dynamics, structures and THE ENEMY IS FA, CND, AND RTOK materials, configuration design, manufacturing method and product J. M. ANDERSON and J. M. LASKEY (General Electric Co., assurance, handling qualities, acoustics, advanced propulsion, and Automated Systems Dept., Burlington, MA) IN: AUTOTESTCON testing and evaluation methods. Attention is given to rotor/airframe '88; Proceedings of the IEEE International Automatic Testing interaction in tilt-rotor aircraft, the evolution of the V-22 tilt-rotor Conference, Minneapolis, MN, Oct. 4-6, 1988. New York, Institute toward ASW, airframe and propulsion assessment for the LHX, of Electrical and Electronics Engineers, Inc., 1988, p. 185-189. human factors in the V-22's cockpit design, helicopter vibration Integrated diagnostic requirements of a modern avionic analysis and control, structural dynamics of a helicopter rotor blade subsystem are identified. A conceptual integrated diagnostic system, and five candidate designs for civil tilt-rotor aircraft. Also approach to meeting these requirements is postulated. Its essential discussed are the processing and properties of AI-Li alloys, the elements, layered onboard built-in test (BIT), flight-line BIT aeroelastic optimization of a helicopter rotor, the determination of augmentation, depot automatic test equipment (ATE), and a control laws for a single-pilot helicopter, the sand and ice ingestion diagnostic support information system are described. Modern behavior of dual centrifugal compressors, active acoustical control maintenance concepts into which these must be embedded are for cylindrical fuselage structures, and air-to-air combat helicopter outlined and discussed. Mechanisms for false alarm (FA), cannot development. O.C.

141 01 AERONAUTICS (GENERAL)

A8918859 A8948873 AIR COMBAT TACTICS FOR THE EVALUATION OF ' IMPROVED LIFE CYCLE 'REPS SERVICES - V-22 ROTORCRAFT CHARACTERISTICS IN THE LOW AIR WAR OF ENGINEERING TECHNICAL SERVICES AND LOGISTICS 2010 PLANNING DAVID L. GREEN (Starmark Corp., Arlington, VA) and JACK V. CRESSWELL D. ELMORE (US. Navy, Naval Air Systems MACKMULL IN: AHS, Annual Forum, 44th, Washington, DC. Command, Washington, DC) IN: AHS, Annual Forum, 44th, June 16-18, 1988, Proceedings. Alexandria, VA. American Washington, DC, June 16-18. 1988, Proceedings. Alexandria, VA, Helicopter Society, 1988, p. 119-1 37. refs American Helicopter Society, 1988, p. 255-259. The characteristics of an aerial battlefield below 100-m altitude The V-22 Integrated Logistics Support Program capitalizes on are postulated for 2010-timeframe technologies. This scenario is the early implementation of Cognizant Field Activity (CFA) applied, together with a conceptual high-performance rotorcraft capabilities to reduce armed services' dependency on system, to a holistic analytical method for the synthesis of air contractor-purveyed engineering services. This has entailed the combat tactics. The utility of a rotorcraft possessing a large power formulation of firm, fixed-price requirements for V-22 full-scale margin and speed advantage over its adversary is evaluated engineering development, as well as option items contract through the iterative application of an action-reaction analysis which specifications that call for early incremental training for depot-level converges on tactics and rules-of-engagement. A sample set of support. CFA will ensure that the Naval Air Engineering Support these synthesized tactics are presented to indicate the king of Unit's personnel are trained during the late full-scale engineering tactical advantage thus achievable. O.C. development and early operations phases. O.C.

A8918860 A89-19551 US ARMY AIRCRAFT COMBAT MAINTENANCE/BATTLE AEROSPACE SIMULATION 111; PROCEEDINGS OF THE SCS DAMAGE REPAIR PROGRAM MULTICONFERENCE, SAN DIEGO, CA, FEB. 3-5, 1988 MING-LEUNG LAU (US. Army, Aviation Applied Technology MONTE UNG, ED. (Southern California, University, Los Angeles, Directorate, Fort Eustis, VA) IN: AHS, Annual Forum, 44th, CA) Conference sponsored by the Society for Computer Simulation Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, International. San Diego, CA, Society for Computer Simulation American Helicopter Society, 1988, p. 139-142. International (Simulation Series. Volume 19, No. 2, Apr. 1988), This paper discusses the research and development efforts 1988, 316 p. For individual items see A89-19552 to A89-19573. conducted by the US. Army Aviation Applied Technology The conference presents papers on hardware-in-the-loop, Directorate (AATD) under the Aircraft Combat Maintenance/Battle aircrafts and rotorcrafts, missile applications. space applications, Damage Repair (ACM/BDR) program. Under the ACM/BDR SDI. and research and developments. Particular attention is given program, battle damage repair (BDR) kits for aircraft systems and to scene generation for real-time missile flight test, imaging missile battle damage assessment and repair (BDAR) manuals for simulations, and X-29 validation methodology for simulation and helicopters are being developed, evaluated and fielded. Fielding flight control system. Other topics include real-time simulation of of the BDR kits and BDAR manuals will provide Army aviation the Space Station mobile service center, a model of the earth's units with the maintenance resources needed to support increased magnetic field as applied to missile attitude reference, and maintenance workloads associated with sustained combat AHIS-detailed endoatmospheric endgame digital simulation. K.K. operations. Author A89-19864# A8918862 COMPARISON OF FAA DO-178A AND DOD-STD-2167A TILTROTOR EVOLUTION LEADS TO ASW REVOLUTION APPROACHES TO SOFTWARE CERTIFICATION MIKE JAGIELSKI, JACK LATCHFORD, DICK SPIVEY (Bell MICHAEL P. DEWALT (FAA, Seattle, WA) AIAA, Digital Systems Helicopter Textron, Inc., Fort Worth, TX), and R. P. KRULIS (US. Conference, 8th. San Jose, CA, Oct. 17-20. 1988. 8 p. Navy, Naval Air Systems Command, Washington. DC) IN: AHS, (AIAA PAPER 88-4044) Annual Forum, 44th, Washington, DC, June 16-18, 1988, There are two popular standards for developing avionics proceedings. Alexandria, VA. American Helicopter Society, 1988, software. The standard used for commercial aircraft is p. 149-157. RTCA/DO-l78A, Software Considerations in Airborne Systems and The 'missionization' of the SV-22 for ASW is analyzed. Evolving Equipment Certification whereas military environment uses SV-22 requirements are profiled from the perspective of the DOD-STD-P167A, Military Standard Defense System Software increasing Soviet submarine threat. The unique flexibility of the Development. This paper compares these two standards and SV-22 to respond to a wide variety of ASW tactical situations, demonstrates that, with some minor additional documentation ranging from carrier-based operations to other ship-based missions changes, software developed under the military standard that demand operations from smaller surface combatants capable DOD-STD-2167A could be compatible with certification of supporting only VTOL aircraft, is highlighted. The SEAHUNT requirements imposed by the Federal Aviation Administration computer model is used to analyze and graphically demonstrate through RTCA/DO-l78A for commercial aircraft. Author the SV-22's contribution to Navy battle group survivability. Author A89-20226 YEARBOOK 1987 II; DGLR, ANNUAL MEETING, BERLIN, A8918869 FEDERAL REPUBLIC OF GERMANY, OCT. 5-7, 1987, AH-64A CONTRACTOR LOGISTIC SUPPORT - THE REPORTS [JAHRBUCH 1987 II; DGLR, JAHRESTAGUNG, CONTRACTORS PERSPECTIVE BERLIN, FEDERAL REPUBLIC OF GERMANY, OCT. 5-7, 1987, JOHN E. REAGAN and JACK WOOD (McDonnell Douglas VORTRAEGE] Helicopter Co., Mesa, AZ) IN: AHS, Annual Forum, 44th, Meeting sponsored by DGLR. Bonn, Deutsche Gesellschaft fuer Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, LuA- und Raumfahrt, 1987, 567 p. In German and English. For American Helicopter Society, 1988, p. 235, 236. individual items see 1489-20227 to A89-20245. This paper provides an overview of the AH-64A Apache Various papers on aerodynamics and space flight are presented. Contractor Logistics Support (CLS) Program from first flight, January The topics addressed include: technological tasks in 26, 1984, through the formal end of CLS, February 1, 1987. To aerothermodynamics; uses and technologies of future regenerative gain an understanding of the magnitude of the tasks accomplished communications satellites; German-Italian program in microgravity during the CLS phase, 270 Apaches were fielded. Additionally, research; new testbeds for future space travel developments and more than 10,000 lines of spares and repair parts, trainers, and hypersonic flight; primary and regenerative fuel cell systems for test program sets were delivered, along with spares and repair the European space flight scenario; BIOTEX project for biological parts to support fielding of 10 Authorized Stockage Lists and eight experiments in microgravity; balloon-borne microgravity Prescribed Load List. Author experiments; numerical methods for hypersonic flows. Also

142 02 AERODYNAMICS discussed are: MPC 75 project for advanced regional air traffic; progress towards a commercial aircraft design expert system; concept and testing of a modern longitudinal movement controller using an inverse model; flight guidance technology; design and AERODYNAMICS integration of air-breathing propulsion systems of space flight and hypersonic flight vehicles; ruggedness of dynamically loaded power Includes aerodynamics of bodies, combinations, wings, rotors, and inlets in fiber-reinforced composite rotors; fiber-reinforced control surfaces; and internal flow in ducts and turbomachinery. composite materials for supersonic flight. A0917147# DETECTION OF LAMINAR-TURBULENT TRANSITION BY INFRARED THERMOGRAPHY G. GAUFFRE (ONERA, Chatillon-sous-Bagneux, France) La Recherche Aerospatiale (English Edition) (ISSN 0379-38OX), no. A8920242 2, 1988, p. 11-22. refs INTRODUCTION OF NEW TECHNOLOGIES IN THE An aerodynamic flow results in major heat transfers between STRUCTURAL AREA FROM THE VIEWPOINT OF IABG an aircraft and the fluid it is flying through. These transfers differ [EINFUEHRUNG NEUER TECHNOLOGIEN AUF DEM greatly depending on the laminar or turbulent state of the boundary STRUKTURGEBIET AUS DEM BLICKFELD DER IABG] layer. Using the infrared radiation from the body itself, it is possible K. WOITHE (Industrieanlagen-Betriebsgesellschaft mbH, Ottobrunn, to establish an approximate thermal mapping and thereby localize Federal Republic of Germany) IN: Yearbook 1987 II; DGLR, the transition between the regions of laminar and turbulent flow. Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, In the first part of the present paper, we study the creation of the 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und thermal distribution on the surface of the model and the phenomena Raumfahrt, 1987, p. 867-872. In German. that disturb this map. The infrared systems used are then described, (DGLR PAPER 87-107) along with the precautions to be taken to obtain significant thermal An overview is presented of significant developments in the images. Very probative results have already been obtained application of reinforced fiber composites to aircraft structures in throughout the subsonic domain and the extension to the West Germany. Helicopters, fighter aircraft, commercial aviation, supersonic and hypersonic domains is now under way. Author and general aviation are considered. Goals for the future in this area are examined. C.D. A89-17150# COMPUTATION OF THE PRESSURE IN AN INCOMPRESSIBLE ROTATIONAL FLOW OF INVISCID FLUID B. CANTALOUBE and C. REHBACH (ONERA, Chatillon- sous-Bagneux, France) La Recherche Aerospatiale (English Edition) (ISSN 0379-38OX), no. 2, 1988, p. 57-61. refs A8920744 In an unsteady flow of inviscid incompressible fluid with vorticity, V-22 OSPREY ENABLING TECHNOLOGIES the static pressure is computed by solving a type 2 Fredholm STANLEY MARTIN and ALLEN H. SCHOEN (Bell Helicopter integral equation. This is the logical complement of the integral Textron, Inc., Fort Worth, TX) Vertiflite (ISSN 0042-4455), vol. solution known for the velocity field, and avoids introducing the 34, Nov.-Dec. 1988, p. 46-50. idea of the velocity potential of a vortex field that appears in the The technologies most essential to the success of the V-22 unsteady Bernoulli integral usually used for evaluating the tilt-rotor VTOL aircraft were largely identified in the course of the pressure. Author VX-15 tilt-rotor research aircraft program, which also established flight envelope contours required by the variety of Navy and Marine A89-17460 Corps missions for which the V-22 is intended. The technologies SPATIAL MARCHING TECHNIQUES FOR APPROXIMATE that will ensure such missions’ success encompass digital SOLUTIONS TO THE HYPERSONIC BLUNT BODY PROBLEM fly-by-wire controls, in the form of a triplex self-monitored primary FREDERICK G. BLOTTNER (Sandia National Laboratories, flight control system with triplicated and separated hydraulics, and Albuquerque, NM) International Journal for Numerical Methods composite primary structures capable of satisfying not only the in Fluids (ISSN 0271-2091), vol. 8, Oct. 1988, p. 1331-1347. obvious stiffness and lightness criteria, but the high ballistic refs tolerance necessary for military missions as well. O.C. (Contract DE-AC04-76DP-00789) Two reduced forms of the Euler equations which allow spatial marching in subsonic flow regions are investigated for solving the inviscid blunt-body problem. An analysis of the eigenvalues to determine the properties of the steady and unsteady forms of the governing equations is performed. Numerical results from the thin-layer equations are less accurate, and the suitability of this A8920747 approach in a global iteration procedure is questioned, as the NASA/AHS ROTORCRAFT NOISE REDUCTION PROGRAM - analysis shows information is not transmitted upstream. The MCDONNELL DOUGLAS HELICOPTER COMPANY pressure-gradient splitting method gives more accurate results with ACCOMPLISHMENTS a single downstream march and appears better suited for use in R. D. JANAKIRAM (McDonnell Douglas Helicopter Co., Phoenix, a global iteration procedure to obtain the complete solution of the AZ) Vertiflite (ISSN 0042-4455), vol. 34, Nov.-Dec. 1988, p. Euler equations. Author 64-68. The contributions of a major U.S. aircraft manufacturer to the A8917874# NASA Advanced Helicopter Systems noise reduction program are STUDY THE AERODYNAMICS CHARACTERISTICS OF evaluated. These efforts have encompassed NASA-Wallops and AIRFOIL ON VECTOR PROCESSORS NASA-Langley main rotor noise-dominant MD500E helicopter test LAI-CHEN CHIEN, WEN-YUAN HSU, and HSIN-HUA TSUEI flights and HARP rotor anechoic wind tunnel tests. Major (National Central University, Chung-Li, Republic of China) IAF, contributions have also been made to the development and International Astronautical Congress, 39th, Bangalore, India, Oct. evaluation of prediction methodologies such as NASA-Langley’s 8-15, 1988. 7 p. refs ROTONET; this provides component source aerodynamic and noise (IAF PAPER ST-88-09) prediction models of varying complexity, and allows the The time-dependent, two-dimensional Euler equation in substantiation of user-generated prediction modules. O.C. conservative form is taken into account to study the problem

143 considered. The modified differential quadrature method is A8918546 incorporated with a Runge-Kutta time integration scheme to solve CONVECTIVE HEAT TRANSFER IN A BOUNDARY LAYER the governing equations. In the modified differential quadrature BEHIND A SHOCK WAVE PROPAGATING ALONG A FLAT method, the spatial derivatives are approximated by a weighted PLATE WITH A SHARP LEADING EDGE - A CALCULATION sum of unknown function at properly chosen neighboring points METHOD AND A COMPARISON WITH EXPERIMENTAL DATA to generate a set of differential equations in time. Then the set of [KONVEKTIVNYI TEPLOOBMEN V POGRANICHNOM SLOE ZA ordinary equations is solved by a vectorized fourth-order UDARNOl VOLNOI, DVIZHUSHCHEISIA VDOL' PLOSKOI Runge-Kutta time integration scheme using a vector processor. PLASTINY S OSTROI PEREDNEI KROMKOI - METOD The details of the vectorization process are presented. Author RASCHETA I SRAVNENIE S EKSPERIMENTAL'NYMI DANNYMI] V. I. ZUEV and V. K. SHIKOV (AN SSSR, lnstitut Vysokikh Temperatur, Moscow, USSR) Teplofizika Vysokikh Temperatur (ISSN 0040-3644), vol. 26, Sept.-Oct. 1988, p. 909-917. In A89-17940*# National Aeronautics and Space Administration. Russian. refs Lewis Research Center, Cleveland, OH. EULER ANALYSIS OF A SWIRL RECOVERY VANE DESIGN FOR USE WITH AN ADVANCED SINGLE-ROTATION A8918669 PROPFAN SELF-SIMILAR PROBLEM OF THE SEPARATED FLOW OF AN CHRISTOPHER J. MILLER (NASA, Lewis Research Center, IDEAL FLUID PAST AN EXPANDING PLATE Cleveland, OH) AIAA, ASME, SAE, and ASEE, Joint Propulsion [AVTOMODEL'NAIA ZADACHA OTRYVNOGO OBTEKANIIA Conference, 24th. Boston, MA, July 11-13. 1988. 15 p. Previously RASSHlRlAlUSHCHElSlA PLASTINY IDEAL'NOI ZHIDKOST'IU] announced in STAR as "3-29771. refs V. I. KOPCHENOV, A. N. KRAIKO, and S. K. SHCHlPlN Akademiia (AIAA PAPER 88-3152) Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN Recent work has demonstrated the propulsive efficiency 0568-5281), Sept.-Oct. 1988, p. 62-69. In Russian. refs improvement available from single- and counter-rotation propfans The self-similar problem of nonstationary plane-parallel as compared with current technology high bypass ratio turbofans. separated flow of an ideal fluid past a plate expanding from a The concept known as swirl recovery vanes (SRV) is examined point at a constant rate is analyzed with emphasis on flow topology. through the use of a 3-D Euler code. At high speed cruise In particular, attention is given to the structure of conical flow conditions, the SRV can improve the efficiency level of a lines and their runoff and spread points (for a special nonlinear single-rotation propfan, but a concern is to have adequate hub law of plate expansion and variable incoming flow speed). A choke margin. The SAV was designed with 2-0 methods and was comparison of results produced by vortex sheet and vortex filament predicted to have hub choking at Mach 0.8 cruise. The 3-0 Euler models is carried out over a wide range of flow parameters. V.L. analysis properly accounts for sweep effects and 3-D relief, and predicts that at cruise the SRV will recover roughly 5 percent of the 10 percent efficiency loss due to swirl and have a good hub A89-18671 choke margin. Author MATHEMATICAL MODELING OF LAMINAR AND TURBULENT SUPERSONIC FLOW PAST CONVEX-CONCAVE BODIES [MATEMATICHESKOE MODELIROVANIE LAMINARNOGO I TURBULENTNOGO SVERKHZVUKOVOGO OBTEKANIIA TEL VYPUKLO-VOGNUTOI FORYY] A89-18355 A. M. GRlSHlN and 0. I. POGORELOV Akademiia Nauk SSSR, CALCULATION OF THE UNSTEADY AERODYNAMIC Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281). Sept.-Oct. CHARACTERISTICS OF BODIES IN THE CASE OF 1988, p. 138-145. In Russian. refs SEPARATED FLOW [RASCHET NESTATSIONARNYKH Laminar and turbulent supersonic flow past two convex-concave AERODINAMICHESKIKH KHARAKTERISTIK TEL PRI bodies is analyzed on the basis of Navier-Stokes equations. For OTRYVNOM OBTEKANII] laminar flow, the effect of the Reynolds number on the shock V. A. APARINOV, S. M. BELOTSERKOVSKII, I. K. LIFANOV, and layer structure, pressure distribution, and heat flux is investigated. A. A. MlKHAlLOV Zhurnal Vychislitel'noi Matematiki i For turbulent flow, the calculated results are compared with the Matematicheskoi Fiziki (ISSN 0044-4669), vol. 28, Oct. 1988, p. calculations and experimental data of recent studies. It is shown 1558-1566. In Russian. refs that, in the separation region, the pressure distributions on the A method is developed for the numerical simulation of body and the position and shape of the shock wave based on three-dimensional separated flow past bluff bodies with fixed points the Navier-Stokes equations are found to be in better agreement of flow separation. An integrodifferential mathematical model for with experimental data than results based on the Euler and viscous the three-dimensional separated flow is derived, and a calculation shock layer equations. V.L. example is presented. B.J.

A8918675 DETERMINATION OF THE PERTURBATIONS OF THE FLOW FIELDS OF SUPERSONIC WIND TUNNELS FROM MEASURED A8918357 AERODYNAMIC COEFFICIENTS [OPREDELENIE CALCULATION OF HYPERSONIC FLOW PAST THE VOZMUSHCHENII POLEI POTOKOV SVERKHZVUKOVYKH WINDWARD SIDE OF A LOWASPECT-RATIO WING AT HIGH AERODINAMICHESKIKH TRUB PO IZMERENNYM ANGLES OF AlTACK [RASCHET GIPERZVUKOVOGO ZNACHENIIAM AERODINAMICHESKIKH KOEFFITSIENTOV] OBTEKANIIA NAVETRENNOI STORONY KRYLA MALOGO V. V. EREMIN, IU. M. LIPNITSKII, and S. E. FlLlPPOV Akademiia UDLlNENllA PRI BOL'SHIKH UGLAKH ATAKI] Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN V. N. GOLUBKIN and V. V. NEGODA Zhurnal Vychislitel'noi 0568-5281), Sept.-Oct. 1988, p. 183-185. In Russian. Matematiki i Matematicheskoi Fiziki (ISSN 0044-4669). vol. 28, A new approach is proposed for determining the perturbations Oct. 1988, p. 1586-1594. In Russian. refs of flow fields in supersonic wind tunnels, including the downwash. The paper presents a theoretical analysis of the hypersonic The approach is based on solving the inverse problem whereby flow past a thin low-aspect-ratio wing at an angle of attack close the real values of these perturbations are reconstructed from the to pV2. An asymptotic method is used to study the two-layer measured values of the integral aerodynamic characteristics of structure of compressed-gas flow between the bow shock and the model moving in the test section of the wind tunnel. The the windward side of the wing. B.J. method is illustrated by a specific example. V.L.

144 02 AERODYNAMICS

A8918749# speed. Also presented are new analysis methods for the intimate RECENT DEVELOPMENTS IN TRANSONIC FLOW interactions between vortices and fixed surfaces which include a COMPUTATION specialized treatment of the vortex velocity field for close P. NlYOGl (Indian Institute of Technology, Kharagpur, India) interactions with paneled surfaces. O.C. Institution of Engineers (India), Journal, Aerospace Engineering Division (ISSN 0257-3423), vol. 68, Sept. 1987-Mar. 1988, p. 12-23. refs A89-18855' National Aeronautics and Space Administration. This paper is a brief survey of some of recent developments Langley Research Center, Hampton, VA. in transonic flow computation carried out in India over the past ROTOR INFLOW VARIABILITY WITH ADVANCE RATIO few years. The survey is divided into two parts: the first deals DANNY R. HOAD, SUSAN L. ALTHOFF, and JOE W. ELLIOlT with results obtained through integral method, and the second (NASA, Langley Research Center: U.S. Army, Aerostructures reports works in transonic flow, using finite difference method. Directorate, Hampton, VA) IN: AHS, Annual Forum, 44th, Author Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, American Helicopter Society, 1988, p. 57-72. refs A8918750# A comparative study is conducted for the results of inflow calculations based on several analytical wake methods and COMPUTATION OF AXISYMMETRIC SUPERSONIC JET USING laser-velocimeter rotor inflow measurements near a rectangular SPACE MARCHING TECHNIQUE M. A. RAMASWAMY (Indian Institute of Science, Bangalore, India) four-bladed rotor system operating in forward flight. The induced-flow characteristics at all advance ratios were found to and N. MADHAVAN (Aeronautical Development Agency, Bangalore, India) Institution of Engineers (India), Journal, Aerospace be unsymmetrical about the longitudinal centerline, with maximum downwash in the rear portion of the disk, and skewed toward the Engineering Division (ISSN 0257-3423), vol. 68, Sept. 1987-Mar. 1988, p. 24-30. advancing blade-side. Comparisons among analytical methods An efficient space marching technique which has been applied show that the region of induced upflow over the rotor disk was effectively modeled only at an advance ratio value of 0.15. O.C. earlier for computing inviscid supersonic flow over complex bodies has been applied to compute the flow field of axisymmetric supersonic free jets. Application of this technique to free jet flows A89-18856 involves modifications to take care of constant pressure boundary A CORRELATION STUDY OF ROTOR INFLOW IN FORWARD condition and the singularity of the axisymmetric equation at the FLIGHT axis. The present results are compared with those obtained from BRUCE D. CHARLES and AHMED A. HASSAN (McDonnell Douglas experiments and from the method of characteristics. The agreement Helicopter Co., Mesa, AZ) IN: AHS. Annual Forum, 44th, is found to be quite satisfactory. This gives confidence in applying Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, this technique to compute more complicated three-dimensional American Helicopter Society, 1988, p. 73-85. refs free jets. Author Correlation of the experimental inflow data obtained in the NASA Langley 14- by 22-Foot Subsonic Tunnel with the predicted inflow A8918803 using Scully and Sadler free wake models has been performed. COMPUTATIONAL ANALYSIS OF UNSTEADY SUPERSONIC The sensitivity of time averaged induced velocities to wake CAVITY FLOWS DRIVEN BY THICK SHEAR LAYERS geometry variations is examined here using the CAMRAD X. ZHANG and J. A. EDWARDS (Cambridge University, England) prescribed wake model. A comparison of the predicted free wake Aeronautical Journal (ISSN 0001 -9240), vol. 92, Nov. 1988, p. velocities is made with the time varying data to illustrate the 365-374. Research supported by the Ministry of Defence influence of blade and vortex passage near the measurement point. Procurement Executive. refs A computational fluid dynamic model of the rotor, based on the Supersonic cavity flows driven by a thick shear layer at Mach solution of the unsteady full potential equation, has been employed 1.5 and' 2.5 are studied by solving the two-dimensional unsteady to examine velocities induced at points passing near the blade. compressible Navier-Stokes equations in terms of mass-averaged The experimental and full potential results are compared with variables. The length to depth ratio of the rectangular cavity is velocities predicted using the lifting line bound vortex methodology three. The numerical scheme used is the finite-difference algorithm inherent in the wake analysis. Author by Brailovskaya. A two-layer eddy-viscosity turbulence model is used. The results are compared with experimental data. The computations show the self-sustained oscillations at Mach 1.5 and A89-18857' National Aeronautics and Space Administration. 2.5. The continuous formation and downstream shedding of leading Ames Research Center, Moffett Field, CA. edge vortices is demonstrated. The oscillatory modes are correctly AN ENTROPY AND VISCOSITY CORRECTED POTENTIAL predicted. The first mode is attributed to a large unsteady trailing METHOD FOR ROTOR PERFORMANCE PREDICTION edge vortex moving in the transverse direction. Based on the JOHN 0. BRIDGEMAN (Woodside Summit Group, Inc., Mountain analysis, it is considered that the oscillation in the length to depth View, CA), ROGER C. STRAWN, and FRANCIS X. CARADONNA ratio three cavity is a longitudinal one and is controlled by a fluid (NASA, Ames Research Center: U.S. Army, Aeroflightdynamics dynamic mechanism rather than a purely acoustic one. Author Directorate, Moffett Field, CA) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, A8918853 American Helicopter Society, 1988, p. 87-98. refs FREE WAKE CALCULATION OF ROTOR FLOW FIELDS FOR An unsteady Full-Potential Rotor code (FPR) has been INTERACTIONAL AERODYNAMICS enhanced with modifications directed at improving its drag TODD R. QUACKENBUSH (Continuum Dynamics, Inc., Princeton, prediction capability. The shock generated entropy has been NJ) and DONALD B. BLISS (Duke University, Durham, NC) IN: included to provide solutions comparable to the Euler equations. AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, A weakly interacted integral boundary layer has also been coupled Proceedings. Alexandria, VA, American Helicopter Society, 1988, to FPR in order to estimate skin-friction drag. Pressure distributions, p. 29-43. refs shock positions, and drag comparisons are made with various (Contract DAAL03-87-C-0013) data sets derived from two-dimensional airfoil, hovering, and An evaluation is made of the applicability of novel advancing high speed rotor tests. In all these comparisons, the vortex-dynamics analyses to rotorcraft interactional aerodynamics effect of the nonisentropic modification improves (i.e., weakens) problems. A novel full-span rotor wake representation constructed the shock strength and wave drag. In addition, the boundary layer on the basis of curved vortex elements is noted to yield both method yields reasonable estimates of skin-friction drag. Airfoil qualitatively and quantitatively accurate predictions of wake velocity drag and hover torque data comparisons are excellent, as are data in low- and high-speed forward flight, and to illustrate the predicted shock strength and positions for a high speed advancing radical changes occurring in the wake velocity field with increasing rotor. Author

145 02 AERODYNAMICS

A8918858 A89-18917

-AN .._ EXAMINATION ...... ~~ ~ OF SOME ROTOR AERODYNAMIC A UNIFIED THEORETICAL-COMPUTATIONAL APPROACH MODELS USINGTHE RSRAIX-WING MODEL TEST DATA FOR VISCOUS UNSTEADY ROTOR AERODYNAMICS S. JON DAVIS, JOHN P. SHANLEY, and PAUL BUETTIKER (United J. C. WU and I. H. TUNCER (Georgia Institute of Technology, Technologies Corp., Sikorsky Aircraft Div., Stratford, CT) IN: Atlanta) IN: AHS, Annual Forum, 44th, Washington, DC, June AHS, Annual Forum, 44th, Washington, DC, June 16-18,1988, 16-18, 1988, proceedings. Alexandria, VA, American Helicopter Proceedings. Alexandria, VA, American Helicopter Society, 1988, Society, 1988, p. 809-818. Army-supported research. refs p. 99-110. refs (Contract AF-AFOSR-86-0121) A serious deficiency in a drag-calculating Prandtl-model’s A unified theoretical-computation approach far viscous unsteady accuracy in determining the value for an X-wing’s fixed operational aerodynamic analysis is presented. This approach is shown to be mode has prompted the present imposition of simple loading valid under general circumstances and to possess the ability of distributions on forward- and aft-swept wings, using both the Prandtl confining aerodynamic analysis to the viscous region of the flow. lifting-line model and a combination of the Weissinger (1947) In addition, it is shown that the approach permits the flow zones L-method and Munk’s (1921) stagger theorem. Substantial coexisting in the viscous region to be analyzed individually. differences are found between the total induced drag predicted Predictive methods using the unified approach which are described by the two methods for elliptical, uniform, and triangularly tip-loaded are shown to be highly efficient and accurate. Selected results for lift distributions. Attention is also given to the results of a CRUISE5 the blade-vortex interaction problem and the oscillating airfoil configuration-performance analysis of the X-wing in conjunction problem are presented and discussed. Author with body-interference velocities calculated by the VSAERO panel code. O.C. A89189 18 HELICOPTER FREE WAKE PREDICTION OF COMPLEX WAKE STRUCTURES UNDER BLADE-VORTEX INTERACTION A89-18915 OPERATING CONDITIONS IMPROVEMENTS TO TRANSONIC FLOWFIELD T. ALAN EGOLF (United Technologies Research Center, East CALCULATIONS Hartford, CT) IN: AHS, Annual Forum, 44th, Washington, DC. D. S. PRICHARD and L. N. SANKAR (Georgia Institute of June 16-18, 1988, Proceedings. Alexandria, VA. American Technology, Atlanta) IN: AHS, Annual Forum, 44th, Washington, Helicopter Society, 1988, p. 81 9-832. refs DC, June 16-18, 1988, proceedings. Alexandria, VA, American A free wake method for helicopter rotor application is described Helicopter Society, 1988, p. 785-796.Research supported by the which removes many simplifying and limiting assumptions McDonnell Douglas Helicopter Co. refs concerning the structure of the rotor wake geometry. In this method Several improvements have been made to a transonic full the complete wake surface is modeled using a vortex lattice potential flow code, to allow more accurate and flexible analysis structure. The method was successfully applied to both a main of helicopter rotor blade flowfields. Rigid body motion about rotor and a tail rotor operating under Blade-Vortex Interaction flapping, pitch, and lead-lag hinges has been incorporated into conditions. The analysis predicted complex multiple tip vortex-like the grid, with flow velocities due to blade motion incorporated structures which have been observed experimentally for the tail into the solution explicitly through grid velocity terms. Along with rotor conditions studied. Author explicit handling of blade motion, inflow due to the farfield wake has been recast in terms of a velocity parallel to the shaft axis. A89-18919 Boundary layer effects have been incorporated into the potential ROTORCRAFT AEROMECHANICAL ANALYSIS USING A flow code by using a strip-theory approach in conjunction with a NONLINEAR UNSTEADY AERODYNAMIC MODEL 2-13 boundary layer analysis in a coupled viscous-inviscid ANDREW S. ELLIOTT (McDonnell Douglas Helicopter Co., Mesa, interaction. This work provides skin friction information as well as AZ). J. GORDON LEISHMAN, and INDERJIT CHOPRA (Maryland, modification of the inviscid flow behavior. Also, a Newton iteration University, College Park) IN: AHS, Annual Forum, 44th, method has been developed to reduce the number of time steps Washington, DC, June 16-18,1988, Proceedings. Alexandria, VA, required for a given analysis and to minimize errors due to American Helicopter Society, 1988, p. 833-845. refs approximate solution of the linear system. Author A unified, two-dimensional, time domain model has been developed for calculating unsteady nonlinear aerodynamic forces throughout the rotor flight envelope, including compressible and A891891 6 separated flows. The model is conceptually and computationally AN EVALUATION OF A NAVIER-STOKES CODE FOR separated into three parts: (1) a linear, attached flow solution, (2) CALCULATIONS OF RETREATING BLADE STALL ON A a nonlinear, separated flow solution, and (3) a dynamic stall HELICOPTER ROTOR solution. It has been validated against test data for the “02 J. C. NARRAMORE (Bell Helicopter Textron, Inc., Fort Worth, TX), airfoil undergoing unsteady forcing, including dynamic stall. The L. N. SANKAR (Georgia Institute of Technology, Atlanta), and R. process dynamics of each model constituent are expressed as VERMELAND (Cray Research, Inc., Mendota Heights, MN) IN: equivalent continuous time state space subsystems which augment AHS, Annual Forum, 44th, Washington. DC. June 16-18, 1988, the system state equations. The model is incorporated into a finite Proceedings. Alexandria, VA, American Helicopter Society, 1988, element rotor dynamics code and demonstrates the importance p. 797-808.Army-supported research. refs of nonlinear aerodynamic effects when the rotor is highly loaded A hybrid time-marching technique for the numerical solution of or operating at high advance ratio. Author the three-dimensional unsteady, Reynolds-averaged, Navier-Stokes equations has been used to compute the three-dimensional A89-18939’ Notre Dame Univ., IN. retreating blade stall characteristics on a helicopter rotor. An SEVEN HOLE PROBE MEASUREMENT OF LEADING EDGE evaluation of the results from this solution is being carried out. VORTEX FLOWS Forces computed by the Navier-Stokes code are compared to F. M. PAYNE, T. T. NG, and R. C. NELSON (Notre Dame, University, results from a modularized, two-dimensional strip, blade element IN) Experiments in Fluids (ISSN 0723-4864),vol. 7, no. 1, 1989, theory method that includes a free wake analysis module, an p. 1-8. Research supported by the University of Notre Dame. unsteady aerodynamics module, and an aeroelastic rotor module. refs Initial results from the three-dimensional Navier-Stokes analysis (Contract NAG2-258) indicate that there is an outflow in the separated region of the This paper discusses the use of a seven-hole probe on retreating blade. This three-dimensional separation phenomenon measurements of leading edge vortices of highly sweep delta wing generates forces that cannot be predicted by current state-of-the-art planforms. Intrusive probe data taken with the pressure probe analysis codes that use two-dimensional airfoil stall characteristics were compared with nonintrusive measurements made with laser to predict the rotor blade characteristics. Author Doppler anemometry system. In addition to probe size, the natural

146 02 AERODYNAMICS position of breakdown and the sweep angle of the wing are also DAVID A. PETERS (Georgia Institute of Technology, Atlanta) and factors in determining sensitivity of the flow to probe interference. NlNH HAQUANG (Boeing Helicopters, Philadelphia, PA) American At low angles of attach vortex breakdown does not occur in the Helicopter Society, Journal (ISSN 0002-871l), vol. 33, Oct. 1988, vicinity of the model and the seven hole probe was found to yield p. 64-68. Army-supported research. refs reasonably accurate measurements. When the angle of attack of (Contract NAS2-12341) the model was increased so that vortex breakdown was near the A derivation is presented which gives both the nonlinear dynamic trailing edge, introducing the probe over the wing would cause inflow model and the perturbation dynamic inflow model in a general the breakdown position to move ahead of the probe. However, coordinate system. The perturbation model includes perturbations when breakdown naturally occurred ahead of the mid-chord of in hub motions, in skew angle, and in yaw angle. The governing the wing the vortices were found to be less sensitive to a probe equations may be switched to their dimensional forms prior to placed behind the breakdown point. Vortex breakdown on a lower application. K.K. swept wing is found to be more sensitive to interference. Near the breakdown region, seven hole probe measurement is less accurate due to a combination of probe interference and flow A89-19660 reversal. Author ANALYSIS OF A FIGHTER TYPE AIRCRAFT CONFIGURATION WITH THE HISSS PANEL METHOD AT SUBSONIC AND A8918940 SUPERSONIC SPEEDS THE USE OF SWEEP-FREQUENCY EXCITATION FOR S. HEISS and L. FORNASIER (Messerschmitt-Boelkow-Blohm UNSTEADY PRESSURE MEASUREMENT GmbH, Munich, Federal Republic of Germany) (DGLR, B. L. WELSH and C. R. PYNE (Royal Aircraft Establishment, Jahrestagung, Berlin, Federal Republic of Germany, Oct. 5-7, 1987) Bedford, England) Experiments in Fluids (ISSN 0723-4864), vol. Zeitschrift fuer Flugwissenschaften und Weltraumforschung (ISSN 7, no. 1, 1989, p. 9-16. refs 0342-068X), vol. 12, July-Aug. 1988, p. 224-232. refs The use of sweep-frequency excitation for rapid measurement (DGLR PAPER 87-085) of time-dependent pressures on wind-tunnel models is examined. HlSSS is a computer program for predicting subsonic or Results obtained from two different wind-tunnels covering the Mach supersonic linear potential flow about arbitrary configurations. The number range from 0.2 to 0.85, and a wide range of flow conditions, program was used for calculations on a complex fighter-type aircraft are compared with measurements made using the slower, design with a canard, delta wing, and an underbelly intake. The traditional method of discrete-frequency excitation. It is concluded range of problems for which the program gives adequate solutions that the sweep-frequency excitation method can reduce testing was analyzed by comparing the lift and pitch moment predictions time in certain flow conditions with no significant loss in accuracy. for zero lift with an experimental database for the model at different Author Mach numbers. The lift and pitch moment coefficients for the model with deflected trailing edge flaps were computed for M A89-18946 (infinity) = 0.4 and M (infinite) = 1.2 and compared with MEASUREMENT AND ANALYSIS OF UNSTEADY FLOW experiment. A separate model of the air duct was used to analyze STRUCTURES IN ROTOR BLADE WAKES the duct flow for the subsonic Mach number M (infinity) = 0.585. V. R. CAPECE and S. FLEETER (Purdue University, West Lafayette, The recently added streamline capability was used to assess the IN) Experiments in Fluids (ISSN 0723-4864), vol. 7, no. 1, 1989, predicted flow visually. Author p. 61 -67. USAF-supported research. refs Unsteady flow phenomena leading to differences in the instantaneous rotor blade wake data are investigated, and the variations in the data are analyzed by developing a mathematical A89-19664 model of the rotor blade exit flow field, with a vortex sheet structure AN ANALYTICAL DESCRIPTION OF UNSTEADY TRANSONIC for the blade wake. Predictions of the mathematical model are LAVAL-NOZZLE FLOW then used to interpret the instantaneous rotor blade exit flow field F. OBERMEIER (Max-Planck-lnstitut fuer Stroemungsforschung, data and demonstrate the existence of a vortex street structure in Goettingen, Federal Republic of Germany) Zeitschrift fuer the rotor blade wake. This wake vortex street flow structure is Flugwissenschaftenund Weltraumforschung (ISSN 0342-068X), vol. shown to be analogous to the unsteady flow field behind bluff 12, July-Aug. 1988, p. 253-257. refs bodies due to classical von Karman vortex shedding. V.L. Unsteady pressure waves in an otherwise stationary transonic Laval-nozzleflow are studied by the method of strained coordinates. In particular, the steepening of weak perturbations fed into the A8949167 flow in the subsonic region behind an initially stationary shock CHARACTERIZATION OF BOUNDARY LAYER CONDITIONS IN wave and their effects on the movement of this shock wave are WIND TUNNEL TESTS THROUGH IR THERMOGRAPHY predicted in terms of the amplitude and the frequency of the IMAGING perturbation. The results agree with those obtained by more GlOVANNl M. CARLOMAGNO, LUlGl DE LUCA (Napoli, Universita, extended numerical calculations. Author Naples, Italy), GUIDO BURESTI, and GlOVANNl LOMBARD1 (Pisa, Universita, Italy) IN: Applications of infrared technology; Proceedings of the Meeting, London, England, June 9. 10, 1988. Bellingham, WA, Society of Photo-Optical Instrumentation A89-19788# Engineers, 1988, p. 23-29. CNR-supported research. refs A NEW APPROACH FOR COMPUTING FULL UNSTEADY A computerized infrared (IR) imaging system is evaluated as a AERODYNAMIC CHARACTERISTICS diagnostic tool for aerodynamic research by performing ZHENGYIN YE, LINGCHENG ZHAO, and YONGNIAN YANG experimental tests in a subsonic wind tunnel. In particular, the IR (Northwestern Polytechnical University, Xian, People's Republic of technique is used to characterize the behavior of the boundary China) Acta Aeronautica et Astronautica Sinica (ISSN 1000-6893), layer on two wing models, having different cross-sections, by vol. 9, July 1988. p. A307-A312. In Chinese, with abstract in measuring the temperature distribution over their heated surfaces. English. refs The results show that IR thermography is capable of immediately A new numerical method, the velocity potential-difference yielding accurate information on the location and extent of the method, is developed for predicting the aerodynamic force on transition between laminar and turbulent flow and on the region fully unsteady wings in subsonic flow. The method is capable of of separation, for the whole boundary layer over the surface of a computing the varying aerodynamic force or velocity field in time model wing. Author domain over wings with arbitrary motion. The computed results of some test cases are compared with those of other computational A8919625' Georgia Inst. of Tech., Atlanta. methods and experiments and are found to be in good DYNAMIC INFLOW FOR PRACTICAL APPLICATIONS agreement. Author

147 A8919801# Journal of Spacecraft and Rockets (ISSN 0022-4650), voi. 25, THE RELATIONSHIP BETWEEN THE AERODYNAMIC Sept.-Oct. 1988, p. 382-384. Research supported by the Ministry CHARACTERISTICS OF DOUBLE-DELTA WINGS AND of Defence Procurement Executive. refs VORTICES WITH SIDESLIPS AT HIGH ANGLES OF ATTACK An experimental investigation has been conducted into the pitch GUOHUA BAO (Northwestern Polytechnical University, Xian, stability characteristics of a plate-supported half-model in People’s Republic of China) Acta Aeronautica et Astronautica hypersonic flow that is held by an axial gas bearing; this novel Sinica (ISSN 1000-6893), vol. 9, Aug. 1988, p. 8317-8323. In support method facilitates the study of oscillation amplitudes greater Chinese, with abstract in English. than those generally available on sting support. The test program An experimental study of the aerodynamic forces on conducted indicates that the interference-free static pitch stability double-delta wings with sideslips is presented. Force, pressure, data desired at low angles of attack is not thus obtainable, due spatial flow measurements, and flow visualizations have been to the presence of the reflection plate surface ahead of the model carried out. Results show that the sideslip delays the joining vortices nose region. O.C. on the windward side, but the vortex will break down earlier; on the leeward side, the opposite is true. The asymmetric vortex A8919927 breakdown has important effects on the aerodynamic forces, and EXPERIMENTAL STUDY ON UNSTEADY AERODYNAMIC makes rolling moment unstable at high angle of attack. Author CHARACTERISTICS OF AN OSCILLATING CASCADE WITH TIP CLEARANCE A8919805# TOSHlNORl WATANABE (Tokyo University of Agriculture and MEASUREMENTS OF THE BUFFET BOUNDARY OF WINGS IN Technology, Koganei, Japan) and SHOJIRO KAJI (Tokyo, TRANSONIC FLOW WITH HOT-FILM METHOD University, Japan) JSME International Journal, Series II (ISSN QIAOSEN WANG, XUEJUN QIU, and ZHAOMING ZHANG (Nanjing 0914-8817), vOI. 31, NOV. 1988, p. 660-667. Aeronautical Institute, People’s Republic of China) Acta An experimental study was conducted for revealing unsteady Aeronautica et Astronautica Sinica (ISSN 1000-6893), vol. 9, Aug. aerodynamic characteristics of oscillating cascades with tip 1988, p. 8346-8351. In Chinese, with abstract in English. refs clearance. To obtain aerodynamic forces acting on blades, the This paper presents a new hot film method (HFM) for measuring surface pressure was measured in both the chordwise and the buffeting onset of wings, and describes the principle and spanwise directions. To evaluate the aerodynamic forces due to technique for using HFM to measure wing buffeting onset. The oscillations of arbitrary interblade phase angle, the method of experimental results are quite consistent with the available data. influence coefficients was adopted. Tip clearances were changed The present work indicates that the HFM can be used for measuring from 0.056 to 2.8 percent of the blade span. The aerodynamic the buffeting onset of wings. Author blade loading was also changed. Results show that the tip clearance has a strong influence on the distribution of unsteady A8919904# aerodynamic forces along the blade span: when tip clearance MULTIGRID ACCELERATION OF A RELAXATION exists, aerodynamic damping forces decrease considerably over a PROCEDURE FOR THE REDUCED NAVIER-STOKES large portion of the blade span. However, when steady aerodynamic EQUATIONS loading acts on the blades, the influence of tip clearance is A. HIMANSU and S. G. RUBlN (Cincinnati, University, OH) suppressed. The tip vortex increases the absolute value of the (Computational Fluid Dynamics Conference, 8th. Honolulu, HI, June unsteady aerodynamic force in the region near the blade tip. 9-11, 1987, Technical Papers, p. 478-489) AlAA Journal (ISSN Author 0001-1452), vol. 26, Sept. 1988, p. 1044-1051. Previously cited in issue 18, p. 2800, Accession no. A87-42091. refs A892Ql31# (Contract NO0014-79-C-0849; F49620-85-C-0027) A STUDY ON AERODYNAMIC HEATING IN THE INTERACTION REGIONS OF SHOCK WAVES AND A8919905# TURBULENT BOUNDARY LAYERS INDUCED BY SHARP FINS INTERACTIVE AND LARGE-DOMAIN SOLUTIONS OF MASANORI HAYASHI, SHIGERU ASO, ANZHONG TAN, and HIGHER-ORDER VISCOUS-FLOW EQUATIONS HlROAKl MURAKAMI Kyushu University, Technology Reports F. STERN, S. Y. YOO, and V. C. PATEL (Iowa, University, Iowa (ISSN 0023-2718), vol. 61, Aug. 1988. p. 465-471. In Japanese, City) AlAA Journal (ISSN 0001-1452), vol. 26, Sept. 1988, p. with abstract in English. refs 1052-1060. refs A study on aerodynamic heating in the interaction regions of (Contract NO0014-83-K-0136) shock waves and turbulent boundary layers induced by sharp fins Two approaches for the solution of the partially parabolic is performed at a Mach number of 4 and under the cold wall Reynolds equations are evaluated using the same numerical conditions. Attack angles of fins are 4, 10 and 16 degrees. Heat techniques and turbulence model. Comparisons are made between transfer distributions are measured by multilayered thin film heat interactive viscous-inviscid solutions and noninteractive transfer gauges. The results of oil-flow tests and wall pressure large-domain solutions for the flow over the tail and in the wake measurements are compared with the heat transfer distributions of axisymmetric and three-dimensional bodies to highlight the in the flowfields. Heat transfer distributions at 4 and 10 degrees differences between the two strategies. Both approaches yield have a similar tendency qualitatively. Both have a peak before satisfactory results, although the interaction solutions appear to the separation line and a trough near the separation line, and at be computationally more efficient for the three-dimensional the downstream of the shock waves heat flux begins to increase bodies. Author again. At 16 degrees, where secondary separation line is observed, the heat transfer has a peak after the primary separation line, A89-19908‘# Old Dominion Univ., Norfolk, VA. and then drops till the midway to the secondary separation line, FULL-POTENTIAL INTEGRAL SOLUTION FOR TRANSONIC and two kinks are observed near the secondary separation line FLOWS WITH AND WITHOUT EMBEDDED EULER DOMAINS and near the position of the shock wave. Author OSAMA A. KANDIL and HONG HU (Old Dominion University, Norfolk, VA) AlAA Journal (ISSN 0001-1452), vol. 26, Sept. A89-20132# 1988, p. 1079-1086. Previously cited in issue 18, p. 281 0, Accession A STUDY ON HYPERSONIC SHOCK TUNNEL no. A87-42472. refs MASANORI HAYASHI, SHIGERU ASO, MASASHI MATSUMOTO, (Contract NAG1-648) and AKlO ON0 Kyushu University, Technology Reports (ISSN 0023-2718), vol. 61, Aug. 1988, p. 473-477. In Japanese, with A89-19924# abstract in English. refs INTERFERENCE EFFECTS ASSOCIATED WITH A A hypersonic shock tunnel is designed and constructed. In the PLATE-SUPPORTED HALF-MODEL IN HYPERSONIC FLOW design of nozzle contour the effect of boundary layer along the G. R. HUlT and R. A. EAST (Southampton, University, England) nozzle wall on Mach number profile in the test section is

148 02 AERODYNAMICS investigated. Two contour nozzles of Mach 8, with and without A8920141# boundary layer correction, are prepared for the experiments. EXPERIMENTAL INVESTIGATION OF A JET IMPINGING ON A Cresci's method is used for the design of nozzle contour and GROUND PLANE IN CROSSFLOW Tucker's method for boundary layer correction. The results show J. M. CIMBALA, D. R. STINEBRING, A. L. TREASTER, M. L. that the development of boundar; layer along the nozzle wall is BILLET (Pennsylvania State University, University Park), and M. remarkable and the correction of boundary layer along the nozzle M. WALTERS (US. Navy, Naval Air Development Center, wall is necessary. Also, the boundary layer along the nozzle wall Warminster, PA) (International Powered Lift Conference and is overestimated by Tucker's method. The results show that a Exposition, Santa Clara, CA, Dec. 7-10, 1987, Proceedings, p. more precise boundary layer correction method should be 243-251) Journal of Aircraft (ISSN 0021-8669), vol. 25, Oct. 1988, developed. Author p. 923-931. Navy-supported research. Previously cited in issue 15, p. 2391, Accession no. A88-37195. refs

A89-20133'# JAI Associates, Mountain View, CA. A89-20142'# West Virginia Univ., Morgantown. NAVIERSTOKES CALCULATIONS OF HOVERING ROTOR WINGLETS ON LOW-ASPECT-RATIO WINGS FLOWFIELDS JOHN M. KUHLMAN and PAUL LlAW (West Virginia University, G. R. SRlNlVASAN (JAI Associates, Inc., Mountain View, CA) and Morgantown) Journal of Aircraft (ISSN 002143669), vol. 25, W. J. MCCROSKEY (NASA, Ames Research Center, Moffett Field, Oct. 1988, p. 932-941. Previously cited in issue 21, p. 3339, CA) Journal of Aircraft (ISSN 0021-8669), vol. 25, Oct. 1988, p. Accession no. A87-49097. refs 865-874. refs (Contract NAG1 -625) (Contract DAAG29-85-C-0002) (AIAA PAPER 87-2629) A89-20145'# Sterling Federal Systems, Inc., Palo Alto, CA. Unsteady, thin-layer Navier-Stokes equations written in rotor UNSTEADY TRANSONIC AERODYNAMICS AND coordinates are solved using a partially flux-split, implicit numerical AEROELASTIC CALCULATIONS AT LOW-SUPERSONIC algorithm to calculate the flowfields of a hovering rotor blade at FREESTREAMS subsonic and transonic conditions. Numerical results are in good GURU P. GURUSWAMY (Sterling Federal Systems, Inc., Palo Alto, agreement with experimental data for both nonlifting and lifting CA) and PETER M. GOORJIAN (NASA, Ames Research Center, rectangular blades. For the lifting case, the rotor wake effects are Moffett Field, CA) Journal of Aircraft (ISSN 0021-8669), vol. 25, modeled by applying a correction to the geometric angle of attack Oct. 1988, p. 955-961. USAF-sipported research. refs of the blades. Alternate methods of calculating the hovering rotor A computational procedure is presented to simulate transonic flowfields in blade-fixed mode that have the same circulation unsteady flows and corresponding aeroelasticity of wings at distribution as a hovering blade are explored. All of the results low-supersonic freestreams. The flow is modeled by using the presented in this paper were computed on a Cray-2 transonic small-perturbation theory. The structural equations of supercomputer. Author motions are modeled using modal equations of motion directly coupled with aerodynamics. Supersonic freestreams are simulated A89-20134'# National Aeronautics and Space Administration. by properly accounting for the boundary conditions based on Ames Research Center, Moffett Field, CA. pressure waves along the flow characteristics in streamwise planes. TRANSONIC NAVIER-STOKES SOLUTIONS FOR A The flow equations are solved using the time-accurate, FIGHTER-LIKE CONFIGURATION alternating-direction implicit finite-difference scheme. The coupled JOLEN FLORES, STEVEN G. REZNICK, TERRY L. HOLST (NASA, aeroelastic equations of motion are solved by an integration Ames Research Center, Moffett Field, CA), and KAREN GUNDY procedure based on the time-accurate, linear-accelerationmethod. Journal of Aircraft (ISSN 0021 -8669), vol. 25, Oct. 1988, p. 875-881. The flow modeling is verified by comparing calculations with Previously cited in issue 09, p. 1191, Accession no.. A87-24906. experiments for both steady and unsteady flows at supersonic refs freestreams. The unsteady computations are made for oscillating wings. Comparisons of computed results with experiments show good agreement. Aeroelastic responses are computed for a A89-20137"# Douglas Aircraft Co., Inc., Long Beach, CA. rectangular wing at Mach numbers ranging from subtransonic to FURTHER COMPARISONS OF INTERACTIVE upper-transonic (supersonic) freestreams. The extension of the BOUNDARY-LAYER AND THIN-LAYER NAVIER-STOKES transonic dip into the upper transonic regime is illustrated. PROCEDURES Author K. C. CHANG, TUNCER CEBECI (Douglas Aircraft Co., Long Beach, CA), N. ALEMDAROGLU (California State University, Long Beach), A8920147# and UNMEEL MEHTA (NASA, Ames Research Center, Moffett LOW-SPEED PRESSURE DISTRIBUTION ON AXISYMMETRIC Field, CA) Journal of Aircraft (ISSN 0021-8669), vol. 25, Oct. ELLIPTIC-NOSED BODIES 1988, p. 897-903. Previously cited in issue 08, p. 1039, Accession ERIK S. LARSON (Flygtekniska Forsoksanstalten, Bromma, no. A87-22625. refs Sweden) Journal of Aircraft (ISSN 0021-8669), vol. 25, Oct. 1988, p. 969, 970. Research sponsored by the Swedish Armed A8920140# Forces. VALIDATION OF APPROXIMATE INDlClAL AERODYNAMIC A semiempirical representation of the pressure distribution of FUNCTIONS FOR TWO-DIMENSIONAL SUBSONIC FLOW ellipsoids of revolution and elliptic-nosed semiinfinite bodies of J. G. LEISHMAN (Maryland, University, College Park) Journal of revolution in axial incompressible potential flow. These analytic Aircraft (ISSN 0021-8669), vol. 25, Oct. 1988, p. 914-922. expressions, which are obtained by the peak velocity ratio and Army-supported research. refs the normalized thickness-dependent angle between body axis and Approximations for two-dimensional indicial (step) aerodynamic radius vector, should prove satisfactory for the rapid estimation of responses due to angle of attack and pitch rate are obtained and velocity and pressure distributions in the cases of nose-slenderness generalized to account for compressibility effects up to a Mach ratios up to and including unity. O.C. number of 0.8. Using the Laplace transform method, these indicial functions are manipulated to produce explicit solutions for idealized A8920148# harmonic forcings. These explicit solutions are subsequently THREE-DIMENSIONAL VORTEX SYSTEMS OF FINITE WINGS compared with experimentally obtained pitch and plunge PETER FREYMUTH (Colorado, University, Boulder) Journal of aerodynamic data in the reduced frequency domain. The results Aircraft (ISSN 0021-8669), vol. 25, Oct. 1988, p. 971, 972. refs of this comparison are used to relate back and substantiate the (Contract F49620-84-C-0065) generalization of the compressible indicial lift and moment Global flow-visualizations, in which the flow-trace functions. Author smoke-producing titanium tetrachloride is introduced as

149 02 AERODYNAMICS homogeneously as possible into areas of vorticity production, are A89-2018 1# capable of documenting the connection and reconnection of VORTICAL WAKES OVER A PROLATE SPHEROID vortices. Attention is given to the photographically recorded results C. E. COSTIS and D. P. TELlONlS (Virginia Polytechnic Institute thus obtained for half-wings and delta-wings. Complete flow and State University, Blacksburg) AlAA Journal (ISSN 0001-1452), resolution is noted to remain an elusive goal; it becomes impossible vol. 26, Oct. 1988, p. 1189-1193. Previously cited in issue 22, p. in a strongly turbulent regime. O.C. 3179, Accession no. A84-46120. refs (Contract NO0167-844-0044) A8920149# ROTATING AIR SCOOP AS AIRFOIL BOUNDARY-LAYER A8920182# C0 N T R0 L INTERACTIONS BETWEEN TURBULENT WAKES AND F. MOKHTARIAN, V. J. MODI, and T. YOKOMIZO (British Columbia, BOUNDARY LAYERS University, Vancouver, Canada) Journal of Aircraft (ISSN D. AGOROPOULOS and L. C. SQUIRE (Cambridge University, 0021-8669), vOI. 25, Oct. 1988, p. 973-975. England) AlAA Journal (ISSN 0001-1452), vol. 26, Oct. 1988, p. (Contract NSERC-A-2181) 1194-1200. refs An evaluation is made of the results of an experimental program Experimental measurements and numerical computations are aimed at determining the effectiveness of a scooped-cross section presented for five cases of two-dimensional turbulent wakes mixing configuration of leading edge rotating cylinder on a Joukowsky with boundary layers. These were set up so as to simulate the airfoil. Although the rotating airscoop appears to redirect more air positive streamwise pressure gradient and wake structure found over the upper surface, the higher rates of cylinder rotation cause on multielement aerofoils. The algebraic stress turbulence model it to behave as a simple, unscooped cylinder, precluding the of Rodi, in conjunction with the boundary-layer equations, lower-rotation flow advantages. O.C. successfully postdicted all five test cases, outperforming an improved version of the k-epsilon model. A minor failure of both methods to postdict accurately the edge of the wake may be A89-20176"# JAI Associates, Mountain View, CA. attributed to its intermittency. Author NUMERICAL SIMULATION OF TIP VORTICES OF WINGS IN SUBSONIC AND TRANSONIC FLOWS A8920184# G. R. SRlNlVASAN (JAI Associates, Inc., Mountain View, CA), W. TIME-ITERATIVE SOLUTIONS OF VISCOUS SUPERSONIC J. MCCROSKEY, J. D. BAEDER, and T. A. EDWARDS (NASA, NOZZLE FLOWS Ames Research Center, Moffett Field, CA) AlAA Journal (ISSN CHAU-LYAN CHANG, YIGAL KRONZON, and CHARLES L. 0001-1 452), vol. 26, Oct. 1988, p. 1153-1 162. Previously cited in MERKLE (Pennsylvania State University, University Park) AlAA issue 17, p. 2469, Accession no. A86-38456. refs Journal (ISSN 0001-1452), vol. 26, Oct. 1988, p. 1208-1215. (Contract DAAG29-85-C-0002) USAF-sponsored research. Previously cited in issue 18, p. 2806, Accession no. A87-42364. refs A89-20179# COMPUTATION OF ROTATIONAL TRANSONIC FLOWS USING A8920235 A DECOMPOSITION METHOD NUMERICAL METHODS FOR HYPERSONIC FLOWS K. GIANNAKOGLOU, P. CHAVIAROPOULOS, and K. D. [NUMERISCHE METHODEN FUER PAPAlLlOU (Athens, National Technical University, Greece) AlAA HYPERSCHALLSTROEMUNGEN] Journal (ISSN 0001-1452), vol. 26, Oct. 1988, p. 1175-1 180. C. WEILAND (Messerschmitt-Boelkow-Blohm GmbH, Munich, Research supported by Avions Marcel Dassault Breguet Aviation. Federal Republic of Germany), H. OERTEL (DNLR, lnstitut fuer refs theoretische Stroemungsmechanik, Goettingen, Federal Republic Any vector field may be decomposed, in a unique way, into an of Germany), and 6. WAGNER (Dornier GmbH, Friedrichshafen, irrotational and a rotational part, if appropriate boundary conditions Federal Republic of Germany) IN: Yearbook 1987 II; DGLR, are imposed to the scalar and vector potentials introduced by the Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, above decomposition. In the present work, the transformation is 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und applied to the mass flux vector, in order to calculate Raumfahrt, 1987, p. 691-703. In German. refs two-dimensional, steady, rotational, transonic flows in arbitrarily (DGLR PAPER 87-084) shaped ducts and plane cascades. The whole procedure is Numerical studies in hypersonic flows are necessary for the discussed from an analytical and a numerical point of view, while development of future spacecraft. The types of such spacecraft finite difference-finitevolume schemes are used to derive numerical are reviewed, and the very complex physical phenomena involved results. Author in hypersonic flows are considered. The relevant theoretical and numerical prediction methods are examined, including the A89-20180'# North Carolina State Univ., Raleigh. continuum region Euler, boundary layer, viscous shock layer, and NAVIERSTOKES CALCULATIONS USING CARTESIAN GRIDS. Navier-Stokes procedures as well as the gas-kinetic region I - LAMINAR FLOWS simulation methods for solving the Boltzmann equations. Solutions PAUL D. FRYMIER, JR.. H. A. HASSAN (North Carolina State using these methods for hypersonic flows about test configurations University, Raleigh), and M. D. SALAS (NASA, Langley Research and realistic spacecraft are addressed. It is shown that a significant Center, Hampton, VA) AlAA Journal (ISSN 0001-1452), vol. 26, development step involves extending these methods to real gas Oct. 1988, p. 1181-1188. refs flows. C.D. (Contract NCC1-22) A finite-volume formulation for the Navier-Stokes equations A89-20311# using Cartesian grids is used to study flows past airfoils. In addition MOVING WALL EFFECTS IN UNSTEADY FLOW to the solution of the complete equations, solutions for two L. E. ERICSSON (Lockheed Missiles and Space Co., Inc., simplified versions of the governing equations were obtained and Sunnyvale, CA) Journal of Aircraft (ISSN 0021-8669). vol. 25, compared with those using body-fitted grids. Results are presented Nov. 1988, p. 977-990. Previously cited in issue 08, p. 1052, for two airfoil sections, NACA 0012 and RAE 2822, for a range of Accession no. A87-22504. refs Mach numbers, angles of attack, and Reynolds numbers. It is shown that the results are highly dependent on the smoothness A89203 12# of the surface grid. Without such smoothness, the skin friction VORTEX BREAKDOWN MEASUREMENTS ON A 70 DEG and pressure converge to nonuniform distributions. On the other SWEEPBACK DELTA WING hand, when surface cells with smoothly varying areas are used, JOHN F. MCKERNAN, FRANCIS M. PAYNE, and ROBERT C. the results compared favorably with calculations employing NELSON (Notre Dame, University, IN) Journal of Aircraft (ISSN body-fitted grids. Author 0021-8669), vol. 25, Nov. 1988, p. 991, 992. refs

150 02 AERODYNAMICS

An investigation of the breakdown of the leading edge vortices with 5 load cells and flow is visualized with oil flow technique and on a flat plate delta wing having a leading edge sweep angle of mini-tuft method. Their aerodynamic characteristics have strong 70 deg was studied using flow visualization and surface pressure nonlinearities especially in side-force coefficient. Presence of the measurements. The progression of the vortex breakdown position side force is related to that of the maximum normal force coefficient was determined from flow visualization experiments as a function which can be seen from oil flow patterns. Author of angle of attack and sideslip angle and correlated with the force and moment data obtained from integrating surface pressure N8913395'# National Aeronautics and Space Administration. measurements. Tests were conducted at low subsonic speeds, Langley Research Center, Hampton, VA. and the Reynolds number, based upon the centerline chord, was A WATER TUNNEL STUDY OF GURNEY FLAPS 225,000. Vortex breakdown was observed to play a strong role in DAN H. NEUHART (PRC Systems Services Co., Hampton, Va.) the nonlinear behavior of the rolling moment. Author and ODlS C. PENDERGRAFT, JR. Nov. 1988 21 p Original contains color illustrations A89-20313# (NASA-TM-4071; L-16467; NAS 1.15:4071) Avail: NTlS HC DOWNSTREAM VORTICITY MEASUREMENTS FROM A03/MF A01 CSCL 01A ULTRASONIC PULSES Several Gurney flap configurations were tested in the NASA WOLFGANG SEND (DFVLR, lnstitut fuer Aeroelastik, Goettingen, Langley 16 x 24 inch Water Tunnel. These devices provided an Federal Republic of Germany) (ICAS, Congress, 15th, London, increased region of attached flow on a wing upper surface relative England, Sept. 7-12, 1986, Proceedings. Volume 2, p. 1190-1200) to the wing without the flaps. The recirculation region behind the Journal of Aircraft (ISSN 0021-8669), vol. 25, Nov. 1988, p. 993, flap was visualized and shown to be consistent with hypotheses 994. Previously cited in issue 24, p. 3532, Accession no. stated in previous research. Although the test Reynolds number A86-49102. refs for this study was several orders of magnitude below those in previous investigations, the effect of the Gurney flaps is in A8920316*# Texas A&M Univ., College Station. qualitative agreement with them. This is as would be expected TRANSONIC WING DESIGN USING INVERSE METHODS IN from first order effects for high lift devices. Author CURVILINEAR COORDINATES THOMAS A. GALLY and LELAND A. CARLSON (Texas A & M N89-13396'# National Aeronautics and Space Administration. University, College Station) Journal of Aircraft (ISSN 0021-8669), Langley Research Center, Hampton, VA. vol. 25, Nov. 1988, p. 1009-1017. Previously cited in issue 21, p. THEORETICAL DERIVATION AND CALIBRATION TECHNIQUE 3340, Accession no. A87-49103. refs OF A HEMISPHERICAL-TIPPED, FIVE-HOLE PROBE (Contract NAG1-61 9) SCOTT 0. KJELGAARD Dec. 1988 27 p (NASA-TM-4047; L-16454; NAS 1.15:4047) Avail: NTlS HC A89203 17# A03/MF A01 CSCL 01A AERODYNAMIC CHARACTERISTICS OF RECTANGULAR A technique is presented for the calibration of a hemispherical CROSS-SECTIONAL BODIES AT M = 0.85 tipped 0.125 inch diameter 5-hole probe. The derivation of ASHER SIGAL (Technion - Israel Institute of Technology, Haifa) equations from the potential flow over a sphere relating the flow (Israel Annual Conference on Aviation and Astronautics, lath, Tel angle and velocity to pressure differentials measured by the probe Aviv and Haifa, Israel, Feb. 19, 20, 1986, Papers, p. 81-86) Journal is presented. The technique for acquiring the calibration data and of Aircraft (ISSN 0021-8669), vol. 25, Nov. 1988, p. 1018-1022. the technique used to calculate the calibration coefficients are Research supported by the Technion - Israel Institute of Technology presented. The accuracy of the probe in both the uniform calibration and Rafael Armament Development Authority. Previously cited in flow field and the nonuniform flow field over a 75 degree swept issue 14, p. 2104, Accession no. A87-35012. refs delta wing is discussed. Author A89-20319# FLOW UNSTEADINESS CONSIDERATIONS IN HIGH-ALPHA N89-13399'# Flow Research, Inc., Kent, WA. TESTING USER'S MANUAL FOR AN AERODYNAMIC OPTIMIZATION L. E. ERICSSON (Lockheed Missiles and Space Co., Inc., SCHEEME THAT UPDATES FLOW VARIABLES AND DESIGN Sunnyvale, CA) Journal of Aircraft (ISSN 002143669), vol. 25, PARAMETERS SIMULTANEOUSLY Flow Report No. 444 Nov. 1988, p. 1033-1037. Previously cited in issue 07, p. 927, MAGDl H. RlZK Jul. 1988 33 p Accession no. A88-22040. refs (Contract NAS3-24855) (NASA-CR-182180; NAS 1.26:182180) Avail: NTlS HC A03/MF A89-20325# A01 CSCL01A DRAG REDUCTION FACTOR DUE TO GROUND EFFECT This user's manual is presented for an aerodynamic optimization YOUNG B. SUH and CYRUS OSTOWARI (Texas A 8 M University, program that updates flow variables and design parameters College Station) Journal of Aircraft (ISSN 0021-8669), vol. 25, simultaneously. The program was developed for solving constrained Nov. 1988, p. 1071, 1072. refs optimization problems in which the objective function and the A theoretical working-formula is derived for the increasing constraint function are dependent on the solution of the nonlinear lift-curve slope and decreasing induced drag experienced by wings flow equations. The program was tested by applying it to the in ground effect. The derivation has its basis in Oswalds wing problem of optimizing propeller designs. Some reference to this efficiency, which is a measure of departure from the ideal elliptical particular application is therefore made in the manual. However, loading in the induced drag portion of the aerodynamic system. the optimization scheme is suitable for application to general The results obtained are compared with extant experimental data. aerodynamic design problems. A description of the approach used O.C. in the optimization scheme is first presented, followed by a description of the use of the program. Author A89-20835# EXPERIMENTAL STUDY ON LOW-SPEED AERODYNAMIC N89-13400'# Vigyan Research Associates, Inc., Hampton, VA. CHARACTERISTICS OF NON-AXISYMMETRIC SLENDER WALL ADJUSTMENT STRATEGY SOFTWARE FOR USE WITH BODIES THE NASA LANGLEY 0.3-METER TRANSONIC CRYOGENIC MASAYOSHI MATSUZAKA Japan Society for Aeronautical and TUNNEL ADAPTIVE WALL TEST SECTION Space Sciences, Journal (ISSN 0021-4663), vol. 36, no. 416, 1988, STEPHEN W. D. WOLF Nov. 1988 188 p p. 410-417. In Japanese, with abstract in English. refs (Contract NAS1-17919) Low speed aerodynamic characteristics of non-axisymmetric (NASA-CR-181694; NAS 1.26:181694) Avail: NTlS HC AO9/MF slender bodies are experimentally investigated. The model shapes A01 CSCL01A are elliptic cone, semi-circular cone and cone. The test range of The Wall Adjustment Strategy (WAS) software provides attack angle is from 0 to 90 deg. Forces/moments are measured successful on-line control of the 2-D flexible walled test section

151 02 AERODYNAMICS of the Langley 0.3-m Transonic Cryogenic Tunnel. This software table 10 of part 1. Appendix B includes plots of overall air loads package allows the level of operator intervention to be regulated vs. incidence for continuous oscillating model. A survey of the as necessary for research and production type 2-D testing using runnumbers of these plots is given in table 11 of part 1. GRA and Adaptive Wall Test Section (AWTS). The software is designed to accept modification for future requirements, such as 3-0 testing, N89-13403# General Dynamics/Fort Worth, TX. with a minimum of complexity. The WAS software described is an UNSTEADY LOW-SPEED WINDTUNNEL TEST OF A STRAKED attempt to provide a user friendly package which could be used DELTA WING, OSCILLATING IN PITCH. PART 5: POWER to control any flexible walled AWTS. Control system constraints SPECTRAL DENSITY PLOTS OF THE OVERALL LOADS FOR influence the details of data transfer, not the data type. Then this HARMONIC OSCILLATION AND THE RESPONSE OF entire software package could be used in different control systems, OVERALL LOADS TO (140s) INPUTS Final Report, Jun. 1985 if suitable interface software is available. A complete overview of - Aug. 1987 the software highlights the data flow paths, the modular architecture A. M. CUNNINGHAM, JR., R. G. DEN BOER, C. S. DOGGER, E. of the software and the various operating and analysis modes G. GEURTS, and A. J. PERSOON Apr. 1988 292 p Prepared available. A detailed description of the software modules includes in cooperation with National Aerospace Lab., Amsterdam listings of the code. A user’s manual is provided to explain task (Netherlands) generation, operating environment, user options and what to expect (Contract F33615-85-(3-3013) at execution. Author (AD-A198683; AFWAL-TR-87-3098-PT-5) Avail: NTlS HC A13/MF A01 CSCL 01A Results are discussed of a wind tunnel test of an oscillating N89-13401*# Analytical Services and Materials, Inc., Hampton, straked wing. The report provides unsteady airloads and pressure VA. distributions for a range of incidences (-8 to 50 deg) and amplitudes DEVELOPMENT OF THREE-DIMENSIONAL CODE FOR THE (1 to 16 deg). The wind speed was 80 meters/second, which ANALYSIS OF JET MIXING PROBLEM. PART 1: LAMINAR provided reduced frequencies up to 0.50 based on root chord. SOLUTION The zeroth and first harmonic as well as the continuous time KHALED S. ABDOL-HAMID Washington NASA Dec. 1988 history of the pressure and overall loads were measured. Flow 49 P visualization was performed for flow of 30 meters/second using a (Contract NASl-18599) pulsating laser light sheet. The power spectral densities for various (NASA-CR-4200; NAS 1.26:4200) Avail: NTlS HC A03/MF A01 conditions present the relative frequency content of selected overall CSCL 01A loads at continuous oscillating model conditions ranging from nearly Future aircraft will eventually feature nonaxisymmetric or linear (first harmonic dominant) to highly nonlinear (many higher rectangular nozzles. Developing a three-dimensional code to harmonics) characteristics. A survey of the selected runs and their stimulate the characteristics of the jet exhaust plume, issuing from test conditions is given including the components of the balance nonaxisymmetric nozzles, in general, at different flight conditions, and the corresponding plot numbers of the spectra presented. is very important. Two three-dimensional codes were developed The time history plots are given of incidence and all air loads for to simulate the shock-cell structure of circular nozzles. These codes (1-cos) pitch pulses that simulate transient aircraft maneuvers. were developed to solve the parabolized and simplified Included are half pulse data which represent a pitch-up and hold Navier-Stokes equations respectively. Both codes are based on a at a higher angle of attack as well as a pitch-down and hold at a method previously developed by Newsome et al. These codes lower angle of attack. To give an idea of the reproducibility plots are fully vectorized on the VPS 32 at NASA Langley Research for all three runs of the balance components vs. incidence for Center. The axisymmetric underexpanded supersonic jet flow two test conditions are also enclosed at the end. GRA problem, exhausting into still air, was used as a test case for developing an efficient three-dimensional problems and preserving crossplane symmetry of the flow downstream of the jet exit. N89-13404# General Dynamics/Fort Worth, TX. Author UNSTEADY LOW-SPEED WINDTUNNEL TEST OF A STRAKED DELTA WING, OSCILLATING IN PITCH. PART 6 PRESENTATION OF THE VISUALIZATION PROGRAM Flnal N89-13402# General DynamicdFort Worth, TX. Report, Jun. 1985 - Aug. 1987 UNSTEADY LOW-SPEED WINDTUNNEL TEST OF A STRAKED A. M. CUNNINGHAM, JR., R. G. DEN BOER, C. S. DOGGER, E. DELTA WING, OSCILLATING IN PITCH. PART 4 PLOTS OF G. GEURTS, and A. J. PERSOON Apr. 1988 108 p TIME HISTORIES OF PRESSURES AND OVERALL LOADS (Contract F33615-85-C-3013) Flnal Report, Jun. 1985 - Aug. 1987 (AD-A198684; AFWAL-TR-87-3098-PT-6) Avail: NTlS HC A. M. CUNNINGHAM, JR., R. G. DEN BOER, C. S. DOGGER, E. AO6/MF A01 CSCL 01A G. GEURTS, and A. J. PERSOON Apr. 1988 274 p Prepared Results of a wind tunnel test of an oscillating straked wing in cooperation with National Aerospace Lab., Amsterdam are presented. The report provides unsteady airloads and pressure (Netherlands) distributions for a range of incidence (-8 to 50 deg) and amplitudes (Contract F33615-85-C-3013) (1 to 16 deg). The wind speed was 80 meters/second, which (AD-A198682; AFWAL-TR-87-3098-PT-4) Avail: NTlS HC provided reduced frequencies up to 0.50 based on root chord. A12/MF A01 CSCL 01A The zeroth and first harmonic as well as the continuous time Results of a wind tunnel test of an oscillating straked wing. history of the pressure and overall loads were measured. Flow The report provides unsteady airloads and pressure distributions visualization was performed for flow of 30 meters/second using a for a range of incidences (-8 to 50 deg) and amplitudes (1 to 16 pulsating laser light sheet. In part 6 results of the flow visualization deg). The wind speed was 80 meters/second, which provided investigation are presented in. the appendix in the form of tables reduced frequencies up to 0.50 based on root chord. The zeroth and plots of vortex core positions, both as a function of phase and first harmonic as well as the continuous time history of the angle during one cycle of oscillation. Table 13a through c in part pressure and overall loads were measured. Flow visualization was 1 provides a convenient cross-reference of test conditions and performed for flow of 30 meters/second using a pulsating laser the table numbers in this part. The phase angles are varied in light sheet. In part 4, the plots of time history data for both pressures Steps on 45 deg so that a time history is developed during one and overall air loads for continuous oscillating model are presented cycle. When it was impossible to measure vortex core positions, for conditions in which non-linearities and higher harmonics are due to either vortex burst or overexposure, no values are given in expected. Appendix A includes the pressure plots in a carpet the tables and plots. Results are presented for the three laser format which shows the distributions at every 45 deg of phase light screen positions. The entries in the table for the aft position angle in a manner similar to the unsteady flow visualization photos. near the wing trailing edge are limited because very few core The distributions are shown similarly for all four pressure sections. position measurements were possible due to vortex bursting. A survey of the test conditions and their runnumbers is given in GRA

152 02 AERODYNAMICS

N89-13405# Boeing Commercial Airplane Co., Seattle, WA. R. M. HEFFERNAN, G. K. YAMAUCHI, M. GAUBERT, and W. COUPLING LINEARIZED FAR-FIELD BOUNDARY CONDITIONS JOHNSON (Johnson Aeronautics, Palo Alto, Calif.) Dec. 1988 WITH NONLINEAR NEAR-FIELD SOLUTIONS IN TRANSONIC 40 p Presented at the 14th European Rotorcraft Forum, Milano, FLOW Flnal Report, 1 Jul. 1983 - 29 Feb. 1988 Italy, 20-23 Sep. 1988 WILLIAM S. ROWE and F. E. EHLERS 29 Feb. 1988 175 p (NASA-TM-101061; A-88270; NAS 1.15:101061) Avail: NTlS HC (Contract F49620-83-C-0118) AO3/MF A01 CSCL 01C (AD-A198721; D6-52895; AFOSR-88-0719TR) Avail: NTlS HC The forces and moments at the rotor hub of an Aerospatiale AOB/MF A01 CSCL 01A SA34912 helicopter were investigated. The study included three Research has been conducted to evaluate the feasibility of main topics. First, measured hub forces and moments for a range coupling linearized far-field solutions with near-field finite difference of level flight conditions (mu = 0.14 to 0.37) were compared with equations to reduce the number of unknowns and thus the predictions from a comprehensive rotorcraft analysis to examine computer resources required in transonic flow calculations. For the influence of the wake model on the correlations. Second, the two dimensional flow, changes to an existing finite difference effect of changing the blade mass distribution and blade chordwise program involved distributing sources on the grid boundary in order center of gravity location on the 3/rev nonrotating frame hub loads to obtain the proper far field outgoing wave boundary conditions was studied for a high-speed flight condition (mu = 0.37). Third, on a reduced grid. Validation of the matching procedure was made the use of higher harmonic control to reduce nonrotating frame for zero thickness airfoils by comparison of the results with those 3/rev hub shear forces was investigated. The last two topics were of the kernel function method. For airfoils with finite thickness, a theoretical studies only. Author criterion based on the gradient of the flowfield Mach number was developed for establishing the minimum size finite difference region N89-13411*# Arizona State Univ., Tempe. Dept. of Mechanical necessary for accurate unsteady calculations. This approach could and Aerospace Engineering. not be applied directly to three-dimensional flow because of the DESIGN OF HIGH-REYNOLDSNUMBER FLAT-PLATE large number of variables required in the exterior solution. However, EXPERIMENTS IN THE NTF Final Report it is shown that the number of unknowns can be reduced to a WILLIAM S. SARlC 19 Dec. 1988 18 p practical number by using both source and doublet distributions (Contract NCC1-89) on the boundaries, describing these distributions with low-order (NASA-CR-184627; NAS 1.26:184627) Avail: NTIS HC AO3/MF polynomials, and using a least squares procedure to satisfy the A01 CSCL 01A matching conditions across the boundaries. GRA The design of an experiment to measure skin friction and turbulent boundary layer characteristics at Reynolds numbers N89-13408'# National Aeronautics and Space Administration. exceeding 1 x 10 to the 9th is described. The experiment will be Langley Research Center, Hampton, VA. conducted in a zero-pressure-gradient flow on a flat plate in the AERODYNAMIC DESIGN VIA CONTROL THEORY Final Report National Transonic Facility (NTF). The development of ANTONY JAMESON Nov. 1988 42 p Submitted for computational codes to analyze the aerodynamic loads and the publication blockage is documented. Novel instrumentation techniques and (Contract NASI-18107) models, designed to operate in cryogenic environments, are (NASA-CR-181749; ICASE-88-64; NAS 1.26:181749) Avail: NTlS presented. Special problems associated with aerodynamic loads, HC A03/MF A01 CSCL 01A surface finish, and hot-wire anemometers are discussed. Author The question of how to modify aerodynamic design in order to improve performance is addressed. Representative examples are N89-13412'# National Aeronautics and Space Administration. given to demonstrate the computational feasibility of using control Lewis Research Center, Cleveland, OH. theory for such a purpose. An introduction and historical survey PREDICTIONS OF AIRFOIL AERODYNAMIC PERFORMANCE of the subject is included. Author DEGRADATION DUE TO ICING ROBERT J. SHAW. MARK G. POTAPEZUK, and COLIN S. N89-13409'# National Aeronautics and Space Administration. BIDWELL 1988 16 p Presented at the 4th Symposium on Lewis Research Center, Cleveland, OH. Numerical and Physical Aspects of Aerodynamic Flows, Long LASER VELOCIMETER MEASUREMENTS OF THE FLOWFIELD Beach, Calif., 16-19 Jan. 1989; sponsored by California State GENERATED BY AN ADVANCED COUNTERROTATING Univ. PROPELLER (NASA-TM-101434; E-4541; NAS 1.15:101434) Avail: NTIS HC GARY G. PODBOY and MARTIN J. KRUPAR 1989 33 p A03/MF A01 CSCL 01A Prepared for presentation at the 27th Aerospace Sciences Meeting, An overview of NASA's ongoing efforts to develop an airfoil Reno, Nev., 9-12 Jan. 1989; sponsored by AIAA icing analysis capability is developed. An indication is given to the (NASA-TM-101437; E-4525 NAS 1.15:101437; AIAA-89-0434) approaches being followed to calculate the water droplet Avail: NTlS HC A03/MF A01 CSCL 01B trajectories past the airfoil, the buildup of ice on the airfoil, and Results are presented of an investigation to measure the the resultant changes in aerodynamic performance due to the flowfield generated by an advanced counterrotating pusher leading edge ice accretion. Examples are given of current code propeller model similar to the full-scale Unducted Fan demonstrator capabilities/limitations through comparisons of predictions with engine. A laser Doppler velocimeter was used to measure the experimental data gathered in various calibration/validation velocity field in several planes normal to the centerline of the experiments. A brief discussion of future efforts to extend the model at axial stations upstream and downstream of each rotor. analysis to handle three dimensional components is included. During this investigation, blades of the F4/A4 type were installed Author on the model which was operating in a freestream Mach 0.72 regime, with the advance ratio of each rotor set at 2.80. The N89-14213*# National Aeronautics and Space Administration. measured data indicate only a slight influence of the potential Langley Research Center, Hampton, VA. field of each front rotor blade on the flowfield upstream of the THRUST-REVERSER FLOW INVESTIGATION ON A rotor. The data measured downstream of the front rotor TWIN-ENGINE TRANSPORT characterize the tip vortices, vortex sheets and potential field GREGORY M. GATLIN and P. FRANK QUINT0 Washington, nonuniformities generated by the front rotor. The unsteadiness of DC Dec. 1988 156 p the flow in the rotating frame of reference of the aft rotor is also (NASA-TP-2856; L-16426; NAS 1.602856) Avail: NTlS HC illustrated. Author AOB/MF A01 CSCL 01A An investigation was conducted in the NASA Langley 14 x 22 N89-13410'# National Aeronautics and Space Administration. foot Subsonic Tunnel to study the effects of engine thrust reversing Ames Research Center, Moffett Field, CA. on an aft-mounted twin-engine transport and to develop effective HUB LOADS ANALYSIS OF THE SA34912 HELICOPTER testing techniques. Testing was done over a fixed and a moving-belt

153 ground plane and over a pressure instrumented ground board. of using parabolic partial differential equation techniques for Free-stream dynamic pressure was set at values up to 12.2 psf, numerical grid generation for two-dimensional aerodynamic which corresponded to a maximum Reynolds number based on configurations. The contents include a discussion of grid generation the mean aerodynamic chord of 765,000. The thrust reversers concepts and schemes in the literature, iterative methods for examined included cascade, target and four-door configurations. numerical grid generation and two differential grid generation The investigation focused on the range of free-stream velocities schemes: (1) an elliptic, and (2) a parabolic scheme. A detailed and engine thrust-reverser flow rates that would be typical for mathematical and numerical representation of both schemes is landing ground-roll conditions. Flow visualization techniques were given. The main purpose in the treatment of the elliptic scheme is investigated, and the use of water or smoke injected into the to introduce the necessary transformations to provide equations reverser flow proved effective to determine the forward progression that will establish the particular parabolic scheme development. of the reversed flow and reingestion limits. When testing over a Surface singularity methods are found to be a good means for moving-belt ground plane, as opposed to a fixed ground plane, solution of potential flow problems. They can handle both single forward penetration of the reversed flow was reduced. The use of and multicomponent airfoils in analysis and design processes. The a pressure-instrumented ground board enabled reversed flow stream function approach appears to be very stable and a simple ground velocities to be obtained, and it provided a means by panel method applicable for practical initial analysis and design which to identify the reversed flow impingement point on the airfoil problems. The method provides reduction in the number of ground. Author panels in comparison with other surface singularity methods and the best results were obtained with 40 to 60 panels per airfoil N89-14216'# National Aeronautics and Space Administration. section. The modified approach for computing the actual position Ames Research Center, Moffett Field, CA. of the trailing edge provides designed airfoils with smooth shapes TWO-DIMENSIONAL AERODY NAYlC CHARACTERISTICS OF and stable design process. GRA THE OLS/TAAT AIRFOIL MICHAEL E. WATTS, JEFFREY L. CROSS, and KEVIN W. N89-14223 Technische Hogeschool, Delft (Netherlands). Faculteit NOONAN (Army Aviation Research and Development Command, der Luchtvaart- en Ruimtevaarttechniek. Hampton, VA.) Apr. 1988 92 p A WALK ALONG INTERFACES [EEN WANDELING LANGS (NASA-TM-89435; A-871 32; NAS 1.1589435) Avail: NTlS HC RAAKVLAKKEN] AOWMF A01 CSCL 01A R. J. ZWANN 1988 41 p In DUTCH Two flight tests have been conducted that obtained extension (BE817008; ISSN-9-06-275445-7; ETN-89-93456) Avail: Delft pressure data on a modified AH-1G rotor system. These two tests, University Press, Stevinweg 1, 2628 CN Delft, Netherlands the Operational Loads Survey (OLS) and the Tip Aerodynamics Aeroelasticity and its relation to other disciplines is reviewed. and Acoustics Test (TAAT) used the same rotor set. In the analysis Examples of aeroelastic problems are presented. Research items of these data bases, accurate 2-D airfoil data is invaluable, for that can play a role in the evaluation, development, and certification not only does it allow comparison studies between 2- and 3-D of aircraft types are discussed. Transonic adjacent flow, transonic flow, but also provides accurate tables of the airfoil characteristics buffet and buzz, and free vortex planes are described. Problems for use in comprehensive rotorcraft analysis codes. To provide in aircraft vibration are introduced. The investigation of flutter in this 2-D data base, a model of the OLS/TAAT airfoil was tested wind tunnels and during flight is discussed. Aeroelastic tailoring, over a Reynolds number range from 3 x 10 to the 6th to 7 x 10 active control technology, and aeroelastic designs are introduced. to the 7th and between Mach numbers of 0.34 to 0.88 in the ESA NASA Langley Research Center's 6- by 28-Inch Transonic Tunnel. The 2-D airfoil data is presented as chordwise pressure coefficient N89-14224' National Aeronautics and Space Administration. plots, as well as lift, drag, and pitching moment coefficient plots Langley Research Center, Hampton, VA. and tables. Author HIGH LIFT, LOW PITCHING MOMENT AIRFOILS Patent KEVIN W. NOONAN, inventor (to NASA) 11 Oct. 1988 19 p N89-14217'# National Aeronautics and Space Administration. Filed 5 Sep. 1986 Supersedes N87-14282 (25 - 06, p 715) Langley Research Center, Hampton, VA. (NASA-CASE-LAR-13215-1;US-PATENT-4,776,531; INVESTIGATION OF A MOVING-MODEL TECHNIQUE FOR US-PATENT-APPL-SN-904132; US-PATENT-CLASS-244-35-R; MEASURING GROUND EFFECT US-PATENT-CLASS-416-2234) Avail: US Patent and GUY T. KEMMERLY and JOHN W. PAULSON, JR. Washington, Trademark Office CSCL 01A DC Jan. 1989 35 p Two families of airfoil sections which can be used for (NASA-TM-4080; L-16481; NAS 1.1 5:4080) Avail: NTlS HC helicopter/rotorcraft rotor blades or aircraft propellers of a particular AO3/MF A01 CSCL 01A shape are prepared. An airfoil of either family is one which could A ground-based testing technique is under development for be produced by the combination of a camber line and a thickness the measurement of dynamic or time-dependent ground effects distribution or a thickness distribution which is scaled from these. which may be present during aircraft approach and landing. The An airfoil of either family has a unique and improved aerodynamic technique utilizes a model moving horizontally over an performance. The airfoils of either family are intended for use as upwardly-inclined ground plane to simulate rate of descent. Results inboard sections of a helicopter rotor blade or an aircraft were obtained in the Langley Research Center (LaRC) Vortex propeller. Research Facility (VRF) for a generic 60 delta wing and for an Official Gazette of the US. Patent and Trademark Office F-18 configuration, both with and without thrust reversing, at forward speeds up to 100 ftlsec. These same models and support hardware N89-14897'# College of William and Mary, Williamsburg, VA. were also tested in the LaRC 14 by 22 Foot Subsonic Tunnel at Dept. of Mathematics. identical conditions (but without rate of descent) with and without OPTIMIZATION OF SLENDER WINGS FOR a moving-belt ground plane to obtain data for comparison. CENTER-OF-PRESSURE SHIFT DUE TO CHANGE IN MACH Author NUMBER Abstract Only CARL M. ANDERSEN ln Hampton Inst., NASAIAmerican Society N89-14219# Air Force Inst. of Tech., Wright-Patterson AFB, for Engineering Education (ASEE) Summer Faculty Fellowship OH. Program 1988 p 36-37 Sep. 1988 NUMERICAL GRID GENERATION AND POTENTIAL AIRFOIL Avail: NTlS HC A07/MF A01 CSCL 01A ANALYSIS AND DESIGN M.S. Thesis It is observed that the center of pressure on a wing shifts as MAT0 F. SlLADlC 1988 138 p the Mach number is changed. Such shifts are in general undesirable (AD-A197972; AFIT/CI/NR-88-72) Avail: NTlS HC A07/MF A01 and are sometimes compensated for by actively shifting the center CSCL 20D of gravity of the aircraft or by using active stability controls. To The primary objective of this thesis is to explore the feasibility avoid this complication, it is desirable to design the wings of a

154 03 AIR TRANSPORTATION AND SAFETY high speed aircraft so as to minimize the extent of the A89-18910 center-of-pressure shifts. This, together with a desire to minimize DOLPHIN EATS SNOW the center-of-pressure shifts in missile control surfaces, provides JOHN A. MURPHY (Aerospatiale Helicopter Corp., Grand Prairie, the motivation for this project. There are many design parameters TX) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, which affect center-of-pressure shifts, but it is expected that the 1988, Proceedings. Alexandria, VA, American Helicopter Society, largest effects are due to the wing planform. Thus, for the sake 1988, p. 695-706. refs of simplicity, this study is confined to an investigation of thin, flat, The paper describes the solution to the engine surge problem (Le., no camber or twist), relatively slender, pointed wings flying connected with the flight of the Coast Guard HH-65A Dolphin at a small angle of attack. Once the dependence of the center of helicopter in snow. The solution chosen was an engine plenum pressure on planform and Mach number is understood, we can inlet which added a plenum chamber at the inlet of a modified expect to investigate the sensitivity of the center-of-pressureshifts engine. The plenum inlet successfully completed snow certification to various other parameters. Author testing on April 1, 1985. B.J.

A891981O# THE GENERAL RULE OF BIRDS COLLIDING AGAINST AEROPLANES AND ANTICOLLISION MEASURES 03 QlYlNG LI (Air Force PR China, Second Training School of Aviation Technology, People’s Republic of China) Acta Aeronautica et AIR TRANSPORTATION AND SAFETY Astronautica Sinica (ISSN 1000-6893), vol. 9, Aug. 1988, p. 8383-8386. In Chinese, with abstract in English. refs Bird collision is one type of the frequently occurring accidents Includes passenger and cargo air transport operations; and aircraft that threaten flight security and cause economic losses. On the accidents. basis of statistical materials from home and abroad, this article gives an analysis to the general rule of birds’ bumping against aeroplane and makes explanations and comments on some A8918883 efficient anticollision methods. Design requirements of airplanes THE DEVELOPMENT OF THE V-22 OSPREY ARMORED ENERGY-ABSORBING CREWSEAT ASSEMBLY and engines for preventing then from colliding with birds have HOWARD A. LINDSAY, JOSEPH W. COLTMAN (Simula, Inc., been given in this article as well. Author Phoenix, AZ), and CHARLIE V. EDNIE (Boeing Helicopters, Philadelphia, PA) IN: AHS, Annual Forum, 44th, Washington, A89-20314# DC, June 16-18, 1988, Proceedings. Alexandria, VA, American PERFORMANCE PREDICTION ANALYSIS FOR FULLY Helicopter Society, 1988, p. 391-397. DEPLOYED PARACHUTE CANOPIES The design and development of the crewseat for the joint T. YAVUZ (Karadeniz Technical University, Trabzon, Turkey) services V-22 Osprey tiltrotor aircraft is described. The seat is Journal of Aircraft (ISSN 0021-8669), vol. 25, Nov. 1988, p. armored for ballistic protection and energy absorbing for enhanced 995-1000. Previously cited in issue 03, p. 291, Accession no. crash survivability. As the V-22 Osprey was developed under A87-13809. refs stringent weight criteria, innovative concepts were designed into both the energy absorption mechanism and the armor system: A89-20320# the energy-absorbing support structure was bulkhead mounted to DYNAMIC TIRE/SOIL CONTACT SURFACE INTERACTION minimize weight and the armored seat bucket incorporates the MODEL FOR AIRCRAFT GROUND OPERATIONS first production use of an ultra-lightweight Spectralboron carbide W. S. PI (Northrop Corp., Hawthorne, CA) (Structures, Structural armor system. Advancements made in the design of the V-22 Dynamics, and Materials Conference, 26th, Orlando, FL, Apr. 15-17, crewseat resulted in a weight reduction of approximately 23 percent 1985, Technical Papers. Part 2, p. 321-329) Journal of Aircraft compared to current crewseats that perform the same function. (ISSN 0021-8669), vol. 25, Nov. 1988, p. 1038-1044. Research Author supported by the Northrop Independent Research and Development Program. Previously cited in issue 13, p. 1847, Accession no. A85-30358. refs A8918909 ANALYTICAL DETERMINATION AND EXPERIMENTAL COMPARISON OF PERFORMANCE DEGRADATION ON A A89-20321# HELICOPTER MAIN ROTOR DUE TO ICE ACCRETION NEW SOLUTION METHOD FOR STEADY-STATE CANOPY R. C. JOHNSON, A. A. PETERSON (Boeing Helicopters, STRUCTURALLOADS Philadelphia, PA), K. D. KORKAN (Texas A 8 M University, College W. D. SUNDBERG (Sandia National Laboratories, Albuquerque, Station), and R. K. BRllTON IN: AHS, Annual Forum, 44th, NM) Journal of Aircraft (ISSN 0021-8669), vol. 25, Nov. 1988, Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, p. 1045-1051. Previously cited in issue 03, p. 291, Accession no. American Helicopter Society, 1988, p. 683-693. refs A87-13816. refs A series of computer codes have been integrated into one (Contract DE-AC04-76DP-00789) routine to calculate the performance degradation due to ice accretion on a helicopter main rotor. Performance degradation is N89-13413# National Transportation Safety Board, Washington, found in terms of aerodynamic lift and drag increments related to DC. Bureau of Field Operations. ice formation which results in a significant rotor torque rise as a AIRCRAFT ACCIDENT REPORTS BRIEF FORMAT, US CIVIL function of time. The routine permits the calculation of the potential AND FOREIGN AVIATION, ISSUE NUMBER 4 OF 1987 flowfield, particle trajectories, and the two-dimensional energy ACCIDENTS balance which determines the type and extent of ice accumulation. 27 May 1988 399 p Aerodynamic coefficient correlations are then applied to obtain (PB88-916908; NTSB/AAB-88/08) Avail: NTIS HC A17/MF AO1; lift, drag and moment increments to be utilized in a helicopter also available on subscription, North American Continent HC performance code. A centrifugal forcelshedding model and heat $185.00/year; all others write for quote CSCL 01C transfer model are also included. This analysis has been compared Reports of selected aircraft accidents that occured in U.S. civil to actual icing data for a Boeing CH-47 helicopter in terms of and foreign aviation operations during 1987 are given in brief format. torque rise on the rotor as a function of time, with acceptable Approximately 200 general aviation and air carrier accidents agreement. Several areas for future studies are also identified contained in the publication represent a random selection. The along with suggested improvements to the current methodology. facts, conditions, circumstances and probable cause(s) for each Author accident are given. GRA

155 03 AIR TRANSPORTATION AND SAFETY

N8913414'# Virginia Polytechnic Inst. and State Univ., with AEDC, Arnold AFS, Tenn. Blacksburg. Dept. of Chemistry and Mechanical Engineering. (AD-A198941 ; AEDC-TR-87-23; DOT/FAA/CT-87/31) Avail: A FUNDAMENTAL APPROACH TO THE STICKING OF INSECT NTlS HC A04/MF A01 CSCL 01B RESIDUES TO AIRCRAFT WINGS Final Report An investigation was conducted of the requirements for setting 0. YI, N. S. EISS, and J. P. WIGHTMAN Sep. 1988 117 p icing test conditions for aircraft engine certification tests. (Contract NAG1-300) Experimental data were gathered and analyzed to determine how (NASA-CR-183041; NAS 1.26183041; REPT-118; much each of the ice scaling parameters could be allowed to CAS/CHEM-29-88) Avail: NTlS HC AO6/MF A01 CSCL 01C deviate from specified conditions without affecting the similarity of The aircraft industry is concerned with the increase of drag on the ice accretions. Also studied were how changes in the ice planes due to the sticking of insects on critical airfoil areas. The scaling parameters and changes in the icing test conditions objectives of the present study were to investigate the effects of themselves affected the resulting ice shapes. The results indicate surface energy and elasticity on the number of insects sticking that: (1) icing similitude criteria must be established in advance of onto the polymer coatings on a modified aircraft wing and to the test; (2) changes in the scaling parameters do not necessarily determine the mechanism by which insects stick onto surfaces indicate a change in the ice shape; (3) experimental data are during high velocity impact. Analyses including scanning electron useful in determining allowable changes in the icing test conditions; microscopy, electron spectroscopy for chemical analysis and (4) determination of allowable tolerances for icing test parameters contact angle measurements of uncoated and polymer coated will depend on which icing regime one is operating in; and (5) aluminum surfaces were performed. A direct relation between the scaling laws used in this report cannot solely be used to determine number of insects sticking on a sample and its surface energy tolerances in setting icing test conditions. GRA was obtained. Since the sticky liquid from a burst open insect will not spread on the low energy surface, it will ball up providing poor adhesion between the insect debris and the surface. The N89-13419# Federal Aviation Administration, Washington, DC. incoming air flow can easily blow off the insect debris and thus Office of Aviation Policy and Plans. reducing the number of insects that remain stuck on the surface. TERMINAL AREA FORECASTS FISCAL YEARS 1988-2000 Also a direct relation between the number of insect sticking onto Mar. 1988 433 p a surface and their modulus of elasticity was obtained. Author (AD-A198079; FAA-APO-88-3) Avail: NTlS HC A19/MF A01 CSCL 01E N89-13415# Science and Engineering Associates, Inc., Seattle, This report contains forecasts of aviation activity for 847 airports WA. in the United States for fiscal years 1988 to 2000. These include LIGHTNING SIMULATION TEST TECHNIQUE EVALUATION 399 airports with FAA air traffic control towers and radar approach Final Report, Sep. 1904 - Sep. 1987 control service and 14 FAA contract towers. For each airport, WILLIAM W. COOLEY and DEBORAH L. SHORTESS Oct. 1988 detailed forecasts are made for the four major users of the air 130 p traffic system: air carriers, air taxi/commuters, general aviation, (Contract DTFA03-84-C-00064) and military. Summary tables contain national, FAA regional, and (DOT/FAA/CT-87/38) Avail: NTlS HC A07/MF A01 state aviation data and other airports specific highlights. The The results of four separate lightning simulation tests on a forecasts have been prepared to meet the budget and planning specially designed test bed aircraft is documented. The simulation needs of the constituent units of the FAA headquarters and regional techniques utilized are low-level swept continuous wave, low-level offices and to provide airport-specific information that can be used fast rise pulse, moderate-level pulse, and shock-excitation. The by state and local aviation authorities, the aviation industry, as a test bed is made up of advanced composite materials with built-in whole, and the general public. GRA lightning protection and electrical equipment installations. This configuration is electrically and geometrically representative of a general aviation heavy single engine aircraft. Comparative data N89-14225# Army Aviation Engineering Flight Activity, Edwards was developed to determine the effectiveness of the four test AFB, CA. methods and used to quantify differences between them. Analysis EVALUATION OF THE IMPROVED OV-1D ANTI-ICING SYSTEM necessary to extrapolate the results of the tests to the severe Final Report, 28 Jan. - 21 Feb. 1988 lightning environment is discussed. Predicted values from computer JOSEPH MIESS, MICHAEL BLACKER, and JOSEPH models are compared with test results. Author PlOTROWSKl Apr. 1988 68 p (AD-A198438; USAAEFA-87-25) Avail: NTlS HC A04/MF A01 CSCL 01c N8913417# Army Aeromedical Research Unit, Fort Rucker, AL. The Army Aviation Engineering Flight Activity evaluated DISORIENTATION ACCIDENTS AND INCIDENTS IN U.S. ARMY U.S. the improved OV-lD anti-icing system from 28 January to 21 HELICOPTERS, 1 JANUARY 1980 30 APRIL 1987 Final - February 1988 at Duluth, Minnesota. Ten flights (6.5 hours cloud Report immersion) in artificial conditions and four flights (5.8 hours cloud P. WRNWY-JONES Mar. 1988 65 p immersion) in natural conditions were conducted. One enhancing (AD-Al98720; USAARL-88-3) Avail: NTlS HC A04/MF A01 CSCL 01c characteristics, nine deficiencies, and three shortcomings were Accident data was obtained from the U.S. Army Safety Center identified. The windshield anti-ice system, when working, enhances for all U.S. Army helicopter spatial disorientation accidents which safe mission accomplishment. The nine deficiencies were: the occurred during the period beginning on 1 January 1980 and ending inability of the pneumatic deicing system to remove wing and on 30 April 1987. During this time, there were 120 accidents caused empennage leading edge ice accumulations; the excessive number by spatial disorientation which were responsible for 37 fatalities of AC generator drive shaft failures; the ice accretion characteristics and 56 disabling injuries. Major causal factors are analyzed and of the engine inlet cowl at temperatures colder than -15 C; the recommendations made for changes in aircrew training, education ice accretion and shedding characteristics of the propeller spinner and aircraft instrumentation. Also discussed are the effects of afterbody; the numerous dropouts of one or both windshield anti-ice systems and lack of failure warning to the pilot; the numerous operations undertaken in hostile environments. GRA dropouts of the AC generators during flight, the increased pilot workload required to reset them and the distraction caused by N8913418# Sverdrup Technology, Inc., Arnold Air Force Station, illumination of the Master Caution light: the numerous converter TN. dropouts during normal operations, the increased pilot workload AN EMPIRICAL LOOK AT TOLERANCES IN SElTlNG ICING required to reset them, and the resulting pilot distractions caused TEST CONDITIONS WITH PARTICULAR APPLICATION TO by illumination of the Master Caution light; and the numerous ICING SIMILITUDE Final Report, Apr. 1986 - Jan. 1987 inverter dropouts and the ensuing delay and actions required to C. SCOTT BARTLElT Aug. 1988 57 p Prepared in cooperation reestablish flight essential and normal inverter loads. GRA

156 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

N89-14226# Aeronautical Systems Div., Wright-Patterson AFB, the channel irreducible error rate. However, since the OH. Crew Station Design Facility. carrier/multipath ratio is usually large for aeronautical applications, COMPARISON OF THE GENERAL DYNAMICS GROUND this rise in the irreducible error rate should not be interpreted as CLOBBER ALGORITHM WITH THE GCAS AND LAWS a practical limitation of aeronautical satellite communications. ALGORITHMS Flnal Report, Mar. 1986 - Apr. 1988 C.D. M. A. DIPADUA, R. GEISELHART, J. GAVERN, and P. LOVERING (Midwest Systems Research, Inc., Dayton, OH.) April. 1988 A89- 18093# 170 p RECENT STUDIES OF MLS APPLICATION (AD-A198479; ASD-TR-88-5022) Avail: NTlS HC AOB/MF A01 BARRY C. SCOT (FAA, Technical Field Office, Moffett Field, CSCL 01D CA) and TSUYOSHI GOKA (Seagull Technology, Inc., Sunnyvale, Three ground avoidance algorithms were evaluated over a CA) IN: AIAA/IEEE Digital Avionics Systems Conference, 8th, variety of mission profiles to determine their effectiveness in San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 1. avoiding Controlled Flight into Terrain (CFIT) mishaps. Eight Air Washington, DC, American Institute of Aeronautics and Force pilots flew nine data collection missions each while Astronautics, 1988, p. 283-293. subjectively evaluating the system’s nuisance warnings. During (AIM PAPER 88-3916) each mission one of the three algorithms was on-line while the This paper discusses the results of two recent simulation other two were being flown off-line. This provided a mechanism studies examining the effects of the MLS capabilities in the terminal to directly compare each algorithms’ performance over identical area environment. In the first study, multiple scenarios involving flight conditions. There were 107 crashes in the experiment ILS and MLS capabilities and using models of the New York resulting in 107 crash plots used for the comparison. The crash Terminal Areas were simulated in an effort to evaluate air traffic plots indicated no significant difference between algorithm control procedures and to identify future efforts needed to ensure performance with regard to crash frequency. The algorithms did air traffic control personnel can facilitate the use of the MLS differ slightly when performance was evaluated over specific flight capabilities. The test disclosed several procedural issues that regimes, to include diving into flat terrain, level flight into rising require further effort and showed there was a significant reduction terrain, and diving into rising terrain. Subjective evaluation of in controller workload in an all-MLS environment. The second study nuisance warnings indicate significant philosophical differences examined the use of back azimuth guidance for missed approaches between the algorithms. GRA and departures. The issues addressed included deviation display sensitivity, methods for selecting and annunciating the back azimuth N89-14227# Boeing Advanced Systems Co., Seattle, WA. function, and determining the maximum operationally acceptable FIRE EXTINGUISHING AGENT EVALUATION IN THE offset angle upon which procedures may be based. The results AIRCRAFT ENGINE NACELLE FIRE TEST SIMULATOR indicate that the MLS back azimuth signal can support use of up (AENFTS) Flnal Report, Jan. 1985 - Mar. 1987 to a 30-deg offset radial during either takeoffs or missed ALAN M. JOHNSON Jun. 1988 169 p approaches and that the switch from front to back azimuth guidance (Contract F33615-84-C-2431) should be automatic. Author (AD-A198523; D180-30962-1; AFWAL-TR-88-2022) Avail: NTlS HC AOB/MF A01 CSCL 016 A89-18127# Fire tests and extinguishant concentrationtests were conducted DIGITAL AUDIO APPLICATIONS IN BUSINESS AND using a simulated portion of the F-16 aircraft engine compartment REGIONAL AIRLINE AIRCRAFT in the Aircraft Engine Nacelle Fire Test Simulator (AENFTS) at H. W. BENINGFIELD (Rockwell International Corp., Melbourne, Wright-Patterson Air Force Base. Engine compartment ventilation FL) IN: AIAAAEEE Digital Avionics Systems Conference, 8th, airflow pressure and temperature were varied to simulate a variation San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. in altitude and ram air pressure. Combat damage simulation Washington, DC, American Institute of Aeronautics and included inflow with ambient temperature, simulating outer Astronautics, 1988, p. 528-534. compartment wall penetration and inflow at elevated temperature (AIAA PAPER 88-3958) simulating fan case perforation or engine bleed air line damage. A digital audio system for business and regional air carrier The length of time between ignition and agent release was found aircraft reduces installation complexity and noise pickup, and critical, particularly when ventilation air pressure greater than sea provides significant performance enhancements. To meet the level ambient was simulated. The existing Halon 1301 specifications marketplace requirements, a new electrical data bus concept was were found to be adequate but a revision is proposed to encourage developed to permit connecting stations freely at any points along actual agent release tests with high realism for all planned flight an electrically long bus. The same protocol and bus management conditions, discourage the use of Halon 1202 and include circuits may be used for a fiber optic version of the data bus. survivability/vulnerability considerations. GRA With most of the aircraft audio signals available in digital form, digital signal processing and computation techniques make possible both audio quality improvements and operational improvements to 04 reduce pilot workload and stress. Author A89-18143# AIRCRAFT COMMUNICATIONS AND NAVIGATION COMBINED NUMERICAL AND SYMBOLIC PROCESSING FOR AIRBORNE SURVEILLANCE Includes digital and voice communication with aircraft; air navigation THOMAS KURIEN and ADAM CAROMlCOLl (Alphatech, Inc., Systems (satellite and ground based); and air traffic control. Burlington, MA) IN: AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, American Institute of Aeronautics and A89-17183’ Jet Propulsion Lab., California Inst. of Tech., Astronautics, 1988, p. 622-631. refs Pasadena. (Contract NO0014-87-C-0757) IRREDUCIBLE ERROR RATE IN AERONAUTICAL SATELLITE (AIAA PAPER 88-3985) CHANNELS In this paper, an architecture for an airborne surveillance F. DAVARIAN (California Institute of Technology, Jet Propulsion decision aid consisting of both numerical and symbolic processing Laboratory, Pasadena) Electronics Letters (ISSN 0013-51 94), algorithms is defined and analyzed. Numerical algorithms are based vol. 24, OCt. 13, 1988, p. 1332, 1333. on the mathematics of estimation theory and are applicable to The irreducible error rate in aeronautical satellite systems is the problem of multisensor multitarget tracking and identification. experimentally investigated. It is shown that the introduction of a Symbolic algorithms are based on the domain knowledge of the delay in the multipath component of a Rician channel increases airborne surveillance mission and are applicable to the problem

157 of threat evaluation. The numerical algorithms have been are outlined, including developmental activities related to the implemented in FORTRAN and the symbolic algorithms have been validation of the concept of Automatic Dependent Surveillance implemented in PROLOG. Results obtained with a prototype of (ADS) in which aircraft navigational information is data linked from the decision aid show that evaluated threat conditions are the aircraft directly to ATC facilities. It is concluded that ATC consistent with those actually simulated. Author operational use of VHF data link has sufficient potential to warrant further consideration. Author A89-18145# MULTIPLE SAMPLE POLYGONAL CORRELATION A89-18153# ALGORITHM FOR THE DETERMINATION OF GROUND MODE S DATA LINK APPLICATIONS RESEARCH IN THE UK EMITTER LOCATION A. J. HUGHES, M. F. WORSLEY (Royal Signals and Radar S. J. FU, J. L. VIAN, and D. L. GROSE (Boeing Military Airplanes, Establishment, Malvern, England), P. A. PLAlT (Civil Aviation Wichita, KS) IN: AIAAIIEEE Digital Avionics Systems Conference, Authority, London, England), and N. WIT (Royal Aircraft 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. Establishment, Bedford, England) IN: AIAAIIEEE Digital Avionics Washington, DC, American Institute of Aeronautics and Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Astronautics, 1988, p. 640-643. refs Technical Papers. Pat? 2. Washington, DC, American Institute of (AIM PAPER 88-3987) Aeronautics and Astronautics, 1988, p. 684-688. Passive techniques to locate ground emitters from an airborne (AIAA PAPER 88-3996) platform provide threat warning to aircraft in hostile airspace while This paper summarizes three aspects of the UK program aimed maintaining the electronic silence of the vehicle. These techniques at developing a Mode S data link. Firstly, the existing experimental are based on triangulation methods and extended Kalman filters data link equipment and capability is reviewed and probable future using only bearing measurements. In this paper a new approach, enhancements discussed. Secondly, data link applications requiring which takes into consideration of the maximum measurement error air-crew access to ground data bases are considered, taking as of the sensor and approximates an area of uncertainty of the an example the provision of an automatic VOLMET service. Finally, emitter location by polygons, is proposed. The performance of the transmission and use of air-derived meteorological data is this algorithm is demonstrated by simulation results and an example described and the potential benefits discussed. Preliminary results is shown for the comparison of this algorithm and the extended obtained using an elementary wind model are presented. Author Kalman filter approach. Author A89-18154# A89-18151'# National Aeronautics and Space Administration. AIR TRAFFIC CONTROL (ATC) AND AWGROUND DIGITAL Langley Research Center, Hampton, VA. COMMUNICATIONS - DEMONSTRATION AND EVALUATION A SIMULATION STUDY OF DATA LINK MESSAGE EXCHANGE LYNNE FELLMAN and JOHN CHRIS MOODY (Mitre Corp., - FLIGHT DECK PERSPECTIVE McLean, VA) IN: AIAAIIEEE Digital Avionics Systems Conference, MARVIN C. WALLER (NASA, Langley Research Center, Hampton, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. VA) IN: AIAAIIEEE Digital Avionics Systems Conference, 8th, Washington, DC, American Institute of Aeronautics and San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. Astronautics, 1988, p. 689-694. Washington, DC, American Institute of Aeronautics and (AIAA PAPER 88-3998) Astronautics, 1988. p. 672-678. An approach for providing a data-link interface to the flight (AIAA PAPER 88-3993) crew has been designed and a prototype system built. This interface Data link message exchange for Air Traffic Control (ATC) offers is described, and its use is illustrated through a hypothetical flight the potential of increasing flight safety and efficiency by reducing scenario. The scenario, showing sample data-link transactions, communication errors and enabling more information to be covers all phases of flight: preflight, departure, en route domestic, exchanged between aircraft and ground facilities. Digital en route oceanic, and arrival. Author communication also presents an opportunity to relieve the overloading of air traffic control radio frequencies, which hampers A89-18155# efficient message exchange during peak traffic periods in many THE MODE S DATA LINK - EXPERIMENTAL WORK AND busy terminal areas. A study has been completed at NASA Langley POSSIBLE FUTURE APPLICATIONS IN WESTERN EUROPE Research Center to compare the use of data link, for tactical MAURICE E. COX (EUROCONTROL, Brussels, Belgium) IN: ATC messages and ATlS reports, to conventional voice AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, communication. The results indicate that flight crews prefer the CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, data link message exchange for routine communication with air American Institute of Aeronautics and Astronautics, 1988, p. traffic control facilities. The data link communication process, 695-703. refs however, entailed delays related to the physical characteristics of (AIAA PAPER 88-3999) the link and the nature of the interface explored in this study. Since the early 1970s, because of an anticipated growth in air Consequently, the crews preferred voice radio when exchanging traffic in Europe, studies have been undertaken by Eurocontrol to time critical messages. Author determine a suitable basis for the control of higher traffic densities in continental airspace. This work has led to proposals for a concept A89181 52# of ATC based on the use of accurate trajectory prediction OCEANIC CLEARANCE DELIVERY VIA AWGROUND DATA techniques and the automatic monitoring of traffic to minimize the LINK risk of conflict situations, which, in turn, would permit controllers SHY AITKEN (Transport Canada, Air Navigation Systems to handle a greater volume of traffic. The SSR Mode S digital Directorate, Ottawa) IN: AIAAIIEEE Digital Avionics Systems data link has been identified as having a key role in this concept, Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. and work has been undertaken to demonstrate the feasibility of Part 2. Washington, DC, American Institute of Aeronautics and using it accordingly. Author Astronautics, 1988, p. 679-683. (AIM PAPER 88-3994) A89-18156# This paper describes ongoing tests utilizing a VHF data link to THE FUTURE OF AEROMOBILE DIGITAL COMMUNICATIONS transmit Air Traffic Control (ATC) oceanic clearances from a ground RICHARD A. RUCKER and GEORGE W. FLATHERS (Mitre Corp., based automated ATC system directly to aircraft in flight. The McLean, VA) IN: AIAAAEEE Digital Avionics Systems Conference, motivation for these trials is to reduce cockpit workload, alleviate 8th, San Jose, CA, Oct. 17-20, 1988. Technical Papers. Part 2. frequency congestion through reduced pilot-controller voice Washington, DC, American Institute of Aeronautics and communications and increase integrity of information transfer. The Astronautics, 1988, p. 704-710. trial activities are described along with an explanation of the (AIAA PAPER 88-4001) operation of the total system. Enhancements that are contemplated An aeronautical telecommunications network (ATN) to provide

158 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

digital links between ground and airborne users is described and Changes in the winds over time assure that there will always illustrated with diagrams. The ATN architecture and hardware be error in wind forecasts, and forecast error is the major problem implementation are discussed, and specific types of utilization are in achieving high-accuracy arrival-time guidance by a flight considered, including links to ACARS, SatCom, and Mode S management system. Through a series of simulations, two methods systems and mixed radiotelephone and digital communication with for compensating for forecast errors are evaluated. The first ATC and AOC facilities. Examples of ATN use at different flight method, used in current systems, blends measured aircraft wind phases are provided. T.K. with forecast wind to achieve some improvement in prediction accuracy. Thsi method is found to be unsatisfactory for arrival-time A89181 57# guidance. A second method is proposed where the flight speed is DATA LINK ORGANIZATION IN MODE S SECONDARY adjusted by the current forecast error. It appears to provide SURVEILLANCE RADAR SYSTEMS - OPERATIONAL improved arrival-time performance. Author COMPATIBILITY WITH OTHER MODE S SYSTEMS A. BOLSHEV (All-Union Scientific Research Institute of Radio A89- 18180# Equipment, Leningrad, USSR) IN: AIAAAEEE Digital Avionics AUTOMATIC DEPENDENT SURVEILLANCE DATA TRANSFER Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, THOMAS D. JUDD (Boeing Commercial Airplanes, Seattle, WA) Technical Papers. Part 2. Washington, DC, American Institute of IN: AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, Aeronautics and Astronautics, 1988, p. 71 1-713. CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, (AIAA PAPER 88-4003) American Institute of Aeronautics and Astronautics, 1988, p. The current status of Mode S SSR data-link technology in the 058-864. refs USSR is briefly surveyed, and particular attention is given to (AIAA PAPER 88-3997) problems of compatibility on an international level. The major types Automatic dependent surveillance (ADS) and the newly of uplink and downlink messages are discussed, including developed and developing communication paths available to the coilision-avoidance messages, ATC service messages, aeronautical community are discussed. These paths are modeled pilot-initiated messages, and replies to ground queries. The need after the OS1 communication model. The OS1 model divides the for international standard message transmission and formatting digital communication process into seven separate functions, which protocols is indicattsd. T.K. can be conceptualizedas seven layers. Each layer's specific digital communication function is explored in this paper. The ~ standardization of the communications system allows each path ~ A89-18173# ' TERMINAL NAVIGATION FOR THE COMBAT TALON II to be open for use by applications such as ADS. Author 1 AIRCRAFT 1 N. F. TODA, S. C. FELTER, and F. H. SCHLEE (IBM, Systems A89-18 18 1# ' Integration Div., Owego, NY) IN: AIAAIIEEE Digital Avionics TERMINAL INFORMATION FOR DATA LINK Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, FREDERICK KUHL (Mitre Corp., Civil Systems Div., McLean, VA) Technical Papers. Part 2. Washington, DC, American Institute of IN: AIAAIIEEE Digital Avionics Systems Conference, 8th, San Jose, 1, Aeronautics and Astronautics, 1988, p. 809-814. CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, ' (AIM PAPER 88-4021) American Institute of Aeronautics and Astronautics, 1988, p. This paper describes the Terminal Navigation System (TNS) of 865-870. the MC-130H Combat Talon II aircraft. The system provides a (AIAA PAPER 88-4000) capability for autonomous instrument approach to landing, satisfying The Automatic Terminal Information Service (ATIS) has often i an operational need for precision landings on austere airfields. been mentioned as a candidate application of Mode Select Beacon The TNS is initiated during cruise flight, proceeds with aircraft System Data Link. It is intended that the prototype ATIS work 1 transition onto a glideslope, and ends just prior to aircraft flare station will be evaluated in an operational setting at the Atlantic I' and landing. A Kalman filter, an onboard inertial navigation unit, City, NJ, Airport. A significant part of this effort has been the FLIR, and/or a radar tracker estimate aircraft inertial position and identificationof a vocabulary for ATIS messages and the estimation velocity relative to the runway. Author of the degree to which any vocabulary would need to be adapted for use at various airports. This paper discusses the preliminary vocabulary proposed for the Atlantic City Airport, the size and '1 A89-18175# FAULT TOLERANT INERTIAL NAVIGATION SYSTEM required adaptation of ATIS vocabularies, the implications for data KEVIN VANDERWERF and KNUT WEFALD (Honeywell, Inc., link coding of ATIS messages, and the prototype work station Minneapolis, MN) IN: AIAAIIEEE Digital Avionics Systems intended to generate data link ATIS. Author I Conference, Bth, San Jose, CA, Oct. 17-20, 1988, Technical Papers. , Part 2. Washington, DC, American Institute of Aeronautics and A89-18182# Astronautics, 1988, p. 821-829. refs DEVELOPMENT OF THE TRAFFIC ALERT AND COLLISION (AIM PAPER 88-4024) AVOIDANCE SYSTEM 111 (TCAS Ill) This paper describes the sensor redundancy management LAWRENCE J. NIVERT, JOSEPH A. WALSH, and JOHN J. ' concept employed in a fault-tolerant inertial reference system. The WOJCIECH (FAA, Washington, DC) IN: AIAAAEEE Digital Avionics Systems Conference, 8th. San Jose, CA, Oct. 17-20, 1988, ~' concept uses a sensor hexad and employs separate fault detection and isolation (FDI) algorithms for navigation computations and Technical Papers. Part 2. Washington, DC, American Institute of outputs to the FCS. The FDI algorithm implementation is based Aeronautics and Astronautics, 1988, p. 871-876. refs on the generalized likelihood ratio test (GLRT). Enhancements to (AIAA PAPER 88-4002) 1 the failure isolation logic virtually eliminate the probabilities of false TCAS 111 is the most complex and versatile member of the detection and wrong isolation inherent with the basic GLRT TCAS family of airborne collision-avoidance systems currently being concept, thus making the GLRT scheme practical in the real world developed and evaluated by the FAA. TCAS 111 has the capability I of high reliability requirements. Author not only to recognize potential collision threats but also to display to the flight crew recommended horizontal and vertical escape 1 A89-18176# maneuvers for avoiding these threats. This paper provides both ARRIVAL-TIME GUIDANCE IN VARIABLE WINDS programmatic and technical overview concerning the TCAS 111 SAM LIDEN (Honeywell, Inc.. Air Transport Systems Div., Phoenix, development effort. Author AZ) IN: AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. A89-18183# Washington, DC, American Institute of Aeronautics and TCAS 111 - BRINGING OPERATIONAL COMPATIBILITY TO Astronautics, 1988, p. 830-838. AIRBORNE COLLISION AVOIDANCE (AIM PAPER 88-4025) W. DWIGHT LOVE (Mitre Corp., McLean, VA) IN: AIAAAEEE

159 Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. at least 2005 are discussed. The establishment of a 15-year period 17-20, 1988, Technical Papers. Part 2. Washington, DC, American of transition to GPS and the resoltuion of international commitments Institute of Aeronautics and Astronautics, 1988, p. 877-881. are examined. Results from evaluations the Omega system (AIM PAPER 88-4004) elements are presented, including performance statistics, TCAS II is an airborne system that can alert a pilot to the operational requirements, regional validations, propagation effects, presence of a nearby aircraft and recommend a vertical escape and the recapitalization of the Omega infrastructure. Changes to maneuver to avoid a possible midair collision. TCAS 111 is intended extend the service life of the system are considered, such as to be a more capable version of TCAS more accurate bearing redesigning or replacing transmitting station equipment, changes measurements will enable TCAS 111 to recommend escape in system monitors and system control software, and system maneuvers in the horizontal dimension in addition to the vertical propagation corrections. R.B. dimension. The paper describes the principal ways in which the TCAS 111 collision-avoidance logic has been designed to enhance A89-20117 operational acceptability. This discussion covers three major areas AERONAUTICAL SATELLITE NETWORKS of the TCAS 111 logic: threat detection, modeling of escape WALTER J. GRlBBlN (Aeronautical Radio, Inc., Annapolis, MD) maneuvers, and threat resolution. Author IN: EASCON '88; Proceedings of the Twenty-first Annual Electronics and Aerospace Conference, Arlington, VA, Nov. 9-11, A89-18751 1988. New York, Institute of Electrical and Electronics Engineers, ARCHITECTURE OF AN OPTIMAL NAVIGATION SYSTEM Inc., 1988, p. 135-138. INTEGRATING GPS [ARCHITECTURE DUN SYSTEME The design and development of a satellite-based network that OPTIMAL DE NAVIGATION INTEGRANT LE GPSl is to provide critical safety-of-life communications services to the E. TARNOWSKI (Airbus Industries, Blagnac, France) (Instituts air transport industry are described. The system uses a fully de Navigation, Congres International, Sydney, Australia, Feb. 2-5, integrated digital transmission system for cockpit and passenger 1988) Navigation (Paris) (ISSN 0028-1530), vol. 36, Oct. 1988, p. voice and data. The voice-transmission system provides for multiple 437-449. In French. channels of near-toll-quality communications using 8-9.6-kb/s In the early 199Os, GPS shall be fully operational. The voice-coding algorithms. Applications of this system are discussed, advantages and performance of this system are predicted to be and attention is given to the number and locations of satellites, outstanding; however, GPS will be one unit among an overall network capacity, avionics, the ground segment, and network navigation system. Thus it must be properly integrated in order to interoperability. Also provided is a description of the take maximum benefit out of its qualities. Author near-term-service development plans for aviation satellite services. LE. A8918753 RADIONAVIGATION NEEDS FOR THE EUROPE OF THE A89-20122 FUTURE [BESOINS EN RADIONAVIGATION POUR L'EUROPE AN OVERVIEW OF SPACE-BASED RADIONAVIGATION DE DEMAIN] SYSTEMS JEAN FOURNIER (Institut Francais de Navigation, Paris, France) ALISON K. BROWN and JOHN W. LAVRAKAS (NAVSYS Corp., Navigation (Paris) (ISSN 0028-1530). vol. 36, Oct. 1988, p. 508-516. Monument, CO) IN: EASCON '88; Proceedings of the Twenty-first In French. Annual Electronics and Aerospace Conference, Arlington, VA, Nov. Present and projected radionavigation systems are described, 9-11, 1988. New York, Institute of Electrical and Electronics and the European radionavigation needs for the 1990s are Engineers, Inc., 1988, p. 161-171. refs discussed. Systems such as GPS. VOR, and DME aid in the A survey of the major space-based radio navigation systems optimization and guidance of commercial aircraft flights. It is currently operating or in development is presented, considering predicted that in the future, Loran C will be used for coastal their design, capabilities, and current status. The basic principles navigation, fishing monitoring, and merchant marine applications. of space-based radio navigation are described. Orbital A hybrid NavstarIGPS-Loran C system will be used for general characteristics, signal structure, accuracy, and coverage are and transport aviation, and ground based systems will be used examined for the following systems: Transmit, NavstarIGPS, for such applications as fire fighting and mobile position location. Glonas, Starfix, Geostar, and ESA Navsat. I.E. R.R. A89-20123# A8918754 AN OVERVIEW OF THE FEDERAL RADIONAVIGATION PLAN SPECIAL COMMITTEE ON FUTURE AIR NAVIGATION LARRY V. GRANT (DOT, Research and Special Programs SYSTEMS (FANS) [COMITE SPECIAL DES FUTURS Administration, Washington, DC) IN: EASCON '88; Proceedings SYSTEMES DE NAVIGATION AERIENNE /F.A.N.S./] of the Twenty-first Annual Electronics and Aerospace Conference, OLlVlER CAREL (Service Technique de la Navigation Aerienne, Arlington, VA, Nov. 9-11, 1988. New York, lnstitute of Electrical Paris, France) Navigation (Paris) (ISSN 0028-1530), vol. 36, Oct. and Electronics Engineers, Inc., 1988, p. 173-177. refs 1988, p. 517-527. In French. A brief review of FRP (the US. Federal Radionavigation Plan) The recommendations of the ICAO committee on future history is presented. Current and future federal requirements for navigation systems for the next 25 years are presented, radionavigation systems and the status of the GPS and its possible emphasizing new satellite technology. The present insufficiency impact on existing systems are addressed. Issues such as the and future evolution of communications, navigation, and role of the private sector and uses other than navigation, that surveillance (CNS) systems are discussed in detail. It is suggested appeared for the first time in the 1986 FRP, are highlighted. The that future air traffic control needs can be fulfilled by improvement radionavigation users' conference held in Washington DC in March of data transmission between users, extension of existing 1988 and other user-oriented actions are discussed. LE. surveillance coverage, and the use of advanced data treatment systems. Future CNS systems will include automatic dependent A89-20239 surveillance, secondary surveillance radar, and a satellite-based FLIGHT GUIDANCE TECHNOLOGY 4 mobile aeronautical service. R.R. [FLUGFUEHRUNGSTECHNIK] I G. SCHAENZER (Braunschweig, Technische Universitaet, A8919867 Brunswick, Federal Republic of Germany) IN: Yearbook 1987 II; OMEGA NAVIGATION SYSTEM - A STATUS REPORT DGLR, Annual Meeting, Berlin, Federal Republic of Germany, Oct. ROBERT J. WENZEL (USCG, Omega Navigation System Center, 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und Alexandria, VA) Navigation (ISSN 0028-1522), vol. 35, Fall 1988, Raumfahrt, 1987, p. 738-761. In German. refs p. 309-315. refs (DGLR PAPER 87-119) Plans to continue operating the Omega Navigation System until Technological developments and problems in the area of flight

160 ~~ ~~

05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE guidance are discussed. Advances made in sensors and HARRY HOPKINS Flight International (ISSN 0015-371 0), vol. measurement technology, data processing, and communications 134, NOV.12, 1988, p. 25-31. as they relate to flight guidance are considered. Problems Flight test impressions are presented for the third production encountered in flight guidance in a high-wind environment, including 8747-400 airliner, which is being used as the test platform for the takeoff and landing and safety-enhancement measures. are candidate propulsion system RB.211-524G turbofans (CF6-8OC2 examined. C.D. or PW4000 turbofans are additional candidates). The B747-400 is the worlds longest-range airliner; since a relief crew will often be N89-14228'# Systems Technology, Inc., Hawthorne, CA. needed, full crew rest facilities have been provided for both cockpit AUTONOMOUS RPRV NAVIGATION, GUIDANCE AND and cabin crewmembers. In addition, the cockpit is fitted for long CONTROL hours of operation without a third crewmember. Comparative data DONALD E. JOHNSTON, THOMAS T. MYERS, and JOHN W. are furnished for the performance of the three candidate engines, ZELLNER Mar. 1983 170 p and a cut-away drawing is provided. O.C. (Contract NAS4-2896) (NASA-CR-179425; NAS 1.26:179425; TR-1180-1) Avail: NTlS A89-18350 HC AOB/MF A01 CSCL 17G NEW DESIGN, PRODUCTION TOOLS WILL PLAY KEY ROLE Dryden Flight Research Center has the responsibility for flight IN 8-2 COST testing of advanced remotely piloted research vehicles (RPRV) to WILLIAM B. SCOTT Aviation Week and Space Technology (ISSN explore highly maneuverable aircraft technology, and to test 0005-2175), vol. 129, Dec. 5, 1988, p. 18-22. advanced structural concepts, and related aeronautical Novel CAD/CAM and CIM processes developed under USAF technologies which can yield important research results with sponsorship for the 8-2 program at a cost of about $1 billion significant cost benefits. The primary purpose is to provide the feature a three-dimensional computer graphics system that links preliminary design of an upgraded automatic approach and landing the primary contractor to both the USAF and all its subcontractors. control system and flight director display to improve landing This system is being credited with the substantial reduction of the performance and reduce pilot workload. A secondary purpose is time and cost involved in design, fabrication, assembly, inspection, to determine the feasibility of an onboard autonomous navigation, and testing. Among the consequences of this system's use are orbit, and landing capability for safe vehicle recovery in the event the virtual elimination of master tooling, the use of the same data of loss of telemetry uplink communication with the vehicles. The base by all concerned parties, near-perfec? dixensioning o! current RPRV approach and landing method, the proposed components, and direct generation of technical manuals by the automatic and manual approach and autoland system, and an data base. O.C. autonomous navigation, orbit, and landing system concept which is based on existing operational technology are described. Author A89 18752 THE UNUSED STRATEGIC TOOL - THE AIRSHIP [L'OUTIL STRATEGIQUE 'MANQUANT' - LE DIRIGEABLE] 05 JEROME SINET (Societe Dirigeables-Espace, France) Navigation (Paris) (ISSN 0028-1530), vol. 36, Oct. 1988, p. 471-483. In AIRCRAFT DESIGN, TESTING AND French. PERFORMANCE The characteristics of the 10 existing gas-propelled airships, and possible applications beyond their current use for advertising, are discussed. The present airships range in volume from about Includes aircraft simulation technology. 5500 to 7000 cu m, and they are currently limited to a maximum of 20 hours of flight. Airships can carry radar antennas of up to 18 m, and they can be used for the routine surveillance of regicns A8817624 of the order of 200 miles in diameter, the modeling of risk zones DESIGNING HYDRAULIC SYSTEMS FOR SURVIVABILITY above industrial sites, and remote sensing. The characteristics of JAMES H. BRAHNEY Aerospace Engineering (ISSN 0736-2536), a projected airship of over 10,000 cu m volume, a maximum speed vOI. 8, NOV.1988, p. 11-14. of 130 km/hr, a mission length of 100 hours (at an average speed An account is given of novel criteria in the design practices of 70 km/hr), and a capacity for carrying over 12 passengers is used for the armoring and subsystem-features design of military described. R.R. aircraft hydraulic systems, in order to improve aircraft survivability in combat scenarios without compromise of performance levels. Attention is given to the concept of 'proximity armoring', which A89-18854 protects only critical components. Proximity armoring is added in ROTOR/AIRFRAME INTERACTIONS ON TILTROTOR locations where the lines of independent hydraulic systems cross AIRCRAFT generally, and specifically in locations where a single hit could MICHAEL A. MCVEIGH, WILLIAM K. GRAUER, and DAVID J. cause a catastrophic malfunction of the system. O.C. PAISLEY (Boeing Helicopters, Philadelphia, PA) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, Proceedings. A8918346 Alexandria, VA, American Helicopter Society, 1988, p. 45-55. SIZING UP THE 146-300 refs HARRY HOPKINS Flight International (ISSN 0015-3710), vol. The aerodynamic interactions between the rotors and the 134, OCt. 22, 1988, p. 19-25. airframe of tiltrotor aircraft are discussed. Data obtained from A design features account and flight test report are presented powered scale model tests are presented and compared with other for the BAe 146-300 four-turbofan commuter airliner, whose 8-foot test data and with analysis. It is shown that significant interactions fuselage stretch over older versions of the 146 family will expand exist between the rotor and the airframe in all modes of flight passenger capacity to 112 in six-abreast configuration. The present and that these interactions influence performance. The effects of assessment praises landing gear softness as well as the cockpit's the direction of rotor rotation on wing download in hover and on roominess and the design layout of the instruments suite. In addition airplane lift and drag are described and explained. Author to a cut-away drawing, tabular comparative data are presented for the 146-300 and its current commercial competitors, the F100, A8918863 MD-87, and 8737-500 commuter airliners. O.C. AIRFRAME AND PROPULSION ASSESSMENT OF ALTERNATIVE LIGHT HELICOPTER TECHNOLOGIES (LHX) A8918349 KAYDON A. STANZIONE and RANDALL F. SMITH (Praxis BOEING 747-400 - FLIGHT TEST Technologies Corp., Woodbury, NJ) IN: AHS, Annual Forum,

161 44th. Washington, DC, June 16-18, 1988, Proceedings. Alexandria, AZ) IN: AHS, Annual Forum, 44th, Washington. DC, June 16-18, VA, American Helicopter Society, 1988, p. 159-188. refs 1988, Proceedings. Alexandria, VA, American Helicopter Society, This paper describes the methodology and results of an 1988, p. 293-304. refs independent assessment of the alternative airframes and propulsion This paper addresses the formulation of a generalized systems which could be used to satisfy the US. Army's light rotor-fuselage coupling procedure using impedance matching in helicopter mission requirements. This paper provides an the frequency domain. The use of the transfer matrix approach to assessment of technologies applicable for advanced vehicle design. predict rotor loads and fuselage vibrations is described. The tool The aircraft configurations assessed in this study included the is extended to formulate a bearingless main rotor configuration helicopter and tilt rotor as part of the fundamental ground rules and for the modeling and analysis of higher harmonic control (HHC). jointly agreed to by the Army Aviation Research and Technology It is found that the approach can be used to model redundant Activity and the two LHX contractor teams. Author load paths on a bearingless rotor, and that torsional loads induced in the flexbeam are primarily due to applied feathering rather than A8918870 aerodynamically induced loads. HHC trends are found to be largely CORROSION AND CORROSION CONTROL OF SELECTED independent of the modal character of the rotor to which it is FIELD PROBLEMS applied. Analysis of the mechanisms behind HHC indicates a HERBERT JACOBS and MARY J. LLOYD (McDonnell Douglas primary role of the phase of the aerodynamic loads at the harmonics Helicopter Co., Mesa, AZ) IN: AHS, Annual Forum, 44th, of interest rather than the magnitude of loads. The modes of the Washington, DC, June 16-18, 1988, proceedings. Alexandria, VA, fuselage influence minimum vibrations for given hubloads and in American Helicopter Society, 1988, p. 237-242. the Computation of hubloads. C.D. The present discussion of factors implicated in helicopter corrosion during field operations furnishes perspective on the A89-18877' California Univ., Los Angeles. resolution of those problems in the field, rather than through DESIGN OF A SIMPLE ACTIVE CONTROLLER TO SUPPRESS redesign. The provocative concept of a 'universal' corrosion HELICOPTER AIR RESONANCE prevention/correction compound is formulated and evaluated in M. D. TAKAHASHI and P. P. FRIEDMANN (California, University, light of speculative performance criteria for surface wetting and Los Angeles) IN: AHS. Annual Forum, 44th, Washington, DC, infiltration characteristics, mechanical application and lubricity June 16-18, 1988, Proceedings. Alexandria, VA, American characteristics, environmental response behavior, electrical and Helicopter Society, 1988, p. 305-316. refs electronics system application consequences, and human tolerance (Contract NAG2-209; NAG2-477) characteristics. O.C. A coupled rotor/fuselage helicopter analysis with the important effects of blade torsional flexibility, unsteady aerodynamics, and A89-18874 forward flight is presented. Using this mathematical model, a EXPERIMENTAL VERIFICATION OF HELICOPTER BLADE nominal configuration is selected that experiences an air resonance DESIGNS OPTIMIZED FOR MINIMUM VIBRATION instability throughout most of its flight envelope. A simple WILLIAM H. WELLER and MARK W. DAVIS (United Technologies multivariable compensator using conventional swashplate inputs Research Center, East Hartford, CT) IN: AHS, Annual Forum, and a single body roll rate measurement is then designed. The 44th, Washington, DC, June 16-18, 1988, Proceedings. Alexandria, controller design is based on a linear estimator in conjunction VA, American Helicopter Society, 1988, p. 263-279. refs with optimal feedback gains, and the design is done in the An experimental program was conducted to demonstrate the frequency domain using the Loop Transfer Recovery method. The capability of an automated modal-based design optimization controller is shown to suppress the air resonance instability analysis to predict helicopter blade structural properties leading to throughout wide range helicopter loading conditions and forward improved rotor vibratory characteristics. Nineteen articulated model flight speeds. Author rotor configurations were wind-tunnel tested, and the resulting vibratory responses were measured. Each configuration was based A89-18878 on a unique combination of mass distribution and structural STRUCTURAL DYNAMICS OF A HELICOPTER ROTOR BLADE stiff ness, corresponding to designs developed to achieve alternative SYSTEM objectives. The experimental results show that the modal-based A. V. SRINIVASAN, D. G. CUl-fS, H. T. SHU (United Technologies optimization analysis can be used to tailor blade structural Research Center, East Hartford, CT), D. L. SHARPE (US. Army, properties to achieve low vibration rotor designs. Author Aeroflightdynamics Directorate, Moffett Field, CA), and 0. A. BAUCHAU (Rensselaer Polytechnic Institute, Troy, NY) IN: AHS, A89-18875 Annual Forum, 44th. Washington, DC, June 16-18, 1988, DEVELOPMENTS IN DYNAMICS METHODOLOGY AT BELL Proceedings. Alexandria, VA, American Helicopter Society, 1988, HELICOPTER TEXTRON p. 317-329. refs J. J. CORRIGAN, J. J. SCHILLINGS, S. K. YIN, and P. Y. HSlEH Structural dynamic characteristics of a 6.32-ft-diameter (Bell Helicopter Textron, lnc., Fort Worth, TX) IN: AHS, Annual torsionally soft two-bladed composite rotor were measured in Forum, 44th, Washington, DC, June 16-18, 1988, Proceedings. vacuum over a speed range of 0 to 1000 rpm. Measurements of Alexandria, VA, American Helicopter Society, 1988, p. 281 -292. vibratory strains for five modes of vibration were made on the refs blades for several combinations of precone, droop, and flexure The second-generation global rotorcraft flight simulation stiff ness. Theoretical predictions of the dynamic characteristics program designated 'COPTER' incorporates the well-validated, were made using a fully nonlinear FEM. This paper presents and first-generation 'C81' code through a process of restructuring and compares the resonant frequencies and corresponding strain mode modularization to reduce development time and cost. Improvements shapes obtained from the experimental and analytical efforts. made to the modal displacement methodology are noted to have Excellent agreement (within 0.5 percent) was found for all flapping dramatically improved the computation of steady blade loads; in and lead-lag modal frequencies. Correlation with torsional addition, an updating of modal data as a function of cyclic pitch frequencies was within 2 percent with stiff flexure and within 7 has yielded improvements in the Computation of oscillatory loads. percent for the soft flexure configuration. Author The free-wake module added to COPTER has produced encouraging results for the prediction of higher harmonic blade A89-18879' Bell Helicopter Co., Fort Worth, TX. loads and vibrations. O.C. INVESTIGATION OF DIFFICULT COMPONENT EFFECTS ON FEM VIBRATION PREDICTION FOR THE AH-1G HELICOPTER A8918876 ROBERT V. DOMPKA (Bell Helicopter Textron, Inc., Fort Worth, BEARINGLESS ROTORS AND HIGHER HARMONIC CONTROL TX) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, MODELING USING RACAP 1988, Proceedings. Alexandria, VA, American Helicopter Society, KARAN B. SANGHA (McDonnell Douglas Helicopter Co., Mesa, 1988, p. 331-343. NASA-sponsored research. refs

162 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

Under the NASA-sponsored Design Analysis Methods for helicopter mission radius capability. Various fuel tank pod design Vibrations program, a series of ground vibration tests and concepts were evaluated from state-of-the-art metal to advanced NASTRAN finite element model correlations were conducted on composite designs. The most efficient structural design based on the Bell AH-1G helicopter gunship to investigate the effects of weight, parts count, tooling count, material data base available difficult components on the vibration response of the airframe. and the resulting final cost, was selected. This paper summarizes Secondary structure and damping were found to have significant the sequence of design events from initial design concepts up to effects on the frequency response of the airframe above 15 Hz. and including full-scale structural tests. Author The nonlinear effects of thrust stiffening and elastomeric mounts on the low-frequency pylon modes below the main rotor were A89-18888 also significant. C.D. ADVANCEMENTS IN EROSION TESTING OF ROTOR BLADE LEADING EDGES A8918880 DAVID A. HAYNIE (Bell Helicopter Textron, Inc., Fort Worth, TX) DESIGN AND FABRICATION OF AN ADVANCED LIGHT IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, ROTOR Proceedings. Alexandria, VA, American Helicopter Society, 1988, HARLAN W. FRIEDMAN (Bell Helicopter Textron, Inc., Fort Worth, p. 453-466. refs TX) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, Data that identify and quantify the parameters influencing 1988, Proceedings. Alexandria, VA, American Helicopter Society, helicopter rotor blade erosion are used to design a new erosion 1988, p. 347-354. test stand that more accurately simulates the erosion environment The successful model 680 four-bladed composite bearingless encountered in flight. The parameters controlled by the test stand rotor has been modified by incorporating new rotor blades designed include airfoil shape, tip speed, angle of attack, sand cloud, and and fabricated with advanced technology. This paper describes rain field. A comparison is made with actual rain erosion the aerodynamic design requirements and structural design experiences in flight. C.D. practices used to create the simple blade structure, the dynamic tuning methods used to achieve low vibration, and the use of A8918893 CAD to disseminate engineering and tooling information. Discussion NOTAR HYBRID COMPOSITE/METAL FAN BLADE of tooling and manufacturing approaches that yield the blades at R. A. LOFLAND and JIM NEMO (McDonnell Douglas Helicopter a 33-percsnt time savings and a 40-percent cost savings over Co., Mesa, AZ) IN: AHS, Annual Forum, 44th. Washington, DC, typical preproduction blades are included. Author June 16-18, 1988, Proceedings. Alexandria, VA, American Helicopter Society, 1988, p. 493-495. A89-18881 For the past ten years McDonnell Douglas Helicopter Company THE POINTER - A REVOLUTIONARY IDEA TO IMPROVE RPV has been developing the NOTAR (No Tail Rotor) helicopter. At CAPABlLIT1 ES the start of the NOTAR Program, a metal blade and hub assembly RODNEY S. TAYLOR (Bell Helicopter Textron, Inc., Fort Worth, were selected to supply the air for both the tail boom and the TX) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, thruster. Though adequate for proving the viability of the NOTAR 1988, Proceedings. Alexandria, VA, American Helicopter Society, concept, as the program matured it became clear that the 1988, p. 355-363. performance of the blade was not suitable for continued use and The paper describes the 'Pointer', which is a small remotely improvement in directional control would have to be made. Towards piloted vehicle. It can operate routinely from unprepared and this end, an outside company was contracted in 1984 to design confined areas or from the decks of small vessels with no and fabricate an all-composite fan blade that would be compatible requirement for launch or recovery equipment. Pointer integrates with the existing hub. Though this was accomplished, the composite the advantages of VTOL and low-speed flight with the speed and blades that were supplied failed. This paper will discuss the design endurance associated with fixed-wing aircraft. Mission turn-around changes of the all-composite blade that resulted in the evolution time is minimized and the high '9' forces associated with launch of a hybrid composite/metal fan blade. Author and recovery are eliminated. A half-scale model of the developmental version of Pointer is presented. K.K. A89-18896 SIX DEGREE OF FREEDOM CREW ISOLATION DESIGN, A8918882 Boeing Helicopter Co., Philadelphia, PA. BENCH TEST AND FLIGHT TEST CIVIL TILTROTOR AIRCRAFT - A COMPARISON OF FIVE R. DESJARDINS, R. GABEL, and V. SANKEWITSCH (Boeing CANDIDATE DESIGNS Helicopters, Philadelphia, PA) IN: AHS, Annual Forum, 44th, JOSEPH B. WILKERSON (Boeing Helicopters, Philadelphia, PA) Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA. and RODNEY S.TAYLOR (Bell Helicopter Textron, Inc., Fort Worth, American Helicopter Society, 1988, p. 521-530. refs TX) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, A six-degree-of-freedom isolation system has been developed 1988, Proceedings. Alexandria, VA, American Helicopter Society, for the cockpit crew module of the Boeing Model 360 helicopter, 1988, p. 365-388. NASA-FAA-DOD-sponsored research. refs an advanced technology demonstrator. Analyses, bench tuning The results of a NASA, FAA, and DOD funded study on civil tests, an aircraft shake test and flight test have demonstrated the tiltrotor missions and applications showed that a substantial share effectiveness of the system. Flight vibration levels on the floor of the Northeast Corridor shorthaul market may be captured by near the co-pilot seat at the dominant 4P frequency for 200 knots civil tiltrotor aircraft with strategically located IFR-certifiedvertiports. are + or - 0.06 g vertical, + or - 0.02 g lateral, and 0.02 g A slightly enlarged version of the XV-15 and commercial versions longitudinal. Author of the basic V-22 were the baseline configurations for the study. Three totally new commercial tiltrotor concepts were developed A89-18898' Maryland Univ., College Park. as well. K.K. AEROELASTIC OPTIMIZATION OF A HELICOPTER ROTOR JOON W. LIM and INDERJIT CHOPRA (Maryland, University, A8918885 College Park) IN: AHS, Annual Forum, 44th, Washington, DC, DESIGN, ANALYSIS, AND TEST OF COMPOSITE FUEL TANK June 16-18, 1988, Proceedings. Alexandria, VA, American PODS FOR THE CH-46E HELICOPTER Helicopter Society, 1988, p. 545-558. refs JOHN P. KELLEHER and SIDNEY MOSZER (Boeing Helicopters, (Contract NAG1-739; DAAG29-83-K-0002) Philadelphia, PA) IN: AHS, Annual Forum, 44th, Washington, Structural optimization of a hingeless rotor is investigated to DC, June 16-18, 1988, Proceedings. Alexandria, VA, American reduce oscillatory hub loads while maintaining aeroelastic stability Helicopter Society, 1988, p. 423-431. in forward flight. Design variables include spanwise distribution of The logistic effectiveness of the helicopter is limited by its nonstructural mass, chordwise location of blade center of gravity mission radius capability. The U.S.Navy requested an increase in and blade bending stiffnesses (flap, lag and torsion). A fuel capacity from 356 gallons to 600 gallons to improve the CH-46E comprehensive aeroelastic analysis of rotors, based on a finite

163 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE element method in space and time, is linked with optimization structural sections of the helicopter: roof, bulkheads and frames, algorithms to perform optimization of rotor blades. Sensitivity side panels, internal acoustic spaces, floor, and external acoustic derivatives of blade response, hub loads, and eigenvalues with spaces. Each of these sections is substructured into smaller parts, respect to the design variables are derived using a direct analytical and the degree of resolution required is defined by its proximity approach, and constitute an integral part of the basic blade to the transmission gearbox attachment points. The substructures response and stability analyses. This approach reduces the are further subdivided into subsystems which represent mode group computation time substantially; an 80 percent reduction of CPU types, such as bending or in-plane modes. Ground and flight tests time to achieve an optimum solution, as compared to the widely conducted to obtain acoustic and vibration data for validating the adopted finite difference approach. Through stiffness and SEA prediction model are described. Good agreement between nonstructural mass distributions, a 60-90 percent reduction in all the predicted and flight test data showed that the SEA technique six 4hev hub loads is achieved for a four-bladed soft-inplane can be used to model and predict cabin noise of an all-composite rotor. Author airframe. The flight test noise data showed that the ACAP helicopter cabin noise is dominated by the main transmission gear-box. There A89-18899 is no local amplification of noise observed in the ACAP cockpit. DYNAMIC CHARACTERISTICS OF ADVANCED BEARINGLESS Author ROTORS AT MCDONNELL DOUGLAS HELICOPTER COMPANY A89-18920 JEFFREY L. SORENSEN, LOUIS J. SILVERTHORN, and THOMAS BELL ACAP FULL-SCALE AIRCRAFT CRASH TEST AND H. MAIER (McDonnell Douglas Helicopter Co., Mesa, AZ) IN: KRASH CORRELATION AHS, Annual Forum, 44th, Washington, DC. June 16-18, 1988, JAMES D. CRONKHITE (Bell Helicopter Textron, Inc., Fort Worth, Proceedings. Alexandria, VA, American Helicopter Society, 1988, TX) and L. T. MAZZA (US. Army, Aviation Applied Technology p. 559-570. Directorate, Fort Eustis, VA) IN: AHS, Annual Forum, 44th, Two bearingless main rotor systems consisting of advanced Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, composite blades and composite flexbeams were designed, American Helicopter Society, 1988, p. 849-863. fabricated, and tested. This paper addresses dynamic and A full-scale ACAP aircraft crast test was carried out to verify aeroelastic stability issues affecting the design of both rotor that the aircraft met the specified crash requirements and that all systems. First, the paper presents analytical results on the effects of the important components functioned properly as a system. of dynamic requirements on damper sizing, pitch-flap-lag stability, Adequate crash protection involved providing a protective shell or blade frequency placement, whirl-mode stability, and vibration. Next, livable volume around the occupied areas and containing fuel to the document confirms the assumptions made in the design and prevent postcrash fire. ACAP worthiness requirements are analysis of the rotor system using test results. Finally, the paper discussed as well as drop test preparations, and the correlation compares the dynamic characteristics of the two flexbeam of the KRASH analysis with the test. K.K. designs. Author A8918921 A891890 1 APPLICATION OF DAMAGE TOLERANCE METHODOLOGY TO TIP LOSS AND BLADE STRIKE SIMULATIONS USING DYSCO HELICOPTER DYNAMIC COMPONENTS USING THE EXAMPLE B. A. GUSTAVSON (Kaman Aerospace Corp., Bloomfield, CT) IN: OF A MAIN ROTOR PITCH LINK FOR THE AH-1S AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, HELICOPTER Proceedings. Alexandria, VA, American Helicopter Society, 1988, B. R. KRASNOWSKI, W. W. SPENCE (Bell Helicopter Textron, p. 581-585. refs Inc., Fort Worth, TX), and K. M. ROTENBERGER (U.S. Army, (Contract DAAJO2-85-C-0033; DAAJ02-86-C-0027) Aviation Systems Command, Saint Louis, MO) IN: AHS, Annual A modeling technology has been developed to evaluate the Forum, 44th. Washington, DC, June 16-18, 1988, Proceedings. damage tolerance of rotorcraft dynamic systems and has been Alexandria, VA, American Helicopter Society, 1988, p. 865-878. incorporated into an interactive computer program called DYSCO refs (Dynamic System Coupler). The motion of a rotorcraft can be A simplified engineering approach to damage tolerance analysis simulated with changes in control inputs, physical and geometric of typical helicopter components is presented. The equivalent properties, and applied loads imposed at any instant. Changes to method of stress intensity factor determination and crack growth single or multiple blades of an aeroelastic rotor representation was found to be effective in the analysis of helicopter components. due to ballistic damage or other anomalies can be made. The The results of the analysis and testing of the crack growth in the feasibility of a strike-tolerant main rotor blade was investigated; a thread root showed that, in this case, high stresses in a small blade striking an obstacle would cause a frangible blade tip to portion of the crack front did not influence crack growth. K.K. separate from the blade, preventing impact loads from being transmitted to the blade root and hub. The loss of one blade tip A8918923 from a teetering rotor and a blade strike were modeled. The effects EVOLUTION OF THE ACAP CRASH ENERGY MANAGEMENT on the system dynamic response, corresponding blade loads, and SYSTEM control inputs were demonstrated. Using the coupling procedure CHARLES W. CLARKE (United Technologies Corp., Sikorsky unique to DYSCO, forcing functions can be applied at any point Aircraft Div., Stratford, CT) IN: AHS, Annual Forum, 44th, or points along a blade, allowing precise definitions of the impact Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, function associated with a strike to be implemented. Author American Helicopter Society, 1988, p. 887-897. refs A full-scale drop test of the S75 ACAP was carried out in an A8818911 attempt to establish an effective crash management system for ANALYTICAL PREDICTION AND FLIGHT TEST EVALUATION meeting the Army survivability and crashworthiness requirements. OF BELL ACAP HELICOPTER CABIN NOISE A dynamic simulation software program, KRASH, was used to GOPAL P. MATHUR (Bell Helicopter Textron, Inc., Fort Worth, evaluate the system performance and to predict the effects of TX), JEROME E. MANNING, and LOUIS R. QUARTARARO alternate design concepts. KRASH was also used to provide (Cambridge Collaborative, Inc., MA) IN: AHS, Annual Forum, guidance in selecting the drop test condition and to predict the 44th, Washington, DC, June 16-18, 1988, Proceedings. Alexandria, results. K.K. VA, American Helicopter Society, 1988. p. 719-729. Army-supported research. A8918924 The application of Statistical Energy Analysis (SEA) approach METHODOLOGY FOR FATIGUE SUBSTANTIATION OF to Bell ACAP (Advanced Composite Airframe Program) helicopter ALTERNATE SOURCES AND DEGRADED MODES ON for cabin noise modeling and prediction is discussed. The SEA HELICOPTER DYNAMIC COMPONENTS model of the composite airframe is based on the following major D. 0. ADAMS (United Technologies Corp., Sikorsky Aircraft Div.,

164 ~~~~ ~ ~~ ~-~ ~

05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

Stratford, CT), C. ALBRECHT (Boeing Helicopters, Philadelphia, performance of rotors in hover and axial flight. The analysis PA), and W. D. HARRIS (McDonnell Douglas Helicopter Co., Mesa, finds the rotor wake geometry using a novel influence AZ) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, coefficient/relaxation scheme. In this paper, the features of the 1988. Proceedings. Alexandria, VA, American Helicopter Society, analysis are reviewed, and the accuracy of the analysis is assessed 1988, p. 899-910. for a wide range of rotor configurations in hover and vertical climb. It is shown that the qualification of alternate sources and The effects of variations in the analysis parameters are addressed, degraded modes on new helicopter dynamic components can and recommendations for future development are presented. reduce fatigue-related problems in the field and improve safety Generally good results were obtained for the predicted performance margins. The alternate process evaluation of a main rotor pitch of a wide range of rotor geometries and operating conditions without horn is discussed as well as the alternate supplier evaluation of any special ’tuning’ of the analysis. The analysis also provides stainless steel sheet. Degraded mode qualifications are considered predictions of rotor performance in vertical climb that are as well. K.K. substantially more accurate than momentum theory. Author

A8918928 A89-18934’# National Aeronautics and Space Administration. DEVELOPMENT AND QUALIFICATION TESTING, TEAMING Ames Research Center, Moffett Field, CA. FOR THE V-22 MULTI-SERVICE AIRCRAFT SYSTEM DEVELOPMENT AND FLIGHT TEST OF A PRECISION K. LUNN, P. DUNFORD (Boeing Helicopters, Philadelphia, PA), R. AUTOHOVER CAPABILITY FOR TACTICAL ROTORCRAFT MAGNUSON (Bell Helicopter Textron, Inc., Fort Worth, TX), and W. S. HINDSON and G. E. TUCKER (NASA, Ames Research S. PORTER (US. Navy, Naval Air Test Center, Patuxent River, Center, Moffett Field, CA) AHS, Annual Forum, 44th, Washington, MD) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, DC, June 16-18, 1988, Paper. 27 p. refs 1988, Proceedings. Alexandria, VA, American Helicopter Society, This paper describes the implementation of an automatic 1988, p. 941-954. position-hold system in the NASAIArmy CH47B variable-stability The design phase of the V-22 tiltrotor aircraft program has research helicopter. The test helicopter is briefly described, and a been concluded, the required preflight qualification testing is well detailed documentation is given of the position-measurement underway, and the first flight of the Full Scale Development test system. The control system design model and the design procedure aircraft will take place soon. This paper will discuss the teaming are described, and flight-test data describing overall system required between major subcontractors and the engine performance in strong winds are presented. C.D. manufacturer and Government test teams to prepare for the flight test program. The paper will also present a progress report. A89-18935# Author BOEING MODEL 360 ADVANCED TECHNOLOGY HELICOPTER - DESIGN FEATURES AND FLIGHT TEST UPDATE A8918929 LAWRENCE J. HARTMAN, RON MECKLIN, and ROBERT AIR-TO-AIR COMBAT HELICOPTER DEVELOPMENT WIESNER AHS, Annual Forum, 44th, Washington, DC, June JAMES M. MCCOLLOUGH, CHRISTOPHER J. STRONCEK, and 16-18. 1988, Paper. 8 p. HUGH W. WARD (Bell Helicopter Textron, Inc., Fort Worth, TX) This paper describes the design feature and fabrication methods IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, involved in the Boeing Model 360 Advanced Technology Helicopter. Proceedings. Alexandria, VA, American Helicopter Society, 1988, The high-performance rotor, dry composite hub, composite upper p. 955-963. controls, composite drive shafts, low-drag composite fuselage, The purpose of this paper is to illustrate how the air-to-air vibration isolation system, integrated avionics system, and combat environment can affect helicopter designs. To accomplish automatic flight control system are addressed. The flight test this, a case study of the Bell 406CS helicopter in an air-to-air program is discussed, including the airborne instrumentation, combat role is presented. The preparations for testing, flight aeromechanical stability, drive system verification, envelope envelope expansion and simulated air combat against other expansion, performance, acoustics, and vibration are examined. helicopters during Air-to-Air Combat Tests IV are discussed from C.D. both an engineer’s and a pilot’s point of view. Finally, requirements for a superior air combat helicopter are discussed. Author A89-18938# THREE-DIMENSIONAL INTERACTIVE SYSTEM A8918931# IDENTIFICATION OF HELICOPTER ROTOWBODY DYNAMICS AN ANALYTICAL MODEL FOR THE PREDICTION OF YR/TR ROBERT M. MCKILLIP, JR. (Princeton University, NJ) AHS, INTERACTION NOISE Annual Forum, 44th, Washington, DC, June 16-18, 1988, Paper. HORMOZ TADGHlGHl (McDonnell Douglas Helicopter Co., Mesa, 11 p. refs AZ) AHS, Annual Forum, 44th, Washington, DC, June 16-18, System identification results on UH-60 Blackhawk flight test 1988, Paper. 14 p. refs data in hover are described. Simple quasi-static models of the A detailed analytical study of helicopter tail rotor noise due to helicopter’s flight dynamics characteristics were generated using interaction with the main rotor tip vortices was carried out. The a two-pass estimation approach. The method incorporates airloads due to MR/TR (main rotor/tail rotor) vortex interaction Kinematic Observer theory for the initial state estimation phase, were modeled assuming an airfoil of infinite span cutting through and a factorized Kalman Filter for the stability derivative extraction. a moving vortex. A comparison with experimental data showed The study also employs the novel use of a graphics workstation that, overall, acoustic pressure time histories for multiple rotor in order to aid the identification process, through superposition of revolutions and interactions were found to be reasonably both flight test data and identified responses in real time. This predicted. B.J. approach allows the identification engineer to visualize and understand significantly larger amounts of data than would be A89-18933’# National Aeronautics and Space Administration. possible through examination of purely numerical data alone, Ames Research Center, Moffett Field, CA. providing an interactive environment for modeling of flight COMPARISONS OF PREDICTED AND MEASURED ROTOR dynamics. Author PERFORMANCE IN HOVER USING A NEW FREE WAKE ANALYSIS A89-19427 FORT F. FELKER, JEFFREY S. LIGHT (NASA, Ames Research CARBONICARBON COMPOSITE MATERIALS FOR AIRCRAFT Center, Moffett Field, CA), TODD R. QUACKENBUSH (Continuum BRAKES Dynamics, Inc., Princeton, NJ), and DONALD B. BLISS (Duke S. AWASTHI and J. L. WOOD (Allied-Signal Aerospace Co., Bendix University, Durham, NC) AHS, Annual Forum, 44th, Washington, Wheels and Brakes Div., South Bend, IN) Ceramic Engineering DC, June 16-18, 1988, Paper. 22 p. refs and Science Proceedings (ISSN 0196-6219), vol. 9, July-Aug. 1988, A new free-wake analysis has been developed to predict the p. 553-559.

165 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

Aircraft brake manufacturers are meeting the challenge of Aeronautica et Astronautica Sinica (ISSN 1000-6893), vol. 9, Aug. reducing the weight of the braking system by using carbodcarbon 1988, p. 8381, 8382. In Chinese, with abstract in English. (C/C) composite materials which serve as the friction material, The background of airship development in China is reviewed, heat sink, and structural components. Different types of C/C and the main difficulty involved, the lack of helium, is discussed. composite materials, their processing and properties are A new scheme for structural design of a hydrogen airship is discussed. Author considered. This scheme's advantages over the helium airship are described, and ways to avoid explosions and/or burning are A89-19559 addressed. C.D.

MODELLING...-~ ~ OF ~ GROUND EFFECTS ON AIRCRAFT ALEXANDER DJORDJEVICH (New Brunswick, University, A89- 1998 1 Fredericton, Canada) IN: Aerospace simulation 111; Proceedings COCOMAT, A CAE SYSTEM FOR COMPOSITE STRUCTURES of the SCS Multiconference, San Diego, CA, Feb. 3-5,1988. San DESIGN Diego, CA, Society for Computer Simulation International, 1988, H. J. W. M. KOELMAN and H. W. VEERBEEK (Nationaal Lucht- p. 102-116. en Ruimtevaartlaboratorium, Amsterdam, Netherlands) IN: For the purpose of mathematical modeling and computer Computer aided design in composite material technology; simulation of all the phases of an aircraft's flight, there is a necessity Proceedings of the International Conference, Southampton, for a better description of the dynamic interaction between an England, Apr. 13-15, 1988. Southampton, EnglandIBerlin and New aircraft's landing gear and its connecting surface. Landing and York, Computational Mechanics Publications/Springer-Verlag, take-off are certainly the most delicate phases of the flight regime; 1988, p. 75-88. yet, these phases are the least mathematically developed. This The proliferation of aircraft structural design variables that is a paper mathematically describes the problem, defining the dynamic consequence of the introduction of composite materials calls for influence of a surface to an aircraft, as an additional module for the use of CAE as a design aid. Controlling specialized composite numerous aircraft mathematical models. This influence is structural analysis programs imposes severe generality and determined for every individual component of the aircraft's landing flexibility requirements on such CAE tools; attention is presently gear, as a function of the aircraft's and surface's parameters, and given to a CAE system, COCOMAT, which meets such criteria the majority of the dynamic state variables. Results can be during the preliminary design phase of a structure. Illustrative generalized to all other wheeled vehicles. Mathematical modeling applications of COCOMAT in hat-stiffener structures are of the entire object (aircraft) is not considered. Author presented. O.C.

A89-19675 A89-19982 8-2 BOMBER ROLLS OUT PROCESSING COMPOSITE FINITE ELEMENT MODEL WITH Aviation Week and Space Technology (ISSN 0005-2175), vol. 129. CADCOMP NOV. 28, 1988, p. 20-27. A. MORAN, B. HOFFMAN, A. KLUNOVER, and A. NEER (Israel USAF officials have stated during the unveiling ceremonies for Aircraft Industries. Ltd., Lod) IN: Computer aided design in the 8-2 'stealth' bomber that this aircraft combines all the best composite material technology; Proceedings of the International attributes of a penetrating bomber: long range, efficient cruise, Conference, Southampton, England, Apr. 13-15, 1988. heavy payload, all-altitude penetration capability, accurate delivery, Southampton, England/Berlin and New York, Computational and reliability and maintainability. The aircraft will fly only at Mechanics Publications/Springer-Verlag, 1988, p. 105-120. subsonic speeds to ranges of 6000 n.mi. at 50,000 ft., and is The CADCOMP computer modeling system displays FEM speculated to be capable of eliminating contrails at high altitude models of both composite and noncomposite material structures, by using a fuel additive that minimizes the size of exhaust particles. accompanying design engineers through the structure preanalysis Armament consists of SRAMs, advanced cruise missiles, and phase in order to evaluate structural model properties, and then gravity-drop bombs. A multiyear procurement approach may be through the postanalysis phase, for the processing and employed to allow contractors to save on contract costs by buying implementation of results. System development has focused on long-lead items. Attention is given to the computational power user control over the engineering data to be displayed; color and sophistication required aboard the 8-2 for effective graphics are employed in order to more clearly define the operations. O.C. distribution of engineering data, both at the level of the whole model and at that of the single element. O.C. A89-19790# NONLINEAR STABILITY ANALYSIS FOR HELICOPTER A89-20020 GROUND RESONANCE NOTAR - AN ALTERNATIVE TO THE HELICOPTER TAIL DEMAN TANG (Nanjing Aeronautical Institute, People's Republic ROTOR of China) Acta Aeronautica et Astronautica Sinica (ISSN JAMES VAN HORN (McDonnell Douglas Helicopter Co., Mesa, 10006893), vol. 9, July 1988, p. A319-A325. In Chinese, with AZ) ICAO Bulletin (ISSN 0018-8778). vol. 43, Aug. 1988, p. abstract in English. refs 10-13. A simplified analytical method for calculating the limit-cycle The 'NOTAR' rotorless helicopter tail boom system incorporates behavior of a helicopter model with nonlinear dampers in both a circulation-control tailboom, a direct-jet thruster, and a the landing gear and blades is presented. It has provided a new variable-pitch fan; the main rotor wake interacts with the way to protect effectively against the ground resonance instability circulation-control slot's airstream to generate a powerful Coanda for helicopter designers. The chaotic oscillations induced by both effect that constitutes lift-antitorque moment. Water-tank the geometrical nonlinearities of the blade lag motion and the flow-visualizationtests have been conducted on a 9.5-percent scale nonlinear dampers and the effect of initial disturbances on the model of the NOTAR demonstrator helicopter. Development efforts instability response are also discussed. An experiment has been to date have solved fan-efficiency and premature tailboom carried out using a helicopter scale model. The experimental results flow-separation problems. O.C. agree with those of the theoretical analysis. Author A89-20135'# Purdue Univ., West Lafayette, IN. A89-19809# INFLUENCE OF A FLOOR ON SOUND TRANSMISSION INTO SELECTION OF THE OPTIMAL LIGHTER-THAN-AIR GAS FOR AN AIRCRAFT FUSELAGE MODEL AIRSHIP AND A SCHEME OF DOUBLE-LAYER STRUCTURAL J. D. JONES (Purdue University, West Lafayette, IN) and C. R DESIGN FULLER (Virginia Polytechnic Institute and State University, YOUFU WANG and DAYONG CHANG (Beijing University of Blacksburg) Journal of Aircraft (ISSN 002143669), vol. 25, Oct. Aeronautics and Astronautics, People's Republic of China) Acta 1988, p. 882-889. Previously cited in issue 22, p. 3223, Accession

166 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE no. A86-45426. refs A89-20318# (Contract NAG1-390) DESIGN STUDIES OF PRIMARY AIRCRAFT STRUCTURES IN ARALL LAMINATES JAN WILLEM GUNNINK (Delft, Technische Hogeschool, A8420138# Netherlands) (International Conference on Composite Materials, NEW DESIGN PROCEDURES APPLIED TO LANDING GEAR 6th, and European Conference on Composite Materials, 2nd, DEVELOPMENT London, England, July 20-24, 1987) Journal of Aircraft (ISSN JACQUES VEAUX (Messier-Hispano-Bugatti, Montrouge, France) 0021-8669), vol. 25, Nov. 1988, p. 1023-1032. Previously (ICAS, Congress, 15th, London, England, Sept. 7-12, 1986, announced in STAR as N88-22888. refs Proceedings. Volume 2, p. 1361-1371) Journal of Aircraft (ISSN Use of ARALL for fatigue dominated structural parts, like the 0021-8669), vol. 25, Oct. 1988, p. 904-910. Previously cited in lower wing and the pressure cabin of an aircraft, was assessed. issue 24, p. 3542, Accession no. A86-49117. To investigate the potential of the material, preliminary design studies were carried out on these components. The studies result A89-20144# in a weight reduction of more than 25 percent for the lower wing STATIC AEROELASTIC CHARACTERISTICS OF ClRCULATiON and the pressure cabin. Author CONTROL WINGS DAVID J. HAAS (David W. Taylor Naval Ship Research and A89-20637# Development Center, Bethesda, MD) and INDERJIT CHOPRA A NOTE ON THE OPTIMAL HYPERSONIC FLIGHT PATH (Maryland, University, College Park) (Structures, Structural YOSHlNORl WARllSHl and KANlCHlRO KAT0 Japan Society Dynamics and Materials Conference, 28th, Monterey, CA, Apr. 6-8, for Aeronautical and Space Sciences, Journal (ISSN 0021-4663), 1987 and AlAA Dynamics Specialists Conference, Monterey, CA, vol. 36, no. 416, 1988, p. 427-432. In Japanese, with abstract in Apr. 9, 10, 1987, Technical Papers. Part 28, p. 717-729) Journal English. of Aircraft (ISSN 0021-8669), vol. 25, Oct. 1988, p. 948-954. Flight paths of a hypersonic plane are formulated as optimal Previously cited in issue 14, p. 2105, Accession no. A87-33724. control problems. Minimum-time, minimum-fuel and maximum-range refs solutions are shown with varying fuel-to-weight and thrust-to-weight ratios. One of the findings is that an initial path with a slight A8420150# upward angle is usually advantageous because of the smaller drag COMMENT ON 'AEROELASTIC OSCILLATIONS CAUSED BY (in higher altitude) when in high speed. Author TRANSITIONAL BOUNDARY LAYERS AND THEIR ATTENUATION A89-20745 L. E. ERICSSON (Lockheed Missiles and Space Co., Sunnyvale, THE V-22 - 'AM I GONNA LIKE IT?' CA) Journal of Aircraft (ISSN 0021-8669), vol. 25, Oct. 1988, p. WILLIAM S. LAWRENCE (U.S. Navy, Naval Air Systems Command, 975, 976 Authors' Reply, p. 976. refs Washington, DC) Vertiflite (ISSN 0042-4455). vol. 34, Nov.-Dec. 1988, p. 51-55. A8420236 Full flight testing of the V-22 tilt-rotor VTOL aircraft will require PROJECT FOR AN ADVANCED REGIONAL TRANSPORT about four years; this developmental testing will encompass AIRCRAFT [PROJEKT ElNES FORTSCHRITTLICHEN performance and flying qualities, systems operability in combat REGIONALVERKEHRSFLUGZEUGES] and other hazardous conditions, structural durability, and propulsion H.-G. KLUG and B. FISCHER (Messerschmitt-Boelkow-Blohm reliability and maintainability. In order to accomplish this test GmbH, Hamburg, Federal Republic of Germany) IN: Yearbook program, six instrumented aircraft are undergoing preparation and 1987 II; DGLR, Annual Meeting, Berlin, Federal Republic of will be assigned to geographically and climatologically appropriate Germany, Oct. 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft test sites throughout the U.S. Attention is presently given to flight fuer Luft- und Raumfahrt, 1987, p. 709-722. In German. control and cockpit instrumentation features that will be important (DGLR PAPER 87-079) to the success of developmental flight testing. O.C. The MPC regional transport aircraft, scheduled to go into service in the mid-l990s, is discussed. The market for the aircraft and N89-13422*# Princeton Univ., NJ. Dept. of Mechanical and the aircraft requirements are examined, and the design of the Aerospace Engineering. aircraft is described, including the configuration, the tail and the STUDIES OF THE DYNAMICS OF THE TWIN-LIFT SYSTEM cabin, and the weight and performance. The application of new Interim Report, Jul. 1983 - Sep. 1987 technologies to the MPC, including natural laminates, reinforced H. C. CURTISS, JR. Oct. 1988 63 p fiber composites, and engines with very high secondary flow ratio, (Contract NAG2-244) is addressed. C.D. (NASA-CR-183273; NAS 1.26183273; MAE-TR-1840) Avail: NTlS HC A04/MF A01 CSCL 01C A8420237 A full set of equations of motion for the twin lift system, PROGRESS TOWARDS A COMMERCIAL AIRCRAFT DESIGN linearized about a hover trim condition were derived and presented. EXPERT SYSTEM It is shown that this full set of equations of motion decouples into J. ALSINA, J. P. FIELDING, A. J. MORRIS (Cranfield Institute of simpler sets of equations of motion if the aerodynamic coupling Technology, Bedford, England), A. ANINOS, and N. EROL derivatives of the helicopters are neglected. One of these (Muenchen, Technische Universitaet, Munich, Federal Republic of decoupled sets of equations of motion (referred to as the planar Germany) IN: Yearbook 1987 II; DGLR, Annual Meeting, Berlin, set) was studied at length. The other decoupled set (referred to Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, as the nonplanar set) is examined here. It is shown that when Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. the geometric configuration of the twin-lift is symmetric that a 723-730. refs further decoupling is possible into antisymmetric and symmetric (DGLR PAPER 87-120) sets of equations. One set of these reduced equations of motion The current status of an aircraft design expert system based referred to as the antisymmetric set is directly equivalent to the on a two-pass implementation approach is described. The first longitudinal motion of a single helicopeter with a sling load. The pass, which involved the creation of a wing design program, is second set, referred to as the symmetric set corresponds to the outlined, and attempts made in the second pass at an aircraft rotation of the entire system without load motion. As in the case configuration are addressed, reporting the main details of the of the planar symmetric motion, the location of the tether resulting output in terms of the knowledge base. The basic attachment point influences the stability of the nonplanar symmetric differences with the wing design program are enumerated and the mode. The trend is opposite however in the nonplanar case in current status of the configuration program is described. C.D. that an attachment point below the helicopter center of gravity

167 gives a favorable effect on the stability. The effect is not as strong Institute under a five year contract with the US. Army Research however as the unfavorable effect on the planar symmetric mode. Office are reported here. These include measures taken to provide Author comprehensive and in-depth curricula at advanced levels in rotorcraft technology; attract and retain outstanding young people N89-13424'# National Aeronautics and Space Administration. in these programs; perform basic research at the leading edge of Ames Research Center, Moffett Field, CA. technology in structures, structural dynamics, unsteady REAL-TIME FLIGHT TEST ANALYSIS AND DISPLAY aerodynamics and aeroelasticity disciplines as applied to rotorcraft; TECHNIQUES FOR THE X-29A AIRCRAFT developing useful new national research resources in these areas; JOHN W. HICKS and KEVIN L. PETERSEN Nov. 1988 20 p and accomplishing technology transfer to the rotorcraft community Presented at the 73rd Flight Test Techniques Symposium Flight beyond the Rensselaer campus. Descriptions, references and Mechanics Panel, Edwards AFB, Calif., 17-20 Oct. 1988 statistics are provided to allow assessment of the extent to which (NASA-TM-101692; H-1520; NAS 1.15:101692; AGARD-PAPER-6) these goals have been realized. GRA Avail: NTlS HC AO3/MF A01 CSCL 01C The X-29A advanced technology demonstrator flight envelope expansion program and the subsequent flight research phase gave N89-13427# Boeing Advanced Systems Co., Seattle, WA. impetus to the development of several innovative real-time analysis OPTICAL FIRE DETECTOR TESTING IN THE AIRCRAFT and display techniques. These new techniques produced significant ENGINE NACELLE FIRE TEST SIMULATOR Final Report, Jul. improvements in flight test productivity, flight research capabilities, 1985 - Oct. 1986 and flight safety. These techniques include real-time measurement ALAN M. JOHNSON Mar. 1988 85 p and display of in-flight structural loads, dynamic structural mode (Contract F33615-84-C-2431) frequency and damping, flight control system dynamic stability and (AD-A197974; D180-30348-1; AFWAL-TR-87-2089) Avail: NTlS control response, aeroperformance drag polars, and aircraft specific HC A05/MF A01 CSCL 01C excess power. Several of these analysis techniques also provided Optical fire detector systems for aircraft engine compartments for direct comparisons of flight-measured results with analytical provided by fire vendors were evaluated in the Aircraft Engine predictions. The aeroperformance technique was made possible Compartment Fire Test Simulator (AENFTS). Their ability to sense by the concurrent development of a new simplified in-flight net JP-4 fires of two sizes and provide fire warnings in a variety of thrust computation method. To achieve these levels of on-line simulated flight environments was monitored along with their flight test analysis, integration of ground and airborne systems freedom from false fire warnings. One systems was identified which was required. The capability of NASA Ames Research Center, provided fire warnings for every test fire and was completely free Dryden Flight Research Facility's Western Aeronautical Test Range of false alarms. GRA was a key factor in enabling implementation of these methods. Author N89-14231 Texas A&M Univ., College Station. A UNIFIED APPROACH TO VEHICLE DESIGN, CONTROL, N89-13425# Army Aviation Engineering Flight Activity, Edwards AND FLIGHT PATH OPTIMIZATION Ph.D. Thesis AFB. CA. RUSH DALETH ROBINETT, 111 1987 205 p ROTOR SYSTEM EVALUATION, PHASE 1 Final Report, 1 Sep. Avail: Univ. Microfilms Order No. DA8808822 - 2 Feb. 1987 A set of vehicle design and control optimization methods is ROBERT M. BUCKANIN, WARREN GOULD, PAUL W. LOSIER, presented that minimizes the difference between the desired and DAVID A. DOWNEY, and ROY LOCKWOOD Mar. 1988 207 p actual dynamical flight paths. The approach taken seeks the (AD-A198794; USAAEFA-65-15) Avail: NTlS HC AlO/MF A01 optimum, physically admissible mass properties and/or the thrust CSCL 01c history of the vehicle to minimize a quadratic measure of departure Flight testing was conducted on a UH-GOA Black Hawk from the desired path. The minimization process developed belongs helicopter in support of the NASA-Ames Modern Technology Rotors to a family of problems which are commonly referred to as program to provide and validate the technology, acoustics, handling constrained parameter optimization. A recursive quadratic qualities and cost of civil and military rotorcraft. In cooperation programming algorithm is used to implement the analytical with the Rotorcraft Flight Investigations Branch of NASA-Ames formulation as a numerical algorithm. The derivations are presented Research Center and the US. Army Aviation Research and of the equations of motion for fixed and variable mass bodies Technology Activity, the U.S. Army Aviation Engineering Flight which include the unification of the control volume and particle Activity (AEFA) conducted flight tests totalling 31 productive flight dynamics analyses of the variable mass body problem. Analytical hours between 9 January and 2 June 1987. This report summarizes and numerical optimization procedures are discussed in detail. the flight tests accomplished, test conditions, data, and techniques Basic concepts are defined along with measures of stability and used to obtain the data. Data measurements included: atmospheric robustness of motion matching in terms of the uniform boundedness and aircraft state parameters; main rotor blade structural loads, of the deviation from the desired flight path. The theoretical results positions and accelerations; flight control positions and structural are illustrated with a set of test cases. Dissert. Abstr. loads; main rotor hub accelerations and various vibration measurements for the aircraft cabin floor. The handling qualities data in this report, although not representative of a UH-GOA in N89-14232'# National Aeronautics and Space Administration. typical operating conditions, were similar to previous AEFA test Langley Research Center, Hampton, VA. results in similar configurations. The power required for level flight PASSIVE VENTING TECHNIQUE FOR SHALLOW CAVITIES and hovering out-of-ground effect also agreed with previous Patent Application results. GRA ROBERT L. STALLINGS, JR., inventor (to NASA) and FLOYD J. WILCOX, JR., inventor (to NASA) 30 Sep. 1988 9 p N8413426# Rensselaer Polytechnic Inst., Troy, NY. (NASA-CASE-LAR-14031-1; NAS 1.71 :LAR-14031-1; THE CENTER OF EXCELLENCE IN ROTARY TECHNOLOGY US-PATENT-APPL-SN-252081) Avail: NTlS HC AO2/MF A01 AT RENSSELAER POLYTECHNIC INSTITUTE Final Report CSCL 01c R. G. LOEWY, ed., 0. BAUCHAU, R. BIELAWA, M. DARLOW, R. A device is introduced for reducing drag and store separation J. DIEFENDORF, R. DUFFY, R. MAYLE, H. NAGAMATSU, M. difficulties caused by shallow cavities on aircraft in supersonic SHEPHARD, and S. WINCKLER 15 Apr. 1988 327 p flight consisting of a group of hollow pipes the same length as (Contract DAAG29-82-K-0093) the cavity. The pipes are attached to the cavity floor so as to (AD-A198964; CERL-TR-E-88/08; ARO-19431.23-EG-RW) Avail: allow air to flow through the pipes. This device allows air to flow NTlS HC A15/MF A01 CSCL 01C through the pipes opposite to the direction of flow outside the The activities associated with establishing a Center of pipes. This results in reduced drag and improved store separation Excellence in Rotary Wing Technology at Rensselaer Polytechnic characteristics. NASA

168 06 AIRCRAFT INSTRUMENTATION

N8%14233'# National Aeronautics and Space Administration. 06 Langley Research Center, Hampton, VA. PASSIVE VENTING TECHNIQUE FOR SHALLOW CAVITIES AIRCRAFT INSTRUMENTATION Patent Appllcatlon ROBERT L. STALLINGS. JR. and FLOYD J. WILCOX, JR. 28 sep. 1988 11 p Includes cockpit and cabin display devices; and flight instruments. (NASA-CASE-LAR-13875-1: NAS 1.71:LAR-13875-1: US-PATENT-APPL-SN-250468) Avail: NTlS HC AO3/MF A01 CSCL 01c A89-18051 A device is disclosed for reducing drag and store separation AIAAAEEE DIGITAL AVIONICS SYSTEMS CONFERENCE, 8TH, difficulties caused by shallow cavities on aircraft in supersonic SAN JOSE, CA, OCT. 17-20, 1988, TECHNICAL PAPERS. flight consisting of a slab of porous material cut to fit precisely PARTS 1 & 2 inside the cavity. This slab is mounted inside the cavity such that Conference sponsored by AIAA and IEEE. Washington, DC, a plemun chamber is formed between the slab and the floor of American Institute of Aeronautics and Astronautics, 1988, p. Pt. the cavity. This device allows air to flow through the chamber 1, 461 p.; pt. 2, 467 p. For individual items see A89-18052 to opposite to the direction of flow outside the chamber. This results A89-18113, A89-18115 to A89-18188. in reduced drag and improved store separation characteristics. Various papers on avionics systems are presented. The general NASA topics discussed include: modular avionics, design for testability, systems engineering methods and tools, vehicle management systems, Japanese avionics, pilot-vehicle interface, advanced N89-14234# Logistics Management Inst., Bethesda, MD. aviation for next generation aircraft, fault-tolerant avionics, Ada THE NATURE OF THE AIRCRAFT COMPONENT FAILURE applications, commercial avionics, rotorcraft avionics, optical PROCESS: A WORKING NOTE technology and systems, advanced architecture and processing, F. M. SLAY and CRAIG C. SHERBROOKE Feb. 1988 28 p and management techniques for software development. Also (Contract MDA903-85-C-0139) addressed are: European avionics, general aviation avionics, crew (AD-A197979; LMI-IR701R1) Avail: NTlS HC A03/MF A01 station technology, space systems, sensor signal processing, CSCL 01c software verification and quality assurance, data link, data The physics of component failures is normally assumed to bus, embedded processors and operating systems, communi- follow a Poisson process. However, many studies have shown cation/navigation/identification systems, artificial intelligence that the component demands in the US. Air Force supply system and expert systems, application-specific integrated circuits, have a variance-to-mean ratio (VMR) much higher than 1.0, the and 32-bit microprocessors. C.D. VMR of a Poisson process. This apparent contradiction is resolved by modeling component failures as a Poisson process whose A89-18052# demand rate is not fixed, but rather is itself a stochastic process, MODULAR AVIONICS SYSTEMS STUDIES wandering over time as a result of various causes such as weather, LARRY D. BROCK and JOHN J. DEYST, JR. (Charles Stark Draper flying intensity, reliability growth, and, presumably, other unknown Laboratory, Inc., Cambridge, MA) IN: AIAAAEEE Digital Avionics factors. Component and program data for the F-16 and A-10 aircraft Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, show that demand over short time periods is Poisson. This is Technical Papers. Part 1. Washington, DC, American Institute of even more apparent when demands per flying hours are used Aeronautics and Astronautics, 1988, p. 1-7. instead of demands per day. However, when demands are (Contract F04606-87-D-0051) aggregated over longer periods of time or more flying hours, the (AIAA PAPER 88-3850) VMR increases. A gamma-Poisson model for future demands as Engineering analyses of modular avionics for military aircraft a function of past observations fits the measured data. We call will be discussed. A data base of avionics requirements for bath this process planetary Poisson to distinguish it from the general future and existing military aircraft forms the basis for these studies. class of nonstationary Poisson models. GRA Avionics modules, consistent with both projected new aircraft and retrofits, are being defined. Avionics architectures for a few of the N89-14922'# Oklahoma Univ., Norman. Dept. of Aerospace vehicles in the data base have been configured from the modules. and Mechanical Engineering. Quantitative evaluations of these architectures have been carried THE POSTSTALL NONLINEAR DYNAMICS AND CONTROL OF out to determine their relative performance, mission availability, AN F-18 A PRELIMINARY INVESTIGATION Abstract Only probabilities of mission success, and life cycle costs. The WILLIAM N. PATTEN In Hampton Inst., NASA/American Society architectures will be discussed, strengths and weaknesses for Engineering Education (ASEE) Summer Faculty Fellowship examined, and general recommendations put forward on the Program 1988 p 90-92 Sep. 1988 feasibility and merits of modular avionics. Author Avail: NTlS HC A07/MF A01 CSCL 01C The successful high angle of attack (HAOA) operation of fighter A89-18054# aircraft will necessarily require the introduction of a new onboard FAULTS WITH NONSTATIONARY OBSERVABILITY ARE control methodology that address the nonlinearity of the system LIMITING AVIONICS RIM when flown at the stalVpoststall limits of the craft's flight envelope. JEAN GEBMAN, DOUGLAS MCIVER, and HY SHULMAN (Rand As a precursor to this task, a researcher endeavored to familarize Corp., Santa Monica, CA) IN: AIAAAEEE Digital Avionics Systems himself with the dynamics of one specific aircraft, the F-18, when Conference, 8th, San Jose, CA, Oct. 17-20,1988, Technical Papers. it is flown at HAOA. This was accomplished by conducting a number Part 1. Washington, DC, American Institute of Aeronautics and of real time flight sorties using the NASA-Langley Research Astronautics, 1988, p. 16-23. Center's F-18 simulator, which was operated with a pilot in the (AIAA PAPER 88-3852) loop. In addition to developing a first hand familarity with the This paper addresses of avionics faults that have nonstationary aircraft's dynamic characteristic at HAOA, work was also performed observability. This class of faults threatens to cause erosion in to identify the input/output operational footprint of the F-18s control needed levels of avionics performance and unacceptable growth surfaces. This investigator proposes to employ the nonlinear in the avionics support burden. The challenges posed by such models of the plant identified this summer in a subsequent research faults and weaknesses in correcting the faults are considered. A effort that will make it possible to fly the F-18 effectively at poststall data collection and analysis conducted to improve deficiencies in angles of attack. The controller design used there will rely on a the support process for the F-15 avionics is discussed. It is new technique proposed by this investigator that provides for the concluded that traditional measures of R&M are completely automatic generation of online optimal control solutions for inadequate to measure the frequency and duration of performance nonlinear dynamic systems. Author degradation caused predominantly by faults with nonstationary

169 observability. Current weaknesses in the ability to correct such testing at the NASA Ames Reconfigurable Digital Flight Control faults are the dominant R&M limitation for contemporary avionics. System Facility. Fault detection was correlated with hardware and C.D. software fault monitoring and, in limited cases, with sensitivity to flight program execution modes. The results are statistically A8918055# assessed to ascertain system-level reliability implications based ADVANCED AVIONICS INTERCONNECTION on a single-fault model. Extension to multiple-fault models is R. AL MORRISON and JON SIMMONS (Lockheed Aeronautical addressed. The overall methodology/facility itself is judged to be Systems Co., Marietta, GA) IN: AIAAIIEEE Digital Avionics a promising enhancement to current practice. C.D. Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, American Institute of Aeronautics and Astronautics, 1988, p. 24-31. A8918072# (AIAA PAPER 88-3856) OPTIMAL INTEGRATION OF INERTIAL SENSOR FUNCTIONS Recent and ongoing improvements in avionics interconnection FOR FLIGHT-CONTROL AND AVIONICS are discussed. Increases in system reliability being achieved by UWE K. KROGMANN (Bodenseewerk Geraetetechnik GmbH, these advances are examined. The improvements in mission Ueberlingen, Federal Republic of Germany) IN: AIAAAEEE Digital availability which are to be achieved using Pave Pillar avionics Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, architecture are addressed. Advances being made in basic 1988, Technical Papers. Part 1. Washington, DC, American Institute connector research are discussed. C.D. of Aeronautics and Astronautics, 1988, p. 148-155. (AIAA PAPER 88-3878) The development of an integrated, strapdown inertial sensor A8918057# system is discussed. The integration steps are outlined, and the A METHODOLOGY FOR THE DESIGN OF HIERARCHICALLY development of the basic integrated redundant reference system TESTABLE AND MAINTAINABLE DIGITAL SYSTEMS (IRRS) which represents a first step toward the final system is M. A. BREUER and J. C. LIEN (Southern California, University, addressed. Failure detection, isolation, and dynamic reconfiguration Los Angeles, CA) IN: AIAA/IEEE Digital Avionics Systems are examined, and integration of the IRRS with the flight control Conference, 8th, San Jose, CA. Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, American Institute of Aeronautics and system is considered. C.D. Astronautics, 1988, p. 40-47. DARPA-supported research. refs (Contract NO001 4-87-K-0861) A89-18080# (AIAA PAPER 88-3859) STEREOSCOPIC 3-0 DISPLAYS FOR COCKPITS A methodology for the design of hierarchical testable and RONALD E. OPP, II, JOHN M. REISING, and JOHN P. ZENYUH maintainable (HTM) systems is proposed. Typical major building (USAF. Flight Dynamics Laboratory, Wright-Patterson AFB, OH) blocks and bus structures for such a system are shown. Functional IN: AIAAIIEEE Digital Avionics Systems Conference, 8th, San Jose, requirements and related design issues are presented, as well as CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, procedures for testing such a system. The proposed HTM system American Institute of Aeronautics and Astronautics, 1988, p. is able to support correct fault detection and isolation in a timely 203-206. and cost-effective manner; reduce, eliminate or explain (AIAA PAPER 88-3887) discrepancies in test results; support a uniform design for test The crewstations of future military aircraft will rely upon methodology; reduce problems in maintenance, such as false computer generated displays to present information to the pilot. alarms, CND, and RTOK; and support a two-level maintenance The increased availability of information due to greater sensor scheme. Author and data link capability will greatly challenge the ability of displays to present the information to the pilot in a clear manner. More A89-18058# capable types of displays will be required to give the pilot the FAULT DETECTION AND ISOLATION FOR RECONFIGURABLE information he needs. One possible display type is the stereoscopic FLIGHT CONTROL SYSTEMS three-dimensional display. The focus of this paper is to discuss ELLEN R. MAYHEW and DANIEL GLEASON (USAF, Institute of the three-dimensional technologies currently being used by the Technology, Wright-Patterson AFB. OH) IN: AIAAIIEEE Digital Flight Dynamics Lab to evaluate the advantages, if any, of using Avionics Systems Conference, Eth, San Jose, CA, Oct. 17-20, stereoscopic three-dimensional displays in cockpits. Results show 1988, Technical Papers. Part 1. Washington, DC, American Institute a significant performance advantage for a visual search task when of Aeronautics and Astronautics, 1988, p. 48-55. refs performed on a three-dimensional display versus the same format (AIAA PAPER 88-3860) presented on a two-dimensional display. Three-dimensional Reconfigurable flight control systems can maintain aircraft performance is also superior to two-dimensional as a function of mission effectiveness even after control surface failure occurs. complexity of the format. Additional research efforts have shown Quick and accurate fault detection and isolation (FDI) are essential that the inclusion of multi-color symbology in a three-dimensional for implementing reconfiguration. This paper presents an analytic format reduces the amount of response time required on the part redundancy FDI methodology and integrates it with a pseudoinverse of the subject. Author reconfiguration scheme. Minimum effort control theory is used to develop the control mixing strategies. Simulation results for a highly maneuverable, multiple control surfaced aircraft demonstrate the A89-18085# viability of the techniques described. Author DESIGN AND VALIDATION OF THE IFTAS FAULT-TOLERANT CLOCK A89-18060'# Allied Signal Corp., Teterboro, NJ. DAVID FURA, TODD HILL, and MICHAEL RAFTERY (Boeing A METHOD OF MEASURING FAULT LATENCY IN A DIGITAL Aerospace Co., Seattle, WA) IN: AIAAIIEEE Digital Avionics FLIGHT CONTROL SYSTEM Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, JOHN MCGOUGH (Allied-Signal, Inc.. Bendix Flight Systems Div., Technical Papers. Part 1. Washington, DC, American Institute of Teterboro, NJ), DENNIS MULCARE (Lockheed-Georgia Co., Aeronautics and Astronautics, 1988, p. 235-242. Atlanta, GA), and WILLIAM E. LARSEN (NASA, Ames Research (AIAA PAPER 88-3899) Center; FAA, Moffett Field, CA) IN: AIAAAEEE Digital Avionics A fault-tolerant distributed clock was designed and validated Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, for use in an integrated fault-tolerant avionics systems (IFTAS) Technical Papers. Part 1. Washington, DC, American Institute of computer. The clock synchronization algorithm and its functional Aeronautics and Astronautics, 1988, p. 64-72. refs implementation are described. The synchronization error and (AIM PAPER 88-3863) resynchronization overhead are characterized on the basis of the This paper describes the motivation, conduct, and analysis of assumptions used in the validation. Both meet IFTAS some 2500 low-level hardware fault cases applied in automated requirements. K.K.

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A89-18090# A89-18096# A CASE STUDY - F-16 ADA DIGITAL FLIGHT CONTROL DESIGN OF A CERTIFIABLE PRIMARY ON-BOARD AIRCRAFT SYSTEM WEIGHT AND BALANCE SYSTEM KEN GARLINGTON and AMY TYRRELL (General Dynamics Corp., LEE E. VETSCH and LARRY L. BURGENER (Honeywell, Inc., Data Systems Div., Fort Worth, TX) IN: AIAAAEEE Digital Avionics Phoenix, AZ) IN: AIAAIIEEE Digital Avionics Systems Conference, Systems Conference, 8th, San Jose, CA, Oct. 17-20. 1988, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 1. Technical Papers. Part 1. Washington, DC, American Institute of Washington, DC, American Institute of Aeronautics and Aeronautics and Astronautics, 1988, p. 267-272. Astronautics, 1988, p. 314-323. (AIAA PAPER 88-3911) (AIAA PAPER 88-3919) The F-16 Ada Digital Flight Control System (FLCS) project, The load sensor of an on-board aircraft weight and balance which started in May 1985, is one of several Ada technology system is described as well as its weight and balance computer, programs at General Dynamics. The project’s goal was to develop its calibration module, pitch attitude sensor, in-axle mounts, cockpit the necessary software tools and in-house expertise to support display, and remote dedicated display unit. Gear load measurement future Ada software development for digital flight control Systems. is examined with attention given to shear deflection, gear types, The F-16 Ada FLCS was built using a language-independent design and the deflection range requirement. Consideration is also given baseline from an earlier JOVIAL implementation of the production to load sensor design, measuring shear and rejecting nonvertical FLCS. After completing rigorous low-level tests using A VAX-base strain, system calibration, system architecture and bite, cross MIL-STD-1750A simulator/debugger, laboratory testing was channel fault detection, and cross gear sensor fault isolation. performed to validate the system in a realistic hardware K.K. environment. The project was successful; the Ada system did perform as expected, and several lessons were learned concerning A89-18097# the application of the Ada language to embedded flight systems. CENTRAL MAINTENANCE COMPUTER SYSTEM A BOLD Author - STEP FORWARD ON THE 747-400 MATT ASLIN (Boeing Co.. Seattle, WA) and LYNN COLE (Rockwell A89-18092# International Corp., Collins Air Transport Div., Cedar Rapids, IA) RESULTS OF THE IN-SERVICE EVALUATlON OF THE IN: AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, INDUSTRY PROTOTYPE American Institute of Aeronautics and Astronautics, 1988, p. DANIEL H. TILLOTSON (ARINC Research Corp., Annapolis, MD) 324-331. IN: AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, (AIM PAPER 88-4039) CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, The 747-400 features longer range, a two-crew flight deck, American Institute of Aeronautics and Astronautics, 1988, p. new passenger accommodations, a fuel-eff icient power plant, digital 277-282. Avionics, and a Centralized Maintenance Computer System (AIAA PAPER 88-3915) (CMCS). Currently, the CMCS consolidates the maintenance activity This paper provides a summary of the operational findings and from nearly 70 aircraft systems. Most everything with a wire out anomalies detected during a 10-month in-service evaluation of of it is monitored by the CMCS. One of the primary design goals the Traffic Alert and Collision Avoidance System (TCAS) on board was to provide a consistent man-machine maintenance interface a Piedmont Airlines Boeing 727 aircraft. The objectives of the for all maintenance activity. The 747-400 takes a bold step forward in-service evaluation were to assess the utility of TCAS to the in aircraft maintenance. This paper will overview the CMCS system flight crews and to determine how well TCAS performed in its design, highlighting the capabilities of the system and how the intended operational environment. The evaluation was successful user operates the system under a common set of operations. in meeting these objectives, and the use of the system was easily Author incorporated with the crewmembers’ other tasks. However, several minor operational anomalies were noted, resulting in A89-18102# recommendations for improving the system. The observed STRAPDOWN ISSUES FOR AIRBORNE EO SENSORS anomalies did not significantly affect pilot acceptance of TCAS, JOSEPH E. CARROLL and PETER SYMOSEK (Honeywell Systems and corrections for the anomalies have been incorporated into and Research Center, Minneapolis, MN) IN: AIAAIIEEE Digital changes to the TCAS logic. Author Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, American Institute A89-18095# of Aeronautics and Astronautics, 1988, p. 367-375. AN AIR DATA INERTIAL REFERENCE SYSTEM FOR FUTURE (AIAA PAPER 88-3927) COMMERCIAL AIRPLANES The access of airborne EO sensors to large FORs is discussed as well as what to do about image motions. Field of viewlfield of DAVID L. SEBRING and MELVILLE D. MCINTYRE (Boeing regard issues are addressed as well as vehicle motion issues. Commercial Airplanes, Seattle, WA) IN: AIAAAEEE Digital Avionics Particular attention is given to image smearing causes and effects, Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, random vibration, sinusoidal vibration, and desmearing Technical Papers. Part 1. Washington, DC, American Institute of approaches. K.K. Aeronautics and Astronautics, 1988, p. 308-313. (AIM PAPER 88-3918) An air data, inertial reference system architecture featuring A89- 18 109# skewed axis inertial sensors, fault-tolerant electronics, and remote FAULT TOLERANT AVIONICS air data modules has been developed. An efficient means of design ANDY D. HILLS and NISAR A. MIRZA (GEC Avionics, Ltd., Flight verification and certification using flight test data and flight code Controls Div., Rochester, England) IN: AIAAIIEEE Digital Avionics hosted on execution vehicles has also been developed. The new Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, architecture surpasses the functional integrity of classic Technical Papers. Part 1. Washington, DC, American Institute of architectures, using about half as many parts. Its modular Aeronautics and Astronautics, 1988, p. 407-414. Research fault-tolerance also allows the system to be configured with supported by Boeing Commercial Airplanes. refs additional redundancy providing the airline the option to defer (AIAA PAPER 88-3901) maintenance to a convenient time and place. While developed This paper discusses the design issues relating to a novel specifically for commercial transports, this approach could offer fault-tolerant reconfigurable architecture targetted for real-time substantial benefits to military transports and fighters and embedded flight-control applications. The architecture can absorb aerospace applications requiring robust air data and /or inertial multiple random failures and thus enables the realization of systems reference systems. Author which exhibit ultrahigh reliability and require little maintenance

171 06 AIRCRAFT INSTRUMENTATION action. The architecture is based on replication of the computing Washington, DC, American Institute of Aeronautics and hardware which is partitioned into elements or links. Author Astronautics, 1988, p. 489-492. (AIAA PAPER 88-3950) A89-18112'# Illinois Univ., Urbana. The increasing quantity and complexity of the electronic IMPACT OF DEVICE LEVEL FAULTS IN A DIGITAL AVIONIC equipments onboard an aircraft soon require research on PROCESSOR integration. The first attempts were limited by the available S. KIM and R. K. IYER (Illinois, University, Urbana) IN: AIAAIIEEE technology. The last and supposedly optimal concept progressively Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. took form: general-purpose black boxes (transmitter/receivers, 17-20, 1988, Technical Papers. Part 1. Washington, DC, American sensors, computers, indicators, controls, etc.) adaptively Institute of Aeronautics and Astronautics, 1988, p. 428-435. refs interconnected to perform the required missions. This paper (Contract NAG1-602) considers the drawbacks of this concept. An alternative is (AIAA PAPER 88-3904) presented, taking account of the technology limitations. Author This paper describes an experimental analysis of the impact of gate and device-level faults in the processor of a flight control A8918122# system. Via mixed mode simulation faults were injected both at DIGITAL CONTROL OF A QUADRUPLEX DIRECT DRIVE the gate (stuck-at) and at the transistor levels, and their propagation ACTUATOR through the chip to the output pins was measured. The results REINHARD W. REICHEL (Bodenseewerk Geraetetechnik GmbH, show that there is little correspondence between a stuck-at and a Ueberlingen, Federal Republic of Germany) IN: AIAAAEEE Digital device-level fault model insofar as error activity or detection within Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, a functional unit is concerned. Insofar as error activity outside the 1988, Technical Papers. Part 2. Washington, DC, American Institute injected unit and at the output pins are concerned, the stuck-at of Aeronautics and Astronautics, 1988, p. 493-500. and device models track each other, although the stuck-at model (AIAA PAPER 88-3951) overestimates, by over one hundred percent, the probability of Digital fly-by-wire aircraft are fitted with a redundant Flight fault propagation to the output pins. The stuck-at model significantly Control Computer (FCC). Some of its functions are input of underestimates the impact of an internal chip fault on the output analogue and discrete signals, demodulation of LVDTIRVDT inputs, pins. Author voting/monitoring of inputs, controVmonitoring of the actuators. The module within a lane of the FCC performing all these functions A8918119# is called Analog-l/O. The realization of such an Analog-l/O based MODERN DIGITAL PRESSURE CONTROL SYSTEM on analogue techniques is hardware-intensive. This paper deals HANNS-ULRICH ElTL (Nord-Micro Elektronik Feinmechanik AG, with an Analog-l/O built in purely digital technology, thus saving Frankfurt am Main, Federal Republic of Germany) IN: AIAAIIEEE hardware. Author Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988. Technical Papers. Part 2. Washington, DC, American Institute of Aeronautics and Astronautics, 1988, p. 478-483. A89-18123# (AIAA PAPER 88-3948) DEVELOPMENT AND APPLICATIONS OF AN AVIONICS This paper describes the system concept, system design, and RESEARCH TESTBED system performance of an overall digital cabin pressure control JOB BRUEGGEN (Nationaal Lucht- en Ruimtevaartlaboratorium. system (CPCS). It has been developed and already flight-test Amsterdam, Netherlands) IN: AIAA/IEEE Digital Avionics Systems proven on the Airbus A-320. The following major system features Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. are presented: (1) digital implementation of all control loops to Part 2. Washington, DC, American Institute of Aeronautics and guarantee high accuracy and reliability; (2) fully microproces- Astronautics, 1988, p. 501-507. sor-controlled actuation system provides fast response; (AIAA PAPER 88-3952) (3) all system interconnections in the aircraft like ADIRS, FMS, The Avionics Research Testbed (ART) was started in 1986 CFDS; and (4) use of flight management system data for optimum with the aim to develop an airborne facility for inflight research on pressure schedules and rate control. Flight Test results for typical the optimal use of advanced avionics systems. The main flight profiles and the response to flow changes demonstrate the components of the system are described and it is explained how excellent performance of this modern design concept. Author the specific qualities of the ART enables research applications in the field of human engineering and in the field of flight A89-18120# procedures. Author AN ICE DETECTION SYSTEM FOR HELICOPTERS T. JOHN SPRIGGS (Plessey Avionics, Ltd., Havant, England) IN: A8918125# AIAAIIEEE Digital Avionics Systems Conference, 8th, San Jose, THUNDERSTORM AVOIDANCE FOR GENERAL AVIATION CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, AIRCRAFT American Institute of Aeronautics and Astronautics, 1988, p. ERNEST W. COLEMAN (Honeywell, Inc., Phoenix, AZ) IN: 484-488. Research supported by the Ministry of Defence and Royal AIAAIIEEE Digital Avionics Systems Conference, 8th, San Jose, Aircraft Establishment. refs CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, (AIAA PAPER 88-3949) American Institute of Aeronautics and Astronautics, 1988, p. A probe has been designed and developed which will permit 51 5-519. refs accurate measurement of the liquid water content of air. This is (AIAA PAPER 88-3955) achieved by measuring the power dissipation of a thermally This paper presents the design and summary of test results of self-stabilizing cylinder fabricated from a semiconducting a new Wideband Lightning Sensor System (LSS). The LSS senses ferro-electric perovskite ceramic exhibiting a positive temperature electrostatic and electromagnetic disturbances caused by lightning coefficient of resistance. Measurements from the probe can be discharge activity. When a discharge occurs, the system analyzes used with other air data to predict the onset of icing. A novel the lightning discharge and creates the proper symbol for display icing detection system based on the probe is being developed for on a radar, an EFIS/MFD or a stand-alone indicator. The system all current and future helicopters requiring an all-weather 24-hour determines the rate of lightning in a fixed geographical area and capability. Author displays the centroid of that area with the unique lightning rate symbol. The system has a 700 KHz bandwidth and a maximum A89181 21 # range of 100 nm radius. Tests on a number of lightning storms at REFLECTIONS ON AVIONIC INTEGRATION distances to 100 nm indicate the angular resolution is better than ALBERT JANEX (LMT Radio Professionnelle, Boulogne-Billancourt, + or - 10 deg and may be in the range of less than 3 deg with France) IN: AIAAIIEEE Diaital Avionics Svstems Conference. no dependence on the number of active thunderstorm cells which 8th, San Jose, CA, Oct. 17-50, 1988, Technical Papers. Part 2: are at different angles. Author

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A8818126# Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, COCKPIT MANAGEMENT FOR REGIONAL AIRLINES AND Technical Papers. Part 2. Washington, DC, American Institute of BUSINESS AIRCRAFT AS APPLIED IN THE BEECH STARSHIP Aeronautics and Astronautics, 1988, p. 552-557. refs R. BRUCE RAY and PAUL D. HEYSSE (Rockwell International (AIAA PAPER 88-3965) Corp., Pittsburgh, PA) IN: AIAAAEEE Digital Avionics Systems Stereo 3-D was researched as a means to present cockpit Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. displays which enhance a pilot's situational awareness while Part 2. Washington, DC, American Institute of Aeronautics and maintaining a desirable level of mental workload. The initial study Astronautics, 1988, p. 520-527. at the NASA Langley Research Center used two different (AIAA PAPER 88-3957) pathways-in-the-sky to augment a computer-generated pictorial The development of an all-digital aircraft affords a rare primary flight display. One pathway resembled the outline of opportunity in the design of avionics systems. Top-down design signposts, while the other pathway resembled a monorail. That of new digital systems allows avionics engineers to create display was configured for a curved approach to a landing such operationally consistent systems throughout the cabin. This new as could be used in a Microwave Landing System (MLS) approach. generation of electronic systems provides an opportunity to It could also be used for military transports which would have to conceive concepts for simpler and more direct access to fly a precision curved pathway. Each trial was initialized with the highly-used avionics features, while insisting on cockpit operational pilot on the desired flight path. After 2 seconds, he suddenly was consistency in an attempt to enhance safety and reduce training. shifted to one of eight flight path offsets. The pilot was then Flight Management Systems will continue to play a growing role required to make the initial pitch and/or roll input to correct back in these new-generation systems. Author to the nominal flight path. As soon as the input was made, the trial was over. No input was required for control trials with no A89-18128# flight path offset. Pilots responded statistically significantly faster A SIMPLIFIED AIRCRAFT COLLISION AVOIDANCE SYSTEM when the display was presented in the stereo version than when DALE POLLACK (Northern Illinois University, De Kalb, IL) IN: it was presented in the nonstereo version. Author AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, A89-18134# American !nstitute o! Aeronautics and Astronautics, 1988, p. ONE MILLION PIXEL FULL COLOR LIQUID CRYSTAL 535-537. DISPLAY FOR AVIONICS APPLICATIONS (AIAA PAPER 88-3961) ELIAS HAM, FANG-CHEN LUO, GARY BIERMANN, and MICHAEL This simple aircraft collision avoidance system is based on the CUSHING (General Electric Co., Infrared Systems and Displays principle that two aircraft cannot collide unless they are at the Dept., Wilmington, MA) IN: AIAAAEEE Digital Avionics Systems same altitude. In this system all aircraft transmit on a common Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. radio-frequency, which is frequency modulated by a tone Part 2. Washington, DC, American Institute of Aeronautics and proportional to the altitude of that aircraft. Since Astronautics, 1988, p. 564-570. refs frequency-modulated signals exhibit the capture effect, each (AIAA PAPER 88-3967) receiver will respond only to the strongest intruder signal. In all A 6.25 x 6.25 in. active matrix liquid crystal display (LCD) unit likelihood, the strongest signal would be that from the nearest with optical display characteristics sufficient for avionics use has airplane, which is, of course, the only one of concern to the pilot. been designed and fabricated. Major components development An instrument on the panel tells the pilot the difference in altitude included the display panel, lighting and associated dimming between his airplane and that of the nearest intruder. A second electronics, optical components, and display driver electronics. instrument indicates the signal strength of the intruder, and tells Emphasis was placed on meeting the needs of military applications the pilot whether the intruder is approaching or departing. while improving display optical characteristics. In this paper, display Author manufacturing methods, fluorescent backlighting, polarizer and diffuser optical elements, display drivers, and associated electronics A8818129# are described. Typical display performance is presented and COMMERCIAL AVIONICS APPLICATIONS OF FLAT PANEL compared to requirements for avionics use. Author DISPLAYS SCOlT RAUSCH (Honeywell, Inc., Phoenix, AZ) IN: AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. A8818165# 17-20, 1988, Technical Papers. Part 2. Washington, DC, American A FAULT TOLERANT INTEGRATED AVIONICS COMPUTER Institute of Aeronautics and Astronautics, 1988, p. 538-541. refs SYSTEM (AIAA PAPER 88-3962) JOHN R. FRANZEL (Boeing Electronics, Seattle, WA) IN: Recent advances in liquid crystal active matrix color flat panel AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, displays will allow for utilization in the next generation of commercial CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, avionics equipment. Four aspects of flat panel display utilization American Institute of Aeronautics and Astronautics, 1988, p. in the cockpit to be reviewed are flat panel technical challenges, 756-760. display system architecture considerations, cost, and schedule. (AIAA PAPER 88-4041) The primary question in deciding whether flat panels are applicable A fault-tolerant Integrated Avionics Computer System (IACS) is to the cockpit is whether or not flat panels look as good as a proposed which would provide central processing for multiple cathode ray tube (CRT). Comparisons to color shadow mask CRTs avionics functions in the same cabinet. Through this approach a currently in operation in today's aircraft are made throughout this single IACS cabinet could replace many individual airplane systems, paper. The next generation cockpit display systems will provide and multiple cabinets could replace the majority of the avionics new opportunities and advantages in the areas of systems and on a commercial airplane. A significant reduction in development architecture. Speculation is offered as to what a new display system cost could be achieved using this approach. Author will be like. Author A89-18174# A89-18132'# National Aeronautics and Space Administration. MODELING MISSION RELIABILITY OF ADVANCED Langley Research Center, Hampton, VA. INTEGRATED COMMUNICATION, NAVIGATION, STEREO 3-D AND NON-STEREO PRESENTATIONS OF A IDENTIFICATION AVIONICS SYSTEMS COMPUTERGENERATED PICTORIAL PRIMARY FLIGHT ROBERT L. HARRIS and DANA L. HOWELL (USAF, Wright DISPLAY WITH PATHWAY AUGMENTATION Aeronautical Laboratories, Wright-Patterson AFB, OH) IN: MARK NATAUPSKY (NASA, Langley Research Center, Hampton, AIAAIIEEE Digital Avionics Systems Conference, 8th, San Jose, VA) and LUCILLE CRITTENDEN (Research Triangle Institute, CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, Research Triangle Park, NC) IN: AIAAAEEE Digital Avionics American Institute of Aeronautics and Astronautics, 1988, p.

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815-820. refs paper discusses the transition of a tactical routing KBS from rapid (AIAA PAPER 88-4023) prototype versions on a Symbolics computer to a time-efficient The combination of new technologies, changing mission version on IBM PC AT and PS/2 computers. Author requirements, increased electronic warface, increasingly complicated logistics support, and escalating costs have forced a A891840 1 move toward modular, integrated Communication, Navigation, OPTIMIZATION OF ALGORITHMS FOR DATA PROCESSING IN Identification (CNI) systems for solutions of these problems in RADAR ALTIMETERS WITH ELECTRONIC STABILIZATION OF future generation avionics. During early development of integrated THE RADIATION PATTERN [OPTIMIZATSIIA ALGORITMOV CNI concepts, an analytical tool known as the Mission Reliability OBRABOTKI INFORMATS11 V RADIOVYSOTOMERAKH S Model (Mirem) was concurrently created to aid in system design. ELEKTRONNOI STABlLlZATSlEl DIAGRAMMY Mirem allows system designers to model any specific configuration NAPRAVLENNOSTI] of integrated CNI and obtain a preliminary indication of several A. S. BOGACHEV Radiotekhnika (ISSN 003343486), Sept. 1988, figures of merit. This paper will describe the modeling of a 'generic' p. 9-12. In Russian. refs integrated CNI architecture using Mirem and show the usefulness The method of conditional Markov processes is used to obtain of such a tool in the early development of integrated avionics quasi-optimal algorithms for the complex processing of data in architectures. Author low-altitude radar altimeter with array receiving antennas. It is shown that optimization of the processing algorithms in altimeters A89-18188# with sufficiently narrow electronically stabilizable array radiation ADVANCED APACHE ARCHITECTURE patterns leads to highly accurate measurements of flight altitude FRANK BOOTH (McDonnell Douglas Helicopter Co., Mesa, AZ) and altimeter noise immunity. B.J. IN: AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, A89-18865 American Institute of Aeronautics and Astronautics, 1988, p. HUMAN FACTORS IMPACT ON THE V-22 OSPREY COCKPIT 905-911. DEVELOPMENT - AN OVERVIEW (AIAA PAPER 88-3928) VIRGIL A. GRAF and CHARLES D. HOLLEY (Bell Helicopter The computer architecture being developed for the advanced Textron, Inc., Fort Worth, TX) IN: AHS, Annual Forum, 44th, version of the US. Army Apache helicopter is described and Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, illustrated with block diagrams. Consideration is given to American Helicopter Society, 1988, p. 201 -212. refs avionics-system partitioning; system mechanization; the multiplex The V-22 is a multimission, multiservice tiltrotor aircraft that data bus; aircraft-survivability equip ment ; and subsystems for will make its first flight this year. The crewstation configuration, aircraft management, communication, control and display functions, with its advanced cockpit management system, represents the navigation, sight management, weapons management, and culmination of the human engineering (HE) program from predesign maintenance management. T.K. through full-scale development. To illustrate the HE impact on the development program, three representative cockpit domains are A89-18189# described: control and display architecture, display design, and VEHICLE MANAGEMENT SYSTEM ARCHITECTURAL cockpit visibility. The HE process, including associated tools, is CONSIDERATIONS emphasized throughout the discussion. Implementation of this WON-ZON CHEN, LEO J. STEIN, and KARL R. HAIGES (Northrop process has resulted in a cockpit that is designed with the user Corp., Aircraft Div., Hawthorne, CA) AIAA and IEEE, Digital as a prime consideration. Author Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988. 7 p. A89-18867' National Aeronautics and Space Administration. (AIAA PAPER 88-3875) Ames Research Center, Moffett Field, CA. The vehicle Management System (VMS) concept provides DYNAMIC PERSPECTIVE DISPLAYS AND THE CONTROL OF significant performance benefits via functional and physical TILT-ROTOR AIRCRAFT IN SIMULATED FLIGHT integration of all the flight-critical subsystems aboard an aircraft. C. T. BENNETT, W. W. JOHNSON (NASA, Ames Research Center, The key to realizing these benefits is the design of a VMS Moffett Field, CA), and K. A. O'DONNELL (U.S. Army, architecture that not only satisfies overall functional requirements, Aeroflightdynamics Directorate, Moffett Field, CA) IN: AHS, Annual but also achieves a good balance between minimizing the Forum, 44th, Washington, DC, June 16-18, 1988, Proceedings. technology risks and optimizing various performance metrics such Alexandria. VA, American Helicopter Society, 1988, p. 21 9-226. as weight, cost and supportability. In the Air Force's lntegrqted refs Control Law Evaluation (ICLE) program, the VMS requirements Two simulations were conducted to study the effect of dynamic for an advanced fighter aircraft were identified and translated to a perspective displays on performance measures collected during set of architectural design issues. This paper discusses these simulated flight. The first study was a pure altitude regulation task architectural design issues along with a description of four VMS with simple first order plant dynamics. In the second simulation, configurations that were developed by Northrop to study several pilots performed two basic rotary-wing flight tasks with dynamic of the issues through laboratory evaluation. Author perspective displays projected out-the-window (panoramic head up display) or on a panel mounted simulation of a sensor display. A89-18190# The data from the two studies, taken together, show that when APPLICATION OF AI TECHNOLOGY TO TIME-CRITICAL such displays are used during flight, they will not degrade FUNCTIONS performance; and, under certain display configurations, they will IRA GLlCKSTElN and PETER STILES (IBM, Systems Integration minimize flight control errors. Author Div., Owego. NY) AIM and IEEE, Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988. 7 p. A89-18868 (AIAA PAPER 88-4030) AIRBORNE INTEGRATED MONITORING SYSTEM Applicability of AI technology in the development of automated ALBERT H. NEUBAUER, JR. (Teledyne Controls, Los Angeles, time-critical functions for tactical rotorcraft is a subject of great CA) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, interest. (A time-critical function requires response in at most a 1988, Proceedings. Alexandria, VA, American Helicopter Society, few seconds to tens of seconds.) A number of researchers have 1988, P. 227-232. developed laboratory demonstration versions of knowledge-based Goals and tasks of the onboard monitoring techniques to be 'expert' systems (KBS) that may provide acceptable solutions to implemented in the V-22 tiltrotor aircraft are discussed with a tactical problems, but which run too slowly for time-critical tactical view to input and output signal interface goals and the applications and require excessive and nonstandard processor microprocessor and memory technology required for successful resources. Using an ongoing IR8D project as a case study, this implementation. Memory and recording call for solid-state

174 07 AIRCRAFT PROPULSION AND POWER

nonvolatile devices able to furnish error-free, long-lasting data 07 storage while withstanding hostile environments. Aircraft sensors will furnish the basic data analyzed and formatted by the monitoring system processor; the display of pertinent information for review AIRCRAFT PROPULSION AND POWER by the flight crew is usually controlled by the primary flight computer via the system bus. O.C. includes prime propulsion systems and systems components, e.g., gas turbine engines and compressors; and on-board auxiliary power A8418932# plants for aircraft. STANDARDIZED ADVANCED INFRARED SENSOR - A PROGRAM STATUS CHERYL G. HOWARD and DENNIS VAN DERLASKE (US. Army, A8917742# Center for Night Vision and Electro-Optics, Fort Belvoir, VA) AHS, VARIABLEGYCLE ENGINES FOR BOOSTINGGRUISING VEHICLES Annual Forum, 44th, Washington, DC, June 16-18, 1988, Paper. N. IU. ROTMISTROV and M. M. TSKHOVREBOV (AN SSSR, Sovet 5 P. SAlRS is a concept feasibility prototype for a second generation Interkosmos, Moscow, USSR) IAF, International Astronautical thermal imager. Two sensors are currently being developed, one Congress, 39th, Bangalore, India, Oct. 8-15, 1988. 15 p. refs (IAF PAPER 88-249) by Texas Instruments Incorporated and one by Martin Marietta . Corporation. The near-term program goal of SAlRS is to provide The present consideration of variable-cycle airbreathing booster target acquisition system technology to minimize risks in time to vehicle engines for operation at Mach 5-6 gives attention to a variable-cycle engine with ramjet duct whose optimum energy impact the LHX system design review and ensuing technical transfer value into the duct is optimized. The thermodynamic and decisions under the LHX DEMIVAL program. SAlRS will incorporate many design improvements over first generation thermal imagers. kinematic parameters of powerplant configurations of this type are presented; the boosting instantaneous overall efficiency is used These improvements will provide a higher fidelity image to automatic target recognizers, and will also improve target to estimate these configurations' efficiencies at representativeflight acquisition performance for human observers. Extensive testing regimes. O.C. will be performed iising the two SAlRS sensors in both ground and airborne environments. The results of these tests will allow A89-17941'# National Aeronautics and Space Administration. the Center for Night Vision and Electro-Optics to provide the LHX Lewis Research Center, Cleveland, OH. program with a technology benchmark for second generation EXPERIMENTAL INVESTIGATION OF PROPFAN thermal imager and automatic target recognizer technology. AEROELASTIC RESPONSE IN OFF-AXIS FLOW WITH Author MISTUNING ORAL MEHMED (NASA, Lewis Research Center, Cleveland, OH) A89-19186' Mesoscale Environmental Simulations, Inc., Hampton, and DURBHA V. MURTHY (Toledo University, OH) AIAA, ASME, VA. SAE, and ASEE, Joint Propulsion Conference, 24th, Boston, MA, NUMERICAL SIMULATION OF THE 2 AUGUST 1985 DFW July 11-13, 1988. 28 p. Previously announced in STAR as MICROBURST WITH THE THREE-DIMENSIONAL TERMINAL N88-28344. refs AREA SIMULATION SYSTEM (AIAA PAPER 88-3153) FRED H. PROCTOR (MESO, Inc., Hampton, VA) IN: Conference Measured vibratory strain amplitudes from off-axis flow are on Numerical Weather Prediction, 8th, Baltimore, MD, Feb. 22-26, compared for the blades of two, 8-bladed propfan model rotors 1988, Preprints. Boston, MA, American Meteorological Society, with mistuning. One rotor had inherent mistuning. The other was 1988, p. J99J102. refs intentionally mistuned by replacing every other blade of the first (Contract NAS1-18336) rotor with a blade of same geometry but different frequencies and A model simulation is performed for a small, intense mode shapes. The data shows that the intentional mistuning had thunderstorm which occurred at the Dallas-Fort Worth airport on a beneficial effect on the aeroelastic response of the propfan August 2, 1985, leading to the crash of a commercial jetliner. The motors for a wide range of off-axis flow angles, blade pitch angles, simulation is conducted with the three-dimensional Terminal Area and rotational speeds. Statistical trends of blade strain amplitudes Simulation System, a nonhydrostatic cloud model. The simulation are compared for both the rotors in terms of the ratio of the is in good agreement with observations of the storm. It is found maximum to the mean and the coefficient of variation. Author that for similar events, very little warning time may be possible as warning is based only on the surface level winds. R.B. A8417942'# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. N8913429'# Toledo Univ., OH. Dept. of Chemical AEROELASTIC RESPONSE OF METALLIC AND COMPOSITE Engineering. PROPFAN MODELS IN YAWED FLOW A COMPARISON OF NUMERICAL METHODS FOR THE KRISHNA RAO KAZA, ORAL MEHMED, G. V. NARAYANAN PREDICTION OF TWO-DIMENSIONAL HEAT TRANSFER IN AN (NASA, Lewis Research Center, Cleveland, OH), and MARC H. ELECTROTHERMAL DEICER PAD M.S. Thesis. Flnal WILLIAMS (Purdue University, West Lafayette, IN) AIAA, ASME, Contractor Report SAE, and ASEE, Joint Propulsion Conference, 24th, Boston, MA, WILLIAM B. WRIGHT Washington NASA Dec. 1988 138 p July 11-13, 1988. 26 p. Previously announced in STAR as (Contract NAG3-72) N88-29807. refs (NASA-CR-4202; E-4380; NAS 1.264202) Avail: NTlS HC (AIAA PAPER 88-3154) A07/MF A01 CSCL 01D An analytical investigation of aeroelastic response of metallic Transient, numerical simulations of the deicing of composite and composite propfan models in yawed flow was performed. The aircraft components by electrothermal heating have been analytical model is based on the normal modes of a rotating blade performed in a 2-D rectangular geometry. Seven numerical and the three-dimensional unsteady lifting surface aerodynamic schemes and four solution methods were used to find the most theory including blade mistuning. The calculated blade stresses or efficient numerical procedure for this problem. The phase change strains are compared with published wind tunnel data on two in the ice was simulated using the Enthalpy method along with metallic and three composite propfan wind tunnel models. The the Method for Assumed States. Numerical solutions illustrating comparison shows a good agreement between theory and deicer performance for various conditions are presented. experiment. Additional parametric results indicate that blade Comparisons are made with previous numerical models and with response is very sensitive to the blade stiffness and also to blade experimental data. The simulation can also be used to solve a frequency and mode shape mistuning. From these findings, it is variety of other heat conduction problems involving composite concluded that both frequency and mode shape mistuning should bodies. Author be included in aeroelastic response analysis. Furthermore, both

175 07 AIRCRAFT PROPULSION AND POWER calculated and measured strains show that combined blade TAO SONG, ME1 MA, and ZHAOHONG SONG (Beijing University frequency and mode shape mistuning has beneficial effects on of Aeronautics and Astronautics, People's Republic of China) Acta response due to yawed flow. Author Aeronautica et Astronautica Sinica (ISSN 1000-6893), vol. 9, July 1988, p. A342-A349. In Chinese, with abstract in English. refs A8917943'# National Aeronautics and Space Administration. In order to get the most stable mistuned blade system, a new Lewis Research Center, Cleveland, OH. design procedure has been developed. The damping factor of the VIBRATION, PERFORMANCE, FLUlTER AND FORCED most unstable mode shape of the mistuned blade system is chosen RESPONSE CHARACTERISTICS OF A LARGE-SCALE as the cost function of optimization. The results of the computation PROPFAN AND ITS AEROELASTIC MODEL show that the mistuning pattern with which the system is the RICHARD AUGUST (NASA, Lewis Research Center; Sverdrup most stable will vary as the aerodynamic condition changes, but Technology, Inc., Cleveland, OH) and KRISHNA RAO V. KAZA all these optimum mistuning patterns have the same characteristic, (NASA, Lewis Research Center, Cleveland, OH) AIAA, ASME, that the amounts of mistuning between neighboring blades are SAE, and ASEE, Joint Propulsion Conference, 24th, Boston, MA, large. The results also show that the mistuning pattern which is July 11-13, 1988. 28 p. Previously announced in STAR as being used in engines for the Chinese air force is effective in N89-10043. refs controlling flutter. Author (AIAA PAPER 88-3155) An investigation of the vibration, performance, flutter, and forced response of the large-scale propfan, SR7L, and its A89-19003# aeroelastic model, SR7A, has been performed by applying available EFFECT OF BLADE MISTUNING AND BLADE-DISK ON structural and aeroelastic analytical codes and then correlating CASCADE FLUTTER BOUNDARIES measured and calculated results. Finite element models of the JINGBO CHEN, QUN CHEN, DAKUAN SHEN, and FEIDA FAN blades were used to obtain modal frequencies, displacements, (Northwestern Polytechnical University, Xian, People's Republic of stresses and strains. These values were then used in conjunction China) Acta Aeronautica et Astronautica Sinica (ISSN 1000-6893), with a 3-D, unsteady, lifting surface aerodynamic theory for the vol. 9, Aug. 1988, p. 0330-6337. In Chinese, with abstract in subsequent aeroelastic analyses of the blades. The agreement English. refs between measured and calculated frequencies and mode shapes The eigenvalue method is presented for determining the effects for both models is very good. Calculated power coefficients of blade mistuning and blade-disk on cascade flutter boundaries correlate well with those measured for low advance ratios. Flutter in incompressible flow. Results presented illustrate that mistuning results show that both propfans are stable at their respective has a beneficial effect on the cascade flutter. With the mistuning design points. There is also good agreement between calculated amplitude increasing, the flutter boundaries move more backward and measured blade vibratory strains due to excitation resulting and different mistuning orders have different effects on flutter from yawed flow for the SR7A propfan. The similarity of structural boundaries, depending on the order of the modal cascade flutter. and aeroelastic results show that the SR7A propfan simulates the Addition of bladed-disk makes mistuned cascade flutter boundaries SR7L characteristics. Author move forward. Author

A89-18124# FUNCTIONAL AUGMENTATION OF DIGITAL ENGINE A09-20240 CONTROLLERS TO IMPLEMENT AN INTEGRATED DEVELOPMENT OF RAM PROPULSION FOR FLIGHT TESTABILITY CONCEPT VEHICLES [ENTWICKLUNG ElNES STAUANTRIEBS FUER GRAHAM F. TANNER (Rolls-Royce, PLC, Bristol, England) IN: DEN FLUGKOERPEREINSATZ] AIAAIIEEE Digital Avionics Systems Conference, 8th, San Jose, W.-D. POHL (Messerschmitt-Boelkow-Blohm GmbH, Munich, CA, Oct. 17-20, 1988. Technical Papers. Part 2. Washington, DC, Federal Republic of Germany) IN: Yearbook 1987 11; DGLR, American Institute of Aeronautics and Astronautics, 1988, p. Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, 508-514. 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und (AIAA PAPER 88-3953) Raumfahrt, 1987, p. 806-820. In German. refs Some techniques proposed for an integrated aircraft engine (DGLR PAPER 87-101) test concept and their evolution from previous system designs The use of ram propulsion in flight vehicles is reviewed, and are considered. Suggestions are given on how greater use of recent technological advances in this area are discussed in detail. existing on-board engine electronics can be made in order to Progress made toward developing a ram propulsion engine for achieve a higher testability factor. Necessary areas of interface flight vehicles is discussed. Experimental test results are with the airframe manufacturer are discussed. C.D. reported. C.D.

A8918908 DUAL CENTRIFUGAL COMPRESSORS - THE HELICOPTER A8920241 SOLUTION TO SAND AND ICE INGESTION DESIGN AND INTEGRATION OF AIR-BREATHING JOHN PUGNALE (Allied-Signal Aerospace Co., Garrett Engine Div., PROPULSION SYSTEMS OF SPACE TRANSPORTS AND Phoenix, AZ) IN: AHS, Annual Forum, 44th, Washington. DC, HYPERSONIC AIRCRAFT [AUSLEGUNG UND INTEGRATION June 16-18, 1988, Proceedings. Alexandria, VA, American LUFTATMENDER ANTRIEBSSYSTEME VON Helicopter Society, 1988, p. 673-681. refs RAUMTRANSPORTER-HYPERSCHALLFLUGZEUGEN] The engine design characteristics that result in engines with 0. HERRMANN (Messerschmitt-Boelkow-BlohmGmbH, Ottobrunn, reduced susceptibility to foreign object damage (FOD) are Federal Republic of Germany) and H. RICK (Muenchen, Technische discussed, with particular attention given to helicopter engines. It Universitaet, Munich, Federal Republic of Germany) IN: Yearbook is demonstrated that, for the helicopter engines, which are 1987 II; DGLR, Annual Meeting, Berlin, Federal Republic of especially vulnerable to damage in hostile environments, the dual Germany, Oct. 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft centrifugal compressor is superior to the axial and axiaVcentrifugal fuer Luft- und Raumfahrt, 1987, p. 853-866. In German. refs compressors by offering competitive performance; reduced (DGLR PAPER 87-103) acquisition and maintenance cost; and superior reliability, The usefulness of propulsion concepts for hypersonic flight availability, and maintainability, FOD, survivability and vulnerability, vehicles based on contemporary high-performance turbopropulsion and sand erosion features. Design diagrams are included. I.S. devices with afterburners are investigated. The usefulness of the concepts for spaceflight vehicles is also addressed. The design A8819793# and operational behavior of turbo-ram propulsion Combinations are OPTIMIZATION OF MISTUNED BLADE ROTOR FOR considered, and the operational behavior of individual components CONTROLLING FLUlTER of such propulsions is examined. C.D.

176 07 AIRCRAFT PROPULSION AND POWER

A8920625 (Contract DAAK70-86-C-0011) SELECTED PAPERS ON FUNDAMENTAL ASPECTS OF GAS (AD-A198197; CRC-560) Avail: NTlS HC AlO/MF A01 CSCL TURBINE COMBUSTION 21 D ARTHUR H. LEFEBVRE (Purdue University, West Lafayette, IN) Fuel system components have experienced problems with the Beijing, Chinese Astronautic Publishing House, 1987, 706 p. refs slipperiness or lubricity of the fuel back to the early 1960's. As a Theoretical, experimental, and applications aspects of consequence of the level of refinement necessary for the PWA gas-turbine combustion are examined in a collection of the author's 523 fuel (now designated Mil-T-38219 grade JP-7) to obtain its previously published papers. The main topics addressed are high-temperature stability, many of the polar compounds ignition, flame stabilization, flame propagation, atomization, fuel contributing to lubricity had been removed, resulting in abnormal evaporation, and flame radiation. Extensive diagrams, drawings, hydraulic fuel pump wear. A lubricity-enhancing compound was and graphs are provided. T.K. developed (PWA 536) to eliminate the wear problem. High-pressure piston-type fuel pumps were one of the first parts of the engine N89-13430# Air Force Inst. of Tech., Wright-Patterson AFB, fuel system to exhibit problems related to fuel properties. One OH. early problem manifested itself as corrosion of silver-plated slipper EARLY JET ENGINES AND THE TRANSITION FROM pads and was related to carryover of residual chlorides fuel. Fuel CENTRIFUGAL TO AXIAL COMPRESSORS A CASE STUDY IN controls were another part of the engine fuel system susceptible TECHNOLOGICAL CHANGE Ph.D. The515 to fuel properties. Lack of lubricity agents caused fuel control BRIAN J. NICHELSON 1988 257 p sliding servo valves to stick. GRA (AD-A198775; AFIT/CI/NR-88-192) Avail: NTlS HC A12/MF A01 CSCL 21E N89-13435'# National Aeronautics and Space Administration. The transition from centrifugal-flow compressors to axial-flow Hugh L. Dryden Flight Research Center, Edwards, CA. compressors in the jet engines of the late 1940's and early 1950's FLIGHT MEASURED AND CALCULATED EXHAUST JET provides an illuminating case study of the evolutionary nature of CONDITIONS FOR AN FlOO ENGINE IN AN F-15 AIRPLANE technological change. A look at the development of the turbojet FRANCISCO J. HERNANDEZ and FRANK W. BURCHAM, JR. in light of engineering design reveals that incremental changes Oct. 1988 17 p came about in response to changing needs. The iterative nature (NASA-TM-100419; H-1449; NAS 1.15:100419) Avail: NTlS HC of engineering design, whereby a designer repeats a step until he A03/MF A01 CSCL 20E arrives at an acceptable solution, allows the designer to take into The exhaust jet conditions, in terms of temperature and Mach account new needs and new information. The first two turbojets, number, were determined for a nozzle-aft end acoustic study flown invented independently in England and Germany in the mid-1930's, on an F-15 aircraft. Jet properties for the F100 EMD engines both used centrifugal compressors. The inventors built upon the were calculated using the engine manufacturer's specification deck. two hundred year-old tradition of centrifugal-flow turbomachinery The effects of atmospheric temperature on jet Mach number, M10, to design a successful turbojet compressor. In contrast, all attempts were calculated. Values of turbine discharge pressure, PTGM, jet at designing and building an axial-flow compressor prior to the Mach number, and jet temperature were calculated as a function twentieth century failed. Yet, researchers in four different countries of aircraft Mach number, altitude, and power lever angle for the persisted in their efforts because of their faith in the potential of test day conditions. At a typical test point with a Mach number of the axial compressor to produce a higher pressure ratio at a better 0.9, intermediate power setting, and an altitude of 20,000 ft, M10 efficiency than the centrifugal compressor. GRA was equal to 1.63. Flight measured and calculated values of PTGM were compared for intermediate power at altitudes of 15500,20500, N89-13431# Avco Lycoming Div., Stratford, CT. and 31000 ft. It was found that at 31000 ft, there was excellent T55-L-714 ENGINE DEVELOPMENT AND QUALIFICATION TIP agreement between both, but for lower altitudes the specification CLEARANCE ANALYSIS Flnal Report deck overpredicted the flight data. The calculated jet Mach numbers S. SAWDYE 31 May 1988 23 p were believed to be accurate to within 2 percent. Author (Contract DAAJ09-87-C-A072) (AD-A198849; LYC-T55-88-04) Avail: NTlS HC A03/MF A01 CSCL 21 E N89-13436'# General Electric Co., Cincinnati, OH. Aircraft The performance of the T55-L-714 engine has shown to be Engine Business Group. strongly influenced by gas turbine running tip clearance. In order CONSTITUTIVE MODELING FOR ISOTROPIC MATERIALS to ensure both optimum steady state performance and to prevent Annual Report, May 1983 - Apr. 1984 V. G. RAMASWAMY, R. H. VANSTONE. L. T. DAME, and J. H. rubs Of the gas producer turbine upon rapid deceleration and acceleration, a steady state and transient tip clearance analysis LAFLEN 15 Apr. 1985 86 p has been conducted. GRA (Contract NAS3-23927) (NASA-CR-174805; NAS 1.26174805) Avail: NTlS HC AO5/MF A01 CSCL 21E N89-13432'# National Aeronautics and Space Administration. The first year of progress on a NASA-Lewis contract with the Lewis Research Center, Cleveland, OH. General Electric Co is documented. The purpose of this contract SENSOR FAILURE DETECTION FOR JET ENGINES (NAS3-23927) is to develop and evaluate unified constitutive WALTER C. MERRILL Nov. 1988 43 p Submitted for equations for applications to hot-path components of aircraft gas publication turbine engines such as high pressure turbine blades and vanes. (NASA-TM-101396; E-4402; NAS 1.15101 396) Avail: NTlS HC To accomplish this goal, uniaxial, notched, and multiaxial specimens A03/MF A01 CSCL 21E made of conventionally cast Rene 80 are being tested under The use of analytical redundancy to improve gas turbine engine conditions that simulate engine operating conditions. To reduce control system reliability through sensor failure detection, isolation, the raw data, automated data reduction techniques are being and accommodation is surveyed. Both the theoretical and developed that produce computer files containing the information application papers that form the technology base of turbine engine needed to analyze proposed constitutive theories. Described are analytical redundancy research are discussed. Also, Several the analytical methods being developed to determine the important application efforts are reviewed. An assessment of the parameters for these nonlinear unified theories by using the reduced state-of-the-art in analytical redundancy technology is given. data files. In another activity, a dedicated finite-element computer Author code is being developed to use unified theories in the structural analysis of hot-section components. This code was extensively N8913434# Coordinating Research Council, Inc., Atlanta, GA. verified for one such theory by successfully predicting the strain AVIATION FUEL LUBRICITY EVALUATION histories measured experimentally at the notch root of complex Jul. 1988 212 p specimens taken from complex laboratory specimens. Author

177 07 AIRCRAFT PROPULSION AND POWER

N8913437'# National Aeronautics and Space Administration. will provide a large increase in core thermal efficiency, which is Lewis Research Center, Cleveland, OH. the thermodynamic parameter of most concern for transport ISOLATED TESTING OF HIGHLY MANEUVERABLE INLET propulsion. However, when all potentially achievable advancements CON CEPTS are considered, there occurs a synergism that produces significant W. P. NORBY, B. A. HAEFFELE (McDonnell Aircraft Co., St. Louis, cycle and mission performance benefits. The nature of these Mo.), and R. R. BURLEY Dec. 1986 167 p benefits are presented along with the technology challenges. (NASA-CR-179544; NAS 1.26:179544) Avail: NTlS HC A08/MF Author A01 CSCL21E Ten percent scale models of a Mach 2.2 two dimensional inlet N8914238'# National Aeronautics and Space Administration. and a Mach 2.0 axisymmetric inlet were tested in the NASA Lewis Lewis Research Center, Cleveland, OH. Research Center 8'x6 Supersonic Wind Tunnel as part of a SIMULATION OF 3-0 VISCOUS FLOW WITHIN A cooperative effort with the McDonnell Aircraft Company. The MULTI-STAGE TURBINE objective of this effort was to test methods designed to increase JOHN J. ADAMCZYK, MARK L. CELESTINA, TIM A. BEACH, and the maneuvering performance of fighter aircraft inlets. Maneuvering MARK BARNETT (United Technologies Research Center, East improvement concepts were tested up to 40-deg angle of attack Hartford, Conn.) 1989 14 p Proposed for presentation at the for Mach numbers of 0.6 and 0.9, and up to 25 deg for Mach 34th International Gas Turbine and Aeroengine Congress and numbers 1.2 and 1.4. Maneuvering improvement concepts included Exposition, Toronto, Ontario, 4-8 Jun. 1989; sponsored by ASME a rotating cowl lip, auxiliary inlets aft of the inlet throat, and a (NASA-TM-101376; E-4430; NAS 1.15:101376) Avail: NTlS HC retracting centerbody for the axisymmetric inlet. Test results show AO3/MF A01 CSCL 21E that the rotating cowl design was effective in improving subsonic This work outlines a procedure for simulating the flow field maneuvering performance for both inlets. Auxiliary inlets did not within multistage turbomachinery which includes the effects of produce significant performance increases for either model. The unsteadiness, compressibility, and viscosity. The associated retracted centerbody resulted in some performance benefits at modeling equations are the average passage equation system high angles of attack. None of the maneuvering improvement which governs the time-averaged flow field within a typical passage concepts were effective at Mach 1.2 and 1.4. Author of a blade row embedded within a multistage configuration. The results from a simulation of a low aspect ratio stage and a one-half N8914236# Weapons Systems Research Lab., Adelaide turbine will be presented and compared with experimental (Australia). measurements. It will be shown that the secondary flow field ENGINES FOR MINI-RPV XM-1A generated by the rotor causes the aerodynamic performance of E. H. BARNARD-BROWN Jan. 1988 110 p the downstream vane to be significantly different from that of an (AD-A198336; WSRL-0566-TM; DODA-AR-005-348) Avail: NTlS isolated blade row. Author HC AO6/MF A01 CSCL 21G There were very few light-weight reciprocating engines in the N89-14239'# National Aeronautics and Space Administration. five to ten horsepower range existing in Australia or overseas Lewis Research Center, Cleveland, OH. when a program of research and exploratory development of the PLOTTING COMPONENT MAPS IN THE NAVY/NASA ENGINE techniques required to operate unmanned airborne vehicles from PROGRAM (NNEP): A METHOD AND ITS USAGE a remote base station started in 1975. Those that did were generally ROBERT M. PLENCNER Jan. 1989 20 p single cylinder engines which are difficult to balance over the (NASA-TM-101433; E-4539; NAS 1.1 5101433) Avail: NTlS HC speed range necessary for mini remotely piloted vehicle (RPV) A03/MF A01 CSCL 21E operation. A twin cylinder Kolbo D238 engine and a larger The Navy/NASA Engine Program (NNEP) and the new extended Herbrandson Dyad 160 engine were flown. When fitted with a version which handles chemical equilibrium (NNEPEQ) are very locally developed capacitor discharge ignition system, both these general cycle analysis codes that have been used extensively to engines performed reliably in flight trials of the mini-RPV XM-1 A. calculate design and off-design performance of a wide range of However, the Kolbo engine had insufficient power for aircraft with turbine engine cycles and configurations. Component maps are a take-off mass of more than about 35 kg. This memorandum used to obtain the off-design engine performance and a matched records the experience and test results gained at Weapons engine cycle. This paper describes a method of plotting the scaled Systems Research Laboratory (WSRL) on small engines from its NNEP compressor and turbine maps as the user runs the NNEP mini-RPV program conducted during 1975 to 1981. GRA code as well as plotting the operating line defined by all the cases that were computed in that particular NNEP run. Afterwards, N8414237'# National Aeronautics and Space Administration. an example demonstrates the use of this capability to help analyze Lewis Research Center, Cleveland, OH. an engine cycle model and then make improvements to that ADVANCED CORE TECHNOLOGY: KEY TO SUBSONIC cycle. Author PROPULSION BENEFITS ARTHUR J. GLASSMAN, CHRISTOPHER A. SNYDER, and GERALD KNIP. JR. 1989 13 p Prepared for presentation at the 34th International Gas Turbine and Aeroengine Congress and Exposition, Toronto (Ontario), 4-8 Jun. 1989; sponsored in part by ASME AIRCRAFT STABILITY AND CONTROL (NASA-TM-101420; E-4519; NAS 1.15:101420) Avail: NTlS HC A03/MF A01 CSCL 21E Includes aircraft handling qualities; piloting; flight controls; and A study was conducted to identify the potential performance autopilots. benefits and key technology drivers associated with advanced cores for subsonic high bypass turbofan engines. Investigated first were the individual sensitivities of varying compressor efficiency, pressure A8918068# ratio and bleed (turbine cooling); combustor pressure recovery; ENERGY MANAGEMENT FOR INTEGRATED FLIGHT AND and turbine efficiency and inlet temperature on thermal efficiency PROPULSION CONTROL SYSTEMS and core specific power output. Then, engine cycle and mission KEITH W. ROSENBERG (GEC Avionics, Ltd., Combat Aircraft Performance benefits were determined for systems incorporating Controls Div., Rochester, England) IN: AIAAAEEE Digital Avionics all potentially achievable technology advancements. The individual Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, thermodynamic sensitivities are shown over a range of turbine Technical Papers. Part 1. Washington, DC. American Institute of temperatures (at cruise) from 2900 to 3500 R and for both constant Aeronautics and Astronautics, 1988, p. 120-127. refs (current technology) and optimum (maximum thermal efficiency) (AIAA PAPER 88-3873) overall pressure ratios. It is seen that no single parameter alone The use of energy state approximations for aircraft performance

178 08 AIRCRAFT STABILITY AND CONTROL optimization is extended to tactical energy management. Until now 17-20, 1988, Technical Papers. Part 1. Washington, DC, American it has primarily been applied to minimum time, minimum fuel and Institute of Aeronautics and Astronautics, 1988, p. 177-184. maximum range types of problems. This study is extended to (AIAA PAPER 88-3882) provide propulsion management by throttle modulation, utilizing The research program of the T-2 control configured vehicle the full dry thrust and afterburner range while taking account of (CCV) with a triplex digital flight control system and CCV modes the variation in fuel conversion efficiency throughout the range. is described. Results showed that the automatic tracking control To provide tactical maneuvering the analysis takes account not law can provide increased tracking performance and survivability only of current and terminal aircraft state requirements but also with reduced pilot workload. The simulated target projected on en-route threats and prohibited volumes of airspace. As an example the HUD for the automatic tracking and HQDT flight tests proved the air interception of a noncooperative target is developed to to be highly effective and economical. K.K. demonstrate the concept. Emphasis has been placed on the development of real time algorithms which exhibit Baysian behavior A89-18077# rather than the more rigorous approaches which involve the solution TRIPLEX DIGITAL FLIGHT CONTROL SYSTEM FOR THE of classic two point boundary value problems. Author STOL RESEARCH AIRCRAFT 'ASKA TADAO UCHIDA, AKlRA WATANABE, NORIAKI OKADA (National Aerospace Laboratory, Tokyo, Japan), YUKIO SHIMIZU, KOJl A8418070# IWASAKI (Kawasaki Heavy Industries, Ltd., Japan) et al. IN: VEHICLE MANAGEMENT SYSTEM REQUIREMENTS AIAAAEEE Digital Avionics Systems Conference, 8th. San Jose, D. R. KATT (McDonnell Aircraft Co., Saint Louis, MO) IN: CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, American Institute of Aeronautics and Astronautics, 1988, p. CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, 185-192. American Institute of Aeronautics and Astronautics, 1988, p. (AIAA PAPER 88-3883) 136-141. A research aircraft, Aska, designed to demonstrate the feasibility (Contract F33615-86-C2630) of STOL at low airspeed is described. The Aska uses a stability (AIAA PAPER 88-3876) and control augmentation system (SCAS) to improve flying qualities This paper presents the results obtained from a study of the at low airspeed. The SCAS is composed of triplex SCAS computers, design objectives, design requirements, performance specifications, triplex interface units, triplex electronic control units, sensors, and a design approach for a vehicle management system JVMS). actuators, a mode control panel, and maintenance units. K.K. The approach seeks to maximize the benefits of the VMS concept for a given integrated system definition while ensuring that the functional control requirements are satisfied by the implementation. A89-18098# The approach is applied to a baseline system including STOL GUIDANCE AND FLIGHT DIRECTOR SYSTEM FOR THE V-22 and Maneuver Technology Demonstrator and Performance-Seeking TI LTROTOR Control laws as well as utility integration concepts such as thermal ROBERT L. KILMER, JR. (IBM, Systems Integration Div., Owego, management, engine start scheduling, and adaptive CG control. NY) IN: AIAA/IEEE Digital Avionics Systems Conference, 8th, The baseline also includes a number of mission-related design San Jose, CA. Oct. 17-20, 1988, Technical Papers. Part 1. issues which drive the VMS implementation to an architecture Washington, DC, American Institute of Aeronautics and configuration. Several configurations are examined to show the Astronautics, 1988, p. 332-339. impact of different design issues of the VMS implementation. (AIAA PAPER 88-3921) C.D. The V-22 Tiltrotor has the unique capability to operate in the airplane mode, the helicopter mode, or throughout the conversion region between the two modes. The thrust vectoring provided by A8418071 # rotating the nacelles causes the aircraft to transition from VEHICLE MANAGEMENT SYSTEM FOR A MANNED conventional fixed wing (frontside) operation in the airplane mode HYPERSONIC VEHICLE to 'backside' operation in the helicopter mode. The technique used JACK M. HERRLIN (Honeywell Systems and Research Center, to accommodate the transition from frontside to backside operation Minneapolis, MN) and HENDRIK GELDERLOOS (Honeywell, Inc., and the resulting Flight Director control laws are discussed in this Space and Strategic Avionics Div., Cleanvater, FL) IN: AIAAAEEE paper. The paper concludes with a summary of piloted simulation Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. results using a group of industry and military test pilots. Author 17-20. 1988, Technical Papers. Part 1. Washington, DC, American Institute of Aeronautics and Astronautics, 1988, p. 142-147. A89-18099# (AIM PAPER 88-3877) DIGITAL FLY-BY-WIRE SYSTEM FOR ADVANCED AH64 A study was performed to determine the advantages of using HELICOPTERS advanced technology in the design of a Vehicle Management STEPHEN S. OSDER (McDonnell Douglas Helicopter Co., Mesa, System for a Manned Hypersonic Vehicle (MHV). An integrated AZ) IN: AIAA/IEEE Digital Avionics Systems Conference, 8th. system architecture was derived from the Pave Pillar model, and San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 1. the functional architecture was mapped onto the system Washington, DC, American Institute of Aeronautics and architecture. Size, weight, and power dissipation estimates were Astronautics, 1988, p. 340-346. refs made for a modular mechanization of the proposed system. (AIAA PAPER 88-3922) Software size and performance estimates were made along with This paper describes the Fly-By-Wire Flight Control System comparisons with Space Shuttle Orbiter (SSO) data. The results being developed for Advanced AH-64 (Apache) aircraft. It showed that an increase in throughput of an order of magnitude emphasizes the system architecture and control mode concepts. was required for the flight management portion of the computations It is a double fail-operativeconfiguration featuring triplex computers relative to the equivalent functions for the SSO. An order of which drive dual-dual actuator interfaces for main rotor and tail magnitude more memory is required for the MHV compared to rotor control. The paper describes the sensor requirements needed the SSO. C.D. to implement control laws that provide flight path management directly from the sidestick controllers and it reviews the redundancy A89-18076# management techniques used for sensors, computers and THE 1-2 CONTROL CONFIGURED VEHICLE DEVELOPMENT, actuators. Author INTEGRATION AND FLIGHT TEST KATSUHEI SHIBATA (Japan Defense Agency, Technical Research A89-18100# and Development Institute, Tokyo, Japan) and HlDEAKl OHMIYA X-WING FLY-BY-WIRE VEHICLE MANAGEMENT SYSTEM (Mitsubishi Heavy Industries, Ltd., Nagoya, Japan) IN: AIAAAEEE WILLIAM C. FISCHER (United Technologies Corp., Sikorsky Aircraft Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. Div., Stratford, CT) IN: AIAAIIEEE Digital Avionics Systems

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Conference, 8th. San Jose, CA, Oct. 17-20,1988, Technical Papers. Central issues influencing the design of a fault tolerant computer Part 1. Washington, DC, American Institute of Aeronautics and for a FBW application are addressed. K.K. Astronautics, 1988. p. 347-355. (AIAA PAPER 88-3923) A89-18114# The paper discusses the Rotor System Research Aircraft APPLICATION OF DIGITAL TECHNOLOGY TO AIRCRAFT (RSRA)/X-Wing Program, which combines a circulation control rotor UTILITY SYSTEMS with the NASA RSRA to demonstrate an inflight flight conversion 1. MOlR (Smiths Industries Aerospace and Defence Systems, Ltd., to and from a stopped rotor state. The development of the vehicle Cheltenham, England) AIAA and IEEE, Digital Avionics Systems management system, which controls many subsystems and Conference, 8th, San Jose, CA, Oct. 17-20, 1988. 7 p. refs provides functions beyond the classical flight control system, is (AIAA PAPER 88-3872) considered. Redundancy is addressed as well as hardware, The integrated Utilities Management System (UMS) developed development testing, productionization, and system status. K.K. for the UK Experimental Aircraft Program (EAP) is described and illustrated with diagrams and photographs. The UMS employs a MIL-STD-15538 data bus, 16-bit microprocessors, and A89-18101*# National Aeronautics and Space Administration. state-of-the-art memory devices to control or monitor about 600 Ames Research Center, Moffett Field, CA. aircraft-system signals and provide relevant information to the pilot SIMULATION EVALUATION OF HELICOPTER TERRAIN on three multicolor multifunction displays; the EAP prototype with FOLLOWING/TERRAIN AVOIDANCE CONCEPTS HERRY N. SWENSON, GORDON H. HARDY (NASA, Ames UMS was successfully test flown in August 1986. T.K. Research Center, Moffett Field, CA), and PAT M. MORRIS (United Technologies Corp., Sikorsky Aircraft Div., Stratford, CT) IN: A89-18903 AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, THE IMPACT OF YAW AXIS CONTROL MODES, FLIGHT CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, DIRECTORS AND AUTOMATIC CONTROL COUPLING ON American Institute of Aeronautics and Astronautics, 1988, p. DECELERATING IFR APPROACHES FOR ROTORCRAFT 356-366. refs STEWART BAILLIE, STAN KERELIUK (National Aeronautical (AIAA PAPER 88-3924) Establishment, Flight Research Laboratory, Ottawa, Canada), and A helicopter Terrain-Following/Terrain-Avoidance (TF/TA) ROGER HOH (Systems Technology, Inc., Hawthorne, CA) IN: system was developed and evaluated using a real-time piloted AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, simulation. The TF/TA system included a guidance algorithm based Proceedings. Alexandria, VA, American Helicopter Society, 1988, upon dynamic programming and a head-up display (HUD) concept p. 613-623. refs which incorporates a pathway in the sky, a phantom aircraft, and The handling qualities and certification impacts of various issues flightpath vector/predictor symbology. The simulation was on low minima decelerating flight directed IFR approaches for conducted at the NASA Ames Research Center Interchangeable rotorcraft are studied on the basis of an in-flight simulation Cab (CAB) Laboratory using NASA test pilots. The pilots performed experiment. Particular attention is given to the use of crab versus the TF/TA task by manually tracking the HUD symbology. The sideslip techniques to maintain lateral tracking under crosswind conditions, the effects of various methods of vertical axis display, pilots were able to satisfactorily perform the TF/TA tasks with an 1 acceptable level of pilot workload. Author guidance and control, and the benefits of coupling flight director control signals directly to the rotorcraft control actuators. It was found that coupling any axis of control to the flight director provided A89-18108# slight workload relief benefits. The collective axis is expected to COMMERCIAL JET TRANSPORT FLY-BY-WIRE be the most likely axis for this implementation. K.K. ARCHITECTURE CONSIDERATIONS ROBERT J. BLEEG (Boeing Commercial Airplanes, Seattle, WA) A89-18904 IN: AIAAAEEE Digital Avionics Systems Conference, 8th. San Jose, DETERMINATION OF CONTROL LAWS FOR A SINGLE PILOT, CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, AlTACK HELICOPTER American Institute of Aeronautics and Astronautics, 1988, p. PATRICK J. HOLLlFlELD and ANNE M. OETTING (Bell Helicopter 399-406. Textron, Inc., Fort Worth, TX) IN: AHS, Annual Forum, 44th, (AIAA PAPER 88-3900) Washington, DC, June 16-18, 1988. Proceedings. Alexandria, VA, Fly-by-wire (FBW) for jet transports has come of age with the American Helicopter Society, 1988, p. 625-634. introduction to service of the first pitch and roll axes system this A piloted simulation recently conducted at the Bell Helicopter year. There are tangible advantages to FBW and the Boeing Textron Inc. (BHT) flight simulation facility defined the flight control Company has committed to a development program, with the laws for the AH-4BW. This four-bladed, single pilot, attack helicopter objective of validating system architecture and a prototype Primary will enter flight testing in mid-1988. This paper describes the control Flight Computer System (PFCS). The program includes system and control law evolution and the role played by simulation performance and safety analyses of a specific architecture, and in their development. A discussion of the computer simulation PFCS laboratory testing with special emphasis on fault tolerance programs and their use during the development of the AH-4BW investigation. The rationale behind architecture selection and a control laws is presented. The SCAS (Stability and Control review of safety requirements are presented, in addition to Augmentation System) evaluation process used is also discussed. discussion of the analysis and test program. Author Flight test data from a demonstration four-bladed helicopter that was used to help define the goals for aircraft response are shown. A89-1811 O# Comparisons between simulation results and current and proposed MAFT - AN ARCHITECTURE FOR RELIABLE FLY-BY-WIRE handling qualities specifications are made. The proposed handling FLIGHT CONTROL qualities specifications are found in ADS-33 (Reference 1). CHRIS J. WALTER (Allied-Signal Aerospace Technology Center, Author Columbia, MD) IN: AIAAIIEEE Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20,1988, Technical Papers. A89- 18905 Part 1. Washington, DC, American Institute of Aeronautics and A COMPARISON BETWEEN VARIOUS SIDE-ARM Astronautics, 1988, p. 415-421. refs CONTROLLER CONFIGURATIONS IN A FLY-BY-WIRE (AIAA PAPER 88-3902) HELICOPTER MAR, a multilane architecture suitable for real-time control J. M. MORGAN (National Research Council of Canada, Flight applications requiring high reliabilty, is described. The MAFT Research Laboratory, Ottawa) IN: AHS, Annual Forum, 44th. architecture was applied to the design of a digital flight control Washington, DC, June 16-18, 1988. Proceedings. Alexandria, VA, system in a fly-by-wire (FEW) aircraft which has a failure probability American Helicopter Society, 1988, p. 635-648. DND-supported requirement of 10 to the -10 failureslhr for a 10 hr mission time. research. refs

180 08 AIRCRAFT STABILITY AND CONTROL

A piloted experiment was flown in the National Aeronautical 1000-6893), vol. 9, July 1988, p. A393-A397. In Chinese, with Establishment variable stability Bell 205A-1 to examine the effects abstract in English. refs on both handling qualities and pilot performance of varying control The most obvious use of direct sideforce control (DSC) is for configurationswhen using multi-axis sidestick controllers. Two types counteracting sidewind during takeoff and landing of aircraft. Based of controller were used in fully and partially integrated on the review of the two conventional methods (crabbed and configurations, conventional controls were also evaluated in the sideslipping) for coping with a crosswind on approach, this paper same study to provide direct comparisons between the inceptor presents a feasible scheme which applies DSC to facilitate types. The flight control systems comprised rate command in pitch correction of lateral offsets to runway. An open-loop control and and roll, rate command heading hold in yaw and simple direct closed-loop correction strategy has been employed in this scheme. drive for collective. In general the data suggest that there was no The results of the digital simulation of this system show that the clear or obvious preference for any particular inceptor or effect on the counteracting sidewind is obvious. Author configuration. The performance analyses indicate that there was no sianificant chanae in the pilot’s control capabilities as controllers A89-19813# or chigurations were changed. Author DESIGN OF MULTI-LEVEL FLIGHT CONTROL SYSTEMS GANG FENG (Nanjing Aeronautical Institute, People’s Republic of

68819557~ China) Acta Aeronautica et Astronautica Sinica (ISSN 1000-6893), X-29 VALIDATION METHODOLOGY FOR SIMULATION AND vol. 9, Aug. 1988, p. 8407-8412. In Chinese, with abstract in FLIGHT CONTROL SYSTEM English. D. WALLER and M. SOLAN (Grumman Aerospace Corp., Bethpage, This paper discusses the design principle of hierarchical NY) IN: Aerospace simulation 111; Proceedings of the SCS controllers and its application to flight control systems. A new Multiconference, San Diego, CA, Feb. 3-5, 1988. San Diego, CA, way to the real-time realization of optimal flight control systems is Society for Computer Simulation International, 1988, p. 68-88. explored, giving an example. Simulation results are reported which refs show that the achieved performance of the hierarchical optimal Lessons learned and important results of the X-29 verification flight control system is almost equivalent to that of a conventional and validation testing program over the past three years are optimal flight controller. C.D. discussed. Particuiar attention is given to the cmtribu?ion of real-time simulation to the overall success of the program. It is A89-20170 found that significant nonlinearities and high-order dynamic effects AN EXAMPLE OF THE BEHAVIOR OF AN AIRCRAFT WITH must be included in the math-model simulation early in order to ACCUMULATED ICE - LATENT INSTABILITY accelerate control law development for specification of flight JAMES W. TELFORD (Nevada, University, Reno) Journal of hardware/software. K.K. Applied Meteorology (ISSN 0894-8763), vol. 27, Oct. 1988, p. 1093-1108. refs A8919558 Performance details related to the unstable behavior of a RECONFIGURABLE FLIGHT CONTROL SYSTEM SIMULATION research aircraft after ice accumulation which caused the aircraft JOSEPH ANDERSON, CURT CLARK, PAUL MADSEN, and to crash are examined. The data system remained fully operational FREDERICK UNFRIED (USAF, Flight Dynamics Laboratory, during the flight and the final spiraling dive. The observations Wright-Patterson AFB, OH) IN: Aerospace simulation 111; show a reduced lift effect, involving transition to partial stall on Proceedings of the SCS Multiconference, San Diego, CA, Feb. the inboard wing. The data suggest that the anomalous behavior 3-5. 1988. San Diego, CA, Society for Computer Simulation produced an equivalent to control reversal in pitch, in which forward International, 1988, p. 89-101. refs pressure on the control column could have induced increased lii A man-in-the-loop simulation was carried out for the and a nose up response. It is suggested that the effects of ice self-repairing flight control system program to demonstrate the accumulation should be studied in more detail. R.B. system’s ability to detect and correct for control surface or actuator failures. A reconfiguration strategy, developed for the AFWF-16 A8920238 aircraft, was employed to minimize the effects of battle damage CONCEPT__ __ AND FLIGHT TESTING OF A MODERN or actuator failure. This was done by: (1) detecting and isolating LONGITUDINAL MOTION REGULATOR USING AN INVERSE the failure, (2) estimating the remaining control effectiveness, and MODEL [KONZEPT UND FLUGERPROBUNG EINES (3) reapportioning the control power among the remaining surfaces MODERNEN LAENGSBEWEGUNGSREGLERS MI1 INVERSEM to restore the best possible aircraft handling qualities. K.K. MODELL] A. REDEKER (Aerodata Flugmesstechnik GmbH, Brunswick, A8919661 Federal Republic of Germany) IN: Yearbook 1987 II; DGLR, IDENTIFICATION OF UNSTABLE FLIGHT-MECHANICAL Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, SYSTEMS USING AN OUTPUT ERROR METHOD 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und [IDENTIFIZIERUNG INSTABILER FLUGMECHANISCHER Raumfahrt, 1987, p. 731-737. In German. refs SYSTEME MI1 ElNEM AUSGANGSFEHLERVERFAHREN] (DGLR PAPER 87-121) E. PIAETSCHKE (DFVLR, lnstitut fuer Flugmechanik, Brunswick, It is demonstrated that a nonlinear precontrol for longitudinal Federal Republic of Germany) Zeitschrift fuer Flugwissenschaften flight regulation is possible with limited identification costs, and und Weltraumforschung (ISSN 0342-068X), vol. 12, July-Aug. 1988, leads to excellent results in flight accuracy. The precontrol is p. 233-240. In German. refs diagrammed and described, and the longitudinalflight and controller The identification of unstable systems by using an output error design are analyzed. Flight test results using the precontrol are method leads to severe numerical difficulties. In this paper, the reported. C.D. modification of a maximum-likelihood-output error method to circumvent these difficulties is addressed. The testing of the method A89-20322’# Old Dominion Univ., Norfolk, VA. on a simple unstable system simulation is shown, and the use of COUPLED FLOW, THERMAL, AND STRUCTURAL ANALYSIS the modified method to identity the lateral movement of the US. OF AERODYNAMICALLY HEATED PANELS research aircraft XV-15 in hover flight is reported. C.D. EARL A. THORNTON (Old Dominion University, Norfolk, VA) and PRAMOTE DECHAUMPHAI (NASA, Langley Research Center, A89-19800# Hampton, VA) (Structures, Structural Dynamics and Materials COUNTERACTING SIDEWIND CONTROL SYSTEM FOR Conference, 28th, Monterey, CA, Apr. 6-8, 1987, Technical Papers. AIRCRAFT LANDING Part 1, p. 1-9) Journal of Aircraft (ISSN 0021-8669), vol. 25, Nov. YIDONG YANG (Nanjing Aeronautical Institute, People’s Republic 1988, p. 1052-1059. Previously cited in issue 14. p. 2164, Accession of China) Acta Aeronautica et Astronautica Sinica (ISSN no. A87-33552. refs

181 08 AIRCRAFT STABILITY AND CONTROL

A8920323# are presented for a representative helicopter flying at various APPLICATION OF TRANSIENT AERODYNAMICS TO THE combinations of advance ratio, turbulence intensity, and scale STRUCTURAL NONLINEAR FLUlTER PROBLEM length typical of low altitude and nap-of-the-earth flight L. 0. BRASE (McDonnell Aircraft Co., Saint Louis, MO) and W. environments. These include deterministic and statistical blade EVERSMAN (Missouri-Rolla, University, Rolla) (Structures, loads, deflections, and hub motions. Inclusion of an appropriate Structural Dynamics and Materials Conference, 28th, Monterey, unsteady model for the aerodynamic forcing is shown to be CA, Apr. 6-8, 1987 and AIM Dynamics Specialists Conference, essential to accurate response prediction at high advanced ratios. Monterey, CA, Apr. 9, 10, 1987, Technical Papers. Part 28, p. Dissert. Abstr. 648-656) Journal of Aircraft (ISSN 0021-8669), vol. 25, Nov. 1988, p. 1060-1068. Previously cited in issue 14, p. 2110, Accession no. N89-14744# Aeronautical Systems Div., Wright-Patterson AFB, A87-33717. refs OH. RECONFIGURABLE FLIGHT CONTROL AN OPPORTUNITY A89-20638# FOR INTEGRATED DIAGNOSTICS A NOTE ON THE AIRCRAFT MINIMUM-TIME TURNS E. RACHOVITSKY, J. W. DAVISON, and R. E. GUTH ln Colorado KAZUHIRO OBAYASHI and KANlCHlRO KAT0 Japan Society ilniv., Proceedings of the Air Force Workshop on Artificial for Aeronautical and Space Sciences, Journal (ISSN 0021 -4663), Intelligence Applications for Integrated Diagnostics p 138-161 Jul. vol. 36, no. 416, 1988, p. 433-439. In Japanese, with abstract in 1987 Prepared in cooperation with Air Force Flight Dynamics English. Lab., Wright-Patterson AFB, OH Three-dimensional minimum-time turns are formulated and Avail: NTlS HC A23/MF A01 CSCL 01C solved numerically as optimal control problems. The formulation Modern flight control technology is a key for achieving flight covers the drag increase and the lift decrease due to sideslip. safety and enhanced performance for future high performance Inequality constraints are used to simulate the upper and lower military aircraft where mission complexities and multiple subsystem bounds of thrust, angle of attack, sideslip and load factor. A integration are dominant characteristics. Integrated flight/weapon state-variable constraint is included to treat the flight sustaining control and systems have already demonstrated dramatic the corner velocity. Numerical results explain the effect of thrust, improvements in aircraft lethality. Now, the Flight Dynamics sideslip and initial velocity in optimal maneuvers. Author Laboratory (FI) examine revolutionary integration schemes involving reconfigurable flight control techniques and fault detection and N89-13438’# National Aeronautics and Space Administration. isolation (FDI) methods which will dramatically enhance aircraft Ames Research Center, Moffett Field, CA. survivability, yield increased lethality and provide improvements in CONTROL OF A HUMAN-POWERED HELICOPTER IN HOVER reliability and maintainability. This paper presents an overview of JOSEPH J. TOTAH and WILLIAM PATTERSON (California key flight control R and D programs which contribute to the Flight Polytechnic State Univ., San Luis Obispo.) Nov. 1988 65 p Dynamics Laboratory’s pursuit of safer, more enduring military (NASA-TM-101029; A-88280; NAS 1.15:101029) Avail: NTlS HC aircraft and highlights the potential role of expert systems for A04/MF A01 CSCL 01C diagnosis, isolation and correction of system faults. Author The study of a control system for the Da Vinci 2 human-powered 4 helicopter in hovering flight is documented. This helicopter has two very large, slowly rotating rotor blades and is considered to 09 be unstable in hover. The control system is designed to introduce stability in hover by maintaining level rotors through the use of rotor tip mounted control surfaces. A five degree of freedom RESEARCH AND SUPPORT FACILITIES (AIR) kinematic model was developed to study this control system and is documented. Results of this study show that the unaugmented Includes airports, hangars and runways; aircraft repair and overhaul configuration is unstable due to the large Lock Number, and the facilities; wind tunnels; shock tube facilities; and engine test augmented configuration is stable. The role of NASA in this study blocks. included the development and analysis of the kinematic model and control laws. Both analytical and numerical techniques were used. Author A89-18133# AN ADVANCED FACILITY FOR COCKPIT STUDIES N89-14240 Maryland Univ., College Park. P. A. LYPACZEWSKI (CAE Electronics, Ltd., Montreal, Canada) CALCULATION OF THE STEADILY PERIODIC AND GUST IN: AIAAIIEEE Digital Avionics Systems Conference, 8th, San Jose, RESPONSES OF A HINGELESS ROTOR HELICOPTER USING CA, Oct. 17-20. 1988, Technical Papers. Part 2. Washington, DC, TWO-DIMENSIONAL TIME DOMAIN UNSTEADY American Institute of Aeronautics and Astronautics, 1988, p. AERODYNAMICS Ph.D. Thesis 558-563. ANDREW SETH ELLIOTT 1987 194 p (AIAA PAPER 88-3966) Avail: Univ. Microfilms Order No. DA8808542 As modern aircraft become appreciably more complex, a great The deterministic and random gust response of a helicopter deal of study is being done on how best to interface the in forward flight is examined analytically, using a state space pilot/operator to the equipment. In response to the US. Army’s formulation in the time domain. The gust response is considered needs in this area a Crew Station Research and Development to be a perturbation about the steadily periodic solution. The Facility (CSRDF) has been constructed for NASA Ames. This facility hingeless rotor blades are modelled structurally as rotating elastic simulates a wide range of new aircraft technologies. The facility’s beams undergoing out-of-plane bending. The blades are discretized advanced cockpit includes a wide-field-of-view fiber-optic using the finite element method and the equation of motion are helmet-mounted display, ’ which is used to provide both sensor transformed into a modal space using the first few normal models. and out-the-window views of the outside world to the pilot. The rotor hub and fuselage are considered as a rigid body with a Interactive voice recognition and voice synthesis systems allow single degree of freedom along the shaft axis. The aerodynamic hands-off control of the aircraft systems. High-resolution forcing is developed from a two-dimensional unsteady time domain touch-sensitive displays provide reconfigurable graphics for studies model based on an exponential series approximation for the on how best to present information to the crew members. response to an indicia1 change in the downwash. Compressibility Author effects are included. This model is converted to an equivalent state space representation at radial stations along each blade A89-18900 and these states are appended to the state vector. For computation TESTING AND CORRELATION ON AN ADVANCED of the steadily periodic rotor responses, the aerodynamic model TECHNOLOGY, BEARINGLESS ROTOR is extended to include separation effects and dynamic stall. Results KAREN PERRY and JIM WHITE (Bell Helicopter Textron, Inc.,

182 09 RESEARCH AND SUPPORT FACILITIES (AIR)

Fort Worth, TX) IN: AHS, Annual Forum, 44th, Washington, DC, data on 140 channels and is controlled by two digital computers. June 16-18, 1988, Proceedings. Alexandria, VA, American Reserve ability, strain, and fatigue can be measured in order to Helicopter Society, 1988, p. 571-579. refs evaluate workloads, display concepts, and cockpit configurations. This paper describes a wind tunnel test of a one-sixth Froude Diagrams, drawings, graphs of typical data, and flow charts (all in scale model of an optimized design, advanced technology, English) are provided. T.K. soft-inplane, bearingless rotor. The model was designed to match not only the first out-of-plane and first inplane frequencies of the A89-19884# full-scale optimized rotor, but also the rotor torsional and second METHOD FOR SIMULATING TURBULENCE order out-of-plane and inplane modes. The rotor support system CHARACTERISTICS FOR WIND ENVIRONMENT IN WIND was designed to simulate the flexibilities of the full-scale helicopter, TUNNEL including pylon mount flexibility, mast-bending flexibility, and control SHUZO MURAKAMI and YASUSHIGE MORIKAWA Tokyo, system stiffness. The model was tested for pylon stability in hover University, Institute of Industrial Science, Report (ISSN 0040-9006), and for rotor lead-lag stability in forward flight. The effects of vol. 34, no. 4, Aug. 1988, p. 177-237. In Japanese, with abstract various aeromechanical couplings on aeroelastic stability was in English. refs investigated by testing four pitch-horn/pitch-link locations. The Methods of analyzing problems associated with wind in urban paper presents the results of these tests and correlation with the areas and around buildings are studied from an environmental COPTER computer analysis. Author engineering point of view. Research carried out on correlations and reproductions in wind tunnels of the atmospheric boundary A8919565 layer is considered. A comparison is made between numerical EVALUATION OF SIMULATOR MOTION CHARACTERISTICS and experimental data on mean wind speed, pressure, turbulence BASED ON AGARPAR-144 PROCEDURES intensity, power spectra, and frequency distributions. K.K. WILLIAM CHUNG and WILLIAM Y. WANG (SYRE, Moffett Field, CA) IN: Aerospace simulation 111; Proceedings of the SCS A89-19950# Multiconference, San Diego, CA, Feb. 3-5, 1988. San Diego, CA, FAN ACOUSTIC MODES MEASURING SYSTEM Society for Computer Simulation International, 1988, p. 177-188. KOUSUKE ISOMURA, YOSHIYA NAKAMURA, and ICHIRO This paper presents ?he results of applying a set of motion ISHIKAWA Ishikawajima-Harima Engineering Review (ISSN evaluation procedures based on performance criteria developed 0578-7904), vol. 28, July 1988, p. 244-250. In Japanese, with by the North Atlantic Treaty Organization Advisory Group for abstract in English. refs Aerospace Research and Development on the Vertical Motion The fan acoustic modes detecting system has been developed Simulator at Ames Research Center. The criteria being evaluated to separate fan rotor-stator and rotor-struts interaction noise to include the describing function, operational limits and acceleration evaluate the low-noise fan design method. To measure the data, noise. The procedures include the development of a real-time two devices were developed. One is the Induct Acoustic Modes operating system to generate the motion system drive commands Measuring Device to detect acoustic modes in the intake duct. and collect the response. The data analysis reveals the describing The other is the Radiated Acoustic Modes Measuring Device which function and operational envelopes of the six motion axes, and detects acoustic modes radiated from the duct lip to free field. To the cross coupling between the motion axes. Author analyze the data, the Noise Data Automatic Analyzer has been developed. This can analyze multple points of noise data A89-19808# automatically by utilizing the multiplexer system while the measuring AN INVESTIGATION OF WALL INTERFERENCE CORRECTION device is rotating slowly with some microphones on it. The system TO THE PRESSURE MEASUREMENT IN LOW SPEED WIND with all these devices enables detection of dominant acoustic TUNNEL WITH SOLID WALLS modes within 5 dB of accuracy. Author GUlQlNG JIANG (China Aerodynamics Research and Development Centre, Sichuan, People's Republic of China) Acta Aeronautica A89-20234 et Astronautica Sinica (ISSN 1000-6893), vol. 9, Aug. 1988, p. IMPROVING THE HALF-MODEL TECHNOLOGY IN THE 83758380. In Chinese, with abstract in English. GOElTlNGEN TRANSONIC WIND TUNNEL [VERBESSERUNG Pressure measurements were made on a group of cuboids DER HALBMODELLTECHNIK lM TRANSSONISCHEN and cylinders with streamlined nose in a low-speed wind tunnel. WINDKANAL GOElTlNGEN] Each group consists of models of different sizes with blockage G. HEFER, H. SOBIECZKY, and S. TUSCHE (DFVLR, Goettingen, ratio of 4.4, 6, 12, and 17.5 percent, respectively. During testing Federal Republic of Germany) IN: Yearbook 1987 II; DGLR, the pressure on the wall of the tunnel was measured, and the Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, pressure results corrected by wall pressure signature matrix method 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und are presented. The results show that although the flow Raumfahrt, 1987, p. 686-690. In German. characteristics around the two groups of models are completely (DGLR PAPER 87-083) different, the pressure coefficients of different models corrected A half-model with a boundary layer separation plate is described by the method tend to agree with each other. It has been proved whose inflow is calculated using pressure measurements in the that pressure at the stagnation point on the model is not affected nose area and is controlled using a flap at the separation plate by the wall and the wall blockage interference cannot be eliminated and a suction in the secondary flow channel. The device is suitable by applying dynamic pressure correction for the pressure now only for making pressure distribution measurements, but force measurement. Author measurements will be made in the future. Pressure distribution test results are presented. C.D. A89-19876# INTRODUCTION OF PILOT'S OPERATIONAL WORKLOAD A89-20245 EVALUATION RESEARCH SIMULATOR, POWERS, IN THE OETZTAL WIND TUNNEL AS BASIC IDEA AND AEROMEDICAL LABORATORY, JASDF INCENTIVE FOR PLANNING THE USAF RESEARCH CENTER ZOJIRO KATOH Japan Air Self Defence Force, Aeromedical AEDC TULLAHOMA [WINDKANAL OETZTAL ALS GRUNDIDEE Laboratory, Reports (ISSN 0023-2858), vol. 28, Dec. 1987, p. UND ANREGUNG FUER DIE PLANUNG DES 91-110. In Japanese, with abstract in English. refs US-LUWAFFENFORSCHUNGSZENTRUMSAEDC The design, performance, and applications of the POWERS TULLAHOMA] workload-evaluation simulator, developed to reproduce the flight ERNSTFRIED THIEL IN: Yearbook 1987 II; DGLR, Annual characteristics of a T-2 twin-engine jet trainer aircraft, are reviewed. Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, 1987, POWERS is a fixed-base single-seat simulator with two wide-FOV Reports. Bonn, Deutsche Gesellschaft fuer Luft- und Raumfahrt, computer-generated-image multipurpose displays; it permits 1987, p. 956-963. In German. refs simultaneous acquisition of pilot performance and physiological The history of the Oetztal wind tunnel, in its time the largest

183 and most important wind tunnel in the world, is retold. The 10 relationship of the tunnel to the USAF Tullahoma research center is examined. The role played by the Oetztal wind tunnel in ASTRONAUTICS aerodynamical advances is pointed out. C.D. Includes astronautics (general); astrodynamics; ground support N89-14241' National Aeronautics and Space Administration. systems and facilities (space); launch vehicles and space vehicles; Langley Research Center, Hampton, VA. space transportation; spacecraft communications, command and THE ISINCH MAGNETIC SUSPENSION AND BALANCE tracking; spacecraft design, testing and performance; spacecraft SYSTEM WIND TUNNEL WILLIAM G. JOHNSON, JR. and DAVID A. DRESS Jan. 1989 instrumentation; and spacecraft propulsion and power. 48 P (NASA-TM-4090; L-16515; NAS 1.1 54090) Avail: NTlS HC A03/MF A01 CSCL 148 NASA Langley has a small, subsonic wind tunnel in use with the 13-inch Magnetic Suspension and Balance System (MSBS). The tunnel is capable of speeds up to Mach 0.5. This report presents tunnel design and construction details. It includes flow uniformity, angularity, and velocity fluctuation data. It also compares experimental Mach number distribution data with computed results for the General Electric Streamtube Curvature Program. Author

N8914242# Illinois Inst. of Tech., Chicago. Fluid Dynamics Research Center. EQUIPMENT TO UPGRADE THE FACILITIES OF THE Ill (ILLINOIS INSTITUTE OF TECHNOLOGY) FLUID DYNAMICS RESEARCH CENTER Final Technical Report JOHN L. WAY, DAVID WILLIAMS, THOMAS CORKE, HASSAN NAGIB, and MUKUND ACHARYA Jun. 1988 3 p (Contract AF-AFOSR-0038-87) (AD-A198084; AFOSR-88-0742TR) Avail: NTlS HC A02/MF A01 CSCL 148 We are currently approaching the completion of the National Diagnostic Facility at IIT. The facility is based on a computer-controlledwind tunnel with a test section 4 ft. high, 5 ft. wide and 36 ft. long exhibiting very high quality flow conditions under both constant and oscillating free-stream velocity conditions. The funding of this facility was initiated under a 1983 DOD University Research Instrumentation Program (AFOSR-Grant-83-0339). A key aspect of the wind tunnel design is the manner in which heat energy produced by fan inefficiencies, is removed from the recirculating tunnel air. This involves the first use of turning vanes which also act as heat transfer elements. The system is sized to allow continuous operation of the wind tunnel at speeds of 250 fps, which is 2.5 times those of common university wind tunnels, and two hours of operation at the maximum tunnel velocity of 550 fps. This new and unique facility will be dedicated to basic research at near-flight Reynolds numbers, thereby, aiding in the design of the next generation of aircraft. The equipment acquired under this Grant has made many of these objectives become realities. GRA

N89-14243# Rockwell International Corp., Columbus, OH. Aircraft Operations. FABRICATION AND TESTING OF LIGHTWEIGHT HYDRAULIC SYSTEM SIMULATOR HARDWARE. PHASE 2 ADDENDUM Report, 15 N~v.1985 - 15 JuI. 1988 WILLIAM N. BICKEL and ROBERT K. HANING Jul. 1988 107 p (Contract N62269-80-C-0261) A8920233 (AD-A198524; NA-88-0011; NADC-79024-60-1) Avail: NTlS HC NEW APPLICATION POSSIBILITIES FOR BALLOON-BORNE AO6/MF A01 CSCL 200 CASE STUDIES - MIKROBA (MICROGRAVITY BY BALLOONS) Follow-on work was conducted in a development program to [NEUE ANWENDUNGSMOEGLICHKEITEN VON design, fabricate, and test a full scale 8000 psi Lightweight Hydraulic BALLONGESTUETZTEN FALLVERSUCHEN - MIKROBA System simulator. The principal task was the performance of an /MIKRO-GRAVITATION MI1 BALLONEN/] additional 600 hours of mission/profile cycling (1200 hours total). E. OVERESCH, K. KRETSCHMAR, and H. STOCKFLETH , Three flight control actuators completed approximately 5 million (OHB-System GmbH, Bremen, Federal Republic of Germany) IN: cycles under simulated aircraft loading. All minor hydraulic Yearbook 1987 11; DGLR, Annual Meeting, Berlin, Federal Republic components performed satisfactorily. The results demonstrated that 8000 psi hydraulic systems pose no technological problems for aircraft applications. Other tasks completed were ground support equipment re-work, piston seal evaluation test, coil tube design guidelines, black residue investigation, hybrid pump development, and tube fitting re-design. GRA

184 11 CHEMISTRY AND MATERIALS systems for producing microgravity are reviewed, and the rationale IN AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, for MIKROBA is described. The structure of the MIKROBA system Proceedings. Alexandria, VA, American Helicopter Society, 1988, is addressed, including the attitude control, propulsion, salvage p. 91 1-923. refs system, and flight control. C.D. Normal storage conditions can result in spontaneous body fractures in some AI alloys. Forged 7049T73 appears to be highly susceptible to this failure mechanism and is the primary subject of this paper. The very unusual failure mode is characterized by 11 critical crack formation and resultant static fracture in the parting plane of the forging. This environmentally induced cracking region CHEMISTRY AND MATERIALS is intergranular and resembles stress-corrosion cracking, except that there are no corrosion products. The failure mode was Includes chemistry and materials (general); composite materials; reproduced by extended exposure to conditions up to 180 F and inorganic and physical chemistry; metallic materials; nonmetallic 90 percent RH, with the resulting data used to predict real materials; and propellants and fuels. life-to-failure. Author A8919481 A8917619 CHEMICAL VAPOR DEPOSITION OF OXIDATION RESISTANT DWELL TIME EFFECTS ON THE FATIGUE BEHAVIOUR OF HFB2 + SIC COMPOSITE COATINGS TITANIUM ALLOYS W. J. LACKEY, ARLYNN W. SMITH, and DOUGLAS J. TWAIT 2. SONG and D. W. HOEPPNER (Utah, University, Salt Lake City) (Georgia Institute of Technology, Atlanta) Ceramic Engineering International Journal of Fatigue (ISSN 0142-1123), vol. 10, Oct. and Science Proceedings (ISSN 0196-6219), vol. 9, Sept.-Oct. 1988, p. 211-218. refs 1988, p. 1223-1231. refs Dwell effects on titanium alloys have drawn much attention (Contract NO0014-87-K-0036 N60921-86-C-0035) since the in-service failure of RB 21 1 fan disks in the early 1970s. Prior testing has repeatedly shown an HfB2 + SIC composite Different test methods and specimens have been used by different to have oxidation resistance superior to that of HfB2 or Sic. The invesiigators, and there is wide discrepancy and even contradiction majority of the prior work has relied on hot pressing or hipping for in the results. This study attempts to correlate findings from different fabrication. At!emp!s to prepare the material by chemical vapor researchers to draw some conclusions and to rationalize the deposition have been unsuccessful. Computerized thermodynamic existing discrepancies in the results. Suggestions are presented free energy minimization calculations have been performed that for future work to achieve better understanding of dwell effects predict reagent concentrations for the HfC14-CH3-SiC13-BC13-H2 on the behavior of titanium alloys and other materials. Author system which should result in the codeposition of the HfB2 + Sic composite at 1200-1500 K. Coatings of HfB2 + Sic offer A8917622 potential for oxidation protection of graphite and carbon-carbon PM AL ALLOYS - HOT PROSPECTS FOR AEROSPACE composites. Author APPLICATIONS W. E. FRAZIER (U.S. Navy, Naval Air Development Center, A8920243 Warminster, PA) Advanced Materials and Processes (ISSN STRENGTH OF DYNAMICALLY LOADED FORCE 0882-7958). vol. 134, Nov. 1988, p. 42-46. refs INTRODUCTION FOR FIBER-REINFORCED ROTORS A development status report is presented for [FESTIGKEIT VON DYNAMISCH BEANSPRUCHTEN dispersion-strengthened P/M AI alloys, whose resistance to creep KRAFTEINLEITUNGEN FUER FASERVERBUNDROTOREN] deformation and fatigue at service temperatures in excess of 375 H. BANSEMIR (Messerschmitt-Boelkow-Blohm GmbH, Munich, C recommends them as lower-density replacements for more Federal Republic of Germany) IN: Yearbook 1987 II; DGLR, expensive Ti alloys in supersonic aircraft primary airframe structures Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, and moderate-temperature turbine engine sections. The most highly 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und developed P/M AI alloys for such elevated-temperature applications Raumfahrt, 1987, p. 873-898. In German. refs are those produced via rapid solidification processing in the AI-Fe-X (DGLR PAPER 87-108) system, where X is Ce, Mo, Cr, or V; their strength and thermal Research results on retaining and bolt elements as well as stability is attributable to fine dispersions of incoherent intermetallic glues whose function is to retard erosion in fiber-reinforced phases, oxides, and carbides. O.C. composite helicopter rotor blades are discussed. Force introduction requirements for such rotors are reviewed. The dynamic strength A8918650 of bolts, retaining bonds, and erosion protection glues is PERFORMANCE OF COATED MATERIALS IN addressed. C.D. HIGH-ENTHALPY OXIDIZING GAS FLOWS [RABOTOSPOSOBNOST' MATERIALOV S POKRYTllAMl V A89-20244 WSOKOENTACPIINY KH OKISLITEL'NYKH GAZOWKH CARBON FIBER COMPOSITES FOR SUPERSONIC POTOKAKH] TECHNOLOGY [CFC-VERBUNDWERKSTOFFE FUER DEN P. D. LEBEDEV, A. G. SMOLIN. V. S. TERENT'EVA, and N. V. UEBERSCHALLFLUG] KHOLODKOV Akademiia Nauk SSSR, Izvestiia, Metally (ISSN H. LEIS (Messerschmitt-Boelkow-Blohm GmbH, Munich, Federal 0568-5303), Sept.-Oct. 1988, p. 157-164. In Russian. Republic of Germany) IN: Yearbook 1987 II; DGLR, Annual Methods of the analysis of the oxidizing capacity of gas flow Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, 1987, are examined with reference to conditions typically encountered Reports. Bonn, Deutsche Gesellschaft fuer Luft- und Raumfahrt, in the operation of high-speed flight vehicles. In particular, it is 1987, p. 899-921. In German. demonstrated that testing in stationary or low-velocity gas media (DGLR PAPER 87-124) is unacceptable for coatings used under conditions of high heat The production of carbon fiber composites for the supersonic transfer coefficients and pressure gradients. Performance testing high-temperature environment is discussed. The fabrication of the of such coatings must include laboratory testing under conditions fiber network, protection against oxidation, and the joining of multiparametric modeling. The heating temperature of the technology are addressed. The requisite characteristics of the material should be calculated with allowance for the possibility of finished product are examined, and the use of the composite in local superheating due to oxidation in the defect zone. V.L. aircraft applications is considered. C.D.

A8918925 N8913642'# National Aeronautics and Space Administration. ENVIRONMENTALLY INDUCED CRACKING IN ALUMINUM Lewis Research Center, Cleveland, OH. LUIS R. RODRIGUEZ (Kaman Aerospace Corp., Bloomfield, CT) THERMAL BARRIER COATINGS. ABSTRACTS AND FIGURES

185 11 CHEMISTRY AND MATERIALS

1985 220 p Workshop held in Cleveland, Ohio, 21-22 May Barrier Coatings. Abstracts and Figures p 187-196 1985 1985 Avail: NTlS HC AlO/MF A01 CSCL 11C (NASA-CP-10019; E-4425; NAS 1.551 0019) Avail: NTlS HC One of the main concerns of airline operators for the use of AlO/MF A01 CSCL 11C thermal barrier coatings (TBC) in the turbine is that the coating The Thermal Barrier Coatings Workshop was held May 21 will spall and cause a premature engine removal. Even though and 22, 1985, at the NASA Lewis Research Center in Cleveland, much cyclic data is available on TBCs, high time data is much Ohio. Six sessions covered Failure Mechanisms and Life Modeling, harder and expensive to come by. The typical 150 h type test Effects of Oxidation and Creep, Phase Stability and Microstructural used to qualify hardware, or modifications, falls far short of the 5 Aspects, Nondestructive and Analytical Assessment, Coating to 10,000 hour experience desired. One way to obtain data Development, and Alternative Applications. demonstrating the longevity of TBCs is through a service evaluation program on a commercial engine. For a meaningful evaluation of the TBC system it must be applied to a component which operates N89-13643*# Garrett Turbine Engine Co., Phoenix, AZ. in a typical hot end environment. In addition the component DEVELOPMENT OF THERMOMECHANICAL LIFE PREDICTION performance should not suffer if the coating is lost. For these MODELS FOR THERMAL BARRIER COATINGS T. E. STRANGMAN In NASA, Lewis Research Center, Thermal reasons Rolls-Royce chose to coat the IP turbine nozzle guide Barrier Coatings. Abstracts and Figures p 1-7 1985 vanes, and run these in an RB211 engine. Two ceramic top coats and several different bond coats were tested in a rainbow fashion Avail: NTlS HC AlO/MF A01 CSCL 11C on several engines. Three layer magnesium zirconate was used Thermal barrier coatings (TBCs) for turbine airfoils in as a base line. Various yttria stabilized zirconia ceramics were high-performance engines represent an advanced materials used. Top MCrAlY bond coats were applied by various techniques. technology with both performance and durability benefits. The Some of the coated vanes have now accumulated ofer hours. foremost TBC benefit is the reduction of heat transferred into 5000 The results are presented from the first sets with 2500 and 4200 air-cooled components. To achieve these benefits, however, the TBC system must be reliable. Mechanistic thermomechanical and hours of service respectively. Author thermochemical life models and statistically significant design data are therefore required for the reliable exploitation of TBC benefits N89-14264'# National Aeronautics and Space Administration. on gas turbine airfoils. Garrett's NASA-HOST Program Langley Research Center, Hampton, VA. (NAS3-23945) is designed to fulfill these requirements. This MATERIALS AND STRUCTURES FOR HYPERSONIC program focuses on predicting the lives of two types of VEHICLES strain-tolerant and oxidation-resistant TBC systems that are DARREL R. TENNEY, W. BARRY LISAGOR, and SIDNEY C. produced by commercial coating suppliers to the gas turbine DIXON Oct. 1988 46 p Presented at the 16th Congress of industry. The plasma-sprayed TBC system, composed of a the International Council of Aeronautical Sciences (CAS), low-pressure plasma-spray (LPPS) applied oxidation resistant Jerusalem, Israel, 28 Aug. - 2 Sep. 1988 Previously announced NiCrAlY bond coating, and an air-plasma-sprayed yttria partially in IAA as A89-13542 stabilized zirconia insulated layer is applied by both Chromalloy (NASA-TM-101501; NAS 1.15:101501) Avail: NTlS HC AO3/MF and Klock. The second type of TBC is applied by the electron A01 CSCL 11D beam-physical vapor deposition process by Temescal. Hypersonic vehicles are envisioned to require, in addition to Thermomechanical life models are being tailored to predict TBC carbon-carbon and ceramic-matrix composities for leading edges strain tolerance in terms of materials, engine, and mission heated to above 2000 F, such 600 to 1800 F operating temperature parameters. Continuum and fracture mechanics approaches and materials as advanced Ti alloys, nickel aluminides, and metal-matrix statistical methods are being evaluated to develop tensile and composited; These possess the necessary low density and high compressive strain functions required to drive a mission analysis strength and stiffness. The primary design drivers are maximum capable thermomechanical life model for TBCs. Results of initial vehicle heating rate, total heat load, flight envelope, propulsion testing to calibrate these life models will be presented. Author system type, mission life requirements and liquid hydrogen containment systems. Attention is presently given to aspects of these materials and structures requiring more intensive N89-13648*# National Aeronautics and Space Administration. development. Author Lewis Research Center, Cleveland, OH. AN INVESTIGATION OF ENVIRONMENTAL INFLUENCE ON THE CREEP BEHAVIOR OF A LOW PRESSURE PLASMA SPRAYED NICOCRALY ALLOY 12 M. G. HEBSUR and R. V. MINER ln its Thermal Barrier Coatings. Abstracts and Figures p 53-58 1985 ENGINEERING Avail: NTlS HC AlO/MF A01 CSCL 11C Low pressure sprayed MCrAlY overlay coatings are currently Includes engineering (general); communications; electronics and being used on advanced single crystal superalloy blades for gas electrical engineering; fluid mechanics and heat transfer; turbine engines. Many studies were made on the influence of instrumentation and photography; lasers and masers; mechanical coatings on the mechanical properties of superalloys in oxidizing or hot-corroding environments, but very few on the properties of engineering; quality assurance and reliability; and structural the bulk coating alloy itself. The creep behavior of a typical mechanics. NiCoCrAlY alloyd (PWA 276) was studied in air and vacuum. The as-received low pressure plasma sprayed NiCoCrAlY plates were heat treated for 4 h at 1080 C followed by 32 h at 870 C, the A89-17401' National Aeronautics and Space Administration. heat treatment applied to coated superalloy parts. Standard creep Langley Research Center, Hampton, VA. specimens 12.7 mm long and 3.2 mm in diameter were then MECHANICS OF FATIGUE CRACK CLOSURE machined. Constant load creep-rupture tests were performed in J. C. NEWMAN, JR., ED. (NASA, Langley Research Center, air and vacuum at 650,850, and 1050 C and various initial stresses. Hampton, VA) and WOLF ELBER, ED. (U.S. Army, Army In addition, some specimens were preoxidized at 1050 C for 100 Aerostructures Directorate, Hampton, VA) Philadelphia, PA, American Society for Testing and Materials, 1988, 675 p. For h prior to testing. Results are briefly discussed. Author individual items see A89-17402 to A89-17435. Papers are presented on plasticity induced crack closure, crack N89-13660'# Rolls-Royce, Inc., Atlanta, GA. closure in fatigue crack growth, the dependence of crack closure HIGH TIME SERVICE EVALUATION OF THERMAL BARRIER on fatigue loading variables, and a procedure for standardizing COATINGS ON THE ROLLS-ROYCE RB211 ENGINE crack closure levels. Also considered are a statistical approach to F. CHRIS TORI2 In NASA, Lewis Research Center, Thermal crack closure determination, the crack closure behavior of surface

186 12 ENGINEERING cracks under pure bending, closure measurements on short fatigue San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 1. cracks, and crack closure under plane strain conditions. Other Washington, DC, American Institute of Aeronautics and topics include fatigue crack closure behavior at high stress ratios, Astronautics, 1988, p. 382, 383. the use of acoustic waves for the characterization of closed fatigue (AIAA PAPER 88-3930) cracks, and the influence of fatigue crack wake length and state Some fiber optic systems for the high-altitude reconnaissance of stress on crack closure. R.R. vehicle are described. These are: (1) a single-fiber full duplex transmission system for multiple signals, and (2) a very-high-speed A8417448 data distribution network incorporating a crosspoint switch. The STRESS INTENSITY FACTORS FOR PERIODIC RADIAL electronic switch network will use an off-the-shelf GaAs switch. CRACKS IN A ROTATING DISC K.K. D. P. ROOKE (Royal Aircraft Establishment, Farnborough, England) and J. TWEED (Old Dominion University, Norfolk, VA) International A89-18105# Journal of Engineering Science (ISSN 0020-7225), vol. 26, no. 10, RELIABILITY IN FIBER OPTIC CABLE HARNESS 1988, p. 1059-1069. refs MANUFACTURING Stress intensity factors have been derived for periodically BRUCE M. MCCOY (Boeing Military Airplanes, Wichita, KS) IN: distributed radial cracks in rotating disks; both internal and edge AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, cracks have been studied. It is shown that in general as the CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, number of cracks increases, there is a shielding effect which lowers American Institute of Aeronautics and Astronautics, 1988, p. the stress intensity factors. Author 384-389. (AIAA PAPER 88-3931) A8917979 Key aspects of manufacturing cable harnesses for aircraft and INTERFACING SENSOR ASSEMBLIES WITH WINDOWLESS spacecraft that incorporate optical fiberlcables along with COCKPIT DISPLAYS traditional wiring are discussed. Issues regarding feasibility of JOHN J. DEVORE (Kansas State University, Manhattan) IEEE automation of assembly processes, manual assembly, testing, Transactions on Instrumentation and Measurement (ISSN installation, quality assurance, reliability and maintainability are 0018-9456). vol. 37, Dec. 1988, p. 501-505. Research sponsored addressed. Training procedures, formal training programs, and their by the Boeing Military Airplane Co. results are reviewed. Author An interface for converting aircraft instrument information into a video display was created. Due to the limited development time available, the interface was divided into two subsystems. The goal A89-18158# of the division was to allow concurrent work on two major system THE HIGH SPEED BUS TECHNOLOGY DEVELOPMENT components. The division used greatly aided the development, PROGRAM test, and calibration tasks. The key to being able to develop and M. T. LUDVIGSON, M. B. MODROW (Rockwell International Corp., test them simultaneously was attributable to two factors. Both Cedar Rapids, IA), and P. C. GOLDMAN (USAF, Avionics subsystems had local intelligence in the form of microprocessors, Laboratory, Wright-Patterson AFB, OH) IN: AIAAAEEE Digital and their interconection was kept physically simple. Testing of Avionics Systems Conference, 8th, San Jose, CA. Oct. 17-20, each subsystem was accomplished by simulating the other 1988, Technical Papers. Part 2. Washington, DC, American Institute subsystem on a general-purpose computer. It is concluded that of Aeronautics and Astronautics, 1988, p. 714-718. the testing went as expected. The only suprise when the instrument (AIAA PAPER 88-4005) interface was eventually connected to the PC was the lock-up The current development status of a high-speed data bus to problem. The system specifications and design, the link MIL-STD-1750A computers in avionics applications is reviewed instrument-toPC interface, the PC-resident software, and and illustrated with diagrams and photographs. The bus subsystem test and calibration are described. LE. requirements include data rate 50 Mb/s, a linear token-passing scheme permitting both electronic and fiber-optic implementation, up to 64-terminal capacity, maximum terminal separation 300 ft, A89-18094# latency control via token-rotation-timer priority, self-test and SHARING THE PROTECTION OF AIRCRAFT ELECTRONIC bus-loop test capability, and automatic clock synchronization. The SYSTEMS AGAINST THE EFFECTS OF HIGH-LEVEL design concept and performance of a breadboard wire bus tested ELECTROMAGNETIC ENVIRONMENTS BETWEEN in July 1986 are discussed in detail, with particular attention to TRADITIONAL PROTECTION AND SYSTEM ARCHITECTURE the redundancy manager, the output controller, the input controller, RICHARD F. HESS, LARRY J. YOUNT (Honeywell, Inc., Phoenix, the ringmaster topology manager, and typical initial-placement HENRY KNOLLER (Lockheed Aeronautical Systems Co., AZ), problems. T.K. Burbank, CA), GERALD M. MASSON (Johns Hopkins University, Baltimore, MD), and WILLIAM E. LARSEN (FAA, Moffett Field, CA) IN: AIAAAEEE Digital Avionics Systems Conference, 8th, A89-18159# San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 1. AN SAE HIGH SPEED RING BUS OVERVIEW Washington, DC, American Institute of Aeronautics and BRIAN W. KROEGER and HUBERT SHIH (Westinghouse Electric Astronautics, 1988, p. 294-307. refs Corp., Electronic Systems Group, Baltimore, MD) IN: AIAAAEEE (AIAA PAPER 88-3917) Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. It is shown how architectural techniques can be used as a 17-20, 1988, Technical Papers. Part 2. Washington, DC, American complement to traditional protection techniques to provide Institute of Aeronautics and Astronautics, 1988, p. 719-723. refs additional protection of sensitive avionics against high-level (AIAA PAPER 88-4008) electromagnetic fields. Consideration is given to potential threats, An overview of the protocols and important features of the the data processor susceptibility response, protection from the SAE high-speed ring bus (HSRB) standard is presented here, along threat, system architecture, and transparent recovery. The wave with the functional design of a typical ring interface unit architecture. shape of engineering waveforms that reproduce important lightning The counterrotating ring topology, with both loopback and bypass waveform parameters (amplitude, rise time, and action integral) is mechanisms, provides the high degree of fault tolerance desirable presented. K.K. in many military and avionic systems. The error-detection, fault-detection, and recovery mechanisms are briefly described to A89181 04# illustrate the robustness of the HSRB system. The reserved-priority FIBER OPTIC APPLICATIONS TO THE HIGH ALTITUDE token-passing protocol is shown to provide efficient and RECONNAISSANCE VEHICLE deterministic performance, uselful in real-time applications where C. E. POLCZYNSKI (Lockheed Aeronautical Systems Co., Burbank, messages must be transmitted predictably, quickly, and reliably. CA) IN: AIAAIIEEE Digital Avionics Systems Conference, 8th, Author

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A8918161# A8918757

THE.. .- FIBER. ~ OPTIC DATA DISTRIBUTION NETWORK - A GAAS MMICS SATISFY EW REQUIREMENTS NETWORK FOR NEXTOENERATION AVIONICS SYSTEMS JAIME G. TENEDORIO (Harris Corp., Microwave Semiconductor MARC D. COHN (Northrop hp., Advanced Systems Div., Pic0 Div., Milpitas, CA) and JAMES J. KOMIAK (General Electric Co., Rivera, CA) IN: AIAAAEEE Digital Avionics Systems Conference, Fairfield, CT) Microwaves 8 RF (ISSN 0745-2993), vol. 27, Nov. Bth, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. 1988, p. 51, 52, 54, 56. refs Washington, DC, American Institute of Aeronautics and The characteristics of GaAs MMlCs are discussed with Astronautics, 1988, p. 731-737. refs emphasis placed on the features required for their application to (AIAA PAPER 88-4011) electronic warfare. Several examples of GaAs MMlCs developed A fault-tolerant, high-performance interprocess communications for phased-array application are described. Attention is also given mechanism is required to support next-generation avionic platforms. to an X-band MMIC-based module designed for the multifunction The fiber-optic data distribution network (FDDN) provides the high active-array radar for fighter aircraft and to a C-band T/R module degree of availability and real-time performance necessary for designed for a ground-based tactical radar. Two examples of GaAs distributed avionic systems. State-of-the-art communication MMlC applications to electronic countermeasure technology are protocols, network management, and VLSl technology have been presented. IS. incorporated into the FDDN approach to offer avionic designers a powerful tool. Avionics communication requirements are briefly A8918766 examined, and the FDDN architecture is presented. Author MODAL ANALYSIS OF CONTINUOUS ROTOR-BEARING SYSTEMS C.-W. LEE and Y.-G. JEI (Korea Advanced Institute of Science A8918 185# and Technology, Seoul, Republic of Korea) Journal of Sound COMPUTER-AIDED ENGINEERING METHODS FOR and Vibration (ISSN 0022-46OX), vol. 126, Oct. 22, 1988, p. SUCCESSFUL VHSlC APPLICATION 345-361. refs R. GARY WOOD (Boeing Electronics Co., Seattle, WA) IN: Modal analysis is applied to continuous rotor systems with AlAAllEEE Digital Avionics Systems Conference, 8th, San Jose, various boundary conditions, including isotropic and anisotropic CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, natural boundary conditions. The rotor includes the effects of rotary American Institute of Aeronautics and Astronautics, 1988, p. inertia and gyroscopic moment. In particular, the whirl speeds and 887-894. refs mode shapes, backward and forward, of a rotating shaft are (AIAA PAPER 88-4035) obtained as spin speed and boundary conditions vary, and the Through the example of a VHSlC implementation of a unbalanced responses are calculated by using modal analysis. MIL-STD-1750A avionic processor subsystem, an effective The effects of asymmetry in boundary conditions on the system approach has applied CAE methods tailored to the job of VHSlC dynamic characteristics are also investigated. Author integration. Structured hierarchical design organization combined with rigorous mixed-mode digital simulation permitted an entire A89-18801 VHSIC-based subsystem and its integral application-specific IC A GUIDE TO CLASSICAL FLUlTER I design to be verified with a high degree of confidence. Accurate L. T. NIBLETT Aeronautical Journal (ISSN 0001-9240), vol. 92, performance data were obtained well in advance of fabrication. Nov. 1988, p. 339-354. refs Author First essentials of classical flutter are demonstrated by a comprehensive study of the behavior of a lifting surface with two A8918644 degrees of freedom under the action of airforces limited to those A STUDY OF CONTACT INTERACTION IN AIRCRAFT in phase with displacement. Structural coupling between the STRUCTURAL ELEMENTS [ ISSLEDOVANIE KONTAKTNOGO coordinates is eliminated by taking the normal modes to be the VZAlMODElSTVllA V ELEMENTAKH AVIATSIONNYKH deflection coordinates, and this results in conditions for stability KONSTRUKTSII] with particularly concise forms. It is shown that the flutter stability V. 1. GRlSHlN and T. K. BEGEEV Problemy Prochnosti (ISSN can be seen to be very much a matter of the relative amplitudes 0556-171X). Sept. 1988, p. 84-87. In Russian. refs of heave and pitch in the normal modes. In-quadrature airforces A procedure for calculating contact interaction between the are then introduced and it is shown that they have little effect structural elements of aircraft is proposed which employs the when the flutter is severe. They are of more importance in the method of finite elements in displacements. The method has been milder forms of flutter, the extreme of which are shown to be little implemented in a specialized software pack. The convergence different from instabilities in a single degree of freedom. Author and reliability of the method are evaluated, and solutions are presented for two-dimensional, axisymmetric, and three- A8918852 dimensional problems involving riveted and bolted joints. V.L. A ’NEW PHILOSOPHY OF STRUCTURAL RELIABILITY, FAIL SAFE VERSUS SAFE LIFE KENNETH B. AMER (Rand Corp., Santa Monica, CA) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, A8918741 Proceedings. Alexandria, VA, American Helicopter Society, 1988, GROUND SIMULATION FOR AIRBORNE EQUIPMENT p. 3-16. refs D. SlMS (British Aerospace, PLC, Air Weapons Div., Hatfield, The draft RFP for the US. Army’s LHX requires a factor of England) Environmental Engineering (ISSN 0954-5824), vol. 1, reliability against catastrophic failure of 0.999999 in a 10,000-hour Sept. 1988, p. 31-33, 36. refs service life; any attempt to meet this requirement through a safe-life This paper discusses the application of acoustic techniques design approach will impose major weight and cost penalties for realistic representation of the service environment for airborne relative to current stress-analysis procedures. An account and equipment and for the reproduction of the various stresses of comparative evaluation is presently given for the alternative, operational life in the correct combinations, sequences, and levels. ’fail-safe’ redundant design approach, and to the possibility of It is shown that vibrations of the type similar to that seen in combining fail-safe and safe-life design practices where required. service can be induced by applying high-intensity noise to the The combination of the two approaches eliminates both weight outer skin; it is possible to provide the required distributed input and cost penalties while reducing the probability of catastrophic to the store’s surface in all axes at once. The US. and the U.K. failure. O.C. programs set up to develop acoustic techniques have demonstrated that the acoustic method of testing yields superior results, as A841887 1 compared to methods that use mechanical vibrators, in representing HELICOPTER VIBRATION ANALYSIS AND CONTROL the aircraft carriage flight vibrational environment. IS. DALE CLAY (McDonnell Douglas Helicopter Co., Mesa, AZ) and

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JIM CHADWICK (Chadwick-Helmuth Co., Inc., El Monte, CA) IN: test. Numerous other tests, such as simulated tree strikes, AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, rain/sand erosion, and paint adhesion were also performed. Proceedings. Alexandria, VA, American Helicopter Society, 1988, Author p. 243-250. refs The present evaluation of available methods for helicopter A8948894 vibration characteristics’ determination-and-control projects GENESIS OF A FLEXIBLE TURNING CENTER prospective, Higher Harmonic Control (HHC) systems in light of PAUL SANCLEMENTE and ROBERT D. FRENCH (General Electric both observed technology-performance trends and the features Co.,Lynn Aircraft Engine Production Div., MA) IN: AHS. Annual and capabilities of the recently implemented OH-6A helicopter HHC Forum, 44th, Washington, DC, June 16-18, 1988, Proceedings. system. In the OH-6A, the HHC hydraulic actuators have been Alexandria, VA, American Helicopter Society, 1988, p. 497-503. placed in parallel with the existing control system to allow fail-safe GE - Aircraft Engines has designed, built, and is operating a reversion in the event of hydraulic failure. Attention is given to flexible turning center for jet engine hardware. Although the plant the effects of HHC on blade and pitch-link loads, tail boom is in the forefront of manufacturing technology development, it vibrations, and transient maeuvers. O.C. was intended from the start to be a production facility. So while there was much to learn from being involved in all phases of the A8818884 project, meeting production schedules was, and is, key to its OPTIMAL DESIGN OF AN ADVANCED COMPOSITE success. This paper reviews the early history of the project and ROTATING FLEXBEAM ends with a view of its recent production status. Author BRIAN HAMILTON, JAMES PETERS, and CYNTHIA CALLAHAN (McDonnell Douglas Helicopter Co., Mesa, AZ) IN: AHS, Annual A89-18895 Forum, 44th, Washington, DC, June 16-18, 1988, Proceedings. AUTOMATED WIRE PREPARATION SYSTEM Alexandria, VA, American Helicopter Society, 1988, p. 409-421. DEBORAH J. MCCULLEY (McDonnell Douglas Helicopter Co., This paper presents an automated procedure for the design Mesa, AZ) IN: AHS, Annual Forum, 44th, Washington, DC, June analysis of composite flexbeams for bearingless rotor hubs. 16-18, 1988, Proceedings. Alexandria, VA, American Helicopter State-of-the-art finite element and optimization methods were Society, 1988, p. 505-511. inccrporated to develop a mathematical model which is used to The first step toward an automated wire harness facility for perform flexbeam sizing. The automation of this analysis tool the aerospace industry has been taken by implementing the Wire enables flexbeam design iterations to be reduced from nearly six Vektor 2000 into the wire harness preparation area. An overview months to less than a week with a minimum of computational of the Wire Vektor 2000 is given, including the facilities for wire requirements. C.D. cutting, marking, and transporting, for wire end processing, and for system control. Production integration in the Wire Vektor 2000 A8918891 system is addressed, considering the hardware/software debug NONDESTRUCTIVE TESTING OF COMPOSITE AIRCRAFT system and the system throughput. The manufacturing changes STRUCTURES WITH INFRARED AND SHEAROGRAPHIC that have to be made in implementing the Wire Vektor 2000 are IMAGING TECHNOLOGIES discussed. C.D. JOHN W. NEWMAN (Laser Technology, Inc., Norristown, PA) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, 1988, A8918897 Proceedings. Alexandria, VA, American Helicopter Society, 1988, DYNAMIC MODELING OF A HELICOPTER LUBRICATION p. 481-485. SYSTEM The increased use of advanced composite materials for primary WILLIAM A. WELSH (United Technologies Corp., Sikorsky Aircraft aircraft structures and blading has placed new and difficult demands Div., Stratford, CT) IN: AHS, Annual Forum, 44th, Washington, on the traditional methods of nondestructive testing, from both DC, June 16-18, 1988, Proceedings. Alexandria, VA, American the productivity and maintainability standpoints. Two new Helicopter Society, 1988, p. 531-544. refs technologies, electronic shearography and thermal/microwave A dynamics model of a typical helicopter transmission lubrication coupled infrared imaging, offer dramatic increases in testing system is presented. The computer fluid and structural model is throughput and sensitivity to defects in materials and structures. shown to correctly simulate both mean pressures and also a Electronic shearography has a proven application in the detection troublesome self-excited pressure oscillation phenomenon seen in of unbonds, crushed core, impact damage, and delamination in test. The model is effectively utilized to predict the efficacy of composites, honeycomb, and foam-cored structures. Corrosion in design changes intended to stabilize the chatter. Author aluminum honeycomb is easily detected. Thermal/microwave coupled infrared imaging can easily detect delaminations and A89-18906’ National Aeronautics and Space Administration. entrapped moisture. The paper will provide a background to these Lewis Research Center, Cleveland, OH. new technologies and discuss field tests. Author ADVANCED TRANSMISSION STUDIES JOHN J. COY (NASA, Lewis Research Center, Cleveland, OH) A89-18892 and ROBERT C. BILL (NASA, Lewis Research Center; U.S. Army, ACHIEVING RELIABILITY AND MAINTAINABILITY GOALS Propulsion Directorate, Cleveland, OH) IN: AHS, Annual Forum, WITH A COMPOSITE MAIN ROTOR BLADE 44th, Washington, DC, June 16-18, 1988, Proceedings. Alexandria, JAMES T. HALL and HERMAN FRANKS (Bell Helicopter Textron, VA, American Helicopter Society, 1988, p. 651-662. Previously Inc., Fort Worth, TX) IN: AHS, Annual Forum, 44th, Washington, announced in STAR as N88-21454. refs DC, June 16-18, 1988, Proceedings. Alexandria, VA, American The NASA Lewis Research Center and the U.S. Army Aviation Helicopter Society, 1988, p. 487-492. Systems Command share an interest in advancing the technology The UH-1H Composite Main Rotor Blade (CMRB) represents for helicopter propulsion systems. In particular, this paper presents the current state-of-the-art in main rotor blades. To complement highlights from that portion of the program in drive train technology the new design, stringent R8M requirements were imposed. The and the related mechanical components. The major goals of the intensive design support program and an extensive program are to increase the life, reliability, and maintainability; test/validation/demonstration effort to qualify the blade are reduce the weight, noise, and vibration; and maintain the relatively described. The CMRB has had the most extensive test program high mechanical efficiency of the gear train. The current activity ever pursued in the development of a main rotor blade. Fatigue emphasizes noise reduction technology and analytical code tests were performed on both clean and repaired blades. A development followed by experimental verification. Selected MIL-STD-471A maintainability demonstration was conducted which significant advances in technology for transmissions are reviewed, included 37 blade repairs of typical field incurred damage. Following including advance configurations and new analytical tools. Finally, the demonstration, the repaired blade underwent a 1OO-hour whirl the plan for future transmission research is presented. Author

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A8818907 the presence of aperiodic responses characterized by spectral ADVANCED LUBE SYSTEM DIAGNOSTICS FOR V-22 sidebands which diverge with increasing shaft speed is noted. An HENRY M. BELMAN and FRANK DIPASQUALE (Aeroquip Corp., explanation of the mechanism generating these sidebands is Tedeco Div.. Glenolden, PA) IN: AHS, Annual Forum, 44th, advanced. Author Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, American Helicopter Society, 1988, p. 663-671. refs A8949718 The next generation of military aircraft, entering service in the TURBINE DESIGN USING COMPLEX MODES AND early to mid-1990s will incorporate innovative sensing technology SUBSTRUCTURING in many systems in order to maximize reliability and maintainability H.-L. OLAUSSON (ABB Stal, AB, Finspong, Sweden) and B. J. characteristics, improve safety and operational readiness and TORBY (California State University, Long Beach) International reduce the cost of ownership. A sophisticated new concept in Journal of Analytical and Experimental Modal Analysis (ISSN on-line, oil debris based diagnostics - the Quantitative Debris 0886-9367), vol. 3, Oct. 1988, p. 148-157. refs Monitor (QDM) - used in conjunction with a uniquely designed A complex modal-analysis method for studying the behavior of housing, which insures a very high probability of wear particle a turbine near its design speed is presented. The modal calculations capture, has been applied to the V-22 so as to optimize early account for gyroscopic moments as well as nonsymmetric bearing failure detection capability and reduce the ’false alarm’ rate. The effects. Results of calculations performed for a 650 MW ASEA OSPREY is unique in the fact that it will be the first aircraft to STAL turbine installation are presented. K.K. utilize this system in both engines and gearboxes. This paper will discuss the details of the application of these devices - in the A8819806# form of new sensors, supporting integrated circuits and novel oil THE COMBINATION OF SIMULATION AND RESPONSE debris separators - for each gearbox and engine of the V-22. METHODOLOGY AND ITS APPLICATION IN AN AGGREGATE Author PRODUCTION PLAN ZHlMlNG CHEN and YUNCHENG FENG (Beijing University of A89-18926 Aeronautics and Astronautics, People’s Republic of China) Acta MATRIX ANALYSIS METHOD FOR COMPOSITE FLEXBEAM Aeronautica et Astronautica Sinica (ISSN 1000-6893). vol. 9..- Aua. SMRlTlMAY DATA and ROBERT R. FILLER (McDonnell Douglas 1988, p. 8359-8365. In Chinese, with abstract in English. refs Helicopter Co., Mesa, AZ) IN: AHS, Annual Forum, 44th, This paper describes an algorithmic structure for combining Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, simulation and optimization techniques both in theory and practice. American Helicopter Society, 1988, p. 925-929. Response surface methodology is used to optimize the decision I A helicopter rotor composite flexbeam is discussed and a variables in the simulation environment. A simulation-optimization method of analysis is presented. The flexbeam is modeled into a software has been developed and successfully implemented, and number of beam elements. The analysis has two major divisions - its application to an aggregate production planning overall beam load-displacement analysis and ply analysis in the simulation-optimization model is reported. The model’s objective individual beam elements for the computed loadings. The is to minimize the production cost and to generate an optimal methodology presented for beam analysis is a direct method which production plan and inventory control strategy for an aircraft is derived from the basic techniques of structural analysis. Since factory. C.D. I a composite flexbeam may be represented by an assemblage of one-dimensional elements only, the direct method is as powerful as the variational method of finite element analysis. Author A89-19909*# Korean Inst. of Science and Technology, Seoul. , PLENUM CHAMBER EFFECT ON WIND-TUNNEL RESONANCE 1 BY THE FINITE-ELEMENT METHOD A89-18936# IN LEE (Korea Advanced Institute 01 Science and Technology, I ROBOTIC DEBURRING OF COMPLEX MACHINED PARTS Seoul, Republic of Korea) (Structures, Structural Dynamics and FREDERICK C. EDMAN and GARY H. BURDORF (McDonnell Materials Conference, 27th, San Antonio, TX, May 19-21, 1986, 1 Douglas Helicopter Co., Mesa, AZ) AHS, Annual Forum, 44th, Technical Papers. Part 2, p. 266-278) AlAA Journal (ISSN Washington, DC, June 16-18, 1988, Paper. 4 p. 0001-1452). vol. 26, Sept. 1988, p. 1087-1093. Previously cited in i Using an articulated-arm five axis robot, McDonnell Douglas issue 18, p. 2658, Accession no. A86-38909. refs I Helicopter Company has developed a robotic deburring and (Contract NGL-05-020-243) blending cell for complex machined parts. Previous to the development of this robotic deburring cell, most deburring and blending was performed manually with hand-held airmotors A89- 199 11 # equipped with abrasive disks, wheels, brushes, or rotary files. This BUCKLING AND FINAL FAILURE OF GRAPHITE/PEEK labor-intensive methodology for deburring AH-64 Apache machined STIFFENER SECTIONS parts leads to inconsistent edge finishes from part to part, in SCOTT M. CAUSBIE (Boeing Commercial Airplane Co., Seattle, addition to being fatiguing and repetitious for the operator. The WAI and PAUL A. LAGACE (MIT, Cambridqe, MA) (Structures, robotic deburring cell was implemented into production in July of Structural Dynamics and Materials Conference, 27th, San Antonio, 1987. Some of the benefits achieved by the robotic cell are: 60 TX, May 19-21, 1986, Technical Papers. Part 1, p. 280-287) AlAA percent reduction in deburr cycle times, improved quality, and Journal (ISSN 0001-1452), vol. 26, Sept. 1988, p. 1100-1106. eliminated part rework. Author Previously cited in issue 18, p. 2655, Accession no. A86-38831. refs A8919125 DYNAMICS OF A RIGID ROTOR MOUNTED ON A89201 14 DISCONTINUOUSLY NON-LINEAR ELASTIC SUPPORTS TELEPORT AS A CONCENTRATION POINT FOR DOMESTIC R. D. NEILSON and A. D. S. BARR (Aberdeen, University, AND INTERNATIONAL TRAFFIC Scotland) Institution of Mechanical Engineers, Proceedings, Part ANAND KUMAR (Washington International Teleport, Washington, C - Mechanical Engineering Science (ISSN 0263-7154), vol. 202, DC) IN: EASCON ’88; Proceedings of the Twenty-first Annual no. C5, 1988, p. 369-376. Research supported by the Ministry of Electronics and Aerospace Conference, Arlington, VA, Nov. 9-1 1, Defence. refs 1988. New York, Institute of Electrical and Electronics Engineers, The equations of motion of a rigid rotor mounted at both ends Inc., 1988, p. 109-114. in discontinuously nonlinear supports and subject to excitation by The teleport concept is defined, and types of teleports are arbitrary imbalance are presented. The methods used to solve described. The Washington International Teleport is discussed as the equations are described briefly and the responses obtained an example. It is argued that major teleports should concentrate from the model and an experimental rig are discussed and on three major areas of implementation and growth to create a compared. Good correlation is found. Over a range of shaft speed successful gateway linking domestic and international networks.

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These areas are video networks, private networks, and international accomplished on the BRL Flight Simulator using a full-scale cylinder voiceldata networks. LE. and larger instrumentation payload capacity. GRA

A89-20146'# National Aeronautics and Space Administration. N89-13735# Naval Ship Research and Development Center, Langley Research Center, Hampton, VA. Bethesda, MD. MODERN WING FLUTTER ANALYSIS BY COMPUTATIONAL A POTENTIAL FLOW SOLUTION ON MARINE PROPELLER FLUID DYNAMICS METHODS AND AXIAL ROTATING FAN Final Report HERBERT J. CUNNINGHAM, JOHN T. BATINA, and ROBERT M. Y. T. LEE, C. W. JIANG, and T. W. BElN Aug. 1988 30 p BENNETT (NASA, Langley Research Center, Hampton, VA) (AD-A198781; DTRC-88/031) Avail: NTlS HC AO3/MF A01 Journal of Aircraft (ISSN 0021 -8669), vol. 25, Oct. 1988, p. 962-968. CSCL 20D Previously cited in issue 22, p. 3690, Accession no. A88-51329. Integral equations are derived to model the solid surfaces and refs the inlet condition for both external and internal flows with an axially rotating element. Vortex filaments are used to simulate the A89-20188# lifting surfaces. Global iterations for surface-panel source densities ANALYSIS OF ARTIFICIAL DISSIPATION MODELS FOR THE and vortex strengths are used in conjunction with the Neumann TRANSONIC FULL-POTENTIAL EQUATION iterations for solving integral equations. A special kernel treatment GEORGE S. DULIKRAVICH (Pennsylvania State University, is adopted in the solution scheme of the integral equation. Solutions University Park) AlAA Journal (ISSN 0001-1452), vol. 26, Oct. converge within 10 to 20 iterations. Calculated results and 1988, p. 1238-1245. Previously cited in issue 07, p. 1010, Accession measured data for a propeller tested in open water are in good no. A88-22536. refs agreement. Predictions are also made for an axial-flow pump. The overall performance parameters for the pump agree within a few percent of the design values. GRA A89-20315# EVALUATION OF ALUMINUM-LITHIUM ALLOYS IN COMPRESSION-STIFFENEEDAIRCRAFT STRUCTURES N89-13736# Illinois Inst. of Tech., Chicago. Fluid Dynamics J. C. EKVALL and D. J. CHELLMAN (Lockheed Aeronautical Research Center. Systems Co., Burbank, CA) Journal of Aircraft (ISSN 0021 -8669), MANAGEMENT AND CONTROL OF SEPARATION BY vol. 25, Nov. 1988, p. 1001-1008. Previously cited in issue 17, p. UNSTEADY AND VORTICAL FLOWS Final Technical Report, 2691, Accession no. A87-39641. refs Oct. 1984 - Oct. 1987 HASSAN M. NAGIB, MUKUND ACHARYA, PATRICK H. REISENTHEL, JOHN L. WAY, and DAVID R. WILLIAMS Jun. A89-20324'# Notre Dame Univ., IN. 1988 7 p METHOD OF COLD SMOKE GENERATION FOR VORTEX (Contract F49620-84-C-0080) CORE TAGGING (AD-A198902; AFOSR-88-0745TR) Avail: NTlS HC A02/MF A01 R. C. NELSON, T. T. NG (Notre Dame, University, IN), and K. D. CSCL 01A VISSER Journal of Aircraft (ISSN 0021-8669), vol. 25, Nov. Management and Control of 2-D and 3-D separated flows by 1988, p. 1069-1071. refs unsteady and/or vortical flows is investigated in a number of (Contract NCA2-162) configurations aimed at an enhanced basic understanding of Attention is given to the flow-visualization problem posed by governing mechanisms. The investigations are aimed at impacting the 'dark-core' region of the vortices formed on the upper side of a delta wing; the low particle density in the core region minimizes the design of future generations of aircraft with improved maneuverability for better performance and safety. Also, novel the density of tracing particles whose presence is essential in techniques are being developed for the measurement, mapping LDV measurements. An effort is presently undertaken using Tic14 and documentation of these complex unsteady flowfields. GRA smoke in subsonic wind tunnel tests of a 70-deg sweep delta wing model. O.C. N89-13746'# National Aeronautics and Space Administration. N89-13727# Ballistic Research Labs., Aberdeen Proving Ground, Ames Research Center, Moffett Field, CA. MD. AN EXPERIMENTAL AND ANALYTICAL EVALUATION OF THE INTERNAL PRESSURE MEASUREMENTS FOR A LIQUID TAPERED TENSION-TORSION STRAP CONCEPT PAYLOAD AT LOW REYNOLDS NUMBERS ALEXANDER LOUIE Nov. 1988 18 p DAVID J. HEPNER, KEITH P. SOENCKSEN, BRADFORD S. DAVIS, (NASA-TM-101049; A-88321; NAS 1.15:101049) Avail: NTlS HC and NICHOLAS G. MAIORANA Jun. 1988 63 p AOBlMF A01 CSCL 20D (ADA197438; AD-E900740; BRL-MR-3674) Avail: NTlS HC A new free-tip rotor moment controller designed to increase A04/MF A01 CSCL 01A torque output (a restoring moment) was proposed. The controller Spin-stabilized projectiles can experience poor flights due to would be used as a retention device for the freely pitching tip of the influence of liquid payloads. Substantial analytical and numerical a helicopter rotor. The new design featured a tapered work has been done on this problem, but quality experimental tension-torsion strap instead of the previously used parellel strap. data on the primitive variables of the liquid (pressure and velocity) A tapered strap has a larger separation between the tension wires are still required to evaluate the accuracy and applicability of models at the retention end than at the oscillating end; separation is and codes. In free gyroscope tests for Reynolds numbers less equal at both ends for a parallel strap. A simple dynamic analysis than 100, the broadening effect of low Reynolds numbers is also was developed and an experiment performed to evaluate this evident. Evidence of related liquid instabilities for actual flight data tapered strap concept. The test results indicated that the torsional was reported. A full-scale three-degree-of-freedomflight simulator spring stiffness of the strap, represented by a torsional pendulum, was used to examine both endwall and sidewall pressure increased with the amount of taper. The predicted dynamic fluctuations, as well as the phase relationship between the characteristics of the pendulum also confirmed this observation maximum pressure and cylinder orientation for a high Reynolds and correlated reasonably well with the experimental results. It number of 18,200. Scale simulations of high viscosity liquid could be concluded from the experimental and analytical results payloads were completed for a Reynolds number range of 3.1 to that the tapered strap accomplished increased torque output when Author 8.9. Testing included establishing instrumentation reliability, compared to the parellel strap. repeating previously published low Reynolds number data, expanding the range in nondimensional coning frequency and N89-13747'# National Aeronautics and Space Administration. Reynolds number, and providing a data base for comparisons Ames Research Center, Moffett Field, CA. with current linear theory applications at low Reynolds number. SURFACE GRID GENERATION FOR COMPLEX Based on these preliminary results, extensive testing can be THREE-DIMENSIONAL GEOMETRIES

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RAYMOND CHING-CHUNG LUH OCt. 1988 15 p N89-13755'# Purdue Univ., West Lafayette, IN. School of (NASA-TM-101046; A-88318; NAS 1.15:101046) Avail: NTlS HC Aeronautics and Astronautics. AO3/MF A01 CSCL 20D LDV MEASUREMENTS IN AN ANNULAR COMBUSTOR MODEL An outline is presented for the creation of surface grids from M.S. Therh primitive geometry data such as obtained from CAD/CAM systems. DEAN A. BARRON Aug. 1986 161 p The general procedure is applicable to any geometry including full (Contract NAS3-24350) aircraft with wing, nacelle, and empennage. When developed in (NASA-CR-182207; NAS 1.261182207; PURDUE-MS-34971) an interactive graphics environment, a code based on this Avail: NTlS HC AO8/MF A01 CSCL 20D procedure is expected to substantially improve the turn around The design and setup of a Laser Doppler Velocimeter (LDV) time for generating surface grids on complex geometries. Results system used to take velocity measurements in an annular are shown for a general hypersonic airplane geometry. Author combustor model are covered. The annular combustor model is of contemporary design using 60 degree flat vane swirlers, producing a strong recirculation zone. Detailed measurements are N89-13751# Illinois Inst. of Tech., Chicago. Fluid Dynamics taken of the swirler inlet air flow and of the downstream enclosed Research Center. swirling flow. The laser system used is a two color, two component MANAGEMENT ANDCONTROLOF UNSTEADY AND system set up in forward scatter. Detailed are some of the special TURBULENT FLOWS Annual Technical Report, Oct. 1986 - considerations needed for LDV use in the confined turbulent flow Oct. 1987 of the combustor model. The LDV measurements in a single swirler HASSAN M. NAGIB, MUKUND ACHARYA, THOMAS C. CORKE, rig indicated that the flow changes radically in the first duct height. PATRICK H. REISENTHEL, and CANDACE E. WARK Jun. 1988 After this, a flow profile is set up and remains constant in shape. The magnitude of the velocities gradually decays due to viscous 15 P (Contract F49620-86-C-0133) damping. Author (AD-A198091; AFOSR-88-0747TR) Avail: NTlS HC A03/MF A01 CSCL 20D N89-13756'# United Technologies Research Center, East Progress in four areas of research has been achieved during Hartford, CT. the first year: (1) controlled transitioning boundary layers; phase THE EFFECTS OF INLET TURBULENCE AND coupled plane TS waves and oblique waves are used to study ROTOR/STATOR INTERACTIONS ON THE AERODYNAMICS various types of transition including detuned modes, (2) turbulent AND HEAT TRANSFER OF A LARGE-SCALE ROTATING boundary layer structure and control; the structures responsible TURBINE MODEL, VOLUME 1 Final Report for the turbulence production in high Reynolds number boundary R. P. DRING, M. F. BLAIR, H. D. JOSLYN, G. D. POWER, and J. layers have been documented and manipulated, (3) management M. VERDON Washington, D.C. Jul. 1987 173 p of unsteady and three-dimensional flows; flows over airfoils, (Contract NAS3-23717) axisymmetric forebodies, vortex-wing interactions, and wing-body (NASA-CR-4079; E-3536; NAS 1.26~4079; junctions, are examined with and without passive and active flow UTRC-R86-956480-VOL-1) Avail: NTlS HC AO8/MF A01 CSCL , manipulators including zero-mass base bleed, (4) scanning laser 20D anemometry; a technique capable of mapping the flowfield in a A combined experimental and analytical program was conducted plane has been developed. GRA to examine the effects of inlet turbulence on airfoil heat transfer. Heat transfer measurements were obtained using low conductivity airfoils with miniature thermocouples welded to a thin, electrically N89-13754'# General Motors Corp., Indianapolis. IN. Allison heated surface skin. Heat transfer data were acquired for various Gas Turbine Div. combinations of low or high inlet turbulence intensity, flow THE EFFECTS OF LEADING EDGE AND DOWNSTREAM FILM coefficient (incidence), first-stator/rotor axial spacing, Reynolds COOLING ON TURBINE VANE HEAT TRANSFER Final Report number, and relative circumferential position of the first and second L. D. HYLTON, V. NIRMALAN, B. K. SULTANIAN, and R. M. stators. Aerodynamic measurements include distributions of the KAUFMAN Nov. 1988 175 p mean and fluctuating velocities at the turbine inlet and, for each (Contract NAS3-24619) airfoil row, midspan airfoil surface pressures and circumferential (NASA-CR-182133; NAS 1.26:182133; ALLISON-EDR-13481) distributions of the downstream steady state pressures and Avail: NTlS HC AOWMF A01 CSCL 200 fluctuating velocities. Analytical results include airfoil heat transfer The progress under contract NAS3-24619 toward the goal of predictions and a examination of solutions of the unstead boundary establishing a relevant data base for use in improving the predictive layer equipment. Author design capabilities for external heat transfer to turbine vanes, including the effect of downstream film cooling with and without N89-13784# Texas A&M Univ., College Station. Turbomachinery leading edge showerhead film cooling. Experimental measurements Labs. were made in a two-dimensional cascade previously used to obtain THE MEASUREMENT AND PREDICTION OF ROTORDYNAMIC vane surface heat transfer distributions on nonfilm cooled airfoils FORCES FOR LABYRINTH SEALS Flnal Report, 1 Sep. 1982 - under contract NAS3-22761 and leading edge showerhead film 31 Dec. 1987 cooled airfoils under contract NAS3-23695. The principal D. W. CHILDS and D. L. RHODE Mar. 1988 212 p independent parameters (Mach number, Reynolds number, (Contract F49620-82-K-0033) turbulence, wall-to-gas temperature ratio, coolant-togas (AD-A1971 85; AFOSR-88-0662TR) Avail: NTlS HC AlO/MF A01 temperature ratio, and coolant-to-gas pressure ratio) were CSCL 13G maintained over ranges consistent with actual engine conditions Measurements of rotordynamic (stiffness and damping) and the test matrix was structured to provide an assessment of coefficients and leakage characteristics were completed for the independent influence of parameters of interest, namely, exit labyrinth-rotor/honeycombe stator seals. Comparisons to Mach number, exit Reynolds number, coolant-to-gas temperature labryinth-rotor/smooth-stator seals showed no stability ratio, and coolant-to-gas pressure ratio. Data provide a data base improvements. Tests were also carried out on smooth-rotor/ for downstream film cooled turbine vanes and extends the data honeycombe-stator seals and demonstrated superior bases generated in the two previous studies. The vane external stability and leakage performance for this type of seal if the entering heat transfer obtained indicate that considerable cooling benefits flow is pre-rotated in the direction of rotation. A new bulk-flow can be achieved by utilizing downstream film cooling. The data theory for labyrinth seals has been developed and its prediction obtained and presented illustrate the interaction of the variables compares well with measured results for tooth-on-rotor labyrinths. and should provide the airfoil designer and computational analyst Also, a more sophisticated model was developed which solves , the information required to improve heat transfer design capabilities the 3-D Reynolds-averaged Navier-Stokes equations for I for film cooled turbine airfoils. Author compressible flow. GRA

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N89-13794'# National Aeronautics and Space Administration. applied load, the overall test data correlated fairly well with Lewis Research Center, Cleveland, OH. theoretically predicted buckling interaction curves. The structural EFFECT OF ADVANCED COMPONENT TECHNOLOGY ON efficiency of the tubular panels was slightly higher than that of HELICOPTER TRANSMISSIONS the beaded panels which they replaced. Author DAVID G. LEWlCKl and DENNIS P. TOWNSEND 1989 18 p Prepared for presentation at the International Power Transmission N89-13817'# Florida Atlantic Univ., Boca Raton. Dept. of Ocean and Gearing Conference, Chicago, Ill., 25-27 Apr. 1989; sponsored Engineering. by ASME Prepared in cooperation with Army Aviation Systems APPLICATION OF THE MOBILITY POWER FLOW APPROACH Command, Cleveland, Ohio TO STRUCTURAL RESPONSE FROM DISTRIBUTED LOADING (NASA-TM-101431; E-4531; NAS 1.15:101431; Progress Report AVSCOM-TR-87-C-38) Avail: NTlS HC AO3IMF A01 CSCL J. M. CUSCHlERl Dec. 1988 19 p 01c (Contract NAG1-685) Experimental tests were performed on the NASAIBell Helicopter (NASA-CR-181342 NAS 1.26:181342) Avail: NTlS HC AO3/MF Textron (BHT) 500 hp advanced technology transmission (Am at A01 CSCL20K the NASA Lewis Research Center. The ATT was a retrofit of the The problem of the vibration power flow through coupled OH-58C helicopter 236 kW (317 hp) main rotor transmission, substructures when one of the substructures is subjected to a upgraded to 373 kW (500 hp), with a design goal of retaining distributed load is addressed. In all the work performed thus far, long life with a minimum increase in cost, weight, and size. Vibration, point force excitation was considered. However, in the case of strain, efficiency, deflection, and temperature experiments were the excitation of an aircraft fuselage, distributed loading on the performed and the results were compared to previous experiments whole surface of a panel can be as important as the excitation on the OH-58A, OH-58C, and UH-GOA transmissions. The from directly applied forces at defined locations on the structures. high-contact-ratiogears and the cantilevered-mounted, flexible ring Thus using a mobility power flow approach, expressions are gear of the ATT reduced vibration compared to that of the OH-58C. developed for the transmission of vibrational power between two The ATT flexible ring gear improved planetary load sharing coupled plate substructures in an L configuration, with one of the compared to that of the rigid ring gear of the UH-GOA transmission. surfaces of one of the plate substructures being subjected to a The ATT mechanical efficiency was lower than that of the OH-58A distributed load. The types of distributed loads that are considered transmission, probably due to the high-contact-ratio planetary are a force !oad wi!h an arbitrary function in space and a distributed gears. Author load similar to that from acoustic excitation. Author

N89-13796 Old Dominion Univ., Norfolk, VA. N89-13819"# Toledo Univ., OH. THE EFFECTS OF NONLINEAR DAMPING ON THE LARGE SOLUTION AND SENSITIVITY ANALYSIS OF A COMPLEX DEFLECTION RESPONSE OF STRUCTURES SUBJECTED TO TRANSCENDENTAL EIGENPROBLEM WITH PAIRS OF REAL RANDOM EXCITATION Ph.D. Thesis EIGENVALUES Final Report CHUNCHU BHAVANI PRASAD 1987 161 p DURBHA V. MURTHY Jan. 1989 25 p Avail: Univ. Microfilms Order No. DA8805584 (Contract NAG3-742) Effects of both nonlinear damping and large deflection stiffness (NASA-CR-182241; E-4560; NAS 1.26:182241) Avail: NTlS HC are included in the theoretical anlaysis in an attempt to explain AOIIMF A01 CSCL 20K the experimental phenomena of aircraft panels excited at high This paper considers complex transcendental eigenvalue sound pressure levels; that is the broadening of the strain response problems where one is interested in pairs of eigenvalues that are peak and the increase in modal frequency. Beams and restricted to take real values only. Such eigenvalue problems arise symmetrically laminated plates subjected to acoustic excitation are in dynamic stability analysis of nonconsewative physical systems, considered in the analyses. A polynomial containing both linear Le., flutter analysis of aeroelastic systems. Some available solution and nonlinear damping terms is considered as a damping model. methods are discussed and a new method is presented. Two The Galerkin method is used to derive modal equations. Direct computational approaches are described for analytical evaluation equivalent linearization is used to solve nonlinear damping terms of the sensitivities of these eigenvalues when they are dependent to determine mean square maximum deflection, mean square on other parameters. The algorithms presented are illustrated maximum strain, and spectral density function of maximum strain through examples. Author for the structures. For beams, simply supported and clamped, three modes are considered in the analysis. Isotropic material is N89-14372 Physics and Electronics Lab. TNO, The Hague considered for beams. For laminated plates, simply supported and (Netherlands). clamped, only single mode analysis is performed. This analytical PRECISION APPROACH RADARS TWENTHE AND VOLKEL investigation will help to broaden the basic understanding of the (NETHERLANDS). MULTIPATH PROPAGATION PROBLEMS role of nonlinear damping on random response of structures and J. C. A. VANGESSEL Mar. 1988 31 p In DUTCH; ENGLISH lead to better sonic fatigue design criteria. Dissert. Abstr. summary (Contract A78/KLU/049) N8S-13816. # National Aeronautics and Space Administration. (FEL-1988-15; TD-88-2572; ETN-89-93418) Avail: Physics and Hugh L. Dryden Flight Research Facility, Edwards, CA. Electronics Lab. TNO, P.O. Box 96864, 2509 JG 'Gravenhage, BUCKLING CHARACTERISTICS OF HYPERSONIC AIRCRAFT Oude Waalsdorperweg 63, 's-Gravenhage, Netherlands WING TUBULAR PANELS The problems caused by multipath propagation effects in the WILLIAM L. KO, JOHN L. SHIDELER (National Aeronautics and Precision Approach Radars (PAR) of Air Force bases were solved. Space Administration. Langley Research Center, Hampton, Va.), Problems such as tracking errors and lock breaks hampered the and ROGER A. FIELDS Dec. 1986 70 p air traffic control. The problems occurred when the aircraft were (NASA-TM-87756; L-16128; NAS 1.1587756) Avail: NTlS HC on the glide path from 3 miles up to touchdown, corresponding to A04/MF A01 CSCL 20K a sector of 5 deg seen by the PAR. Screens consisting of fences The buckling characteristics of Rene 41 tubular panels installed with stainless steel wires with a 2 mm mesh width were placed in as wing panels on a hypersonic wing test structure (HWTS) were certain areas of the airfield, providing a 25 dB damping for a 3 determined nondestructively through use of a force/stiffness cm wavelength. The results show that these screens solve the technique. The nondestructive buckling tests were carried out under multipath propagation problems very effectively. ESA different combined load conditions and different temperature environments. TWO panels were subsequently tested to buckling N89-14373# Institute for Perception RVO-TNO, Soesterberg failure in a universal tension compression testing machine. In spite (Netherlands). Afdeling Audiologie. of some data scattering because of large extrapolations of data SOUND AlTENUATlON AND SPEECH TRANSMISSION points resulting from termination of the test at a somewhat low QUALITY OF FIVE TYPES OF HEADSETS

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A. M. MIMPEN Sep. 1987 19 p In DUTCH; ENGLISH an approximation of the AFTI-16 (Advanced Fighter Technology summary Integration) aircraft multivariable longitudinal dynamics. Author (Contract A861M / 16 1) (IZF-1987-23; TD-87-4247; ETN-89-93448) Avail: NTlS HC N89-14386'# National Aeronautics and Space Administration. A03/MF A01 Lewis Research Center, Cleveland, OH. Five types of headset intended for use in the Fokker-27 cockpit EXPERIMENTAL RESULTS FOR A TWO-DIMENSIONAL were compared. Sound attenuation was measured as a function SUPERSONIC INLET USED AS A THRUST DEFLECTING of frequency with 10 subjects. Calculations show that the sound NOZZLE level under the headsets H10-36 and H10-86 in the cockpit does ALBERT L. JOHNS and PAUL L. BURSTADT 1984 14 p not exceed the recommended damage-risk criterion of 80 dB (A), Presented at the 19th Joint Propulsion Conference, Seattle, WA, while for the other headsets this criterion is violated. The speech 27-29 Jun. 1983; cosponsored by AIAA. SAE and ASME transmission quality of the microphones, used at a short distance Sponsored by NASA, Washington, D.C. Original contains color from the lips, is good to excellent (except for the headset H10-86). illustrations Speech intelligibility of the telephones is good to moderate. Headset (NASA-TM-83439; E-1737; NAS 1.1 583439) Avail: NTlS HC H10-36 is recommended. ESA A03/MF A01 CSCL 200 Nearly all supersonic V/STOL aircraft concepts are dependent N89-14376'# Schwartz Electro-Optics, Inc., Orlando, FL. on the thrust deflecting capability of a nozzle. In one unique OPTICAL FIBER DATA TRANSFER SYSTEM concept, referred to as the reverse flow dual fan, not only is S. H. MCMILLAN Sep. 1988 124 p there a thrust deflecting nozzle for the fan and core engine exit (Contract NAS1-18331) flow, but because of the way the propulsion system operates during (NASA-CR-181704; NAS 1.26:181704) Avail: NTlS HC AO6/MF vertical takeoff and landing, the supersonic inlet is also used as a A01 CSCLO9C thrust deflecting nozzle. This paper presents results of an This Phase 2 effort applies the results of Phase 1 to design experimental study to evaluate the performance of a supersonic and fabricate an optical slip ring system for a helicopter rotor inlet used as a thrust deflecting nozzle for this reverse flow dual blade/wind tunnel application. In this application, there are two fan concept. Results are presented in terms of nozzle thrust assemblies: one on the rotating portion of the mechanical system, coefficient and thrust vector angle for a number of inlet/nozzle one on the stationary portion. The assembly on the rotating portion configurations. Flow visualization and nozzle exit flow survey results digitizes and encodes 128 transducer signals from various parts are also shown. Author of the blade, and optically transfers data across the noncontacting coupling. Two complete identical independent channels are N89-14397# Naval Postgraduate School, Monterey, CA. provided. On the stationary side, the signals are decoded and DYNAMIC STALL COMPUTATIONS USING A ZONAL one channel is transmitted in digital form to a computer for recording NAVIER-STOKES MODEL M.S. Thesis and analysis. The second channel reconstructs the analog JACK H. CONROYD, JR. Jun. 1988 212 p transducer signals for real time observation. In the opposite (AD-A197942) Avail: NTlS HC AlO/MF A01 CSCL 01A 4 direction, eight signal channels enable control signals to be passed A zonal Navier-Stokes model, is installed and verified on the from the stationary to the rotating part of the system. Power to NASA Ames Gray X/MP-48 computer and is used to calculate the rotor mounted electronics is supplied via power slip rings. The the flow field about a NACA 0012 airfoil oscillating in pitch. Surface advantages of the optical over the traditional electro-mechanical pressure distributions and integrated lift, pitching moment, and slip ring method of data transfer across a rotating joint are long drag coefficient versus angle of attack are compared to existing life, low-maintenance, immunity to crosstalk, and wider bandwidth. experimental data for four cases and existing computational data 1 Successful completion of this effort demonstrated that this method for one case. These cases involve deep dynamic stall and fully ' is practical and reliable, and can be implemented under difficult detached flow at and below a freestream Mach number of .184. conditions of available space, power, environment, and stringent The flow field about the oscillating airfoil is investigated through ' performance and equipment life requirements. Author the study of pressure, vorticity, local velocity and stream function. 1 Finally, the effects of pitch rate on dynamic stall are investigated. 1 GRA N89-14377*# Massachusetts Inst. of Tech., Cambridge. Lab. for Information and Decision Systems. DESIGN OF FEEDBACK CONTROL SYSTEMS FOR UNSTABLE N89-14456'# California State Univ. at Long Beach. PLANTS WITH SATURATING ACTUATORS TEMPERATURE EFFECT ON STRESS CONCENTRATION , PETROS KAPASOURIS, MICHAEL ATHANS, and GUNTER AROUND CIRCULAR HOLE IN A COMPOSITE MATERIAL STEIN 17 Nov. 1988 30 p Proposed for presentation at the SPECIMEN REPRESENTATIVE OF X-29A FORWARPSWEPT Symposium on Nonlinear Control Systems Design, 1989; sponsored WING AIRCRAFT by IFAC Sponsored in part by General Electric Corp. Research HSIEN-YANG YEH Aug. 1988 44 p and Development Center (Contract NGT-05-020-412) (Contract NAG2-297) (NASA-CR-179439; H-1514; NAS 1.26379439) Avail: NTlS HC (NASA-CR-183392; NAS 1.26:183392) Avail: NTlS HC A03/MF AO3/MF A01 CSCL 20K A01 CSCLO9C The theory of anisotropic elasticity was used to evaluate the A new control design methodology is introduced for anisotropic stress concentration factors of a composite laminated multi-input/multi-output systems with unstable open loop plants plate containing a small circular hole. This advanced composite and saturating actuators. A control system is designed using well was used to manufacture the X-29A forward-swept wing. It was known linear control theory techniques and then a reference found for composite material, that the anisotropic stress prefilter is introduced so that when the references are sufficiently concentration is no longer a constant, and that the locations of small, the control system operates linearly as designated. For maximum tangential stress points could shift by changing the fiber signals large enough to cause saturations, the control law is orientation with respect to the loading axis. The analysis showed modified in such a way to ensure stability and to preserve, to the that through the lamination process, the stress concentration factor extent possible, the behavior of the linear control design. Key could be reduced drastically, and therefore the structural benefits of this methodology are: the modified feedback system performance could be improved. Both the mixture rule approach never produces saturating control signals, integrators and/or slow and the constant strain approach were used to calculate the stress dynamics in the compensator never windup, the directional concentration factor of room temperature. The results predicted properties of the controls are maintained, and the closed loop by the mixture rule approach were about twenty percent deviate system has certain guaranteed stability properties. The advantages from the experimental data. However, the results predicted by the of the new design methodology are illustrated in the simulation of constant strain approach matched the testing data very well. This

194 13 GEOSCIENCES showed the importance of the inplane shear effect on the evaluation fiber unidirectional ceramic matrix composites under monotonic of the stress concentration factor for the X-29A composite plate. loads are surveyed. Author Author N89-14918'# Mississippi State Univ.. Mississippi State. Dept. N89-14465'# National Aeronautics and Space Administration. of Mathematics and Statistics. Lewis Research Center, Cleveland, OH. OVERLAPPING GRIDS FOR FLOW FIELD CALCULATIONS Abstract Only PARAMETRIC STUDIES OF ADVANCED TURBOPROPS J. G. MASER, D. G. FERTIS (Akron Univ., OH.), C. C. CHAMIS, CHARLES WAYNE MASTIN ln Hampton Inst., NASA/American Society for Engineering Education (ASEE) Summer Faculty and R. A. AIELLO 1988 16 p Presented at the 29th Structures, Fellowship program 1988 p 84-85 Structural Dynamics and Materials Conference, Williamsburg, VA, Sep. 1988 Avail: NTlS HC A07/MF A01 CSCL 20D 18-20 Apr. 1988; sponsored by AIAA, ASME, ASCE, AHS and Many problems in computational fluid dynamics (CFD) involve ACS the calculation of flow fields within or around complex geometric (NASA-TM-101389; E-4451; NAS 1.1 5101389) Avail: NTlS HC configurations. The flow solution is computed on a computational AO3/MF A01 CSCL 20K The effects of geometric variables (sweep and twist) on the grid. The construction of the grid is one of the major difficulties in the application of CFD to the analysis of flow about actual aircraft structural performance of advanced turboprops are investigated. configurations. Due to geometric complexity, the grid has to be The investigation is limited to aerodynamically efficient turboprops constructed in simple subregions and then all of these subgrids using an acceptable design configuration as a baseline. The have to be pieced together to form a complete grid for the entire baseline configuration is modified using a seven by seven array flow field. The entire grid, which is called a composite grid because of independently varying sweep and twist parameters while it is formed from many parts, may have common regions. In either maintaining acceptable aerodynamic efficiency. The turboprop case, the computation of the flow field, using any numerical structural performance is evaluated in terms of critical speeds, tip algorithm, will require the transfer of information between individual displacements, and vibration frequencies where geometric subgrids. The transfer of information is more difficult with nonlinearities are included. The results obtained are presented in overlapping grids. Algorithms have been developed and tested for such a manner as to highlight the effects of sweep and twist on automating the transfer of information between two overlapping the structural performance of aerodynamically efficient turboprop configurations. Author grids. Author N89-14924'# Arkansas State Univ., State University. Dept. of N89-14466# Foster-Miller Associates, Inc., Waltham, MA. Computer Science. AUTOMATED FATIGUE CRACK GROWTH MEASUREMENT A FLIGHT TEST DESIGN FOR STUDYING AIRBORNE Final Report, 28 Jul. 1987 - 28 Jan. 1988 APPLICATIONS OF AIR TO GROUND DUPLEX DATA LINK TED E. KIRCHNER and JOHN MCCOY Jul. 1988 69 p COMMUNICATIONS Abstract Only (Contract F33615-87-C-3240) CHARLES H. SCANLON ln Hampton Inst., NASA/American (AD-A198642; AFW-8767; ARNAL-TR-88-3032) Avail: NTlS HC Society for Engineering Education (ASEE) Summer Faculty A04/MF A01 CSCL 21E Fellowship Program 1988 p 94-96 Sep. 1988 Fatigue testing is a key element in the development of aircraft Avail: NTlS HC A07/MF A01 CSCL 178 and engines. The higher performance temperatures of both airframe The Automatic En Route Air Traffic Control (AERA) and the and engines of future aircraft makes precise high temperature Advanced Automated System (AAS) of the NAS plan, call for fatigue testing vital. The goal of this program is to develop a new utilization of data links for such items as computer generated tool that will automate this test and provide fatigue crack flight clearances, enroute minimum safe altitude warnings, sector measurement to a precision of 0.001 in. at varying temperatures probes, out of conformance check, automated flight services, and up to 2000 F and likely higher. In the Phase I program reported flow management of advisories. A major technical challenge here we have experimentally shown the feasibility of two different remaining is the integration, flight testing, and validation of data approaches using laser and X-ray technology. We have link equipment and procedures in the aircraft cockpit. The flight recommended that the laser approach be selected for hardware test organizational chart, was designed to have the airplane side development. GRA of data link experiments implemented in the NASA Langley Research Center (LaRC) experimental Boeing 737 airplane. This N89-14470'# National Aeronautics and Space Administration. design would enable investigations into implementation of data Lewis Research Center, Cleveland, OH. link equipment and pilot interface, operations, and procedures. A REVIEW OF FAILURE MODELS FOR UNIDIRECTIONAL The illustrated ground system consists of a work station with links CERAMIC MATRIX COMPOSITES UNDER MONOTONIC to a national weather database and a data link transceiver system. LOADS The data link transceiver system could be a Mode4 transponder, DAVID E. TRIPP, JOHN H. HEMANN (Cleveland State Univ., OH.), ACARS, AVSAT, or another type of radio system such as the and JOHN P. GYEKENYESI 1989 19 p Proposed for military type HF data link. The airborne system was designed so presentation at the 34th International Gas Turbine and Aeroengine that a data link transceiver, workstation, and touch panel could Congress and Exposition, Toronto, Ontario, 4-8 Jun. 1989; be interfaced with an input output processor to the aircraft system sponsored by the American Society of Mechanical Engineers bus and thus have communications access to other digital airplane (NASA-TM-101421; E-4520; NAS 1.15:101421) Avail: NTlS HC systems. Author A03/MF A01 CSCL 20K Ceramic matrix composites offer significant potential for improving the performance of turbine engines. In order to achieve 13 their potential, however, improvements in design methodology are needed. In the past most components using structural ceramic matrix composites were designed by trial and error since the GEOSCIENCES emphasis of feasibility demonstration minimized the development of mathematical models. To understand the key parameters Includes geosciences (general); earth resources; energy production controlling response and the mechanics of failure, the development and conversion; environment pollution; geophysics; meteorology of structural failure models is required. A review of short term and climatology; and oceanography. failure models with potential for ceramic matrix composite laminates under monotonic loads is presented. Phenomenological, semi-empirical, shear-lag, fracture mechanics, damage mechanics, A89-18259 and statistical models for the fast fracture analysis of continuous THREE DIMENSIONAL HAZARD ZONES

195 13 GEOSCIENCES

DAVID P. SAUTER (U.S. Army, Atmospheric Sciences Laboratory, N8913833# California Univ., Riverside. Statewide Air Pollution White Sands Missile Range, NM) IN: Symposium on Turbulence Research Center. and Diffusion, 8th, San Diego, CA, Apr. 25-29, 1988, Preprints. ATMOSPHERIC PHOTOCHEMICAL MODELING OF TURBINE Boston, MA, American Meteorological Society, 1988, p. 260-262. ENGINE FUELS AND EXHAUSTS. COMPUTER MODEL refs DEVELOPMENT, VOLUME 2 Flnal Report, OCt. 1984 - Dec. The US. Army’s Atmospheric Sciences Laboratory has 1986 developed a three-dimensional hazard model, ’BDHZD’, which can WILLIAM 0. CARTER, ARTHUR M. WINER, ROGER ATKINSON, predict the horizontal and vertical extent of the vapor hazard due SUSAN E. HEFFRON, and MlNN P. POE May 1988 210 p to toxic chemical vapors released by chemical spills from storage (Contract FO8635-C-80-0359) facilities or vehicles. Hazard volumes can be predicted in near-real (AD-A198691 ; AFESC/ESL-TR-87-35-VOL-2) Avail: NTlS HC time on a microcomputer, given the chemical and meteorological AlO/MF A01 CSCL 04A parameters. It can in this way be shown that, for an accidental This User’s Manual documents how to use an atmospheric spill of acrolein, a significant hazard will exist for low-flying photochemical reactivity modeling software system which has been helicopters. O.C. developed for the US. Air Force under this contract. The modeling software can be used to conduct floating box type airshed model simulations to determine the air quality impacts of many types of A8918554 reactive organic gases (ROG) emitted under a variety of air pollution AN AUTOMATED METHOD FOR FORECASTING THE scenarios. GRA PROBABILITY OF CLEAR AIR TURBULENCE [AVTOMATIZIROVANNYI SPOSOB PROGNOZA VEROIATNOSTI TURBULENTNOSTI V IASNOM NEBEI N89-13839 Brunei Univ., Uxbridge (England). T. V. LES H K E V IC H (G idro me t eo ro Iog ic he s kii Na uc h n o - THE QUALITY OF FIBRE REINFORCED THERMOPLASTICS Issledovatel’skii Tsentr SSSR, Moscow, USSR) Meteorologiia MOULDINGS Ph.D. Thesls i Gidrologiia (ISSN 0130-2906), Oct. 1988, p. 44-54. HUGH ADRIAN POTTS 1987 362 p In Russian. refs Avail: Univ. Microfilms Order No. BRDX81180 A physical-statistical relationship between clear air turbulence The requirement for injection molded short carbon fiber and local characteristics of the meteorological fields under various reinforced thermoplastics in helicopter applications is based on synoptic conditions in the 850-500 hPa layer. The synoptic component coat and weight savings. The presence of short fibers conditions for the existence or abscence of intense clear air in a thermoplastic polymer can exert a significant influence upon turbulence are identified. An objective synoptic statistical method the rheological properties of the melt. As it is the rheology of the for forecasting zones of intense turbulence and a program for material which determines melt flow performance and hence the calculating the probability of clear air turbulence at the 850, 700, flow-induced fiber orientation in the final molded part, accurate and 500 hPa levels are presented. R.B. data are required to understand and predict polymer flow. Although standard procedures exist for determining the rheological characteristics of melts, their relevance to the injection modling A89-20265’ Mesoscale Environmental Simulations, Inc., Hampton, proscess was questioned. Consequently, a high shear rate VA. rheometer was developed, and the results for the filled and unfilled NUMERICAL SIMULATIONS OF AN ISOLATED MICROBURST. melts compared with the standard equipment. Significant effects I - DYNAMICS AND STRUCTURE involving thermal conductivity and fiber breaking were identified FRED H. PROCTOR (MESO, Inc., Hampton. VA) Journal of the which leads to errors in the data produced using the standard Atmospheric Sciences (ISSN 0022-4928), vol. 45, Nov. 1, 1988, device. Two techniques using reflected light and thermal imaging p. 3137-3160. refs were successfully developed for the characterization of the (Contract NASl-17409; NAS1-18336) orientation of short carbon fibers in injection molded parts. Welds Isolated and stationary microbursts are simulated using a are a common feature in injection molded parts. This study also time-dependent, high-resolution, axisymmetric numerical model. A addresses the problem of the knit weld in a specially designed microburst downdraft is initiated by specifying a distribution of test specimen. Applying fracture mechanics principles, the integrity precipitation at the top boundary of the model and allowing it to of the welded structure was analyzed, and the results correlated fall into the domain. Two case studies of a hazardous wet (high with microstructural observations. Finally, impact studied using reflectivity) microburst are presented. The initial and boundary subcomponent geometries have addressed the effects of flow specifications, evolution, microphysics, ring vortex, burst front, induced fiber orientation in specific geometrical features. vorticity, and structure of the microbursts are discussed. R.B. Dissert. Abstr.

N8913832# California Univ., Riverside. Statewide Air Pollution N89-13854# Air Force Inst. of Tech., Wright-Patterson AFB, Research Center. OH. ATMOSPHERIC PHOTOCHEMICAL MODELING OF TURBINE ANALYSIS OF TEMPERATURE AND VELOCITY ENGINE FUELS AND EXHAUSTS. COMPUTER MODEL MICROTURBULENCE PARAMETERS FROM AIRCRAFT DATA DEVELOPMENT, VOLUME 1 Final Report, Oct. 1984 - Dec. AND RELATIONSHIP TO ATMOSPHERIC REFRACTIVE INDEX 1986 STRUCTURE M.S. Thesis WILLIAM 0. CARTER, ARTHUR M. WINER, ROGER ATKINSON, ELIZABETH A. BEECHER May 1988 180 p SUSAN E. HEFFRON, and MlNN P. POE May 1988 260 p (AD-AI96542; AFIT/CI/NR-88-20) Avail: NTlS HC AO9/MF A01 (Contract FO8635-C-80-0359) CSCL 048 (AD-A198690; AFESC/ESL-TR-87-35-VOL-l) Avail: NTlS HC Due to inherent turbulence, the atmosphere has a temporally A12/MF A01 CSCL 04A and spatially variable refractive index, which degrades propagating A computer model capable of predicting photochemical electromagnetic radiation. (C sub n)sq is a key parameter for reactivity of turbine engine fuel emissions and exhaust emissions describing refractive variations. Data was analyzed from several from routine AF operations is developed. This Phase 2 report instruments involved in an electro-optics/rneteorology experiment; describes experimental work on engine exhaust components scintillometer; thermosonde; radar vertical profiler, and conducted in environmental chamber facilities. The results indicate instrumented aircraft. The aircraft measured (C sub T) sq and (C that engine exhaust is significantly more reactive than the fuels sub u) sq using hot and cold wire sensors and FM recording themselves. The reaction mechanism incorporates new methods apparatus. The taped data was processed via FFT to produce for lumping of complex reactive organic gas (ROG) mixtures when one-dimensional variance spectra (wavenumber range 0.01 to representing them in model simulations. This technical report is 10/m). Flights usually produced a 10 km vertical profile processed divided into two volumes. Volume 1 explains the computer model to give roughly 0.5 km resolution. Spectral editing was based on development, while Volume 2 is the User’s Manual. GRA regression analysis fit to -513 frequency dependence. A majority

196 15 MATHEMATICAL AND COMPUTER SCIENCES of spectra showed the classic inertial subrange. (C sub n) sq and in detail, and numerical results for problems involving aircraft epsilon were calculated from (C sub T) sq and (C sub u) sq, longitudinal and lateral motion are presented in graphs. The new respectively. In active regions, the following relationship can be criteria are shown to be significantly more effective than derived. (C sub T) sq((C sub u) sq. = 1.6 R sub i)(P sub r - R conservative criteria in evaluating robust stability. T.K. sub i) (thetalg) (delta thetaldelta z). GRA A89-17965' Systems Control Technology, Inc., Palo Alto, CA. N89-14616# Federal Aviation Administration, Washington, DC. EFFECT OF MODEL UNCERTAINTY ON FAILURE DETECTION Office of Environment and Energy. - THE THRESHOLD SELECTOR A MICROCOMPUTER POLLUTION MODEL FOR CIVILIAN ABBAS EMAMI-NAEINI, MUHAMMAD M. AKHTER, and STEPHEN AIRPORTS AND AIR FORCE BASES, MODEL DESCRIPTION M. ROCK (Systems Control Technology, Inc., Palo Alto, CA) IEEE H. M. SEGAL and P. L. HAMILTON (Minority Services, Inc., Transactions on Automatic Control (ISSN 0018-9286), vol. 33, Dec. Washington, DC.) Aug. 1988 140 p 1988, p. 1106-111 5. refs (ADA199003; FAA-EE-88-4; AFESC/ESL-TR-88-53) Avail: NTIS (Contract NAS3-24079) HC A07/MF A01 CSCL 24A The performance of all failure detection, isolation, and This is one of three reports describing the Emissions and accomodation (DIA) algorithms is influenced by the presence of Dispersion Modeling System (EDMS). EDMS is a complex source model uncertainty. A unique framework is presented to incorporate emissions/dispersion model for use at civilian airports and Air a knowledge of modeling error in the analysis and design of failure Force bases. It operates in both a refined and a screening mode detection systems. The tools being used are very similar to those and is programmed for an IBM-XT (or compatible) computer. This in robust control theory. A concept is introduced called the report--MODEL DESCRIPTION-provides the technical description threshold selector, which is a nonlinear inequality whose solution of the model. It first identifies the key design features of both the defines the set of detectable sensor failure signals. The threshold emissions (EMISSMOD) and dispersion (GIMM) portions of EDMS. selector represents an innovative tool for analysis and synthesis It then describes the type of meteorological information the of DIA algorithms. It identifies the optimal threshold to be used in dispersion model can accept and identifies the manner in which it innovations-based DIA algorithms. The optimal threshold is shown preprocesses National Climatic Center (NCC) data prior to a refined to be a function of the bound on modeling errors, the noise model run. The report presents the results of running EDMS on a properties, the speed of DIA filters, and the classes of reference number of different microcomputers and compares EDMS results and failure signals. The size of the smallest detectable failure is with those of comparable models. The appendices elaborate on also determined. The results are applied to a multivariable turbofan the information noted above and list the source code. GRA jet engine example, which demonstrates improvements compared to previous studies. LE. N8914899'# State Univ. of New York, Brockport. Dept. of the Earth Sciences. USE OF THE TERMINAL AREA SIMULATION SYSTEM (TASS) A89-18009 TO STUDY MICROBURST WIND SHEARS UNIVERSAL ADA TEST LANGUAGE (UATL) TO SUPPORT GREGORY P. BYRD ln Hampton Inst., NASA/American Society REAL-TIME SOFTWARE/SYSTEM INTEGRATION AND for Engineering Education (ASEE) Summer Faculty Fellowship FACTORY/MAINTENANCE FAULT ISOLATION Program 1988 p 44-45 Sep. 1988 JEHUDA ZIEGLER, JERRY M. GRASSO, LINDA BURGER- Avail: NTlS HC A07/MF A01 CSCL 048 MEISTER, and BART VOYCE (ITT, ITT Avionics Div., Ground-based and airborne Doppler radar and LIDAR systems Nutley, NJ) IN: AUTOTESTCON '88; Proceedings of the IEEE are being designed to alert pilots when a hazardous windshear is International Automatic Testing Conference, Minneapolis, MN, Oct. present. A key element in this design effort is understanding the 4-6, 1988. New York, Institute of Electrical and Electronics microburst itself. This is accomplished by means of the TASS Engineers, Inc.. 1988, p. 85-92. refs model which was developed for NASA by Proctor (1987a,b). The (Contract N60921-87-C-0285) time-dependent TASS model has two vesions: a two-demensional The universal Ada test language (UATL), developed to high resolution axisymmetric model, and a three-demensional encourage, and provide support to, the use of Ada in eventually model. The model includes a sophisticated parameterization of replacing ATLAS, BASIC, and other special-purpose test control cloud microphysics and a friction layer, both of which are essential languages for generating automatic test programs, is presented. to a realistic simulation of the microburst phenomenon. The TASS The UATL consists of a set of modular, portable, Ada packages model has been successfully tested on well-observed convective that define a higher-leveltest language that supports the generation events. Author of test programs in Ada. These packages provide the user with a complete complement of standardized reusable test functions that shorten the test-program-generation effort. These test functions include interactive test operator controls, real-time test data 15 stimulus/response, data recording, and data reduction. The UATL also allows the sophisticated user to develop any unique test MATHEMATICAL AND COMPUTER SCIENCES functions at the Ada code level. I.E.

Includes mathematical and computer sciences (general); computer A8948015 operations and hardware; computer programming and software; ATE HARDWARE DIAGNOSTICS, FAULT DETECTION, AND computer systems; cybernetics; numerical analysis; statistics and FAULT ISOLATION TOOL (SELF-TEST ADAPTER) probability; systems analysis; and theoretical mathematics. RICHARD 1. LAMBRECHT (Honeywell, Inc., Defense Avionics Systems Div., Albuquerque, NM) IN: AUTOTESTCON '88; Proceedings of the IEEE International Automatic Testing A8917489 Conference, Minneapolis, MN, Oct. 4-6, 1988. New York, Institute REDUCED CONSERVATIVE SINGULAR VALUE ANALYSIS of Electrical and Electronics Engineers, Inc., 1988, p. 125-128. FOR ROBUSTNESS The question of multiple levels of self-test for automatic test TSUYOSHI OKADA, MASAHIKO KIHARA, and YASUNORI NlSHlO equipment (ATE) is examined, and a three-level self-test concept (Defense Academy, Yokosuka, Japan) International Journal of is proposed. Level one will verify test resource communication Control (ISSN 0020-7179), vol. 48, Oct. 1988, p. 1455-1473. and built-in test (BIT), level two will check all of the switching refs resources, and level three will test the measurement and output Criteria for the robust stability and sensitivity reduction of MlMO stimulus resources. All three levels are distinct in their functions systems are developed analytically in the framework of the but each is dependent on the successful completion of the functions frequency-domain singular-value method. The derivation is given tested at the previous level. Depending on the problems

197 15 MATHEMATICAL AND COMPUTER SCIENCES encountered, only one or two levels of self-test will need to be CA, Oct. 17-20,1988, Technical Papers. Part 1. Washington, DC, run. I.E. American Institute of Aeronautics and Astronautics, 1988, p. 80-87. refs A8918030 (AIAA PAPER 88-3865) AN OVERVIEW OF SEDACS - A STATE OF THE ART This paper describes a high productivity Computer Aided TRD/TPS ENVIRONMENT Software Engineering (CASE) environment that assists with the MARK R. HANSCH (Honeywell, Inc., Military Avionics Div., Golden early phase of the software development life cycle. The method Valley, MN) IN: AUTOTESTCON '88;Proceedings of the IEEE and tools are geared specifically for real-time embedded software, International Automatic Testing Conference, Minneapolis, MN, Oct. which is prevalent in digital avionics systems. They are based on 4-6, 1988. New York, Institute of Electrical and Electronics significant extensions to the Real-Time Structured Analysis Engineers, Inc., 1988, p. 253-255. methods. With the extended method, the specifications are fully The support equipment data acquisition and control system executable, yet retain the benefits of the structured methods. A (SEDACS) was developed to allow a prime contractor to control set of tools from the environment allows the specification to be the development of test requirement documents (TRD) and automatically analyzed and simulated to rapidly build a behavioral associated ATLAS programs for the suite of avionics residing on prototype. The simulation can be used for overall system validation an aircraft. The system allows multiple avionics manufacturers to and demonstration, evaluation of design trade-offs, predicting timing supply data for the test program set (TPS) to SEDACS directly performance, and detection of constraint violations. A highly from facilities located in various sites in the nation. It utilizes a interactive, graphical user interface makes the environment easy menu-driven interface, forms data entry, relational data storage, to use even by less experienced users. A library of reusable proprietary data protection, a sophisticated full-screen editor for executable models customized for embedded software systems test program development, and electronic transfer of source and facilitates the rapid construction of the specifications. Author object to the automatic test equipment (ATE) for execution. SEDACS integrates all these functions for complete configuration A89- 18064# control and management by the prime contractor. A further A STRUCTURED APPROACH TO SYSTEM DESIGN overview of SEDACS is given. LE. C. INGVAR SVENSSON (Boeing Commercial Airplanes, Seattle, WA) IN: AIAAIIEEE Digital Avionics Systems Conference, 8th, A89-18034 San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 1. HYBRID ARCHITECTURE OF FIELD-TESTED DIAGNOSTIC Washington, DC, American Institute of Aeronautics and EXPERTSYSTEM Astronautics, 1988, p. 95-103. ARTHUR F. GRIFFIN and JOHN A. MAGUIRE (Hughes Aircraft (AIAA PAPER 88-3867) Co., Long Beach, CA) IN: AUTOTESTCON '88;Proceedings of Current approaches to systems design frequently result in large, the IEEE International Automatic Testing Conference, Minneapolis, incremental costs during system integration testing and service MN, Oct. 4-6,1988. New York, Institute of Electrical and Electronics introduction to remove design errors that were introduced during Engineers, Inc., 1988, p. 281-286. refs the requirements and design phases of the life-cycle. This study Three approaches to diagnostic expert systems have emerged was conducted to assess the possibility of reducing system over the last decade: rule-based, dependency models, and development cost by elimination or early detection of design errors deep-knowledge models. A fourth approach is a hybrid architecture through the use of a systematic design approach. The study that combines two or more of the three pure forms so that the indicates that such possibilities do exist and should be exploited. strengths of one support the weaknesses of the other and vice Author versa. The advantages and disadvantages of each of these I approaches are examined. Al-Ferret, a system that was field-tested A8918065# by US Army technicians troubleshooting operational equipment, AVIONICS FAILURE PROPAGATION ANALYSIS TOOL and which implements a rule-dependency hybrid architecture, is YOSHlKl NAKAMURA, ABHlJlT CHAKRAVARTY, and IRVING R. described. The beliefs that: (1)the hybrid architecture will become REESE (Boeing Commercial Airplanes, Seattle, WA) IN: the dominant approach to practical diagnostic expert systems, and AIAA/IEEE Digital Avionics Systems Conference, 8th, San Jose, (2) cost and performance benefits of hybrids will be determined CA, Oct. 17-20,1988, Technical Papers. Part 1. Washington, DC, by the level of interaction between rule and model parts are also American Institute of Aeronautics and Astronautics, 1988, p. analyzed. LE. 104-109. (AIAA PAPER 88-3868) A89-18056# The Avionics Failure Propagation Analysis Tool (AFPAT) is a THE ROLE OF TESTABILITY IN THE INTEGRATED computer program designed and built to provide failure propagation DIAGNOSTIC PROCESS visibility for a network of avionics subsystems. It is programmed WILLIAM L. KEINER (U.S. Navy, Naval Surface Warfare Center; in the Artificial Intelligence (AI) language PROLOG and is hosted Dahlgren, VA) IN: AIAAAEEE Digital Avionics Systems on both PC-compatible and Apollo workstations. This analysis tool Conference, 8th, San Jose, CA, Oct. 17-20,1988, Technical Papers. helps identify potential design integration problems among the Part 1. Washington, DC, American Institute of Aeronautics and avionics line replaceable units (LRUs) during the equipment design Astronautics, 1988, p. 32-39. refs and testing phases. It can also assist avionics/flight systems design (AIAA PAPER 88-3858) engineers in the preparation of system failure analyses for airplane This paper examines present and future roles for testability certification support. Author within the avionics integrated diagnostics process, emphasizing the use of computer-aided testability tools during the avionics A8918083'# Research Triangle Inst., Research Triangle Park, system's design phase. The evolution of diagnostics is reviewed, NC. and the definition of integrated diagnostics is discussed. The A SIMULATION-BASED FAULT INJECTION EXPERIMENT TO concept of embedded diagnostics is summarized, and the evolution EVALUATE SELF-TEST DIAGNOSTICS FOR A and definition of testability are examined. A framework for integrated FAULT-TOLERANT COMPUTER diagnostics process is presented, and diagnostics measures and ROBERT L. BAKER, L. SCOTT MANGUM, and CHARLOTTE 0. authoring are considered. C.D. SCHEPER (Research Triangle Institute, Research Triangle Park, NC) IN: AIAAAEEE Digital Avionics Systems Conference, 8th, A8918062# San Jose, CA, Oct. 17-20,1988, Technical Papers. Part 1. SDAR - A HIGH PRODUCTIVITY SOFTWARE ENGINEERING Washington, DC, American Institute of Aeronautics and ENVIRONMENT FOR EMBEDDED SYSTEMS Astronautics, 1988, p. 220-226. refs DONALD CHIN (Athena Systems, Inc., Sunnyvale, CA) IN: (Contract NASl-17964) AIAAIIEEE Digital Avionics Systems Conference, 8th, San Jose, (AIAA PAPER 88-3897)

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The design and results of a fault injection experiment conducted modules. An overview of the multiprocessing system architecture in the Airlab facility at NASA-Langley using a logic network simulator is presented as well as a discussion of the requirements and are described. An attempt was made to determine the effectiveness support for the distributed Ada programming system. K.K. of the diagnostic self-test sequences used to detect failures in the communicatorhterstage (C/I) of a fault-tolerant processor A8%18111# (RP). Identification of the undetected faults in the C/I Status ON THE EFFECTIVENESS OF MULTIVERSION SOFTWARE IN Register logic resulted in changes in the diagnostic test sequences DIGITAL AVIONICS implemented for the FTP. K.K. ALGIRDAS AVlZlENlS and MICHAEL R. LYU (California, University, Los Angeles) IN: AIAAAEEE Digital Avionics Systems Conference, A8918086'# Duke Univ., Durham, NC. 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 1. AN APPROACH TO SOLVING LARGE RELIABILITY MODELS Washington, DC, American Institute of Aeronautics and MARK A. BOYD, MALATHI VEERARAGHAVAN, JOANNE BECHTA Astronautics, 1988, p. 422-427. refs DUGAN, and KISHOR S. TRlVEDl (Duke University, Durham, NC) (AIAA PAPER 88-3903) IN: AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, Ways of attaining effective tolerance of design faults by means CA, Oct. 17-20, 1988, Technical Papers. Part 1. Washington, DC, of multiversion software are discussed. Two recent investigations American Institute of Aeronautics and Astronautics, 1988, p. (U. of VirginiaN. of California at Irvine, and UCLA/Honeywell) 243-250. Research supported by the Research Triangle Institute. that have produced differing results are compared. A design refs paradigm for multiversion software is presented. K.K. (Contract NAG1-70; AF-AFOSR-84-0132) (AIAA PAPER 88-3905) A89-18115# This paper describes a unified approach to the problem of USE OF THE GALA AND PALAS TOOLS TO ENHANCE THE solving large realistic reliability models. The methodology integrates DEVELOPMENT OF AVIONIC SOFTWARE behavioral decomposition, state trunction, and efficient sparse P. CORON (SFENA, Velizy-Villacoublay, France) IN: AIAAAEEE matrix-based numerical methods. The use of fault trees, together Digital Avionics Systems Conference, 8th, San Jose, CA, Oct. with ancillary information regarding dependencies to automatically 17-20, 1988, Technical Papers. Part 2. Washington, DC, American generate the underlying Markov model state space is proposed. Institute of Aeronautics and Astronautics, 1988. p. 445-457. The effectiveness of this approach is illustrated by modeling a (AIAA PAPER 88-3943) state-of-the-art flight control system and a multiprocessor system. Two software tools for assuring avionics software safety and Nonexponential distributions for times to failure of components quality are presented. One is a configuration and modification are assumed in the latter example. The modeling tool used for management tool called Palas and a tool for automatic code most of this analysis is HARP (the Hybrid Automated Reliability Predictor). Author generation called Gala. The Gala advantages, graphic language, real-time aspects, organization are examined. The Palas functions are reviewed and the use of Palas in workshops is reported on. A8918087# C.D. ADA IN AVIONICS - BEYOND VALIDATION W. B. KEEN (Plessey Avionics, Ltd., Havant, England) IN: AIAAAEEE Digital Avionics Systems Conference, Eth, San Jose, A89-18137# CA, Oct. 17-20, 1988. Technical Papers. Part 1. Washington, DC, AN AUTOMATED METHODOLOGY FOR PARTITIONING American Institute of Aeronautics and Astronautics, 1988, p. SOFTWARE FUNCTIONS IN A DISTRIBUTED AVIONICS 251-255. ARCHITECTURE (AIAA PAPER 88-3907) M. ABDI-MORADI (TRW, Inc.. TRW Defense System Group, The validation of Ada compilers is necessary but not sufficient, Houston, TX) IN: AIAAIIEEE Digital Avionics Systems Conference, particularly for constrained, real-time, embedded systems. It has Eth, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. distorted compiler development away from real world support Washington, DC, American Institute of Aeronautics and features and so has delayed Ada's wide scale application. The Astronautics, 1988, p. 585-592. evaluation criteria required for avionic applications must firstly (AIAA PAPER 88-3971) consider technical feasibility in terms of configurabiity of the Ada Designing a modern avionics system includes the partitioning run-time system and the impact on hardware design; and secondly, of software functions into a fintie set of subsystems. This paper the cost and performance implications. Plessey Avionics has describes an automated approach to partitioning based on a applied Ada to a range of avionic systems and have observed pre-established set of objectives and constraints. A program called the rapid maturation of Ada compilers. Armed with the appropriate 'Bus' partitions the functions into subsystems, with the objective evaluation criteria, the adoption of Ada for avionic applications is of minimizing data flow between subsystems and meeting a seen to provide significant benefits over previous languages. constraint on the availability of computer resources. Another Consequently, Plessey Avionics has adopted Ada for several program called 'Subsys' will generate a set of subsystems with projects even though Ada was not a specific customer the objectives of: (1) creating stand-alone functional entities, (2) requirement. Author maintaining simple interfaces between the subsystems, and (3) minimizing bus traffic between processors. A program called 'Type' A89-18088# creates subsystems based on grouping of functions which have A FAiiii TOLEEANT BG'iONiCS WJLiiPROCESSiiiG SYSTEM common identification (ID) numbers. The ID numbers assigned by ARCHITECTURE SUPPORTING CONCURRENT EXECUTION the designer, represent function characteristics such as: criticality, OF AD ATASKS type of data handled, the function execution rate, or some other DAVID W. BEST, KEVIN L. MCGAHEE, and ROGER K. SHULTZ factor related to an objective which should influence the functional (Rockwell International Corp., Collins Government Avionics Div., partitioning. By using the automated approach, the author Cedar Rapids, IA) IN: AIAAIIEEE Digital Avionics Systems concludes that the partitioning task can be performed faster, but Conference, Eth, San Jose, CA, Oct. 17-20, 1988, Technical Papers. more importantly, the process ensures traceability between Part 1. Washington, DC, American Institute of Aeronautics and subsystems and functions and produces a clear audit trail for future reassessment or modification of the design. Author Astronautics, 1988, p. 256-262. refs (AIAA PAPER 88-3908) A distributed multiprocessing computer architecture which fulfills A89181 41 # the requirements of fully integrated avionics systems is described. A PARALLEL MODULAR SIGNAL PROCESSOR The PRISM (prototype, reconfigurable, integrated system for MARK COLESTOCK (Control Data Corp., Minneapolis, MN) IN: multiprocessing) architecture is designed to provide a fault tolerant AIAAAEEE Digital Avionics Systems Conference, 8th, San Jose, and damage tolerant network of processor, memory, and I10 CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC,

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American Institute of Aeronautics and Astronautics, 1988, p. A robust Ada-based executive for distributed avionics 607-613. refs applications is being implemented within the Air-to-Air Attack (AIAA PAPER 88-3981) Management Program. Algorithms and controlldisplay concepts The parallel modular signal processor (PMSP) is a high-speed for cooperative, multiple target attack in beyond visual range air airborne programmable VLSl signal processor capable of a peak combat are being developed. A discussion of the current status FET processing rate of 625 million operations per second. Special of the executive function is presented along with a look at future software tools are also needed to match this new-generation signal plans for development of a comprehensive Ada executive for processor. The PMSP's software tools and modular architecture generalized distributed avionics applications. Author are designed to meet the requirements of today and into the 1990s. Author A89181 78# AI APPLICATIONS TO TACTICAL DECISION AIDS A89-18160# C. R. OVENDEN (Smiths Industries Aerospace and Defence INTER-PARTITION DATA INTEGRITY IN THE Systems, Ltd., Cheltenham, England) IN: AIAAlIEEE Digital ASYNCHRONOUS DATAC ENVIRONMENT Avionics Systems Conference, 8th, San Jose, CA, Oct. 17-20, DAVID E. BAKKEN (Boeing Commercial Airplanes, Seattle, WA) 1988, Technical Papers. Part 2. Washington, DC, American Institute IN: AIAAlIEEE Digital Avionics Systems Conference, Bth, San Jose, of Aeronautics and Astronautics, 1988, p. 842-846. Research CA, Oct. 17-20, 1988, Technical Papers. Part 2. Washington, DC, supported by the Alvey Directorate of England. American Institute of Aeronautics and Astronautics, 1988, p. (AIAA PAPER 88-4027) 724-730. refs As the environment in which military aircraft operate becomes (AIAA PAPER 88-4010) increasingly hostile and the advances in avionics systems provide The Digital Autonomous Terminal Access Communication the crew with ever more data, mission effectiveness will be put at (DATAC) system, a two-way multiple-access data bus for avionics risk by the increase in crew workload. The tactical decision aid applications, is described, with a focus on data-integrity problems (TDA) is a system designed to alleviate this workload problem by arising when time-sliced processes or process groups communicate using the incoming data to supply the crew with high-level via DATAC variables. Particular attention is given to the Integrated information upon which tactical decisions can be made. This paper Avionics Computer System software developed to solve these outlines the primary processes of the TDA namely sensor fusion problems in future transport aircraft. The partition interface and and mission planning which have been approached from an AI RTE routine implementation are discussed and illustrated with perspective. The test-bed for this work has been a ground attack diagrams, and the relative advantages of hardware and software mission and in particular the hostile ingress and egress phases of solutions to the integrity problem are considered. T.K. the mission. Author

A8918162# A89- 18864 GAAS 32-BIT SINGLE BOARD COMPUTER SOFTWARE DEVELOPMENT FOR LARGE SCALE AVIONIC JAN W. WINE (McDonnell Douglas Astronautics Co., Huntington INTEGRATION PROGRAMS Beach, CA) IN: AIAAlIEEE Digital Avionics Systems Conference, RALPH HAMPP and CECIL RICHARDSON (IBM Corp., Federal 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. Systems Div., Owego, NY) IN: AHS, Annual Forum, 44th, Washington. DC, American Institute of Aeronautics and Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, Astronautics, 1988, p. 738-741. refs American Helicopter Society, 1988, p. 191-200. refs (AIAA PAPER 88-4012) Good management and control of software development is a This paper describes the architecture and design of an necessity in today's digital avionic environment. The last 20 years all-gallium arsenide (GaAs)32-bit, single board computer. The GaAs have seen a major trend away from the analog systems of the single board computer is part of a technology development program 1950s to the digital avionics of the 1980s. This trend encompasses to produce a radiation hard, low power, high speed GaAs not only the extensive computer systems found on almost all processing system suitable for a variety of applications. This paper modern airplanes and helicopters, but also every newly developed focuses on an architecture designed for an embedded system, black box is designed around a microprocessor and uses digital where space and power are limiting constraints. Author firmware. Laboratory facilities needed to validate the performance of these systems and their black boxes have also undergone a A8918163# digital transformation with insignificant focus on the ability to A MlL-STD-l750A, SINGLE-BOARD COMPUTER FOR simulate hardware before the hardware is delivered. This paper EMBEDDED MULTIPROCESSOR APPLICATIONS describes the structured approach that IBM uses to manage and JOHN M. DREES (McDonnell Douglas Astronautics Co., Huntington control software development on large scale avionic programs. Beach, CA) IN: AIAAlIEEE Digital Avionics Systems Conference,. The paper also describes the software specification process, 8th, San Jose, CA, Oct. 17-20, 1988, Technical Papers. Part 2. system validation techniques, and test facilities used by IBM Federal Washington, DC, American Institute of Aeronautics and Systems (FS) since these are so closely related to the software Astronautics, 1988, p. 742-747. development. Author (AIAA PAPER 88-4015) This paper details the development of a standard-building-block A8918922 1750A-multiprocessor-single-boardcomputer. It also describes a HOLOMETRICS - AN INFORMATION TRANSFORMATION MIL-STD-1750A development environment that supports these METHODOLOGY concepts. Such topics as using a cache memory scheme in a C. T. GUNSALLUS, W. L. PELLUM, and W. G. FLANNELLY (Kaman multiprocessing environment and using the VME bus as a Aerospace Corp., Bloomfield, CT) IN: AHS, Annual Forum, 44th, multiprocessing system bus are also discussed. Author Washington, DC, June 16-18, 1988, Proceedings. Alexandria, VA, American Helicopter Society, 1988, p. 879-885. A89181 66# Mathematical signal processing and information correlation ADA EXECUTIVE FOR DISTRIBUTED AVIONICS PROCESSING techniques have been developed which make real time rotating DAVID W. LYNESS (TAU Corp., Long Beach, CA), ROBERT A. system load determination possible using only fixed system MANSKE (USAF, Wright Aeronautical Laboratories, information. These mathematical techniques are presented. In Wright-Patterson AFB, OH), and RICHARD A. ROGERS (Rogers addition, the results of these techniques when applied to recorded Aerospace, Redondo Beach, CA) IN: AIAAlIEEE Digital Avionics flight data are shown as a comparison between the recorded Systems Conference, 8th, San Jose, CA, Oct. 17-20, 1988, rotating system parameter(s) and the same parameter(s) as Technical Papers. Part 2. Washington, DC, American Institute of determined by the mathematical techniques applied to fixed system Aeronautics and Astronautics, 1988, p. 761-766. information. The mathematical technique and some results which (AIAA PAPER 88-4042) have been obtained are presented. Author

200 15 MATHEMATICAL AND COMPUTER SCIENCES

A89-18937# 17-20, 1988. 5 p. A FIXED BASE DATA SYSTEM FOR FLIGHT TESTING (AIAA PAPER 88-3946) DONALD L. MARSHALL (McDonnell Douglas Helicopter Co.,Mesa, This paper elaborates on the methodologies used to develop AZ) and JAMES L. WlLLlS (New Mexico State University, Las and apply software quality indicators (SQls) that assist software Cruces) AHS, Annual Forum, 44th, Washington, DC, June 16-18, managers in their control of software development projects. The 1988, Paper. 7 p. use of Operational Flight Programs and Quality Improvement A new flight test data system for testing of current and future Program reports in such methodologies is addressed. The generation helicopters is described. The system uses off-the-shelf application of SQls to avionics software for the F-16 aircraft is main frame computers and a hybrid of peripherals not previously reviewed. C.D. utilized in telemetry system applications. Included are high-speed I/O processors, computer disks, fast laser printer/plotters, and a A89-19861# unique utilization of distributed microcomputer preprocessors that HIGH-SPEED DATA BUS PROCESSING NODE allow future expandability. The design goal is to permit modular DARYLE B. HAMLIN (Unisys Corp., Computer Systems Div., Saint expansion and/or change with little or no effect on other system Paul, MN) AIAA, Digital Systems Conference, 8th. San Jose, modules. C.D. CA, Oct. 17-20, 1988. 13 p. (AIAA PAPER 88-4009) A8919560 Future avionics system architectures and concepts are A PARALLEL ARCHITECTURE FOR A REAL-TIME BLADE becoming increasingly dependent upon VHSIC/VLSI technology ELEMENT ROTORCRAFT SIMULATION that supports very highly integrated, distributed processing nodes. HERBERT GILLMAN, 111 (Advanced Rotorcraft Technology, Inc., This paper describes an implementation of such a processing node Mountain View, CA) IN: Aerospace simulation 111; Proceedings of which is based on a 3.8 MIPS MIL-STD-1750A CPU supporting the SCS Multiconference, San Diego, CA, Feb. 3-5, 1988. San 256K of local memory combined with a dual-redundant interface Diego, CA, Society for Computer Simulation International, 1988, to a fiber-optic, linear token-passing, high-speed, serial data bus p. 117-126. and a standard PI-bus backplane interconnect. This node is a A methodology which makes it possible to design and evaluate common module implementation featuring surface-mount parallel processing architectures iadependent of hardware is technology on a single-width, SEM E printed circuit module presented. The methodology was applied to an existing real-time supporting custom CMOS, ECL, and hybrid devices. The serial simulation of the X-wing circulation control rotor system on architectural features of the high-speed processing mode that NASA‘s rotor system research aircraft. The results indicate that provide for high performance, distributed processing, fault an update rate of 100 Hz is attainable with relatively low cost tolerance, high reliability, interoperability, and standardized devices hardware that is currently available. K.K. are described. C.D. A89- 19862# A8919679 INTEGRATED CNI TERMINAL SOFTWARE ARCHITECTURE DEVELOPING ERROR-FREE SOFTWARE RICHARD A. BRYSON (TRW, Inc., Military Electronics and Avionics B. G. KOLKHORST and A. J. MACINA (IBM Corp., Systems Div., San Diego, CA) AIAA, Digital Systems Conference, 8th, Integration Div., Houston, TX) IEEE Aerospace and Electronic San Jose, CA, Oct. 17-20, 1988. 9 p. Systems Magazine (ISSN 0885-8985), vol. 3, Nov. 1988, p. 25-31. (AIAA PAPER 88-4022) The authors describe experience gained in designing This paper describes the current architecture and features of reconfiguration-error-freesoftware. From 1982-1985, this division the integrated communication-navigation-identification (CNI) family reduced software product defects to 0.11 errors per thousand of integrated avionic systems and how they apply to the PAVE lines of source code. Four measurements defining software quality PILLAR preferred system architecture for the next generation of are described. Also discussed is NASA’s development of a avionics. The key features are a hierarchically distributed design siandardized suii+iaie siippoii enviionmon!, zn:! !he US from the avionics authority (pilot, mission tapeldisk or mission Department of Defense Software Technology for Adaptive Reliable data computer) down through the CNI subsystem and into the Systems (STARS) program. These environments provide for early line-replaceable modules, infusion of expert system technology into control, standardization, and integration of requirements, leading the integrated built-in test and maintenance segment, and an to more easily maintained software and reduction of critical skill integration of the resource management and integrated built-in level for its maintenance. I.E. test and maintenance segments at each level of the hierarchy to effect efficient dynamic reconfiguration of the common modules A8919811# of these systems. Author A METHOD OF COMPUTER AIDED DESIGN OF STRUCTURAL TYPE - AN APPLICATION OF EXPERT SYSTEM AND FUZZY A8920139# SETS THEORY ZONAL GRID GENERATION METHOD FOR COMPLEX YONGSHUN ZHANG and FAJIE WE1 (Beijing University of CONF~GURATIONS Aeronautics and Astronautics, People’s Republic of China) Acta E. ATTA, L. BIRCKELBAW, and K. HALL (Lockheed-Georgia Co., Aeronautica et Astronautica Sinica (ISSN 1000-6893), vol. 9, Aug. Marietta) Journal of Aircraft (ISSN 0021-8669), vol. 25, Oct. 1988, p. 8387-8391. In Chinese, with abstract in English. refs 1988, p. 911-913. Previously cited in issue 08, p. 1140, Accession The conception of CAD (Computer Aided Design) is briefly no. A87-22528. refs discussed. Moreover, the application of expert system and fuzzy sets theory to CAD is described. Two examples of choosing N89-14749# Boeing Military Airplane Development, Seattle, structural type of airplane wings are given in this paper to illustrate WA. the method discussed here. A degree of ’satisfaction’ for index of CEPS AN ARTIFICIAL INTELLIGENCE APPROACH TO structural weight and cost is expressed by a value of the AVIONICS MAINTENANCE membership function of fuzzy sets. The membership functions DAVID W. PAPENHAUSEN and BRENT L. HADLEY In Colorado embody experiences of experts. The results of the two examples Univ., Proceedings of the Air Force Workshop on Artificial are satisfactory. Author Intelligence Applications for Integrated Diagnostics p 208-217 Jul. 1987 A89-19860# Avail: NTlS HC A23/MF A01 CSCL 121 THE DEVELOPMENT AND APPLICATION OF SOFTWARE This discussion presents CEPS, the B-1B ClTS Expert QUALITY INDICATORS Parameter System. CEPS combines expert system technology, WILLIAM A. WHITFILL, 111 (General Dynamics Corp., Fort Worth, conventional programming and a large data base to provide a TX) AIM, Digital Systems Conference, 8th, San Jose, CA, Oct. system which assists in maintenance diagnostics. This approach

201 optimizes the use of avionics design knowledge, avionics JOSEPH C. HINTZ In Colorado Univ., Proceedings of the Air maintenance expertise, and statistical analysis of past and present Force Workshop on Artificial Intelligence Applications for Integrated failure indications to improve fault detection and isolation. Diagnostics p 375-383 Jul. 1987 Development of a prototype CEPS applied to the B-1B avionics is Avail: NTlS HC A23/MF A01 CSCL 121 being performed by the Boeing Military Airplane Company under Large, complex weapons systems are maintained by several contract to the Air Force's Aeronautical Systems Division, B-1B echelons of troubleshooting personnel. Each echelon repairs a Program Office. This paper presents a brief background of CEPS certain category of faults and notifies a higher echelon if unable and describes the elements which compose the prototype to effect repairs. As the level of the echelon increases, the system. Author mean-time-to-repair, the training level of the maintenance personnel, the complexity of troubleshooting tools, and the difficulty N8914758# Lockheed Missiles and Space Co., Palo Alto, CA. in locating faults all increase. In addition, multiple faults become Research and Development Div. much more likely as maintenance-induced faults appear. An expert ON-BOARD EXPERT DIAGNOSTICS FOR AN AVIONICS system that aids a higher echelon maintenance team in one SUBSYSTEM subsystem (a phased array antenna) of a ground-based radar PRESTON A. COX In Colorado Univ., Proceedings of the Air system is discussed. At this time, the expert system exceeds 33,000 Force Workshop on Artificial Intelligence Applications for Integrated lines of code (500+ rules). Lower level echelons will have repaired Diagnostics p 349-351 Jul. 1987 95 percent of the faults by using sophisticated BITE and Avail: NTlS HC A23/MF A01 CSCL 121 computer-aided troubleshooting techniques. The faults requiring a Fault detection and isolation in military weapons systems is an higher echelon will require expert experienced assistance in area of interest to the military. Current on-board diagnostic tools successful troubleshooting techniques. The expert system utilized report a costly number of faults that cannot be reproduced or knowledge of previous maintenance activities and system level isolated by maintenance technicians. Maintenance testing of a symptoms to determine the type of fault most probable. It then subsystem that cannot be found to be faulty is costly in terms of selects the information sources that are most useful in making a equipment downtime and maintenance manhours. The need exists more accurate diagnosis and instructs the user in the procedures for diagnostic tools that will provide an improved fault detection used to obtain the information. For example, diagnostic tests may and isolation capability. Expert systems technology can contribute be executed singly or in groups. Futhermore, the tests may be significantly to satisfying this need. This paper describes a program executed once in a search for hard faults or in a loop when to develop an Expert Integrated Diagnostician to apply advanced searching for intermittents. Schematics may be used for expert system capabilities to improving on-board fault detection connectivity information. Diagnostic test pseudo-code and fault and isolation in the military avionics domain. Author mapping data may be considered to isolate the fault to plausible regions of malfunction. Discussion includes the use of N8914760# McDonnell Aircraft Co., St. Louis, MO. meta-knowledge in the expert system to control the execution of AVIONICS FAULT TREE ANALYSIS AND ARTIFICIAL rules, the development of an interface between the expert system INTELLIGENCE FOR FUTURE AIRCRAFT MAINTENANCE and an existing graphical data base of schematics, and the expert MICHAEL E. HARRIS and THOMAS D. SNODGRASS In Colorado system's ability to diagnose intermittent and multiple faults. In Univ., Proceedings of the Air Force Workshop on Artificial concludes with lessons learned and future plans. Author Intelligence Applications for Integrated Diagnostics p 363-374 Jul. 1987 N89-14763# Air Force Wright Aeronautical Labs., Avail: NTlS HC A23/MF A01 CSCL 121 Wright-Patterson AFB, OH. The F/A-18 aircraft has demonstrated that reduced Life Cycle THE 6-16 CENTRAL INTEGRATED TEST SYSTEM EXPERT Costs and improved operational readiness can be designed-in PARAMETER SYSTEM without retreating from performance requirements when emphasis GERARD J. MONTGOMERY In Colorado Univ., Proceedings of is properly balanced between Reliability, Maintainability and Design. the Air Force Workshop on Artificial Intelligence Applications for The Avionics Fault Tree Analyzer (AFTA) is a suitcase size flight Integrated Diagnostics p 388-393 Jul. 1987 Previously line tester capable of extending the F/A-18 fighter's built-in-test announced in IAA as A87-16839 (BIT) fault isolation capabilities beyond the Weapon Replaceable Avail: NTlS HC A23/MF A01 CSCL 121 Assembly (WRA), to the Shop Replaceable Assembly (SRA) Level. The B-18 Central Integrated Test System (CITS) provides a The AFTA was developed as an interim support tool for the Navy comprehensive on aircraft diagnostic capability and records prior to attainment of total organic support capability, and as an approximately 19,600 parameters. The 6-1B CITS Expert Parameter alternate method of support to reduce Life Cycle Cost for F/A-18 System (CEPS) is an initiativeto improve B1B diagnostic capabilities foreign military sales. With the transformation of the AFTA concept by applying expert system and data analysis techniques to the from ground support equipment to avionics, a quantitative in-flight recorded data. The manner in which CEPS enhances B-1B improvement in Life Cycle Costs will be obtained through the on and off aircraft diagnostic capabilities and reduces false alarm, application of Artificial Intelligence (AI) techniques. AI is expected can not duplicate and re-test okay accurrences will be presented. to see applications to practical problems in many disciplines; and The CEPS capabilities will be discussed and an overview of the one of which is the implementation of the military fault diagnostic accomplishments and status of the CEPS program will be given. system. Using AI techniques, a smart BIT is being developed which This paper will illustrate the applicability of the B-1B CEPS concepts will reduce false alarms, identify intermittent failures, and improve to other existing and future weapon systems. The ability to reduce fault isolation to the lowest possible element. Increasing density future weapon system built-in test requirements through the use of computer memory, modularly designed avionic functions and of on-aircraft expert systems will be discussed, along with the the use of very large scale and high speed integrated devices will need for a ground based diagnostic system. Author allow future aircraft to fly with the AFTA function. Ramifications such as eliminating the need for intermediate avionic repair facilities, N89-14795'# California Univ., Los Angeles. Lab. for Flight increased aircraft operational readiness, decrease in aircraft Systems Research. recurring cost, and a reduction in spares investment are discussed. EFFICIENT LOAD MEASUREMENTS USING SINGULAR VALUE This paper will summarize the AFTA concept, Life Cycle Cost DECOMPOSITION Flnal Report, 1 Jan. 1987 - 31 Mar. 1988 advantages, and the implementation of Artificial Intelligence in KUNG YAO and A. V. BALAKRISHNAN 1988 18 p future avionic designs relative to improved reliability and (Contract NAG2-433) maintainability. Author (NASA-CR-184614; NAS 1.26:184614) Avail: NTlS HC A03/MF A01 CSCL 12A N89-14761# Raytheon Co.,Bedford, MA. Various basic research was performed on efficient load EXPERT SYSTEMS IN HIGHER ECHELON MAINTENANCE measurement estimation techniques for aircraft structure analysis. ACTIVITIES An overview is presented of the load measurement problem. Two

202 16 PHYSICS basic equivalent approaches to load measurement evaluations were a large aeroacoustic wind tunnel are presented to investigate the considered. Under approach 1, the load values are modeled as parametric effects of rotor operating conditions on blade-vortex depending linearly on the measured values. Under approach 2, interaction (BVI) impulsive noise. Contours of a BVI noise metric the measured values depend linearly on the load values. By using are employed to quantify the effects of rotor advance ratio and the modern Singular Value Decomposition method, it was shown tip-path-plane angle on BVI noise directivity and amplitude. Acoustic that under all conditions of the number of loads and number of time history data are presented to illustrate the variations in gages, approach 1 is equivalent to approach 2. By using the impulsive characteristics. The directionality, noise levels and conventional normal equation (linear regression) approach, impulsive content of both advancing and retreating side BVI are approach 1 is only valid when the number of loads is equal to or shown to vary significantly with tip-path-plane angle and advance greater than the number of gages, while approach 2 is the reverse. ratio over the range of low and moderate flight speeds Furthermore, except for the case of the number of loads equals considered. Author the number of gages, the load prediction formulas under the two approaches are not equivalent. Author A89-18948 MEASUREMENTS IN THE FIELD OF A SPARK EXCITED COMPRESSIBLE AXISYMMETRIC JET 16 S. EMAMI (General Dynamics Corp.. Fort Worth, TX), C. OSTOWARI, and A. AHMED (Texas A & M University, College Station) Experiments in Fluids (ISSN 0723-4864), vol. 7, no. 1, PHYSICS 1989, p. 69-71. refs Acoustic phase (ensemble) averaged measurements were Includes physics (general); acoustics; atomic and molecular performed in a constant temperature, axisymmetric. Mach 0.6 jet physics; nuclear and high-energy physics; optics; plasma physics; of air. These measurements show that the noise directly radiated solid-state physics; and thermodynamics and statistical physics. by the coherence structure in the jet flow field was responsible for the directivity of the acoustic field. Author

A89-18912 A89-19672 EXPERIMENTAL ASSESSMENT OF A TURBULENCE CONTRIBUTIONS TO THE THEORY OF SOUND PRODUCTION INGESTION NOISE THEORY BY VORTEX-AIRFOIL INTERACTION, WITH APPLICATION TO JOHN SIMONICH, ROBERT SCHLINKER (United Technologies VORTICES WITH FINITE AXIAL VELOCITY DEFECT Research Center, East Hartford, CT), and ROY AMlET IN: AHS, M. S. HOWE (BBN Laboratories, Inc., Cambridge, MA) Royal Annual Forum, 44th. Washington, DC, June 16-18, 1988, Society (London), Proceedings, Series A - Mathematical and Proceedings. Alexandria, VA, American Helicopter Society, 1988, Physical Sciences (ISSN 0080-4630), vol. 420, no. 1858, Nov. 8, p. 731-745. refs 1988, p. 157-182. Navy-supported research. refs A model helicopter rotor was tested in a closed anechoic The sound produced when a vorticity field is cut by an airfoil chamber to assess the accuracy of a rotor noise theory for in low-Mach-number flow is analyzed. A general formula is nonisotropic turbulence ingestion. The measured aerodynamic presented for the acoustic pressure when the airfoil is rigid and properties were used as inputs to a noise prediction procedure. the chord is acoustically compact. This makes it possible to express The agreement between the experimental data and predictions is the radiation in terms of an integral over the region occupied by good, although the analysis generally overpredicts the quasi-tonal the vorciticity; the integrand contains factors describing the effect low to mid range frequencies and underpredicts the higher of the thickness, twist, and camber of the airfoil. Explicit analytical broadband signals. The predicted sound power level as a function results are obtained for a rectilinear vortex, having small core of polar angle is in close agreement with measurements, except diameter and finite axial velocity defect, which is cut by a nonlifting ncz: the :et=: p!s~o,urhich nc? mnrlelnd hy the present is Cl,,,",~riAmil nfVI Inmn.'.J - .--r.....rrcnnrt rrrtin B.J. analysis. V.L.

A89-18913 A89-19902# A COMPARISON OF ACOUSTIC PREDICTIONS WITH MODEL FREQUENCY-DOMAIN METHOD FOR THE COMPUTATION OF ROTOR TEST DATA FROM THE NASA 14 X 22 FT WIND PROPELLER ACOUSTICS TUNNEL J. B. H. M. SCHULTEN (Nationaal Lucht- en Ruim- CHRISTIAN J. SCHWINDT and JAMES M. FITZGERALD (United tevaartlaboratorium, Amsterdam, Netherlands) AI AA Journal Technologies Corp., Sikorsky Aircraft Div., Stratford, CT) IN: (ISSN 0001-1452), vol. 26, Sept. 1988, p. 1027-1035. Research AHS, Annual Forum, 44th. Washington, DC, June 16-18, 1988, supported by Nederlands lnstituut voor Vliegtuigontwikkeling en Proceedings. Alexandria, VA, American Helicopter Society, 1988, Ruimtevaart. Previously cited in issue 04, D. 569, Accession no. p. 747-756. refs A88-16537. refs A study to correlate the predictions of the NASA-developed ROTONET rotorcraft acoustic prediction code and the Sikorsky A89-19903# in-house rotorcraft acoustic prediction code with model wind tunnel HOLE TONE GENERATED FROM ALMOST CHOKED TO tests is presented. The prediction methodology models thickness, HIGHLY CHOKED JETS steady and unsteady loading effects, with the unsteady loading Y. UMEDA, H. MAEDA, and R. ISHll (Kyoto University, Japan) derived from forward flight and simple wake models. The predictions AlAA Journal (ISSN 0001-1452), vol. 26, Sept. 1988, p. have been compared with the acoustic data on the basis of similarity 1036-1043. refs of the acoustic pressure time histories. Author The hole tone generated from the interaction of high-speed jets with a round hole was experimentally investigated in order to A89-18914' Planning Research Corp., Hampton, VA. clarify its generation mechanism. Measurements of far-field TIP-PATH-PLANE ANGLE EFFECTS ON ROTOR pressure waves as well as schlieren flow visualization were carried BLADE-VORTEX INTERACTION NOISE LEVELS AND out. The frequency characteristics of the present hole tone are DIRECTIVITY similar to those of hole tones radiated from a low-speed jet. Flow CASEY L. BURLEY (Planning Research Corp., Hampton, VA) and visualization confirms that this hole tone is generated by essentially RUTH M. MARTIN (NASA, Langley Research Center, Hampton, the same feedback mechanism as that of the impinging tone VA) IN: AHS, Annual Forum, 44th, Washington, DC, June 16-18, radiated from high-speed jets. When a ring vortex interacts with 1988, Proceedings. Alexandria, VA, American Helicopter Society, the plate with a hole, an acoustic pulse is emitted with a strong 1988, p. 757-771. refs directional peak in the upstream direction. The acoustic pulse Acoustic data of a scale model BO-105 main rotor acquired in propagates outside the jet and forces the generation of a new

203 16 PHYSICS eddy on reaching the nozzle lip. The new eddy grows as it coordinate system on a body-conformed, curvilinear grid of C-H propagates downstream to interact with the circumference of the topology. Detailed boundary layer and global numerical hole. Author comparisons of NACA-0012 symmetrical and CAST7-158 supercritical airfoils are made under identical forward flight A8920143*# Planning Research Corp., Hampton, VA. conditions. The rotor wake effects are modeled by applying a ACOUSTIC TRANSMISSIBILITY OF ADVANCED TURBOPROP correction to the geometric angle of attack of the blade. This AIRCRAFT WINDOWS correction is obtained by computing the local induced downwash FERDINAND W. GROSVELD (Planning Research Corp., Hampton, velocity with a free wake analysis program. The calculations are VA) Journal of Aircraft (ISSN 0021-8669), vol. 25, Oct. 1988, p. performed on the Numerical Aerodynamic Simulation Cray 2 and 942-947. Previously cited in issue 04, p. 568, Accession no. the VPS32 (a derivative of a Cyber 205 at the Langley Research A88-16530. refs Center) for a model helicopter rotor in forward flight. Author (Contract NASl-16978) N8914818# Bolt, Beranek, and Newman, Inc., Canoga Park, 17 CA. DETAILED DESIGN SPECIFICATION FOR A PROTOTYPE ASSESSMENT SYSTEM FOR AIRCRAFT NOISE (ASAN) SOCIAL SCIENCES Interim Report, 12 Feb. - 15 Oct. 1987 FIDELL SANFORD, MICHAEL HARRIS, and NICHOLAAS Includes social sciences (general); administrationand management; REDDlNGUlS Jul. 1988 93 p documentation and information science; economics and cost (Contract F33615-86-(2-0530) analysis; law and political science; and urban technology and (AD-A197936 BBN-R-6499) Avail: NTlS HC A05/MF A01 transportation. CSCL 12G The US. Air Force Noise and Sonic Boom Impact Technology (NSBIT) Program is sponsoring a multi-stage effort to create a A8918949 computer system containing tools needed by the environmental NEW PROPOSALS FOR NEW DIRECTIONS - 1992 AND THE planning community to perform a variety of tasks related to GAlT APPROACH TO TRADE IN AIR TRANSPORT SERVICES assessing the environmental impacts of aircraft noise on people, PAUL V. MIFSUD (KLM Royal Dutch Airlines, New York) Air animals, and structures. This interim report provides a detailed Law (ISSN 0165-2079), vol. 13, Oct. 1988, p. 154-171. refs design specification for a prototype version of the NSBIT Developments significantly affecting both European and North Assessment System for Aircraft Noise (ASAN) that is the major American air transport are discussed. These are: (1) the Single project of the first stage of this effort. The purposes and expected European Act which calls for an open 'internal market' by the uses of ASAN are presented in Fidell and Harris (1987). The end of 1992; (2) the invasion of a mature, deregulated, and general functional capabilities of this system are described by Harris consolidated US. airline industry into international air transport; and Fidell (1987). The current report describes the organization and (3) the current Uruguay Round, which is causing GATT trade of ASAN, its functional capabilities, and its major software negotiators to consider application of the GAlT principles to trade modules. GRA in services. It is noted that consideration must be given to the complications of multiple routings, third country obligations, and N89-14820'# Planning Research Corp., Hampton, VA. intercarrier arrangements. K.K. USERS MANUAL FOR THE LANGLEY HIGH SPEED PROPELLER NOISE PREDICTION PROGRAM (DFP-ATP) A89-18950 M. H. DUNN and G. M. TARKENTON Washington, DC NASA PROPOSED REVISIONS TO AMERICAS NATIONAL Jan. 1989 46 p AIRSPACE SYSTEM - A CRISIS IN LEADERSHIP? (Contract NAS1-18000) ALAN ARMSTRONG Air Law (ISSN 0165-2079), vol. 13, Oct. (NASA-CR-4208; NAS 1.26:4208) Avail: NTlS HC A03/MF A01 1988, p. 172-177. refs CSCL 20A The paper discusses the legislative origins of a debate The use of the Dunn-Farassat-Padula Advanced Technology concerning the extent to which Mode 'C' (altitude reporting) Propeller (DFP-ATP) noise prediction program which computes the transponder equipment may be required of aircraft operated in periodic acoustic pressure signature and spectrum generated by US. airspace. The current proposal regarding Mode 'C' equipment propellers moving with supersonic helical tip speeds is described. and airspace reconfiguration advanced by the FAA is examined The program has the capacity of predicting noise produced by a as well as Congressional and general aviation's response to the single-rotationpropeller (SRP) or a counter-rotationpropeller (CRP) proposal. An attempt is made to find alternate solutions to the system with steady or unsteady blade loading. The computational problems which caused the debate in the first place. K.K. method is based on two theoretical formulations developed by Farassat. One formulation is appropriate for subsonic sources, A89201 36# and the other for transonic or supersonic sources. Detailed GENERAL AVIATION COST EFFECTIVENESS descriptions of user input, program output, and two test cases RICHARD E. ETHERINGTON (Gates Learjet Corp., Wichita, KS) are presented, as well as brief discussions of the theoretical Journal of Aircraft (ISSN 0021-8669), vol. 25, Oct. 1988, p. 890-896. formulations and computational algorithms employed. Author Previously cited in issue 03, p. 413, Accession no. A87-14037. refs N8914821*# Planning Research Corp., Hampton, VA. Aerospace Technologies Div. NUMERICAL SIMULATION AND COMPARISON OF SYMMETRICAL/SUPERCRITICAL AIRFOILS FOR THE NEAR 19 TIP REGION OF A HELICOPTER IN FORWARD FLIGHT F. F. BADAVI Washington, DC NASA Jan. 1989 54 p GENERAL (Contract NAS1-18000) (NASA-CR-4212; NAS 1.26:4212) Avail: NTlS HC A04/MF A01 CSCL 20A Aerodynamic loads on a multi-bladed helicopter rotor in forward flight at transonic tip conditions are calculated. The unsteady, A89-17867# three-dimensional, time-accurate compressible Reynolds-averaged THE X-20 SPACE PLANE - PAST INNOVATION, FUTURE thin layer Navier-Stokes equations are solved in a rotating VISION

204 19 GENERAL

TERRY L. SUNDAY (Martin Marietta Corp., Astronautics Group, El Paso, TX) and JOHN R. LONDON, 111 (Florida Institute of Technology, Las Cruces, NM) IAF, International Astronautical Congress, 39th, Bangalore, India, Oct. 8-15, 1988. 17 p. refs (IAF PAPER 88-598) The X-20 space plane, known as Dyna-Soar, never reached operational status -- it was cancelled in December 1963, before the first prototype was built. This paper examines both the history and the technology of Dyna-Soar. The space plane's unique design and its proposed missions are examined, along with the ever-changing political, economic and programmatic environments that led to its conception, its long, painful gestation period, and its demise. Author

A89-20251 THE X-PLANES X-1 TO X-31 (2ND REVISED AND ENLARGED EDITION) JAY MILLER (Aerofax, Inc.. Grand Prairie, TX) New York, Orion Books, 1988, 216 p. refs Development histories are presented for the family of 'X-designated' experimental aircraft designed for, and operated by, NACA and NASA from 1945 to the present. The initial aircraft of the series, the rocket-powered X-1, investigated the dynamic flight characteristics of an aircraft passing the sonic barrier into the supersonic speed regime. Additional noteworthy aircraft included the variable wing-sweep X-5, the uncompleted nuclear-powered X-6, the vectorable-thrust VTOL X-14, !he hypersonic X-15, the tilt-winghacelle VTOL X-18, and the BLC-incorporating X-21. Among next-generation X-aircraft are the X-30 testbed for the hypersonic National Aerospace Plane and the X-31 post-stall condition maneuvering aircraft. O.C. SUBJECT INDEX

AERONAUTICAL ENGINEERING /AContinuing Bibliography (Supplement 238) April 1989

Typical Subject Index Listing AEROACOUSTICS A study on aerodynamic heating in the interaction regions Tip-path-plane angle effects on rotor blade-vortex of shock waves and turbulent boundary layers induced interaction noise levels and directivity by sharp fins p 148 A89-20131 p 203 A89-18914 Coupled flow, thermal, and structural analysis of Frequency-domain method for the computation of aerodynamically heated panels p 181 A89-20322 propeller acoustics p 203 A89-19902 AERODYNAMIC INTERFERENCE AERODYNAMIC CHARACTERISTICS An investigation of wall interference correction to the Study the aerodynamics characteristics of airfoil on pressure measurement in low speed wind tunnel with solid AEROSPACEPLANES vector processors walls p 183 A89-19808 [IAF PAPER ST-88-09] p 143 A89-17874 Technology Issues associated with lueling the national Interference effects associated with a plate-supported Calculation of the unsteady aerodynamic characteristics Ierosoace Diane wilh slush hydropen half-model in hypersonic flow p 148 A89-19924 of bodies in the case of separated flow p 144 A89-18355 AERODYNAMIC LOADS Determination of the perturbations of the flow fields of A correlation study of rotor inflow in forward flight supersonic wind tunnels from measured aerodynamic p 145 A89-18856 coefficients p 144 A89-18675 Helicopter free wake prediction of complex wake - Rotorcraft aeromechanical analysis using a nonlinear structures under Blade-Vortex Interaction operating unsteady aerodynamic model p 146 A89-18919 conditions p 146 A89-18918 A new approach for computing full unsteady Holometrics - An information transformation aerodynamic characteristics p 147 A89-19788 methodology p 200 A89-18922 Measurements of the buffet boundary of wings in Unsteady low-speed windtunnel test of a straked delta trznsonic !!ow with hot-film method p 148 A89-19805 wing. oscillating in pitch. Part 5: Power spectral density Experimental study on unsteady aerodynamic plots of the overall loads for harmonic oscillation and the The subject heading is a key to the subject COntent characteristics of an oscillating cascade with tip response of overall loads lo (1-COS) inputs of the document The title IS used to provide a clearance p 148 A89-19927 [ AD-A1986831 p 152 N89-13403 description of the subject matter When the litle is Navier-Stokes calculations of hovering rotor flowfields Unsteady low-speed windtunnel test of a straked delta insufficiently descriptive of document content. a [AIAA PAPER 87.26291 p 149 A89-20133 wing, oscillating in pitch. Part 6: Presentation of the Validation of approximate indicia1aerodynamic functions title extension is added, separated from the title visualization program for two-dimensional subsonic flow p 149 A89-20140 [ AD-A1986841 ' p 152 N89-13404 by three hyphens The (NASA or AIAA) accession Low-speed pressure distribution on axisymmetric Efficient load measurements using singular value number and the page number are included in each elliptic-nosed bodies p 149 A89-20147 decomposition entry to assist the user in locating the abstract in Three-dimensionalvortex systems of finite wings [ NASA-CR-1846141 p 202 N89-14795 p 149 A89-20148 Numerical simulation and comparison of the abstract section Ifapplicable. a report number Rotating air scoop as airfoil boundary-layer control symmetricallsupercritical airfoils for the near tip region of IS also included as an aid in identifying the docu. p 150 A89-20149 a helicopter in forward flight Numerical methods for hypersonic flows ment Under any one subject heading. the acces- [ NASA-CR-42121 p 204 N89-14821 sion numbers are arranged in sequence with the [DGLR PAPER 87-0841 p 150 A89-20235 Moving wall effects in unsteady flow AERODYNAMIC NOISE AIAA accession numbers appearing first p 150 ABS-20311 Experimental assessment of a turbulence ingestion Aerodynamic characteristics of rectangular noise theory p 203 A89-18912 An analytical model for the prediction of MRlTR crosgsectional bodies at M = 0.85 p 151 A89-20317 interaction noise main rotorltail rotor Drag reduction factor due to ground effect ... p 151 A8920325 p 165 A89-18931 A Measurements in the field of a spark excited Experimental study on low-speed aerodynamic -..---^^^.LI^ ^"i^..".."..t.i^ k, .,.v"lw"Ay'"-a- ,a.....-.,,- ,-. p 293 +.eO-!eoAa ACOUSTIC EXCITATION characteristics of non-misymmetric slender bodies p 151 A89-20635 Contributions to the theory of sound production by Measurements in the field of a spark excited vortex-airfoil interaction, with application to vortices with compressible axisymmetric jet p 203 A89-18948 User's manual for an aerodynamic optimizationscheeme finite axial velocity defect p 203 A89-19672 that updates flow variables and design parameters The effects of nonlinear damping on large deflection Hole tone generated from almost choked to highly the simultaneously response of structures subjected to random excitation choked jets p 203 A89-19903 [ NASA-CR-1821801 p 151 N89-13399 p 193 N89-13796 AERODYNAMIC STABILITY Aerodynamic design via control thew Studies 01 the dynamics of the twin-lift system Application of the mobility power flow approach to [ NASA-CR-1817491 p 153 N89-13408 structural response from distributed loading [NASA-CR-183273] p 167 N89-13422 Two-dimensional aerodynamic characteristics of the [NASA-CR-t81342] p 193 N89-13817 AERODYNAMIC STALLING OLSITAAT airfoil An evaluation of a Navier-Stokes code for calculations ACTIVE CONTROL [NASA-TM-894351 p 154 N89-14216 of retreating blade stall on a helicopter rotor Design of a simple active controller to suppress AERODYNAMIC COEFFICIENTS p 146 A89-18916 helicopter air resonance p 162 A89-18877 Determination of the perturbations of the flow fields of Further comparisons of interactive boundary-layer and ACTUATORS supersonic wind tunnels from measured aerodynamic thin-layer Navier-Stokes procedures p 149 A89-20137 Digital control of a quadruplex direct drive actuator coefficients p 144 A89-18675 Dynamic stall computations using a zonal Navier-Stokes [AIAA PAPER 88-3951] p 172 A89-18122 AERODYNAMIC CONFIGURATIONS model Design of feedback control systems for unstable plants Numerical grid generation and wtential airfoil analysis [AD-A197942] p 194 N89-14397 with saturating actuators and design AERODYNAMICS [NASA-CR-183392] p 194 N89-14377 [ AD-A1979721 p 154 N89-14219 The Oetztal wind tunnel as basic idea and incentive AERODYNAMIC DRAG lor planning the USAF research center AEDC Tullahoma ADA (PROGRAMMING LANGUAGE) p 183 A89-20245 Universal Ada Test Language (UATL) to support An entropy and viscosity corrected potential method for rotor performance prediction p 145 A89-18857 A walk along interfaces --- aeroelasticity real-time softwarelsystem integration and [ B88170081 p 154 N89-14223 factorylmaintenancefault isolation p 197 A89-18009 Winglets on low-aspect-ratio wings p 149 A89-20142 AEROELASTICITY Ada in avionics - Beyond validation Experimental investigation of propfan aeroelastic [AIM PAPER 88-39071 p 199 A89-18087 A fundamental approach to the sticking of insect response in off-axis flow with mistuning residues to aircraft wings [AIAA PAPER 88-31531 p 175 A89-17941 A fault tolerant avionics multiprocessing system [NASA-CR-183041I p 156 N89-13414 architecture supporting concurrent execution of Ada Aeroelastic response of metallic and composite propfan tasks AERODYNAMIC FORCES models in yawed flow The relationship between the aerodynamic [AIM PAPER 88-39081 p 199 A89-18088 [AIAA PAPER 88-31541 p 175 A89-17942 characteristics of dwbledelta wings and vortices with Vibration, performance, flutter and forced response A study - F-16 Ada Digital Flight Control System case sideslips at high angles of attack p 148 A89-19801 characteristics of a large-scale propfail and its aeroelastic [AIAA PAPER 88-3911 ] p 171 A89-18090 Experimental study on unsteady aerodynamic model Ada executive for distributed avionics processing characteristics of an oscillating cascade with tip [AIAA PAPER 88-31551 p 176 A89-17943 [AIAA PAPER 88-40421 p200 A89-18166 clearance p 148 A89-19927 Bearinglessrotors and higher harmonic control modeling ADAPTIVE CONTROL AERODYNAMIC HEATING using RACAP p 162 A89-18876 Reconfigurable flight control system simulation Detection of laminar-turbulent transition by inhared Aeroelastic optimization of a helicopter rotor p 181 A89-19558 thermography p 143 A89-17147 p 163 A89-18898

A- 1 AERONAUTICAL ENGINEERING SUBJECT INDEX

Dynamic characteristics of advanced bearingless rotors Modeling mission reliability of advanced integrated A MIL-STD-1750ASsingle-board computer for embedded at McDonnell Douglas Helicopter Company communication. naviaation. identification avionics multiprocessor applications p 164 A89-18899 systems [AIM PAPER 88-40151 p 200 A89-18163 Static aeroelastic characteristics of circulation control [AIAA PAPER 88-40231 p 173 A89-18174 AIRCRAFT ACCIDENT INVESTIGATION wings p 167 A89-20144 Architecture of an optimal navigation system integratmg Disorientation accidents and incidents in U.S. Army Unsteady transonic aerodynamics and aeroelastic GPS p 160 ABS-18751 helicopters. 1 January 1980 - 30 April 1987 calculations at low-supersonic freestreams Radionavigationneeds for the Europe of the future [APAI987201 p 158 N89-13417 p 149 A89-20145 p 160 A89-18753 AIRCRAFT ACCIDENTS Modern wing flutter analysis by computational fluid Special commitlee on future air navigation systems Numerical simulation of the 2 August 1985 DFW dynamics methods p 191 A89-20146 (FANS) p160 A89-18754 microburst with the three-dimensional Terminal Area Comment on 'Aeroelastic oscillations caused by Integrated CNI terminal software architecture Simulation System p 175 A89-19186 transitional boundary layers and their anenuation' Aircraft accident reports: Brief format. civil and [AIM PAPER 88-40221 p 201 A89-19862 US p 167 A89-20150 foreign aviation. issue number 4 of 1987 accidents Omega Navigation System A status report A walk along interfaces --- aeroelasticity - [ PE88-9169081 p 155 N89-13413 [E88170081 p 154 N89-14223 p160 A8919867 AIRCRAFT BRAKES AERONAUTICAL ENGINEERING Low-orbit navigation concepts p 184 ABS-1 9870 Carbonlcarbon composite materials for aircraft brakes The Center of Excellence in Rotary Technology a1 Teleport as a concentration point for domestic and p 165 A89-19427 Rensselaer Polytechnic lnsiiite international traffic p 190 A89-20114 AIRCRAFT COMMUNICATION [AD-A198964] p 168 N89-13426 Flight guidance technology Air traffic control (ATC) and airlaround diaital- AERONAUTICAL SATELLITES [DGLR PAPER 87-1191 p 160 A89-20239 communications - Demonstration and evahion Aeronautical satellite networks p 160 ABS-201 17 AIR POLLUTION [AIAA PAPER 88-39981 p 158 A89-18154 AERONAUTICS Atmospheric photochemical modeling of turbine engine Modeling mission reliability of advanced integrated Yearbook 1987 11: DGLR, Annual Meeting, Berlin, fuels and exhausts. Computer model development,volume communication. navigation. identification avionics Federal Republic of Germany, Oct. 5-7, 1987. Reports 2 systems p 142 A89-20226 [AD-A198691] p 196 N89-13833 [AIAA PAPER 88-40231 p 173 A89-18174 AEROSPACE PUNES A microcomputer pollutionmodel for civilian airports and Automatic dependent surveillance data transfer Conceptual study of turbogngines for horizontal takeoff air force bases, model description [AIAA PAPER 88-39971 p 159 A89-18180 and landing space plane [AD-A1990031 p 197 N89-14616 Terminal information for data link [IAF PAPER 88.2531 p 184 A89-17745 [AIAA PAPER 88-40001 p 159 A89-18181 AIR TRAFFIC Special committee on future air navigation systems The X-20 space plane - Past innovatin. future vision Arrival-time guidance in variable winds [IAF PAPER 88-5981 p204 A89-17867 (FANS) p 160 A89-18754 [AIAA PAPER 88-40251 p 159 A89-18176 HYpeNelOCity technology escape system concepts Integrated CNI terminal software architecture AIR TRAFFIC CONTROL program p 184 A89-17929 [AIAA PAPER 88-40221 p 201 A89-19862 A simulation study of data link message exchange. Flight An overview of the Federal Radionavigation Plan Numerical methods for hypersonic flaws deck perspectie o 160 A89-20123 [DGLR PAPER 87-0841 p 150 A8920235 [AIAA PAPER 88-39931 p 158 A89-18151 AEROSPACE SYSTEMS A flight test design for studying airborne applications Oceanic clearance delivery via airlground data link of air to ground duplex data link communications AIAAlIEEE Digital Avionics Systems Conference, 8th. [AIM PAPER 88-39941 p 158 A89-18152 San Jose, CA, Oct. 17-20, 1988. Technical Papers. Parts p 195 N89-14924 Mode S data link applications research in the UK AIRCRAFT COMPARTMENTS 182 p 169 A89-18051 [AIAA PAPER 88-39961 p 158 A89-18153 Modern digital pressure control system A simulation-basedfault injection experiment to evaluate Air traffic control (ATC) and airlground digital [AIAA PAPER 8839481 p 172 A89-18119 self-test diagnostics for a fault-tolerant computer communications Demonstration and evaluation Influenceof a floor on sound transmission into an aircraft [AIAA PAPER 88-38971 p198 A89-18063 . [AIAA PAPER 88-39981 p 158 A89-18154 fuselage model p 166 ABS-20135 I Design and validation of the IFTAS fault-tolerant clock The mode S data link - Experimental work and possible AIRCRAFT CONFIGURATIONS _-_Integrated Fault-Tolerant Avionics System future applications in Western Europe Analysis of a fighter type aircraft configuration with the [AlAA PAPER 88-38991 p 170 A89-18085 [AIAA PAPER 88-39991 p 158 A89-18155 HISS panel method at subsonic and supersonic I AEROTHERMODYNAMICS Data link organization in Mode S secondary surveillance speeds I Detection of laminar-turbulent transition by infrared radar systems -Operational compatibility with other Mode [DGLR PAPER 87-0851 p147 A89-19660 thermography p 143 A89-17147 S systems Transonic Navier-Stokes solutions for a fighter-like ~ AH-1G HELICOPTER [AIM PAPER 88-40031 p 159 A89-18157 configuration p 149 A89-20134 Investigation of CkKcutt component effects on FEM Automatic dependent surveillance data transfer Zonal grid generation method for complex 1 vibration prediction for the AH-1G helicopter [AIAA PAPER 88.39971 p 159 A89-18180 configurations p 201 A89-20139 p 162 A89-18879 Development of the Traffic Alert and Collision Avoidance AIRCRAFT CONSTRUCTION MATERIALS Twodimensional aerodynamic characteristics of the System 111 VCAS Ill) PM AI alloys - Hot prospects for aerospace i OLSlTAAT aidoil [AIM PAPER 88-40021 p 159 A89-18182 applications p 185 A89-17622 [ NASA-TM-894351 p 154 N89-14216 TCAS 111 - Bringing operational compatibility lo airborne Nondestructive testing of composite aircraft structures I AH44 HELICOPTER collision avoidance with infrared and shearographic imaging technologies Digital Fly-By-Wire system for advanced AH-64 [AIAA PAPER 88-4004 J p 159 A89-18183 p 189 ABS-18891 helicopters Terminal area forecasts: Fiscal years 1988-2000 NOTAR hybrid compositelmetal fan blade I [AIAA PAPER 88-39221 p 179 A89-18099 [ AD-A1980791 p 156 N89-13419 p 163 A89-18893 Advanced Apache architecture A flight test design for studying airborne applications Boeing Model 360 Advanced Technology Helicopter - [AIAA PAPER 88-39281 p 174 A89-18188 of air to around duolex data link communications Design features and flight test update p 165 A89-18935 AWAContractor Logistic Support The contractors' p 195 N89-14924 . AIR TRANSPORTATION Introduction of new technologies in the structural area perspectNe p 142 A89-18869 New orooosals for new directions ~ 1992 and the GATT from the viewpoint of IAEG Robotic deburring of complex machined parts approach to trade in air transport services [DGLR PAPER 87-1071 p 143 A89-20242 p 190 A89-18936 p 204 A89-18949 Carbon fiber composites for supersonic technology AIR BREATHING ENGINES AIRBORNE EQUIPMENT [DGLR PAPER 87-1241 p 185 A89-20244 I Variablecycle engines for boostingcruisingvehicles Multiple sample polygonal correlation algorithm for the Evaluation of aluminum-lithium alloys in I [IAF PAPER 88-2491 p 175 A89-17742 determination of ground emitter location compression-stiened aircraft structures Design and integration of air-breathing propulsion [AIM PAPER 88-39871 p i5a ABS-18145 p 191 A89-20315 systems of swce transpals and hypersonic aircraft Ground simulation for airborne equipment Materials and structures for hypersonic vehicles [DGLR PAPER 87-1031 p 176 A89-20241 p 188 ABS-18741 [NASA-TM-101501] p 186 N89-14264 AIR DATA SYSTEMS AIRBORNE INTEGRATED RECONNAISSANCE SYSTEM AIRCRAFT CONTROL I An air data inertial reference system for future Fiber optic applmtions to the hgh altitude Application of dgital technology to aircraft utili mmercial airplanes reconnaissance vehicle systems i [AIM PAPER M-39181 p 171 A89-18095 [AIM PAPER 88-39301 p 187 A89-18104 [AIAA PAPER 88-38721 p 180 A8918114 AIR DEFENSE AIRBORNE SURVEILLANCE RADAR Digital control of a quadruplex direct drive actuator Air combat tactics for the evaluation of rotorcraft Combined numerical and symbolic processing for [AIAA PAPER 88-39511 p 172 A89-18122 characlerislb in the low air wfu of 2010 airborne sweillance An advanced facili for cockpit studiis p 142 A89-18859 [AIM PAPER 88-39851 p 157 A89-18143 [AIAA PAPER 88-39661 p 182 A89-18133 Air-to-air combat helicopter development Data link organization in Mode S secondary surveillance The high speed bus technology development program p 165 A89-18929 radar Systems - Operational Compatibility with other Mode [AIAA PAPER 88-40051 p 187 A89-18158 S systems management system architectural AIR FLOW Vehicle considerations Passive venting technique for shallow cavities [AIAA PAPER 88-40031 p 159 A89-18157 AIRBORNEISPACEBORNE COMPUTERS [AIAA PAPER 88-38751 p 174 A89-18189 [NASA-CASE-LAR-14031-1] p 168 N89-14232 Central maintenance computer system ~ A bold step The unused strategic tool - The airship 1 AIR JETS fornard on the 747-400 p 161 A89-10752 Measurements in the field a excited d spark [AIAA PAPER 88-40391 p 171 A89-18097 Dynamic perspective displays and the control of tilt-rotor compressible axisymmetric jet p 203 A89-18948 Fault tolerant avionics aircraft in simulated flight p 174 A89-18867 AIR LAW [AIAA PAPER 88-39011 p 171 A89-18109 Design of a simple active controller to suppress Proposed revisions lo America's nationel airspace Combined numerical and symbolic processing for helicopter air resonance p 162 A89-18877 System - A MisiS in leadershi? p 204 A89-18950 ailborne surveillance counteracting sidewind control System for aircraft AIR NAVIGATION [AIAA PAPER 88-39851 p 157 A89-18143 landing p 181 A89-19800 Terminal na*tion for the Combat Talon I1 aircraft GaAs 32-bit single board computer Flight guidance technology [AIAA PAPER 884021] p 159 A89-18173 [AIAA PAPER 88-40121 P200 A89-18162 [DGLR PAPER 87-1191 p 160 A89-20239 A-2 SUBJECT INDEX AIRCRAFT SURVIVABILITY

A note on the aircraft minimumtime turns AIRCRAFT FUELS AIRCRAFT PARTS p 182 A89-20638 Aviation fuel lubricity evaluation Application 01 damage tolerance methodology to Management and control of separation by unsteady and [AD-A1981 971 p 177 N89-13434 helicopter dynamic components using the example of a VMtiCal flaws Atmospheric photochemical modeling of turbine engine main rotor pitch link for the AH-IS helicopter [ADAI 98902 1 p 191 N89-13736 fuels and exhausts. Computer model development. volume p 164 A89-18921 A unified approach to vehicle design. control, and flight 1 Methodology for fatigue Substantiation of alternate path optimization p 188 N89-14231 [ AD-A1986901 p 196 N89-13832 sources and degraded modes on helicopter dynamic AIRCRAFT GUIDANCE The poststall nonlinear dynamics and control of an F-18: components p 164 A89-18924 Guidance and Flight Director system lor the V-22 A preliminary investigation p 169 N89-14922 Robotic deburring of complex machined parts Tiltrotor p 190 A89-18936 AIRCRAFT DESIGN [AIAA PAPER 68-39211 p 179 A89-18098 New design, production tools will play key role in 8-2 AIRCRAFT PERFORMANCE Strapdown issues for airborne EO senm Down with drag p 141 A89-18347 cos1 p 161 A89-18350 [AIAA PAPER 88-39271 p 171 A89-18102 The unused strategic tool The airship Human factors impact on the V-22 Osprey cockpit AIRCRAFT HAZARDS - p 161 A89-18752 development - An overview p 174 A89-18865 Thunderstorm avoidance for general aviation aircraft CMl tiltrotor aircraft - A comparison of five candidale [AIAA PAPER 88-39551 p 172 A89-18125 The Pointer - A revolutionary idea to improve RPV designs p 163 A89-18882 A simplified aircraft wllision avoidance system capabilities p163 A89-18881 The development of the v-22 Osprey armored [AIAA PAPER 88-39611 p 173 A89-18128 AIRCRAFT PILOTS energy-absorbingcrewseat assembly Use of the Terminal Area Simulation System (TASS) Introduction 01 Pilot’s Operational Workload Evaluation p 155 A89-18883 to study microburst wind shears p 197 N89-14899 ResearchSimulator, POWERS, in Aeromedical Laboratory. JASDF p 183 A89-19876 Development and qualification testing, teaming for the AIRCRAFT HYDRAULICSYSTEMS V-22 multi-service aircraft system p 165 A89-18928 Designing hydraulic SyStems for survivability AIRCRAFT PRODUCTION New design, production tools will play key role in 8-2 Carbonlcarbon composite materials for aircraft brakes p 161 A89-17624 p 165 A89-19427 AIRCRAFT INDUSTRY cost p 161 A89-18350 Terminal area forecasts: Fiscal years 1988-2000 Automated wire preparation system The development and application 01 software quality [AD-A1980791 p 156 N89-13419 p 189 A89-t8895 indicators [AIM PAPER 8839481 p2Ot A89-19860 AIRCRAFT INSTRUMENTS AIRCRAFT RELIABILITY Interfacing sensor assemblies with windowless cockpit MAFT - An architecture lor reliable fly-by-wre flight General aviation cost effectiveness displays p 187 A89-17979 p 204 A89-20136 control _-- Multicomputer Architecture lor Fault Design of a certifiable primary on-board aircraft weight Tolerance New design procedures applied to landing War and balance system [AIM PAPER 88-39021 p 180 A89-18110 development p 167 A89-20138 [AIAA PAPER 88-39191 p 171 A89-18096 A’new’ philosophy of slructural reliability. fail safeversus Zonal grid generation method for complex Application of AI technology to time-critical functions safe life p 188 A89-18852 configurations p 201 A89-20139 [AIM PAPER 88-40301 p 174 A89-18190 Achieving reliability and maintainability goals with a Optlmizawn of aigorithms for data przcassing in radar Project lor an advanced regional transport aircraft composite main rotor blade p 188 A89-18892 [DGLR PAPER 874791 p 167 A89-20236 altimeters with electronic stabilization of the radiation Comparison of FAA DO-178A and WD-STD2167A Progress towards a commercial aircraft design expert pattern p 174 A89-18401 approaches to software certification Ground simulation lor airborne equipment system [AIAA PAPER 88-40441 p 142 A89-19864 [DGLR PAPER 87-1201 p 167 A89-20237 p 188 A89-18741 AIRCRAFT SAFETY The X-planes: X-1 to X-31 (2nd revised and enlarged Tiltrotor evolution leads to ASW revolution _-- Results of the in-service evaluation of the traffic alert edition) --_ Book p 205 A89-20251 antisubmarine warlare p 142 A89-18862 Transonic wing design using inverse methods in and collision avoidance system industry prototype Holomebics - An information lranslormalion [AIAA PAPER 88-39151 p 171 A89-18092 curvilinear coordinates p 151 A89-20316 methodology p 200 A89-18922 V-22 Osprey enabling technologies A ‘new’ philosophy of slructural reliability. fail safeversus AIRCRAFT UNDING safe life p 188 A89-18852 p 143 A8920744 Modelling of ground effects on aircraft --- landing The general NIB01 birds colliding against aeroplanes The V-22 - ’Am I gonna like it” p 167 A89-20745 ~esr-r~n~ayinteractbns p 166 A89-19559 The effects of nonlinear damping on the large deflection and anticollision measures p 155 A89-19810 Counteracting sidewind control System for aircraft response of structures subjected to random excitation AIRCRAFT SPECIFICATIONS landing p 181 A89-19800 p 193 N89-13796 8-2 bomber rolls out p 166 A89-19675 A walk along interlaces ___ aeroelasticity Precision approach radars Twenthe and Volkel AIRCRAFT STABILITY [ B8817M)8] p 154 N89-14223 (Netherlands). Mukipath propagation problems Identification of unstable flight-mechanical systems A unilied approach to vehicle design, control, and flight [ FEL-1988-151 p 193 N89-14372 using an output error method p 181 A89-19661 path optimization p 188 N89-14231 AIRCRAFT MAINTENANCE An example of the behavior of an aircraft with

AIRCRAFT DETECTION Faun detection and isolation for reconfigurable flight accumulated ice ~ Latent instability p 181 A89-20170 Multiple sample polygonal correlation algorithm for the control systems Coupled llow, thermal, and structural analysis of determination of around emitter location [AIAA PAPER 88-38601 p 170 A89-18058 aerodynamically healed panels p 181 A89-20322 [AIAA PAPER 88.39871 p 158 A89-18145 cantrat marnrenance cvrrq~tsi%,Sa= - A bo!d z!ep Applirntinn at transient aerodvnamics to the structural AIRCRAFT ENGINES forward on the 747-400 nonlinear flutter problem p 182 A89-20323 PM AI alloys - Hot prospects for aerospace [AMPAPER 88-40391 p 171 A89-18097 A unified approach to vehicle design. control. and night applications p 185 A89-17622 US Army aircraft combat maintenancelbattle damage path optimization p 188 N89-14231 Functional augmentation of digital engine wntrollers to repair program p 142 A89-18860 optimization01 slender wings for center-of-pressureshift implement an integrated testability concept due to change in Mach number p 154 NW-14897 AH-64A Contractor Logistic Support ~ The COntractors’ [AIM PAPER 88-39531 p 176 A89-18124 perspective p 142 A89-18869 AIRCRAFT STRUCTURES Optimization of mistuned blade rotor for controlling A study of contact interaction in aircraft structural Corrosion and corrosion control of selected field elements p 188 A89-18644 flutter p 176 A89-19793 problems p 162 A89-18870 Effect of blade misluning and blade-disk on cascade Nondestructive testing of composite aircraft structures Achieving reliabihty and maintainability goals with a flutter boundaries p 176 A89-19803 with infrared and shearographic imaging technologies composite main rotor blade p 189 A89-18892 Development 01 ram propulsion for flight vehicles p 189 A89-18891 [DGLR PAPER 87-101 ] p 176 A89-20240 The nature of the aircraft component failure process: Six degree of freedom crew isolation design, bench test An empirical look at tolerances in setting icing test A wofking note and flight test p 163 A89-18896 conditions with particular application lo icing similitude [ AD-A1979791 p 169 N89-14234 Nonlinear stability analysis for helicopter ground [AD-A198941] p 156 N89-13418 Expert systems in higher echelon maintenance resonance p166 A89-19790 Optical fire detector testing in the aircraft engine nacelle activities p 202 N89-14761 Selection 01 the optimal lighter-than-air gas for airship fire test simulator AIRCRAFT MANEUVERS and a scheme of double-layer struclural design [ AD-A1979741 p 168 N89-13427 A note on the aircraft minimum-time turns p 166 A89-19809 Aviation fuel lubricity evaluation p 182 A89-20638 COCOMAT. a CAE system lor composite structures [ADA1981971 p 177 N89-13434 Calculation of the steadily periodic and gust responses design ___ for aircraft p 166 A89-19981 Fire extinguishingagent evaluation in the Aircraft Engine 01 a hingeless rotor helicopter using two-dimensional time Evaluation of aluminum-lithium alloys in Nacelle Fire Test Simulator (AENFTS) domain unsteady aerodynamics p 182 N89-14240 compression-stiffeneed aircraft structures p 191 A89-20315 [AD-A198523] p 157 N89-14227 The poststall nonlinear dynamics and control of an F-18: Engines for Mini-RPV XM-1A A prelimiray investigation p 169 N89-14922 Design studies of primary aircraft structures in ARALL laminates p 167 A89-20318 [AD-A198336] p 178 N89-14236 AIRCRAFT MODELS AIRCRAFT EQUIPMENT A Comparison of numerical methods for the prediction Evolution of the ACAP crash energy management of two-dimensional heal transfer in an electrothermal Sharing the protection of aircraft electronic systems system p 164 A89-18923 against the effects of high-level electromsgnetic deicer pad environments between traditional protection and system Dynamic tirelsoil contact surface interaction model for [NASA-CR-4202] p 175 N89-13429 aircraft ground operations p 155 A89-20320 architecture Materials and slructures for hypersonic vehicles [AIAA PAPER 88-39171 p 187 A89-18094 AIRCRAFT NOISE [NASA-TM-101501I p 186 N89-14264 Advanced lube system diagnostics for V-22 Influenceof a floor on sound transmissioninto an aircraft Efficient load measurements using singular value p 190 A89-18907 fuselage model p 166 A89-20135 decomposition Concept and flight testing of a modern longitudinal NASAIAHS rotorcraft noise reduction program - [ NASA-CR-1846141 p 202 N89-14795 motion regulator using an invem model McDonnell Douglas Helicopter Company AIRCRAFT SURVIVABILITY [DGLR PAPER 87-1211 p 181 A8920238 accomplishments p 143 A89-20747 Designing hydraulic systems for survivability Fabrication and testing of lightweight hydraulic system Detaileddesign specification for a prototype Assessment p 161 A89-17624 simulator hardware. Phase 2 Addendum System for Aircraft Noise (ASAN) Bell ACAP full-scale aircraft crash test and KRASH [ADA1985241 p 184 N89-14243 [ AD-A1979361 p 204 N89-14818 correlation p 164 A89-18920 A-3 AIRCRAFT TIRES SUBJECT INDEX

AIRCRAFT TIRES The relationship between the aerodynamic AUTOMATIC FLIGHT CONTROL Dynamic tirelsoil contact surface interaction model for Characteristics of double-delta wings and vortices with Guidance and Flight Director system for the V-22 aircraft ground operations p 155 A89-20320 sideslips at high angles of attack p 148 A89-19801 Tiltrotor AIRFIEW SURFACE MOVEMENTS Flow unsteadiness considerations in high-alpha tasting [AIM PAPER 88-3921] p 179 A89-18098 Dynamic tirelsoil contact surface interaction model for p 151 A89-20319 AUTOMATIC TEST EQUIPMENT aircraft ground operations p 155 A89-20320 Dynamic stall computations using a zonal Navier-Stokes ATE hardware diagnostics, fault detection, and fault AIRFOIL OSCILLATIONS model isolation tool (Self-test adapter) p 197 A89.18015 A unified theoreticaltompltationalapproach for viscous [ AD-A1979421 p 194 N89-14397 Integrated diagnosbc concepts for advanced technology unsteady rotor aerodynamics p 146 A89-18917 The poststall nonlinear dynamics and control of an F-18: rotorcraft p 141 A89-18023 Experimental study on unsteady aerodynamic A preliminary investigation p 169 N89-14922 An overview of SEDACS - A state of the art TRDlTPS characteristics of an oscillating cascade with tip ANNULAR FLOW environment p 198 A89-18030 clearance p 148 A89-19927 The role of testability in the integrated diagnostic LDV measurements in an annular combustor model Dynamic stall computations using a zonal Naviar-Stokes process [NASA-CR-182207] p 192 N89-13755 model [AIM PAPER 88-38581 p 198 A89-18056 ANTISUBMARINE WARFARE AIRCRAFT [ADA1979421 p 194 N89-14397 SOAR ~ A high productivity software engineering AIRFOIL PROFILES Tiltrotor evolution leads to ASW revolution --. environment for embedded systems -_- System Design Coupling linearized far-fmld boundary conditions with antisubmarine warfare p 142 A89-18862 Automation Resources nonlinear near-fieldsolutions in transonic flow ARCHITECTURE (COMPUTERS) [AIAA PAPER 88.38651 p 198 A89-18062 [ADA1987211 p 153 N89-13405 Hybrid architecture of field-tested diagnostic expert Avionics failure propagation analysis tool AIRFOILS system p 198 A89-18034 [AIAA PAPER 88-38681 p 198 A89-18065 Study the aerodynamics characteristics of airfoil on MAFT . An architecture for reliable fly-by-wire flight A simulation-basedfault injection experiment to evaluate vector processors control .__Multicomputer Architecture for Fault self-test diagnostics for a fault-tolerant computer [IAF PAPER ST-88-09] p 143 A89-17874 Tolerance [AIAA PAPER 88-38971 p 198 A89-18083 Contributions to the theory of sound production by [AIM PAPER 88-39021 p 180 A89-18110 Automated fatigue crack growth measurement vortex-airfoil interaction, with application to vortices with An automated methodology for partitioning software [ AD-A1986421 p 195 N89-14466 finite axial velocity defect p 203 A89-19672 functions in a distributed avionics architecture On-board expert diagnostics for an avionics Further comparisons of interactive bwndary-layer and [AIAA PAPER 88-39711 p 199 A89-18137 subsystem p 202 N89-14758 thin-layer Navier-Stokes procedures p 149 A89-20137 A fault tolerant integrated avionics computer system Avionics fault tree analysis and artificial intelligence for Rotating air scoop as airfoil boundary-layer control [AIAA PAPER 88-40411 p 173 A89-18165 future aircraft maintenance p 202 N89-14760 p 150 A89-20149 Terminal information for data link AUTOMATIC TRAFFIC ADVISORY AND RESOLUTION Predictions of airfoil aerodynamic performance [AIAA PAPER 8840001 p 159 A89-18181 Results of the in-service evaluation of the traffic alert degradation due to icing Advanced Apache architecture and collision avoidance system industry prototype [ NASA-TM-1014341 p 153 N89-13412 [AIAA PAPER 88.39281 p 174 A89-18188 [AIAA PAPER 88-39151 p 171 A89-18092 Development of thermomechanical life prediction Vehicle management system architectural AUTOMATION models for thermal banier coatings p 186 N89-13643 considerations An automated method for forecasting the probability of Management and control of unsteady and turbulent [AIM PAPER 88-38751 p 174 A89-18189 clear air turbulence p 196 A89-18554 flows Architecture of an optimal navigation system integrating Automated wire preparation system [AD-A198091] p 192 N89-13751 GPS p 160 A89-18751 p 189 A89-18895 The effects of inlet turbulence and rotorlstator A parallel architecture for a real-time blade element AVIATION METEOROLOGY interactions on the aerodynamics and heat transfer of a rotorcraft simulation p 201 A89-19560 ARival-time guidance in variable winds large-scale rotating turbine model. volume 1 AREA NAVIGATION [AIAA PAPER 88-40251 p 159 A89-18176 [NASA-CR-4079] p 192 N89-13756 Recent studies of MLS application AVIONICS Two-dimensional aerodynamic characteristics of the [AIAA PAPER 88-39161 p 157 A89-18093 Universal Ada Test Language (UATL) to support OLSITAAT airfoil ARTIFICIAL INTELLIGENCE real-time softwarelsystem integration and [NASA-TM-89435] p 154 N89-14216 AI applications to tactical decision aids factorylmaintenancefault isolation p 197 A89-18009 Numerical grid generation and potential airfoil analysis [AIM PAPER 8840271 p 200 A89-18178 Avionics testing in the military bare-base environment and design CEPS An artificial intelligence approach to avionics p 141 A89-18011 [AD-A197972] p 154 N89-14219 maintenance p 201 N89-14749 The enemy is FA, CND. and RTOK High lift, low pitching mament airfoils Awonics fault tree analysis and artificial intelligence for p 141 A89-18025 [NASA-CASE-LAR-13215-1] p 154 N89-14224 future aircraft maintenance p 202 N89-14760 An overview of SEDACS - A state of the art TRDlTPS AIRFRAME MATERIALS ASPECT RATIO environment p 198 A89-18030 COCOMAT. a CAE system for composite structures Winglets on low-aspect-ratio wings AIAAlIEEE Digital Avionics Systems Conference. 8th. design --- for aircraft p 166 A89-19981 p 149 A89-20142 San Jose, CA. Oct. 17-20, 1988, Technical Papers. Parts AIRFRAMES ASTRlONlCS 1 a2 p 169 A89-18051 Analytical prediction and flight test evaluation of Bell AIAAIIEEE Digital Avionics Systems Conference. 8th. Modular avionics systems studies ACAP helicopter cabin noise --- Advanced Composite San Jose, CA. Oct. 17-20, 1988, Technical Papers. Parts [AIM PAPER 88-38501 p 169 A89-18052 Airframe Program p 164 A89-18911 1 a2 p 169 A89-18051 Modular avionics systems architecture (MASA) - Seeds AIRPORTS ASTRONAUTICS of destruction or seeds of progress? Terminal information for data link Yearbook 1987 II; DGLR. Annual Meeting. Berlin, [AIAA PAPER 88-3851] p 141 A89-18053 Federal Republic of Germany, Oct. 5-7. 1987. Reports [AIAA PAPER 88-40001 p 159 A89-18181 Faults with nonstationary observability are limiting p 142 A89-20226 Teleport as a concentration point for domestic and avionics RBM ATMOSPHERICBOUNDARYLAYER international traffic p 190 A89-20114 [AIAA PAPER 88-38521 p 169 A89-18054 Method for simulating turbulence characteristics for wind A microcomputer pollution model for civilian airports and Advanced avionics interconnection environment in wind tunnel p 183 A89-19884 air force bases, model description ATMOSPHERIC CIRCULATION [AIM PAPER 88-38561 p 170 A89-18055 [ADA199OO31 p 197 N89-14616 Numerical simulations of an isolated microburst. I . The role of testability in the integrated diagnostic Use of the Terminal Area Simulation System (TASS) Dynamics and structure p 196 A89-20265 process to study microburst wind shears p 197 N89-14899 ATMOSPHERIC MODELS [AIAA PAPER 88-38581 p 198 A89-18056 AIRSHIPS Numerical simulations of an isolated microburst. I . A methodology for the design of hierarchically testable The unused strategic tool - Ttm airship Dynamics and structure p 196 A8920265 and maintainable digital systems p 161 A89-18752 Atmospheric photochemical modeling of turbine engine [AIAA PAPER 88-38591 p 170 A89-18057 Selection of the optimal lighter-than-air gas for airship fuels and exhausts. Computer model development, volume A structured approach to system design and a scheme of double-layer structural design 2 [AIAA PAPER 88-38671 p 198 A89-18064 p 166 A89-19809 [ADA1986911 p 196 N89-13833 Avionics failure propagation analysis tool ALGORITHMS ATMOSPHERIC REFRACTION [AIAA PAPER 88-38681 p198 A89-18065 Zonal grid generation method for complex Analysis of temperature and velocity microturbulence Optimal integration of inertial sensor functions for configurations p201 A89-20139 parameters from aircraft data and relationship to flightcontrol and avionics Comparison of the general dynamics ground clobber atmospheric refractive index structure [AIAA PAPER 88-38781 p 170 A89-18072 algorithm with the GCAS and laws algorithms [ AD-A1965421 p 196 N89-13854 AlTACK AIRCRAFT A simulation-basedfault injection experiment to evaluate [ADA19847Q] p 157 N89-14226 self-test diagnostics for a fault-tolerant computer Determination of control laws for a single pilot, attack ALUMINUM ALLOYS [AIAA PAPER 88-38971 p 198 A89-18083 helicopter P 180 A89-18904 PM AI alloys - Hot prospects for aerospace Design and validation of the IFTAS fault-tolerant clock applications p 185 A89-17622 AUDIO SIGNALS Dgital audio applications in business and regional airline _-- Integrated Fault-Tolerant Avionics System Environmentally induced cracking in aluminum aircraft [AIM PAPER 88-38991 p 170 A89-18085 p 185 A89-18925 [AIM PAPER 88-39581 p 157 A89-18127 Ada in avionics - Beyond validation Evaluation of aluminum-lithium alloys in AUTOMATIC CONTROL [AIAA PAPER 88-39071 p 199 A89-18087 compression-stifleneed aircraft smturas The impact of yaw axis control modes. flight directors A fault tolerant avionics multiprocessing system p 191 A89-20315 and automatic control coupling on decelerating IFR architecture supporting concurrent execution of Ada AMBIENT TEMPERATURE approaches for rotorcraft p 180 A89-18903 tasks An ice detection system foc helicopters Design of feedback control systems for unstable plants [AIAA PAPER 88-39081 p 199 A89-18088 [AIM PAPER 88-39491 p 172 A89-18120 with saturating actuators Sharing the protection of aircraft electronic systems ANGLE OF ATTACK [NASA-CR-183392] p 194 N89-14377 against the effects of high-level electromagnetic Calculation of hypersonic flow past the windward side A flight test design for studying airborne applications environments between traditional protection and system of a low-aspect-ratio wing at hgh angles of attack of air to grwnd duplex data link communications architecture 0144 A89-18357 p 195 N89-14924 [AIAA PAPER 88-39171 p 187 A89-18094 A-4 SUBJECT INDEX CARTESIAN COORDINATES

On the effectiveness of multiversion software in daital Measurements in the field of a spark excited BODIES OF REVOLUTION avionics compressible axisymmetric jet p 203 A89-18948 Low-speed pressure distribution on axisymmetric [AIAA PAPER 88-39031 p 199 A89-18111 elliptic-nosed bodies p 149 A89-20147 Impact of device level faults in a digital avionic BOEING AIRCRAFT pfocessor B Boeing Model 360 Advanced Technology Helicopter . [AIM PAPER 8839041 p 172 A89-18112 Design features and flight test update 6-1 Application of digital technology to aircraft utili AIRCRAFT p 165 A89-18935 CEPS An artificial intelligence approach to avionics systems BOEING 747 AIRCRAFT [AIM PAPER 88-38721 p 180 A89-18114 maintenance p 201 N89-14749 The 6-16 central integrated test system expert Central maintenance computer system - A bold step Use of the GALA and PALAS tools to enhance the forward on the 747-400 parameter system p 202 N89-14763 development of avionic software [AIAA PAPER 88-40391 p 171 A89-18097 [AIAA PAPER 88-39431 p 199 A89-18115 BALANCE Design of a certifiable primary on-board aircraft weight Boeing 747-400 - Flight test p 161 A89-18349 Reflections on avionic integration BOMBER AIRCRAFT [AIAA PAPER 88-39501 p 172 A89-18121 and balance system New design, production tools will play key role in 8-2 Development and applications of an avionics research [AlAA PAPER 88-39191 p 171 A89-18096 cost p 161 A89-18350 testbed The 13-inch magnetic suspension and balance system [AIM PAPER 88-39521 p 172 A89-18123 wind tunnel 8-2 bomber rolls out p 166 A89-19675 [NASA-TM-4090] p 184 N89-14241 Cockpit management for regional airlines and business BOUNDARIES BALLOON FLIGHT aircraft as applied in the Beech Starship Coupling linearized far-field boundary conditions with [AIAA PAPER 8849571 p 173 A89-18126 New application possibilities for balloon-borne case nonlinear near-field solutions in transonic flow studies MIKROBA (Microgravity by balloons) Commercial avionics applications of flat panel displays - [AD-A198721] p 153 N89-13405 [AIAA PAPER 88-39621 p 173 A89-18129 [DGLR PAPER 87-0691 p 184 A89-20233 BOUNDARYLAYERCONTROL Stereo 3-D and non-stereo presentations of a BARRIER LAYERS Rotating air scoop as airfoil boundary-layer control computer-generated pictorial primary flight display with Thermal Barrier Coatings. Abstracts and figures p 150 A89-20149 pathway augmentation [ NASA-CP-100191 p 185 N89-13642 BOUNDARYLAYEREQUATIONS [AIAA PAPER 88-39651 p 173 A89-18132 Development of thermomechanical life prediction Further comparisons of interactive boundary-layer and One million pixel full color liquid crystal display for models for thermal barrier coatings p 186 N89-13643 thin-layer Navier-Stokes procedures p 149 A89-20137 High time service evaluation of thermal barrier coatings avionics applications BOUNDARY LAYER FLOW on the Rolls-Royce RB211 engine D 186 N89-13660 [AIM PAPER 88-39671 p 173 A89-18134 Convective heat transfer in a boundary layer behind a An automated methodology for partitioning software BEAMS (SUPPORTS) Matrix analysis method for composite flexbeam shock wave propagating along a flat plate with a sharp functions in a distributed avionics architecture leading edge. A calculation method and a comparison [AIAA PAPER 88-39711 p 199 A89-18137 p 190 A89-18926 BEARINGLESS ROTORS with experimental data p 144 A89-18546 A parallel modular signal processor Interactions between turbulent wakes and boundary [AIAA PAPER 88-39811 p 199 A89-18141 Bearinglessrotors and higher harmonic control modeling :si- RACAP p 162 ~a9-18876 layers p 150 A89-20182 Mode S data link applications research in the UK BOUNDARYLAYERSEPARATION [AIAA PAPER 88-39961 p 158 A89-18153 Design and fabrication of an advanced light rotor Improving the half-model technology in the Goettingen The high speed bus technology development program p 163 A89-18880 Optimal design of an advanced composite rotating transonic wind tunnel [AIAA PAPER 88-40051 p 187 A89-18158 [DGLR PAPER 87-0831 p 183 A8920234 An SAE high speed ring bus overview flexbeam p 189 A89-18884 [AIM PAPER 88-40081 p 187 A89-18159 Dynamic charactenstics of advanced bearingless rotors Moving wall effects in unsteady flow Inter-partition data integrity in the asynchronous DATAC at McDonnell Douglas Helicopter Company p 150 A89-20311 environment p 164 A89-18899 Management and control of unsteady and turbulent [AIM PAPER 88-40101 p 200 A89-18160 Testing and correlation on an advanced technology. flows The fiber optic data distribution network - A network bearingless rotor p 182 A89-18900 [AD-AI 98091] p 192 N89-13751 for next-generation avionics systems BEARINGS BOUNDARY LAYER TRANSITION [AIAA PAPER 88-401 11 p 188 A89-18161 Modal analysis of continuous rotor-bearing systems Detection of laminar-turbulent transition by infrared GaAs 32-bit single board computer p 188 A89-I8766 thermography p 143 A89-17147 [AIAA PAPER 88-40121 p200 A89-18162 BEECHCRAFT AIRCRAFT Characterization of boundary layer conditions in wind A MIL-STD-l'I5OA. single-boardcomputer for embedded Cockpit management for regional airlines and business tunnel tests through IR thermography imaging multiprocessor applications aircraft as applied in the Beech Starship p 147 A89-19167 [AIM PAPER 88-40151 p200 A89-18163 [AIAA PAPER 88-39571 p 173 A89-18126 Comment on 'Aeroelastic oscillations caused by A fault tolerant integrated avionics computer system BELL AIRCRAFT transitional boundary layers and their attenuation' [AIM PAPER 88-40411 p 173 A89-18165 Developments in dynamics methodology at Bell p 167 A89-20150 Ada executive for distributed avionics processing Helicopter Textron p 162 A89-18875 BUCKLING [AIAA PAPER 88-40421 p 200 A89-18166 Analyfical prediction and flight test evaluation of Bell Buckling characteristics of hypersonic aircraft wing Modeling mission reliability of advanced integrated ACAP helicopter cabin noise ... Advanced Composite tubular panels communication, navigation, identification avioncs -.. ----^. - .h" won .?O.f Airframe Program p 164 AUY-lUY11 lNH3A-I M-Of 1001 #, I"" I.""~.lll- systems Bell ACAP full-scale aircraft crash test and KRASH BUFFETING [AIAA PAPER 8840231 p 173 A89-18174 correlation p 164 A89-18920 Measurements of the buffet boundary of wings in Advanced Apache architecture transonic flow with hot-film method p 148 A89-19805 [AIM PAPER 88-39281 p 174 A89-18188 BENDING MOMENTS Application of AI technology to time-critical functions Matrix analysis method for composite flexbeam BUILDINGS Method for simulating turbulence characteristics for wind [AIM PAPER 88.40301 p 174 A89-18190 p 190 A89-18926 environment in wind tunnel p 183 A89-19884 Software development for large scale avionic integration BIRD-AIRCRAFT COLLISIONS programs p 200 A89-18864 The general rule of birds colliding against aeroplanes Airborne integrated monitoring system and anticollision measures p 155 A89-19810 p 174 A89-18868 BIT ERROR RATE C The development and application of software quality Irreducible error rate in aeronautical satellite channels indicators p 157 A89-17183 CABINS [AIAA PAPER 88-39461 p 201 A89-19860 BLADE-VORTEX INTERACTION Analytical prediction and flight lest evaluation of Bell High-speed data bus processing node A comparison of acoustic predictions with model rotor ACAP helicopter cabin noise -_.Advanced Composite [AIM PAPER 88-40091 p 201 A89-19861 test data from the NASA 14 x 22 ft wind tunnel Airframe Program p 164 A89-18911 Integrated CNI terminal software architecture p 203 A89-18913 CABLES [AIAA PAPER 88-40221 p 201 A89-19862 Tip-path-plane angle effects on rotor blade-vortex Reliability in fiber optic cable harness manufacturing Comparison of FAA DO-178A and DOD-STD-2167A interaction noise levels and directivity [AIAA PAPER 88-3931 1 p 187 A89-18105 approaches to software certification p 203 A89-18914 CALIBRATING [AIAA PAPER 88-40441 p 142 A89-19864 A unifii theoretical-computatial approach for viscous Theoretical derivation and calibration technique 01 a Aeronautical satellite networks p 160 A89-20117 unsteady rotor aerodynamics p 146 A89-18917 hemispherical-tipped,live-hole probe CEPS: An artificial intelligence approach to avionics [NASA-TM-4047I p 151 N89-13396 Helicopter free wake prediction of complex wake CANOPIES maintenance p 201 N89-14749 structures under Blade-Vortex Interaction operating On-board expert diagnostics lor an avionics Performance prediction analysis for fully deployed conditions p 146 A89-18918 subsystem p 202 N89-14758 parachute canopies p 155 A89-20314 Avbnics fault tree analysis and artificial intelligence for An analytical model for the prediction of MRlTR New solution method for steady-state canopy structural interaction noise main rotorltail rotor future aircraft maintenance p 202 N89-147M) .-- loads p 155 A89-20321 AXIAL FLOW p 165 A89-18931 CARBON FIBER REINFORCED PLASTICS Experimental investigation of propfan aeroelastic Contributions to the theory of sound production by Carbon fiber composites for supersonic technology response in off-axis flow with mistuning vortex-airfoil interaction, with application to vortices with [DGLR PAPER 87-1241 p 185 A89-20244 [AIAA PAPER 88-31531 p 175 A89-17941 finite axial velocity defect p 203 A89-19672 CARBON FIBERS AXISYMMETRIC BODIES BLUFF BODIES The quality of fibre reinforced thermoplastics Low-speed pressure distribution on axisymmetric Calculation of the unsteady aerodynamic characteristics mouldings p 196 NEB-13839 elliptic-nosed bodies p 149 A89-20147 of bodies in the case of separated flow CARBON-CARBON COMPOSITES AXISYMMETRIC FLOW p 144 A89-18355 Carbonlcarbon composite materials for aircraft brakes Recent developments in transonic flow computabon BLUNT BODIES p 165 A89-19427 p 145 A89-18749 Spatial marching techniques for approximate solutions CARTESIAN COORDINATES Computation of axisymmetric supersonic jet using space to the hypersonic blunt body problem Navier-Stokes calculations using Cartesian grids. I - marching technique p 145 A89-18750 p 143 A89-17460 Laminar flows p 150 A89-20180

A-5 CASCADE FLOW SUBJECT INDEX

CASCADE FLOW Cockpn management for regional aitiiies and business COMPLEX SYSTEMS Experimental study on unsteady aerodynamic aircraft as applii in the Beech Starship An apxoach to solving large reliability models characteristics of an osdllating caacade with tip [AIM PAPER 8839571 p173 A8918126 [AIM PAPER 8839051 p 199 A89-18088 clearance p 148 A89-19927 An advanced facility for cockpit studiis COMPLEX VARIABLES CAVITATION FLOW [AIM PAPER 88-39663 p 182 A89-18133 Solution and sensitivity analysis of a complex Computational analysis of unsteady supersonic cavity Air tram control (ATC) and airlgrwnd diiital transcendental eigenproblem with pairs of real flows driven by thick shear byers p 145 A89-18803 communications - Demonstration and evaluation eigemalues CAVITIES [AIM PAPER 88-39981 p158 A89-18154 [NASACR-182241I p 193 N89-13819 Passive venting technique for shallow cavities Human factors impact on the V-22 Osprey cockpit COMPONENT RELIABILITY [ NASA-CASE-LAR-14031 -11 p 168 N89-14232 development - An overview p 174 A89-18865 Reliability in fiber optic cable harness manufacturing Passive venting technique for shallow cavities [AIM PAPER 88-3931 p 187 A89-18105 Six degree of freedom crew isolation design. bench test I [NASA-CASE-LAR-13875-11 p 169 N89-14233 Grwnd simulation for airborne equipment and fliht test p 163 A89-18896 CENTER OF PRESSURE p 188 A89-18741 Optimizationof slenderwings for centerof-pressureshii Sound attenuation and speech transmission qualiity of The nature of the aircraft component failure process: due to change in Mach number p 154 N89-14897 five tvpes of headsets A working note CENTRAL PROCESSING UNITS [IZF-1987-23] p 193 N89-14373 [AD-A1979791 p 169 N89-14234 Hih-speed data bus processing node CODING COMPOSITE MATERIALS [AIM PAPER 8840091 p 201 A89-19861 Modern wing flutter analysis by computational fluid Lihtning simulation test technique evaluation CENTRIFUGAL COMPRESSORS dynamics methods p 191 A89-20146 [DOT/FM/CT-87/38] p 156 N89-13415 Duel centrifugal compressors - The helicopter solution COLD SURFACES The Center of Excellence in Rotary Technology at to sand and ice ingesti p176 A8918908 Convective heat transfer in a boundary layer behind a Rensselaer Polytechnic Institute Early jet engines and the transition from centrifugal to shock wave propagating along a flat plate with a sharp [AD-A198964] p 168 N89-13426 axial compre&rs: A case study in technological change leading edge - A calculation method and a comparison COMPOSITE STRUCTURES IADA1987751 D 177 N89-13430 with expefimental data p 144 A89-18546 Design, analysis, and test of composite fuel tank pods CERAMIC COATINGS COLLISION AVOIDANCE for the CH46E helicopter p163 A89-18885 Chemical vapor depositkm of oxidation resistant HfB2 Results of the ireservice evaluation of the trahk alert Nondestructive testing of composite aircraft structures + Sic composite coatings p 185 A89-19481 and collision avoidance system industry prototype with infrared and shearographic imaging technobps CERAMIC MATRIX COMPOSITES [AIM PAPER 88-39151 p 171 A89-18092 p 189 A89-18891 Chemical vapor deposition of oxidation resistant HfB2 Simulation evaluation of helicopter Terrain Achieving reliability and maintainability goals with a + Sicomposite coatings p185 A8819481 Follawing/Terrain Avoidance concepts composite main rotor blade p 189 A89-18892 A review of failure models for unidirectional ceramic [AIM PAPER 88-39241 p 180 A89-18101 Application of damage tolerance methodology to matrix composites under monotonic loads A simplified aircraft collision avoidance system heliter dynamic components using the example of a [NASA-TM-101 421 ] p 195 N89-14470 [AIM PAPER 88-39611 p 173 A89-18128 main rotor pitch link for the AH-1S helicopter CERTIFICATION Data link organization in Mode S secondary surveillance p 164 A89-18921 Dolphin eats snow -__helicopter engine surge during radar systems - Operational compatibility with other Mode Matrix analysis method for composite flexbeam flight in snowfall p 155 ABS18910 S systems pl90 A89-18926 Cn-rS HELICOPTER [AIM PAPER 8840031 p 159 A89-18157 COCOMAT. a CAE system for composite structures Design. analysis, and test of composite fuel tank pods Developmentof the Traffic Alert and Collision Avoidance deaign - for aircraft p 166 A89-19981 for the CH46E helicopter p 163 A89-18885 System 111 (TCAS Ill) Processing composite finite element model with CH-47 HELICOPTER [AIM PAPER 88-40021 p 159 A89-18182 CADCOMP .--for aircraft structures p 186 A89-19982

Development and flight test of a precision autohwer TCAS 111 ~ Bringing operational compatibility to airborne Introduction of new technologies in the structural area capabdity for tactical rotorcraft p 165 A89-18934 collision avoidance from the viewpoint of IABG CHANNELS (DATA TRANSMISSION) [AIAA PAPER 8840041 p 159 A89-18183 [DGLR PAPER 87-1071 p 143 A8920242 The high speed bus techdogy development program The general rule of birds colliding against aeroplanes Strength of dynamically loaded force introductbn for [AIM PAPER 88-40051 p 187 A89-18158 and anticollision measures p 155 A89-19810 fiber-reinforced rotors An SA€ high speed ring bus overview Comparison of the general dynamics ground clobber [DGLR PAPER 87-1081 p 185 A89-20243 [AIM PAPER 88-40081 p 187 A89-18159 algorithm with the GCAS and laws algorithms A comparison of numerical methods for the prediin The fiber optic data disbibuihn network . A network [ADA1984791 p 157 N89-14226 of two-dimensional heat transfer in an electrothermal for nextgeneration avionlcs systems COMBAT deiipad [AIM PAPER 88-401 11 p188 A8918161 Air combat tactics for the evaluation of rotorcraft [ NASA-CR-4202J p 175 N89-13429 CHECKOUT characteristics in the low air war of 2010 COMPRESSIBILITY EFFECTS Airborne integrated monitoring system p 142 A89-18859 Validation of approximate indicia1aerodynamic functions p 174 A89-18868 US Army aircraft combat maintenance/battle damage for two-dimensional subsonic flow p 149 A89-20140 CIRCUIT PROTECTION repair program p 142 A89-18860 COMPRESSIBLE FLOW Sharing the protecmn of aircraft electronic systems Air-t+air combat helicopter development The measurement and prediction of rolordynamk forces against the effects of high-level electromagnetic p 165 A89-18929 for labyrinth seals environments between traditional protection and system COMBUSTION CHAMBERS [ AD-A1971 851 p 192 N89-13784 architecture Selected papers on fundamental aspects of gas turbine COMPRESSION TESTS [AIM PAPER 88-39171 p 187 A8818094 combustion --- Book p 177 A89-20625 Evaluation of aluminum-lithium alloys in CIRCULATION CONTROL AIRFOILS LDV measurements in an annular combustor model compressiowstienwd aircraft structures Static aeroelastic characterisks of circulation control [NASA-CR-182207] p 192 N89-13755 p 191 A89-20315 wiw p167 A89-20144 COMMERCIAL AIRCRAFT COMPRESSOR BLADES cims An air data inertial reference system for future Measurement and analysis of unsteady flow structures Method for simulating turbulence characteristics for wind commercial airplanes in rotor blade wakes p 147 A89-18946 environment in wind tunnel p 183 A89-19884 [AIM PAPER 88-39181 p 171 A89-18095 COMPRESSOR EFFICIENCY CIVIL AVIATION Commercial jet transport fly-by-wire architecture Advanced wre technology: Key to subsonic propulsion special committee on Mure air navigation systems considerations benefits (FANS) p 160 A89-18754 [AIM PAPER 88-39001 . p 180 A89-18108 [NASA-TM-101 4201 p 178 N89-14237 Low-nbil navigation concepts p 184 A89-19870 Cockpit management for regional airlines and business COMPUTATIONAL FLUID DYNAMICS General aviation cost effectiveness aircraft as applied in the Beech Starship Study the aerodynamics characteristics of airfoil on p 204 A89-20136 [AIM PAPER 88.39571 p 173 A89-18126 vector processors Aircraft accident reports: BM format. US civil and LXgltal audio applications in business and regional airline [IAF PAPER ST-88-091 p 143 A8917874 foreign aviation, iswe number 4 of 1987 accidents aircraft Self-similar problem of the separated Row of an ideal [P888-916908] p 155 N89-13413 [AIM PAPER 88-39581 P157 A89-18127 fluid past an expanding plate p 144 A89-18669 CLEAR AIR TURBULENCE Commercial avionics applications of flat panel displays Mathematical modeling of laminar and turbulent An automated method for forecasting the probability of [AIM PAPER 88-39621 P 173 A89-18129 supersonic flow past convex-concave bodiis clear air turbulence p 196 A89-18554 Sizing up the 146-300 - new commuter aircraft by British p144 A89-18671 CLOCKS AeCospace p161 A89-18346 Recent developments in transonic flow computation Design and validation of the IFTAS faun-tolerant ckck Civil tiltrotor aircraft - A comparison of five candidate p 145 A89-18749 Integrated Fault-TolerantAvionics System -- designs p 163 A89-18882 Computation of axisymmetric supersonic jet using space [AIM PAPER 88-38991 p 170 A89-18085 Progress towards a commercial aircraft design expert marching technique p 145 A89-18750 CLOUD PHYSICS system Use of the Terminal Area Simulation System (TASS) Computational analysis of unsteady supersonic cavity [DGLR PAPER 87-1201 p 167 A89-20237 flows driven by thick layers p 145 A89-18803 to study microburst wind shean, p 197 N89-14899 COMMUNICATION NETWORKS shear CLOUDS (MEl€OROLOGv) The future of aeromobile diiital communications lmpwements to transonic flowfield calculations p146 A89-18915 Use of the Terminal Area Simulation System (TASS) [AIAA PAPER 88-40011 P 158 A89-18156 to study microburs1wind shean, p 197 N89-14899 COMMUTER AIRCRAFT An evaluation of a Navier-Stokes code for calculations COCKPIT SIMULATORS Sizing up the 146300 .-new commuter aircraft by British 01 retreating blade stall on a helicopter rotor Introduction of Pilot's operahl Workload Evaluation Aeroepece p 161 A89-18346 p 146 A8918916 Research Simulator, POWERS, in Aeromedical Laboratory, COMPARTMENTS Helicopter free wake prediction of complex wake JASDF p 183 A89-19876 OpW fire detector testing in the aircraft engine nacelle structures under Blade-Vortex Interaction operating COCKPITS fire test simulator conditions p 146 A89-18918 Intafacing sensor assemblies with windowless cockpit [ AD-A1979741 p 168 N89-13427 Analysis of a fighter type aircraft confiurabn with the diaplays p 187 A89-17979 Fire extinguishingagent evaluation in the Aircraft Engine HlSSS panel method at subsonic and supersonic Sterermwpic 3-D &plays for cockpits Nacelle Fire Test Simulator (AENFTS) speeds [AIM PAPER 88-36871 p170 A89-18080 [ADA1985231 D 157 N89-14227 [DGLR PAPER 87-0851 p 147 A8919660

A-6 SUBJECT INDEX CONTROL SYSTEMS DESIGN

Multigrid acceleration of a relaxation procedure for the Use of the GALA and PALAS tools to enhance the New solution method for steady-state canopy structural reduced Navier-Stokes equations p 148 A89-19904 development of avionic software loads p 155 A89-20321 Interactive and large-domain solutions of higher-order [AIM PAPER 88-39431 p 199 A89-18115 Predictions of airfoil aerodynamic performance viscous-flow equations p 148 A89-19905 Stereo 3-D and non-stereo presentations of a degradation due to icing Full-potential integral solution for transonic flows with computer-generated pictorial primary flight display with [NASA-TM-101 4341 p 153 N89-13412 and without embedded Euler domains pathway augmentation Atmospheric photochemical modeling of turbine engine p 148 A89-19908 [AIAA PAPER 88-39651 p 173 A89-18132 fuels and exhausts. Computer model development,volume Plenum chamber effect on wind-tunnel resonance by COMPUTER PROGRAM INTEGRITY 1 the finite-element method p 190 A89-19909 Developing error-tree software p 201 A89-19679 [AD-A198690] p 196 N89-13832 Navier-Stokes calculations of hovering rotor flowtields COMPUTER PROGRAMS Atmospheric photochemical modeling of turbine engine [AIAA PAPER 87-26291 p 149 A89-20133 Modern wing flutter analysts by computational fluid fuels and exhausts. Computer model development,volume Transonic Navier-Stokes solutions for a fighter-like dynamics methods p 191 A8940146 2 configuration p 149 A8920134 Wall adjustment strategy software for use with the NASA [AD-A198691] p 196 N89-13833 Modern wing flutter analysis by computational fluid Laogley 0.3-meter transonic cryogenic tunnel adaptive wall A microcomputerpollutin model for civilian airports and dynamics methods p 191 A89-20146 test section air force bases. model descriptum Computation of rotational transonic flows using a [ NASA-CR-1816941 p 151 N89-13400 [ AD-A1990031 p 197 N89-14616 decomposition method p 150 A89-20179 Development of three-dimensional code for the analysis Numerical simulation and comparison of Navier-Stokes calculations using Cartesian grids. I - of jet mixing problem. Part 1: Laminar solution symmetricallsupercritical airfoils for the near tip region of Laminar flows p 150 A89-20180 [ NASA-CR-42001 p 152 N89-13401 a helicopter in forward flight Vortical wakes over a prolate spheroid Predictions of airfoil aerodynamic performance [ NASA-CR-42121 p 204 N89-14821 p 150 A89-20181 degradation due to icing CONCENTRATION (COMPOSITION) Time-iterative solutions of viscous supersonic nozzle [NASA-TM-101 4341 p 153 N89-13412 Three dimensional hazard zones p 195 A89-18259 flows p 150 A89-20184 Constitutive modeling for isotropic materials CONFERENCES Analysis of artificial dissipation models for the transonic [NASA-CR-174805] p 177 N89-13436 AIAAIIEEE Digital Avionics Systems Conference. 8th. full-potential equation p 191 A89-20188 LDV measurements in an annular combustor model San Jose. CA. Oct. 17-20, 1988. Technical Papers. Parts Developmentof three-dimensional code for the analysis I NASA-CR-1822071 p 192 N89-13755 182 p 169 A89-18051 of jet mixing problem. Part 1: Laminar solution Plotting component maps in the NavyINASA Engine AHS. Annual Forum, 44th. Washington. DC. June 16-18. [ NASA-CR-42001 p 152 N89-13401 Program (NNEP): A method and its usage 1988. Proceedings p 141 A89-18851 LDV measurements in an annular combustor model [ NASA-TM-1014331 p 178 N89-14239 Aerospace simulation Ill; Proceedings of the SCS [NASA-CR-182207] p 192 N89-13755 Detaileddesign specification for a prototype Assessment Multiconference. San Diego. CA, Feb. 3-5. 1988 The measurement and prediction of rotordynamicforces System for Aircraft Noise (ASAN) p 142 A89-19551 for labyrinth seals [AD-A197936] p 204 N89-14818 Yearbook 1987 II; DGLR. Annual Meeting. Berlin. [ADA1971851 p 192 N89-13784 Users' manual for the Langley high speed propeller noise Federal Republic of Germany. Oct. 5-7, 1987, Reports Numerical simulation and comparison of prediction program (DFP-ATP) p 142 A89-20226 symmetricallsupercritical airfoils for the near tip region of [NASA-CR-4208] p 204 N89-14820 Thermal Barrier Coatings. Abstracts and ligures a helicopter in forward flight COMPUTER SYSTEMS DESIGN [ NASA-CP-1OO! 9: p 185 N89-13642 [NASA-CR-4212] p204 N89-14821 SDAR - A high productivity software engineering CONFIGURATION MANAGEMENT Overlapping grids lor flow field calculations environment for embedded systems --- System Design Reconfigurable flight control: An opportunity for p 195 N89-14918 Automation Resources integrated diagnostics p 182 N89-14744 COMPUTATIONAL GEOMETRY [AIAA PAPER 88.38651 p 198 A89-18062 CONTACTLOADS Surface grid generation for complex three-dimensional Design and validation of the IFTAS fault-tolerant clock A study of contact interaction in aircraft structural geometries --- Integrated Fault-Tolerant Avionics System elements p 188 A89-18644 [ NASA-TM-1010461 p 191 N89-13747 [AIAA PAPER 88-38991 p 170 A89-18085 CONTROL CONFIGURED VEHICLES COMPUTATIONAL GRIDS Impact of device level faults in a digital avionic The T-2 control configured vehicle development, Multigrid acceleration of a relaxation procedure for the processor integration and flight test reduced Navier-Stokes equations p 148 A89-19904 [AIAA PAPER 88.39041 p 172 A89-18112 [AIM PAPER 88-38821 p 179 A89-18076 Zonal grid generation method for complex A MIL-STD-1750A.single-board computer lor embedded CONTROL EQUIPMENT configurations p 201 A89-20139 multiprocessor applications Rotating air scoop as airfoil boundary-layer control Numerical grid generation and potential airfoil analysis [AIAA PAPER 88.40151 p200 A89-18163 p 150 A89-20149 and design Ada executive lor distributed avionics processing Concept and flight testing 01 a modern longitudinal [AD-A197972] p 154 N89-14219 [AIAA PAPER 88-40421 p 200 A89-18166 motion regulator using an inverse model Numerical simulation and cornparison of A fixed base data system for flight testing [DGLR PAPER 87-1211 p 181 A89-20238 symmetricallsupercritical airfoils for the near tip region of p 201 A89-18937 CONTROL SIMULATION a helicopter in forward flight Comparison of FAA W178A and GOD-STD-2167A Determination of control laws for a single pilot. attack [NASA-CR-4212] p 204 N89-14821 approaches to software certihcation helicopter p 180 A89-18904 Overlapping grids for flow field calculations (AIM PAPER 88-40441 p 142 A89-19864 X-29 validation methodology for simulation and flight p 195 N89-14918 Wall adjustment strategy software for use with the NASA control system p 181 A89-19557 COMPUTER AIDED DESIGN La:.g!ej 0.3 -&e: 5:c~cck cy%yGc tiinnel adaptive wall Raronfigirrnblefliaht control svstem Simulation Computer-aided engineering methods for successhil test Section p 181 A89-19558 VHSlC applition [NASA-CR-181694] p 151 N89-13400 CONTROL STABILITY [AIAA PAPER 88-40351 p 188 A89-18185 COMPUTER SYSTEMS PERFORMANCE Reduced conservative singular value analysis for New design. production tools will play key role in 8-2 Ada in avionics .Beyond validation robustness p 197 A89-17489 cost p 161 A89-18350 [AIM PAPER 88-39071 p 199 A89-18087 CONTROL SURFACES Tip loss and blade strike simulations using DYSCO Central maintenance computer system - A bold step A guide to classical flutter p 188 A89-18801 p 164 A89-18901 forward on the 747-400 CONTROL SYSTEMS DESIGN Dual centrifugal compressors - The helicopter solution [AIAA PAPER 88-40391 p 171 A89-18097 Designing hydraulic Systems for survivability to sand and ice ingestion p 176 A89-18908 On the effectiveness of multiversion software in digital p 161 A89-17624 A method of computer aided design of structural type avionics Eflect of model uncertainty on failure detection - The - An application of expert system and fuzzy sets theory [AIAA PAPER 88-39031 p 199 A89-18111 threshold selector p 197 A89-17965 p 201 A89-19811 Comparison of FAA DO-178A and DOD-STD-2167A Fault detection and isolation for reconligurable flight COCOMAT, a CAE system lor composite structures approaches to software certilication control systems design --- for aircraft p 166 A89-19981 [AIAA PAPER 88-40441 p 142 A89-19864 [AIM PAPER 88.38601 p 170 A89-18058 Processing composite finite element model with Wall adjustment strategy software for use with the NASA A method of measurina fault latency in a diaital~- fliaht CADCOMP --- for aircraft structures p 166 A89-19982 Langley 0.3-meter transonic cryogenic tunnel adaptive wall control system Progress towards a commercial aircraft design expert test Section [AIAA PAPER 88-38831 p 170 A89-18060 system [ NASA-CR-l81694] p 151 N89-13400 Vehicle manaaement system requirements [DGLR PAPER 87-1201 p 167 A8920237 COMPUTERIZED SIMULATION [AIAA PAPER 88-38781 p 179 A89-18070 Aerodynamic design via control theory Analytical determination and experimental comparison Vehicle management system for a manned hypersonic [NASA-CR-l817491 p 153 N89-13408 of performance degradation on a helicopter main rotor vehicle Surface grid generation for complex threedimensional due to ice accretion p 155 A89-18909 [AIM PAPER 88.38771 p 179 A89-18071 geometries Evolution of the ACAP crash energy management Fault tolerant inertial navigation system [ NASA-TM-1010461 p 191 N89-13747 system p 164 A89-18923 [AIAA PAPER 88-40241 p 159 A89-18175 Numerical grid generation and potential airfoil analysis Aerospace simulation Ill: Proceedings of the SCS Vehicle management system architectural and desian Multiconference, San Diego. CA. Feb. 3-5. 1988 considerations [AD-A19?972] p 154 N89-14219 p 142 A89-19551 [AIAA PAPER 88-38751 p 174 A89-18189 COMPUTER AIDED MANUFACTURING X-29 validation methodology for simulation and flight Design of a simple active controller to suppress New design,-. production tools will Dlav key role in 8-2 control system p 181 A89-19557 helicopter air resonance p 162 A89-18877 cost ' p-161. A89-18350 Modelling of ground effects on aircraft --- landing Determination of control laws for a single pilot. attack Robotic debuning of complex machined parts gear-runway interactions p 166 A89-19559 helicopter p 180 A89-18904 p 190 A89-18936 A parallel architecture for a real-time blade element A comparison between various side-arm controller COMPUTER DESIGN rotorcraft simulation p 201 A89-19560 configurations in a fly-by-wire helicopter Gas 32-bit single board computer The Combination of Simulation and response p 180 A89-18905 [AIM PAPER 88-40121 p 200 A89-18162 methodology and its application in an aggregate production Development and flight test of a precision autohover COMPUTER GRAPHICS plan p190 A89-19806 capability for tactical rotorcraft p 165 A89-18934 Stereoscopic 3-13 displays for cockpits Numerical simulations of an isolated microburst. I - Reconfigurable flight control system simulation [AIM PAPER 88-38871 p 170 A89-18080 Dynamics and structure p 196 A89-20265 p 181 A89-19558

A-7 CONTROL THEORY SUBJECT INDEX

Design of multi-level flight control systems D Investigationof a moving-modeltechnique for measuring p 181 A89-19813 ground effect Wall adjustment strategy software for use with the NASA DAMAGE ASSESSMENT [ NASA-TM-40801 p 154 N89-14217 Langley 0.3-meter transonic cryogenic tunnel adaptivewall Tip loss and blade strike simulations using DYSCO DESIGN ANALYSIS test section p 164 A89-18901 Euler analysis of a swrl recovery vane design for use [NASA-CR-1816941 p 151 N89-13400 DAMPING with an advanced single-rotation propfan Control of a human-powered helicopter in hover The effects of nonlinear damping on the large deflection [AIAA PAPER 88-31521 p 144 A89- 17940 [ NASA-TM-1010291 p 182 N89-13438 response of structures subjected to random excitation Civil tiltrotor aircraft ~ A comparison 01 five candidate Design of feedback control systems for unstable plants p 193 N89-13796 designs p 163 A89-18882 Design, analysis, and test of composite fuel tank with saturating actuators DATA ACOUlSlTlON pods [NASA-CR-1833921 p 194 N89-14377 Equipment to upgrade the facilities of the IIT (Illinois for the CH-46E helicopter p 163 A89-18885 Advanced transmission studies p 189 A89-18906 CONTROL THEORY Institute of Technology) Fluid Gynamics Research Center User's manual for an aerodynamic optimization Scheeme Reduced conservative singular value analysis for that updates flow variables and design parameters robustness p 197 A89-17489 [AD-A198084] p 184 N89-14242 simultaneously Aerodynamic design via control theory DATA BASES A fixed base data system for flight testing [ NASA-CR-l82180] p 151 N89-13399 [ NASA-CR-1817491 p 153 N89-13408 Design of high-Reynolds-numberflat-plate experiments p 201 A89-18937 CONTROLLERS in the NTF Modern chgilal pressure control system A microcomputerpollution model for civilian airports and [NASA-CR-184627] p 153 N89-13411 [AIAA PAPER 88-39481 p 172 A89-18119 air force bases model description The 13-inch magnetic suspension and balance system Functional augmentation of digital engine controllers to [ AD-A1990031 p 197 N89-14616 wind tunnel implement an integrated testability concept DATA CORRELATION [NASA-TM-4090] p 184 N89-14241 [AIM PAPER 88-39531 p 176 A89-18124 HolomeFrics - An information transformation DESTRUCTIVE TESTS The poststall nonlinear dynamics and control of an F-1B: methodology p 200 A89-18922 Advancements in erosion testing of rotor blade leading A preliminary investigation p 169 N89-14922 DATA INTEGRATION edges p 163 A89-18888 CONVECTIVE HEAT TRANSFER Inter-partition data integrity in the asynchronous DATAC DIAGNOSIS Convective heat transfer in a boundary layer behind a environment ATE hardware diagnostics, fault detection, and fault shock wave propagating along a flat plate with a sharp [AIM PAPER 88-40101 p 200 A89-18160 isolation tool (Self-test adapter) p 197 A89-18015 leading edge - A calculation method and a comparison DATA LINKS Integrated diagnostic concepts for advanced technology with experimental data p 144 A89-18546 A simulation study of data link message exchange - Flight rotorcraft p 141 A89-18023 CONVERGENT-DIVERGENT NOZLES deck perspective The enemy is FA, CND, and RTOK An analytical description of unsteady transonic [AIAA PAPER 88-39931 p 158 A89-18151 p 141 A89-18025 Laval-nozzle flow p 147 A89-19664 Oceanic clearance delivery via airlground data link Hybrid architecture of field-tested diagnostic expert system p 198 A89-18034 CORE FLOW [AIAA PAPER 88-39941 p 158 A89-18152 Reconfigurable flight control: An opportunity lor Method of cold smoke generation for vortex core Mode S data link applications research in the UK integrated diagnostics p 182 N89-14744 tagging p 191 A89-20324 [AIAA PAPER 88-39961 p 158 A89-18153 On-board expert diagnostics for an avionics The mode data link Experimentalwork and possible CORROSION RESISTANCE S - subsystem p 202 N89-14758 future applications in Western Europe Corrosion and corrosion control of selected field DIGITAL ELECTRONICS [AIM PAPER 88.39991 p 158 A89-18155 problems p 162 A89-18870 Software development lor large scale avionic integration COST EFFECTIVENESS Data link organization in Mode S secondary surveillance programs p 200 A89-18864 General aviation cost effectiveness radar systems - Operational compatibility with other Mode DIGITAL SYSTEMS p 204 A89-20136 S systems AlAAllEEE Digital Avionics Systems Conference, 8th. COUNTER ROTATION [AlAA PAPER 88-40031 p 159 A89-18157 San Jose. CA, Oct. 17.20, 1988. Technical Papers. Parts Laser velocimeter measurements of the flowfield Terminal information for data link 182 p 169 A89-18051 generated by an advanced counterrotating propeller [AIM PAPER 88-40001 p 159 A89-18181 A methodology for the design of hierarchically testable [ NASA-TM-1014371 p 153 N89-13409 A flight test design lor studying airborne applications and maintainable digital systems CRACKCLOSURE of air to ground duplex data link communications [AIAA PAPER 88-38591 p 170 A89-18057 Mechanics of fatigue crack closure p 195 N89-14924 A method of measuring fault latency in a digital fliht p 186 A89-17401 DATA MANAGEMENT control system CRACK GEOMETRY The enemy is FA, CND. and RTOK [AIAA PAPER 88-38631 p 170 A89-18060 Stress intensity factors for periodic radial cracks in a p 141 A89-18025 Triplex diiital flight control system for the STOL research rotating disc p 187 A89-17448 DATA PROCESSING aircraft 'Aska' CRACK PROPAGATION Optimization of algorithms for data processing in radar [AIAA PAPER 86-38831 p 179 A89-18077 Application of damage tolerance methodology to altimeters with electronic stabilization of the radiation A case study - F-16 Ada Digital Flight Control System helicopter dynamic components using the example of a pattern p 174 A89-18401 [AIAA PAPER 88-3911 ] p 171 A89-18090 main rotor pitch link for the AH-IS helicopter DATA TRANSFER (COMPUTERS) Digital Fly-By-Wire system tor advanced AH-64 p 164 A89-18921 Automatic dependent surveillance data transfer helicopters [AlAA PAPER 88-39221 p 179 A89-18099 Environmentally induced cracking in aluminum [AIM PAPER 88-39971 p 159 A89-18180 On the effectiveness of multiversion software in digital p 185 A89-18925 Optical fiber data transfer system [ NASA-CR-1817041 p 194 N89-14376 avionics Automated fatigue crack growth measurement DECISION MAKING [AIAA PAPER 88-39031 p 199 A89-18111 [ADA1986421 p 195 N89-14466 AI applications to tactical decision aids Impact of device level faults in a digital avionic CRASH LANDING LAMA PAPER 88-4027) p 200 A89-18178 processor Bell ACAP full-scale aircraft crash test and KRASH DEGRADATION [AlAA PAPER 88-39041 p 172 A89-18112 correlation p 164 A89-18920 Predictions of airfoil aerodynamic performance Application of digital technology to aircraft utility Evolution of the ACAP crash energy management degradation due to icing systems system p 164 A89-18923 [NASA-TM-101434] p 153 N89-13412 [AIM PAPER 88-38721 p 180 A89-18114 CRASHES DEICERS DIGITAL TECHNIOUES Comparison of the general dynamics ground clobber A comparison of numerical methods for the prediction Dgital audio applications in business and regional airline algorithm with the GCAS and laws algorithms of twodimensional heat transfer in an electrothermal aircraft [AD-A1984791 p 157 N89-14226 deicer pad [AIAA PAPER 88-39581 p 157 A89-18127 CRASHWORTHINESS [ NASA-CR-42021 p 175 N89-13429 DISORIENTATION The development of the V-22 Osprey armored Evaluation of the improved OV-1D anti-icing system Disorientation accidents and incidents in US. Army energy-absorbing crewseat assembly [ADA1984381 p 156 N89-14225 helicopters. 1 January 1980 - 30 April 1987 p 155 A89-18883 DELTA WINGS [AD-A1987201 p 156 N89-13417 Bell ACAP full-scale aircraft crash test and KRASH Seven hole probe measurement of leading edge vorlex DISPLAY DEVICES correlation p164 A89-18920 flows p 146 A89-18939 Interfacing sensor assemblies with windowless cockpit Evolution of the ACAP crash energy management The relationship between the aerodynamic displays p 187 A89-17979 system p 164 A89-18923 characteristics of double-delta wings and vortices with Stereoscopic 3-D displays for cockpits sideslips at high angles of attack p 148 A89-19801 CREEP PROPERTIES [AIAA PAPER 88-38871 p 170 A89-18080 Vwtex breakdown measurements on a 70 deg An investigation of environmental influence on the creep Commercial avionics applications of flat panel displays behavior of a low pressure plasma sprayed NiCoCrAlY sweepback delta wing p 150 A89-20312 Unsteady low-speed windtunnel test of a straked delta [AIAA PAPER 88-39621 p 173 A89-18129 alloy p 186 N89-13648 wing. oscillating in pitch. Part 4 Plots of time histories of Stereo 3-D and non-stereo presentations of a CROSS FLOW pressures and overall loads computergenerated pictorial primary flight display with Expftrimental investigation of ajet impinging on a ground pathway augmentation [ADA1986821 p 152 N89-13402 plane in crossflow p 149 A8920141 Unsteady low-speed windtunnel test of a straked delta [AIAA PAPER 88-39651 p 173 A89-18132 CRYOGENIC WIND TUNNELS wing. oscillating in pitch. Part 5 Power spectral density One million pixel full color liquid crystal display for Wall adjustment strategy software for use with the NASA plots of the overall loads foc harmonic oscillation and the avionics applications Langley 0.3meter transonic cryogenic tunnel adaptivewall response of overall loads to (1-COS) inputs [AIAA PAPER 88-39671 p 173 A89-18134 test section [AD-A198683] p 152 N89-13403 Flight guidance technology [NASA-CR-181 6941 p 151 N89-13400 Unsteady low-speed windtunnel test of a straked delta [DGLR PAPER 87-1191 p 160 A89-20239 CYCLIC LOADS wing, Oscillating in pitch. Part 6: Presentation Of the Real-time llight test analysis and display techniques for Dwell time effects on the fatique behaviour of titanium visualization program the X-29A aircraft p 185 A89-17619 [ AD-A1986841 P 152 N89-13404 [ NASA-TM-101692l p 168 N89-13424 A-0 SUBJECT INDEX EULER EQUATIONS OF MOTION

DISSIPATION ELASTIC PROPERTIES Fan acoustic modes measuring system Analysis of artificial dissipation models for the transonic A fundamental approach to the sticking of insect p 183 A89-19950 full-potential equation p 191 A89-20188 residues to aircraft wings Development of ram propulsion for fliht vehicles DISTRIBUTED PROCESSING [NASA-CR-183041] p 156 N89-13414 [GGLR PAPER 87-1011 p 176 A89-20240 An automated methodology for partitioning software ELECTRIC CONNECTORS Design and integration of air-breathing propulsion functions in a distributed avionics architecture Advanced avionics interconnection systems of space transports and hypersonic aircraft [AIAA PAPER 88-39711 p 199 A89-18137 [AIM PAPER 88-38561 p 170 A89-18055 [DGLR PAPER 87.1031 p 176 A89-20241 ELECTRO-OPTICS The fiber optic data distribution network - A network The Center of Excellence in Rotary Technology at Analysis of temperature and velocity microturbulence for next-generation avionics systems Rensselaer Polylechnic Institute parameters from aircraft dnta and relationship to [AIAA PAPER 88-4011 I p 188 A89-18161 [ AD-A1989641 p 168 N89-13426 atmospheric refracbve index structure Ada executive for distributed avionics processing T55-L-714 engine development and qualification: Tip [AIAA PAPER 88-40421 p200 A89-18166 [ AD-A1965421 p 196 N89-13854 ELECTROMAGNETIC INTERFERENCE clearance analysis DOPPLER EFFECT Lghtning simulation test technique evaluabon [ AD-A198849] p 177 N89-13431 Equipment to upgrade the facilities of the IIT (Illinois [DOT/FAAlCT47/38] p 156 N89-13415 Flight measured and calculated exhaust jet conditions Institute of Technology) Fluid Dynamics Research ELECTROMAGNETIC SHIELDING for an FtOO engine in an F-15 airplane Center Sharing the protection 01 aircraft electronic systems [NASA-TM-100419] p 177 N89-13435 [ AD-A1980&21 p 184 N89-14242 against the effects of high-level electromagnetic Materials and structures lor hypersonic vehicles DOPPLER RADAR environments between lradilmnal protection and system [NASA-TM-101501] p 186 N89-14264 Use of the Terminal Area Simulation System (TASS) architecture Parametric studies 01 advanced turboprops to study microburst wind shears p 197 N89-14899 [AIAA PAPER 88-39171 p 187 A89-18094 [ NASA-TM-1013891 p 195 N89-14465 DOWNWASH ELECTRONIC EQUIPMENT A review of failure models for unidirectional ceramic Numerical simulation and comparison of Lightning simulation test technique evaluation matrix composites under monotonic loads symmetricallsupercritical airfoils for the near tip region of [DOTlFAA/CT-87/38] p 156 N89-13415 [NASA-TM-101421] p 195 N89-14470 a helicopter in forward flight ELECTRONIC EQUIPMENT TESTS ENGINE FAILURE [NASA-CR-4212] p 204 N89-14821 Faults with nonstationary observability are limiting Sensor failure detection for jet engines DRAG REDUCTION avionics RBM [NASA-TM-101396] p 177 N89-13432 Down with drag p 141 A89-18347 [AIM PAPER 88-38521 p 169 A89-18054 ENGINE NOISE Winglets on low-aspxt-ratio wings The role of testability in the integrated diagnostic Experimental assessment of a turbulence ingestion p 149 A89-20142 process noise theory p 203 A89-18912 Drag reduction factor due to ground effect [AIM PAPER 88-38581 p 198 A89-18056 Fan acoustic modes measuring system p 151 A89-20325 A methodology for the design of hierarchically testable p 183 A89-19950 Passive venting technique for shallow cavities and maintainable digital systems ENGINE PARTS [ NASA-CASE-IAR-14031-1] p 168 N89-14232 [AIM PAPER 88-38591 p 170 A89-18057 A rev& of lailure models for unidirectional ceramic Passive venting technique lor shallow cavities Avionics failure propagation analysis tool matrix composites under monotonic loads [NASACASE-IAR-13875-1] p 169 N89-14233 [AlAA PAPER 88-3868j p 198 AB9-18065 [NASA-TM-101421j p 195 1.189-14470 DROP TESTS Development and applications of an avionics research ENGINE TESTS Evolution of the ACAP crash energy management testbed Functional augmentation of digital engine controllers to system p 164 A89-18923 [AIAA PAPER 88.39521 p 172 A89-18123 implement an integrated testability concept DUALTHRUSTNOPLES The B-1B central integrated test system expert [AIAA PAPER 88-39531 p 176 A89-18124 Experimental results lor a twodimensional supersonic parameter system p 202 N89-14763 Optical fire detector testing in the aircraft engine nacelle inlet used as a thrust deflecting nozzle ELECTRONIC WARFARE fire test simulator [ NASA-TM-834391 p 194 N89-14386 Modeling mission reliability 01 advanced integrated [ AD-A1979741 p 168 N89-13427 DYNAMIC CHARACTERISTICS communication. navigation. identification avionics Thrust-reverser flow investigation on a twin-engine Modal analysis of continuous rotor-bearing systems systems transport p 188 A8918766 [AIAA PAPER 88-40231 p 173 A89-18174 [NASA-TP-28561 p 153 N89-14213 Dynamic inflow for practical applications GaAs MMlCs satisfy EW requirements Fire extinguishingagent evaluation in the Aircraft Engine p 168 A89-18757 p 147 A89-19625 Nacelle Fire Test Simulator (AENFTS) DYNAMIC CONTROL ELLIPSOIDS [AD-A198523] p 157 N89-14227 Concept and flight testing of a modern longitudinal Low-speed pressure distribution on axisymmetric ENTHALPY motion regulator using an inverse model elliptc-nosed bodies p 149 A89-20147 Performance of coated materials in high-enthalpy [DGLR PAPER 87-1211 p 181 A89-20238 ELLIPTIC DIFFERENTIAL EQUATIONS oxidizing gas flows p 185 A89-18650 DYNAMIC MODELS Numerical grid generation and potential airfoil analysis ENTROPY Dynamic modeling of a helicopter lubrication system and design An entropy and viscosity corrected potential method for [AD-A1979721 p 154 N89-14219 p 189 A89-18897 rotor performance prediction p 145 A89-18857 DYNAMIC RESPONSE EMBEDDED COMPUTER SYSTEMS ENVIRONMENT EFFECTS Exoerimental investigation of proofan aeroelastic SDAR . A high productivity software engineering Detailed design specification for a protolype Assessment anvironmaiii hi ifi-~MiidS~SSGS --- S~S:GECC&~:: -.-- _-_-Y .I_:__ ,ICA.,\ response in off-axis flow with mistuning -.qJWIII .-.I", nllnmll.: I."#_ ,r."r.,., [AIM PAPER 88.31531 p 175 A89-17941 Automation Resources [AD-A197936] p 204 N89-14818 Vibration, performance, flutter and forced response [AIAA PAPER 88-38651 p 198 A89-18062 ENVIRONMENT MODELS characteristics of a large-scale propfan and its aeroelastic A MIL-STD-175OA. single-boardcomputer for embedded A microcomputerpollution model for civilian airports and model multiprocescx applications air force bases, model description [AIAA PAPER 88-40151 p200 A89-18163 [AIAA PAPER 88-31551 p 176 A89-17943 [ AD-Al990031 p 197 N89-14616 DYNAMIC STRUCTURAL ANALYSIS EMITTERS EQUATIONS OF MOTION Stress intensity factors lor periodic radial cracks in a Multiple sample polygonal correlation algorithm for the Dynamics of a rigid rotor mounted on discontinuously determination of ground emitter location rotating disc p 187 A89-17448 non-linear elastic supports p 190 A89-19125 Experimental verification of helicopter blade designs [AlAA PAPER 88-39871 p 158 A89-18145 Performance prediction analysis for fully deployed optimized for minimum vibration p 162 A89-18874 ENERGY ABSORPTION parachute canopies p 155 A89-20314 Structural dynamics 01 a helicopter rotor blade system The development of the V-22 Osprey armored Studies of the dynamics of the twin-lift system energy-absorbingcrewseat assembly p 162 A89-18878 [NASA-CR-l83273] p 167 N89-13422 Dynamics of a rigid rotor mounted on discontinuously p 155 A89-18883 EQUIPMENT SPECIFICATIONS non-linear elastic supports p 190 A89-19125 ENERGY REQUIREMENTS The effects 01 leading edge and downstream film cooling Enerav manaaement for intearated fliaht- and ..orwulsion on turbine vane heat transfer controlSystemS [ NASA-CR-1821331 p 192 N89-13754 E [AIAA PAPER 88-38731 p 178 A89-18068 EROSION ENGINE AIRFRAME INTEGRATION Advancements in erosion testing 01 rotor blade leading EARPHONES Rotcf/airframe interactions on tiltrotor aircraft edges p163 A89-18888 Sound attenuation and speech transmission quali of p 161 A89-18854 ERROR ANALYSIS fke types of headsets Airframe and propulsion assessment 01 alternative light Developing error-free software p 201 A89-19679 [IZF-l987-23] p 193 N89-14373 helicopter technologies (LHX) p 161 A89-18883 ERROR CORRECTING DEVICES EARTH ORBITAL ENVIRONMENTS ENGINE CONTROL An investigation 01 wall interference correction to the Low-orbit navigation concepts p 164 A89-19870 Effect of model uncertainty on failure detection - The pressure measurement in low speed wind tunnel with solid EDITING ROUTINES (COMPUTERS) threshold selector p 197 A89-17965 walls p 183 A89-19808

An overview of SEDACS ~ A state of the art TRDlTPS ERROR SIGNALS Functional augmentation 01 digital engine controllers to Irreducible error rate in aeronautical satellite channels environment p 198 A89-18030 implement an integrated testability concept EIGENVALUES [AIM PAPER 88-39531 p 176 A89-18124 p 157 A89-17183 Solution and sensitivity analysis 01 a complex EXAPE SYSTEMS transcendental eigenproblem with pairs 01 real Sensor failure detection lor jet engines Hypervelocity technology escape system concepts [NASA-TM-101396] p 177 N89-13432 eigenvalues program p 184 A89-17929 [NASA-CR-182241] p 193 N89-13819 ENGINE DESIGN EULER EQUATIONS OF MOTION ELASTIC BUCKLING Dual centrifugal compressors ~ The helicopter solution Spatial marching techniques for approximate solutions Buckling and final failure of graphite/PEEK stiffener to sand and ice ingestion p 176 A89-18908 to the hypersonic blunt body problem sections p 190 A89-19911 Turbine design using complex modes and p 143 A89-17460 ELASTIC DAMPING SubStNCtUring p 190 A89-19718 Euler analysis of a swirl recovery vane design for use Dynamics of a rigid rotor mounted on discontinuously Optimization of mistuned blade rotor for controlling with an advanced single-rotation proplan non-linear elastic supports p 190 A89-19125 fluner D 176 A89-19793 [AIM PAPER 88-31521 p 144 A89-17940

A-9 EUROPEAN AIRBUS SUBJECT INDEX

Full-potential integral solution for transonic flows with FATIGUE (MATERIALS) Temperature effect on stress concentration around and without embedded Euler domains The effects of nonlinear damping on the large deflection circular hole in a composite material specimen p 148 A89-19908 response of structures subjected to random excitation representative of X-29A forward-swept wing aircraft EUROPEAN AIRBUS p 193 N89-13796 [NASA-CR-179439] p 194 N89-14456 Modern digital pressure control system FATIGUE LIFE FIBER OPTICS [AIM PAPER 88-39481 p 172 A89-18119 Helicopter vibration analysis and control Fiber optic applications to the high altitude EVALUATION p 188 A89-18871 reconnaissance vehicle An experimental and analytical evaluation of the tapered FATIGUE TESTS [AIM PAPER 88-39301 p 187 A89-18104 tension-torsion strap concept Mechanics of fatigue crack closure Reliability in fiber optic cable harness manufacturing [ NASA-TM-1010491 p 191 N89-13746 p 186 A89-17401 [AIAA PAPER 88-3931I p 187 A89-18105 The fiber optic data distribution network - A network EXHAUST EMISSION Methodology for fatigue substantiation of alternate for next-generation avionics systems Atmospheric photochemical modeling of turbine engine sources and degraded modes on helicopter dynamic [AIAA PAPER 88-401 1] p 188 A89-18161 fuels and exhausts. Computer model development. volume components p 164 A89-18924 1 Optical fiber data transfer system Automated fatigue crack growth measurement [NASA-CR-181 7041 p 194 N89-14376 [ AD-A1986901 p 196 N89-13832 [ ADA1 986421 p 195 N89-14466 EXPERT SYSTEMS FIBER ORIENTATION FAULT TOLERANCE Hybrid architecture of field-tested diagnostic expert Processing composite finite element model with system p 198 A89-18034 Effect of model uncertainty on failure detection - The CADCOMP --- for aircraft structures p 166 A89-19982 threshold selector p 197 A89-17965 Application of AI technology to time-critical functions FIGHTER AIRCRAFT [AIM PAPER 88-40301 p 174 A89-18190 Universal Ada Test Language (UATL) to support Designing hydraulic systems for Survivability p 161 A89-17624 A method of computer aided design of structural type real-time softwarelsystem integration and .An application of expert system and fuzzy Sets theory factorylmaintenancefault isolation p 197 A89-18009 Analysis of a fighter type aircraft configuration with the p 201 A89-19811 ATE hardware diagnostics, fault detection, and fault HlSSS panel method at subsonic and supersonic Progress towards a commercial aircraft design expert isolation tool (Self-test adapter) p 197 A89-18015 speeds p147 A89-19660 system The enemy is FA, CND. and RTOK [DGLR PAPER 87-0851 [DGLR PAPER 87-1201 p 167 A8920237 p 141 A89-18025 Identification of unstable flight-mechanical systems using an output error method p 181 A89-19661 On-board expert diagnostics for an avionics Faults with nonstationary observability are limiting Introduction of Pilot's Operational Workload Evaluation subsystem p 202 N89-14758 avionics R8M Expert systems in higher echelon maintenance [AIAA PAPER 88.38521 p 169 A89-18054 ResearchSimulator, POWERS, in Aeromedical Laboratory, JASDF p 183 A89-19876 activities p 202 N89-14761 Avionics failure propagation analysis tool Transonic Navier-Stokes solutions for a fighter-like The 6-16 central integrated test system expert [AIAA PAPER 88-38681 p 198 A89-18065 parameter System p 202 N89-14763 configuration p 149 A89-20134 A simulation-basedfault injection experiment to evaluate FILM COOLING self-test diagnostics for a fault-tolerant computer The effects of leading edge and downstream film Cooling F [AIAA PAPER 88-38971 p 198 A89-18083 on turbine vane heat transfer Design and validation of the IFTAS fault-tolerant clock [ NASA-CR-1821331 p 192 N89-13754 F-15 AIRCRAFT --- Integrated Fault-Tolerant Avionics System FINITE DIFFERENCE THEORY Flight measured and calculated exhaust jet conditions [AIAA PAPER 88-38991 p 170 A89-18085 Recent developments in transonic flow computation for an FlOO engine in an F-15 airplane A fault tolerant avionics multiprocessing SyStem p 145 A89-18749 [ NASA-TM-1004191 p 177 N89-13435 architecture supporting concurrent execution of Ada Computation of rotational transonic flows using a F-16 AIRCRAFT tasks decomposition method p 150 A89-20179 A case study - F-16 Ada Digital Flight Control System [AIAA PAPER 88-39061 p 199 A89-18088 Coupling linearized far-field boundary conditions with [AIM PAPER 88-391 1I p 171 A89-18090 Fault tolerant avionics nonlinear near-field solutions in transonic flow The development and application of software quality [AIAA PAPER 88-3901I p 171 A89-18109 [AD-A198721I p 153 N89-13405 indicators MAFT - An architecture for reliable fly-by-wire flight FINITE ELEMENT METHOD [AlAA PAPER 88-39461 p 201 A89-19860 control .-- Multicomputer Architecture for Fault Matrix analysis method for composite flexbeam F-18 AIRCRAFT Tolerance p 190 A89-18926 Investigationof a moving-model technique for measuring [AIM PAPER 88-39021 p 180 A89-18110 Plenum chamber effect on wind-tunnel resonance by the finite-element method p190 A89-19909 ground effect Impact of device level faults in a digital avionic [ NASA-TM-40801 p 154 N89-14217 Processing composite finite element model with processor The poststall nonlinear dynamics and control of an F-18: [AIAA PAPER 88-39041 p 172 A89-18112 CADCOMP --- for aircraft structures p 166 A89-19982 A preliminary investigation p 169 N89-14922 Constitutive modeling for isotropic materials FABRICATION An SAE high speed ring bus overview [NASA-CR-1748051 p 177 N89-13436 [AIAA PAPER 88-40081 p 187 A89-18159 Design and fabrication of an advanced light rotor Parametric studies of advanced turboprops p 163 A89-18880 A fault tolerant integrated avionics computer System [ NASA-TM-1013891 p 195 N89-14465 Fabrication and testing of lightweight hydraulic system [AIAA PAPER 86-40411 p 173 A89-18165 FINITE VOLUME METHOD simulator hardware. Phase 2: Addendum Fault tolerant inertial navigation system Computation of rotational transonic flows using a [AD-A198524] p 184 N89-14243 [AIM PAPER 88-40241 p 159 A89-18175 decomposition method p 150 A89-20179 FACTORIAL DESIGN Tip loss and blade strike simulations using DYSCO FINS The combination of simulation and response p 164 A89-18901 A study on aerodynamic heating in the interaction regions methodology and its application in an aggregate production Application of damage tolerance methodology to of shock waves and turbulent boundary layers induced plan p 190 A89-19806 helicopter dynamic Components using the example of a by sharp fins p 148 A89-20131 FAILURE main rotor pitch link for the AH-1S helicopter FIRE EXTINGUISHERS The nature of the aircraft component failure pfocess: p 164 A89-18921 Fire extinguishingagent evaluation in the Aircraft Engine A working note Methodology for fatigue substantiation of alternate Nacelle Fire Test Simulator (AENFTS) [ AD-A1979791 p 169 N89-14234 sources and degraded modes on helicopter dynamic [ AD-A1985231 p 157 N89-14227 FAILURE ANALYSIS components p 164 A89-18924 FIRES Dwell time effects on the fatigue behawour of titanium FAULT TREES Optical fire detector testing in the aircraft engine nacelle alloys p 185 A89-17619 Avionics fault tree analysis and artificial intelligence for fire test simulator p 168 N89-13427 Effect of model uncerlainty on failure detection ~ The future aircraft maintenance p 202 N89-14760 [ADA1979741 threshold selector p 197 A89-17965 FAULTS Fire eainguishingagent evaluation in the Aircraft Engine Environmentally induced cracking in aluminum Fault detection and isolation for reconfigurable flight Nacelle Fire Test Simulator (AENFLS) p 185 A89-18925 control systems [ AD-A1985231 p 157 N89-14227 Buckling and final failure of graphitelPEEK stiffener [AIM PAPER 88-38601 p 170 A89-18058 FLAT PLATES sectins p 190 A89-19911 A method of measuring fault latency in a digital flight Vortex breakdown measurements on a 70 deg Sensor failure detection for jet engines control system sweepback delta wing p 150 A89-20312 [ NASA-TM-1013961 p 177 N89-13432 [AIM PAPER 88-38631 p 170 A89-18060 Design of high-Reynolds-numberflat-plate experiments Thermal Barrier Coatings. Abstracts and figures FEEDBACK CONTROL in the NTF [ NASA-CP-100191 p 185 N89-13642 Design of feedback control systems for unstable plants [NASA-CR-1846271 p 153 N89-13411 with saturating actuators FLIGHT CONTROL FAILURE MODES [NASA-CR-183392] p 194 N89-14377 A review of failure models for unidirectional ceramic Fault detection and isolation for reconfigurable flight The poststall nonlinear dynamics and control of an F-18: matrix composites under monotonic loads control systems A preliminary investigation p 169 N89-14922 [NASA-TM-101421] p 195 N89-14470 [AIAA PAPER 88-38601 p 170 A89-18058 FIBER COMPOSITES A method of measuring fault latency in a digital flight FALSE ALARMS Introduction of new technologies in the structural area control system The enemy is FA, CND. and RTOK from the viewpoint of IABG p 141 A89-18025 [AIAA PAPER 88-38631 p 170 A89-18060 [DGLR PAPER 87-1071 p 143 A89-20242 FAN BLADES Strength of dynamically loaded force introduction for Energy management for integrated flight and propulsion NOTAR hybrid cornpositelmetal fan blade fiber-reinforced rotors control systems p 178 A89-18068 p 163 A89-18893 [DGLR PAPER 87-1081 p 185 A8920243 [AIAA PAPER 88-38731 Fan acoustic modes measuring system Carbon fiber composites for supersonic technology Optimal integration of inertial sensor functions for p 183 A89-19950 [DGLR PAPER 87-1241 p 185 A89-20244 flight-control and avionics FAR FIELDS Design studis of primary aircraft structures in ARALL [AIAA PAPER 88-38781 p 170 A89-18072 Coupling linearized far-field boundary conditions with laminates p 167 A89-20318 Triplex digital flight control system for the STOL research nonlinear near-field solutions in transonic flow The quality of fibre reinforced thermoplastics aircraft 'Aska' [AD-A198721 ] p 153 N89-13405 mouldings p 196 N89-13839 [AIAA PAPER 88-38831 p 179 A89-18077

A-10 SUBJECT INDEX FLUTTER ANALYSIS

An approach to solving large reliability models FLIGHT PATHS FLlR DETECTORS [AIAA PAPER 88-39051 p 199 A89-18086 Stereo 3-D and non-stereo presentations of a Standardized advanced infrared sensor - A program A case study - F-16 Ada Digital Flight Control System computer-generated pictorial primary flight display with status p 175 A89-18932 [AIAA PAPER 88-3911 ] p 171 A89-18090 pathway augmentation FLOORS Fault tolerant avionics [AIM PAPER 88-39651 p 173 A89-18132 Influence of a floor on sound transmission into an aircraft [AIAA PAPER 88.39011 p 171 A89-18109 A note on the optimal hypersonic flight path fuselage model p 166 A89-20135 p 167 A89-20637 FLOW DISTORTION MAFT ~ An architecture for reliable fly-by-wire flight control --- Multicomputer Architecture for Fault A note on the aircraft minimum-time turns Determination of the perturbations of the flow fields of Tolerance p 182 A89-20638 supersonic wind tunnels from measured aerodynamic [AIAA PAPER 88-39021 p 180 A89-18110 A unified approach to vehicle design. control, and flight coefficients p 144 A89-18675 path optimization p 168 N89-14231 Impact of device level faults in a diital avionic FLOW DISTRIBUTION FLIGHT SAFETY Recent developments in transonic flow computation processor The mode S data link - Experimental work and possible p 145 A89-18749 [AIAA PAPER 88-39041 p 172 A89-18112 future applications in Western Europe Free wake calculation of rotor flow fields for interactional Fault tolerant inertial navigation system [AIM PAPER 88-39991 p 158 A89-18155 aerodynamics p 145 A89-18853 [AIM PAPER 88.40241 p 159 A89-18175 Development of the TrafficAlert and Collision Avoidance Rotor inflow variability with advance ratio The impact of yaw axis control modes, flight directors System 111 (TCAS Ill) p 145 A89-18855 and automatic control coupling on decelerating IFR [AIAA PAPER 88-40021 p 159 A89-18182 Improvements to transonic flowfield calculations approaches for rotorcraft p 180 A89-18903 Airborne integrated monitoring system p 146 A89-18915 Development and qualification testing, teaming for the p 174 A89-18868 Downstream vorticity measurements from ultrasonic V-22 multi-service aircraft system p 165 A89-18928 FLIGHT SIMULATION pulses p 151 A89-20313 Three-dimensional interactive system identicatin of Simulation evaluation of helicopter Terrain A water tunnel study of Gurney flaps helicopter rotorlbody dynamics p 165 A89-18938 Following/Terrain Avoidance concepts [NASA-TM-4071] p 151 N89-13395 Aerospace simulation Ill: Proceedings of the SCS [AIAA PAPER 88-39241 p 180 A89-18101 Theoretical derivation and calibration technique of a Multiconference. San Diego. CA, Feb. 3-5, 1988 A simulation study of data link message exchange - Flight hemispherical-tipped.five-hole probe p 142 A89-19551 deck perspective [NASA-TM-4047] p 151 N89-13396 Reconfigurable flight control System simulation [AIM PAPER 88.39931 p 158 A89-18151 User's manual for an aerodynamic optimizationscheeme p 181 A89-19558 Arrival-time guidance in variable winds that updates flow variables and design parameters Counteracting sidewind control system for aircraft [AIAA PAPER 88-40251 p 159 A89-18176 simultaneously landing p 181 A89-19800 Dynamic perspective displays and the control of tilt-rotor [NASA-CR-1821 801 p 151 N89-13399 Design of multi-level flight control systems aircraft in simulated flight p 174 A89-18867 Coupling linearized far-field boundary conditions with p 181 A89-19813 Developments in dynamics methodology at Bell nonlinear near-field solutions in transonic flow Rotor system evaluation. phase 1 Helicopter Textron p 162 A89-18875 [AD-A198721] p 153 N89-13405 [AD-A1987941 p 168 N89-13425 The impact of yaw axis control modes, flight directors Laser velocimeter measurements of the flowfield Comparison 01 the general dynamics ground clobber and automatic control coupling on decelerating IFR generated by an advanced counterrotating propeller algorithm with the GCAS and laws algorithms approaches for rotorcraft p 180 A89-18903 [NASA-TM-101 4371 p 153 N89-13409 [AD-A1984791 p 157 N89-14226 Development and qualification testing. teaming lor the Management and control of unsteady and turbulent Fabrication and testing of lightweight hydraulic system V-22 multi-service aircraft system p 165 A89-18928 flows simulator hardware. Phase 2: Addendum Aerospace simulation 111; Proceedings of the SCS [AD-A198091] p 192 N89-13751 [AD-A198524] p 184 N89-14243 Multiconference, San Diego. CA. Feb. 3-5, 1988 Dynamic stall computations using a zonal Navier-Stokes Reconfigurable flight control: An opportunity for p 142 A89-19551 model integrated diagnostics p 182 N89-14744 X-29 validation methodology for simulation and flight [ AD-A1 979421 p 194 N89-14397 FLIGHT CREWS control system p 181 A89-19557 Overlapping grids for flow field calculations Mode S data link applications research in the UK Internal pressure measurements for a liquid payload at p 195 N89-14918 [AIM PAPER 88-39961 p 158 A89-18153 low Reynolds numbers FLOW EQUATIONS Six degree of freedom crew isolation design, bench test [AD-A197438] p 191 N89-13727 Interactive and large-domain solutions of higher-order and flight test p 163 A89-18896 FLIGHT SIMULATORS viscous-flow equations p 148 A89-19905 Disorientation accidents and incidents in US. Army Evaluation of simulator motion characteristics based on Analysis 01 artificial dissipation models for the transonic AGARD-AR-144 procedures p 183 A89-19565 helicopters. 1 January 1980 ~ 30 April 1987 full-potential equation p 191 A89-20188 [ AD-A1 987201 p 156 N89-13417 FLIGHT TESTS FLOW GEOMETRY FLIGHT ENVELOPES The T-2 control configured vehicle development, Computation of rotational transonic flows using a Real-time flight test analysis and display techniques for integration and flight test decomposition method p 150 A8920179 the X-29A aircraft [AIAA PAPER 88-38821 p 179 A89-18076 Aerodynamic characteristics of rectangular [NASA-TM-101692] p 168 N89-13424 Modern digital pressure control system cross-sectional bodies at M = 0.85 p 151 A89-20317 Comparison of the general dynamics ground clobber [AIAA PAPER 88.39481 p 172 A89-18119 Experimental study on low-speed aerodynamic algorithm with the GCAS and laws algorithms Boeing 747-400 - Fliht test p 161 A89-18349 characteristics of non-axisvmmetnc slender bodies :a"-!..? 68470j p 157 NRq.iA22fi Six degree of freedom crew isolation design, bench test p 151 A89-20635 FLIGHT HAZARDS and flight test p 163 A89-18896 FLOW MEASUREMENT Three dimensional hazard zones p 195 A89-18259 Analytical prediction and flight test evaluation of Bell Measurement and analysis of unsteady flow structures An automated method for forecasting the probability of ACAP helicopter cabin nose --- Advanced Composite in rotor blade wakes p i47 ~89-18946 clear air turbulence p 196 A89-18554 Airframe Program p 164 A89-18911 Downstream vorticity measurements from ultrasonic FLIGHT INSTRUMENTS Development and qualiimtion testing. teaming for the pulses p 151 A89-20313 Development and applications of an avionics research V-22 multi-service aircraft system p 165 A89-18928 FLOW VELOCITY testbed Air-to-air combat helicopter development Theoretical derivation and calibration technique of a [AIAA PAPER 88-39521 p 172 A89-18123 p 165 A89-18929 hemispherical-tipped.five-hole probe FLIGHT MANAGEMENT SYSTEMS Development and flight test of a precision autohover [ NASA-TM-40471 p 151 N89-13396 Energy management for integrated flight and propulsion capability for tactical rotorcraft p 165 A89-18934 FLOW VISUALIZATION control systems Boeing Model 360 Advanced Technology Helicopter - Hole tone generated from almost choked to highly [AIAA PAPER 88-38731 p 178 A89-18068 Design features and flight test update choked jets p 203 A89-19903 Vehicle management system requirements p 165 A89-18935 Method 01 cold smoke generation for vortex core [AIAA PAPER 88.38761 p 179 A89-18070 A lixed base data system lor flight testing tagging p 191 A89-20324 Vehicle management system for a manned hypersonic p 201 A89-18937 Unsteady low-speed windtunnel test of a straked delta vehicle Concept and flight testing 01 a modern longitudinal wing, oscillating in pitch. Part 6: Presentation of the [AIAA PAPER 88-38771 p 179 A89-18071 motion regulator using an inverse model visualization program Guidance and Flight Director system for the V-22 [DGLR PAPER 87-1211 p 181 A89-20238 [AD-A198684] p 152 N89-13404 Tiltrotor The V.22 - 'Am I gonna like it7 p 167 A89-20745 Aerodynamic design via control theory [AIM PAPER 88.39211 p 179 A89-18098 Real-time flight test analysis and display techniques for [ NASA-CR-1817491 p 153 N89-13408 Application of digital technology to aircraft utility the X-29A aircraft FLUID DYNAMICS systems [ NASA-TM-1016921 p 168 N89-13424 Equipment to upgrade the facilities of the IIT (Illinois [AIAA PAPER 88.38721 p 180 A89-18114 Rotor system evaluation, phase 1 Institute of Technology) Fluid Dynamics Research Cockpit management for regional airlines and business [ AD-A1987941 p 168 N89-13425 Center aircraft as applied in the Beech Starship [ AD-A1 980841 p 184 N89-14242 Engines for Mini-RPV XM-1A [AIAA PAPER 86-39571 p 173 A89-18126 [AD-A1983361 p 178 N89-14236 FLUID FLOW Arrival-lime guidance in variable winds A potential flow solution on marine propeller and axial A flight test design for studying airborne applicabons [AIAA PAPER 88-40251 p 159 A89-18176 rotating fan Vehicle management system architectural of air to ground duplex data link communications [ADA198781 I p 191 N89-13735 p 195 N89-14924 considerations FLUITER ANALYSIS [AIM PAPER 88-38751 p 174 A89-18189 FLIGHT TRAINING Vibration, performance. flutter and forced response FLIGHT MECHANICS Disorientation accidents and incidents in U.S. Army charactenstics of a large-scale proplan and its aeroelastic Identifcatmn of unstable flight-mechanical systems helicopters. 1 January 1980 - 30 April 1987 model using an output error method pl8l A89-19661 [AD-A1987201 p 156 N89-13417 [AIAA PAPER 88-31551 P 178 A89.17943 A note on the optimal hypersonic flight path FLIGHT VEHICLES A guide to classical flutter p 188 A89-18801 p 167 A89-20637 Vehicle management system requirements Optimization of mistuned blade rotor for controlling FLIGHT OPTIMIZATION [AIAA PAPER 88-38761 p 179 A89-18070 flutter p 176 A89-19793 A unified approach to vehicle design, control. and flight X-wing fly-by-wire vehicle management system Effect of blade mistuning and blade-disk on cascade path optirnizatin p 168 N89-14231 [AIM PAPER 88-39231 p 179 A89-18100 flutter boundaries D 176 A89-19803

A-1 1 FLY BY WIRE CONTROL SUBJECT INDEX

Modern wing flutter analysis by computational fluid GAS FLOW GUST ALLEVIATORS dynamics methods p 191 A89-20146 Performance of coated materials in high-enthalpy Counteracting sidewind control system for aircraft Coupled flow, thermal, and structural analysis of oxidizing gas flows p 185 A89-18650 landing p 181 A89-19800 aerodynamically heated panels p 181 A89-20322 GAS TURBINE ENGINES GUSTS Application of transient aerodynamics to the structural Effect of blade mistuning and bladedisk or( cascade Calculation of the steadily periodic and gust responses nonlinear flutter problem p 182 A8920323 flutterbwndaries p 176 A89-19803 of a hingeless rotor helicopter using two dimensional time FLY BY WIRE CONTROL Selected papers on fundamental asDects of oas turbine domain unsteady aerodynamics p 182 N89-14240 Dgital Fly-By-Wire system for advanced AH-64 combusbon --- Book 'p 177 k9-20625 heliten GAS TURBINES [AIM PAPER 88-39221 p 179 A89-18099 Selected papen on fundamental aspects of gas turbine H X-wing fly-by-wire vehicle management system combustion --- Book p 177 A89-20625 [AIAA PAPER 88-39231 p 179 A89-18100 Constitutive modeling for isotropic materials HAFNIUM COMPOUNDS Commercial jet transport fly-by-wire architecture [NASA-CR-174805] p 177 N89-13436 Chemical vapor deposition Of oxidation resistant HfB2 considerations Thermal Barrier Coatings. Abstracts and figures + Sic composite coatings P 185 A89-19481 [AIM PAPER 88-39001 p 180 A89-18108 [ NASA-CP-100191 p 185 N89-13642 HARMONIC CONTROL MAFT - An architecture for reliable fly-by-wire flight Development of thermomechanical life prediction Bearinglessrotors and higher harmonic control modeling control --- Multicomputer Architecture for Fault models for thermal barrier coatings p 186 N89-13643 using RACAP p 162 A89-18876 Tolerance Plotting component maps in the NavylNASA Engine HARMONIC EXCITATION [AIAA PAPER 88-39021 p 180 A89-18110 Program (NNEP): A method and its usage The use of sweepfrequency excitation for unsteady Dgital control of a quadruplex direct drive actuator [ NASA-TM-1014331 p 178 N89-14239 pressure measurement --- in aerodvnamics,- [AIAA PAPER 88-3951I p 172 A89-18122 GASEOUS FUELS p 147 A89-18940 A comparison between various sidearm controller Atmospheric photochemical modeling of turbine engine HARMONIC OSCILLATION

configurations in a fly-by-wire helicopter fuels and exhausts. Computer model development, volume Unsteadv low-speed windtunnel test of a straked~~ delta.~.- p 180 A89-18905 -2 wing, osciliating in pitch. Part 4: Plots of time histories of X-29 validation methodology for simulation and flight [AD-A198691] p 196 N89-13833 pressures and overall loads control system p 181 A89-19557 GEARS [AD-A198682] p 152 N89-13402 FORCE DISTRIBUTION Advanced transmission studies p 189 A89-18906 Unsteady low-speed windtunnel test of a straked delta Application of the mobility power flow approach to GENERAL AVIATION AIRCRAFT wing, oscillating in pitch. Part 5: Power spectral density structural response from distributed loading Thunderstorm avoidance for general aviation aircraft plots of the overall loads for harmonic oscillation and the [NASA-CR-181342] p 193 N89-13817 [AIAA PAPER 88-39551 p 172 A89-18125 response of overall loads to (1-COS) inputs FORCED VIBRATION General aviation cost effectiveness [ADA1986831 p 152 N89-13403 Vibration, performance, flUner and forced response p 204 A89-20136 HARNESSES characteristics of a large-scale propfan and its aeroelastic Aircraft accident reports: Brief format, US civil and Automated wire preparation system model foreign aviation, issue number 4 of 1987 accidents p 189 A89-18895 [AIAA PAPER 88.3155) p 176 A89-17943 [PB88-916908] p 155 N89-13413 HEAD-UP DISPLAYS FORECASTING GLOBAL POSITIONING SYSTEM Dynamic perspective displays and the control of tilt-rotor Terminal area forecasts: Fiscal years 1988-2OOO Architecture of an optimal navigation system integrating aircraft in simulated flight p 174 A89-18867 [ AD-A1980791 p 156 N89-13419 GPS p 160 A89-18751 HEAT RESISTANT ALLOYS FRACTURE MECHANICS An overview of SDace-based radionaviaation svstems PM AI alloys - Hot prospects for aerospace Mechanics of faligue crack closure p 760 A89-20122 applications p 185 A89-17622 p 186 A89-17401 GRID GENERATION IMATHEMATICSI.~ An investigation of environmental influence on the creep An investigation of environmental influence on the creep Zonal grid generation me;hbl for complex behavior of a low pressure plasma sDraved NiCoCrAlY behavior of e low pressure plasma sprayed NiWrAIY configurations p 201 A89-20139 alloy p 166 N89-13648 alloy p 186 N89-13648 Navier-Stokes calculations using Cartesian grids. I - HEAT TRANSFER FREE FLOW Laminar flows p 150 A89-20180 A comparison of numerical methods for the prediction Unsteady transonic aerodynamics and aeroelastic Surface grid generation far complex three-dimensional of two-dimensional heat transfer in an electrothermal calculations at low-supersonic freestreams geometries deicer pad p 149 A89-20145 [NASA-TM-101 046) p 191 N89-13747 [NASA-CR-4202] p 175 N89-13429 Thrust-reverser flow investigation on a twin-engine Numerical grid generation and potential airfoil analysis The effects of leading edge and downstream film cooling tranimn .-r-. . and design on turbine vane heat transfer [NASA-TP-2856] p 153 N89-14213 [ADA1979721 p 154 N89-14219 [NASA-CR-182133] p 192 N89-13754 FREE JETS GROUND EFFECT (AERODYNAMICS) The effects of inlet turbulence and rotorlstator Computationof axisymmetric supersonic jet using space Modelling of ground effects on aircraft --- landing interactions on the aerodynamics and heat transfer of a marching technique p 145 A89-18750 gear-runway interactions p 166 A89-19559 large-scale rotating turbine model. volume 1 FREQUENCY MODULATION Drag reduction factor due to ground effect [NASA-CR-4079] p 192 N89-13756 A slmplihed aircraft collision avoidance system p 151 A89-20325 HELICOPTER CONTROL [AIAA PAPER 88-3961] p 173 A89-18128 Thrust-reverser flow investigation on a twin-engine Digital Fly-By-Wire system for advanced AH-64 FRICTION DRAG transport helicopters Down with drag p 141 A89-18347 [ NASA-TP-28561 p 153 N89-14213 [AIAA PAPER 88-39221 p 179 A89-18099 FRICTION REDUCTION Investigationof a moving-modeltechnique for measuring Simulation evaluation of helicopter Tenain Carbonlcarbon composite materials for aircraft brakes ground effect Following/Tenain Avoidance concepts p 165 A89-19427 [NASA-TM-4080] p 154 N89-14217 [AIAA PAPER 88.39241 p 180 A89-18101 FUEL COMBUSTION GROUNDRESONANCE Determination of control laws for a single pilot. attack Selected papen on fundamental aspects of gas turbine Nonlinear stabili analysis for helicopter ground helicopter pl80 A89-18904 combustion --- Book p 177 A89-20625 resonance p 166 A89-19790 A comparison between various side-arm controller FUEL CONSUMPTION GROUND STATIONS configurations in a fly-by-wire helicopter Down with drag p 141 A89-18347 Multiple sample polygonal conelation algorithm for the p 180 A89-18905 FUEL CORROSION determination of ground emitter location Development and flight test of a precision autohover Aviation fuel luhicity evaluation [AIAA PAPER 88-39871 p 158 A89-18145 capability for tactical rotorcraft p 165 A89-18934 [AD-A1981 971 p 177 N89-13434 GROUNDSUPPORTEQUIPMENT HELICOPTER DESIGN FUEL TANKS Fabrication and testing of lightweight hydraulic system Advanced Apache architecture Design, analysis, and test of composite fuel tank pods simulator hardware. Phase 2 Addendum [AIAA PAPER 88-39281 p 174 A89-18188 for the CH-46E helicopter p 163 A89-18885 [AD-A1985241 p 184 N89-14243 AHS. Annual Forum. 44th. Washington. DC. June 16-18, FULL SCALE TESTS GROUND TESTS 1988. Proceedings p 141 A89-18851 Bell ACAP full-scale aircraft crash test and KRASH Ground simulation for airborne equipment Airframe and propulsion awssment of alternative light conelation p 164 A89-18920 p 188 A89-18741 helicopter technologies (LHX) p 161 A89-18863 FUSELAGES Investigation of difficult component effects on FEM Experimental verification of helicopter blade designs Bearinglessrotors and higher harmonic control modeling vibration prediction for the AH-1G helicopter optimized for minimum vibration p 162 A89-18874 using RACAP p 162 A89-18876 p 162 A89-18879 Design of a simple active controller to suppress Application of the mobili power flow approach lo GROUND WIND helicopter air resonance p 162 A89-18877 structural response from disttibuted loading Arrival-time guidance in variable winds Design and fabrication of an advanced light rotor [NASA-CR-181 3421 p 193 N89-13817 [AIM PAPER 88.40251 p 159 A89-18176 p 163 A89-18880 GROUND-AIRGROUND COMMUNICATION Optimal design of an advanced composite rotating FUPY SETS Air traffic control (ATC) and air/ground digital flexbeam A method of computer aided design of stmctural type communications - Demonstration and evaluation p189 A89-18884 An application of expert system and fuzzy sets theory Design, analysis, and test of composite fuel tank - [AIAA PAPER 88-39981 p156 A89-18154 pods p201 A89-19811 The future of aeromobile digital communications for the CH-46E helicopter p 163 A89-18885 [AIAA PAPER 88-4001] p156 A89-18156 Achieving reliability and maintainability goals with a Terminal information for data link composite main rotor Made p 189 A89-18892 G [AIAA PAPER 88-40001 p 159 A89-18181 NOTAR hybrid compositelmetal fan blade GUIDANCE SENSORS p 163 A89-18893 QAUIUY ARSENIDES Optimal integration of inertial sensor functions for Aeroelastic optimization of a helicopter rotor GaAs 32-bil single bard computer flihtcontrd and avionics p 163 A89-18898 [AIAA PAPER 884121 p200 A89-18162 [AIAA PAPER 88-38781 p 170 A89-18072 Dynamic characteristics of advanced bearingless rotors GaAs MMlCs satisfy EW requirements Strapdown issues for airborne EO sensors at McDonnell Dwglas Helicopter Company p 188 A89-18757 [AIAA PAPER 88-39271 p 171 A89-18102 p 164 A89-18899 A-12 SUBJECT INDEX INERTIAL REFERENCE SYSTEMS

Analytical prediction and flight test evaluation of Bell Cynamic modeling of a helicopter lubrication system HUMAN FACTORS ENGINEERING ACAP helicopter cabin noise --- Advanced Composite p 189 A89-18897 Human factors impact on the V-22 Osprey cockpit Airframe Program p 164 A89-18911 Advanced transmission studies p 189 A89-18906 development - An overview p 174 A89-18865 Bell ACAP full-scale aircraft crash test and KRASH Navier-Stokes Calculations of hovering rotor flowfields HYDRAULIC EQUIPMENT correlation p 164 A89-18920 [AIM PAPER 87-26291 p 149 A89-20133 Fabncation and testing of lightweight hydraulic system Application of damage tolerance methodology to Disorientation accidents and incidents in U.S. Army simulator hardware Phese 2 Addendum helicopter dynamic components using the example of a helicopters. 1 January 1980 ~ 30 April 1987 [ AD-A1985241 p 184 N89-14243 main rotor pitch link for the AH-1S helicopter [AD-AI 987201 p 156 N89-13417 HYPERSONIC AIRCRAFT p 164 A89-18921 Rotor system evaluation. phase 1 Vanable-cycle engines for boosting-cruising vehicles [ AD-A1987941 p 168 N89-13425 Boeing Model 360 Advanced Technology Helicopter - [IAF PAPER 88-2491 p 175 A89-17742 The Center of Excellence in Rotary Technology at Design features and flight test update Matenals and structures for hypersonic vehicles p 165 A89-18935 Rensselaer Polytechnic Institute [NASA-TM-101501) p 186 N89-14264 [ AD-A1989641 p 168 N89-13426 Nonlinear stability analysis for helicopter ground Control of a human-powered helicopter in hover HYPERSONIC FLIGHT resonance p166 A89-19790 A note on the optimal hypersonic flight path [ NASA-TM-1010291 p 182 N89-13438 NOTAR - An alternetiie to the helicopter tail rotor An experimentaland analytical evaluation of the tapeced p 167 A89-20637 p 166 A89-20020 tension-torsbn strap concept HYPERSONIC FLOW Strength of dynamically loaded force introduction for [ NASA-TM-1010491 p 191 N89-13746 Spatial marching techniques for approximate solunons fiber-reinforced rotors Effect of advanced component technology on helicopter to the hypersonic blunt body problem [DGLR PAPER 87-1081 p 185 A89-20243 transmissions p 143 A89-17460 NASAlAHS rotorcraft noise reduction program - [NASA-TM-l01431] p 193 N89-13794 Calculation of hypersonic flow past the mndward side McDonnell Douglas Helicopter Company The quality of fibre reinforced thermoplastics of a low-aspect-ratio wing at high angles of attack accomplishments p 143 A8920747 mouldings p 196 N89-13839 p 144 A89-18357 Hub loads analysis of the SA349f2 helicopter High lift, low pitching moment airfoils Interference effects associated with a plate-supported [NASA-TM-101061] p 153 N89-13410 [NASA-CASE-LAR-13215-1I p 154 N89-14224 half-model in hypersonic flow p 148 A89-19924 Studies of the dynamics of the twin-lift system Numerical simulation and comparison of Numerical methods lor hypersonic flows [NASA-CR-1832731 p 167 N89-13422 symmetricallsupercritical airfoils for the near tip region of [DGLR PAPER 87-0841 p 150 A8920235 Calculation of the steadily periodic and gust responses a helicopter in forward flight HYPERSONIC SHOCK of a hingeless rotor helicopter using two-dimensional time [NASA-CR-4212] p 204 N89-14821 A study on hypersonic shock tunnel domain unsteady aerodynamics p 182 N89-14240 HELIUM p 148 A89-20132 HELICOPTER ENGINES Selection of the optimal lighter-than-air gas for airship HYPERSONIC TEST APPARATUS Airframe and propulsion assessment of alternative light and a scheme of double-layer structural design Buckling characteristics of hypersonic aircraft wing p 166 A89-19809 helicopter technologies (LHX] p 161 A89-18863 tubular panels Dual centrifugal compressors - The helicopter solution HELMET MOUNTED DISPLAYS [ NASA-TM-87756) p 193 N89-13816 to sand and ice ingestion p 176 A89-18908 Ai; advanced facility for cockpit s!gdies HYPERSONIC VEHICLES Dolphin eats snow --- helicopter engine surge during [AIAA PAPER 88.39661 p 182 A89-18133 Vehicle management system for a manned hypersonic flight in snowfall p 155 A89-18910 Dynamic perspectie displays and the control of tilt-rotor vehicle HELICOPTER PERFORMANCE aircraft in simulated flight p 174 A89-18867 [AIM PAPER 88-38771 p 179 A89-18071 AHS. Annual Forum, 44th, Washington. DC. June 1618. HIGH ALTITUDE HYPERSONIC WIND TUNNELS 1988. Proceedings p 141 A89-18851 Fiber optic applications to the high altitude Interference effects associated mth a plate-supported reconnaissance vehicle A 'new' philosophy of structural reliability. fail safe versus hall-model in hypersonic flow p 148 A89-19924 safe life p 188 A89-18852 [AIAA PAPER 88-39301 p 187 A89-18104 HYPERVELOCITY An entropy and viscosity corrected potential method for HIGH ELECTRON MOBILITY TRANSISTORS HypeNelocity technology escape system concepts rotor performance prediction p 145 A89-18857 GaAs MMlCs satisfy EW requirements program p 184 A89-17929 Helicopter vibration analysis and control p 188 A89-18757 p 188 A89-18871 HIGH REYNOLDS NUMBER Developments in dynamics methodology at Bell Design of high-Reynolds-number flat-plate experiments I Helicopter Textron p 162 A89-18875 in the NTF Analytical determination and experimental comparison [NASA-CR-1846271 p 153 N89-13411 ICE ENVIRONMENTS of performance degradation on a heliicopter main rotor HIGH TEMPERATURE AIR Dual centrifugal compressors - The helicopter solution due to ice accretion p155 A89-18909 Convective heat transfer in a boundary layer behind a to sand and ice ingestion p 176 A89-18908 Dolphin eats snow .__helicopter engine surge during shock wave propagating along a flat plate with a sharp Dolphin eats snow --- helicopter engine surge during flight in snowfall p 155 A89-18910 leading edge - A calculation method and a companson flight in snowfall p 155 A89-18910 An evaluation of a Navier-Stokes code for calculations with experimental data p 144 A89-18546 ICE FORMATION of retreating blade stall on a helicopter rotor HIGHLY MANEUVERABLE AIRCRAFT An ice detection system for helicopters p 146 A89-18916 Autonomous RPRV navigation. guidance and control [AIM PAPER 88-39491 p 172 A89-18120 MetnOQOiogy Tor iarigue SuDsianiiaiion oi aiiarriaia [NASA-GH-1 IY426j p i6i i.iBB-i422C Analyiiil determination and experimental companson of performance degradation on a heliter main rotor sources and degraded modes on helicopter dynamic HISTORIES due to ice accretion p 155 A89-18909 components p 164 A89-18924 Early jet engines and the transition from centrifugal to Air-to-air combat helicopter development Development and qualification testing. teaming for the axial compressors: A case study in technological change V-22 multi-service aircraft system p 165 A89-18928 p 165 A89-18929 [AD-A198775] p 177 N89-13430 A fixed base data system for flight testing An example of the behavior of an aircraft with HOLES (MECHANICS) p 201 A89-18937 accumulated ica ~ Latent instability p 181 A89-20170 HELICOPTER TAIL ROTORS Hole tone generated from almost choked to highly Predictions of airfoil aerodynamic performance choked jets p 203 A89-19903 A comparison of acoustic predictions with model rotor degradation due to icing test data from the NASA 14 x 22 ft wind tunnel Temperature effect on stress concentration around [NASA-TM-101434] p 153 N89-13412 p 203 A89-18913 circular hole in a composite material specimen An empirical look at tolerances in setting icing test An analytical model for the prediction of MRfTR representative of X-29A fwward-swept wing aircraft conditions with particular application to icing similitude interaction noise --- main rotorltail rotor [NASA-CR-1794391 p 194 N89-14456 [AD-A198941 I p 156 N89-13418 p 165 A89-18931 HORIZONTAL SPACECRAFT LANDING Evaluation of the improved OV-1D anti-icing system HELICOPTER WAKES Conceptual study of turbo-engines for horizontal takeoff [AD-A198438] p 156 N89-14225 Free wake calculation of rotor flow fields for interactional and landing space plane ICE PREVENTION aerodynamics p 145 A89-18853 [IAF PAPER 88-2531 p 184 A89-17745 Evaluation of the improved OV-1D anti-icing system Rotor inflow variability with advance ratio HOT-FILM ANEMOMETERS [ ADA1984381 p 156 N89-14225 p 145 A89-18855 Measurements of the buffet boundary of wings in IDEAL FLUIDS A correlation study of rotor inflow in forward flight transonic flow with hot-film method p 148 A89-19805 Self-similar problem of the separated flow of an ideal p 145 A89-18856 HOTOL LAUNCH VEHICLE fluid past an expanding plate p 144 A89-18669 Helicopter free wake prediction of complex wake Conceptual study of turbogngines for horizontal takeoff IGNITION SYSTEMS structures under Blade-Vortex Interaction operating and landing space plane Engines for Mini-RPV XM-1A conditions p 146 A89-18918 [ IAF PAPER 88-2531 p 184 A89-17745 [ AD-A1983361 p 178 N89-14236 Comparisons Of predicted and measured rotor HOVERING IMPACT DAMAGE performance in hover using a new tree wake analysis Comparisons of predicted and measured rotor Tip loss and blade strike Simulations using DYSCO p 165 A89-18933 performance in hover using a new free wake analysis pl64 A89-18901 Cynamic inflow for practkal applications p 165 A89-18933 IMPEDANCE MATCHING Bearinglessrotors and higher harmonic control modeling p 147 A89-19625 Development and flight test of a precision autohover HELICOPTERS using RACAP p 162 A89-18876 capability for tactical rotorcraft p 165 A89-18934 An ice detection system for helicopters INCOMPRESSIBLE FLCW Navier.Stokes calculations 01 hovering rotor flowfields [AIM PAPER 88.39491 p 172 A89-18120 Computation of the pressure in an incomprassible [AIAA PAPER 87-26291 p 149 A89-20133 Structural dynamics of a helicopter rotor blade system rotational flow of inviscid fluid p 143 A89-17150 p 162 A8018878 Control of a human-powered helicopter in hover INERTIAL NAVIGATION Advancements in erosion testing of rotor blade leading [ NASA-TM-1010291 p 182 N89-13438 Fault tolerant inertial navigation system edges p 163 A89-18888 HUBS [AIM PAPER 88.40241 p 159 A89-18175 Automated wire preparation system Optimal design of an advanced composite rotating INERTIAL REFERENCE SYSTEMS p 189 A89-18895 flexbeam p 189 A89-18884 Optimal integration of inertial sensor functions for Six degree of freedom crew isolation design, bench test Hub loads analysis of the SA34912 helicopter flight-controland avionics and flight test p163 A89-18896 [NASA-TM-101061I p 153 N89-13410 [AIAA PAPER 88.38781 p 170 A89-18072

A-13 INFORMATION TRANSFER SUBJECT INDEX

An air data inertial reference System for future INTERPROCESSOR COMMUNICATION Autonomous RPRV navigation. guidance and control commercial airplanes Interfacing sensor assemblies with windowless cockpit f NASA-CR-1794251 p 161 N89-14228 [AIAA PAPER 88-39181 p 171 ABS-18095 displays p 187 A89-17979 LANDING GEAR Fault tolerant inertial navigation system INVISCID FLOW Modelling of ground effects on aircraft --- landing [AIM PAPER 88-40241 p 159 A89-18175 Computation of the pressure in an incompressible gear-runway interactions p 166 A89-19559 INFORMATION TRANSFER rotational flow of inviscid fluid p 143 A89-17150 New design procedures applied to landing gear Overlapping grids for flow field calculations Interactive and large-domain solutions of higher-order development p 167 A89-20138 p 195 N89-14918 viscous-flow equations p 148 A89-19905 LASER ANEMOMETERS INFRARED IMAGERY Transonic wing design using inverse methods in Equipment to upgrade the facilities of the IIT (Illinois Standardized advanced infrared sensor A program - curvilinear cmdinates p 151 A89-20316 Institute of Technology) Fluid Dynamics Research status p 175 ABS-1 8932 Center Characterization of boundary layer conditions in wind ITERATIVE SOLUTION Full-potential integral solution for transonic flows with [AD-A1980841 P 184 N89-14242 tunnel tests through IR thermography imaging and without embedded Euler domains LASER DOPPLER VELOCIMETERS p 147 A89-19167 Laser velocimeter measurements of the flowfield p 148 A89-19908 INFRARED INSPECTION generated by an advanced counterrotating propeller Tima-iterative solutions of viscous supersonic nozzle Nondestructive tasting of composite aircraft structures [NASA-TM-101437] P 153 N89-13409 with infrared and shearographc imaging technologies flows p 150 A89-20164 LDV measurements in an annular combustor model p 189 A89-18891 [NASA-CR-l82207] p 192 N89-13755 INFRAREDSCANNERS LEADING EDGES Standardized advanced infrared sensor - A program J Advancements in erosion testing of rotor blade leading status p 175 A89-18932 edges p 163 A89-18888 INGESTION (ENGINES) JET AIRCRAFT Seven hole probe measurement of leading edge vortex Commercial jet transport fly-by-wire architecture Dual centrifugal compressors - The helicopter solution flows p 146 A89-18939 to sand and ice ingestion p 176 A89-18908 considerations Vortex breakdown measurements on a 70 dq Dolphin eats snow __-helicopter engine surge during [AIM PAPER 88-39001 p 180 ABS-18108 swaepback delta wing p 150 A89-20312 flight in snowfall p 155 A89-18910 JET AIRCRAFT NOISE The eflects of leading edge and downstream film cooling Experimental assessment of a turbulence ingestion Fan acoustic modes measuring system on turbine vane heat transfer noise theory p 203 A89-16912 p 183 A89-19950 [NASA-CR-182133] p 192 N89-13754 JET ENGINES INJECTION MOLDING LIFE (DURABlLllY) Early jet engines and the transition from centrifugal to The quality of fibre reinforced thermoplastics Thermal Barrier Coatings. Abstracts and figures axial compressors: A case study in technological change mouldings p 196 N89-13839 [NASA-CP-1001 91 p 165 N89-13642 INLET FLOW [AD-A1987751 p 177 N89-13430 Development of thermomechanical life prediction A correlation study of rotor inflow in forward flight T55-L-714 engine development and qualification: Tip models for thermal barner coatings p 186 N89-13643 p 145 A89-18856 clearance analysis Dynamic inflow for practical applications [AD-A1988491 p 177 N89-13431 LIFE CYCLE COSTS p 147 A89-19625 Sensor failure detection for jet engines Improved life cycle 'reps' services - V-22 engineering Isolated testing of highly maneuverable inlet con cepts [ NASA-TM-1013961 p 177 N89-13432 technical services and logistics planning [NASA-CR-179544] p 178 N89-13437 JET FLOW p 142 A89-18873 The eflects of inlet turbulence and rotor/stator Measurements in the field of a spark excited LIFT interactions on the aerodynamics and heat transfer of a compressible axisymmetric jet p 203 A89-18948 Downstream vorticity measurements from ultrasonic largescale rotating turbine modal, volume 1 Hole tone generated from almost choked to highly pulses p 151 A8920313 [NASA-CR-4079] p 192 N89-13756 choked jets p 203 A89-19903 LIFT AUGMENTATION Experimental results for a two-dimensional supersonic Flight measured and calculated exhaust jet conditions A water tunnel study of Gurney flaps inlet used as a thrust deflecting nozzle for an FlOO engine in an F-15 airplane [NASA-TM-4071] p 151 N89-13395 [NASA-TM-83439] p 194 N89-14386 [ NASA-TM-1004191 p 177 N89-13435 LIFT DEVICES INSECTS JET IMPINGEMENT A water tunnel study of Gurney flaps A fundamental approach to the sticking of insect Experimental investigation of a jet impingingon a ground [NASA-TM-4071] p 151 N89-13395 residues to aircraft wings plane in crossflow p 149 A89-20141 Studies of the dynamics of the twin-lift system JET PROPULSION fNASA-CR-183041] p 156 N89-13414 [NASA-CR-183273] p 167 N89-13422 INSTRUMENT FLIGHT RULES Advanced core technology: Key lo subsonic propulsion benefits LIFTING BODIES The impact of yaw axis control modes. flight directors A guide to classical flutter p 188 A89-18801 and automatic control coupling on decelerating IFR [ NASA-TM-101 4201 p 178 N89-14237 JOINTS (JUNCTIONS) LIFTING ROTORS approaches for rotorcraft p 180 A89-18903 High lift, low pitching moment airfoils INSTRUMENT LANDING SYSTEMS A study of contact interaction in aircraft structural elements p 188 ABS-18644 [NASA-CASE-UR-13215-1] p 154 N89-14224 Terminal navigation for the Combat Talon II aircraf: LIGHT AIRCRAFT [AIM PAPER 88-40211 p 159 ABS-18173 Airframe and propulsion assessment of alternative light INTAKE SYSTEMS K helicopter technologies (LHX) p 161 A89-18863 Isolated testing of highly maneuverable inlet con cepts Engines for Mini-RPV XM-1A [NASA-CR-179544] p 178 N89-13437 KALMAN FILTERS [AD-A1983361 p 178 N89-14236 INTEGRAL EQUATIONS Multiple sample polygonal correlation algorithm for the LIGHTNING A potential flow solution on marine propeller and axial determination of ground emitter location Lightning simulation test technique evaluation rotating fan [AIM PAPER 88-39871 p 158 A89-18145 [lXT/FAA/CT-87/38] p 156 N89-13415 [AD-A198781] p 191 N89-13735 KARMAN VORTEX STREET Measurement and analysis of unsteady flow structures LIQUID CRYSTALS INTEGRATED CIRCUITS One million pixel full color liquid crystal display for GaAs 32-bit single board computer in rotor blade wakes p 147 A89-18946 avionics applications [AIAA PAPER 88-40121 p200 A89-18162 [AIAA PAPER 88.39671 p 173 A89-18134 GaAs MMlCs satisfy EW requirements L LIQUID FILLED SHELLS p 188 A89-18757 Internal pressure measurements for a liquid payload at INTERACTIONAL AERODYNAMICS LABYRINTH SEALS low Reynolds numbers Free wake calculation of rotor flow fields for interactional The measurement and prediction of rotordynamicforces [AD-A197438] p 191 N89-13727 aerodynamics p 145 A89-18853 for labyrinth seals LITHIUM ALLOYS Rotor1airframe interactions on tiltrotor aircraft [AD-A197185] p 192 N89-13784 Evaluation of aluminum-lithium alloys in p 161 A89-18854 LAMINAR BOUNDARY LAYER compression-stiflend aircraft structures An examination of some rotor aerodynamic models using Detection of laminar-turbulent transition by infrared p 191 A8920315 the RSRA1X-wing model test deta p 146 A89-18858 thermography p 143 A89-17147 LOAD DISTRIBUTION (FORCES) A study on aerodynamic heating in the interaction regions LAMINAR FLOW Holometrics - An information transformation of shock waves and turtxrlent boundary lay- induced Mathematical modeling Of laminar and turbulent methodology p 200 A89-18922 supersonic flow past convexconcave bodies by sharp fins p 148 A89-20131 LOADING RATE Further comparisons of interactive boundary-layer and P 144 A89-18671 Dwell time effects on the fatigue behaviour of titanium Navier-Stokes calculations using Cartesian grids, I . thin-layer Navier-Stokes procedures p 149 A89-20137 alloys p 185 A89-17619 Interactions between turbulent wakes and boundary Laminar flows p 150 A89-20180 LAMINAR FLOW AIRFOILS LOADS (FORCES) layers p 150 ABS-20182 A fundamental approach to the sticking of insect New solution method for steady-state canopy structural INTERNAL PRESSURE residues to aircraft wings loads p 155 A89-20321 Internal pressure measurements for a liquid payload at [NASA-CR-183041] p 156 N89-13414 Hub loads analysis of the SA34912 helicopter low Reynolds numbers LAMINATES [NASA-TM-101061] p 153 N89-13410 [AD-A1974381 p 191 N89-13727 Buckling and final failure of graphite1PEEK stiffener Application of the mobility power flow approach to INTERNATIONAL TRADE sections p 190 A89-19911 structural response from distributed loading New proposals for new direcws - 1992 and the GATf COCOMAT. a CAE system for composite structures [ NASA-CR-1813421 p 193 N89-13817 approach to trade in air transport services design -- lor aircraft p 166 A89-19981 LOGISTICS MANAGEMENT p204 A89-18949 Design studies of primary aircraft structuras in ARALL AH-64A Contractor Logistic Support - The contractors' INTERPOLATION laminates p 167 A89-20318 perspective p 142 ABS-18869 Surface grid generation for complex three-dimensional LANDING AIDS Improved life cycle 'reps' services - V-22 engineering geoIlWtrieS Coonteracting sidewind control system for aircraft technical services and logistics planning [ NASA-TM-101O46] p lQl N89-13747 landing Pl81 A89-19800 p 142 A89-18873 A-14 SUBJECT INDEX MULTIPROCESSING(COMPUTERS)

LONGITUDINAL CONTROL MAPPING MICROWAVE LANDING SYSTEMS Concept and flight testing of a modern longitudinal Plotting component maps in the NavylNASA Engine Recent studies of MLS application motion regulator using an inverse model Program (NNEP): A method and its usage [AIAA PAPER 88.39161 p 157 A89-18093 [DGLR PAPER 87.1211 p 181 A89-20238 [ NASA-TM-1014331 p 178 N89-14239 MIDAIR COLLISIONS LOW ASPECT RATIO MARINE ENVIRONMENTS Development of the Traffic Alert and Collision Avoidance Calculation of hypersonic flow past the windward side Oceanic clearance delivery via airlground data link System 111 (TCAS Ill) of a low-aspect-ratio wing at high angles of attack [AIAA PAPER 88-39941 p 158 A89-18152 [AIM PAPER 88-40021 p 159 A89-18182 p 144 A89-18357 MARINE PROPULSION TCAS Ill - Bringing operational compatibility to airborne LOW REVNOLDS NUMBER A potential flow solution on marine propeller and axial collision avoidance Internal pressure measurements for a liquid payload at rotating fan [AIAA PAPER 88.40041 p 159 A89-18183 [AD-A19878l] p 191 N89-13735 low Reynolds numbers MILITARY AIR FACILITIES [AD-A1974381 p 191 N89-13727 MARKOV PROCESSES A microcomputerpollution model for civilian airports and Optimization of algorithms for data processing in radar LOW SPEED air force bases, model descnption altimeters with electronic stabilization of the radiation [ AD-A1990031 p 197 N89-14616 Experimental study on low-speed aerodynamic pattern p 174 ABS-18401 MILITARY AIRCRAFT characteristics of non-axisymmetricslender bodies MATHEMATICAL MODELS p 151 A8920635 AI applications to tactical decision aids Mathematical modeling of laminar and turbulent [AIAA PAPER 88-40271 p 200 A89-18178 Unsteady low-speed windtunnel test of a straked delta supersonic flow past convex-concave bodies wing, oscillating in pitch. Part 5: Power spectral density p 144 A89-18671 The Pointer ~ A revolutionary idea to improve RPV plots of the overall loads for harmonic oscillation and the Aerodynamic design via control theory capabilities p 163 A89-18881 response of overall loads to (1-COS) inputs [ NASA-CR-1817491 p 153 N89-13408 MILITARY HELICOPTERS [ADA1986831 p 152 N89-13403 Constitutive modeling for isotropic materials Application of AI technology to time-critical functions Unsteady low-speed windtunnel test of a straked delta [NASA-CR-1748051 p 177 N89-13436 [AIAA PAPER 88-40301 p 174 A89-18190 wing, oscillating in pitch. Part 6 Presentation of the Thermal Barrier Coatings. Abstracts and figures Air combat tactics for the evaluation of rotorcraft visualization program [ NASA-CP-10019] p 185 N89-13642 characteristics in the low air war of 2010 [AD-A198684] p 152 N89-13404 Development of thermomechanical life prediction p 142 ABS-18859 LOW SPEED WIND TUNNELS models for thermal barrier coatings p 186 N89-13643 US Army aircraft combat maintenancelbattle damage An investigation of wall interference correction to the Atmospheric photochemical modeling of turbine engine repair program p 142 A89-18860 pressure measurement in low speed wind tunnel with solid fuels and exhausts. Computer model development, volume Airframe and propulsion assessment of alternative light walls p 183 A89-19808 1 helicopter technologies (LHX) p 161 A89-18863 LUBRICATION [AD-A1986901 p 196 N89-13832 Corrosion and corrosion control of selected field Aviation fuel lubricity evaluation Calculation of the steadily periodic and gust responses problems p 162 A89-18870 of a hingeless rotor helicopter using two-dimensional time [AD-A198197] p 177 N89-13434 Determination of control laws for a single pilot, attack domain unsteady aerodynamics p 182 N89-14240 LUBRICATION SYSTEMS helicopter p 180 A89-18904 Temperature effect on stress concentration around Dynamic modeling of a helicopter lubrication system Air-to-air cembat helicopter development D 189 A89-18897 circular hole in a composite materiai specimen representative of X-29A forward-swept wing aircraft p 165 A89-18929 Advanced lube system diagnostics for V-22 Standardized advanced infrared Sensor - A program p 190 A89-18907 [ NASA-CR-1794391 p 194 N89-14456 Parametric studies of advanced turboprops status p 175 A89-18932 [ NASA-TM-lOl389l p 195 N89-14465 Development and flight test of a precision autohover M A microcomputer pollution model for civilian airports and capability for tactical rotorcraft p 165 A89-18934 air force bases, model description MILITARY OPERATIONS MACH NUMBER [AD-A199003] p 197 N89-14616 Reconfigurable flight control: An opportunity for A study on hypersonic shock tunnel Use of the Terminal Area Simulation System (TASS) integrated diagnostics p 182 N89-14744 p 148 A89-20132 to study microburst wind shears p 197 N89-14899 MILITARY TECHNOLOGY Flight measured and calculated exhaust jet conditions MATRIX METHODS Avionics testing in the military bare-base environment for an FIOO engine in an F-15 airplane Matrix analysts method for composite flexbeam p 141 A89-18011 [ NASA-TM-1004191 p 177 N89-13435 p 190 A89-18926 Advanced lube system diagnostics for V-22 Optimization of slender wings for center-of-pressureshift Efficient load measurements using singular value p 190 A89-18907 due to change in Mach number p 154 N89-14897 decomposition MISSILE CONTROL MAGNETIC SUSPENSION [NASA-CR-t84614] p 202 N89-14795 Aerospace simulation Ill: Proceedings of the SCS The 13-inch magnetic suspension and balance system MEASURING INSTRUMENTS Multiconference. San Diego. CA, Feb. 3-5, 1988 wind tunnel An ice detection system for helicopters p 142 A89-19551 [ NASA-TM-40901 p 184 N89-14241 [AIM PAPER 88-39491 p 172 A89-18120 MISSION PLANNING MAGNUS EFFECT MECHANICAL DRIVES Comparison of the general dynamics ground clobber Moving wall effects in unsteady flow Advanced transmission studies p 189 A89-18906 algorithm with the GCAS and laws algorithms p 150 A89-20311 UFESAOE PRrnESS!NG [AD-A1984791 p 157 N89-14226 MAINTAINABILITY Asimulation of datalinkmessageexchange- Flight MODAL RESPONSE Evaluation of the improved OV-1D anti-icing system study deck perspective Modal analysis of continuous rotor-bearing systems [AD-A198438] p 156 N89-14225 [AIM PAPER 88-39931 p 158 A89-18151 p 188 A89-18766 MAINTENANCE Universal Ada Test Language (UATL) to support METAL FATIGUE Turbine design using complex modes and substructuring p 190 A89-19718 real-time sottwarelsystem integration and Dwell time effects on the fatigue behaviour of titanium alloys p 185 A89-17619 factorylmaintenancefault isolation p 197 ABS-18009 MODELS ATE hardware diagnostics. fault detection. and fault METEOROLOGY Vibration, performance. flutter and forced response isolation tool (Self-test adapter) p 197 ABS-18015 Analysis of temperature and velocity microturbulence characteristics of a large-scale propfan and its aercslastic A methodology for the design of hierarchically testable parameters from aircraft data and relationship to model and maintainable digital systems atmospheric refractive index structure [AIAA PAPER 88-3155) p 176 A89-17943 [AIAA PAPER 88-38591 p 170 A89-18057 [ AD-A1965421 p196 N89-13854 Unsteady low-speed windtunnel test of a straked delta CEPS: An artificial intelligence approach to avionics METHOWLOGY wing. oscillating in pitch. Part 4 Plots of time histories of maintenance p 201 N89-14749 A rev& of failure models for unidirectional ceramic pressures and overall loads Avionics fault tree analysis and artificial intelligence for matrix composites under monotonic loads [AD-A198682] p 152 N89-13402 future aircraft maintenance p 202 N89-14760 [NASA-TM-101421I p 195 N89-14470 MODULES MAN MACHINE SYSTEMS MICROBURSTS (METEOROLOGY) Modular avionics systems studies An advanced facility for cockpit studies Numerical simulation of the 2 August 1985 DFW [AIAA PAPER 88-38501 p 169 A89-18052 [AIAA PAPER 88-39661 p 182 ABS-18133 microburst with the three.dimensional Terminal Area Modular avionics systems architecture (MASA) - Seeds MAN POWERED AIRCRAFT Simulation System p 175 A89-19186 of destruction or seeds of progress? [AIAA PAPER 88-3851] p 141 A89-18053 Control of a human-powered helicopter in hover Numerical simulations of an isolated microburst. I - [ NASA-TM-1010291 p 182 N89-13438 Dynamics and structure p 196 A89-20265 MOLDING MATERIALS MANAGEMENT The quality of fibre reinforced thermoplastics Use of the Terminal Area Simulation System (TASS) mwldings p 196 N89-13839 Management and control of separation by unsteady and to study microburst wind shears p 197 N89-14899 vortical flows MOTION SIMULATORS MICROCOMPUTERS [ADA1989021 p 191 N89-13736 Evaluation of simulator motion characteristics based on A microcomputer pollution model for civilian airports and MANAGEMENT SYSTEMS AGARD-AR-144 procedures p 183 A89-19565 air force bases, model description MULTIPATH TRANSMISSION X-wing fly-by-wire vehicle management system [AD-A1990031 p 197 N89-14616 [AIM PAPER 88-39231 p 179 ABS-18100 Precision approach radars Twenthe and Volkel MANEUVERABILITY MICROELECTRONICS (Netherlands). Multipath propagation problems Management and control of separation by unsteady and Advanced avionics interconnection [FEL-1988-15] ~ p 193 N89-14372 [AIAA PAPER 88-38561 p 170 A89-18055 vortical flows MULTIPROCESSING (COMPUTERS) [ADA1989021 p 191 N89-13736 MICROGRAVITY APPLICATIONS A fault tolerant avionics multiprocessing system MANEUVERS New application possibilities for balloon-borne case architecture supporting concurrent execution of Ada Isolated testing of highly maneuverable inlet con cepts studies. MIKROBA (Microgravity by balloons) tasks [ NASA-CR-1795441 p 178 N89-13437 [DGLR PAPER 874691 p 184 A8920233 [AIM PAPER 88-39081 p 199 A89-18088 MANUFACTURING MICROWAVE AMPLIFIERS Inter-partition data integrity in the asynchronous DATAC Genesis of a flexible turning center GaAs MMlCs satisfy EW requirements environment p 189 A89-18894 p 188 A89-18757 [AIAA PAPER 88-40101 p 200 A89-18160

A-15 NACELLES SUBJECT INDEX

N NONDESTRUCTIVE TESTS A note on the optimal hypersonic flight path NOndeStruCtive testing of composite aircraft structures P 167 A8920637 NACELLES with infrared and shearographic imaging technologies OPTIMtZATION Fire extinguishingagent evaluation in the Aircraft Engine p 189 A89-18891 Optimal integration of inertial sensor functions for Nacelle Fire Test Simulator (AENFTS) Thermal Barrier Coatings. Abstracts and figures flighttontrol and avionics [AD-A198523] p 157 N89-14227 [ NASA-CP-100191 p 185 N89-13642 [AIAA PAPER 88-38781 P 170 A89-18072 NASTRAN Buckling characteristics 01 hypersonlc aircraft wing Architecture of an optimal navigation system integrating Investigation of difficult component effects on FEM tubular panels GPS P 160 A89-18751 vibration prediction for the AH-1G helicopter [ NASA-TM-877561 p 193 N89-13816 Optimal design of an advanced composite rotating p 162 A89-18879 Reconfigurable flight control: An opportunity for flexbeam P 189 A89-18884 NATIONAL AIRSPACE SYSTEM integrated diagnostics p 182 N89-14744 AerOelastic optimization of a helicopter rotor Proposed revisions to America's national airspace NONLINEAR EQUATIONS P 163 A89-18898 system ~ A crisis in leadership? p 204 A89-18950 The combination of simulation and response Application of transient aerodynamics to the structural NAVIER-STOKES EQUATION methodology and its application in an aggregate production nonlinear flutter problem p 182 A89-20323 An evaluation 01 a Navier-Stokes code lor calculations plan p 190 A89-19806 01 retreating blade stall on a helicopter rotor NONLINEARIN User's manual for an aerodynamic optimization scheeme p 146 A89-18916 The poststall nonlinear dynamics and control 01 an F-18: that updates flow variables and design parameters Multigrid acceleration of a relaxation procedure for the A preliminary investigation p 169 N89-14922 simultaneously reduced Navier-Stokes equations p 148 A89-19904 NOZZLE DESIGN [NASA-CR-1821801 p 151 N89-13399 Transonic Navier-Stokes solutions for a fighter-like Development of three-dimensionalcode for the analysis Optimizationof slender wings for center-of-pressureshift configuration p 149 A89-20134 of jet mixing problem. Part 1: Laminar solution due to change in Mach number p 154 N89-14897 Further comparisons of interactive boundary-layer and [NASA-CR-4200] p 152 N89-13401 OSCILLATING FLOW thin-layer Navier-Stokes procedures p 149 A89-20137 Flight measured and calculated exhaust jet conditions Comment on 'Aeroelastic oscillations caused by Navier-Stokes calculations using Cartesian grids. I - lor an FlOO engine in an F-15 airplane transitional boundary layers and their attenuation' Laminar flows p 150 A89-20180 [NASA-TM-100419] p 177 N89-13435 p 167 A89-20150 Development of three-dimensional code for the analysis NOZZLE FLOW OSCILLATIONS of jet mixing problem. Part 1: Laminar solution An analytical description of unsteady transonic Unsteady low-speed windtunnel test of a straked delta [NASA-CR-lZOO] p 152 N89-13401 Laval-nozzle flow p147 A89-19664 wing. oscillating in pitch. Part 6: Presentation of the Dynamic stall computations using a zonal Navier-Stokes Time-iterative solutions of viscous supersonic nozzle visualization program model flows p 150 A89-20184 [AD-A198684] p 152 N89-13404 [ADA1979421 p 194 N89-14397 NOZZLE GEOMETRY OXIDATION RESISTANCE Numerical simulation and comparison of Computationof axisymmetric supersonic jet using space Chemical vapor deposition 01 oxidation resistant HfB2 symmetricallsupercritical airfoils for the near tip region of marching technique p 145 A89-18750 + Sic composite coatings p 185 A89-19481 a helicopter in forward flight A study on hypersonic shock tunnel Development of thermomechanical life prediction [ NASA-CR-42121 p 204 N89-14821 models for thermal barrier coatings p 186 N89-13643 NAVIGATION AIDS p 148 A89-20132 NOZZLE WALLS OXIDIZERS Radionavigation needs for the Europe of the future A study on hypersonic shock tunnel Performance of coated materials in high-enthalpy p 160 A89-18753 p 148 A89-20132 oxidizing gas flows p 185 A89-18650 Omega Navigation System A status report - NUCLEAR ELECTRIC POWER GENERATION p 160 A89-19867 Turbine design using complex modes and Flight guidance technology substructuring p 190 A89-19718 P [DGLR PAPER 87.1191 p 160 A89-20239 NUMERICAL ANALYSIS Autonomous RPRV navigation, guidance and control PANEL METHOD (FLUID DYNAMICS) A comparison of numerical methods for the prediction [ NASA-CR-1794251 p 161 N89-14228 Recent developments in transonic flow computation of two-dimensional heat transfer in an electrothermal NAVIGATION SATELLITES p 145 A89-18749 deicer pad Low-orbit navigation concepts p 184 A89-19870 An examinationof some rotor aerodynamic models using NAVSTAR SATELLITES [ NASA-CR-42021 p 175 N89-13429 the RSRAlX-wing model test data p 146 A89-18858 Control of a human-powered helicopter in hover An overview of space-based radionavigation systems Analysis of a fighter type aircraft configuration with the [ NASA-TM-1010291 p 182 N89-13438 p 160 A89-20122 HlSSS panel method at subsonic and supersonic NUMERICAL CONTROL NEAR FIELDS speeds Modern digital pressure control system Coupling linearized far-field boundary conditions with [DGLR PAPER 87-0851 p147 A89-19660 nonlinear near-field solutions in transonic flow [AIAA PAPER 88-39481 p 172 A89-18119 PANELS Digital control of a qUadNplex direct drive actuator [AD-A198721] p 153 N89-13405 Buckling and final failure of graphitelPEEK stiffener NETWORK SYNTHESIS [AIAA PAPER 88-39511 p 172 A89-18122 sections p 190 A89-19911 X-29 validation methodology for simulation and flight Computer-aided engineering methods for successful The effects of nonlinear damping on the large deflection VHSIC application control system p 181 A89-19557 response 01 structures subjected to random excitation NUMERICAL FLOW VISUALIZATION [AIM PAPER 88.40351 p 188 A89-18185 p 193 N89-13796 NOISE INTENSITY Helicopter free wake prediction of complex wake PARABOLIC DIFFERENTIAL EQUATIONS structures under Blade-Vortex Interaction operating Tip-path-plane angle effects on rotor blade-vortex Numerical grid generation and potential airfoil analysis interaction noise levels and directivity conditions p 146 A89-18918 and design Numerical simulation of tip vortices of wings in subsonic p 203 A89-18914 [ AD-A1 979721 p 154 N89-14219 Detaileddesign specification fora prototype Assessment and transonic flows p 150 A89-20176 PARACHUTES System for Aircraft Noise (ASAN) Performance prediction analysis for fully deployed [ADA1979361 p 204 N89-14818 parachute canopies p 155 A89-20314 NOISE MEASUREMENT 0 New solution method for steady-state canopy structural Fan acoustic modes measuring system OMEGA NAVIGATION SYSTEM loads p 155 A89-20321 PARALLEL PROCESSING (COMPUTERS) p 183 A89-19950 Omeaa"-, Navioation Svstem - A status rewrt NOISE PREDICTION p 1M) A89-19867 A parallel modular signal processor Users' manual for the Langley high speed propeller noise ONBOARD DATA PROCESSING [AIAA PAPER 88-3981] p 199 A89-18141 prediction program (DFP-ATP) Combined numerical and symbolic processing for A para!lel architecture for a real-time blade element [NASA-CR-4208] p 204 N89-14820 airborne surveillance rotorcraft simulation p 201 A89-19560 NOISE PREDICTION (AIRCRAFT) [AIAA PAPER 88-39851 p 157 A89-18143 PASSENGER AIRCRAFT Analytical pfediction and flqht test evaluation of Bell Developing error-free software p 201 A89-19679 Sizing up the 146-300 -._new commuteraircraft by British ACAP heliter cabin noise -.. Advanced Composite ONBOARD EQUIPMENT Aerospace p 161 A89-18346 Airframe Program p 164 A89-18911 Design of a cmfiable pnmary on-board aircraft weight CMl tiltrotor aircraft ~ A comparison of five candidate Experimental assessment of a turbulence ingestion and balance system designs p 163 A89-18882 noise theory p 203 A89-18912 [AIAA PAPER 88.39191 p 171 A89-18096 Project for an advanced regional transpod airuaft A comparison of acoustic predictions with model rotor Reflections on avionic integration [DGLR PAPER 87-0791 p 167 A89-20236 test data from the NASA 14 x 22 11 wind tunnel [AIAA PAPER 88.39501 P 172 A89-18121 PAYLOADS Internal pressure measurements for a liquid payload at p A89-18913 On-board expert diagnostics for an avionics 203 low Reynolds numbers An analytical model for the prediction of MRlTR subsystem P 202 N89-14758 [AD-A197438] p 191 N89-13727 interaction noise --- main rotorftail rotor Avionics fault tree analysis and artificial intelligence for future aircraft maintenance P 202 N89-14760 PEEK p 165 A89-18931 Buckling and final failure of graphite/PEEK stiffener Detaileddesign specification for a prototypeAssessment OPERATING SYSTEMS (COMPUTERS) Ada executive for distributed avionics processing sections p 190 A89-19911 System lor Aircraft Noise (ASAN) PERFORMANCE PREDICTION [ADA1979361 p 204 N89-14818 [AIAA PAPER 88-40421 p200 A89-18166 OPTICAL EQUIPMENT Comparisons of predicted and measured rotor NOISE REDUCTION One million pixel full color liquid crystal display for performance in hover using a new free wake analysis Fan acoustic modes measuring system avionics applications p 165 A89-18933 p 183 A89-19950 [AIAA PAPER 88-39671 p 173 A89-18134 Performance prediction analysis for fully deployed NASAlAHS rotorcraft noise reduction program - Optical fire detector testing in the aircraft engine nacelle parachute canopies p 155 A8920314 McDonnell Douglas Helicopter Company fire test simulator Hub loads analysis of the SA34912 helicopter accomplishments p 143 A89-20747 [AD-A197974] P 168 N89-13427 [NASA-TM-101061I p 153 N89-13410 Effect of advanced component technology on helicopter OPTIMAL CONTROL Predictions of airfoil aerodynamic performance transmissions Design of multi-level flight control systems degradation due to icing [NASA-TM-101431] p 193 N89-13794 P 181 A89-19813 [ NASA-TM-IOt434l p 153 N89-13412 A-16 SUBJECT INDEX RAMJET ENGINES

Flight measured and calculated exhaust jet conditions Theoretical derivation and calibration technique of a A potential flow solution on marine propeller and axial lor an F100 engine in an F-15 airplane hemispherical-tipped,five-hole probe rotating fan [NASA-TM-100419] p 177 N89-13435 [NASA-TM-4047J p 151 N89-13396 [AD-A198781 J p 191 N89-13735 Development of thermomechanical life prediction A potential flow solution on marine propeller and axial PROPELLERS models for thermal barrier coatings p 186 N89-13643 rotating Ian Euler analysis of a swirl recovery vane design for use PERFORMANCE TESTS [AD-A198781] p 191 N89-13735 with an advanced single-rotation propfan Vibration, performance. flutter and forced response POWDER METALLURGY [AIAA PAPER 88-31521 p 144 A89-17940 characteristics of a large-scale proplan and its aeroelastic PM AI alloys - Hot prospects lor aerospace Frequency-domain method for the computation of model applications p 155 A89-17622 propeller acoustics p 203 A89-19902 [AIAA PAPER 88-31551 p 176 A89-17943 PRECIPITATION HARDENING Laser velocimeter measurements of the flowfield PM AI alloys Hot prospects lor aerospace Optical fire detector testing in the aircraft engine nacelle - generated by an advanced countenotating propeller applications p 185 A89-t7622 tire test simulator [ NASA-TM-1014371 p 153 N89-13409 PRESSURE DlSTRlBUTlON [ AD-A1979741 p 168 N89-13427 A potential flow solution on marine propeller and axial Computation of the pressure in an incompressible Flight measured and calculated exhaust iet COndiOnS rotatinal llow of inviscid fluid p 143 A89-17150 rotating fan [AD-A198781] p 191 N89-13735 for an F100 engine in an F-15 airplane Low-speed pressure distribution on axisymmetric [NASA-TM-100419] p 177 N89-13435 elliptic-nosed bodies p 149 A89-20147 High lift, low pitching moment airfoils Effect of advanced component technology on helicopter Unsteady low-speed windtunnel test of a straked delta [NASA-CASE-lAR-13215-1] p 154 N89-14224 transmissions wing, oscillating in pitch. Part 5 Power spectral density Parametric studies of advanced turboprops [NASA-TM-101431] p 193 N89-13794 plots of the overall loads for harmonic oscillation and the [ NASA-TM-1013891 p 195 N89-14465 Fabrication and testing of lightweight hydraulic system response of overall loads to (1-COS) inputs Users' manual for the Langley high speed propeller noise simulator hardware. Phase 2: Addendum [AD-A198683] p 152 N89-13403 prediction program (DFP-ATP) [ AD-A1985241 p 184 N89-14243 PRESSUREDRAG [NASA-CR-4208] p 204 N89-14820 PHASE SHIFT KEYING Dynamic stall computations using a zonal Navk-Stokes PROPULSION SYSTEM CONFIGURATIONS Irreducible error rate in aeronautical satellite channels model Advanced transmission studies p 189 A89-18906 p 157 A89-17183 [AD-A197942) p 194 N89-14397 Development 01 ram propulsion lor flight vehicles PHASEDARRAYS PRESSURE GRADIENTS [DGLR PAPER 87-1011 p 176 A89-20240 GaAs MMlCs satisty EW requirements Interactions between turbulent wakes and boundary PROPULSION SYSTEM PERFORMANCE p 188 A89-18757 layers p 150 A89-20182 Energy management for integrated flight and propulsion PHOTOCHEMICAL REACTIONS PRESSUREMEASUREMENT control systems Atmospheric photochemical modeling of turbine engine The use of sweep-frequency excitation lor unsteady [AIAA PAPER 88-38731 p 178 A89-18068 fuels and exhausts. Computer model development, volume pressure measurement --- in aerodynamics p 147 A89-18940 PULSE COMMUNICATION 1 Irreducible error rate in aeronautical satellite channels An investigation of wall interference correction to the [ AD-A1986901 p 196 N89-13832 p 157 A89-17183 pressure measurement In !ow speed wind tunnel with solid Atmospheric photochemical modeling of turbine engine walls p 183 A89-19808 Air traffic control (ATC) and airlground digital fuelsand exhausts. Computer model development. volume Internal pressure measurements lor a liquid payload at communications - Demonstration and evaluation 2 low Reynolds numbers [AIM PAPER 88-39981 p 158 A89-18154 [AD-A198691I p 196 N89-13833 [ AD-AI 97438 1 p 191 N89-13727 The future of aeromobile digital communications PILOT PERFORMANCE PRESSURE OSCILLATIONS [AIM PAPER 88-4001 I p 158 A89-18156 Autonomous RPRV navigation. guidance and control Unsteady low-speed windtunnel test of a straked delta Inter-partition data integrity in the asynchronous DATAC [NASA-CR-l79425] p 161 N89-14228 wing, oscillating in pitch. Part 4 Plots of time histories of environment PIPES (TUBES) pressures and overall loads [AIM PAPER 88-40101 p200 A89-18160 Buckling characteristics of hypersonic aircraft wing [ AD-A1986821 p 152 N89-13402 Aeronautical satellite networks p 160 A89-20117 tubular panels PRESSURE RATIO [NASA-TM-87756] p 193 N89-13816 Advanced core technology: Key to subsonic propulsion PISTON ENGINES benefits Q Engines lor Mini-RPV XM-1A [ NASA-TM-101420] p 178 N89-14237 [AD-A1983361 p 178 N89-14236 PRESSUREREQULATORS OUALlFlCATlONS PITCHING MOMENTS Modem digital pressure control system T55-L-714 engine development and qualification: Tip High lift, low pitching moment airfoils [AIM PAPER 88-39481 p 172 A89-18119 clearance analysis [NASA-CASE-LAR-13215-1] p 154 N89-14224 PRESSURESENSORS [ AD-A1988491 p 177 N89-13431 PLANNING meoretical derivation and calibration technique of a OUALITV CONTROL Terminal area forecasts: Fiscal years 1988-ZOO0 hemispherical-tippad. fivehole probe The development and application of software quality [ADA1980791 p 156 N89-13419 [NASA-TM-4047] p 151 N89-13396 indicators PLANT DESIGN PROBABILITY MNSITY FUNCTIONS [AIM PAPER 88-39461 p201 A89-19660 Gwnwsis ui a iiwxkia iuiiiiiiy ceiiiei I_c%!ea_rfyIew-cyd windtunnel test of a straked delta p 189 A89-18894 wing, oscillating in pitch. Part 5: Power spectral density PLASMA SPRAYING plots of the overall loads for harmonic oscillation and the R Thermal Barrier Coatings. Abstracts and figures response of werall loads to (1-COS) inputs [NASA-CP-10019] p 185 N89-13642 [ AD-A198683 ] p 152 N89-13403 RADAR An investigation 01 environmental influence on the creep PRODUCT DEVELOPMENT Analysis of temperature and velocity microturbulence behavior 01 a low pressure plasma sprayed NiCoCrAlY Air-to-air combat helicopter development parameters from aircraft data and relationship to alloy p 186 N89-13648 p 165 A89-18929 atmospheric refractive index structure PLATES (STRUCTURAL MEMBERS) PRODUCTION ENGINEERING [AD-AI 965421 p 196 N89-13854 Temperature effect on stress concentration around Genesis of a flexible turning center RADAR APPROACHCONTROL circular hole in a composite material specimen p 189 A89-18894 Precision approach radars Twenthe and Volkel representative of X-29A forward-swept wing aircraft Automated wire preparation system (Nethedands). Multipath propagation problems [NASA-CR-l79439] p 194 N89-14456 p 189 A89-18895 [FEL-1988-15] p 193 N89-14372 PLENUM CHAMBERS The combination of simulation and response RADAR DETECTION Plenum chamber effect on wind-tunnel resonance by methodology and its applicationin an aggregate production Combined numerical and symbolic processing for the finite4ement method p 190 A89-19909 plan pl90 A89-19806 airborne suweillance PLOlTING PROGRAMMING LANGUAGES [AIAA PAPER 88-39851 p 157 A89-18143 Plotting component maps in the Navy/NASA Engine Use of the GALA and PALAS tools to enhance the RADAR EOUIPMENT Program (NNEP): A method and its usage development of avionic software Optimization of algorithms for data processing in radar [NASA-TM-101433] p 178 N89-14239 [AIM PAPER 88-39431 p 199 A89-18115 altimeters with electronic stabilization of the radiation pattern p 174 A89-18401 PLY ORIENTATION PROLATE SPHEROIDS RADIO ALTIMETERS Processing composite finite element model with Vortical wakes over a prolate spheroid Optimization of algorithms lor data processing in radar CADCOMP -- lor aircraft structures p 166 A89-19982 p 150 A89-20181 POISSON DENSITY FUNCTIONS altimeters with electronic stabilization 01 the radiation The nature 01 the aircraft component failure process: PROP-FAN TECHNOLOGY pattern p 174 A89-18401 Euler analyss of a swirl recovery vane design for use A working note RADIO NAVIGATION with an advanced single-rotation propfan [AD-A1979791 p 169 N89-14234 Radionavigationneeds for the Europe of the future [AIAA PAPER 88-31521 p 144 A89-17940 POISSON EQUATION p 160 A89-18753 The nature of the aircraft component failure process: Experimental investigation of propfan aeroelastic Omega Navigation System - A status report A working note response in ofl-axis flow with mistuning p 160 A89-19867 [AD-A1979791 p 169 N89-14234 [AIM PAPER 88-31531 p 175 A89-17941 An oveMew of space-based radionavigation systems POLLUTION TRANSPORT PROPELLER BLADES An overview of the Federal Radionavigationp 160 A89-20122 Plan Three dimensional hazard zones p 195 A89-18259 Vibration, performance. flutter and forced response POLYMERIC FILMS characteristics of a large-scale propfan and its aeroelastic p 160 A89-20123 A fundamental approach to the sticking 01 insect model RAIN EROSION residues to aircraft wings [AIM PAPER 88-31551 p 176 A89-17943 Advancements in erosion testing 01 rotor blade leading [NASA-CR-183041] p 156 N89-13414 PROPELLER FANS edges p 163 A89-18888 POTENTIAL FLOW Aeroelastic response 01 metallic and composite propfan RAMJET ENGINES Analysis of artificial dissipation models for the transonic models in yawed flow Development 01 ram propulsion for flight vehicles fullpotential equation p 191 A89-20188 [AIAA PAPER 88-31541 p 175 A89-17942 [DGLR PAPER 87-1011 p 176 A89-20240

A-17 REACTIVITY SUBJECT INDEX

Fire extinguishingagent evaluation in the Aircraft Engine RETRACTABLE EQUIPMENT ROTATING SHAFTS Nacelle Fire Test Simulator (AENFTS) New design procedures applied to landing gear Modal analysis of continuous rotor-bearing systems [ AD-A1985231 p 157 N89-14227 development p 167 A89-20138 p 188 A89-18766 REACTIVITY REUSABLE SPACECRAFT ROTATION

Atmospheric photochemical modeling of turbine engine The X-20 space plane ~ Past innovation. future vision A potential flow solution on marine propeller and axial fuels and exhausts. Computer model development, volume [IAF PAPER 88-5981 p 204 A89-17867 rotating fan 1 REVERSED FLOW [AD-A198781] p 191 N89-13735 [ AD-A1986901 p 196 N89-13832 Thrust-reverser flow investigation on a twin-engine ROTOR AERODYNAMICS REAL TIME OPERATION transport AHS. Annual Forum, 44th. Washington. M). June 16-18, Universal Ada Test Language (UATL) to support [ NASA-TP-28561 p 153 N89-14213 1988, Proceedings p 141 A89-18851 real-time softwarelsystem integration and RIGID ROTORS Free wake calculation of rotor flow fields for interactional Iactorylmaintenancefault isolation p 197 A89-18009 Aeroelestic optimization of a helicopter rotor aerodynamics p 145 A89-18853 Real-time flight test analysis and display techniques for p 163 A89-18898 Rotorlairframe interactions on tiltrotor aircraft the X-29A aircraft Dynamics of a rigid rotor mounted on discontinuously p 161 A89-18854 [NASA-TM-101692] p 168 N89-13424 Rotor inflow variability with advance ratio non-linear elastic supports p 190 A89-19125 RECONNAISSANCE AIRCRAFT p 145 A89-I8855 Fiber optic applications lo the high altitude Calculation of the steadily periodic and gust responses A correlation study of rotor inflow in forward flight of a hingeless rotor helicopter using two-dimensionaltime reconnaissance vehicle p 145 A89-18856 [AIAA PAPER 88-39301 p 187 A89-18104 domain unsteady aerodynamics p 182 N89-14240 An entropy and viscosity corrected potential method for RECTANGULAR WINGS RING STRUCTURES rotor performance prediction p 145 A89-18857 Coupling linearized far-field boundary conditions with Optical fiber data transfer system An examinationof some rotor aerodynamic models using nonlinear near-field solutions in transonic flow [ NASA-CR-1817041 p 194 N89-14376 the RSRAlX-wing model test data p 146 A89-18858 [ AD-A19872 1] p 153 N89-13405 ROBOTICS Dynamic characteristics of advanced bearingless rotors REDUNDANCY Robotic deburring of complex machined parts at McDonnell Douglas Helicopter Company Sensor failure detection for jet engines p 190 A89-18936 p 164 A89-18899 [ NASA-TM-I01 3961 p 177 N89-13432 ROBUSTNESS (MATHEMATICS) A unifiedtheweticalcomputational approach for viscous REENTRY VEHICLES Reduced conservative singular value analysis for unsteady rotor aerodynamics p 146 A89-18917 The X-planes: X-1 to X-31 (2nd revised and enlarged robustness p 197 A89-17489 Comparisons of predicted and measured rotor edition) --- Book p 205 A89-20251 ROLLING CONTACT LOADS performance in hover using a new free wake analysis REFRACTIVITY Dynamic tirelsoil contact surface interaction model for p 165 A89-18933 Analysis of temperature and velocity microturbulence aircraft ground operations p 155 A89-20320 Three-dimensional interactive system identitication of parameters from aircraft data and relationship to ROTARYGYROSCOPES helicopter rotorlbody dynamics p 165 A89-18938 atmospheric refractive index structure Modal analysis of continuous rotor-bearing systems Dynamic inflow for practical applications [ AD-A1965421 p 196 N89-13854 p 188 A89-18766 p 147 A89-19625 RELAXATION METHOD (MATHEMATICS) Hub loads analysis of the SA34912 helicopter Multigrid acceleration of a relaxation procedure for the ROTARY STABILITY The measurement and prediction of rotordynamicforces [NASA-TM-101061] p 153 N89-13410 reduced Navier-Stokes equations p 148 A89-19904 The measurement and prediction of rotordynamic forces for labyrinth seals RELIABILITY ANALYSIS for labyrinth seals [AD-A1971851 p 192 N89-13784 An approach to solving large reliability models [AD-A197185] p 192 N89-13784 [AIM PAPER 86-39051 p 199 A89-18086 ROTARY WING AIRCRAFT ROTORBLADES Modeling mission reliability of advanced integrated Rotor system evaluation. phase 1 Experimental verification of helicopter blade designs communication. navigation, identification avionics [AD-A1987941 p 168 N89-13425 optimized for minimum vibration p 162 A89-18874 systems Two-dimensional aerodynamic characteristics of the Structural dynamics of a helicopter rotor blade system [AIM PAPER 88-40231 p 173 A89-18174 OLSlTAAT airfoil p 162 A89-18878 A 'new' philosophy of structural reliability, fail safe versus [NASA-TM-89435] p 154 N89-14216 Design and fabrication of an advanced light rotor safe life p 188 A89-18852 High lift, low pitching moment airfoils p 163 A89-18880 REMOTELY PILOTED VEHICLES [NASA-CASE-lAR-13215-1] p 154 N89-14224 Advancements in erosion testing of rotor blade leading The Pointer - A revolutionary idea to improve RPV ROTARY WINGS edges p 163 A89-18888 capabilities p 163 A89-18881 Rotor inflow variability with advance ratio Achieving reliability and maintainability goals with a Autonomous RPRV navigation. guidance and control p 145 A89-18855 composite main rotor blade p 189 A89- t 8892 [NASA-CR-1794251 D 161 N89-14228 Experimental verification of helicopter blade designs Tip loss and blade strike simulations using DYSCO Engines for Mini-RPV XM-1A optimized for minimum vibration p 162 A89-18874 p 164 A89-18901 [AD-A1983361 p 178 N89-14236 Structural dynamics of a helicopter rotor blade system Tip-path-plane angle effects on rotor blade-vortex REQUIREMENTS p 162 A89-18878 interaction noise levels and directivity An empirical look at tolerances in setting icing test Achieving reliability and maintainability goals with a p 203 A89-18914 conditions with particular application to icing similitude composite main rotor blade p 189 A89-18892 Improvements to transonic flowfield calculations [AD-A198941] p 156 N89-13418 NOTAR hybrid cornpositelmetal fan blade p 146 A89-18915 RESEARCH p 163 A89-18893 A parallel architecture for a real-time blade element Rotor system evaluation. phase 1 Aeroelastic optimization of a helicopter rotor rotorcraft simulation p 201 A89-19560 [ AD-A1987941 p 168 N89-13425 p 163 A89-18898 Strength of dynamically loaded force introduction for The Center of Excellence in Rotary Technology at Analytical determination and experimental companson fiber-reinforced rotors Rensselaer Polytechnic Institute of performance degradation on a helicopter main rotor [DGLR PAPER 87.1081 p 185 A89-20243 [AD-A198964] p 168 N89-13426 due to ice accretion p 155 A89-18909 ROTOR BLADES (TURBOMACHINERY) RESEARCH AIRCRAFT A comparison of acoustic predictions with model rotor Measurement and analysis of unsteady flow structures Triplex digital flight control system for the STOL research test data from the NASA 14 x 22 ft wind tunnel in rotor blade wakes p 147 A89-18946 aircraft 'Aska' p 203 A89-18913 Turbine design using complex modes and [AIAA PAPER 88-38831 p 179 A89-18077 Improvements to transonic flowfield calculations WbStNCturing p 190 A89-19718 Application of digital technology lo aircraft utility p 146 A89-18915 Optimization of mistuned blade rotor for controlling systems An evaluation of a Navier-Stokes code for calculations flutter p 176 A89-19793 [AIAA PAPER 88-38721 p 180 A89-18114 of retreating blade stall on a helicopter rotor Effect of blade mistuning and bladedisk on cascade The X-planes: X-1 to X-31 (2nd revised and enlarged p 146 A89-18916 fluner boundaries p 176 A89-19803 edition) --- Book p 205 A89-20251 Application of damage tolerance methodology to Optical fiber data transfer system RESEARCH ANDDEVELOPMENT helicopter dynamic components using the example of a [NASA-CR-181704] p 194 N89-14376 The X-planes: X-1 to X-31 (2nd revised and enlarged main rotor pitch link for the AH-1S helicopter ROTOR BODY INTERACTIONS edition) .-_Book p 205 A89-20251 p 164 A89-18921 Rotorlairframe interactions on tiltrotor aircraft RESEARCH FACILITIES Environmentally induced cracking in aluminum p 161 A89-18854 Equipment to upgrade the facilities of the IIT (Illinois p 185 A89-18925 An examination of some rotor aerodynamic models using Institute of Technology) Fluid Dynamics Research Matrix analysis method for composite flexbeam the RSRAlX-wing model test data p 146 A89-18858 Center p 190 A89-18926 Bearinglessrotors and higher harmonic control modeling [AD-A198084] p 184 N89-14242 An analytical model for the prediction of MRlTR using RACAP p 162 A89-18876 RESEARCH MANAGEMENT interaction noise --- main rotorltail rotor Early jet engines and the transition from centrifugal to Design of a simple active controller to suppress p 165 A89-18931 helicopter air resonance p 162 A89-18877 axial compressorr: A case study in technological change Comparisons of predicted and measured rotor [AD-A198775] p 177 N89-13430 performance in hover using a new free wake analysis Three-dimensional interactive system identification of helicopter rotorlbody dynamics p 165 A89-18938 RESIDUES p 165 A89-18933 Aviation fuel lubricity evaluation Navier-Stokes calculations of hovering rotor flowfields ROTOR SPEED [ADA1981 971 p 177 N89-13434 [AIM PAPER 87-26291 p 149 A89-20133 Dynamics of a rigid rotor mwnted on discontinuously RESONANT FREQUENCIES Strength of dynamically loaded force introduction for non-linear elastic supports p 190 A89-19125 Investigation of difficult component effects on FEM fiber-reinforced rotors ROTORCRAFT AIRCRAFT vibration prediction for the AH-1G helicopter [DGLR PAPER 87-1081 p 185 A89-20243 Integrated diagnostic Concepts for advancedtechnology p 162 A89-18879 ROTATING DISKS rotorcraft p 141 A89-18023 Plenum chamber effect on wind-tunnel resonance by Stress intensity factors for periodic radial cracks in a Application of AI technology lo time-critical functions the finiteelement method p 190 A89-19909 rotating disc p 187 A89-17448 [AIM PAPER 88-40301 P 174 A89-18190 RESOURCE ALLOCATION ROTATING FLUIDS Air combat tactics for the evaluation of rotorcraft An overview of SEDACS - A state of lhe art TRDlTPS Computation of rotational transonic flows using a characteristics in the low air war of 2010 environment p 198 A89-18030 decomposition method PI50 A89-20179 P 142 A89-18859 SUBJECT INDEX SPATIAL MARCHING

Tip loss and blade strike simulations using DYSCO SHEARLAYERS Software development for large scale avionic integration p 164 A89-18901 Computational analysis of unsteady supersonic cavity programs p 200 A89-18864 The impact of yaw axis control modes, flight directors flows driven by thick shear layers p 145 A89-18803 Developing error-free software p 201 A89-19679 and automatic control coupling on decelerating IFR SHEARSTRESS The development and application 01 software quality approaches for rotorcraft p 180 A89-18903 Nondestructive testing of composite aircraft structures indicators Rotorcraft aeromechanical analysis using a nonlinear with infrared and shearographic imaging technologies [AIAA PAPER 88.39461 p201 A89-19860 unsteady aerodynamic model p 146 A89-18919 p 189 A89-18891 Comparison of FAA DO-178A and DOD-STD-2167A A parallel architecture for a real-time blade element SHELTERS approaches lo software certification Avionics testing in the military bare-base environment rotorcraft simulation p 201 A89-19560 [AIM PAPER 88-40441 p 142 A89-19864 p 141 A89-18011 NASAIAHS rotorcraft noise reduction program - SOITWARE TOOLS McDonnell Douglas Helicopter Company SHOCK TUNNELS A study on hypersonic shock tunnel Interfacing Sensor assemblies with windowless cwkpit accomplishments p 143 A89-20747 displays p 187 A89-17979 ROTORS p 148 A89-20132 SHOCK WAVE INTERACTION Universal Ada Test Language (UATL) lo support Modal analysis of continuous rotor-bearing systems real-time softwarelsystem integration and p188 A89-18766 A study on aerodynamic heating in the interaction regions of shock waves and turbulent boundary layers induced factorylrnaintenance fault isolation p 197 A89-18009 Rotor system evaluation. phase 1 ATE hardware diagnostics, fault detection, and fault [AD-A198794] p 168 N89-13425 by sharp fins p 148 A89-20131 isolation tool (Self-test adapter) p 197 A89-18015 An experimentaland analytical evaluation of the tapered SHOCK WAVE PROPAGATION Convective heat transfer in a boundary layer behind a tension-torsion strap concept A structured approach lo system design [ NASA-TM-1010491 p 191 N89-13746 shock wave propagating along a flat plate with a sharp [AlAA PAPER 88-38671 p 198 A89-18064 The effects of inlet turbulence and rotorlstator leading edge - A calculation method and a comparison Avionics failure propagation analysis tool interactions on the aerodynamics and heat transfer of a with experimental data p 144 A89-18546 [AIM PAPER 88-38681 p 198 A89-18W5 large-scale rotating turbine model, volume 1 SHORT TAKEOFF AIRCRAFT Use of the GALA and PALAS tools to enhance the [NASA-CR-4079] p 192 N89-13756 Triplex digital flight control system for the STOL research development of avionic software aircraft 'As& Two-dimensional aerodynamic characteristics 01 the [AIAA PAPER 8849431 p 199 A89-18115 [AIM PAPER 88.38831 p 179 A89-18077 OLS/TAAT airfoil An automated methodology for partitioning software [NASA-TM-89435] p 154 N89-14216 SIDESLIP functions in a distributed avionics architecture The relationship between the aerodynamic Numerical simulation and comparison of [AIAA PAPER 88-39711 p 199 A89-18137 characteristics of double-delta wings and vortices with symmetricallsupercritical airfoils lor the near tip region of sideslips at high angles 01 attack p 148 A89-19801 SOLID-SOLID INTERFACES a helicopter in forward flight SIGNAL FADING A study of contact interaction in aircraft structural [NASA-CR-4212] p 204 N89-14821 Irreducible error rate in aeronautical Satellite channels elements p 188 A89-18644 p 157 A89-17183 SOLUTIONS S SIGNAL PROCESSING Solution and sensitivity analysis of a complex A parallel modular signal processor !rsnscendental eigenproblem with pairs of real SAFETY [AIAA PAPER 88-3981 1 p 199 A89-18141 eigenvalues Evaluation of the improved OV-1D anti-icing system Optical fiber data transfer system [NASA-CR-162241] p 193 N89-13819 [ AD-A1984381 p 156 N89-14225 [ NASA-CR-1817041 p 194 N89-14376 SONIC BOOMS SANDS SIKORSKY AIRCRAFT Detaileddesign specification fora prototype Assessment Dual centrifugal compressors - The helicopter solution Evolution of the ACAP crash energy management System for Aircraft Noise (ASAN) to sand and ice ingestion p 176 A89-18908 system p 164 A89-18923 [ ADA1 979361 p204 N89-14818 SATELLITE COMMUNICATION SILICON CARBIDES SOUNDGENERATORS Irreducible error rate in aeronautical satellite channels Chemical vapor deposition of oxidation resistant HfB2 Contributions lo the theory of sound production by p 157 A89-17183 + Sicomposite coatings p 185 A89-19481 vortex-airfoil interaction. with application to vortices with SATELLITE DESIGN SIMULATION finite axial velocity defect p 203 A89-19672 Aeronautical satellite networks p 160 A89-20117 Lightning simulation test technique evaluation SOUND PRESSURE SATELLITE NETWORKS [WTIFAA/CT-87/38] p 156 N69-13415 The eflects of nonlinear damping on the large deflection Low-orbit navigation concepts p 184 A89-19870 Investigation01 a moving-modeltechnique lor measuring response of structures subjected lo random excitation Aeronautical satellite networks p 160 A89-20117 ground effect p 193 N89-13796 SCALE MODELS [ NASA-TM-40801 p 154 N89-14217 Users' manual for the Langley high speed propeller noise Testing and correlation on an advanced technology, Fire extinguishing agent evaluation in the Aircraft Engine prediction program (DFP-ATP) bearingless rotor p 182 A89-18900 Nacelle Fire Test Simulator (AENFTS) [ NASA-CR-42081 p 204 N89-14820 SCOOPS [AD-A198523] p 157 N89-14227 SOUND TRANSMISSION Rotating air scoop as airfoil boundaty-layer control Simulation 01 3-D viscous flow within a multi-stage Influence of a floor on sound transmission into an aircraft p 150 A89-20149 turbine fuselage model p 166 A89-20135 SEATS [NASA-TM-1013761, p 176 N89-14238 Acoustic transmissibility of advanced turboprop aircraft The development 01 the V-22 Osprey armored use oi iine ieririiiiai Aa8 S;mda;ioii SL.st:en ;TAPS: wifiiionj ;2c4 AB!? ?"!".3 energy-absorbing crewseat assembly lo study microburst wind shears p 197 N89-14699 Sound attenuation and speech transmission quality of p 155 A89-18883 SIMULATORS five types of headsets SECONDARYRADAR Optical fire detector testing in the aircraft engine nacelle [ IZF-1987-23I p 193 N89-14373 Data link organization in Mode S secondary surveillance fire test simulator SPACE ENVIRONMENT SIMULATION

radar systems ~ Operational compatibility with other Mode [ AD-A1979741 p 168 N89-13427 New application possibilities for balloon-borne case S systems Fire extinguishingagent evaluation in the Aircraft Engine studies . MIKROBA (Microgravity by balloons) [AIAA PAPER 88-40031 p 159 A89-18157 Nacelle Fire Test Simulator (AENFTS) [DGLR PAPER 87-0691 p 184 A89-20233 SELF TESTS [ AD-AI985231 p 157 N89-14227 SPACE FLIGHT ATE hardware diagnostics. fault detection. and fault Fabrication and testing of lightweight hydraulic system Yearbook 1987 II; DGLR. Annual Meeting, Berlin, isolation tool (Sell-test adapter) p 197 A89-18015 simulator hardware. Phase 2 Addendum Federal Republic of Germany, Oct. 5-7. 1987. Reports A simulation-basedfault injection experiment to evaluate [AD-A1985241 p 184 N89-14243 p 142 A89-20226 self-test diagnostics for a fault-tolerant computer SINGLE STAGE TO ORBIT VEHICLES SPACE NAVIGATION [AIAA PAPER 88.38971 p 198 A89-18083 Conceptual study of turbo-engines for horizontal takeoff An overview of space-based radionavigation systems SENSITIVITY and landing space plane p 160 A89-20122 Solution and sensitivity analysis of a complex [IAF PAPER 88-2531 p 184 A89-17745 SPACE SHUlTLES transcendental eigenproblem with pairs of real SINGULARITY (MATHEMATICS) Developing error-free software p 201 A89-19679 eigenvalues Reduced conservative singular value analysis for SPACETRANSPORTATIONSYSTEM [NASA-CR-182241] p 193 N89-13819 robustness p 197 A89-17489 Design and integration 01 air-breathing propulsion SEPARATED FLOW SLENDER BODIES systems of space transports and hypersonic aircraft Calculation of the unsteady aerodynamic characteristics Experimental study on low-speed aerodynamic [DGLR PAPER 87-1031 p 176 A8920241 of bodies in the case of separated flow characteristics of non-axisymmetric slender bodies SPACECRAFT CONFIGURATIONS p 144 A89-18355 p 151 A89-20635 Numerical methods for hypersonic flows Self-similar problem of the separated flow of an ideal SLENDER WINGS [DGLR PAPER 87-0841 p 150 A89-20235 fluid past an expanding plate p 144 A89-18669 Optimizationof slender wings for center-of-pressureshift SPACECRAFT PROPULSION Vortical wakes over a prolate spheroid due to change in Mach number p 154 N89-14897 Design and integration 01 air-breathing propulsion p 150 A89-20181 SMOKE systems of space transports and hypersonic aircraft Flow unsteadiness considerations in high-alpha testing Method of cold smoke generation for vortex core [DGLR PAPER 87-1031 p 176 A89-20241 p 151 A89-20319 tagging p 191 A89-20324 SPAREPARTS Management and control of separation by unsteady and SNOW US Army aircraft combat rnaintenancelbanle damage vortical flows Dolphin eats snow --- helicopter engine surge during repair program p 142 A89-18860 [AD-A198902] p 191 N89-13736 flight in snowfall p 155 A89-18910 SPARKS SERVICE LIFE SOFWARE ENGINEERING Measurements in the field of a spark excited High time sewice evaluation of thermal barrier coatings SDAR - A high produclivily software engineering compressible axisymmetric jet p 203 A89-18948 on the Rolls-Royce RE211 engine p 186 N89-13660 environment for embedded systems --- System Design SPATIAL MARCHING SHARP LEADING EDGES Automation Resources Spatial marching techniques for approximatc solutions Convective heat transler in a boundary layer behind a [AIAA PAPER 88-38651 p 198 A89-18062 to the hypersonic blunt body problem shock wave propagating along a flat plate with a sharp On the effectiveness of multiersion Software in digital p 143 A89-17460

leading edge ~ A calculation method and a comparison avionics Computation 01 axisymmetric supersonic jet using space with expetimenlal data p 144 A89-18546 [AIAA PAPER 88-39031 p 199 A89-18111 marching technique p 145 A89-18750

A-19 SPECTRAL METHODS SUBJECT INDEX

SPECTRALMETHODS Application of damage tolerance methodology to Passive venting technique for shallow cavities Frequency-domain method for the computation of helicopter dynamic components using the example of a [NASA-CASE-LAR-13875-1 ] P 169 N89-14233 propeller acoustics p 203 A89-19902 main rotor pitch link for the AH-1S helicopter SUPERSONIC AIRFOILS SPEECH RECOGNITION p 164 A89-18921 Full-potential integral WlUtiOn for transonic flows with Sound attenuation and speech transmission quality of STRESSSTRAIN RELATIONSHIPS and without embedded Euler domains five lypes of headsets Constitwe modeling for isotropic materials P 148 A89-19908 [IZF-l987-23] p 193 N89-14373 [NASA-CR-1748051 p 177 N89-13436 SUPERSONIC FLOW SPHERICAL COORDINATES The effects of nonlinear damping on the large deflection Mathematical modeling of laminar and turbulent Transonic wing design using inverse methods in response of structures subjected to random excitation supersonic flow pas1 convex-concave bodies cuwilinear coordinates p 151 A89-20316 p 193 N89-13796 P 144 A89-18671 SPILLING STRUCTURAL ANALYSIS Computational analysis of unsteady supersonic cavity Three dimensional hazard zones p 195 A89-18259 A 'new'philosophy d structural reliability. fail safeversus flaws driven by thiik shear layers p 145 A89-18803 STABILITY safe life p 188 A89-18852 Analysis of a fighter lype aircraft configuration with the Design of feedback control systems for unstable plants Design, analysis, and test of composite fuel tank pods HISSS panel method at subsonic and supersonic with saturating actuators for the CH-46E helicopter p 163 A89-18885 speeds [NASA-CR-183392] p 194 N89-14377 COCOMAT, a CAE system for composite structures [DGLR PAPER 87-0851 P 147 A89-19660 STATIC TESTS design --- for aircraft p 166 A89-19981 SUPERSONIC JET FLOW Flow unsteadiness considerations in high-alpha testing Processing composite finite element model with Computation of axisymmetric supersonic let using space p 151 A89-20319 CADCOMP .--for aircraft structures p 166 A89-19982 marching technique p 145 A89-18750 STATISTICAL ANALYSIS New solution method for steady-state canopy structural SUPERSONIC NOZZLES Application of the mobility power flow approach to loads p 155 A89-20321 Time-iterative solutions of viscous supersonic nozzle structural response from distributed loading Rotor system evaluation, phase 1 flows p 150 A89-20184 [ NASA-CR-1813421 p 193 N89-13817 [ADA1987941 p 168 N89-13425 SUPERSONIC WIND TUNNELS STATISTICAL WEATHER FORECASTING Constitutive modeling for isotropic mateMls Determination of the perturbations of the flow fields of An automated method for forecasting the probability of [NASA-CR-1748051 p177 N89-13436 supersonic wind tunnels from measured aerodynamic clear air turbulence p196 A89-18554 The quality of fibre reinforced thermoplastics coefficients p 144 A89-18675 STATORS mouldings p 196 N89-13839 SUPPORT INTERFERENCE The effects of inlet turbulence and rolorlstator Parametric studies of advanced turboprops Interference effects associated with a plate-supported interactions on the aerodynamics and heat transfer of a [ NASA-TM-1013891 p 195 N89-14465 half-model in hypersonic flow p 148 A89-19924 large-scale rotating turbine model. volume 1 STRUCTURAL DESIGN SURFACEENERGY [NASA-CR-40791 p 192 N89-13756 Optimal design of an advanced composite rotating A fundamental approach to the sticking of insect The measurement and predictii of rotordynamicfwces flexbeam p 189 A89-18884 residues to aircraft wings for labyrinth seals Selection of the optimal liihter-than-air gas for airship [NASA-CR-l83041I p 156 N89.13414 [ADA1971 851 p 192 N89-13784 and a scheme of double-layer structural design SURFACE FINISHING STEADYSTATE p 166 A89-19809 Robotic debuning of complex machined parts T55-L-714 engine development and qualiiition: Tip A method of computer aided design of structural type p 190 A89.18936 clearance analysis - An application of expert system and fuzzy sets theory SURVEILLANCE [ AD-A1988491 p 177 N89-13431 p 201 A89-19811 Automatic dependent surveillance data transfer STEREOSCOPIC VISION Design studies of primary aircraft structures in ARALL [AIAA PAPER 88-39971 p 159 A89-18180 Stereoscopic 3-D displays for cockpits laminates p 167 A89-20318 The unused strategic tool - The airship [AIAA PAPER 88-38871 p 170 A89-18080 The effects of leading edge and downstream film cooling p 161 A89-18752 STIFFENING on turbine vane heat transfer SWEEP FREQUENCY Buckling and final failure of graphite1PEEK stiffener [ NASA-CR-1821331 p 192 N89-13754 The use of sweepfrequency excitation for unsteady sections p 190 A89-19911 LDV measurements in an annular combustor model pressure measurement --- in aerodynamics STRAIN MEASUREMENT [ NASA-CR-1822071 p 192 N89-13755 p 147 A89-18940 Nondestructive testing of composite aircraft structures STRUCTURAL DESIGN CRITERIA SWEPT WINGS with infrared and shearographc imaging technologies New design procedures applied to landing gear Static aeroelastic characteristics of circulation control p 189 A89-18891 development p 167 A89-20138 wings p 167 A89-20144 Efficient load measurements using singular value STRUCTURAL INFLUENCE COEFFICIENTS SWEPTBACK WINGS decomposition Efficient load measurements using singular value Vortex breakdown measurements on a 70 dag [ NASA-CR-1846141 p 202 N89-14795 decomposition sweepback delta wing p 150 A89-20312 STRAKES [ NASA-CR-1846141 p 202 N89-14795 SWIRLING Unsteady low-speed windtunnel test of a straked delta STRUCTURAL VIBRATION Euler analysls of a swirl recovery vane design for use wing, oscillating in pitch. Part 4: Plots of time histories of Helicopter vibrabon analysis and control with an advanced single-rotation propfan pressures end overall loads p 188 A89-18871 [AIAA PAPER 88.31521 p 144 A89-17940 LAD-A1986823 p 152 N89-13402 Investigation of diiicult component effects on FEM SYMBOLIC PROGRAMMING Unsteady low-speed windtunnel test of a straked delta vibration prediction for the AH-1G helicopter Combined numerical and symbolic processing for wing, oscillating in pitch. Part 5: Power spectral density p 162 A89-18879 airborne surveillance plots of the overall loads for harmonic oscillation and the SUBSONIC FLOW [AIAA PAPER 88-39851 p 157 A89-18143 response of overall loads to (1COS) inputs Analysis of a fighter type aircraft configuration with the SYSTEM FAILURES [ADA1986831 p 152 N89-13403 HISSS panel method at subsonic and supersonic Effect of model uncertainty on frulure detection - The Unsteady low-speed windtunnel test of a straked delta speeds threshold selector p 197 A89-17965 wing, oscillating in pitch. Part 6: Presentabon of the [DGLR PAPER 870851 p 147 A89-19660 SYSTEM IDENTIFICATION visualization program A new approach for computing full unsteady Three-dimensional interactive system identification of [ADA1986841 p 152 N89-13404 aerodynamic characteristics p 147 A89-19788 Micopter rotorlbody dynamics p 165 A89-18938 STRAPDOWN INERTIAL GUIDANCE Validation of approximate indicia1aerodynamic functions SYSTEMS ANALYSIS Optimal integration of inertial sensor functions for for two-dimensional subsonic flow p 149 A89-20140 Rotor system evaluation, phase 1 fliiht-control and avionics Numerical simulation of tip vortices of wings in subsonic [ AD-A1987941 p 168 N89-13425 [AIM PAPER 88-38781 p 170 A89-18072 and transonic flows p 150 A89-20176 SYSTEMS ENGINEERING Strapdown issues for airborne EO senm SUBSONIC SPEED Interfacing sensor assemblies with windowless cockpit [AIAA PAPER 88-39271 p 171 A8918102 Advanced wre technology: Key to subsonic propulsion displays p 187 A89-17979 STRAPS beWMS Modular avionics systems studies An experimentaland analytical evaluation of the tapered [NASA-TM-101 4201 p 178 N89-14237 [AIM PAPER 88-38501 p 169 A89-18052 tension-torsion strap concept SUBSONIC WIND TUNNELS Modular avionics systems architecture (MASA) -Seeds [NASA-TM-l01049] p 191 N89-13746 A comparison of acoustic predictions with model rotor of destruction or seeds of progress? STREAM FUNCTIONS (FLUIDS) test data from the NASA 14 x 22 ft wind tunnel [AIAA PAPER 88-3851I p 141 A89-18053 Interactions between turbulent wakes and boundary p 203 A89-18913 A structured approach to system design layers p150 A89-20182 Plenum chamber effect on wind-tunnel resonance by [AIAA PAPER 86-3@671 PI98 A89-18064 STRESS ANALYSIS the finitselement method p 190 A89-19909 A simplified aircraft collision avoidance system Aeroelastic response of metallic and composite propfan The 13-inch magnetic suspension and balance system [AIM PAPER 88-3961I p 173 A89-18128 wind Iunnel models in yawed flow The huh speed bus technology development program [AIM PAPER 88-31541 p 175 A89-17942 [ NASA-TM-40901 P 184 N89-14241 [AIM PAPER 88-40051 p 187 A89-18158 SUBSTRUCTURES An investifion of environmental influence on the creep Application of the mobility power flow approach to An SA€ huh speed ring bus overview behavior of a low pressure plasma sprayed NiCoCrAlY structural response frwn distributed loading [AIAA PAPER 88-40081 p 187 A89-18159 alloy p186 N89-13648 [NASA-CR-181342] p 193 N89-13817 The fiber optic data distribution network - A network STRESS CONCENTRATION SUPERCRITICAL AIRFOILS for nextgeneration avionics systems Temperature effect on stress concentration around Numerical simulation and comparison of [AIM PAPER 88-4011 I p 188 A89-18161 circular hole in a composite material specimen symmetrical/supercritical airfoils for the near tip region of Dynamic perspective displays and the control of tilt-rotor representative of X-SA forward-swept wing aircraft a helicopter in forward flight aircraft in simulated fliht p 174 A89-18867 [NASA-CR-179439] p194 N89-14456 [ NASA-CR-42121 p 204 N89-14821 SYSTEMS INTEGRATION STRESS INTENSTY FACTORS SUPERSONIC AIRCRAFT Energy management for integrated flight and propulsion Stress intensity factors for paricdic radial cracks in a Carbon fiber composites for supersonic technology control systems rotating disc p 187 A89-17448 [DGLR PAPER 87-1241 p 185 A8920244 [AIAA PAPER 88-38731 p 178 A89-18068 A study of contact interaction in aircraft structural Passive venting technique for shallow cavities Vehicle management system requirements elements p188 A89-18644 [NASA-CASE-LAR-14031-1] p 168 N89-14232 [AIM PAPER 88-38761 p 179 A89-18070 A-20 SUBJECT INDEX TRANSITION FLOW

Vehicle management system for a manned hypersonic Temperature effect on stress concentration around THREE DIMENSIONAL MODELS vehicle circular hole in a composite material specimen Numerical simulation of the 2 August 1985 DFW [AIAA PAPER 88-38771 p 179 A89-18071 representative of X-29A forward-swept wing aircraft microburst with the three-dimensional Terminal Area Optimal integration of inertial sensor functions for [ NASA-CR-1794391 p 194 N89-14456 Simulation System p 175 A89-19186 flightcontrol and avionics TENSION Development of three-dimensionalcode for the analysis [AIAA PAPER 88-38781 p 170 A89-18072 An experimentaland analylical evaluation 01 the tapered of jet mixing problem. Part 1: Laminar solution The T-2 control configured vehicle development, tension-torsion strap concept [NASA-CR-42001 p 152 N89-13401 integration and flight test [ NASA-TM-1010491 p 191 N89-13746 THRESHOLDS [AIAA PAPER 88-38821 p 179 A89-18076 TERMINAL FACILITIES Effect of model uncertainty on lailure detection - The Reflections on avionic integration Terminal area forecasts: Fiscal years 1988-2000 threshold selector p 197 A89-17965 [AIM PAPER 88.39501 p 172 A89-18121 [ AD-A1980791 p 156 N89-13419 THRUSTREVERSAL A lault tolerant integrated avionics computer system TERMINAL GUIDANCE Thrust-reverser flow investigation on a twin-engine [AIM PAPER 884041 I p 173 A89-18165 Recent studies of MLS application transport Modeling mission reliability 01 advanced integrated [AIM PAPER 88-39161 p 157 A89-16093 [ NASA-TP-28561 p 153 N89-14213 Terminal navigation for the Combat Talon II aircraft communication. navigation. identification avionics Investigationof a moving-model technique for measuring [AIAA PAPER 68-4021 ] p 159 A89-18173 systems TERRAIN ground effect [AIAA PAPER 88-40231 p 173 A89-18174 [NASA-TM-4060] p 154 N89-14217 Computer-aided engineering methods for successful Comparison of the general dynamics ground clobber algorithm with the GCAS and laws algorithms THUNDERSTORMS VHSIC application [ AD-A1 984791 p 157 N89-14226 Thunderstorm avoidance for general aviation aircraft [AIAA PAPER 88-40351 p 188 A89-18185 [AlAA PAPER 88.39551 p 172 A89-18125 Vehicle management system architectural TERRAIN FOLLOWING AIRCRAFT Simulation evaluation of helicopter Terrain Numerical simulation of the 2 August 1985 DFW considerations FollowingITenainAvoidance concepts microburst with the three-dimensional Terminal Area [AIM PAPER 88-38751 p 174 A89-18189 [AlAA PAPER 88.39241 p 180 A69-18101 Simulation System p 175 A89-19186 Software development for large scale avionic integration programs p200 A89-18864 TEST EOUIPMENT TILT ROTOR AIRCRAFT Avionics testing in the military bare-base environment Guidance and Flight Director system for the V-22 Airborne integrated monitoring system p 141 A89-18011 Tiltrotor p 174 A89-18868 [AIAA PAPER 88-39211 p 179 A89-18098 A fixed base data system lor flight testing TEST FACILITIES p 201 A89-18937 The Oemal wind tunnel as basic idea and incentive Rotorlairframe interactions on tiltrotor aircraft Integrated CNI terminal software architecture for planning the USAF research center AEDC Tullahoma p 161 A89-18854 [AIAA PAPER 88-40221 p 201 A89-19862 p 183 A89-20245 Tiltrotor evolution leads to ASW revolution -.- Design and integration of air-breathing propulsion TETHERING antisubmanne warfare p 142 A89-18862 systems of space transports and hypersonic aircraft Studies of the dynamics of the twin-lift system Human factors impact on the V-22 Osprey cockpit [DGLR PAPER 87-1031 p 176 A89-20241 [ NASA-CR-1832731 p 167 N89-13422 development - An overview p 174 A89-18865 The 6-16 central integrated test system expert THERMAL CONTROL COATINGS Dynamic perspectivedisplays and the control of tilt-rotor parameter system p 202 N89-14763 Performance of coated materials in high-enthalpy aircraft in simulated flight p 174 A89-18867 SYSTEMS SIMULATION oxidizing gas flows p 185 A89-18650 Airborne integrated monitoring system A simulation-basedlault injection experiment to evaluate Thermal Barrier Coatings. Abstracts and figures p 174 A89-18868 self-test diagnostics for a fault-tolerant computer [NASA-CP-10019] p 185 N89-13642 Improved lite cycle 'reps' services ~ V-22 engineering [AIAA PAPER 88-38971 p 198 A89-18083 Development 01 thermomechanical life prediction technical services and logistics planning An approach to solving large reliability models models for thermal barrier coatings p 186 N89-13643 p 142 A89-18873 [AIAA PAPER 88-39051 p 199 A89-18086 High time service evaluation of thermal barrier coatings SYSTEMS STABILITY The Pointer - A revolutionary idea to improve RPV on the Rolls-Royce RE211 engine p 186 N89-13660 capabilities p 163 A89-18881 Identification of unstable llight-mechanical systems using an output error method p 181 A89-19661 THERMAL FATIGUE Civil tiltrotor aircraft . A comparison of five candidate Automated fatigue crack growth measurement designs p 163 A89-18882 [AD-A198642] p 195 N89-14466 The development 01 the V-22 Osprey armored T THERMAL STRESSES energy-absorbing crewseat assembly Coupled flow, thermal, and structural analysis of p 155 A89-18883 T-2 AIRCRAFT aercdynarnically hated panels p 181 A89-20322 Advanced lube system diagnostics for V-22 The T-2 control conligured vehicle development, THERMODYNAMIC PROPERTIES p 190 A89-18907 integration and flight test Advanced core technology: Key to subsonic propulsion V-22 Osprey enabling technologies [AIM PAPER 88.38821 p 179 A89-18076 benefits p 143 A89-20744 T-38 AIRCRAFT [ NASA-TM-1014201 p 178 N89-14237 The V-22 - 'Am I gonna like it?' p 167 A8920745 Terminal navigatlon for the Combat Talon II aircraft THERMOGRAPHY TILT ROTOR RESEARCH AIRCRAFT PROGRAM [AIAA PAPER 88-40211 p 159 A89-18173 Detecti of laminar-turbulent transition by infrared Development and qualification testing, teaming lor the ----.. aircraft p I ACAn thermography p i43 AG-iii4i V-22 rnojti-qervira systtnm 165 A89-18928 An overview of space-based radionavigation systems TIME OPTIMAL CONTROL Characterization of boundary layer conditions in wind A note on the aircraft minimum-time turns p 160 A89-20122 tunnel tests through IR thermography imaging p 182 A89-20638 TACTICS p 147 A89-19167 AI applications to tactical decision aids TIP SPEED THERMOPLASTIC RESINS [AIAA PAPER 88-40271 p 200 A89-18178 Users' manual for the Langley high speed propeller noise TAIL ROTORS Buckling and final failure of graphitelPEEK stiffener prediction program (DFP-ATP) sections p 190 A89-19911 NOTAR - An alternative to the helicopter tail rotor [ NASA-CR-42081 p 204 N89-14820 p 166 A89-20020 The quality of fibre reinlorced thermoplastics TIP VANES TAPERING mouldings p 196 N89-13839 An experimental and analytical evaluation 01 the tapered An experimental and analytical evaluation of the tapered THIN WINGS tension-torsion strap concept tension-torsion strap concept Calculation of hypesonic flow past the windward side [ NASA-TM-101049) p 191 N89-13746 [ NASA-TM-l01049] p 191 N89-13746 of a low-aspect-rabowing at high angles of attack TITANIUM ALLOYS TARGET ACOUlSlTlON p 144 A89-18357 Dwell time effects on the fatigue behaviour of titanium Standardized advanced infrared sensor - A program THREAT EVALUATION alloys p 185 A89-17619 status p 175 A89-18932 Air combat tactics for the evaluation of rotorcraft TOLERANCES (MECHANICS) TECHNOLOGY ASSESSMENT characteristics in the low air war 01 2010 An empirical look at tolerances in setting icing test The X-20 space plane - Past innovation, future vision p 142 A89-18859 conditions with particular application to icing similitude [IAF PAPER 88-5981 p 204 A89-17867 THREE DIMENSIONAL BODIES [ADA198941 ] p 156 N89-13418 Down with drag p 141 A89-18347 Surface grid generation for complex three-dimensional TORSION An overview of the Federal Radionavigation Plan geometries An experimentaland analytical evaluation of the tapered p 160 A89-20123 [ NASA-TM-1010461 p 191 N89-13747 tension-torsion strap concept Flight guidance technology THREE DIMENSIONAL FLOW [ NASA-TM-1010491 p 191 N89-13746 [DGLR PAPER 87-1191 p 160 A89-20239 Threedimensonal vortex systems of finite wings TOXIC HAZARDS The OeMal wind tunnel as basic idea and incentive p 149 A89-20148 Three dimensional hazard zones p 195 A89-18259 lor planning the USAF research center AEDC Tullahoma TRAJECTORY OPTIMIZATION Method of cold smoke generation for vortex core note on the optimal hypersonic flight path p 183 A89-20245 tagging p 191 A89-20324 A TECHNOLOGY UTILIZATION p 167 A89-20637 New application possibilities for balloon-borne case Experimental study on low-speed aerodynamic TRANSCENDENTAL FUNCTIONS studies - MIKROBA (Microgravity by balloons) characteristics 01 non-axisymmetnc slender bodies Solution and sensitivity analysis of a complex p 151 A89-20635 [DGLR PAPER 87-0691 p 184 A89-20233 transcendental eigeiipioblem with pairs of real TELECOMMUNICATION Coupling linearized far-field boundary conditions with eigenva!ues The future of aeromobile digital communications nonlinear near-field solutions in transonic flow [NASA-CR-182241] p 193 N89-13819 [AIAA PAPER 88-40011 p 158 A89-18156 [AD-A198721I p 153 N89-13405 TRANSIENT RESPONSE Teleport as a concentration point for domestic and Management and control of unsteady and turbulent Application of transient aerodynamics to the structural international traffic p 190 A89-20114 flows nonlinear flutter problem p 182 A8920323 TEMPERATURE EFFECTS [AD-A198091] p 192 N89-13751 TRANSITION FLOW Flight measured and calculated exhaust jet conditions Simulation of 3-D viscous flow within a multi-stage Characterization of boundary layer conditions in wind lor an Fl00 engine in an F-15 airplane turbine tunnel tests through IR thermography imaging [ NASA-TM-1004191 p 177 N89-13435 [ NASA-TM-1013761 p 178 N89-14238 p 147 A89-19167

A-21 TRANSMISSIONS (MACHINE ELEMENTS) SUBJECT INDEX

TRANSMISSIONS (MACHINE ELEMENTS) Simulation of 3-D viscous flow within a multi-stage UNSTEADY AERODYNAMICS Dynamic modeling of a helicopter lubrication system turbine Computation of the pressure in an incompressible p 189 A89-18897 [NASA-TM-101376] p 178 N89-14238 rotational flow of inviscid fluid p 143 A89-17150 Advanced transmission studies p 189 A89-18906 TURBOFAN ENGINES Spatial marching techniques for approximate solutions Effect of advanced component technology on helicopter Euler analysis of a swirl recovery vane design for use to the hypersonic blunt body problem transmissions with an advanced single-rotation propfan p 143 A89-17460 [NASA-TM-101431I p 193 N89-13794 [AIAA PAPER 88-31521 p 144 A89-17940 Aeroelastic response of metallic and composite propfan TRANSONIC FLOW Fan acoustic modes measuring system models in yawed flow Recent developments in transonic flow computation p 183 A89-19950 [AIM PAPER 88-31541 p 175 A89-17942 p 145 A89-18749 Advanced core technology: Key to subsonic propulsion Calculation of the unsteady aerodynamic characteristics Improvements to transonic flowfield calculations benefits of bodies in the case of separated flow p 146 A89-18915 [NASA-TM-101 4201 p 178 N89-14237 p 144 A89-18355 An analytical description of unsteady transonic Self-similar problem of the separated flow of an ideal TURBOJET ENGINES Laval-nozzle flow p 147 A89-19664 fluid past an expanding plate p 144 A89-18669 Early jet engines and the transition from centrifugal to Measurements of the buffet boundary of wings in An entropy and viscosity corrected potential method for axial compressors: A case study in technological change transonic flow with hot-film method p 148 A89-19805 rotor performance prediction p 145 A89-18857 [AD-A198775] p 177 N89-13430 Full-potential integral solution for transonic flows with A unified theoretical-computationalapproach for viscous and without embedded Euler domains TURBOMACHINERY unsteady rotor aerodynamics p 146 A89-18917 p 148 A89-19908 Simulation of 3-D viscous flow within a multi-stage Rotorcraft aeromechanical analysis using a nonlinear Transonic Navier-Stokes solutions for a fighter-like turbine unsteady aerodynamic model p 146 A89-18919 configuration p 149 A89-20134 [NASA-TM-101 3761 p 178 N89-14238 The use of sweepfrequency excitation for unsteady Further comparisons of interactive boundary-layer and TURBOPROP AIRCRAFT pressure measurement --- in aerodynamics thin-layer Navier-Stokes procedures p 149 A8920137 Acoustic transmissibility of advanced turboprop aircraft Dynamic inflow for practical applicationsp 147 A89-18940 Unsteady transonic aerodynamics and aeroelastic windows p 204 A89-20143 calculations at low-supersonic freestreams TURBOPROP ENGINES p 147 A89-19625 p 149 A89-20145 Parametric studies of advanced turboprops A new approach for computing full unsteady Numerical simulation of tip vortices of wings in subsonic [NASA-TM-101389] p 195 N89-14465 aerodynamic characteristics p 147 A89-19788 and transonic flows p 150 A89-20176 TURBORAMJET ENGINES Experimental study on unsteady aerodynamic Computation of rotational transonic flows using a Conceptual study of tu-engines for horizontal takeoff characteristics of an oscillating cascade with tip decomposition method p 150 A89-20179 and landing space plane clearance p 148 A89-19927 Analysis of artificial dissipation models for the transonic [ IAF PAPER 88-2531 p 184 A89-17745 Unsteady transonic aerodynamics and aeroelastic full-potential equation p 191 A89-20188 TURBULENCE calculations at low-supersonic freestreams Transonic wing design using inverse methods in Analysis of temperature and velocity microturbulence p 149 A89-20145 curvilinear coordinates p 151 A89-20316 parameters from aircraft data and relationship to Flow unsteadiness considerations in high-alpha testing Aerodynamic characteristics of rectangular atmospheric refractive index structure p 151 A89-20319 cross-sectional bodies at M = 0.85 p 151 A89-20317 [AD-A1965421 p 196 N89-13854 Application of transient aerodynamics to the structural Coupling linearized far-field boundary conditions with TURBULENTBOUNDARYLAYER nonlinear flutter problem p 182 A8920323 nonlinear near-field solutions in transonic flow Detection of laminar-turbulent transition by infrared Calculation of the steadily periodic and gust responses [AD-A198721] p 153 N89-13405 thermography p 143 A89-17147 of a hingeless rotor helicopter using two-dimensionaltime TRANSONIC WIND TUNNELS A study on aerodynamic heatingin the interaction regions domain unsteady aerodynamics p 182 N89-14240 Improving the half-model technology in the Goeningen of shock waves and turbulent boundary layers induced UNSTEADY FLOW transonic wind tunnel by sharp fins p 148 A89-20131 Computation of the pressure in an incompressible [DGLR PAPER 87-0831 p 183 A89-20234 Management and control of unsteady and turbulent rotational flow of inviscid fluid p 143 A89-17150 Wall adjustment strategy software for use with the NASA flows Computational analysis of unsteady supersonic cavity Langley 0.3-metertransonic cryogenic tunnel adaptive wall [AD-A198091] p 192 N89-13751 flows driven by thick shear layers p 145 A89-18803 test section TURBULENT FLOW Measurement and analysis of unsteady flow structures [NASA-CR-181 6941 p 151 N89-13400 Mathematical modeling of laminar and turbulent in rotor blade wakes p 147 A89-18946 Design of high-Reynolds-number flat-plateexperiments supersonic flow past convex-concave bodies An analytical description of unsteady transonic in the NTF p 144 A89-18671 Laval-nozzle flow p 147 A89-19664 [NASA-CR-184627] p 153 N89-13411 Experimental assessment of a turbulence ingestion Vortical wakes over a prolate spheroid Two-dimensional aerodynamic characteristics of the p 150 A89-20181 OLS/TAAT airfoil noiw theory p 203 A89-18912 Management and control of unsteady and turbulent Moving wall effects in unsteady flow [NASA-TM-89435] p 154 N89-14216 p 150 A89-20311 TRANSPORT AIRCRAFT flows [AD-A198091] p 192 N89-13751 Flow unsteadiness considerations in high-alpha testing Commercial jet transport fly-by-wire architecture The effects of inlet turbulence and rotor/stator p 151 A8920319 considerations interactions on the aerodynamics and heat transfer of a Unsteady low-speed windtunnel test of a straked delta [AIAA PAPER 88-3900] p 180 A89-18108 large-scale rotating turbine model. volume 1 wing. oscillating in pitch. Part 4 Plots of time histories of Project for an advanced regional transport aircraft [NASA-CR-4079] p 192 N89-13756 pressures and overall loads [DGLR PAPER 87-0791 p 167 A8940236 TURBULENT WAKES [ADA1986821 p 152 N89-13402 Thrust-reverser flow investigation on a twin-engine Vortical wakes over a prolate spheroid Unsteady low-speed windtunnel test of a straked delta transport p 150 A89-20181 wing, oscillating in pitch. Part 5: Power spectral density [NASA-TP-2856] p 153 N89-14213 plots of the overall loads for harmonic oscillation and the TUNING Interactions between turbulent wakes and boundary layers p 150 A89-20182 response of overall loads to (1-COS) inputs Experimental investigation of propfan aeroelastic [ADA1986831 p 152 N89-13403 response in off-axis flow with mistuning TURNING FLIGHT A note on the aircraft minimum-time turns Unsteady low-speed windtunnel test of a straked delta [AIAA PAPER 88-31531 p 175 A89-17941 wing, Oscillating in pitch. Part 6: Presentation of the TURBINE ENGINES p 182 A89-20638 TWO DIMENSIONAL BODIES visualization program Turbine design using complex modes and A comparison of numerical methods for the prediction [AD-A198684] p 152 N89-13404 substructuring p 190 A89-19718 of two-dimensional heat transfer in an electrothermal Management and control of separation by unsteady and High time service evaluation of thermal banier coatings deicer pad vortical flows on the Rolls-Royce RE211 engine p 186 N89-13660 [ADA1989021 p 191 N89-13736 The effects of inlet turbulence and rotor/stator [ NASA-CR-42021 p 175 N89-13429 Two-dimensional aerodynamic characteristics of the Management and control of unsteady and turbulent interactions on the aerodynamics and heat transfer of a flows large-scale rotating turbine model, volume 1 OLSlTAAT airfoil [NASA-TM-89435] p 154 N89-14216 [AD-A198091] p 192 N89-13751 [NASA-CR-4079] p 192 N89-13756 TWO DIMENSIONAL FLOW URBAN PUNNING Atmospheric photochemical modeling of turbine engine Validation of ap+woximateindicia1 aerodynamic functions Method for simulatingturbulence characteristics for wind fuels and exhausts. Computer model development,volume for twc-dimensbnal subsonic flow p 149 A89-20140 environment in wind tunnel p 183 A89-19884 1 Coupling linearized far-field boundary conditions with USER MANUALS (COMPUTER PROGRAMS) [AD-A1986901 p 196 N89-13832 nonlinear near-field solutions in transonic flow User's manual for an aerodynamic optimizationscheeme Ploning component maps in the NavylNASA Engine that updates flow variables and design parameters Program (NNEP): A method and its usage [AD-A198721] p 153 N89-13405 Experimental results for a two-dimensional supersonic simultaneously [ NASA-TM-1014331 p 178 N89-14239 inlet used as a thrust deflecting [NASA-CR-182180] p 151 N89-13399 A review of failure models for unidirectional ceramic nozzle [NASA-TM-83439] p 194 N89-14386 Users' manual for the Langley hghspeed propeller noise mabix composites under monotonic loads prediction program (DFP-ATP] [NASA-TM-101421] p 195 N89-14470 [NASA-CR-4208] p 204 N89-14820 TURBINES U UTILITIES T55-L-714 engine development and qualification: Tip Application of dgital technology to aircraft utility clearance analysis UHsOA HELICOPTER systems [ADA1988491 p 177 N89-13431 Three-dimensional interactive system identification of [AIM PAPER 88-38721 p 180 A89-18114 The measurement and prediction of rotordynamic forces helicopter rotorlbody dynamics p 165 A89-18938 for labynnth seals ULTRASONIC TESTS [ AD-A1971 851 p 192 N89-13784 Downstream vorticity measurements from ultrasonic v TURBOCOMPRESSORS pulses p 151 A89-20313 Early jet engines and the transltion from centrifugal to UNIFORM FLOW V/STOL AIRCRAFT axial compressors: A case study in techwloglcal change Frequency-domain method for tha computation of Experimentalinvestigation of a jet impinging on a ground [ADA1987751 p 177 N89-13430 propeller acoustics p 203 A89-19902 plane in crossflow p 149 A89-20141 A-22 SUBJECT INDEX WORKING FLUIDS

Experimental resuits for a twodimensional supersonic VORTEX SHEDDING WIND TUNNEL MODELS inlet used BS a thrust deflecting nozzle Computational analysis of unsteady suwrsonic cavity Interference effects associated with a plate-supported [ NASA-TM-834391 p 194 N89-14386 flows driven by thick shear layers -p 145 A89-18803 half-model in hypersonic flow p 148 A89-19924 VANES VORTEX SHEETS Improving the half-modal technology in the Goeningen Euler anaiysis of a swirl recovery vane design for use Vortical wakes over a prolate spheroid transonic wind tunnel with an advanced single-rotation propfan p 150 A89-20181 [DGLR PAPER 87-0831 p 183 A89-20234 [AIM PAPER 88-31521 p 144 A89-17940 VORTICES Isolated testing of highly maneuverable inlet con cepts High time service evaluation of thermal barrier coatings Seven hole probe measurement of leading edge vortex [NASA-CR-179544] p 178 N89-13437 on the Rolls-Royce RB211 engine p 186 N89-13660 flows p 146 A89-18939 Two-dimensional aerodynamic characteristics of the The effects of leading edge and downstream film cooling The relationship between the aerodynamic OLSfTAAT airfoil characteristics double-delta wings and vortices with on turbine vane heat transfer of [ NASA-TM-89435J p 154 N89-14216 [ NASA-CR-1821331 p 192 N89-13754 sideslips at high angles of attack p 148 A89-19801 WIND TUNNEL TESTS Experimental study on unsteady aerodynamic A correlation study of rotor inflow in forward flight VAPOR DEPOSITION CharacteristiCs of an oscillating cascade with tip p 145 A89-18856 Chemical vapor deposition of oxidation resistant HfB2 clearance p 148 A89-19927 + Sic mposite coatings p 185 A89-19481 Testing and correlation on an advanced technology. Threedimensional vortex systems of finite wings bearingless rotor p 182 A89-18900 VARIABLE CYCLE ENGINES p 149 A89-20148 A comparison of acoustic predictions with model rotor Variablecycle engines for boosting-cruisingvehicles Downstream vorticity measurements from ultrasonic test data from the NASA 14 x 22 ft wind tunnel [IAF PAPER 88-2491 p 175 A89-17742 pulses p 151 A89-20313 p 203 A89-18913 VELOCITY MEASUREMENT Flow unsteadiness considerations in high-alpha testing Tip-path-plane angle effects on rotor blade-vortex LDV measurements in an annular combustor model p 151 A89-20319 interaction noise levels and directivity [NASA-CR-182207] p 192 N89-13755 Drag reduction lactor due to ground effect p 203 A89-18914 VENTING p 151 A89-20325 The use of swwp-frequency excitation for unsteady Passive venting technique for shallow cavities Unsteady low-speed windtunnel test of a straked delta pressure measurement --- in aerodynamics [NASA-CASE-IAR-14031-1] p 168 N89-14232 wing. oscillating in pitch. Part 6: Presentation of the p 147 A89-18940 Passive venting technique for shallow cavities visualization program Characterization of boundary layer conditions in wind [NASA-CASE-IAR-13875-1] p 169 N89-14233 IAD-Al986841 p 152 N89-13404 tunnel tests through IR thermography imaging VERTICAL MOTION A potential flow solution on marine propeller and axial p 147 A89-19167 Evaluation of simulator motion characteristics based on rotating fan Method for simulating turbulence characteristicsfor wind AGARD-AR-144 procedures p 183 A89-19565 [AD-A198781] p 191 N89-13735 environment in wind tunnel p 183 A89-19884 VERY LARGE SCALE INTEGRATION Manaaement and control of SeDaration bv unsteady and Interference effects associated with a plate-supported High-speed data bus processing node vortical iows half-model in hypersonic flow p 148 A89-19924 [AIAA PAPER 8840091 p 201 A89-19861 [AD-A1989021 p 191 N89-13736 Experimentalinvestigation of a jet impinging on a ground VHSIC (CIRCUITS) plane in crossflow p 149 A89-20141 Computer-aided engineering methods for successful Downstream vorticity measurements from ultrasonic VHSIC application W pulses p 151 A89-20313 [AIM PAPER 8840351 p 188 A89-18185 Aerodynamic characteristics of rectangular WAKES High-speed data bus processing node cross-sectional bodies at M = 0.85 p 151 A89-20317 Measurement and analysis unsteady flow structures [AIM PAPER 88-40091 p 201 A89-19861 of Experimental study on low-speed aerodynamic in rotor blade wakes p 147 A89-18946 VIBRATION characteristics of non-axisymmetric slender bodies Numerical simulation and comparison of A walk along interfaces --_ aeroelasticity p 151 A89-20635 symmetricalfsupercriticalairfoils for the near tip region [Be8170081 p 154 N89-14223 of Unsteady low-speed windtunnel test of a straked delta a helicopter in lwward flight VIBRATION DAMPING wing. oscillating in pitch. Part 4 Plots of time histories of [NASA-CR-4212] p 204 N89-14821 Helicopter vibration analysis and control pressures and overall loads WALL FLOW p 188 A89-18871 [AD-A1986821 p 152 N89-13402 Moving wall effects in unsteady flow Experimental verilication of helicopter blade designs WIND TUNNEL WALLS p 150 A89-20311 optimized for minimum vibration p 162 A89-18874 An investigation of wall interference correction to the Bearinglessrotors and higher harmonic control modeling WARNING SYSTEMS pressure measurement in low speed wind tunnel with solid using RACAP p 162 A89718876 Results 01 the in-service evaluation of the traffic alert walls p 183 A89-19808 and collision avoidance system industry prototype Six degree of freedom crew isolation design, bench test Wall adjustment strategy software for use with the NASA [AIM PAPER 88-39151 p 171 A89-18092 and flight test p 163 A89-18896 Langley 0.3-metertransonic cryogenic tunnel adaptivewall Evaluation the improved OV-1D anti-icing system Nonlinear stability analysis for helicopter ground of test section [AD-A1984381 p 156 N89-14225 resonance p 166 A89-19790 [NASA-CR-1816941 p 151 N89-13400 Optimization of mistuned blade rotor for controlling Use of the Terminal Area Sirnulation System (TASS) WIND TUNNELS flutter p 176 A89-19793 to study microburst wind shears p 197 N89-14899 The Oetztal wind tunnel as basic idea and incentive VIBRATION ISOLATORS A flight test design for studying airborne applications for planning the USAF research center AEDC Tullahoma Nonlinear stability analysis for helicopter ground of air to ground duplex data link communications p 183 A89-20245 .CC "0" <*Ton p 195 N89-14924 ,es"lK¶on.~ p- I"" -"l-."."" WINDOWS (APERTURES) VIBRATION METERS WATER TUNNEL TESTS Acoustic transmissibility of advanced tubprop aircraft Holomelrics - An information transformation A water tunnel study of Gurney flaps windows p 204 A89-20143 [NASA-TM-4071] p 151 N89-13395 methodology p 200 A89-18922 WING FLAPS VIBRATION MODE WEAPON SYSTEMS A water tunnel study of Gurney flaps Effect of blade mistuning and blade-disk on cascade The enemy is FA, CND, and RTOK [NASA-TM-4071] p 151 N89-13395 p 141 A89-18025 fluner boundaries p 176 A89-19803 WING LOADING VIBRATION TESTS Expert systems in higher echelon maintenance A new approach for computing full unsteady activities p 202 N89-14761 Ground simulation for airborne equipment aerodynamic characteristics p 147 A89-19788 The B-1B central integrated test system expert p 188 A89-18741 WING OSCILLATIONS parameter system p 202 N89-14763 Investigation of difficult component effects on FEM A guide to classical flutter p 188 A89-18801 vibration prediction for the AH-1G helicopter WEAPONS DELIVERY Measurements of the buffet boundary of wings in Aerospace simulation Ill; Proceedings of the p 162 A89-18879 SCS transonic flow with hot-film method p 148 A89-19805 VIBRATIONAL STRESS Multiconference, San Diego. CA. Feb. 3-5. 1988 WING PANELS p 142 A89-19551 Structural dynamics of a helicopter rotor blade system Bucklrng characteristics of hypersonic aircraft wing p 162 A89-18878 WEAR RESISTANCE tubular panels VIDEO SIGNALS Carbonfcarbon composite materials for aircraft brakes [ NASA-TM-877561 p 193 N89-13816 p 165 A89-19427 Interfacing sensor assemblies with windowless cockpit WING PROFILES displays p 187 A89-17979 WEIGHT INDICATORS Transonic wing design using inverse methods in VISCOUS FLOW Design of a certilible primary on-board aircraft weight curvilinear coordinates p 151 A89-20316 A unifiedtheoretical-computational approach lor viscous and balance system WING SPAN [AIAA PAPER 88-39191 p 171 A89-18096 unsteady rotor aerodynamics p 146 A89-18917 Drag reduction factor due to ground effect Interactive and large-domain solutions of higher-order WEIGHT REDUCTION p 151 A89-20325 Airframe and propulsion assessment of alternative light viscous-flow equations p 148 A89-19905 WING TIP VORTICES helicopter technologies p 161 A89-18863 Time-iterative solutions 01 viscous supersonic nozzle (LHXJ Numerical simulation of tip vortices of wings in subsonic Effect of advanced component technology on helicopter flows p 150 A89-20184 and transonic flows p 150 A89-20176 Simulation of 3-D viscous flow within a multi-stage transmissions WINGLETS [NASA-TM-101431] p 193 N89-13794 turbine Winglets on low-aspect-ratio wings WIND EFFECTS [ NASA-TM-1013761 p 178 N89-14238 p 149 A89-20142 VOICE COMMUNICATION Arrival-time guidance in variable wnds WINGS [AIAA PAPER 88-40251 p 159 A89-18176 Aeronautical Satellite netwwks p 160 A89-20117 Threedimensionalvortex systems of finite wings VORTEX BREAKDOWN WIND SHEAR p 149 A89-20148 Seven hole probe measurement of leading edge vortex Numerical simulations of an isolated microburst. I - WIRE flows p 146 A89-18939 Dynamics and structure p 196 A89-20265 Automated wire preparati system Vortex breakdown measurements on a 70 deg Use of the Terminal Area Simulation System (TASS) p 189 A89-18895 sweepback delta wing p 150 A89-20312 to study microburst wind shears p 197 N89-14899 WORKING FLUIDS VORTEXGENERATORS WINDTUNNELAPPARATUS Selection of the optimal lighter-than-air gas for airship Method of cold smoke generation for vortex core Optical fiber data transfer system and a scheme 01 double-layer structural design tawing p 191 A8920324 [ NASA-CR-1817041 p 194 N89-14376 D 166 A89-19809

A-23 WORKLOADS (PSYCHOPHYSIOLOGY) SUBJECT INDEX

WORKLOADS (PSYCHOPHYSIOLOOY) Introduction of Pilot's Operational Workload Evaluation Research Simulator, POWERS. in Aeromedical Labcfatoty. JASDF p 183 A89-19876 Autonomous RPRV navigation. guidance and control [NASA-CR-1794251 p 161 N89-14228 X

X WING ROTORS X-wing fly-by-wire vehicle management system [AIM PAPER 88-39231 p 179 A89-18100 An examination of some rotor aerodynamic models using the RSRAIX-wing model test data p 146 A89-18858 A parallel architecture for a real-time blade element rotorcraft simulation p 201 A89-19560 X-20 AIRCRAFT

The X-20 space plane ~ Past innovation, future vision [IAF PAPER 88-5981 p 204 A89-17867 X-29 AIRCRAFT X-29 validation methodology for Simulation and flight control system p 181 A89-19557 Real-time flight test analysis and display techniques for the X-29A aircraft [ NASA-TM-1016921 p 168 N89-13424 Y YAW Aeroelastic response of metallic and composite propfan models in yawed flow [AIM PAPER 88-31541 p 175 A89-17942 The impact of yaw axis control modes. flight directors and automatic control coupling on decelerating IFR approaches lor rotorcraft p 180 A89-18903

A-24 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING /AContinuing Bibliography (Supplement 238) April 1989

npical Personal Author index Listing

ALBRECHT, C. B Methodology for fatigue substantiation of alternate sources and degraded modes on helicopter dynamic BADAVI, F. F. components p 164 ABS-18924 Numerical simulation and comparison of PERSONAL AUTHOR ALEMDAROGLU, N. symmetricallsupercritical airfoils for the near tip region of Further comparisons of interactive boundary-layer and a helicopter in forward flight thin-layer Navier-Stokes procedures p 149 A89-20137 [NASA-CR-4212] p 204 N89-14821 BAEDER, J. D. BOURNE. SIMON M. ALSINA. J. Numencal simulation of tip vortices 01 wings in subsonic He*roptcn roll control effectrvenes Cnteria program Proaress towards a commercial aircraft desian-. exwrt and transonic flows p 150 A89-20176 wmmuy system BAILLIE, STEWART I NASA-CR-177477I p 3'5 N89-10046 r [DGLR PAPER 87-1201 p 167 A89-20237 The impact of yaw axis control modes. flight directors ALTHOFF, SUSAN L and automatic control coupling on decelerating IFR Rotor inflow variability with advance rati approaches for rotorcraft p 180 A89-18903 p 145 ABS-18855 BAKER, ROBERT L AMER, KENNETH 8. A simulation-bad fault injection experiment to evaluate A 'new' philosophy of structural reliability. fail safeversus self-test diagnostics for a fault-tolerant computer sale life p 188 A89-18852 [AIM PAPER 88-38971 p 198 A89-18083 BAKKEN, DAVID E. AMIET, ROY Inter-partitin data integrity in the asynchronous DATAC Experimental assessment of a turbulence ingestion environment Listings this index are arranged alphabetically noise theory p 203 A89-18912 in [AIM PAPER 8840101 p200 A89-18160 by personal author The title 01 the document pro- ANDERSEN, CARL M. BALAKRISHNAN,A. V. vides the user with a briel description of the sub- Optimization of slender wings for center-of-pressureshift Efficient load measurements using singular value due to change in Mach number p 154 N89-14897 ject matter The report number helps to indicate decomposition ANDERSON, J. M. [ NASA-CR-1846141 p 202 N89-14795 the type document listed , report. 01 (e g NASA The enemy is FA, CND. and RTOK BANSEMIR, H. translation. NASA contractor report) The page p 141 A89-18025 Strength of dynamically loaded force introduction for and accession numbers are haled beneath and ANDERSON, JOSEPH fiber-reinforced rotors to the right 01 the title Under any one author's Reconfigurablefliht control system simulation [DGLR PAPER 87-1081 p 185 ABS-20243 BAO, GUOHUA name the accession numbers are arranged in se- p 181 A89-19558 ANINOS, A. The relationship between the aerodynamic quence with the numbers appear- AIAA accession Progress towards a commercial aircraft design expert characteristics of double-delta wings and vortices with ing first system sideslips at high angles of attack p 148 A89-19801 [DGLR PAPER 87-1201 p 167 A89-20237 BARNARDBROWN, E. H. A APARINOV, V. A. Engines for Mini-RPV XM-1A Calculationof the unsteady aerodynamic characteristics [AD-At 983361 p 178 N89-14236 ABDI-MORADI, M. of bodies in the case of separated flow BARNElT, MARK An automated methodology for partitioning software p 144 A89-18355 Simulation of 3-D viscous flow within a multi-stage functions in a distributed avionics architecture ARYSTROM. ALAN turbine [AIM PAPER 88-3971 I p 199 A89-18137 Proposed revisions to America's national airspace [ NASA-TM-I013761 p 178 N89-14238 ABDOL-HAMID. KHALED S. system - A crisis in leadenhip? p 204 A89-18950 BARR, A. D. S. Development of three-dimensional code for the analysis ASLP, MAlT Dynamics of a rigid rotor mounted on discontinuously -' :-."4";"- ^.^*In^ 0"- I -,.,A** "..,.,*h^ Yl p. '.'.^.'.LI r"".-.'.'. . ",... .. L-.I.II.a wnirai rnainienance complier syjieiili - A kid step "O"-!l"nP: n!-a!ic a:p=??s !2 !* aao.!o?E [NASA-CR-4200] p 152 N89-13401 forward on the 747-400 BARRON, DEAN A. ACHARYl MUKUND [AIAA PAPER 88-40391 p 171 A89-18097 LDV measurements in an annular combustor model Management and control of separation by unsteady and ASO, SHIGERU [ NASA-CR-18220071 p 192 N89-13755 vortical flows A study on aerodynamic heabng in the interaction regions BARTLElT. C. SCOlT [AD-A198902] p 191 N89-13736 of shock waves and turbulent boundary layers induced An empirical look at tolerances in setting icing test Management and control of unsteady and turbulent by sharp fins p 148 A89-20131 conditions with particular application to icing Similitude flows A study on hypersonic shock tunnel [AD-A198941] p 156 N89-13418 [ADA198091 ] p 192 N89-13751 p 148 A89-20132 BATINA, JOHN T. Equipment to upgrade the facilities of the IIT (Illinois ATHANS, MICHAEL Modern wing flutter analysis by computational fluid Institute of Technology) Fluid Dynamics Research Design of feedback control systems for unstable plants dynamics methods p 191 A89-20146 Center with saturating actuators BAUCHAU, 0. [AD-A1980841 p 184 N89-14242 [NASA-CR-183392] p 194 N89-14377 The Center of Excellence in Rotary Technology at ADAMCZYK, JOHN J. ATKINSON. ROGER Rensselaer Polytechnic Institute Simulation of 3-0 viscous flow within a multi-stage Atmospheric photochemical modeling of turbine engine [AD-A198964] p 168 N89-13426 turbine fuels and exhausts. Computer model development,volume BAUCHAU. 0. A. [NASA-TM-101376] p 178 N89-14238 1 Structural dynamics of a helicopter rotor blade system p 162 A89-18878 ADAMS. D. 0. [ AD-A1986901 p 196 N89-13832 Methodolcgy for fatigue substantiation of alternate Atmospheric photochemical modeling of turbine engine BEACH. TIM A. sources and degraded modes on helicopter dynamic fuels and exhausts. Computer model development,VOlume Simulation of 3-D viscous flow within a multi-stage components p 164 A89-18924 2 turbine [ADA1986911 p 196 N89-13833 [ NASA-TM-1013761 p 178 N89-14238 AGOROPOULOS, D. BEECHER, ELIZABETH A. Interactions between turbulent wakes and boundary AlTA, E. Analysis of temperature and velocity microturbulence layers p 150 A89-20182 Zonal grid generation method for complex confiourations p 201 A89-20139 parameters from aircraft data and relationship to AHMED, A. atmospheric refractive index structure Measurements in the field of a spark excited AUGUST, RICHARD Vibration, performance. flutter and forced response [AD-A196542] p 196 N89-13854 compressible axisymmetric jet p 203 A89-18948 charactenstics 01 a large-scale propfan and its aeroelastic BEGEEV, T. K. AIELLO, R. A. model A study of contact interaction in aircraft structural Parametric studies of advanced turboprops [AIM PAPER 88-31551 p 176 A89-17943 elements p188 A89-18644 [ NASA-TM-1013891 p 195 N89-14465 AVIZIENIS. ALGIRDAS BEIN, T. W. AITKEN. SHY On the effectiveness of muitkersion software in dgital A potential flow solution on marine propeller and axial Oceanic clearance delivery via airlgrwnd datalink avionics rotating fan [AIM PAPER 88-39941 p 158 A89-18152 [AIAA PAPER 88-39031 p 199 ABS-18111 [AD-A198781I p 191 N89-13735 AKHTER, MUHAMMAD M. AWASTHI, S. BEWAN, HENRY M. Effect of model uncerlainty on failure detection - The Carbonlcarbon composite materials for aircraft brakes Advanced lube system diagnostics for V-22 threshold selector p 197 A89-17965 p 165 A89-19427 p 190 A89-18907

B-1 BELOTSERKOVSKII, S. M. PERSONAL AUTHOR INDEX

BELOTSERKOVSKII. S. M. BRAHNEV, JAMES H. CAROYICOLI, ADAM Calculation of the unsteady aerodynamic characteristics Designing hydraulic systems for SUNivability Combined numerical and symbolic processing for of bodies in the case of Separated flow p 161 A89-17624 airborne surveillance p 144 A89-18355 ERASE, L 0. [AIM PAPER 88-39851 p 157 A89-18143 BENINGFIELD, H. W. Application of transient aerodynamics to the structural CARROLL,JOSEPHE. Digital audio applications in business and regional airline nonlinear flutter problem p 182 A89-20323 Strapdown issues for airborne EO sensors aircraft BREUER, M. A. lAlAA PAPER 88-39271 p 171 A89-18102 [AIAA PAPER 88-39581 p 157 A89-18127 A methodology for the design of hierarchically testable CARTER, WILLIAM 0. and maintainable digital systems Atmospheric photochemical modeling of turbine engine BENNETT, C. T. [AIAA PAPER 88-38591 p 170 A89-18057 Dynamic perspective displays and the control of tilt-rotor fuels and exhausts. Computer model development,volume aircraft in simulated flight p 174 A89-18867 BRIDGEMAN, JOHN 0. 1 An entropy and viscosity corrected potential method for [ AD-A1986901 p 196 N89-13832 BENNElT, ROBERT M. rotor performance prediction p 145 A89-18857 Atmospheric photochemical modeling of turbine engine Modern wing flutter analysis by computational fluid BRITTON, R. K. dynamics methods p 191 A89-20146 fuels and exhausts. Computer model development, volume Analytical determination and experimental comparison BEST, DAVID W. 2 of performance degradation on a helicopter main rotor [AD-A198691I p 196 N89-13833 A fault tolerant avionics multiprocessing system due to ice accretion p 155 A89-18909 CAUSBIE, SCOTT M. architecture supporting concurrent execution of Ada BROCK, LARRY D. tasks Buckling and final failure of graphite/PEEK stiffener Modular avionics systems studies sections p 190 A89-19911 [AIAA PAPER 88-39081 p 199 A89-18088 [AIAA PAPER 88-38501 p 169 A89-18052 BICKEL, WILLIAM N. BROWN, ALISON K. CEBECI, TUNCER Fabrication and testing of lightweight hydraulic system An overview of space-based radionavigation Systems Further comparisons of interactive boundary-layer and simulator hardware. Phase 2: Addendum p 160 A89-20122 thin-layer Navier-Stokes procedures p 149 A89-20137 [AD-At 985241 p 184 N89-14243 BRUEGGEN, JOB CELESTINA, MARK L. BIDWELL, COLIN S. Development and applications of an avionics research Simulation of 3-D viscous flow within a multi-stage Predictions of airfoil aerodynamic performance testbed turbine degradation due lo icing [AIAA PAPER 88-39521 p 172 A89-18123 [NASA-TM-101 3761 p 178 N89-14238 [NASA-TM-1014341 p 153 N89-13412 BRVSON, RICHARD A. CHADWICK, JIM BIELAWA, R. Integrated CNI terminal software archilecture Helicopter vibration analysis and control The Center of Excellence in Rotary Technology at [AIAA PAPER 88-40221 p 201 A89-19862 p 188 A89-18871 Rensselaer Polytechnic Institute BUCKANIN, ROBERT M. CHAKRAVARN. ABHIJIT [ AD-A1989641 p 168 N89-13426 Rotor system evaluation. phase 1 Avionics failure propagation analysis twI BIERMANN. GARY [ADA1987941 p 168 N89-13425 [AIAA PAPER 88-38681 p 198 A89-18065 One million pixel full color liquid crystal display for BUETTIKER, PAUL CHAMIS, C. C. avionics applications An examinationof some rotor aerodynamic models using Parametric studies of advanced turboprops [AIAA PAPER 88-39671 p 173 A89-18134 the RSRAIX-wing model test data p 146 A89-18858 [ NASA-TM-1013891 p 195 N89-14465 BILL, ROBERT C. BURCHAM, FRANK W., JR. CHANG, CHAU-LYAN Advanced transmission studies p 189 A89-18906 Flight measured and calculated exhaust jet conditions Time-iterative solutions of viscous supersonic nozzle for an FlOO engine in an F-15 airplane BILLET, L flows p 150 A89-20184 M. [ NASA-TM-tOO4191 p 177 N89-13435 Expenmental investigation of a jet impinging on a ground CHANG, DAVONG BURDORF, GARY H. plane in crossflow p 149 A89-20141 Selection of the optimal lighter-than-air gas for airship Robotic deburring of complex machined parts and a scheme of double-layer structural design BIRCKELBAW, L p 190 A89-18936 p 166 A89-19809 Zonal grid generation method for complex BURESTI. GUIDO configurations p 201 A89-20139 Characterization of boundary layer conditions in wind CHANG, K. C. BLACKER, MICHAEL tunnel tests through IR thermography imaging Further comparisons of interactive boundary-layer and Evaluation of the improved OV-1D anti-icing system p 147 A89-19167 thin-layer Navier-Stokes procedures p 149 A89-20137 [AD-A198438] p 156 N89-14225 BURQENER, LARRY L CHARLES, BRUCE D. BLAIR. M. F. Design of a certifiable primary on-board aircraft weight A correlation study of rotor inflow in fomard flight The effects of inlet turbulence and rotor/stator and balance system p 145 A89-18856 interactions on the aerodynamics and heat transfer of a [AIAA PAPER 88-39191 p 171 A89-18096 CHAVIAROPOULOS, P. large-scale rotating turbine model. volume 1 BURGERMEISTER, LINDA Computation of rotational transonic flows using a [ NASA-CR-40791 p 192 N89-13756 Universal Ada Test Language (UATL) lo support decomposition method p 150 A8940179 BLEEG. ROBERT J. real-time softwarelsystem integration and CHELLMAN. D. J. Commercial jet transport fly-by-wire architecture factory/maintenance fault isolation p 197 A89-18009 Evaluation of aluminum-lithium alloys in considerations BURLEV, CASEV L compression-stiffeneed aircrafl structures [AIM PAPER 88-39001 p 180 A89-18108 Tip-path-plane angle effects on rotor blade-vortex p 191 A89-20315 BLISS, DONALD 8. interaction noise levels and directivity CHEN, JINGBO Free wake calculation of rotor flow fields for interactional p 203 A89-18914 Effect of blade mistuning and blade-disk on cascade aerodynamics p 145 A89-18853 BURLEV. R. R. flutter boundaries p 176 A89-19803 Compansons of predicted and measured rotor Isolated testing of highly maneuverable inlet con cepts CHEN, QUN performance in hover using a new free wake analysis [NASA-CR-179544] p 178 N89-13437 Effect of blade mistuning and bladedisk on cascade p 165 A89-18933 BURSTADT, PAUL L flutter boundaries p 176 A89-19803 BLOlTNER. FREDERICK 0. Experimental results for a two-dimensional supersonic CHEN, WON-ZON spatial marching techniques for approximate solutions inlet used as a thNSt deflecting nozzle Vehicle management system architectural to the hypersonic blunt body poblem [NASA-TM-834391 p 194 N89-14386 considerations p 143 A89-17460 BYRD, GREGORY P. [AIM PAPER 88.38751 p 174 A89-18189 BOER. R. 0. DEN Use of the Terminal Area Simulation System (TASS) CHEN, ZHIMING Unsteady low-speed windtunnel test of a straked delta to study microburst wind shears p 197 N89-14899 The combination of Simulation and response wing, oscillating in pitch. Part 4 Plots of time histories of methodology and its application in an aggregate production pressures and overall loads plan p 190 A89-19806 [AD-A198682] p 152 N89-13402 C CHIEN, LAICHEN Unsteady low-speed windtunnel test of a straked delta Study the aerodynamics characteristics of airfoil on wing, oscillating in pitch. Part 5 Power spectral density CALLAHAN, CVNTHIA vector processors plots of the overall loads for harmonic oscillation and the Optimal design of an advanced composite rotating [IAF PAPER ST-68-09] p 143 A89-17874 response of overall loads to (1-COS) inputs flexbeam p 189 A89-18884 CHILDS, D. W. [AD-At 986831 p 152 N89-13403 CANTALOUBE. E. The measurement and prediction of rotordynamicforces Unsteady low-speed windtunnel test of a straked delta Computation of the pressure in an incompressible for labyrinth seals wing, oscillating in pitch. Part 6: Presentation of the rotational flow of inviscid fluid p 143 A89-17150 [ AD-A1971 851 p 192 N89-13784 visualization program CAPECE, V. R. CHIN, DONALD SDAR A high productivity software engineering [ AD-A1986841 p 152 N89-13404 Measurement and analysis of unsteady flow structures - environment for embedded systems BOGACHEV, A. S. in rotor blade wakes p 147 A89-18946 Optimization of algorithms for data processing in radar [AIAA PAPER 88-38651 p 198 A89-18062 CARADONNA, FRANCIS X. altimeters with electronic stabilization of the radiation CHOPRA, INDERJIT An entropy and viscosity corrected potential method for pattern p 174 A89-18401 Aeroelastic optimization of a helicopter rotor rotor performance prediction p 145 A89-18857 BOLSHEV, A. p 163 A89-18898 Data link organization in Mode S secondary surveillance CAREL, OUVIER Rotorcraft aeromechanical analysis using a nonlinear radar svstems .Guerational comoatibilitv.. with other Mode Special committee on future air navigation systems unsteady aerodynamic model p 146 A89-18919 S systems (FANS) P160 A89-18754 Static aerwlastic characteristics of circulation control [AIAA PAPER 8840031 p 159 A89-18157 CARLOMAGNO, GIOVANNI M. Wings p 167 A89-20144 BOOTH. FRANK Characterization of boundary layer conditions in wind CHUNG, WILLIAM Advanced Apache architeclure tunnel tests through IR thermography imaging Evaluation of simulator motion characteristics based on [AIM PAPER 88.39281 p 174 A89-18188 P 147 A89-19167 AGARD-AR-144 pfOCedUreS p 183 A89-19565 BOYD, MARK A. CARLSON, LELAND A. CIMBAIA, J. M. An approach to aoiving large reliability models Transonic wing design using inverse methods in Experimentalinvestigation of a jet impinging on a ground [AIM PAPER 88-39051 p 199 A89-15056 curvilinear coordinates p 151 A89-20316 plane in crossflow p 149 A89-20141

6-2 P€RSONAL AUTHOR INDEX EMAMI, S.

CLARK, CURT CUSCHIERI, J. M. DOWNEY, DAVID A. Reconfigurable flight control system simulation Application of the mobility power flow approach to Rotor system evaluation, phase 1 p 181 A89-19558 Structural response from distributed loading [AD-A198794] p 168 N89-13425 CLARKE, CHARLES W. [NASA-CR-181342] p 193 N89-13817 DREES, JOHN M. Evolution of the ACAP crash energy management CUSHING, MICHAEL A MIL-STD-1750A. single-boardcomputer lor embedded system p 164 A89-18923 One million pixel full color liquid crystal display for multiprocessor applications CLAY, DALE avionics applications [AIM PAPER 8840151 p 200 A89-18163 Helicopter vibration analysis and control [AIM PAPER 88-39671 p 173 A89-18134 DRESS, DAVID A. p 188 A89-18871 CUTTS, D. G. The 13-inch magnetic suspension and balance system COHN, MARC D. Structural dynamics of a helicopter rotor blade system wind tunnel The fiber optic data distribution network .A network p 162 A89-18878 [NASA-TM-4090] p 184 N89-14241 for next-generation avionics systems DREWER, CHRIS [AIAA PAPER 88-40111 p 188 A89-18161 Down with drag p 141 A89-18347 COLE, LYNN D DRING, R. P. Central maintenance computer system - A bold step The effects of inlet turbulence and rotor/stator forward on the 747-400 DAME, L T. interactions on the aerodynamics and heat transfer of a [AIM PAPER 88-40391 p 171 A89-18097 Gmstitutie modeling for isotropic materials large-scale rotating turbine model, volume 1 COLEMAN, ERNEST W. [NASA-CR-174805] p 177 N89-13436 [NASA-CR-40791 p 192 N89-13756 Thunderstorm avoidance for general aviation aircran DARLOW. M. DUFM. R. [AIM PAPER 88-39551 p 172 A89-18125 The Center of Excellence in Rotary Technology at The Center of Excellence in Rotary Technology at COLESTOCK, MARK Rensselaer Polytechnic Institute Rensselaer Polytechnic Institute A parallel modular signal processor [AD-A198964] p 168 N89-13426 [AD-A1989641 p 168 N89-13426 [AIAA PAPER 88-3981] p 199 A89-18141 DATTA, SMRlTlMAY DUGAN,JOANNEBECHTA COLTMAN, JOSEPH W. Matrix analysis method for composite llexbeam An approach to solving large reliability models The development of the V-22 Osprey armored p 190 A89-18926 [AlAA PAPER 88-39051 p 199 A89-18086 energy-absorbing crewseat assembly DAVARIAN, F. DULIKRAVICH. GEORGE S. p 155 A89-18883 Irreducible error rate in aeronautical satellite channels Analysis ofartificial dissipation models lor the transonic CONROYD, JACK H., JR. p 157 A89-17183 full-potential equation p 191 A89-20188 Dynamic stall computations using a zonal Navier-Stokes DAVIS, BRADFORD S. DUNFORD, P. model Internal pressure measurements for a liquid payload at Development and qualification testing, teaming for the [ AD-A1979421 p 194 N89-14397 low Reynolds numbers V-22 multi-service aircraft system p 165 A89-18928 COOLEY, WILLIAM W. [AD-A1974381 p 191 N89-13727 DUNN, M. H. Lightning simulation test technique evaluation DAVIS, MARK W. Users' manual for the Langley hghspeed propeller noise [DOT/FAA/CT-87/38] p 156 N89-13415 Experimental verification of helicopter blade designs prediction program (DFP-ATP) CORKE, THOMAS op!imized lor minimum vih:a!icn p 162 AB9-!@@74 [NASA-CR-4208] p 204 N89-14820 Equipment to upgrade the facilities of the IIT (Illinois DAVIS, S. JON Institute 01 Technology) Fluid Dynamics Research An examinationof some rotor aerodynamic models using Center the RSRA/X-wing model test data p 146 A89-18858 E [AD-A1980841 p 184 N89-14242 DAVISON, J. W. CORKE, THOMAS C. Reconfgurable flight control: An opportunity lor EAST, R. A. Management and control of unsteady and turbulent integrated diagnostics p 182 N89-14744 Interference eflects associated with a platesupported flows DE LUCA, LUlGl hall-model in hypersonic flow p 148 A89-19924 [ AD-A198091 ] p 192 N89-13751 Characterization of boundary layer conditions in wind EDMAN, FREDERICK C. CORON, P. tunnel tests through IR thermography imaging Robotic deburring 01 complex machined parts Use of the GALA and PAIAS tools to enhance the p 147 A89-19167 p 190 A89-18936 development of avionic software DECHAUMPHAI, PRAMOTE EDNIE, CHARLIE V. [AIAA PAPER 88-39431 p 199 A89-18115 Coupled flow, thermal, and structural analysis of The development of the V-22 Osprey armored CORRIGAN, J. J. aerodynamically heated panels p 181 A89-20322 energy-absorbing crewseat assembly Developments in dynamics methodology at Bell DESJARDINS, R. p 155 A89-18883 Helicopter Textron p 162 A89-18875 Six degree of freedom crew isolation design, bench test EDWARDS, J. A. and lliht test p 163 A89-18896 cosns, c. E. Computational analysis of unsteady supersonic cavily Vortical wakes over a prolate spheroid DEVORE. JOHN J. flows driven by thick shear layers p 145 A89-18803 p 150 A89-20181 Interlacing Sensor assemblies with windowless cockpit EDWARDS, T. A. displays p 187 A89-17979 Numerical simulation of tip vortices of wings in subsonic COX, MAURICE E. DEWALT, MICHAEL P. The mode S data link Experimental work and possible and transonic flows p 150 A89-20176 - Comparison 01 FAA DO-178A and DOD-STD-2167A future applications in Western Europe opproochos !o sohare calrification EGOLF, T. ALAN Heiicopier iree wake prudir;iiuti ui compiei +eke [AIM PAPER 88-39991 p 158 A89718155 [AIAA PAPER 86-40441 p 142 A89-19864 structures under Blade-Vortex Interaction operating COX, PRESTON A. OEYST, JOHN J., JR. conditions p 146 A89-18918 On-board expert diagnostics for an avionics Modular avionics systems studies subsystem p 202 N89-14758 [AIAA PAPER 88-38501 p 169 A89-18052 EHLERS, F. E. COY. JOHN J. DIEFENWRF, R. J. Coupling linearized far-field boundary conditions mth Advanced transmission Studies p 189 A89-18906 The Center of Excellence in Rotary Technology 81 nonlinear near-field solutions in transonic flow CRITTENDEN. LUCILLE Rensselaer Polytechnic Institute [AD-A198721] p 153 N89-13405 Stereo 3-D and non-stereo presentations of a [AD-A198%4] p 168 N89-13426 EISS. N. S. computer-generated pictorial pnmary flight display with DIPADUA, M. A. A fundamental approach to the sticking of insect pathway augmentation Comparison 01 the general dynamics ground clobber residues to aircraft wings [AIM PAPER 88.39651 p 173 A89-18132 algorithm with the GCAS and laws algorithms [NASA-CR-183041I p 156 N89-13414 CRONKHITE, JAMES D. [AD-At 984791 p 157 N89-14226 EKVALL, J. C. Bell ACAP full-scale aircraft crash test and KRASH DIPASQUALE. FRANK Evaluation 01 aluminum-lithium alloys in correlation p 164 A89-18920 Advanced lube system diagnostics lor V-22 compression-stifleneed aircraft structures CROSS, JEFFREY L p 190 A89-18907 p 191 A89-20315 Two-dimensional aerodynamic characteristics of the DIXON, SIDNEY C. ELBER, WOLF OLSITAAT airfoil Materials and structures for hypersonic vehicles Mechanics of fatgue crack closure [NASA-TM-89435] p 154 N89-14216 [NASA-TM-101501] p 186 N89-14264 p 186 A89-17401 CUNNINGHAM, A. M., JR. DJORDJEVICH, ALEXANDER ELLIOTT, ANDREW S. Modelling of ground effectson aircran Unsteady low-speedwindtunnel test 01 a straked delta Rotorcraft aeromechanical analysis using a nonlinear p 166 A89-19559 wing, oscillating in pitch. Part 4 Plots of time histories 01 unsteady aerodynamic model p 146 A89-18919 pressures and overall loads DOGGER, C. S. ELLIOTT, ANDREW SETH Unsteady low-speed windtunnel test of a straked delta [ AD-A1986821 p 152 N89-13402 Calculation 01 the steadily periodic and gust responses wing, oscillating in pitch. Pari 4: Plots of time histories of Unsteady low-speed windtunnel test of a straked delta of a hingeless rotor helicopter using two-dimensional time pressures and overall loads domain unsteady aerodynamics p 182 N89-14240 wing, oscillating in pitch. Part 5 Power spectral density [ AD-A1986821 p 152 N89-13402 ELLIOTT, JOE W. plots of the overall loads for harmonic oscillation and the Unsteady low-speed windtunnel test of a straked delta Rotor inflow variability with advance ratio response 01 overall loads to (I-COS) inputs wing, oscillating in pitch. Part 5: Power spectral density p 145 A89-18855 [AD-A198683] p 152 N89-13403 plots of the overall loads for harmonic oscillation and the Unsteady low-speed windtunnel test of a straked delta response 01 overall loads to (1-COS) inputs ELMORE, CRESSWELL D. wing, oscillating in pitch. Part 6: Presentation of the [AD-AI 986831 p 152 N89-13403 Improved life cycle 'reps' services - V-22 engineering visualization program Unsteady low-speed windtunnel test of a Straked delta technical services and logistics planning [AD-A198684] p 152 N89-13404 wing. oscillating in pitch. Part 6: Presentation of the p 142 A89-18873 CUNNINGHAM, HERBERT J. visualization program EMAMCNAEINI, ABBAS Modern wing flutter analysis by computational fluid [AD-A198684] p 152 N89-13404 Effect 01 model uncertainty on failure detection - The dynamics methods p 191 A89-20146 DOYPKA, ROBERT V. threshold selector P 197 A89-17965 CURTISS. H. C.. JR. Investigation 01 diflicult component effects on FEM EMAMI. S. Studies of the dynamics 01 the twin-lift system vibration prediction lor the AH-1G helicopter Measurements in the field of a spark excited [NASA-CR-1832731 p 167 N89-13422 p 162 A89-18879 compressible axisymmetric jet p 203 A89-18948 8-3 PERSONAL AUTHOR INDEX

EREYIN, V. V. FOURNIER, JEAN GIANNAKOGLOU, K. Determination of the perturbations of the flow fields of Radionavigation needs for the Europe of the future Computation of rotational transonic flows using a supersonic wind tunnels from measured aerodynamic p 160 A89-18753 decompositicn method P 150 A89-20179 cwfficients p 144 ABS-18675 FRANKS, HERMAN GILLMAN. HERBERT, 111 ERICSSON, L E. Achieving reliability and maintainability goals with a A parallel architecture for a reel-time blade element Comment on 'Aeroelastic oscillations caused by composite main rotor blade p 189 A89-18892 rotorcraft simulation P 201 A89-19560 transitional boundary layers and their attenuation' FRANZEL, JOHN R. GLASSYAN. ARTHUR J. p 167 A89-20150 A fault tolerant integrated avionics computer system Advanced core technology: Key to subsonic propulsion Moving wall effects in unsteady flow [AIM PAPER 88-4041I p 173 A89-18165 benefits p 150 A89-20311 FRAZIER, W. E. [NASA-TM-101420] p 178 N89-14237 PM AI alloys Hot prospects for aerospace Flow unsteadiness considerations in high-alpha testing - GLEASON, DANIEL appbitions p 185 A89-17622 p 151 A89-20319 Fault detecton and isolation for reconfigurable flight FRENCH, ROBERT 0. control systems EROL, N. Genesis of a flexible turning center Progress towards a wmmarcial aircraft design expert [AIAA PAPER 88-38601 p 170 A89-18058 p 189 A89-18894 GLICKSTEIN, IRA system FREYMUTH! PETER [DGLR PAPER 87-1201 p 167 A89-20237 Application of AI technology to time-critical functions Threedimensionalvortex systems of finite wings [AIAA PAPER 88-40301 p 174 A89-18190 ETHERINGTON, RICHARD E. p 149 A89-20148 GOKA, TSUYOSHI General aviation cost effectiveness FRIEDMAN, HARLAN W. Recent studies of MLS application p 204 A89-20136 Design and fabrication of an advanced light rotor [AIAA PAPER 88-39161 p 157 A89-18093 ElTL, HANNSULRICH p 163 A89-18880 GOLDYAN, P. C. Modem tigital pressure control system FRIEDYANN, P. P. The high speed bus technology development program [AIM PAPER 88-39481 p 172 A89-18119 Design of a simple active controller to suppress [AIAA PAPER 88-40051 p 187 A89-18158 EVERSMAN, W. helicopter air resonance p162 A8918877 GOLUBKIN, V. N. Application of transient aerodynamics to the structural FRYYIER, PAUL D.. JR. Calculation of hypersonic flow past the windward side nonlinear flutter problem p 182 A89-20323 Navier-Stokes calculations using Cartesian grids. I - of a low-aspect-ratio wing at high angles of attack Laminar flows p 150 A89-20180 p 144 A89-18357 FU, S. J. GOORJIAN, PETER M. F Multiple sample polygonal correlation algorithm for the Unsteady transonic aerodynamics and aeroelastic determination of ground emitter location calculations at low-supersonic freestreams FAN, FElDA [AIAA PAPER 88.39871 p 158 A89-18145 p 149 A89-20145 Effect of blade mistuning and bladedisk on cascade FUJIMURA, TETSUJI GOULD, WARREN flutter boundaries p 176 A89-19803 Conceptual study of tubengines for horizontal takeoff Rotor system evaluation, phase 1 FELKER, FORT F. and landing space plane [ AD-A1987941 p 168 N89-13425 Comparisons of predicted and measured rotor [IAF PAPER 88-2531 p 184 A89-17745 GRAF, VIRGIL A. performance in hover using a rmw free wake analysis FULLER, C. R Human factors impact on the V-22 Osprey cockpit p 165 A89-18933 Influence of afloor on sound transmissbn into an aircraft development - An overview p 174 A89-18865 FELLMAN, LYNNE fuselage model p 166 A89-20135 GRANT, LARRY V. Air traffic control (ATC) and airlground digital FURA, DAVID An overview of the Federal Radionavigation Plan wmmunications - Demonstration and evaluation Design and validation of the IFTAS fault-tolerant clock p 160 A89-20123 [AIAA PAPER 88-39981 p 158 A89-18154 [AIAA PAPER 55-38991 p 170 A89-18085 GRASSO, JERRY M. FELTER, S. C. Universal Ada Test Language (UATL) to support Terminal navigation for the Combat Talon I1 aircraft real-time softwarelsystem integration and [AIAA PAPER 88.40211 p 159 A89-18173 factorylmaintenancefaun isolation p 197 A89-18009 FENG, GANG G GRAUER, WILLIAM K. Design of multi-level flight control systems GABEL, R. Rotorlairframe interactions on liltrotor aircraft p 181 A89-19813 Six degree of freedom crew isolation design, bench test p 161 A89-18854 FENG, YUNCHENG and flight test p 163 A89-18896 GREEN, DAVID L The combination of simulation and response Air combat tactics for the evaluation of rotorcraft methodology and its applicationin an aggregate production GALLY, THOMAS A. Transonic wing design using inverse methods in characteristics in the low air war of 2010 plan p 190 A89-19806 curvilinear coordinates p 151 A89-20316 p 142 A89-18859 FERTIS, D. G. GRIBBIN, WALTER J. GARLINGTON, KEN Parametric studies of advanced turbqxops Aeronautical satellite networks p 160 A89-20117 A case study F-16 Ada Digital Flight Control System [NASA-TM-101389] p 195 N89-14465 - GRIFFIN, ARTHUR F. [AIAA PAPER 88-391 1 ] p 171 A89-18090 FIELDING, J. P. Hybrid architecture of field-tested diagnostic expert Progress towards a commercial aircraft design expert GATLIN. GREGORY Y. system p 198 A8918034 system Thrust-feveWr flow investigation on a twin-engine GRISHIN, A. M. [DGLR PAPER 87.1201 p 167 A8920237 transport Mathematical modeling of laminar and turbulent FIELDS, ROGER A. [ NASA-TP-28561 p 153 N89-14213 supersonic flow past wnvex-concave bodies Buckling characteristics of hypersonic aircraft wing GAUBERT, M. p 144 A89-18671 tubular panels Hub loads analysis of the SA34912 helicopter GRISHIN, V. 1. [NASA-TM-87756] p 193 N89-13816 [NASA-TM-t01061] p 153 N89-13410 A study of contact interaction in aircraft structural FILIPPOV, S. E. GAUFFRE, G. elements p 188 A89-18644 Determination of the perturbations of the flow fields of Detection of laminar-turbulent transition by infrared GROSE, D. L supersonic wind tunnels from measured aerodynamic thermography p 143 A89-17147 Multiple sample polygonal cmelation algorithm for the coefficients p144 A89-18675 GAVERN, J. determination of ground emitter location FILLER, ROBERT R. Comparison of the general dynamics ground clobber [AIAA PAPER 88.39871 p 158 A89-18145 Matrix analysis method for composite flexbeam algonhm with the GCAS and !aws algcmhms GROSVELD, FERDINAND W. p 190 A89-18926 [AD-A1984791 p 157 N89-14226 Acoustic transmissibility of advanced turboprop aircraft FISCHER, B. GEBYAN, JEAN windows p 204 A89-20143 Prqect for an advanced rmaltranspat aircraft Faults with nonstationary observability are limiting GRUESSNER, ROBERT [DGLR PAPER 874791 p 167 A89-20236 avionics R8M Integrated diagnostic concepts lor advancedtechnology FISCHER, WILLIAM C. [AIM PAPER 88-38521 p 169 A89-18054 rotorcraft p 141 A89-18023 X-wing fly-by-wire vehicle management system GEISELHART, R. GUNDY. KAREN [AIM PAPER 88.39231 p 179 A89-18100 Comparison of the general dynamics ground clobber Transonic Navier-Stokes solutions for a fighter-like FmGERALD, JAMES M. algorithm with Me GCAS and laws algorithms configuration p 149 A89-20134 A comparison of awustic predicfions with model rotor GUNNINK, JAN WILLEY test data from the NASA 14 x 22 ft wind tunnel [ADA1984791 p 157 N89-14226 GELDERLOOS, HENDRIK Design stutiis of primary aircraft structures in ARALL p203 A8818913 laminates p 167 A89-20318 FLANNELLY, W. 0. Vehicle management system for a manned hypersonic vehicle GUNSALLUS, C. T. Holometrics - An information transformation Holometrics An information transformation [AIAA PAPER 88-38771 p 179 A89-18071 - methodology p 200 A89-18922 methoddogy p 200 A89-18922 FLATHERS, GEORGE W. GEURTS, E. G. GURUSWAMY, GURU P. The future of aeromobile digital communications Unsteady low-speed windtunnel test of a straked delta Unsteady transonic aerodynamics and aeroelastic wing, oscillating in pitch. Part 4: Plots of time histories of [AIM PAPER 88-4001] p 158 A89-18156 calculations at low-supersonic freestreams pressures and Overall loads FLEETER, S. p 149 A89-20145 Measurement and analysis of unsteady flow structures [ AD-A1986823 p 152 N89-13402 GUSTAVSON, B. A. in rotor blade wakes p 147 A89-18946 Unsteady low-speed windtunnel test of a straked delta Tip loss and blade strike simulations using DYSCO FLORES, JOLEN wing. oscillating in pitch. Part 5: Power spectral density p164 A89-18901 Transonic Navier-Stokes solutions for a fighter-like plots of the overall loads for harmonic oscillation and the GUTH, R. E. configuration p 149 A89-20134 response of Overall loads to (1-cOS) inputs Reconfgurable fliht control: An oppwlunity for FORNASIER, L [ADA1986831 P 152 N89-13403 integrated diagnostics p 182 N89-14744 Anaiysis of a hghter type aircraft confguration with the Unsteady low-speed windtunnel test of a straked delta GYEKENYESI, JOHN P. HISS panel method at subsonic and supersonic wing, oscillating in pitch. Part 6 Presentation of the A review of failure models for unidirectional ceramic speeds visualization program matrix composites under monotonic loads [DGLR PAPER 874851 p147 A8819660 [ AD-A1986843 P 152 N89-13404 [NASA-TM-101421I p 195 N89-14470 PERSONAL AUTHOR INDEX JOHNSON, ALAN M.

H HEFFERNAN. R. M. HOWE, Y. S. Hub loads analysis of the SA34912 helicopter Contributions to the theory of sound production by HAAS. DAVID J. [NASA-TM-101061] p 153 N89-13410 vortex-airfoil interaction, with application to vortices with Static aeroelastic characteristics of circulation control HEFFRON, SUSAN E. finite axial velocity defect p 203 A89-19672 wings p 167 A89-20144 Atmospheric photochemical modeling of turbine engine HOWELL, DAN? 6 HADLEY, BRENT L fuels and exhausts. Computer model development,volume Modeling mission reliability of advanced integrated CEPS: An artificial intelligence approach to avionics 1 communication, navigation, identification avionics maintenance p 201 N89-14749 [AD-A198690] p 196 N89-13832 systems HAEFFELE, B. A. Atmospheric photochemical modeling 01 turbine engine [AIM PAPER 88-40231 p 173 A89-18174 Isolated testing of highly maneuverable inlet con cepts fuels and exhausts. Computer model development,volume HSIEH, P. Y. [NASA-CR-179544] p 178 N89-13437 2 Developments in dynamics methodology at Bell HAIGES, KARL R. [AD-A198691] p 196 N89-13833 Helicopter Textron p 162 A89-18875 Vehicle management system archaecblral HEISS, S HSU, WEN-YUAN considerations Analysis of a fghter type aircraft configuration with the Study the aerodynamics characteristics of airfoil on [AIM PAPER 88.38751 p 174 A89-18189 HIS panel method at subsonic and supersonic vector processors HAW, ELlAS HU,[IAF HONG PAPER ST-88-09] p 143 A89-17874 speeds One million pixel full color liquid crystal display for [EGLR PAPER 87-0851 p147 A89-19660 avionics applications Full-potential integral solution for transonic flows with HEMANN, JOHN H. [AIM PAPER Et!-39671 p 173 A89-18134 and without embedded Euler domains A review of failure models for unidirectional ceramic HALL, JAMES T. p 148 A89-19908 matrix Composites under monotonic loads Achieving reliability and maintainability goals with a HUGHES, A. J. [NASA-TM-101421] p 195 N89-14470 composite main rotor blade p 189 A89-18892 Mode S data link applications research in the UK HALL, K. HEPNER, DAVID J. [AIM PAPER 88-39961 p 158 A89-18153 Zonal grid generation method for complex Internal pressure measurements for a liquid payload at HUlT, 0. R. configurations p 201 A89-20139 low Reyndds numbers Interference effects associated with a plate-supported HAMILTON, BRIAN [ AD-A1974381 p 191 N89-13727 half-model in hypersonic flow p 148 A89-19924 Optimal design of an advanced composite rotating HERNANDEZ FRANCISCO J. HYLTON. L D. flex beam p189 A89-1W Flight measured and calculated exhaust jet conditions The effects of leading edge and downstream film cooling HAMILTON, P. L for an F100 engine in an F-15 airplane on turbine vane heat transfer A microcomputerpollution model for civilian airports and [ NASA-TM-1004191 p 177 N89-13435 [ NASAGR-1821331 p 192 N89-13754 air force bases, model description HERRLIN. JACK Y. [AD-A199003] p 197 N89-14616 Vehicle management system for a manned hypersonic HAMLIN, DARYLE B. vehicle I High-speed data bus processing node [AIAA PAPER 88-38771 p 179 A89-18071 [AlAA PAPER 88.40091 p 201 A89-19861 HERRMANN, 0. ISHII, R. HAMPP, RALPH Design and integration of air-breathing propulsion Hole tone generated from almost choked to highly Software development for large scale avionic integration systems of space transports and hypersonic aircraft choked jets p 203 A89-19903 programs p 200 A89-18864 [DGLR PAPER 87-1031 p 176 A89-20241 ISHIKAWA, ICHIRO Fan acowc modes measuring system HANING, ROBERT K. HESS, RICHARD F. Fabrication and testing 01 lightweight hydraulic system p 183 A89-19950 Sharing the protection of aircraft electronic systems ISOMURA, KOUSUKE simulator hardware. Phase 2: Addendum against the effects 01 high-level electromagnetic Fan acoustic modes measuring system [ ADA1985241 p 184 N89-14243 environments between traditional protection and system HANSCH, MARK R. p 183 A89-19950 architecture IWASAKI, KOJl An overview of SEDACS - A state of the art TRDITPS [AIAA PAPER 88-39171 p 187 A89-18094 Triplex digital flight control System for the STOL research environment p 198 A89-18030 HEYSSE. PAUL D. HAQUANG, NlNH aircraft 'Aska' Cockpit management for regional airlines and business Dynamic inflow lor practical applications [AIM PAPER 88-38831 p 179 A89-18077 aircraft as applied in the Beech Starship IYER, R. K. p 147 A89-19625 [AIAA PAPER 88-39571 p 173 A89-18126 HARDY, GORDON H. ImDact of device level faults in a dioital avionic Simulation evaluation of helicopter Terrain HICKS, JOHN W. processor FollowinglTenainAvoidance concepts Real-time flight test analysis and display techniques for [AIM PAPER 88-39041 p 172 A89-18112 the X-29A aircraft [AIAA PAPER 88-39241 p 180 A89-18101 HARRIS, MICHAEL [ NASA-TM-1016921 p 168 N89-13424 Detaileddesign specification for a prototype Assessment HILL, TODD J System for Aircraft Noise (ASAN) Design and validation of the IFTAS fault-tolerant clock [AIM PAPER 86-38991 p 170 A89-18085 JACOBS, HERBERT [AD-A197936] p 204 N89-14818 Corrosion and corrosion control of selected field !!A!?!?!S. U!cIUAEI HILLS. ANDY D. E. prubiarris F, i62 AGB-iGGiC Avionics fault tree analysis and artificial intelligence for Fault tolerant avionics [AIAA PAPER 88-39011 p 171 A89-18109 JAGIELSKI. MIKE future aircraft maintenance 0202 N89-14760 Tiltrotor evolution leads to ASW revolution HARRIS, ROBERT L HIYANSU, A. p 142 A89-18862 Modeling mission reliability of advanced integrated Multigrid acceleration of a relaxation procedure for the JAMESON. ANTONY communication. navigation, identification avionics reduced Navier-Stokes equations p 148 A89-19904 Aerodynamic design via control theory systems HINDSON, W. S. [NASA-CR-181 7491 p 153 N89-13408 [AIAA PAPER 88.40231 p 173 A89-18174 Development and flight test of a precision autohover JANAKIRAY, R. D. HARRIS. W. D. capability for tactical rotormall p 165 A89-18934 NASAIAHS rotorcraft noise reduction program - Methodology for fatigue substantiation of alternate HINTZ, JOSEPH C. McDonnell Douglas Helicopter Company sources and degraded modes on helicopter dynamic Expert systems in higher echelon maintenance accomplishments p 143 A89-20747 components p 164 A89-18924 activities p 202 N89-14761 JANEX. ALBERT HARTMAN, LAWRENCE J. HOAD, DANNY R. Reflections on avionic integration Boeing Model 360 Advanced Technology Helicopter - Rotor inflow variability with advance ratio [AIM PAPER 88.39501 p 172 A89-18121 Design features and flight test update p 145 A89-18855 JEl, Y.G. p 165 A89-18935 HOEPPNER, 0. W. Modal analysis of continuous rotor-bearing systems HASSAN, AHMED A. Dwell time effects on the fatigue behaviour of titanium p 188 A89-18786 A correlation study of rotor inflow in forward flight alloys p 185 A89-17619 JIANG. C. W. p 145 A89-18856 HOFFMAN, 8. A potential flow solution on marine propeller and axial HASSAN, H. A. Processing composite finite element model with rotating fan Navier-Stokes calculations using Cartesian grids. I - CADCOMP p 166 A89-19982 [AD-A198781] p 191 N89-13735 Laminar flows p 150 A89-20180 HOH, ROGER JIANG. GUlQlNG HAYASHI, MASANORI The impact of yaw axis control modes. lliht directors An investigation of wall interference correction to the A study on aerodynamic heating in the interaction regions and automatic control coupling on decelerating IFR pressure measurement in low speed wind tunnel with solid approaches for rotorcraft p 180 A89-18903 of shock waves and turbulent boundary layers induced walls p 183 A89-19808 HOLLEY, CHARLES D. by sharp fins p 148 A89-20131 JINES, LANNY A. Human factors impact on the V-22 Osprey cockpit HypeNelOCity technology escape system concepts A study on hypersonic shock tunnel development An overview p 174 A89-18865 - program p 184 A89-17929 p 148 A89-20132 HOLLIFIELD, PATRICK J. HAYNIE, DAVID A. Determination of control laws for a single pilot, attack JOHNS, ALBERT L Advancements in erosion testing of rotor blade leading helicopter p 180 A89-18904 Experimental results fer a two-dimensional supersonic edges p 163 A89-18888 HOLST, TERRY L inlet used as a thrust deflecting nozzle HEBSUR, M. 0. Transonic Navier-Stokes solutions for a fighter-like [ NASA-TM-834391 p 194 N89-14386 An investigation of environmental influence on the creep configuration p 149 A89-20134 JOHNSON, ALAN M. behavior of a low pressure plasma sprayed NCoCrAlY HOPKINS. HARRY Optical fire detector testing in the aircraft engine nacelle alloy p 186 N89-13648 Sizing up the 146-300 p 161 A89-18346 fire test simulator HEFER, 0. Boeing 747-400 - Flight test p 161 A89-18349 [ADA1979741 p 168 N89-13427 Improving the half-model technology in the Goeningen HOWARD, CHERYL 0. Fireextinguishing agent evaluation in the Aircraft Engine transonic wind tunnel Standardized advanced infrared Senw - A program Nacelle Fire Test Simulator (AENFTS) [DGLR PAPER 87-0831 p183 A89-20234 staius p 175 A89-18932 [ADA1985231 p 157 N89-14227

8-5 JOHNSON, R. C. PERSONAL AUTHOR INDEX

JOHNSON, R. C. KILMER, ROBERT L, JR. L Analytical determination and experimental comparison Guidance and Flight Director system for the V-22 of performance degradation on a helicopter main rotor Tiltrotor LACKEY, W. J. due to ice accretion p 155 A89-18909 [AIAA PAPER 88-39211 p 179 A89-18098 Chemical vapor deposition of oxidation resistant HfB2 JOHNSON. W. KIM, S. + Sic composite coatings p 185 A89-19481 Hub loads analysis of the SA34912 helicopter lmoact of device lwel faults in a diaital avionic LAFLEN, J. H. [ NASA-TM-1010611 p 153 N89-13410 processor Constitutive modeling for isotropic materials JOHNSON, W. W. [AIM PAPER 88.39041 p 172 A89-18112 [NASA-CR-174805] p 177 N89-13436 Dynamic perspective displays and the control of tilt-rotor KIRCHNER, TED E. LAGACE, PAUL A. aircraft in simulated flight p 174 A89-18867 Automated fatigue crack growth measurement Buckling and final failure of graphite/PEEK stiffener JOHNSON, WILLIAM G., JR. [ AD-A1986421 p 195 N89-14466 sections p 190 A89-19911 The 13-inch magnetic suspension and balance system KJELGAARD, SCOlT 0. LAMBRECHT, RICHARD 1. wind tunnel Theoretical derivation and calibration technique of a ATE hardware diagnostics, fault detection. and fault [ NASA-TM-40901 p 184 N89-14241 hemispherical-tipped.five-hole probe isolation tool (Self-test adapter) p 197 A89-18015 JOHNSTON, DONALD E. [NASA-TM-4047] p 151 N89-13396 LARSEN, WILLIAM E. Autonomous RPRV navigation, guidance and control KLUG, H.G. A method of measuring fault latency in a digital flight [ NASA-CR-1794251 p 161 N89-14228 Project for an advanced regional transport aircraft control system JONES, J. D. [DGLR PAPER 87-0791 p 167 A89-20238 [AIM PAPER 88-38631 p170 A89-18060 Influence of a floor on sound transmission into an aircraft KLUNOVER, A. Sharing the protection of aircraft electronic systems fuselage model p 166 A89-20135 Processing composite finite element model with against the effects of high-level electromagnetic JOSLYN, H. D. CADCOMP p 166 A89-19982 environments between traditional protection and system The effects of inlet tulbulence and rotorlstator KNIP, GERALD, JR. architecture interactions on the aerodynamics and heat transfer of a Advanced core technology: Key to subsonic propulsion [AIM PAPER 88-39171 p 187 A89-18094 largescale rotating turbine model, volume 1 benefits LARSON, ERIK S. [ NASA-CR-40791 p 192 N89-13756 [ NASA-TM-1014201 p 178 N89-14237 Low-speed pressure distribution on axisymmetric JUDD, THOMAS D. KNOLLER. HENRY elliptic-nosed bodies p 149 A8920147 Automatic dependent surveillance data transfer Sharing the protection of aircraft electronic systems LASKEY, J. M. [AIAA PAPER 88-39971 p 159 A89-18180 against the effects of high-level electromagnetic The enemy is FA, CND, and RTOK environments between traditional protection and system p 141 A89-18025 architecture LATCHFORD, JACK K [AIAA PAPER 88-39171 p 187 A89-18094 Tiltrotor evolution leads to ASW revolution KO, WILLIAM L p 142 ABS-18862 KAJI, SHOJIRO Buckling characteristics of hypersonic aircraft wing LAU. MING-LEUNG Experimental study on unsteady aerodynamic tubular panels US Army aircraft combat maintenancelbattle damage characteristics of an oscillating cascade with tip [NASA-TM-87756] p 193 N89-13816 repair program p 142 A89-18860 clearance p 148 A89-19927 KOELMAN, H. J. W. M. LAVOIE. ROBERT P. KANDIL, OSAMA A. COCOMAT, a CAE system for composite structures Modular avionics systems architecture (MASA) - Seeds Full-potential integral solution for transonic flows with design p 166 A89-19981 of destruction or seeds of progress? and without embedded Euler domains KOLKHORST, E. 0. [AIAA PAPER 88-3851I p 141 A89-18053 p 148 A89-19908 Developing error-free software p 201 A89-19679 LAVRAKAS, JOHN W. KAPASOURIS, PETROS KOMIAK, JAMES J. An overview of space-based radionavigation systems Design of feedback control systems for unstable plants GaAs MMlCs satisfy EW requirements p 160 A89-20122 with saturating actuators p 188 A89-18757 LAWRENCE, WILLIAM S. [NASA-CR-1833921 p 194 N89-14377 KOPCHENOV, V. 1. The V-22 - ’Am I gonna like it?’ p 167 A89-20745 KATO, KANICHIRO Self-similar problem of the separated flow of an ideal LEEEDEV, P. D. A note on the optimal hypersonic flight path fluid past an expanding plate p 144 A89-18669 Performance of coated materials in high-enthalpy p 167 A89-20637 KORKAN. K. D. oxidizing gas flows p 185 A89-18650 A note on the aircraft minimum-time turns AnalyWal determination and experimental Comparison LEE, C.-W. p 182 A89-20638 of performance degradation on a helicopter main rotor Modal analysis of continuous rotor-bearing systems KATOH, ZOJIRO due to ice accretion p 155 A89-18909 p 188 A89-18766 Introduction of Pilot‘s Operational Workload Evaluation KRAIKO, A. N. LEE, IN Research Simulator, POWERS, in Aeromedical Laboratory, Self-similar problem of the separated flow of an ideal Plenum chamber effect on wind-tunnel resonance by JASDF p 183 A89-19876 fluid past an expanding plate p 144 A89-18669 the finite-element method p 190 A89-19909 KAlT, D. R. KRASNOWSKI, 8. R. LEE, Y. T. Vehicle management system requirements Application of damage tolerance methodology to A potential flow solution on marine propeller and axial [AIM PAPER 88-38781 p 179 A89-18070 helicopter dynamic components using the example of a rotating fan KAUFMAN, R. M. main rotor pitch link for the AH-1S helicopter [AD-A198781] p 191 N89-13735 The effects of leading edge and downstream film cooling p 164 A89-18921 LEFEBVRE, ARTHUR H. on turbine vane heat transfer KRETSCHMAR, K. Selected papers on fundamental aspects of gas turbine [NASA-CR-1821331 p 192 N89-13754 New application possibilities for balloon-borne casB combustion p 177 A89-20625 KAZA, KRISHNA RAO studies - MIKROBA (Microgravity by balloons) LEIS, H. Aeroelasti response of metallic and composite propfan [DGLR PAPER 874691 p 184 A89-20233 Carbon fiber composites for supersonic technology models in yawed flow KROEGER, BRIAN W. [DGLR PAPER 87-1241 p 185 A89-20244 [AIM PAPER 88-31541 p 175 A89-17942 An SAE high speed ring bus overview LEISHMAN, J. G. KAZA, KRISHNA RAO V. [AIM PAPER 88-40081 p 187 A89-18159 Validation of approximate indicia1aerodynamic functions Vibration, performance. flutter aid forced response KROOMANN, UWE K. for two-dimensional subsonic flow p 149 A89-20140 characteristics of a large-scab propfan and its amoelastic Optimal integration of inertial sensor functions for LEISHMAN, J. GORDON model flight-controland avionics Rotorcraft aeromechanical analysis using a nonlinear [AIM PAPER 88-31551 p 176 A89-17943 [AIM PAPER 88-38781 p 170 A89-18072 unsteady aerodynamic model p 146 A89-18919 KEEN, W. B. KRONZON, YIGAL LESHKEVICH, T. V. Ada in avionics - Beyond validation Time-iterative solutions of viscous supersonic nonle An automated method for forecasting the probability of [AIM PAPER 88-39071 p 199 A89-18087 flows p 150 A89-20184 clear air turbulence p 196 A89-18554 KEINER, WILLIAM L KRULIS, R. P. LEWICKI, DAVID 0. The role of testability in the integrated diagnostic Tiltrotor evolution leads to ASW revolution Effect of advanced component technology on helicopter process p 142 A89-18862 transmissions [AIM PAPER 88-38581 p I98 A89-18056 KRUPAR, MARTIN J. [NASA-TM-101431] p 193 N89-13794 KELLEHER. JOHN P. Laser velocimeter measurements of the flowfield LI. OlYlNG Design. analysis, and test of composite fuel tank pods generated by an advanced counterrotating propeller The general le 01 birds colliding against aeroplanes for the CH-46E heliter p163 A89-18885 [NASA-TM-l01437] p 153 N89-13409 and anticollision measures p 155 A89-19810 KEMMERLY, GUY T. KUHL, FREDERICK LIAW, PAUL Investigationof a movingmodel technique for measuring Terminal information for data link Winglets on low-aspect-ratio wings ground effect [AIAA PAPER 88-40001 p 159 A89-18181 p 149 A8920142 [ NASA-TM-40801 p 154 N89-14217 KUHLMAN, JOHN M. LIDEN, SAM KERELIUK, STAN Winglets on low-aspect-ratio wings Anival-time guidance in variable winds The impact of yaw axis control modes, flight directors [AIM PAPER 88-40251 p 159 A89-18176 p 149 A89-20142 and automatic control coupling on decelerating IFR LIEN, J. C. approaches for rotorcratl p 180 A89-18903 KUYAR, ANAND A methodology for the design of hierarchically testable KHOLODKOV, N. V. Teleport as a concentration point for domestic and and maintainable digital systems Performance of coated materials in high-enthalpy international traffic pl90 A89-20114 [AIAA PAPER 88-38591 p 170 A89-18057 oxidiing gas flows p 185 A89-18650 KURIEN, THOMAS LIFANOV, 1. K. KIHARA, MASAHIKO Combined numerical and symbolic processing for Calculation of the unsteady aerodynamic characteristics Reduced conservative singular value analysis for airborne surveillamx of bodies in the case of separated flow robustness D 197 A89-17489 [AIAA PAPER 88-39851 p 157 A89-18143 D 144 A89-18355

B-6 PERSONAL AUTHOR INDEX MOKHTARIAN, F.

LIGHT, JEFFREV S. MAEDA, H. MCGAHEE. KEVIN L Comparisons of predicted and measured rotor Hole tone generated from almost choked to highly A fault tolerant avionics multiprocessing system performance in hover using a new free wake analysis choked jets p 203 A89-19903 architecture supporting concurrent execution of Ada p 165 A89-18933 MAGNUSON. R. tasks LIM, JOON W. Development and qualification testing, teaming for the [AIM PAPER 88-39081 p 199 A89-18088 Aeroelastic optimization of a helicopter rotor V-22 multi-seWe aircraft system p 165 A89-18928 MCGOUGH, JOHN p 163 A89-18808 MAGUIRE, JOHN A. A method of measuring fault latency in a digital fliiht LINDSAY, HOWARD A. Hybrid architecture of fbld-tested diagnostic expert control system The development of the V-22 ospcey armored system p 198 A89-18034 [AIAA PAPER 88-38631 p 170 A89-18060 energy-absorbing crewseat assembly MAHANNA, JAMES MCINTVRE, MELVILLE D. p155 A89-18883 Integrateddiagnostic concepts for advanced technology An air data inertial reference system for fuhlre LIPNITSKII, IU. M. rotorcraft p 141 A89-18023 commercial airplanes Determination of the perturbations of the flow fields of [AIM PAPER 88-39181 p 171 A89-18095 MAIER, THOMAS H. supersonic wind tunnels from measured aerodynamic MCIVER, DOUGLAS Gynarnic characteristics of advanced bearingless rotors coefficients p 144 A89-18675 Faults with nonstationary obsewability are limiting at McDonnell Douglas Helicopter Company LISAGOR, W. BARRY avionics RAM p 164 A89-18899 Materials and structures lor hypersonic vehicles [AIM PAPER 88-38521 p 169 A89-18054 [NASA-TM-101501] p 186 N89-14264 MAIORANA, NICHOLAS 0. MCKERNAN, JOHN F. LLOYD. MARV J. Internal pressure measurements for a liquid payload at Vortex breakdown measurements on a 70 deg Corrosion and corrosion control of selected field low Reynolds numbers sweepback delta wing p 150 A89-20312 problems p 162 A89-18870 [ADA1974381 p 191 N89-13727 MCKILLIP, ROBERT M., JR. LOCKWOOD, ROY MANGUM, L SCOTT Three-dimensional interactii system identification of Rotor system evaluation. phase 1 A simulation-based faun injection experiment to evaluate helicopter rotorlbody dynamics p 165 A89-18938 [ADA1987941 p 168 N89-13425 self-test diagnostics for a fault-tolerant computer MCMILLAN, S. H. LOEWV, R. 0. [AIAA PAPER 88-38971 p 198 A89-18083 Optical fiber data transfer system The Center of Excellence in Rotary Technology at MANNING, JEROME E. [ NASA-CR-1817041 p 194 N89-14376 Rensselaer Polytechnic Institute Analytical prediction and fliiht test evaluation of Bell MCVEIGH, MICHAEL A. [ADA1989641 p 168 N89-13426 ACAP helicopter cabin noise p 164 A89-18911 Rotorlairframe interactions on tiltrotor aircraft LOFLAND, R. A. MANSKE, ROBERT A. p 181 A89-18854 NOTAR hybrid compositelmetal fan blade Ada executive for distributed avionics processing MECKLIN, RON p 163 A89-18893 [AIAA PAPER 88-40421 p200 A89-18166 Boeing Model 360 Advanced Technology Helicopter - LOMBARDI. GlOVANNl MARCUS, JAN-DAVID Design features and fliiht test update Characterization of boundary layer conditions in wind Integrated diagnostic concepts for advanced technology p 165 A89-18935 tunnel tests through IR thermography imaging rotorcraft p 141 A89-18023 MEHMED, ORAL p 147 A89-19167 MARSHALL, DONALD L Experimental investigation of propfan aeroelastic LONDON, JOHN R., 111 A fixed base data system for fliiht testing response in off-axis flow with mistuning The X-20 space plane ~ Past innovation. future vision p 201 A89-18937 [AIM PAPER 88-31531 p 175 A89-17941 [IAF PAPER 88-5981 p 204 A89-17867 Aeroelastic response of metallic and composite propfan MARTIN, RUTH M. LOSIER, PAUL W. models in yawed flow Tippathplane angle effects on rotor blade-vortex Rotor system evaluation, phase 1 [AIM PAPER 88-31541 p 175 A89-17942 [ AD-A1987941 p 168 N89-13425 interaction noise levels and directivity MEHTA, UNMEEL p 203 A89-18914 LOUIE, ALEXANDER Further comparisons of interactive boundary-layer and An experimental and analytical evaluationof the tapered MARTIN, STANLEY thin-layer Navier-Stokes procedures p 149 A89-20137 tension-torsion strap concept V-22 Osprey enabling technologies MERKLE. CHARLES L [NASA-TM-1010491 p 191 N89-13746 p 143 A89-20744 Time-iteratNe solutions of viscous supersonic nozzle LOVE, W. DWIGHT MASER, J. 0. flows p 150 A89-20184 TCAS Ill - Bringing operational compatibility to airborne Parametric studies of advanced tuhprops MERRILL, WALTER C. collision avoidance [ NASA-TM-1013891 p 195 N89-14465 Sensor failure detection for jet engines [AIAA PAPER 88-40041 pt59 ABS-18183 MA!BON, GERAW M. [NASA-TM-101396] p 177 N89-13432 LOVERING. P. Sharing the protection of aircraft electronic systems MIESS, JOSEPH Companson of the general dynamics ground clobber against the effects of high-level electromagnetic Evaluation of the improved OV-1 D anti-icing system algorithm with the GCAS and lam algorithms environments between badtiinal protection and system [ ADA1 984381 p 156 N89-14225 [AD-A1984791 p 157 N89-14226 architecture MIFSUD, PAUL V. LUDVIGSON. M. T. [AIAA PAPER 88-39171 p 187 A89-18094 New proposals for new directions - 1992 and the GATT The high speed bos technology development program MASTIN, CHARLES WAVNE approach to trade in air transport setvices [AIAA PAPER 88-40051 p 187 A89-18158 Overlapping grids for flow field calculations p 204 A89-18949 LUH. RAVMOND CHlNGCH.UNG p 195 N89-14918 MIKHAILOV, A. A. Suriace gno ganaraiion lor compiax iir&irnariJiuiiai MATHUR, GOPAL P. cz!cd!:!!O!7 O! tho !z$!ez*; zor*:&!2 ChP!?c!e!!~'irs geometries Analytical pediiction and Hiht test evaluation of Bell of bodies in the case of separated flow [ NASA-TM-1010461 p 191 N89-13747 ACAP helicopter cabin noise p 164 A89-18911 p 144 A89-18355 LUNN, K. MILLER, CHRISTOPHER J. MATSUMOTO, MASASHI Development and qualification testing. teaming for the Euler analysis of a swirl recovery vane design for use A study on hypersonic shock tunnel '4-22 multi-service aircraft system p 165 A89-18928 p 148 A89-20132 with an advanced singlerotation propfan LUO, FANG-CHEN [AIM PAPER 88-31521 p 144 A89-17940 One million pixel full color liquid crystal display for MATSUZAKA, MASAVOSHI MILLER, JAY avionics applications Experimental study on low-speed aerodynamic The X-planes: X-1 to X-31 (2nd revised and enlarged characteristics of non-axisymmetric slender bodies [AIAA PAPER 88-39671 p 173 A89-18134 edition) p 205 A89-20251 p 151 A89-20635 LVNESS, DAVID W. MIMPEN, A. M. Ada executive lor distributed avionics processing MAVHEW, ELLEN R. Sound attenuation and speech transmission quality of Fault detection and isolalbn lor reconfigurable flight [AIAA PAPER 88-40421 p200 A89-18166 fNe types Of headsets LVPACZEWSKI, P. A. control systems [12F-1987-23] p 193 N89-14373 [AIAA PAPER 88-38601 p 170 A89-18058 An advanced facility for cockpit studies MINER, R. V. [AIAA PAPER 88-39661 p 182 A89-18133 MAVLE, R. An investigation 01 environmentalinfluence on the creep LVU, MICHAEL R. The Center of Excellence in Rotary Technology at behavior of a low pressure plasma sprayed NiCoCrAlY On the effectiveness of multiversh software in dml Rensselaer Polytechnic Institute aW p186 N89-13648 [AD-A198964] p 168 N89-13426 avionics MINODA, MlTSUHlRO [AIM PAPER 88-39031 p 199 A89-18111 MAZZA, L T. Conceptual study of turbo-engines for horizontal takeoff Bell ACAP full-scale aircrall crash test and KRASH and landing space plane M correlation p 164 A89-18920 [IAF PAPER 88-2531 p 184 A89-17745 MCCOLLOUGH, JAMES M. MIRZA. NEAR A. Air-to-air combat helicopter development Fault tolerant avionics MA, ME1 p 165 A89-18929 Optimization of mistuned blade rotor lor controlling [AIAA PAPER 88-3901 I p 171 A89-18109 MCCOV, BRUCE M. MODI, V. J. flutter p 176 A89-19793 Reliability in fiber optic cable harness manufacturing Rotating air scoop as airfoil boundary-layer control MACINA, A. J. [AIAA PAPER 88-3931 I p 187 A89-18105 Developing error-free software p 201 A89-19679 p 150 A89-20149 MCCOV, JOHN MACKMULL, JACK V. Automated fatigue crack growth measurement MODROW, M. 8. Air combat tactics for the evaluation of rotorcraft [AD-A1986421 p 195 N89-14466 The hgh speed bus technology development program characteristics in the low air war of 2010 MCCROSKEV, W. J. [AIAA PAPER 88-40051 p 187 A89-18158 p 142 A89-18859 Navier-Stokes calculations of hovering rotor flowfields MOIR. 1. MADHAVAN, N. [AIAA PAPER 87-26291 p 149 A89-20133 Application of digital technology to aircraft utility Computationof axisymmetric supersonic jet using space Numerical simulation of tip vortices of wings in subsonic systems marching technique p 145 A89-18750 and transonic flows p 150 A89-20176 [AIM PAPER 8838721 p 180 A89-18114 MADSEN, PAUL MCCULLEV, DEBORAH J. MOKHTARIAN, F. Rewnfylurable fliiht control system simulation Automated wire preparation system Rotating air scoop as airfoil boundary-layer control p 181 A89-19558 p 189 A89-18895 p 150 A89-20149

8-7 MONTGOMERY, GERARD J. PERSONAL AUTHOR INDEX

MONTGOMERY, GERARD J. NEER, A. OUDA, NORIAKI The E-1B central integrated test system expert Processing composite finite element model with Triplex digital flight control system for the STOL research parameter system p 202 N89-14763 CADCOMP p 166 A89-19982 aircraft 'Aska' MOODY, JOHN CHRIS NEGODA, V. V. [AIM PAPER 88-38831 p 179 A89-18077 Air traffic control (ATC) and airlground digital Calculation of hypersonic flow past the windward side OKADA, TSUYOSHI

communications ~ Demonstration and evaluation of a low-aspect-ratio wing at high angles of attack Reduced conservative singular value analysis for [AIAA PAPER 88-39981 p 158 A89-18154 p 144 A89-18357 robustness p 197 A89-17489 MORAN, A. NEILSON. R. D. OLAUSSON, H.-L Processing composite finite element model with Dynamics of a rigid rotor mounted on discontinuously Turbine design using complex modes and non-linear elastic supports p 190 A89-19125 CADCOMP p 166 A89-19982 substructuring p 190 A89-19718 NELSON, R. C. MORGAN, J. M. ONO, AKlO Seven hole probe measurement of leading edge vortex A comparison between various side-arm controller A study on hypersonic shock tunnel flows p 146 A89-18939 configurations in a fly-by-wire helicopter p 148 A89-20132 p 180 A89-18905 Method of cold smoke generation for vortex core tagging p 191 A89-20324 OPP, RONALD E., II MORIKAWA, YASUSHIGE NELSON, ROBERT C. Stereoscopic 3-D displays for cockpits Method for simulating turbulence characteristics for wind Vortex breakdown measurements on a 70 deg [AIM PAPER 88-38871 p 170 A89-18080 environment in wind tunnel p 183 A89-19884 sweepback delta wing p 150 A8920312 OSDER, STEPHEN S. MORRIS, A. J. NEMO, JIM Digital Fly-By-Wire system for advanced AH-64 Progress towards a commercial aircraft design expert NOTAR hybrid cornpositelmetalfan blade helicopters system p 163 A89-18893 [AIM PAPER 88-39221 p 179 A89-18099 [DGLR PAPER 87-1201 p 167 A89-20237 NEUEAUER, ALBERT H., JR. OSTOWARI, C. MORRIS, PAT M. Airborne integrated monitoring system Measurements in the field of a spark excited Simulation evaluation of helicopter Terrain p 174 A89-18868 compressible axisymmetric jet p 203 A89-18948 FollowinglTerrainAvoidance concepts NEUHART, DAN H. OSTOWARI, CYRUS [AIAA PAPER 88-39241 p 180 A89-18101 A water tunnel study of Gurney flaps Drag reduction factor due to ground effect MORRISON, R. AL [NASA-TM-4071] p 151 N89-13395 p 151 A89-20325 Advanced avionics interconnection NEWMAN, J. C.. JR. OVENDEN. C. R. [AIAA PAPER 88-38561 p 170 A89-18055 Mechanics of fatigue crack closure AI applications to tactical decision aids MOSZER. SIDNEY p 186 A89-17401 [AIAA PAPER 8840271 p200 A89-18178 Design, analysis, and test of composite fuel tank pods NEWMAN, JOHN W. OVERESCH. E. for the CH46E helicopter p 163 A89-18885 Nondestructive testing of composite aircraft structures New application possibilities for balloon-borne case MULCARE, DENNIS with infrared and shearographic imaging technologies studies - MIKROBA (Microgravity by balloons) A method of measuring fault latency in a digital flight p 189 A89-18891 [DGLR PAPER 87-0691 p 184 A8920233 control system NG, T. T. [AIM PAPER 88-38631 p 170 A89-18060 Seven hole probe measurement of leading edge vortex MURAKAMI, HlROAKl flows p 146 A89-18939 P A study on aerodynamic heating in the interaction regions Method of cold smoke generation for vortex core tagging p 191 A89-20324 of shock waves and turbulent boundary layers induced PAISLEY, DAVID J. NIELElT, L T. by sharp fins p 148 A89-20131 Rotorlairframe interactions on tiltrotor aircraft MURAKAMI, SHUZO A guide to classical flutter p 188 A89-18801 NICHELSON, BRIAN J. p 161 A89-18854 Methodfor simulatingturbulence characteristics for wind Early jet engines and the transition from centrifugal to PAPAILIOU, K. D. environment in wind tunnel p 183 A89- 19884 axial compressors: A case study in technological change Computation of rotational transonic flows using a MURPHY, JOHN A. [ AD-A1987751 p 177 N89-13430 decomposition method p 150 A89-20179 Dolphin eats snow p 155 A89-18910 NIRMALAN, V. PAPENHAUSEN, DAVID W. MURTHY, DUREHA V. The effects of leading edge and downstream film cooling CEPS: An artificial intelligence approach to avionics Experimental investigation of propfan aeroelastic on turbine vane heat transfer maintenance p 201 N89-14749 response in off-axis flow with mistuning [NASA-CR-l82133] p 192 N89-13754 PATEL, V. C. [AIAA PAPER 88.31531 p 175 A89-17941 NISHIO. YASUNORI Interactive and large-domain solutions of highersrder Solution and sensitivity analysis of a complex Reduced conservative singular value analysis for viscous-flow equations p 148 A89-19905 transcendental eigenproblern with pairs of real robustness p 197 A89-17489 PATTEN, WILLIAM N. eigenvalues NIVERT, LAWRENCE J. The poststall nonlinear dynamics and control of an F-18: [NASA-CR-182241] p 193 N89-13819 Developmentof the TrafficAlert and Collision Avoidance A preliminary investigation p 169 N89-14922 MYERS, THOMAS T. System Ill (TCAS Ill) PAlTERSON, WILLIAM Autonomous RPRV navigation, guidance and control [AIAA PAPER 88-40021 p 159 A89-18182 Control of a human-powered helicopter in hover [NASA-CR-179425] p 161 N89-14228 NIYOGI. P. LNASA-TM-l01029] p 182 N89-13438 Recent developments in transonic flow computation PAULSON, JOHN W., JR. p 145 A89-18749 Investigationof a moving-modeltechnique for measuring N NOONAN, KEVIN W. ground effect Two-dimensional aerodynamic characteristics of the [ NASA-TM-40801 p 154 N89-14217 NAGAMATSU, H. OLSlTAAT airfoil PAYNE, F. M. The Center of Excellence in Rotary Technology at [NASA-TM-894351 p 154 N89-14216 Seven hole probe measurement of leading edge vortex Rensselaer Polytechnic Institute High lift, low pitching moment airfoils flows p 146 A89-18939 [ADA1989641 p 168 N89-13426 [NASA-CASE-LAR-13215-1] p 154 N89-14224 PAYNE, FRANCIS M. NAGIE, HASSAN NOREY, W. P. Vortex breakdown measurements on a 70 deg Equipment to upgrade the facilities of the IIT (Illinois Isolated testing of highly maneuverable inlet con cepts sweepback delta wing p 150 A8920312 Institute of Technology) Fluid Dynamics Research [ NASA-CR-1795441 p 178 N89-13437 PELLUM, W. L Center NOUSE, HlROYUKl Holometrics . An information transformation [AD-A1980841 p 1@4 N89-14242 Conceptual study of turbo-engines for horizontal takeoff methodology p200 A89-18922 NAGIB, HASSAN M. and landing space plane PENDERGRAFT, ODlS C., JR. Management and control of separation by unsteady and [IAF PAPER 88-2531 p 184 A89-17745 A water tunnel study of Gurney flaps Vortical flows [NASA-TM-4071] p 151 N89-13395 [ADA1989021 p 191 N89-13736 PERRY, KAREN Management and control of unsteady and turbulent 0 Testing and correlation on an advanced technology, flows bearingless rotor p 182 A89-18SOO [ADA198091 ] p 192 N89-13751 ODONNELL, K. A. PERSOON, A. J. NAKAMURA, YOSHlKl Dynamic perspective displays and the control of tilt-rotor Unsteady low-speed windtunnel test of a straked delta Avionics failure propagation analysis tool aircraft in simulated fliht p 174 A89-18867 wing, oscillating in pitch. Part 4: Plots of time histories of [AIM PAPER 88-38881 p 198 A89-18065 pressures and overall loads NAKAMURA, YOSHIYA OEAYASHI, KAZUHIRO A note on the aircraft minimum-time turns [ADA1M2] p 152 N89-13402 Fan acoustic modes measuring system p 182 A89-20638 Unsteady low-speed windtunnel test of a straked delta p183 A89-19950 wing, oscillating in pitch. Part 5: Power spectral density NARAYANAN, 0. V. OEERMEIER, F. An analytical description of unsteady transonic plots of the overall loads for harmonic oscillation and the Aeroelastic response of metallic and composite propfan response of overall loads to (1GoS) inputs Laval-nozzle flow p 147 A8919664 models in yawed flow [ AD-A1986831 p 152 N89-13403 OERTEL H. [AIAA PAPER 88-31541 p 175 A89-17942 Unsteady low-speed windtunnel test of a straked delta WARRAMORE, J. C. Numerical methods for hypersonic flows wing, oscillating in pitch. Part 6: Presentation of the An evaluation of a Navier-Stokes code for calculations [DGLR PAPER 87-0841 P 150 A89-20235 visualization program of retreating blade stall on a helicopter rotor OETTING, ANNE M. [ADA1986841 p 152 N89-13404 p 146 A89-18916 Determination of control laws for B single pilot, attack PETERS, DAVID A. NATAUPSKY, MARK heliter P 180 A89-18904 Dynamic inflow for practical applications Stereo 3-D and non-stereo presentations of a OHMIYA, HlMAKl p 147 A89-19625 computer-generated pictorial primary fliiht display with The T-2 control configured vehicle development, PETERS, JAMES pathway augmentation integration and fliht test Optimal design of an advanced composite rotating [AIAA PAPER 88-39651 p 173 A89-18132 [AIAA PAPER 88-38821 P 179 A89-18076 flexbeam p 189 A89-18884 8-8 PERSONAL AUTHOR INDEX SCHWINDT, CHRISTIAN J.

PETERSEN. KEVIN L QUACKENBUSH, TODD R. ROGERS, RICHARD A. Real-time fliht test analyss and display techniques for Free wake calculation of rotor flow fields for interactional Ada executive for distributed avionics processing the X-29A aircraft aerodynamics p 145 A89-18853 [AIM PAPER 88-40421 p 200 A89-18166 [NASA-TM-1016921 p 168 N89-13424 Comparisons of predicted and measured rotor ROME, H. JAMES PETERSON, A. A. performance in hover using a new free wake analysis Low-orbit navigation concepts p 184 A89-19870 Analytical determination and experimental comparison p 165 A89-18933 ROOKE, D. P. of performance degradation on a helicopter main rotor QUARTARARO. LOUIS R. Stress intensity factors for periodic radii1 cracks in a due to ice accretion p 155 A89-18909 Analytical prediction and flight test evaluation of Bell rotating disc p 187 A89-17448 PETERSON, A. PADGElT ACAP helicopter cabin noise p 164 A89-18911 ROSENBERG, KEITH W. Avionics testing in the military bare-base environment auiwo, P. FRANK Energy management for integrated flight and propulsion p 141 A89-16011 Thrust-reverser flow investigation on a twin-engine control systems PI, w. s. transport [AIAA PAPER 88-38731 p 178 A89-18068 Dynamic tirefsoil contact surface interaction model for [ NASA-TP-28561 p 153 N89-14213 ROTENBERGER, K. M. aircraft ground operations p 155 A89-20320 Application of damage tolerance methodology to PIOTROWSKI, JOSEPH helicopter dynamic components using the example of a Evaluation of the improved OV-1D anti-icing system main rotor pitch link for the AH-1S helicopter [AD-A198438] p 156 N89-14225 R p 164 A89-18921 PLAETSCHKE. E. ROTMISTROV, N. IU. Identification of unstable flight-mechanical systems RACHOVITSKY, E. Variable-cycle engines for boostingcruisingvehicles Reconfigurable Hiht control: An opportunity for using an output error method p 181 A89-19661 [ IAF PAPER 88-2491 p 175 A89-17742 PLAlT, P. A. integrated diagnostics p 182 N89-14744 ROWE, WILLIAM S. Mode S data link applications research in the UK RAFTERY, MICHAEL Coupling linearized far-field boundary conditions with [AIM PAPER 88-39961 p 158 A89-18153 Design and validation of the IFTAS fault-tolerant clock nonlinear near-field solutions in transonic flow PLENCNER, ROBERT Y. [AIAA PAPER 88-38991 p 170 A89-18085 [AD-A1987211 p 153 N89-13405 Plotting component maps in the NavylNASA Engine RAYASWAYY, Y. A. RUBIN, S. 0. Program (NNEP): A method and its usage Computationof axisymmetric supersonic jet using space Multigrid acceleration of a relaxation procedure for the [ NASA-TM-101433) p 178 N89-14239 marching technique p 145 A89-18750 reduced Navier-Stokes equations p 148 A89-19904 PODBOY, GARY 0. RAYASWAYY, V. 0. RUCKER, RICHARD A. Laser velocimeter measurements of the flowfield Constitutive modeling for isotropic materials The future of aeromobile digital communications generated by an advanced counterrotating propeller [NASA-CR-l74805] p 177 N89-13436 [AIAA PAPER 88-4001I p 158 A89-18156 [ NASA-TM-1014371 p 153 N89-13409 RAUSCH, SCOlT POE, YlNN P. Commercial avionics applications of flat panel displays Atmospheric photochemical modeling of turbine engine [AlAA PAPER 88-39621 p 173 A89-18129 S fuels and exhausts. Computer model development volume RAY, R. BRUCE SALAS, M. D. 1 Cockpit management for regional airlines and business Navisr-Stokes calculations using Cartesian griis. I . [ AD-A! 98690: p 196 N89-13832 aircraft as applied in the Beech Starship Laminar flows p150 A89-20180 Atmospheric photochemical modeling of turbine engine [AIM PAPER 88-39571 p 173 A89-18126 fuels and exhausts. Computer model development, volume SANCLEMENTE, PAUL REAGAN, JOHN E. Genesis of a flexible turning center 2 AH-64A Contractor Logistic Support The contractors' [ADA1986911 p 196 N89-13833 - p 189 A89-18894 perspective p 142 A89-18869 POGORELOV, 0.1. SANFORD, FIDELL Mathematical modeling of laminar and turbulent REDDINGUIS, NICHOUAS Detailed design specification for a prototypeAssessment Detaileddesign specification for a prototype Assessment supersonic flow pas1 convex-comve bodies System for Aircraft Noise (ASAN) System for Aircraft Noise (ASAN) p 144 A89-18671 [AD-A197936] p 204 N89-14818 POHL, W.9. [ADA1979361 p 204 N89-14818 SANGHA, KARAN B. Development of ram propulsion for flight vehicles REDEKER, A. Bearinglessrotors and higher harmonic control modeling [DGLR PAPER 87-1011 p 176 A89-20240 Concept and flight testing of a modem longitudinal using RACAP p 162 A89-18876 POLCZYNSKI, C. E. motin regulator using an inversa model SANKAR, L N. Fiber optic applications to the high altitude [DGLR PAPER 87-1211 p 181 A89-20238 Improvements to transonic flowfield calculations reconnaissance vehicle REESE, IRVING R. p 146 A89-18915 [AIAA PAPER 88-39301 p 187 ASS-18104 Avionics failure propagation analysis tool An evaluation of a Navier-Stokes code for calculations POLLACK, DALE [AIAA PAPER 88-38681 p 198 A89-18065 of retreating blade stall on a helicopter rotor A simplified aircraft collision avoidsnce system REHBACH, C. p 146 A89-18916 [AIAA PAPER 88-39611 p 173 A89-18128 campllatlon of the pressure in an incompressible SANKEWITSCH. V. PORTER, S. rotational How of inviscid fluid p 143 A89-17150 Six degree of freedom crew isolation design, bench test and flight test p 163 A89-18896 Development and qualificationtesting, teaming for the REICHEL, REINHARD W. SARIC, WILLIAM V-22 multi-service aircraft system p 165 A89-18928 Dgital control of a quadruplex direct drive actuator S. klaginn of h~!?.aeyy.o!ds-"u-k !!e!-p!=!= =x~rkzx!s POTAPEZUK: MARK 0. ,.,..n.-r- ..I^^*.. I~IM oo-aaa I 1 p ii2 ir6D-i6ii2 rnrcn in the iTF Predictions of airfoil aerodynamic performance REISENTHEL, PATRICK H. [NASA-CR-184627] p 153 N89-13411 degradation due to icing Management and control of separation by unsteady and SAUTER. DAVID P. [NASA-TM-101434] p 153 N89-13412 vortical flows Three dimensional hazard zones p 195 A89-18259 POTIS, HUGH ADRIAN [AD-A198902] p 191 N89-13736 SAWDYE, S. The quality of fibre reinforced thermoplastics Management and control of unsteady and turbulent T55-L-714 engine development and qualification: Tip mouldings p 196 N89-13839 flows clearance analysis POWER, 0. D. [AD-A198091] p 192 N89-13751 [ADA1988491 p 177 N89-13431 The effects of inlet turbulence and rotorlstator REISING, JOHN Y. SCANLON, CHARLES H. interactions on the aerodynamics and heat transfer of a Stereoscopic 3-D displays for cockpits A flight test design for studying airborne applications large-scale rotating turbine model, volume 1 [AIAA PAPER 88-38871 p 170 A89-18080 of air to ground duplex data link communications [ NASA-CR-40791 p 192 N89-13756 REZNICK. STEVEN 0. p 195 N89-14924 Transonic Navier-Stokes solutions for a fighter-like PRASAD, CHUNCHU BHAVANI SCHAENZER, 0. The effects of nonlinear damping on the large deflection confguration p 149 A89-20134 Fliht guidance technology RHODE. D. L response of smtures subjected to random excitation [DGLR PAPER 87-1191 p 160 A89-20239 The measurement and prediction of rotordynamicforces p 193 N89-13796 SCHEPER, CHARLOTTE 0. for labyrinth seals PRICHARD, D. S. A simulation-basedfault injection experiment to evaluate [ADA1971851 p 192 N89-13784 Improvements to transonic flow(ield calculations self-test diagnostics for a fault-tolerant computer RICHARDSON, CECIL p 146 A89-18915 [AIM PAPER 88-38971 p 198 A89-18083 PROCTOR, FRED H. Software development for large scale avionic integration programs p 200 A89-18864 SCHILLINGS, J. J. Numerical simulation of the 2 August 1985 DFW Developments in dynamics methodology at Bell RICK, H. miaoburst with the three-dimensional Terminal Area Heliter Textron p 162 A89-18875 Design and integration of air-breathing propulsion Simulation System p175 A8919186 SCHLEE, F. H. systems of space transports and hypersonic aircraft Numerical simulations of an isolated microburst. I Terminal navigation for the Combat Talon aircraft - [DGLR PAPER 87-1031 p 176 A89-20241 II [AIM PAPER 88-40211 p 159 A89-18173 Dynamics and structure p 196 A89-20265 RIZK, YAGDI H. SCHLINKER, ROBERT PUGNALE. .IO" User's manual for an aerodynamic optimizationscheeme Experimental assessment of a turbulence ingestion hral Centrifugal compressors ~ The helicopter solution that updates flow variables and design parameters noise theory p 203 A89-18912 to sand and ice ingestion p 176 A89-18908 simultaneously PYNE, C. R. [ NASA-CR-1821801 p 151 N89-13399 SCHOEN, ALLEN H. The use of sweepfrequency excitation for unsteady ROBINETT, RUSH DALETH. 111 V-22 Osprey enabling technologies pressure measurement p147 A89-18940 A unifii approach to vehicle design. control. and flight p 143 A89-20744 path optimization p 168 N89-14231 SCHULTEN. J. B. H. Y. ROCK, STEPHEN Y. Frequency-domain method for the computation of Q Effect of model uncertainty on failure detection - The propeller acoustics p 203 A89-19902 threshold selector p 197 A89-17965 SCHWINDT, CHRISTIAN J. aiu, XUEJUN RODRIGUEZ LUIS R. A comparison of acoustic predictions with model rotor Measurements of the buffet boundary of wings in Environmentally induced cracking in aluminum test data from the NASA 14 x 22 11 wind tunnel transonic flow with hot-film method p 148 A89-19805 p 185 A8918925 D 203 A89-18913

B-9 SCOTT, BARRY C. PERSONAL AUTHOR INDEX

SCOlT, BARRY C. SINET, JEROME STOCKFLETH, H. Recent studies of MLS appliCatiOn The unused strategic tool - The airship New application possibilities for balloon-borne case [AIM PAPER 88-39161 p 157 A89-18093 p 161 A89-18752 studies - MIKROBA (Microgravity by balloons) SCOTT, WILLIAM B. SLAY, F. M. [DGLR PAPER 87-0691 P 184 A89-20233 New design, production tools will play key role in 8-2 The nature of the aircraft component failure process: STRANGMAN, T. E. cost p 161 A89-18350 A working note Development of thermomechanical life prediction SEBRINQ, DAVID L [AD-A197979] p 169 N89-14234 models for thermal barrier coatings p 186 N89-13643 An air data inertial reference system for future SMITH, ARLYNN W. STRAWN, ROGER C. commercial airplanes Chemical vapor deposition of oxidation resistant HfB2 An entropy and viscosity corrected potential method for Sicomposite coatings p 185 A89-19481 [AIAA PAPER 88-39181 p 171 A89-18095 + rotor performance prediction P 145 A89-18857 SMITH, RANDALL F. SEGAL, H. M. STRONCEK, CHRISTOPHER J. Airframe and propulsion assessment of alternative light A microcomputerpollution model for civilian airports and Air-to-air combat helicopter development air force bases, model description heliter technologies (LHX) p 161 A89-18863 P 165 A89-18929 [ AD-A1990031 p 197 N89-14616 SMOLIN, A. G. SUH, YOUNG B. SEND, WOLFGANG Performance of coated materials in high-enthalpy Drag reduction factor due to ground effect Downstream vorticity measurements from ultrasonic oxidizing gas flows p 185 A89-18650 pulses p 151 A89-20313 SNODGRASS, THOMAS D. p 151 A89-20325 SHANLEY, JOHN P. Avionics fault tree analysis and artificial intelliince for SULTANIAN, B. K. An examination of some rotor aerodynamic models using future aircraft maintenance p 202 N89-14760 The effects of leading edge and downstream film cooling the RSRAIX-wing model test data p 146 A89-18858 SNYDER, CHRISTOPHER A. on turbine vane heat transfer SHARPE. D. L Advanced core technology: Key to subsonic propulsion [NASA-CR-182133] p 192 N89-13754 Structural dynamics of a helicopter rotor blade system benefits SUNDAY, TERRY L p 162 A89-18878 [NASA-TM-101 4201 p 178 N89-14237 The X-20 space plane - Past innovation, future vision SHAW, ROBERT J. SOBIECZKY, H. [IAF PAPER 88-5981 p 204 A89-17867 Predictions of airfoil aerodynamic performance Improving the half-model technology in the Goettingen SUNDBERG, W. D. degradation due to icing transonic wind tunnel New solution method for steady-state canopy structural [ NASA-TM-1014341 p 153 N89-13412 [DGLR PAPER 874831 p 183 A89-20234 loads p 155 A89-20321 SHCHIPIN, S. K. SOENCKSEN, KEITH P. SVENSSON, C. INGVAR Self-similar problem of the separated flow of an ideal Internal pressure measurements for a liquid payload at A structured approach to system design fluid past an expanding plate p 144 A89-18669 low Reynolds numbers [AIAA PAPER 88-38671 p 198 A89-18064 SHEN. DAKUAN [AD-A197438] p 191 N89-13727 SWENSON, HERRY N. Effect of blade mistuning and bladedisk on cascade SOLAN, M. Simulation evaluation of helicopter Terrain flutter boundaries p 176 A89-19803 X-29 validation methodology for simulation and flight Following/Terrain Avoidance concepts SHEPHARD. M. control system p 181 A89-19557 [AIAA PAPER 88-39241 p 180 A89-18101 SONG, TAO The Center of Excellence in Rotary Technology at SYMOSEK, PETER Rensselaer Polytechnic Institute Optimization of mistuned blade rotor for controlling Strapdown issues for airborne EO sensors flutter p 176 A89-19793 [AD-A198964] p 168 N89-13426 [AIM PAPER 88-39271 p 171 A89-18102 SHERBROOKE, CRAIG C. SONG, Z. The nature of the aircraft component failure process: Dwell time effects on the fatigue behaviour of titanturn A working note alloys p 185 A89-17619 T [AD-A1979791 p 169 N89-14234 SONG, ZHAOHONG SHIBATA, KATSUHEI Optimization of mistuned blade rotor for controlling TADGHIGHI, HORMOZ The T-2 control configured vehicle development, flutter p 176 A89-19793 An analytical model for the prediction of MR/TR integration and flight test SORENSEN, JEFFREY L interaction noise p 165 A89-18931 [AIM PAPER 88-38821 p 179 A89-18076 Dynamic characteristics of advanced bearingless rotors TAKAHASHI, M. D. SHIDELER. JOHN L at McDonnell Douglas Helicopter Company Design of a simple active controller to suppress Buckling characteristics of hypersonic aircraft wing p 164 A89-18899 heliropter air resonance p 162 A89-18877 tubular panels SPENCE, W. W. TAMAKI, TEllCHl [NASA-TM-87756] p 193 N89-13816 Application of damage tolerance methodology to Conceptual study of turbo-engines for horizontal takeoff SHIH, HUBERT helicopter dynamic components using the example of a and landing space plane An SAE high speed ring bus overview main rotor pitch link for the AH-1S helicopter [IAF PAPER 88-2531 p 184 A89-17745 [AIM PAPER 88-4Gt381 p 187 A89-18159 p 164 A89-18921 TAN, ANZHONG SHIKOV, V. K. SPIVEY, DICK A study on aerodynamic heating in the interaction regions Convective heat transfer in a boundary layer behind a Tiltrotor evolution leads to ASW revolution of shock waves and turbulent boundary layers induced shock wave propagating along a flat plate with a sharp p 142 A89-18862 by sharp fins p 148 A89-20131 leading edge - A calculation method and a comparison SPRIGGS, T. JOHN TANG, DEMAN with experimental data p 144 A89-18546 An ice detection system for helicopters Nonlinear stability analysis for helicopter ground SHIMIZU, YUKIO [AIAA PAPER 88-39491 p 172 A89-18120 resonance p 166 A89-19790 Triplex digital flight control system for the STOL research TANNER, GRAHAM F. aircraft 'Aska' SQUIRE, L C. Interactions between turbulent wakes and boundary Functional augmentation of digital engine controllers to [AIAA PAPER 88-38831 p 179 A89-18077 layerr p 150 A89-20182 implement an integrated testability concept SHORTESS. DEBORAH L [AIAA PAPER 88-39531 p 176 A89-18124 SRINIVASAN, A. V. Lightning simulation test technique evaluation TARKENTON, G. M. Structural dynamics of a helicopter rotor blade system [WTIFAA/CT-87/38] p 156 N89-13415 Users' manual forthe Langley high speed propeller noise p 162 A89-18878 SHU, H. T. prediction program (DFP-ATP) Structural dynamics of a helicopter rotor blade system SRINIVASAN. G. R. [NASA-CR-4208] p 204 N89-14820 p 162 A89-18878 Navier-Stokes calculations of hovering rotor flowfields TARNOWSKI, E. SHULMAN. HY [AIAA PAPER 87-26291 p 149 A89-20133 Architecture of an optimal navigation system integrating Faults with nonstationary observabili are limiting Nu-l simulation of tip vortices of wings in subsonic GPS p 160 A89-18751 avionics RBM and transonic flows p150 A89-20176 TAYLOR, RODNEY S. [AIAA PAPER 88-38521 p 169 A89-18054 STALLINGS, ROBERT L, JR. The Pointer - A revolutionary idea to improve RPV SHULTZ, ROGER K. Passive venting technique for shallow cavities capabilities p 163 A89-18881 A fault tolerant avionics multiprocessing system [NASACASE-lAR-14031-1] p 168 N89-14232 Civil tiltrotor aircraft - A comparison of five candidate architecture supporting concurrent execution of Ada Passive venting technique for shallow cavities designs p 163 A89-18882 tasks [NASA-CASE-iAR-13875-1] p 169 N89-14233 TELFORD, JAMES W. [AIAA PAPER 88.39081 p 199 A89-18088 STANZIONE, KAYDON A. An example of the behavior of an aircraft with SIQAL, ASHER Airframe and propulsion assessment of alternative liht accumulated ice - Latent instability p 181 A89-20170 Aerodynamic characteristics of rectangular helicopter technologies (LHX) p 161 A89-18863 TELIONIS, D. P. cross-sectional bodies at M = 0.85 p 151 A89-20317 Vortiil wakes over a prolate spheroid SILADIC, MAT0 F. STEIN, GUNTER Design of feedback control systems for unstable plants p 150 A89-20181 Numerical grid generation and potential airfoil analysis TENEWRIO, JAIME 0. and dwgn with saturating actuators [NASA-CR-183392] p 194 N89-14377 GaAs MMlCs satisfy EW requirements [ADA1979721 p 154 N89-14219 p 188 A89-18757 STEIN, LEO J. SILVERTHORN, LOUIS J. TENNEY, DARREL R. Vehicle management system architectural Dynamic characteristks of advanced bearingless rotors Materials and structures for hypersonic vehicles considerations at McDonnell Douglas Helicopter Company [NASA-TM-101501I p 186 N89-14264 [AIAA PAPER 88-38751 p 174 A89-18189 p 164 A89-18899 TERENT'EVA, V. S. SIMMONS, JON STERN, F. Performance of coated materials in high-enthalpy Advanced avionics interconnection Interactive and largedomain solutions of higher-order oxidizing gas flows p 185 A89-18650 [AIAA PAPER 58-38561 p 170 A89-18055 viscous-flow equations p 148 A89-19905 THIEL, ERNSTFRIED SIMONICH, JOHN STILES, PETER The Oetztal wind tunnel as basic idea and incentive Experimental assessment of a turbulence ingestion Application of AI technology to time-critical functions for planning the USAF research center AEDC Tullahoma noise theory p 203 A89-18912 [AIM PAPER 88-40301 p 174 A89-18190 p 183 A89-20245 SIYS. D. STINEBRING. D. R. THORNTON. EARL A. Ground simulation for airborne equipment Expenmental investigabn of a Jetimpinging on a ground Coupled flow. thermal, and structural analysis of p 188 A89-18741 plane in crossflow P 149 A89-20141 aerodynamically heated panels p 181 A89-20322 E10 PERSONAL AUTHOR INDEX WOITHE. K.

TILLOTSON, DANIEL H. VANSTONE, R. H. WAlTS, MICHAEL E. Results of the in-mice evaluation of the traffic alert Constitutive modeling for isotropic materials Two-dimensional aerodynamic characteristics of the and collision avoidance system industry prototype [ NASA-CR-1748051 p 177 N89-13436 OLSlTAAT airfoil [AIM PAPER 88-39151 p 171 A89-18092 VEAUX, JACQUES [ NASA-TM-894351 p 154 N89-14216 TODA, N. F. New design procedures applied to landing gear WAY, JOHN L Terminal navigation for the Combat Talon II aircraft development p 167 A89-20138 Management and control of separation by unsteady and [AIM PAPER 8840211 p 159 A89-18173 VEERARAGHAVAN, MAUTHI vortical flows TORBY, B. J. An approach to soiving large reliability models [AD-A198902] p 191 N89-13736 Turbine design using complex modes and [AIAA PAPER 88-39051 p 199 A89-18086 Equipment to upgrade the facilities. of the IIT (Illinois substructuring p 190 A89-19718 VEERBEEK, H. W. Institute of Technology) Fluid Dynamics Research TORIC F. CHRIS COCOMAT, a CAE system for composite structures Center High time service evaluation of thermal bamer coatings design p 166 A89-19981 [ AD-A1980841 p 184 N89-14242 on the Rolls-Royce RB211 engine p 186 N89-13660 WEFALD, KNUT VERDON, J. M. TOTAH, JOSEPH J. Fault tolerant inetiil navigation system The effects of inlet turbulence and rotorlstator Control of a human-powered helicopter in hover [AIM PAPER 88-40241 p 159 A89-18175 [NASA-TM-101 0291 p 182 N89-13438 interactions on the aerodynamics and heat transler of a WEI, FAJIE large-scale rotating turbine model. volume 1 TOWNSEND, DENNIS P. A method of computer aided design of structural type [NASA-CR-40791 p 192 N89-13756 Effect of advanced component technology on helicopter - An application of expert system and luny sets theory transmissions VERMELAND, R. p 201 A89-19811 [NASA-TM-101431] p 193 N89-13794 An evaluation of a Navkr-Stokes code for calculations WEILAND, C. TREASTER, A. L of retreating blade stall on a helicopter rotor Numerical methods for hypersonic flows Experimentalinvestigation of a jet impingingon a ground p 146 A89-18916 [DGLR PAPER 87-0841 p 150 A89-20235 plane in crossflow p 149 A89-20141 VETSCH, LEE E. WELLER, WILLIAM H. TRIKHA, ARUN K. Design of a certifiable primary on-board aircraft weight Experimental verification of helicopter blade designs Hypervelocity technology escape system concepts and balance system optimized for minimum wbratiwn p 162 A89-18874 program p 184 A89-17929 [AIAA PAPER 88-39191 p 171 A89-18096 WELSH, B. L TRIPP, DAVID E. VIAN, J. L The use of sweep-frequency excitation for unsteady A review of failure models for unidirectional ceramic Multiple sample polygonal correlation algorithm for the pressure measurement p 147 A89-18940 matrix composites under monotonic loads determination of ground emitter location WELSH, WILLIAM A. [NASA-TM-101421] p 195 N89-14470 [AIM PAPER 88-39871 p 158 A89-18145 Dynamic modeling of a helicopter lubrication system TRIVEDI. KISHOR S. VISSER, K. D. p 189 A89-18897 An approach to solving large reliability models Method of cold smoke generation for vortex core WENZEL, ROBERT J. [AIAA PAPER 88-39051 p 199 A89-18086 tagging p 191 A89-20324 Omega Navigation System - A status report TSKHOVREBOV. M. M. VOYCE, BART p 160 A89-19867 Variablscycle engines for boosting-cruisingvehicles Universal Ada Test LanSuage (UATL: :a support WHITE, JIM [IAF PAPER 88-2491 p 175 A89-17742 real-time software/system integration and Testing and correlation on an advanced technology, TSUEI. HSIN-HUA factotylmaintenancefault isolation p 197 A89-18009 bearingless rotor p 182 A89-18900 Study the aerodynamics characteristics of airfoil on WRNWY-JONES, P. WHITFILL, WILLIAM A., 111 vector processors Disorientation accidents and incidents in US. Army The development and application of software quality indicators [IAF PAPER ST-88-09] p 143 A89-17874 helicopters. 1 January 1980.30 April 1987 TUCKER, 0. E. [AD-A198720] p 156 N89-13417 [AIM PAPER 88-39461 p201 A89-19860 Development and flight test of a precision autohover WIESNER, ROBERT capability lor tactical rotorcraft p 165 A89-18934 Boeing Model 360 Advanced Technology Helicopter - TUNCER, I. n. Design leatures and flight test update W p 165 A89-18935 A unified theoretical-computationalapproach for viscous WIGHTMAN, J. P. unsteady rotor aerodynamics p 146 A89-18917 WAGNER, B. A fundamental approach to the sticking of insect TUSCHE, S. Numerical methods for hypersonic flows residues to aircraft wings Improving the half-model technology in the Goettingen [ DGLR PAPER 87-0841 p 150 A89-20235 [NASA-CR-l83041I p 156 N89-13414 transonic wind tunnel WALLER, D. WILCOX, FLOYD J.. JR. [DGLR PAPER 87-0831 p 183 A89-20234 X-29 validation methodology for simulation and flight Passive venting technique for shallow cavities TWAIT, DOUGLAS J. control system p 181 A89-19557 [NASA-CASE-LAR-14031-1I p 168 N89-14232 Chemical vapor deposition of oxidation resistant HfB2 WALLER. MARVIN C. Passive venting technique lor shallow cavities + Sic composite coatings p 185 A89-19481 Asimulationstudyofdatalinkmessageexchange.Flight [ NASA-CASE-LAR-13875-11 p 169 N89-14233 TWEED, J. deck perspective WILKERSON. JOSEPH 8.

Stress intensity factors for periodic radial cracks in a [AIAA PAPER 88-39931 p 158 A89-18151 Civil tiltrotor aircraft ~ A comparison 01 fie candidate rotating disc p 187 A89-17448 WALSH, JOSEPH A. designs p 163 A89-18882 TYRRELL, AMY Development of the Traffic Alert and Collision Avoidance WILLIAMS, DAVID A case study - F-16 Ada Digital Flight Control System System Ill (TCAS Ill) Equipment to upgrade the facilities 01 the IIT (Illinois [AIAA PAPER 88-3911 ] p 171 A89-18090 [AIM PAPER 88-40021 p 159 A89-18182 Institute of Technology) Fluid Dynamics Research WALTER, CHRIS J. Center MAFT - An architecture for reliable fly-by-wire flight [ AD-A1980841 p 184 N89-14242 U control WILLIAMS, DAVID R. [AlAA PAPER 88-39021 p 180 A89-18110 Management and control of separation by unsteady and UCHIDA. TADAO WALTERS, M. M. vortical flows Triplex digital flight control system for the STOL research Experimental inveshgation of a jet impinging on a ground [ AD-A1989021 p 191 N89-13736 aircraft 'Aska' plane in crossflow p 149 A89-20141 WILLIAMS, MARC H. Aeroelastic response 01 metallic and composite propfan [AIM PAPER 88-38831 p 179 A89-18077 WANG, QIAOSEN models in yawed flow UMEDA, Y. Measurements of the buffet boundary of wings in [AIAA PAPER 88-31541 p 175 A89-17942 Hole tone generated from almost choked to highly transonic flow with hot-film method p 148 A89-19805 choked lets p 203 A89-19903 WILLIS. JAMES L WANG, WILLIAM Y. A fixed base data system for flight testing UNFRIED, FREDERICK Evaluation of Simulator motion characteristics based on p 201 A89-18937 Reconfgurableflight control system simulation AGARD-AR-144 procedures p 183 A89-19565 WINCKLER, S. p 181 A89-19558 WANG, YOUFU The Center of Excellence in Rotary Technology at UNO, MONTE Selection of the optimal lighter-than-air gas for airship Rensselaer Polytechnic Institute Aerospace simulation 111: Proceadirgs ui the SCS and a scheme of double-layer structural design [ AD-A1989641 p 168 N89-13426 Multioonfefence. San Dmgo. CA, Feb. 3-5. 1988 p 166 A89-19809 WINE, JAN W. p 142 A89-19551 WARD, HUGH W. GaAs 32-bit single board computer Air-tc-air combat helicopter development [AIM PAPER 8840121 p 200 A89-18162 p 165 A89-18929 WINER, ARTHUR M. V WARIISHI, YOSHINOR1 Atmosphenc photochemical modeling of turbine engine A note on the optimal hypersonic flight path fuels and exhausts. Computer model development. volume VAN MRLASKE. DENNIS p 167 A89-20637 1 Standardized advanced infrared sensa ~ A program WARK, CANDACE E. [ AD-A1986901 p 196 N89-13832 status p 175 A89-18932 Management and control 01 unsteady and turbulent Atmospheric photochemica: modeling of turbine engine VAN HORN, JAMES flows fuels and exhausts. Computer model development. volume NOTAR .An alternative to the helicopter tail rotor [AD-A198091] p 192 N89-13751 2 p 166 A89-20020 WATANABE. AKIRA [AD-A198691] p 196 N89-13833 VANMRWERF, KEVIN Triplex digital flight control system lor the STOL research WITT, N. Fault tolerant inertial navigation system aircraft 'Aska' Mode S data link applications research in the UK [AIAA PAPER 8840241 p 159 A89-18175 [AIAA PAPER 88-38831 p 179 A89-18077 [AlAA PAPER 88-39961 p 158 A89-18153 VANGESSEL. J. C. A. WATANABE, TOSHlNORl WOITHE, K. Precision approach radars Twenlhe and Volkel Experimental study on unsteady aerodynamic Introduction of new technologies in the structural area (Netherlands). Multipath prcpagatwn problems characteristics of an oscillating cascade with tip from the viewpoint 01 IAEG [ FEL-1988-151 p 193 N89-14372 clearame p 148 A89-19927 [DGLR PAPER 87-1071 p 143 A89-20242

B-11 WOJCIECH, JOHN J.

WOJCIECH, JOHN J. ZHANG. YONGSHUN Development of the Traffic AMand CollisionAvoidance A method of computer aided design of structural type System 111 (TCAS Ill) - An application of expert system and fuzzy sets theory [AIM PAPER 88-40021 p 159 A89-18182 p 201 A89-19811 WOLF, STEPHEN W. D. ZHANG, ZHAOYING Wall adjustment strategy software for use with the NASA Measurements of the buffet boundary of wings in Langley 0.3-meter transonic cnlogenlc tunnel adaptive wall transonic flow with hot-film method p 148 A89-19805 test section ZHAO, LINGCHENG [ NASA-CR-1816941 p 151 N89-13400 A new approach for computing full unsteady WOOD, J. L aerodynamic characteristics p 147 A89-19788 Cafbon/carbon composite materials for aircraft brakes ZIEGLER, JEHUDA p 165 A89-19427 Universal Ada Test Language (UATL) to support real-time softwardsystem integration and WOOD. JACK factoly/maintenance fault isolation p 197 A89-18009 AH-64A Contractor Logistic Support. The contractors' perspective p 142 A89-18889 ZUEV. V. I. Convective heat transfer in a boundary layer behind a WOOD, R. GARY shock wave propagating along a flat plate with a sharp Computer-aided engineering methods for successful leading edge - A calculalion method and a comparison VHSlC application with experimental data p 144 A89-18546 [AIAA PAPER 88-40351 p 188 A89-18185 ZWANN, R. J. WORSLEY, Y. F. A walk along interfaces Mode S data link applications research in the UK [B88170081 p 154 N89-14223 [AIM PAPER 88-39961 p 158 A89-18153 WRIGHT, WILLIAM 6. A comparison of numerical methods for the prediction of twodimensbnal heat transfer in an electrothermal deicer pad [NASA-CR-4202] p 175 N89-13429 WU. J. C. A unified theoretical-computationalapproach for viscous unsteady rotor aerodynamics p 146 A89-18917 Y

YAYAUCHI, 0. K. Hub loads analysis of the SA349/2 helicopter [NASA-TM-t01061] p 153 N89-13410 YANAGI, RYOOJI Conceptual study of turbo-engines for horizontal takeoff and landing space plane [ IAF PAPER 88-2531 p 184 A89-17745 YANG. YIDONG Counteracting sidewind control system for aircraft landii p 181 A89.19800 YANG, YONGNIAN A new approach for computing full unsteady aerodynamic characteristics p 147 A89-19788 YAO, KUNG Efficient load measurements using singular value decomposition [NASA-CR-184814] p 202 N89-14795 YAVUC 1. Performance prediction analysis for fully deployed parachute canopies p 155 A89-20314 YE. ZHENGYIN A new approach for computing full unsteady aerodynamic characteristics p 147 A89-19788 YEH, HSIEN-YANG Temperature effect on stress wncentration around arcular hole in a composite material specimen representative of X-29A forward-swept wing aircraft [NASA-CR-t79439] p 194 N89-14456 YI. 0. A fundamental approach to the sticking of insect residues to aircraft wings [NASA-CR-183041] p 156 N89-13414 YlN, 5. K. Developments in dynamics methodology at Bell Helicopter Textron p 162 A89-18875 YOKOUKO, 1. Rotating air scoop as airfoil boundary-layer control p 150 A89-20149 YOO, s. Y. Interactive and largedomain solutions of higher-order viscous-tlow equations p148 AB9-19905 YOUNT, LARRY J. Sharing the protection of aircraft electronic systems against the effects of high-level electromagnetic environments between traditional protection and system architecture [AIAA PAPER 88-3917) p187 A89-18094

ZELLUER, JOHN W. Automrmars RPRV navigation. guidance and control [NASA-CR-179425] P 161 N89-14228 ZENYUH, JOHN P. Stereoscopic 3-D d-ys for cockpm [AIM PAPER 88-38871 p 170 A89-18080 ZHANQ, X. Computational analysis of unsteady supersonic cavity Rorm driven by thick shear layers p 145 A89-18803

E12 CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 238) April 1989 I.

vpicai Corporate Source Arkansas State Unlv.. State Unlvenlty. C A flight test design for studying airborne applications index Listing of air to ground duplex data link communications Callfomla State Unlv., Long Beach. p 195 N89-14924 Further comparisons of interactive boundary-layer and Army Aaromedlwl Research Unlt, Fort Rucker, AL thin-layer Navier-Stokes procedures p 149 A89-20137 Disorientation accidents and incidents in US. Army Callfornla State Unlv. at Long Beach. CORPORATE SOURCE helicopters. 1 January 1980 - 30 April 1987 Temperature effect on stress concentration around [AD-A198720] p 156 N89-13417 circular hole in a composite material specimen Army Aerootructures Directorate, Hampton, VI. represenlahe of X-29A forward-swept wing aircraft Mechanics of fatgue crack closure [NASAZR-179439] p 194 N89-14456 I p 186 A89-17401 Callfomla Unlv., Loa Angelee. Design of a simple active controller to suppress Federal7 Aviation AdminisIration. Atlantic City. N J Rotor inflow variability with advance ratio p 145 A89-18855 helicopter air resonance p 162 A89-18877 ~HardwawIauII on~eiI80n and mlrumenlal~onSyslem Efficient load measurements using singular value xpcr#mcnlalaon and resulls Army Aviation Englmrlng Fllght Actlvlty, Edwards decomposition AFB, CA. [NASA-CR-184614] p 202 N89-14795 Rotor system evaluation, phase 1 Calltornla Unlv., Rlverslda. [ AD-A1987941 p 168 N89-13425 Atmospheric photochemical modeling of turbine engine Evaluation of the improved OV-1D anti-icing system fuels and exhausts. Computer model development, volume [AD-A1984381 p 156 N89-14225 1 Army Avbtlon Systems Commnd, Cleveland, OH. [ADA1986901 p 196 N89-13832 Effect of advanced component technology on helicopter A!mcspheric photochemical nodeling o! turbine engine transmisbns fuels and exhausts. Computer model development,volume [NASA-TM-101431] p 193 N89-13794 2 Army Avlatlon Systems Command, Moffett Field, CA. [AD-A198691] p 196 N89-13833 An entropy and viscosity corrected potential method for College of Willlam and Mary. WIIIIamsburg, VI. rotor performance prediction p 145 A89-18857 Optimizationof slender wings for center-of-pressureshin Dynamic perspectivedisplays and the control of tilt-rotor due to change in Mach number p 154 N89-14897 Listings in this index are arranged alphabetically aircraft in simulated flight p 174 A89-18867 Continuum Dynamlcs, Inc., Princeton, NJ. Comparisons of predicted and measured roto1 by corporate source The title 01 the document is Army PropuUon Lab., Cleveland, OH. Advanced transmission studies p 189 A89-18906 performance in hover using a new free wake analysis used to provide a brief description of the subject p 165 A89-18933 AmoM Englmrlng Development Center, Arnold Alr Coordlnatlng ReMarch Council, Inc., Atlanta, GA. matter The page number and the accession Force Statlon, TN. Aviation fuel lubricity evaluation number are included in each entry to assist the An empirical look at tolerames in setting icing test [AD-A1981971 p 177 N89-13434 user in locating the abstract in the abstract sec- conditions with particular application to icing similitude [AD-A198941] p 156 N89-13418 tion II applicable. a report number is also included Avco Lycomlng Dlv., StraIford, CT. D as an aid in identifying the document T55-L-714 engine development and qualification: Tip clearance analysis Douglas Aircraft Co., Inc., Long Beach, CA. [ADA1988491 p 177 N89-13431 Further comparisons 01 interactive boundary-layer and A thin-layer Navier-Stokes procedures p 149 A89-20137 Duke Univ., Durham, NC. Aeroneutlcal Svstems Dlv.. Wright-Patterson AFB. OH. B An approach to solving large reliability models Comparison of the general dynamics ground clobber [AIAA PAPER 88-39051 p 199 A89-18086 algorithm with the GCAS and laws algorithms Ballistic Research Labs., Aberdeen Proving Ground, Comparisons of predicted and measured rotor [ AD-A1984791 p 157 N89-14226 MD. performance in hover using a new free wake analysis Internal pressure measurements lor a liquid payload at p 165 A89-18933 Reconfgurable flight control: An opportunity for low Reynolds numbers integrated diagnostics p 182 N89-14744 [AD-A197438] p 191 N89-13727 Air Force Fllght Dymmlcs Lab.. Wright-Patterson AFB, Bell Hellcopter Co., Fort Worth, TX. F OH. Investigation of difficult component effects on FEM Reconfigurable flight control: An opportunity for vibation prediction for the AH-1G helicopter Federal Avlatlon Admlnlstratlon, Washington, DC. integrated diagnostics p 182 N89-14744 p 162 A89-18879 Terminal area forecasts: Fiscal years 1988-2000 Air Force Inat. of Tach., Wright-Patterson AFB, OH. Civil tiltrotor aircraft - A comparison of five candidate [ AD-A1980793 p 156 N89-13419 Early jet engines and the transition from centrifugal to designs p 163 A89-18882 A microcomputerpollution model for civilian airports and axial compressors: A case study in technological change Boelng Advanced Systems Co.. Seattle, WA. air force bases, model description [AD-A1987751 p 177 N89-13430 Optical fire detector testing in the aircraft engine nacelle [ AD-A1990031 p 197 N89-14616 Analysis of temperature and velocity microtumlence fire test Simulator Florida Atlantlc Unlv.. Bou Raton. parameters from aircraft data and relationship to [ADA1979741 p 168 N89-13427 Application of the mobility power flow approach to atmospheric refractive index structure Fire extinguishingagent evaluation in the Aircraft Engine structural response from distributed loading [ADA1965421 p 196 N89-13854 Nacelle Fire Test Simulator (AENFTS] [ NASA-CR-1813421 p 193 N89-13817 Numerical grid generation and potential airfoil analysis [AD-A1985231 p 157 N89-14227 Fiow Research, Inc., Kent. WA. and design Boolng Commercial Alrplane Co., Seattle, WA. User’s manual for an aerodynamic optimization scheeme [AD-A1979721 p 154 N89-14219 Coupling linearized far-fmld boundary conditions with that updates flow variables and design parameters nonlinear near-field solutions in transonic flow simultaneously Air Force Wrlght AeroMutlCaI Lab.., Wrlght-Patterson [NASA-CR-182180] p 151 N89-13399 AFB, OH. [AD-A1987211 p 153 N89-13405 Foster-Mlller Associates, Inc., Waltham, MA. The 6-16 central integrated test system expert Booing Hellcopter Co., Phllsdelphla, PA. Automated fatigue crack growth measurement parameter system p 202 N89-14763 Civil tiltrotor aircraft - A comparison of five candidate designs p 163 A89-18882 [AD-A198642] p 195 N89-14466 Allled 9gMl COrp., Teterboro. MI. A method of measuring fault latency in a digital flight Dynamic inflow lor practical applications p 147 A89-19625 control system Bootng Mllltary Airplane Development, WA. G [AIAA PAPER 88-38631 p170 A89-18060 SeaW, CEPS: An artiicial intelligence approach to avionics A~lytIf.1Wcoa and Meterlals, Inc., Hampton, VA. maintenance p 201 N89-14749 Garrett Turblne Englne Co., Phwnlx, Al Development of threedimensbnal code for the analysis Ban, Bend, and Newman. Inc., Can- Park,CA. Development of thermomechanical life predicbon 01 jet mixing problem. Part 1: Laminar solution Detaileddesign specificationfoc a prototype Assessment models for thermal barrier coatings p 186 N89-13643 [ NASA-CR-42001 p 152 N89-13401 System for Aircraft Noise (ASAN) General DynamlcdFort Worth, TX. Arkona State Unlv.. Tempe. [AD-A1979361 p 204 N89-14818 Unsteady low-speed windtunnel test of a straked delta Design of high-Reynolds-numberflat-plate experiments Brund Unlv., Uxbrldge (England). wing, oscillating in pitch. Part 4: Plots of time histories of in the NTF The quality of fibre reinforced thermoplastics pressures and overall loads [NASA-CR-184627] p 153 N89-13411 mouldings p 196 N89-13839 [AD-A198682] p 152 N89-13402 c-1 General Electric Co. CORPORA TE SOURCE

Unsteady low-speed windtunnel test of a straked delta Numerical simulations of an isolated microburst. I - Investigationof a moving-modeltechnique for measuring wing, oscillating in pitch. Part 5: Power spectral density Dynamics and structure p 196 A8920265 ground effect plots of the overall loads for harmonic oscillation and the Ylululppl State Unlv., Mlulsnlppl State. [NASA-TM-4080] P 154 N89-14217 response of overall loads to (140s) inputs Overlapping grids for flow field calculations High lift, low pitching moment airfoils [ ADA1986831 p 152 N89-13403 p 195 N89-14918 [NASA-CASE-gR-13215-1I P 154 N89-14224 Unsteady low-speed windtunnel test of a straked delta Passive venting technique for shallow cavities wing. oscillating in pitch. Part 6: Presentation of the N [ NASA-CASE-IAR-14031-11 P 168 N89-14232 visualization program Passive venting technique for shallow cavities [AD-AI 986841 p 152 N89-13404 Natlorul AeronauHc. and Space Admlnlatratlon. Amw [NASA-CASE-lAR-13875-1I p 169 N89-14233 (i.cHnl Elo~trkCO., ClnclnMl. OH. Reae~rchCenter, Moffett FIM, CA. The 13-inch magnetic suspension and balance system Constitutive modeling for isotrqJic materials A method of measuring fault latency in a digital flight wind tunnel [NASA-CR-174805] p 177 N89-13436 control system [NASA-TM-4090] p 184 N89-14241 Qenoral Moton Corp., IndlaMpOb, IN. [AIAA PAPER 88-38631 p 170 A89-18060 Materials and structures for hypersonic vehicles The effects of leading edge and downstream film cooling Simulatiin evaluation of helicopter Terrain [NASA-TM-1015013 p 186 N89-14264 on turbine vane heat transfer FollowinglTerrainAvoidance concepts [NASA-CR-182133] p 192 N89-13754 Natlonal Aeronnutlcn and Space Admlnlatntlon. Lewla [AIAA PAPER 88.39241 p 180 A89-18101 Research Center, Cleveland, OH. Qoorgh Inat of Tech., Athntr. An entropy and viscosity corrected potential method for Euler analysis of a swirl recovery vane design for use Dynamic inflow for practical applications rotor performance prediction p 145 A89-18857 with an advanced single-rotation propfan p 147 A8919625 Dynamic perspective displays and the control of tilt-rotor [AIM PAPER 88-31521 p144 A89-17940 aircraft in simulated flight p 174 A89-18867 Experimental investigation of propfan aeroelastic Comparisons of predicted and measured rotor response in off-axis flow with mistuning in hover using a new free wake analysis I performance [AIM PAPER 88-31531 p 175 A89-17941 p 165 A89-18933 Aeroelastc response of metallic and composite propfan Illlnoln Innt. of Tech., Chkago. Development and flight test of a precision autohover models in yawed flow Management and control of separation by unsteady and capability for tactical rotorcraft p 165 A89-18934 vortical flows Navier-Stokes calculations of hovering rotor flowfields [AIAA PAPER 88-31 541 p 175 A89-17942 Vibration, performance, flutter and forced response [ ADA1989021 p 191 N89-13736 [AIAA PAPER 87-26291 p 149 A8920133 characteristics of a large-scale propfan and its aeroelastic Transonic Navier-Stokes solutions for a fighter-like Management and control of unsteady and turbulent model flows configuration p 149 A89-20134 [AIAA PAPER 88-31551 p 176 A89-17943 [AD-A198091] p 192 N89-13751 Further comparisons of interactive boundary-layer and Advanced transmission p 189 A89-18906 thin-layer Navier-Stokes procedures p 149 A89-20137 studies Equipment to upgrade the facilities of the IIT (Illinois Laser velocimeter measurements of the flowfield Unsteady transonic aerodynamics and aeroelastic Institute of Technology) Fluid Dynamics Research generated by an advanced counterrotating propeller calculations at low-supersonic freestreams Center [ NASA-TM-1014371 p 153 N89-13409 p 149 A89-20145 [ADA1980841 p 184 N89-14242 Predictions of airfoil aerodynamic performance Numerical simulation of tip vortices of wings in subsonic IllInOIa Unhr., Urbana. degradation due to icing Impact of device level faults in a digital avionic and transonic flows p 150 A8920176 Hub loads analysis of the SA34912 helicopter [NASA-TM-I01 4341 p 153 N89-13412 processor Sensor failure detection for jet engines [NASA-TM-1010611 p 153 N89-13410 [AIM PAPER 88.39041 p 172 A89-18112 [ NASA-TM-1013961 Real-time flight test analysis and display techniques for p 177 N89-13432 Inatltute for Perceptlon RVDTNO, !%enterberg Isolated testing of highly maneuverable inlet con cepts the X-29A aircraft (Netherlands). [NASA-TM-101 6921 p 168 N89-13424 [NASA-CR-l79544] p 178 N89-13437 Sound attenuation and speech transmission quality of Thermal Barrier Coatings. Abstracts and figures Control of a human-powered helicopter in hover five types of headsets [NASA-CP-10019] [ NASA-TM-1010291 p 182 N89-13438 p 185 N89-13642 [ IZF-1987-231 p 193 N89-14373 An investigationof environmental influence on the creep An experimentaland analytical evaluation of the tapered behavior of a low pressure plasma sprayed NiCoCrAlY tension-torsion strap concept alloy p 186 N89-13648 [ NASA-TM-1010491 p 191 N89-13746 J Effect of advanced component technology on helicopter Surface grid generation for complex threedimensional transmissions geometries JAt A..oclaton, Mountah VIew, CA. [NASA-TM-101 431 p 193 N89-13794 [NASA-TM-101046] p 191 N89-13747 1 Navier-Stokes calculations of hovering rotor flowfields Advanced Cora technology: Key subsonic propulsion Twodimensional aerodynamic characteristics of the to [AIAA PAPER 87.26291 p 149 A8920133 benefits OLSlTAAT airfoil Numerical simulation of tip vorlices of wings in subsonic [ NASA-TM-1014201 p 178 N89-14237 and transonic flows p 150 ~89-mi76 [NASA-TM-89435] p 154 N89-14216 NatlOMl Aeronautlcn and Space Admlnlntratlon. Hugh Simulation of 3-D viscous flow within a multi-stage Jet Propuldon Lab., Callfornla Inat. of Tech.. turbine Pasadena. L Dryden Fllght Research Center, Edwards, CA. Flight measured and calculated exhaust jet conditions [ NASA-TM-1013761 p 178 N89-14238 Irreducible error rate in aeronautical satellite channels Plotting component maps in the NavylNASA Engine for an FlOO engine in an F-15 airplane p 157 A89-17183 Program (NNEP): A method and its usage [ NASA-TM-1004191 p 177 N89-13435 [NASA-TM-101433] p 178 N89-14239 Natlo~lAeronautia and Space Admlnlntnthm. Hugh K L Drydan Flight Research Faclltty, Edwards, CA. Experimental results for a two-dimensional supersonic inlet used Bs a thrust deflecting nozzle Bucklino characteristics of hmmnic aircraft wino Korean lMt Of SCknca and Technology, Seoul. tubular panels [ NASA-TM-834391 p 194 N89-14386 Parametric studies of advanced turbopfops Plenum chamber effect on wind-tunnel resonance by [ NASA-TM-877561 p 193 N89-13816 the finite-element method p 190 A89-19909 Natlonal AmMutIC. and Soace Admlnlatratlon. [ NASA-TM-1013891 p 195 N89-14465 A review of failure models for unidirectional ceramic Langley Research Center, Hampton, VI. matrix composites under manotonic loads Mechanics of fatigue crack closure [NASA-TM-101421] p 195 N89-14470 L p 186 A89-17401 NaUMI.1 Aerospace Lab., Amsterdam (Netherlands). Stereo 3-D and non-stereo presentations of a Unsteady low-speed windtunnel test of a straked delta Lockhad MUknand Space Co., Palo Alto, CA. computergenerated pictorial primary flight display with On-board expert diagnostics for an avionics wing, oscillating in pitch. Part 4 Plots of time histories of pathway augmentation pressures and overall loads subsystem p m2 N89-14758 [AIAA PAPER 88-39651 p 173 A89-18132 t-O!Wka Wmngment Innt.. 8.th..4., MD. [AD-A198882] p 152 N89-13402 The nature of the aircraft component failure process: Asimulation studyofdatalinkmessageexchange-Flight Unsteady low-speed windtunnel test of a straked delta A Wingnote deck perspective wing. oscillating in pitch. Pari 5: Power spectral density [AIAA PAPER 88-39931 p 158 A89-18151 [ADA1979791 p 169 N89-14234 plots of the overall loads for harmonic oscillation and the Rotor inflow variability with advance ratio response of overall loads to (1-COS) inputs p 145 A89-18855 [ AD-A1986831 p 152 N89-13403 M Tip-path-plane angle effects on rotor blade-voctex Natlonal Trannportatlon Safety Board, Wuhlngton, interaction noise levels and directivity Dc. Maryland Unlv., College Park. p 203 A89-18914 Aircraft accident reports: Brief format, US civil and Aeroelastic optimization of a helicopter rotor Modem wing flutter analysis by computational fluid foreign aviation, issue number 4 of 1987 accidents p 183 A89-18898 dynamics methods p 191 A89-20146 [PB88-916908] p 155 N89-13413 Calculation of the steadily periodic and gust responses Navier-Stokes calculations using Cartesian grids. I Naval Pontgmduate School, Monterey, CA. of a hingeless rotor heliterusing two-dimensional time - Laminar flows p 150 A89-20180 Dynamic stall computations using a zonal Navier-Stokes domain unsteady aerodynamics p 182 N89-14240 model y..uchuutta Innt. of Tech., Cambridge. Coupled flow, thermal, and structural analysis of aerodynamically heated panels p 181 A8920322 [ADA1979421 p 194 N89-14397 Design of feedback control systems for unstable plants A water tunnel study of Gurney flaps Naval Shlp Rowarch and Development Center, with saturating actuators B.M..d.. MD. [NASA-TM-4071] p 151 N89-13395 [NASA-CR-183392l p 194 N89-14377 A potential flow solution on marine propeller and axial Theoretical derivation and calibation technique of a UcDOnrwll AhftCo., St Louh, YO. rotating fan hemisphecical-tipped. five-hole probe Avionics faun tree analysis and artificial intelligence for [AD-A198781] p 191 N89-13735 future aircraft maintenance pmz ~89-147m [NASA-TM-4047] p 151 N89-13396 North Carollna State Unlv., Ralelgh. Me8oscak Environmental SlmulaUona, Inc., Hampton, Aerodynamic design via control theory Navier-Stokes calculations using Cartesian grids. I - VA. [NASA-CR-1817491 p 153 N89-13408 Laminar flows p 150 A89-20180 Numerical simulation of tha 2 August 1985 DFW ThNst-reverser flow investigation on a twin-engine Notre Dam Unlv., IN. microburst with the three-dimensional Terminal Area transporl Seven hole probe measurement of leading edge vortex Simulation System p 175 A8919186 [ NASA-TP-28561 P 153 N89-14213 norm p 146 A89-18939 c-2 CORPORA TE SOURCE West Virginia Univ.

Method of cold smoke generation for vortex core SWlng Federal Systems, Inc., Pal0 Alto, CA. wdng p 191 A89-20324 Unsteady transonic aerodynamics and aeroelastic calarlations at low-supersonic freestreams p 149 A8920145 0 Svordrup Technology, Inc., *mold Air Fom Strtfon, TN. Oklahoma Unlv., Nomun. An empirical look at tolerances in selling icing test The poststall nonlinear dynamics and control of an F-18: conditions with particular application to icing similitude A preliminary investigation p 189 NE914922 [ADA198941 ] p 156 N89-13418 Old Domlnion Unlv.. Norlolk. VA. SvOrdNp Technology, IN., Clovelend, OH. Full-potential integral solution for transonic flows with Viatin. performance, flutter and forced response and without embedded Euler domains characteristics of a large-scale propfan and its aeroelastc p 148 A89-19908 model Coupled flow. thermal. and structural analysis of [AIM PAPER 8831551 p 178 A89-17943 aerodynamically heated panels p 181 A89-20322 Systems Control Technology, Inc., Pslo Alto, CA. The effects of nonlinear damping on Me large deflection Eflect of model uncertainty on failure detection - The response of structures subjected to random excitation threshold selector p 197 A89-17965 p 193 N89-13796 Systems Technology, Inc., Hawthorne, CA. Autonomous RPRV navigation. guidance and control P [NASA-CR-179425] p 181 N89-14228 Phyolw and Electronics Lab. Two. Th. Iioguo T (Notilerlands). Precision approach radars Twenthe and Volkel Technlsche Hogeschaol, D.m (Netherlands). (Netherlands). Multipath propagation problems A walk along interfaces [ FEL-1988-151 p 193 N89-14372 [ 688170081 p 154 N89-14223 Planning R.WUch Cwp., Hampton, VA. TOXM ALM Unlv., College Statbn. Tippathplane angle effects on rotor blade-vortex Transonic wing design wing inverse methods in interaction ndse levels and directivity curvilinear coordinates p 151 A89-20318 p 203 A89-18914 The measurement and prediction of rotordynamic forces Acwstic transmissibility of advanced turboprop aircraft for labyrinth seals window s p 204 A89-20143 [ADA1971851 p 192 N89-13784 Users' manual for the Langley high speed propeller noise A unified approach to vehicle design, control. and flight prediction program (DFP-ATP) path optimization p 168 N89-14231 [NASAGR-4208 ] p204 N89-14820 TMOUnlv., OH. Experimental investigation of propfan aeroelastic Numerical simulation and Comparison of response in off-axis flow with mistuning airfoils the tip region of symmetrical/supercritical for near [AIM PAPER 88-31531 p 175 A89-17941 a helicopter in forward flight A comparison of numerical methods for the prediction [NASA-CR-4212] p 204 N89-14821 of twodimensional heat transfer in an electrothermal Prlnwton Unlv., MI. deicer pad studies Of the dynamics of the hvimli system [NASACR-4202] p175 N89-13429 [NASACR-1832731 p 167 N89-13422 Solution and sensithnty analysis of a complex Purdue Unlv., West Lafayetto, IN. transcendental eigenproblem with pairs of real Aeroelastic response of metallic and composite propfan eigenvalues models in yawed flow [NASACR-182241 ] p 193 N89-13819 [AIM PAPER 88-31541 p 175 A89-17942 Influence of a floor on sound trammissioninto an aircraft fuselage model p166 A89-20135 U LDV measurements in an annular combustormodel [ NASA-CR-182207J p 192 N89-13755 Unltd Technologi.. Rmemrch Center, East Hartford, CT. The effects of inlet turbulence and rotor/stator R interactions on the aerodyMmics and heat transfer of a large-scale rotating turbine rodel. volume 1 [NASA-CR-4079] p 192 N89-13756 RamCo.. Bedford, MA. Expert systems in higher echelon maintenance activities p 202 N89-14781 v Renasehar Polytechnic Inst., Troy, NV. The Center of Excellence in Rotary Technology at Vlgyan Research A.roc).trs, me, Hampton. VA. Rensselaer Polytechnic Institute Wall adjustment strategy software for use wth the NASA [ADA1989641 p168 N89-13426 Langley 0 3-meter transonc nyogenic tunnel adaphve wall Research Trlangk Inst.. Reusmh Trlangk Park, NC. test &on A simulation-basedfault injectionexperiment to evaluate [ NASA-CR-181894I p 151 N89-13400 self-test diagnostics for a fault-tolerant computer Virginis Polytechnlc Inst. and Strte Unlv., Ekksburg. [AIM PAPER 88-38971 p 198 A89-18083 Influence of a floor on sound transmission into an aircralt Stereo 3-D and non-stereo presentations of a fuselage model p 166 A89-20135 computergenerated pictorial primary fiiiht display with A fundamental approach to the sticking of insect pathway augmentatjon resdues to aircralt mngs [AIM PAPER 88-39651 p 173 A89-18132 [NASACR-l8304t] p 156 N89-13414 Rockwdl IntwnatloMl Corp., Columbus, OH. Fabrication and testing of lightweight hydraulic system simuletcf hardware. Phase 2 Addendum W [ADA1985241 pt84 N89-14243 Weapons Systems Resoarch lab., Adelaids (Auatrslh). Rollo-Rova. Im., AthnlL GA. Engim !or Uini-RPV XM-!A Hih time service evaluation of thermal barrier coatings [AD-A1988336J p 178 N89-14238 on the Rolls-Royce RB211 engine p 186 N89-13660 West Vlmlnh Unlv.. Morgsntown. Wingiets on low-aspect-ratiowings S p 149 A89-20142

Schwsrb Im., Orlando. FL Optical fiber data transfer system [NASA-CR-181704] p 194 N89-14376 x(.nw and Englnnrlng Auochteo, Inc., Seattle, WA. Lghtning simulation test technique evaluation [DoT/FM/CT-87/38] p156 N89-13415 SIk- AltW~ft,Stntfwd, CT. Simulation evaluation of helicopter Terrain FollowinglTenain Avoidance concepts [AIM PAPER 88-39241 p 180 A89-18101 Stst. Unlv. of Now Vork. Bmdqmt. Use of the Terminal Area Simulation System (TASS) to study microburst wind shean p 197 N89-14899 c-3 FOREIGN TECHNOLOGY INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 238) April 1989

The combination of simulation and response Introduction of new technologies in the structural area Qpicsl Foreign Technology methodology and its applicationin an aggregate production from the viewpoint 01 IABG Index Listing plan p 190 A89-19806 [DGLR PAPER 87-107) p 143 A8920242 An investigation of wall interterence correction to the Strength 01 dynamically loaded lorce introduction for pressure measurement in low speed wind tunnel with solid fiber-reinforced rotors walls p 183 A89-19808 [DGLR PAPER 87-1081 p 185 A8920243 Selection of the optimal lighter-than-airgas for airship Carbon fiber composites for supersonic technology and a scheme 01 double-layer structural design [DGLR PAPER 87-1241 p 185 A89-20244 p 166 A89-19809 The Oehtal wind tunnel as baslc idea and incentlve The general 01 birds colliding against aeroplanes INTELLECTUAL rule for planning the USAF research center AEDC Tullahoma and anticollision measures p 155 A89-19810 p 183 A89-20245 A method of computer aided design of structural type - An application of expert system and fuzzy sets theory Downstream vorticity measurements from ultrasonic p 201 A89-19811 pulses p 151 A89-20313 Design of multi-level flight control systems GREECE CANADA p 181 A89-19813 Computation 01 rotational transonic flows using a Oualil~calionand operal#onalaspecls 01 lhghl weigh1 decomposihon method p 150 A89-20179 (Ilghl ure8ghl survlvai hnI air droppablel p I8 A89 10471 F I FRANCE Detection 01 laminar-turbulent transition by infrared INDIA thermography p 143 A89-17147 Recent developments in transonic llow computation Computation of the pressure in an incompressible p 145 A89-18749 rotational flow of inviscid lluid p 143 A89-17150 Computation of axisymmetnc supersonic let usrng space Use of the GALA and PALAS tools to enhance the marching technique p 145 A89-18750 devebpment of avionic software INTERNATIONAL ORGANIZATION [AIAA PAPER 88-39431 p 199 A89-18115 The mode data link - Experimentalwork and possible Reflections on avionic integration S future applications in Western Europe [AIAA PAPER 88-39501 p 172 A89-18121 [AIM PAPER 88-39991 p 158 A89-18155 The unused strategic tool - The airship Listings in this index are arranged alphabetically p 161 A89-18752 Architecture 01 an optimal navigation system integrahng by country 01 intellectual orlgin The title of the Radionavigation needs lor the Europe of the future GPS p 160 A89-18751 ISRAEL document is used to provide a briel description 01 p 160 A89-18753 Special committee on luture air navigation systems Processing composite finite element model with the subject matter The page number and the ac- (FANS) p 160 A89-18754 CADCOMP p 166 A89-19982 cession number are included in each entry to as- New design procedures applied to landing gear Aerodynamic characteristics of rectangular sist the user in locating the citation in the abstract development p 167 A89-20138 cross-sectional bodies at M = 0 85 p 151 A89-20317 secfion If applicable. a report number IS also in- ITALY Charactenzation of boundary layer conditions in wind cluded as an aid in identilying the document G tunnel tests through IR thermography imaging p 147 A89-19167 GERYANY'FEDERAL REPUBLIC OF A Optimal integration of inertial sensor functions lor !!igh!-C""!!"! =-d \'ioniiCs .I AUSTRALIA - [AiAA PAPER 88-38781 p 170 A89-18072 Engines for Mini-RPV XM-1A [ AD-At 983361 p 178 N89-14236 Modern digital pressure control system JAPAN [AIAA PAPER 88-39481 p 172 A89-18119 Reduced conservative singular value analysis for Digital control of a quadruplex direct drive actuator robustness p 197 A89-17489 C [AIAA PAPER 88-3951I p 172 A89-18122 Conceptual study of turbo-engines lor horizontal takeoff Analysis of a fighter type aircraft configuration with the and landing space plane CANADA HlSSS panel method at subsonic and supersonic [IAF PAPER 88-2531 p 184 A89-17745 An advanced facility for cockpit studies speeds The T-2 control configured vehicle development, [AIAA PAPER 88-39661 p 182 A89-18133 [DGLR PAPER 87-0851 p 147 A89-19660 integration and lliht test Oceanic clearance delivery via airlground data link Identification of unstable flight-mechanical systems [AIAA PAPER 88-38821 p 179 A89-18076 [AIM PAPER 88-39941 p 158 A89-18152 using an output error method p 181 A89-19661 Triplex digital flight control system for the STOL research The impact of yaw axis control modes. flight directors An analytical description 01 unsteady transonic aircraft 'Aska' and automatic control coupling on decelerating IFR Laval-nozzle llow p147 A89-19664 [AIAA PAPER 88-38831 p 179 A89-18077 approaches for rotorcraft pl80 A89-18903 Yearbook 1987 II; DGLR. Annual Meeting, Berlin, Introduction 01 Pilot's Operational Workload Evaluation A comparison between various sidearm controller Federal Republic 01 Germany, Oct. 5-7, 1987. Rems Research Simulator, POWERS, in Aeromedical Laboratory. configurations in a fly-by-wire helicopter p 142 A89-20226 JASDF p 183 A89-19876 p 180 A89-18905 New application possibilities lor balloon-borne case Method for simulatingturbulence characteristics lor wind

Modeiling oi ground effects on aircran stuaies ~ MiKROBA (Mcrograviry by baiioonsj environment in wind tunnel p 183 A89-19884 p 166 A89-19559 [ DGLR PAPER 87-0691 p 184 A89-20233 Hole tone generated from almost choked to highly Rotating air scoop as airfoil boundary-layer control Improving the hall-modeltechnology in the Goeningen choked jets p 203 A89-19903 p 150 A89-20149 transonic wind tunnel Experimental study on unsteady aerodynamic CHINA, PEOPLES REPUBLIC OF [DGLR PAPER 87-0831 p 183 A89-20234 characteristics of an oscillating cascade with tip A new approach for computing full unsteady Numerical methods for hypersonic flows clearance p 148 A89-19927 aerodynamic characteristics p 147 A89-19788 [DGLR PAPER 87-0841 p 150 A8920235 Fan acoustic modes measuring system Nonlinear stability analysis for helicopter ground p 183 A89-19950 Project for an advanced regional transport aircraft study on aerodynamic heating in the interaction regions reson an c e p 166 A89-19790 [DGLR PAPER 87-0791 p 167 A89-20236 A Optimization 01 mistuned blade rotor for controlling 01 shock waves and turbulent boundary layers induced Concept and flight testing 01 a modern longitudinal lluner p 176 A89-19793 by sharp fins p 148 A89-20131 Counteracting sidewind control system for aircraft motion regulator using an invwse nwdel A study on hypersonic shock tunnel [DGLR PAPER 87-1211 p 181 A89-20238 landing p181 A89-19800 p 148 A89-20132 The relahonship between the aerodynamic Flight guidance technology Experimental study on low-speed aerodynamic characteristics of double-delta wings and vortices with [ DGLR PAPER 87-1191 p 160 A89-20239 characteristics 01 non-axisymmetric slender bodies sideslips at high angles of attack p 148 A89-19801 Development of ram propulsion for flight vehicles p 151 A89-20635 Effect of blade mistuning and bladedisk on cascade [DGLR PAPER 87-1011 p 176 A89-20240 A note on the optimal hypersonic flight path lluner boundaries p 176 A89-19803 Design and integration of air-breathing propulsion p 167 A89-20637 Measurements of the bullet boundary of wings in systems 01 space transports and hypersonic aircraft A note on the aircraft minimum-time turns transonic flow with hot-film method p 148 A89-19805 [DGLR PAPER 87-1031 p 176 A89-20241 p182 A89-20638

D- 1 KOREA(S0UTH) FOREIGN TECHNOLOGY INDEX I K Ada in avionics - Beyond validation [AIM PAPER 88.39071 p 199 A89-18087 KOREA(S0uTH) Fault tolerant avionics Modal analysis of continuous rotor-bearing systems [AIM PAPER 88-39011 p 171 A89-18109 p 188 A89-187% Application of dgital technology to aircraft utility Plenum chamber effect on wind-tunnel resonance by systems t the finite-element method p 190 A89-19909 [AIAA PAPER 88-38721 p 180 A89-18114 An ice detection system for helicopters [AIAA PAPER 88-39491 p 172 A89-18120 N FunctioMl augmentation of digital engine controllers to implement an integrated testability concept NETHERLANDS [AIM PAPER 88-39531 p 176 A89-18124 Development and applications of an avionics research Mode S data link applications research in the UK testbed [AIM PAPER 88-39961 p 158 A89-18153 [AIM PAPER 88-39521 p 172 A89-18123 AI applications to tactical decision aids New proposals for new directions - 1992 and the GAT [AIM PAPER 8840271 p200 A89-18178 ap(xoach to trade in air transport services Sizing up the 146-300 p 161 A89-18346 p 204 A89-18949 Down with drag p 141 A89-18347 Frequency-domain method for the Computation of Boeing 747-400 ~ Flight test p 161 A89-18349 propeller acoustics p XI3 A89-19902 Ground simulation for airborne equipment COCOMAT, a CAE system for composite structures p 188 A89-18741 design p 166 A89-19981 A guide to classical flutter p 188 A89-18801 Design studies of primary aircraft structures in ARALL Computational analysis 01 unsteady supersonic cavity laminates p 167 A89-20318 flows driven by thick shear layers p 145 A8918803 A walk along interfaces The use of sweepfrequency excitation for unsteady [e88170081 p 154 N89-14223 pressure measurement p 147 A89-18940 Precision approach radars Twenthe and Volkel Dynamics of a rigid rotor mounted on discontinuously (Netherlands). Multipath propagation problems non-linear elastic supports p 190 A89-19125 [ FEL-1088-151 p 193 N89-14372 Interference effects associated with a plate-supported Sound attenuation and speech transmission quality of hall-model in hypersonic flow p 148 A89-19924 five types of headsets Interactions between turbulent wakes and boundary [ IZF-1987-233 p 193 N89-14373 layers p 150 A89-20182 Progress towards a commercial aircraft design expert system S [DGLR PAPER 87-1201 p 167 A89-20237 SWEDEN The quality of fibre reinforced thermoplastics Turbine design using complex modes and mouldings p 196 N89-13839 substructuring p 190 A89-19718 Low-speed pressure distributicn on axisymmetric elliptic-nosed bodies p 149 A89-20147 T TAIWAN Study the aerodynamics characteristics of airfoil on vector processors [IAF PAPER ST-88-09] p 143 A89-17874 TURKEY Performance prediction analysis for fully deployed parachute canopies p 155 A89-20314 U U.S.S.R. Variable-cycle engines for boosung-cruising vehicles [IAF PAPER 88-2491 p 175 A89-17742 Data link organization in Mode S secondary surveillance

radar systems ~ Operational compatibility with other Mode S systems [AIM PAPER 88-40031 p 159 A89-18157 Calculationof the unsteady aerodynamic characteristics of bodies in the case of separated flow p 144 A89-18355 Celculation of hypersonic llow past the windward side of a low-aspect-ratio wing at high angles of attack p 144 A89-18357 optimization of algorithms for data processing in radar altimeters with electronic stabilization of the radiation pattern p 174 A89-18401 Convective heat transfer in a boundary layer behind a shock wave propagating along a flat plate with a sharp leading edge - A calculation method and a comparison with expedimental data p 144 A89-18546 An automated method for forecasting the probability of clear air turbulence p 196 A89-18554 A study of contact interaction in aircraft structural elements p 188 A89-18644 Performance of coated materials in high-enthalpy oxidizing gas Rows p 185 A89-18650 Self-similar problem of the separated flow of an ideal fluid past an expanding plate p144 A89-18669 Mathematical modeling of laminar and turbulent supersonic flow past convexxconcave bodies p 144 A89-18671 Determination 01 the perturbations of the Row fields of supersonic wind tunnels from measured aerodynamic coe(ficients p 144 A89-18675 UNITED KINQWY Stress intensity factors for periodic radial cracks in a rotating disc p187 A89-17448 Energy management for integrated flight and propulsion CMIW systems [AIM PAPER 8838731 p178 A8918068

D-2 .

CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 238) April 1989

Typical Contract Number Index Listing NAG3-742 ...... NAS1-16978 ...... NAS1-17409 ...... p196 A89-20265 NAGl.724 NAS1-17919 ...... p151 N89-13400 ...... p198 A89-18083 ...... p204 N89-14820 p204 N89-14821 NAS1-18107 ...... p153 N89-13408 7- NAS1-18331 ...... p194 N89-14376 p196 A89-20265 NUMBER NAS1-18599 ...... p152 N89-13401 ...... p147 A89-19625

NAS3-23927 ...... p177 N89-13436 NAS3-24079 ...... p197 A89-17965 NAS3-24350 ...... p192 N89-13755 Listings in this index are arranged alpha-numeri- NAS3-24619 ...... p192 N89-13754 cally by contract number Under each contract NAS3-24855 ...... p151 N89-13399 number. the accession numbers denoting docu- NAS4-2896 NCA2-162 ments that have been produced as a result 01 .. research done under the contract are arranged in NCC1-89 ...... p!53 N89-13411 ascending order with the AlAA accession numbers NGL-05-0200-243 ...... p190 A89-19909 appearing first The accession number denotes NGT-05-020-412 ...... p194 N89-14456 NSERCA-2181 ...... p150 A89-20149 the number by which the citation is identified in N00014-796-0649 ...... p148 A89-19904 the abstract section Preceding the accession N00014-83-K-0136 ...... p148 A89-19905 number is the page number on which the citation NOOOl4-87-GO757 ...... p157 A89-18143 may be lound N00014-87-K-0036 ...... p185 A89-19481 N00014-87-K-0861 ...... p170 A89-18057 N00167-84-C-0044 ...... p150 A89-20181 AF-AFOSR-0038-87 ...... p184 N89-14242 N60921-86-GCQ35 ...... p185 A89-19481 ...... p 199 A89-18M)6 ...... p197 A89-18009 AF-AFOSR-860121 ...... p 146 ABS18917 N622694O-GO261 ...... p184 N89-14243 A78/KLUf049 ...... p 193 N89-14372 ...... p194 N89-14386 ...... p154 N89-14216 A86IMf161 ...... p 193 N89-14373 ...... p151 N89-13396 DAAG29-82-K-0093 ...... p 168 N89-13426 505-61-01-02 ...... p151 N89-13400 DAAG29-83-K-0002 ...... p 163 A89-18898 p184 N89-14241 DAAG29-85-C-0002 ...... p 149 A89-20133 p 150 A89-20176 p 191 N89-13746 DAAJ02-85-C0033 ...... p 164 A89-18901 DAAJ02-86-C-0027 ...... p 164 A89-18901 DAAJ09-87-C-AO72 ...... p 177 N89-13431 9147 NR9-13784 ...... p 177 N89-13434 505-62-71-01 ...... p152 N89-13401 ...... p145 A89-18853 505-63-01 ...... p185 N89-13642 DE-AC04-76DP-00789 ...... p 143 A89-17460 ...... P193 N89-13819 p 155 A89-20321 p 195 N89-14465 DTFAO3-84-cooo64 ...... p 156 N89-13415 505-63-51-07 ...... p204 N89-14821 F04606-87-poO51 ...... p 169 A89-18052 505-63-51 ...... p193 N89-13794 FO8635-C80-0359 ...... p 196 N89-13832 ...... p182 N89-13438 p 196 N89-13833 ...... p153 N89-13412 F33615-84-C-2431 ...... p 168 N89-13427 p175 N89-13429 p 157 N89-14227 505-68-71-04 ...... p153 N89-14213 F33615-85-C-3013 ...... p 152 N89-13402 ...... p178 N89-14237 p 152 N89-13403 ...... p178 N89-14238 p 152 N89-13404 ...... p153 N89-13408 F33615-86-GO530 ...... p 204 N89-14818 508-43-3144 ...... p193 N89-13816 F33815-86-C2630 ...... p186 N89-14264 F33615-87-C3240 ...... p177 N89-13435 F49620-82-K-0033 ...... p168 N89-13424 F4962043-cO118 ...... p 153 N89-13405 ...... p194 N89-14456 F49620-94-co065 ...... p !40 A89-20!48 ...... p152 K89-13756 ...... p191 N89-13736 535-03-01 ...... p153 N89-13409 ...... p 148 A89-19904 535-03-1 1 ...... p204 N89-14820 F49620-86-GO133 ...... p 192 N89-13751 ...... p195 N89-14470 MDA903-85-C-0139 ...... p 169 N89-14234 ...... p151 N89-13395 NAG1-300 ...... p 156 N89-13414

NAG1-602 ...... p 172 A89-18112 NAG1-619 ...... p 151 A89-20316

...... p194 N89-14377

...... p162 A89-18877 ...... p175 N89-13429 E- 1 REPORT NUMBER INDEX

~~ ~ AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 238) April 1989

npical Report Number index Listing AFOSR-88-0745TR ...... p 191 N89-13736 # AlAA PAPER 88-3993 ...... p 158 A89-18151 * # AFOSR-88-0747TR ...... p 192 N89.13751 # AlAA PAPER 88-3994 ...... p 158 A89-18152 # AIM PAPER 88-3996 ...... p 158 A89-18153 # AFW-8787 ...... p 195 N89-14466 # PAPER 88-3997 ...... A89-18180 AlAA PAPER 88-3998 ...... D 158 A89-18154 # AlAA PAPER 88-3999 ...... p 158 A89-18155 # AFWAL-TR-87-2089 ...... p 168 N89-13427 # AlAA PAPER 88-4000 ...... p 159 ABS-18181 # AFWAL-TR-87-3098-PT-4 ...... p 152 N89-13402 # AlAA PAPER 88-4001 ...... p 158 A89-I8156 # AFWAL-TR-87-3098-PT-5 ...... p 152 N89-13403 # AlAA PAPER 88-4002 ...... AFWAL-TR-87-3098-PT-6 ...... p 152 N89-13404 # AlAA PAPER 88-4003 ...... AFWAL-TR-88-2022 p 157 N89-14227 # NASA CR 183247 p 42 N89 10900 * ...... AlAA PAPER 88-4004 ...... AFWAL-TR-88-3032 ...... p 195 N89-14466 # 7 I AlAA PAPER 88-4005 ...... AlAA PAPER 88-4008 ...... AGARD-PAPER-8 ...... p 168 N89-13424 * # NUMBER SPONSORED AlAA PAPER 88-4009 ...... pz-pq AlAA PAPER 88-4010 p A89-18180 # ...... 200 AlAA PAPER 87-2629 ...... p 149 A89-20133 * # AlAA PAPER 88-4011 ...... p 188 A89-18161 # AlAA PAPER 88-3152 ...... p 144 A89-17940 * # AlAA PAPER 88-4012 ...... p 200 A89-18162 # AlAA PAPER 88-3153 ...... p 175 A89-17941 * # AlAA PAPER 88-4015 ...... p 200 ABS-18183 # Listings in this index are arranged alpha-numeri- AlAA PAPER 88-3154 ...... p 175 ABS-17942 * # AlAA PAPER 88-4021 ...... p 159 A89-18173 # cally by reporl number The page number indicates AlAA PAPER 88-3155 ...... p 176 A89-17943 * # ...... p 201 A89-19862 # AlAA PAPER 88-3850 ...... p 169 A89-18052 # Ihe page on which the citation is located The ...... p 173 ABS-18174 # AIM PAPER 88-3851 ...... p 141 A89-18053 # AlAA PAPER 88-4024 ...... p 159 A89-18175 # "nmher denn!as !he number by which accession AlAA PAPER 88-3852 ...... p !60 A8%!8054 # AiAA PAPER 88-4025 ...... p 159 A89-18176 # the citation is identified An asterisk (*) indicates AIM PAPER 88-3856 ...... p 170 A89-18055 # ...... p200 A89-18178 # lhal the item is a NASA report A pound sign (#) AIM PAPER 88-3858 ...... p 198 A89-18056 # ...... p 174 A89-18190 # AlAA PAPER 88-3859 ...... p 170 A89-18057 # mdicales that the ilem is available on microliche AlAA PAPER 88-4035 ...... p 188 A89-18185 # AlAA PAPER 88-3860 ...... p 170 A89-18058 # ...... p 171 A89-18097 # AIM PAPER 88-3863 ...... p 170 A89-18060 * # ...... p 173 ABS-18165 # A-87132 ...... p 154 N89-14216 * # AlAA PAPER 88-3865 ...... p 198 A89-18062 # AlAA PAPER 88-4042 ...... p 200 A89-18166 # A-88270 ...... p 153 N89-13410 * # AIM PAPER 88-3867 ...... p 198 A89-18064 # AlAA PAPER 88-4044 ...... p 142 A89-19864 # A-88280 ...... p 182 N89-13438 * # AlAA PAPER 88-3868 ...... D 198 A89-18065 # ...... p 191 N89-13747 * # ...... p 191 N89-13746 * #

AD-AI96542 ...... p196 N89-13854 # AD-A197185 ...... p 192 N89-13784 # AD-A197438 ...... p 191 N89-13727 # AD-AI97936 ...... p 204 N89-14818 # AlAA PAPER 88-3882 ...... p 179 A89-18076 # p 157 N89-14228 # AD-A197942 ...... p 194 N89-14397 # AlAA PAPER 883883 ...... D 179 A89-18077 # ASD-TR-88-5022 ...... AD-AI97972 ...... p 154 N89-14219 # AD-A197974 ...... p 168 N89-13427 # AD-A197979 ...... p 189 N89-14234 # AD-A198079 ...... p 156 N89-13419 # ...... p184 N89-14242 # ...... piyi! NLICJ-13Tsi # AlAA PAPER 88-3903 ...... p 199 ABS-18111 # p 154 N89-14223 ...... p177 N89-13434 # PAPER 88.3904 ...... 172 A89.18112 * # B8817008 ...... AD-A198338 ...... p 178 N89-14236 # AD-A198438 ...... p 156 N89-14225 # AlAA PAPER 88-3905 ...... p 199 A89-18086 * # CAS/CHEM-29-88 ...... p 156 N89-13414 # p 199 ABS-18087 # AD-A198479 ...... p 157 N89-14226 # AlAA PAPER 88-3907 ...... p 199 A89-18088 # AD-A198523 ...... p 157 N89-14227 # AlAA PAPER 88-3908 ...... CERL-TR-E-88/08 ...... p 168 N89-13426 # p 171 A89-18090 # AD-A198524 ...... p 184 N89-14243 # AlAA PAPER 88-3911 ...... p 171 ABS-18092 # AD-A198642 ...... p 195 N89-14466 # AlAA PAPER 88-3915 ...... CRC-560 ...... p 177 N89-13434 # p 157 A89-18093 # AD-A198882 ...... p 152 N89-13402 # AlAA PAPER 88-3916 ...... AD-A198683 ...... p 152 N89-13403 # AlAA PAPER 88-3917 ...... p 187 A89-18094 # DGLR PAPER 87-069 ...... p 184 A89-20233 AD-A198684 ...... p 152 N89-13404 # AlAA PAPER 88-3918 ...... p 171 ABS-18095 # DGLR PAPER 87-079 ...... p 167 A89-20236 AIM PAPER 88-3919 p 171 A89-18096 # AD-A198690 ...... p 196 N89-13832 # ...... DGLR PAPER 87-083 ...... p 183 A8920234 ...... p196 N89-13833 # AIM PAPER 88-3921 ...... p 179 ABS-18098 # DGLR PAPER 87-084 ...... p 150 A89-20235 ...... p156 N89-13417 # AlAA PAPER 88-3922 ...... p 179 A89-18099 # DGLR PAPER 87-085 ...... p 147 A89-19660 ...... p153 N89-13405 # AlAA PAPER 88-3923 ...... p 179 A89-18100 # DGLR PAPER 87-101 ...... p 176 A89-20240 ...... p177 N89-13430 # AIM PAPER 88-3924 ...... p 180 A89-18101 # DGLR PAPER 87-103 ...... p 176 A8920241 AD-A198781 ...... p 191 N89-13735 # AlAA PAPER 88-3927 ...... p 171 A89-18102 # DGLR PAPER 87-107 ...... p 143 A89-20242 AD-A198794 ...... p 168 N89-13425 # AlAA PAPER 88-3928 ...... p 174 ABS-18188 # DGLR PAPER 87-108 ...... p 177 N89-13431 # AlAA PAPER 88-3930 ...... p 187 A89-18104 # DGLR PAPER 87-1 19 ...... p 191 N89-13736 # AIM PAPER 88-3931 ...... p i87 AS9-18;05 i? DGLR PAPER 87-120 ...... p 167 A89-20237 ...... p 156 N89-13418 # AIM PAPER 88-3943 ...... p 199 A89-18115 # DGLR PAPER 87-121 ...... p 181 A89-20238 p 201 A89-19860 # AD-A198964 ...... p 168 N89-13426 # AlAA PAPER 88-3946 ...... DGLR PAPER 87-124 ...... p 172 A89-18119 # AD-A199003 ...... p 197 N89-14816 # AIM PAPER 88-3948 ...... AIM PAPER 88-3949 ...... p 172 A89-18120 # p178 N89-14236 # AIM PAPER 88-3950 ...... p 172 A89-18121 # M3DA-AR-005-348 ...... AD-E900740 ...... p191 N89-13727 # AlAA PAPER 88-3951 ...... P 172 A89-18122 # MT/FAA/CT-87/31 ...... p 156 N89-13418 # AEDC-TR-87-23 ...... p 156 N89-13418 # AIM PAPER 88-3952 ...... P 172 A89-18123 # M3T/FAA/CT-87/38 ...... p 158 N89-13415 # AIM PAPER 88-3953 ...... p 176 A89-18124 # AFESC/ESL-TR87-35-VOL-l ...... p 196 N89-13832 # AlAA PAPER 88-3955 ...... P 172 A89-18125 # DTRC-88/031 ...... p 191 N89-13735 # AlAA PAPER 88-3957 ...... D 173 ABS-18126 # AFESC/ESL-TR-87-35-VOL-2 ...... p 196 N89-13833 # # AFESC/ESL-TR-88-53 ...... p 197 N89-14616 # AILPAPER 88-3958 ...... p 157 ABS-18127 D180-30348-1 ...... p 168 N89-13427 # AIM PAPER 88-3961 ...... p 173 A89-18128 # D180-30962-1 ...... p 157 N89-14227 # # AFIT/Cl/NR-88-192 ...... p 177 N89-13430 # AlAA PAPER 88-3962 ...... p 173 A89-18129 D6-52895 ...... p 153 N89-13405 # '# AFIT/CI/NR-88-20 ...... p 196 N89-13854 # AlAA PAPER 88-3965 ...... p 173 A89-18132 AIM PAPER 88-3966 ...... p 182 A89-18133 # E-1737 ...... p 194 N69-14386 ' # AFITICVNR-88-72 ...... p 154 N89-14219 # # AlAA PAPER 88-3967 ...... p 173 A89-18134 €4538 ...... p 192 N89-13756 * # AlAA PAPER 88-3971 ...... p 199 ABS-18137 # ...... p 175 N89-13429 * # AFOSR-88-0662TR ...... p 192 N89-13784 # AlAA PAPER 88-3981 ...... p 199 ABS-18141 # AFOSR-88-0719TR ...... p 153 N89-13405 # AlAA PAPER 88-3985 ...... p 157 A89-18143 # AFOSR-88-0742TR ...... P184 N89-14242 # AlAA PAPER 88-3987 ...... p 158 A89-18145 # E-4425 ...... P 185 N89-13842 * # F-1 I

E-4430 REPORT NUMBER INDEX 1 1 E4430 ...... p 178 N89-14238 # NAS 1.264208 . p 204 N89-14820 * # E-4451 ...... p 195 N89-14465 * # NAS 1.26:4212 . p 204 N89-14821 * # NAS 1.5510019 ...... p 185 N89-13642 * # i ...... p 195 N89-14470 * # E4525 ...... _p 153 N89-13409 # t.1 E4531 ...... p 193 N89-13794 # E-4539 ...... p 178 N89-14239 * # ...... p 153 N89-13412 * # NASA-CASE-LAR.13215-1 ...... p 154 N89-14224 * E4560 ...... p 193 N89-13819 * # NASA-CASE-LAR.13875-1 NASA-CASE-LAR-14031-1 ETN-89-93418 ...... p 193 N89-14372 ETN.89.93448 ...... p 193 N89-14373 # NASA-CP-10019 ...... p 185 N89-13642 * # ETN-89-93456 ...... p 1% N89-14223 NASA-CR-174805 ...... p 177 N89-13436 * # FAA-APO-88-3 ...... p 156 N89-13419 #

FAA-EE-88-4 ...... p 197 N89-14616 #

FEL-1988-15 ...... p 193 N89-14372 NASA-CR-181694 ...... p 151 N89-13400 * # NASA-CR-181704 ...... p 194 N89-14376 * # H-1449 ...... p 177 N89-13435 * # NASA-CR-181749 ...... p 153 N89-13408 * # H-1514 ...... p 194 N89-14456 * # NASA-CR-182133 ...... p 192 N89-13754 * # NASA-CR-182180 ...... p 151 N89-13399 * #

IAF PAPER ST-88-09 ..... p 143 A89-17874 # NASA-CR-183041 ...... p 156 N89-13414 * # IAF PAPER 88-249 ...... p 175 A89-17742 # NASA-CR-183273 ...... p 187 N89-13422 # IAF PAPER 88-253 ...... p 184 A89-17745 # NASA-CR-183392 . p 194 N89-14377 * # IAF PAPER 88-598 ...... p 204 A89-17867 #

ICASE-88-64 ...... p 153 N89-13408 * # NASA-CR-4079 ...... p 192 N89-13756 * #

ISSN-9-06-275445-7 ...... p 154 N89-14223 NASA-CR-4202 _...... p 175 N89-13429 # NASA-CR-4208 _._ ...... p 204 N89-14820 * # IZF-1987-23 ...... p 193 N89-14373 # NASA-CR-4212 ...... p 204 N89-14821 * #

L-16128 ...... p 193 N89-13816 * # ...... p 177 N89-13435 * # ...... p 153 N89-14213 * # ...... p 182 N89-13438 * # ...... p 151 N89-13396 * # NASA-TM-101046 ...... p 191 N89-13747 ' # L-16467 ...... p 151 N89-13395 * # NASA-TM-101049 ...... p 191 N89-13746 * # L-16481 ...... p 154 N89-14217 # ...... p 153 N89-13410 * # L-16515 ...... p 184 N89-14241 * ...... p 178 N89-14238 * # NASA-TM-101389 ...... p 195 N89-14465 * # LMI-IR7OlRl ...... p 169 N89-14234 # NASA-TM-101396 ...... p 177 N89-13432 * # ...... p 178 N89-14237 * # LYGT55-88-04 ...... p 177 N89-13431 # ...... p 195 N89-14470 * # NASA-TM-101431 ...... p 193 N89-13794 ' # MAE-TR-1840 ...... p 167 N89-13422 * # NASA-TM-101433 ...... p 178 N89-14239 * # ...... p 153 N89-13412 * # NA-88Mll ...... p184 N89-14243 # NASA-TM-101437 ...... p 153 N89-13409 * #

NADC-79024-M)-1 ...... p 184 N89-14243 # NASA-TM-101692 p 168 N89-13424 * # NASA-TM-4047 _. p 151 N89-13396 * # NAS 1.15:100419 ...... p 177 N89-13435 * # NASA-TM-4071 ...... p 151 N89-13395 * # NAS 1.15:101029 ...... NASA-TM-4080 ...... p 154 N89-14217 * # NAS 1.15:101046 ...... NASA-TM-4090 ...... NAS 1.15101049 ...... p 191 N89-13746 * # NASA-TM-83439 ...... NAS 1.15101061 ...... p 153 N89-13410 * # NASA-TM-87756 ...... p 193 N89-13816 * # NAS 1.15:101376 ...... p 178 N89-14238 * # NASA-TM-89435 ...... p 154 N89-14216 * # ..... p 195 N89-14465 * # NAS 1.15101396 ...... p 177 N89-13432 * # ...... p 153 N89-14213 ' # ...... p 178 N89-14237 ' # ...... p 195 N89-14470 * # NTSE/AAB-68/08 ...... p 155 N89-13413 # NAS 1.15:101431 ...... p 193 N89-13794 * # NAS 1.15101433 ...... p 178 N89-14239 * # PEW-916908 ...... pl55 N89-13413 # NAS 1.15101434 ..... p 153 N89-13412 * # NAS 1.15:101437 ..... p 153 N89-13409 * # PURDUE-MS-34971 ...... p 192 N89-13755 * # NAS 1.15101501 . p 186 N89-14264 * # ...... p 156 N89-13414 * # NAS 1.154047 ...... p 151 N89-13396 * # NAS 1.154071 ...... p 151 N89-13395 * # TD-87-4247 ...... pl93 N89-14373 # NAS 1.1 54080 ...... p 154 N89-14217 * # ~n88-2572...... p 193 ~89-14372 NAS 1.154090 ...... p 184 N89-14241 * ...... p 161 N89-14228 * # NAS 1.1587756 ...... p 193 N89-13816 * # NAS 1.1589435 ...... p 154 N89-14216 * # USPATENT-APPL-SN-2568 ..... p 169 N89-14233 * # NAS 1.26:174805 ...... p 177 N89-13436 # US-PATENT-APPL-SN-252081..... p 168 N89-14232 # USPATENT-APPL-SN-904132 ..... p 154 N89-14224

US-PATENT-CLASS-244-3543 ..... p 154 N89-14224 * USPATENT-CLASS-416-223+ ... p 154 N89-14224 * USPATENT4.776.531 ...... p 154 N69-14224 '

USAAEFA-85-15 ...... p168 N89-13425 # NAS 1.26:182180 ...... p 151 N89-13399 # UWEFA-87-25 ...... p 156 N89-14225 # NAS 1.28382207 ...... p 192 N89-13755 * # USAARL-88-3 ...... p 156 N89-13417 #

UTRGR-956480-VOL-1 ...... p 192 N89-13756 * # NAS 1.26383392 ...... p 194 N89-14377 * # NAS 1.26:184614 ...... p202 N89-14795 * # WSRL-0566-TM ...... p 178 N89-14236 #

NAS 1.26:4200 ...... P 152 N89-13401 * # NAS 1.264202 ...... p 175 N89-13429 * # ACCESSION NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 238) April 1989

Typical Accession Number A89-18178 # p 200 A89-18907 p 190 A89-19924 # p148 Index Listing A89-18180 # p 159 A89-1@908 p 176 ABS-19927 p 148 A89-19950 # p183 ABS-18181 # p159 A89-18909 p 155 ABS-19981 p 166 A89-18182 # p 159 ABS-18910 p 155 A89-18183 p159 A89-19982 p 166 # A89-18911 P 164 A89-18185 # pl88 A89-20020 p 166 A89-18912 p 203 N89 10844 ' # P 15 p174 ABS-20114 PI90 A89-18188 # A89-18913 p 203 p174 A89-20117 P 160 A89-18189 # A89-18914 * p 203 A89-18190 # p174 A89-20122 p 160 A89-18915 P 146 p 195 A89-20123 # p 160 A89-18259 A89-18916 p 146 p 161 A89-20131 # p 148 A89-18346 ABS-18917 p 146 A89-16347 p 141 A89-20132 # p 148 A89-18918 P 146 p 161 A89-20133 '# p 149 ABS-18349 A89-18919 p 146 NUMBER SPONSORED MICROFICHE NUMBER A89-18350 p 161 A89-20134 * # p 149 A89-18920 P 164 A89-18355 p 144 A89-20135 '# P 166 mp?l(q-q A89-18921 P 164 ABS-20136 # P204 ABS-18357 p 144 A89-18922 p 200 A89-18401 p 174 A89-20137 * # P 149 A89-18923 P 164 A89-18546 p 144 A89-20138 # p167 A89-18924 P 164 Listings is this index are arranged alpha-numeri- ABS-20139 # P201 A89-18554 p196 A89-18925 p 185 A89-18644 p 188 A89-20140 # P 149 cally by accession number The page numher A89-18926 P 190 A89-18650 p 185 A89-20141 # p149 listed to the right indicates the page on which the A89-18928 p 165 A89-18669 p 144 A89-20142 *# p 149 A89-1Pa'. D 165 citation is located An asterisk (') indicates that ABS-18671 p 144 A89-20143 * # P 204 A89.1iiG; # p 165 A89-20144 # P 167 the item is a NASA report A pound sign (#) indi. ABS-18675 p 144 A89-18932 # p175 ABS-18741 p 188 A8940145 '# P 149 cates that the item is available on microfiche A89-18933 '# p 165 ABS-18749 # p 145 ABS-20146 '# P 191 A89-18934 '# p 165 A89-20147 # P 149 A89-18750 # p145 A89-18935 # p 165 A89-18751 p 160 A89-20148 # p 149 A89-18936 # p190 A89-20149 # p 150 A89-17147 # PI43 ABS-18094 u P 187 A89-18752 p 161 A89-18937 # p 201 A89-18753 p 160 A89-20150 # P167 A89-17150 .# P 143 A89-18095 # PI71 A89-18938 # P 165 ABS-20170 p 181 A89717183 P 157 ~89.1~~~6x pi71 A89-18754 p 160 A89-1RR!N____ * p 146 A89-18757 p 188 A89-20176 '# P 150 A89-17401 * p 186 ABS-18097 u P 171 A89-18940 p 147 A89-20179 # P 150 A89-17448 p 187 A89-18766 p 188 A89-18946 p 147 A89-18098 # PI79 p 188 A89-20180 '# p 150 A89-17460 p 143 A89-18801 A89-18948 ~88i8088 # ~179 P 203 A89-20181 # P 150 A89-17489 p 197 A89-18803 p 145 A89-18949 p 204 A89181M) # PI79 A89-20182 # P 150 ABS-17619 p 185 ABS-18851 p 141 p 204 Ae9-18101 P 180 ABS-18950 A89-20184 # P150 A89-17622 p 185 'I ABS-18852 p 188 ~~~-18102# ~171 A89-19125 P 190 A89-20188 # P 191 A89-17624 p 161 A89-18853 p 145 A89-19167 p 147 ABS-18104 # ~187 A8920226 P 142 A89-17742 # p175 A89-18854 p 161 p 175 A89-18105 # Pi87 A89-19186 A89-20233 A89-17745 # PI84 A89-18855 * p 145 A89-19427 p 165 A89-18108 # PI80 A89-20234 A89-17867 # p 204 A89-18856 P 145 ABS-19481 p 185 A~S-I~IOS # pi71 A89-20235 P 150 A89-17874 # PI43 A89-18857 * P 145 A89-19551 p 142 A89-18110 # PI80 A89-20236 P 167 A89-17929 P 184 A89-18858 P 146 A89-19557 p 181 A89-18111 # PI99 A89-20237 P 167 A89-17940 '# P 144 A8918859 P 142 ABS-1 9558 p 181 A~S-I~IIZ pi72 A89-20238 P 181 0 *# A89-18860 PI42 A00 .nccn ARR-17RAl *# 175 ""s- ,"..*Ip ?CC A89-18114 # PlW ABY-2U29Y P 1W A89-17942 * # p 175 A89-18882 P 142 A69-19560 A89-18115 # PI99 P 201 A89-20240 P 176 A89-17943 :# p 176 A89-18863 P 161 A89-19565 p 183 A89-18119 # PI72 A89-20241 P 176 A89-17965 p 197 A89-18864 P200 A89-19625 * p 147 ABS-18120 # PI72 A89-20242 P 143 A89-17979 p 187 A89-18865 P 174 p 147 A89-18121 # 11172 A89-19660 A89-20243 P 185 A89-18009 p 197 A89-18867 * P 174 A89-19661 p 181 ABS-18122 # PI72 A8920244 P 185 A89-18011 p 141 A89-18868 P 174 A89-19664 p 147 A89-18123 # P 172 A89-20245 P 183 A89-18015 p 197 ABS-18869 P 142 A89-19672 A89-18124 # PI76 P 203 A89-20251 P 205 A89-18023 p 141 A89-18870 P 162 A89-19675 166 ABS-18125 # PI72 D A89-20265 p 196 A89-18025 p 141 A89-18871 P 188 A89-19679 A89-18126 # p 173 A89-20311 # p 150 ABS-18030 p 198 A89-18873 P 142 A89-19718 A89-18127 # p157 P 190 A89-20312 # p 150 A89-18034 p 198 A89-18874 PI62 A89-l97&i p 147 A89-18128 PI73 # A89-20313 # P 151 A89-18051 p 169 # A89-18875 P 162 ABS-18129 # PI73 A89-19790 # P 166 A8920314 # P 155 ABS-18052 # PI69 A89-18876 P 162 A89-19793 p 176 A89-18132 '# P 173 # A89-20315 # P A89-18053 # P 141 A89-18877 * P 162 ABS-18133 # PI82 A89-19800 # pl8l A89-20316 '# P A89-18054 # p 169 A89-18878 PI62 A89-18134 # P 173 A89-19801 # p 148 A89-20317 # P A89-18055 # p 170 A89-18879 * P 162 A89-18137 # P199 A89-19803 # p 176 A89-20318 # P ABS-18056 # p 198 A89-18880 P 163 A89-18141 # P 199 A89-19805 # p 148 A89-20319 # P A89-18057 # p170 A89-18881 P 163 A89-18143 # p157 A89-19806 # p 190 A89-20320 # D A89-18058 # Pi70 A89-:8882 p 153 A89-19808 # p 183 A89-18145 # PI58 A89-20321 # P A89-18060 '# P 170 A89-18883 P 155 A89-19809 # p 166 A89-18151 '# PI58 A89-20322 '# P A89-18062 # P 198 A89-18W P 189 A89-19810 # 0155 A89-18152 # PI58 A8920323 # P A89-18064 # PI98 A89-18885 PI63 A89-19811 # p201 A89-18153 # PI58 A89-20324 '# P A89-18065 # P 198 A89-18888 PI63 ABS-19813 # pl8l A89-18154 # P 158 A89-20325 # P A89-18068 # PI78 A89-18891 P 189 A89-19860 # P 201 A89-18155 # PI58 A89-20625 P ABS-18070 # P 179 A89-18892 P 189 A89-19861 # p201 A89-18156 # PI58 A89-20635 # P A89-18071 # P 179 A89-18893 P 163 A89-19882 p 201 A89-18157 # p 159 # A89-20637 # P A89-18072 # PI70 A89-18894 P 189 A89-18158 # PI87 A89-19W # p142 ABS-20638 # P A89-18078 # P 179 A89-18895 P 189 ABS-19867 p 160 A89-18159 # p187 A89-20744 P A89-18077 # p 179 A89-18896 P 163 A89-19870 p 184 A89-18160 # P200 A89-20745 P A89-1BMH) # p 170 A89-18897 P 189 A89-19876 # p 183 A89-18161 # P 188 A89-20747 PI 143 A89-18063 '# p 198 ABS-18098 * P 163 ABS-19884 # p 183 A89-18162 # Pm A89-18085 # p170 A89-18899 P 164 A89-19902 # p 203 A89-18163 # P200 N89-13395 '# P 151 A89-18086 '# p199 A89-18900 P 182 A89-19903 p 203 ~89-181% # P 173 # N89-13396 '# P 151 A89-18087 p199 A89-18901 PI64 A89-19904 # p 148 # A89-18166 P200 N89-13399 '# P 151 # A89-18903 P 180 A89-19905 # p148 A89-18088 # p199 A89-18173 # PI59 N89-13400 '# P 151 A89-18904 PI80 A89-19908 '# p 148 A89-18090 # PI71 A89-18174 # PI73 A89-19909 '# p 190 N89-13401 '# p 152 A89-18092 # PI71 A89-18175 # PI59 A89-18905 PI80 A89-18906 * P 189 ABS-19911 # D190 N89-13402 # p 152 ABS-18093 # P 157 A89-18176 # P 159 G-1 N89-13403 ACCESSION NUMBER INDEX

N89-13403 # p 152 N89-14899 '# p 197 N89-13404 # p 152 N89-14918 '# p 195 N89-14922 * # p 169 N89-13405 # PI53 N89-14924 'X P 195 N89-13408 * # p 153 N89-13409 * # P 153 N89-13410 '# P 153 I N89-13411 '# P 153 N89-13412 '# P 153 N89-13413 # P 155 N89-13414 '# P 156 N89-13415 # PI56 N89-13417 # p156 N89-13418 # p156 N89-13419 # p156 N89-13422 '# p 167 N89-13424 '# p 168 N89-13425 # p168 N89-13426 # p 168 N89-13427 # p 168 N89-13429 * # p 175 N89-13430 # p 177 N89-13431 # p177 N89-13432 '# p 177 N89-13434 # p 177 N89-13435 '# p 177 N89-13436 '# p 177 N89-13437 '# p 178 N89-13438 '# p 182 N89-13642 '# p 185 N89-13643 '# p 186 N89-13648 '# p 186 N89-13660 '# p 186 N89-13727 # p 191 N89-13735 # pl91 N89-13736 # p191 N89-13746 * # p 191 N89-13747 '# p 191 N89-13751 # p 192 N89-13754 * # p 192 N89-13755 '# p 192 N89-13756 '# p 192 N89-13784 # p192 N89-13794 '# p 193 N89-13796 p 193 N89-13816 '# p 193 N89-13817 '# p 193 N89-13819 * # p 193 N89-13832 # p196 N89-13833 # p 196 N89-13839 p 196 N89-13854 # p 196 N89-14213 '# p 153 N89-14216 '# p 154 NA9-14217 '# p 154 N89-14219 # p 154 N89-14223 p 154 N89-14224 * p 154 N89-14225 # p 156 N89-14226 # p 157 N89-14227 # p157 N89-14228 * # p 161 N89-14231 p 168 N89-14232 '# p 168 N89-14233 '# p 169 N89-14234 # p 169 N89-14236 # p 178 N89-14237 '# p 178 N89-14238 '# p 178 N89-14239 '# p 178 N89-14240 p 182 N89-14241 p 184 N89-14242 # p184 N89-14243 # p 184 N89-14264 '# p 186 N89-14372 p 193 N89-14373 # p193 N89-14376 *# p 194 N89-14377 *# p 194 N89-14386 '# p 194 N89-14397 # p 194 N89-14456 '# p 194 N89-14465 '# p 195 N89-14466 # p 195 N89-14470 '# p 195 N89-14616 # p197 N89-14744 # p182 N89-14749 # p201 Fi89-14758 # p202 N89-14760 # p202 N89-14761 # p202 N89-14763 # p202 N89-14795 * # p 202 N89-14818 # p204 N89-14820 * # p 204 N80-14821 # p 204 N89-14897 '# p 154

6-2 AVAILABILITY OF CITED PUBLICATIONS

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15. Supplementary Notes

16. Abstract This bibliography lists 458 reports, articles and other documents introduced into the NASA scientific and technical information system in March, 1989.

17. Key Words (Suggested by Authors(s)) 18. Distribution Statement Aeronautical Engineering Unclassified - Unlimited Aeronautics Bibliographies

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