Aeronautical NASA SP-7037 (116) Engineering December 1979 A Continuing NASA Bibliography with Indexes

National AeronaQs F. Space Administration A S E C U Irt Anautical Engineering Aei ring Aeronautical E uineering Aeronautical Engin ;al Engineering Aeronautic111 iautical Engineering Aeronau Rnautical Engineering Mr bring Aeronautical Engineerin ineering AeFUnautical Erviry al Engineering Aeronautical E iautical EngineeringAeromU1 \eronauticalEngineering Aen ring Aeronautical Engsineerinc NASA SP-1031(116)

AERONAUTICAL ENGINEERING

A Continuing Bibliography

Supplement 116

A selection of annotated references to unclas- sified reports and journal articles that were introduced into the NASA scientific and tech- nical information system and announced in November 1979 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (/AA).

Scientific and Technical Information Branch 1979 ,-ANational AeronaUtics and Space Administration NfG Wàshihgton, DC INTRODUCTION

Under the terms of an interagency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and -technical community concerned with the field of aeronautical engineering. The first issue of this bibliography was published in September 1970 and the first supplement in January 1971. Since that time, monthly supplements have been issued. This supplement to A eronautical Engineering -- A Continuing Bibliograph y (NASA SP-7037) lists 550 reports, journal articles, and other documents originally announced in November 1979 in Scientific and Technical Aerospace Reports (STAR) or in International A erospace A bstracts (IA A). 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 in two major sections, IAA Entries and STAR Entries, in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally in IAA and STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes -- subject, personal author, and contract number -- are included. An annual cumulative index will be published. AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A79-10000 Series)

All publications abstracted in this Section are available from the Technical Information Service, American Institute of Aeronautics and Astronautics, Inc. (AIAA), as follows: Paper copies of accessions are available at $6.00 per document up to a maximum of 20 pages. The charge for each additional page is $0.25. Microfiche of documents announced in /AA are available at the rate of $2.50 per microfiche on demand, and at the rate of $1.10 per microfiche for standing orders for all /AA microfiche. The price for the IAA microfiche by category is available at the rate of $1.25 per microfiche plus a $1.00 service charge per category per issue. Microfiche of all the current AIAA Meeting Papers are available on a standing order basis at the rate of $1.35 per microfiche.

Minimum air-mail postage to foreign countries is $1.00 and all foreign orders are shipped on payment of pro-forma invoices.

All inquiries and requests should be addressed to AIAA Technical Information Service. Please refer to the accession number when requesting publications.

STAR ENTRIES (N79-10000 Series)

One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviations are listed below. If the publication is available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line.

Avail: NTIS. Sold by the National Technical Information Service. Prices for hard copy (HC) and microfiche (MF) are indicated by a price code followed by the letters HC or MF in the STAR citation. Current values for the price codes are given in the tables on page viii.

Documents on microfiche are designated by a pound sign (#) following the accession number. The pound sign is used without regard to the source or quality of the microfiche.

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iv Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration, Public Documents Room (Room 126). 600 Independence Ave., SW., Washington, D.C. 20546, or public document rooms located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Office at the Jet Propulsion Laboratory.

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Avail: Issuing Activity, or Corporate Author, or no indication of availability. Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document.

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Other availabilities: If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line.

v GENERAL AVAILABILITY All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and IAA Entries sections. It is suggested that the bibliography user contact his own library or other local libraries prior to ordering any publication inasmuch as many of the documents have been widely distributed by the issuing agencies, especially NASA. A listing of public collections of NASA documents is included on the inside back cover.

SUBSCRIPTION AVAILABILITY This publication is available on subscription from the National Technical Information Service (NTIS). The annual subscription rate for the monthly supplements is $45.00 domestic; $75.00 foreign. All questions relating to the subscriptions should be referred to NTIS. Attn: Subscrip- tions, 5285 Port Royal Road, Springfield Virginia 22161.

vi ADDRESSES OF ORGANIZATIONS

American Institute of Aeronautics Pendragon House, Inc. and Astronautics 899 Broadway Avenue Technical Information Service Redwood City, California 94063 555 West 57th Street, 1 2th Floor New York, New York 10019 Superintendent of Documents British Library Lending Division, U.S. Government Printing Office Boston Spa, Wetherby, Yorkshire, Washington, D.C. 20402 England

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vii NTIS PRICE SCHEDULES

Schedule A STANDARD PAPER COPY PRICE SCHEDULE (Effective October 1. 1977)

Price Pg Range Naeth Ams.ic.r Fo.u.gss Cod. Pñas Price AOl Microfiche $ 300 $ 4.50 A02 001.025 4.00 8.00 A03 026-050 4.50 9S00 A04 051-075 5.25 10,50 A05 076-100 6.00 1200 A06 - - 101-125 - 650 13.00

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Ell - ' , , , , 22.50 45,00 E12 , 2500 5000 E13 2800 5600 E14 . 31.00 6200 E15 - 3400 6800

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viii TABLE OF CONTENTS

IAAEntries ...... 601 STAR Entries ...... 649

SubjectIndex ...... A-i Personal Author Index ...... B-i Contract Number Index ...... C-i

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED DOCUMENT______AVAILABLE ON if MICROFICHE NASA N79-10024'# Northrop Corp., Hawthorne. Calif Aircraft Group NUMBER -.- STUDY OF AERODYNAMIC TECHNOLOGY FOR VSTOL L CORPORATE AIRCRAFT: HORIZONTAL ATTITUDE SOURCE CONCEPT Final Report May 1978 242 refs Sponsored in part by TITLE S H. Brown p the David Taylor Naval Ship Research and Development Center, I PUBLICATION Bethesda. Md. (Contract NAS2-9771) DATE AUTHOR (NASA-CR-152130; N0R78-54( Avail: NTIS HC A11/MF AOl CSCLO1A A horizontal attitude VSTOL (HAVSTOL) supersonic fighter L AVAILABILITY CONTRACT attack aircraft powered by RALS turbofan propulsion system is SOURCE OR GRANT analyzed Reaction control for subaerodynamic flight is obtained in pitch and yaw from the RALS and roll from wingtip jets powered by bleed air from the RALS duct. Emphasis is placed COSATI REPORT on the development of aerodynamic characteristics and the CODE NUMBERS identification of aerodynamic uncertainties. A wind tunnel program is shown to resolve some of the uncertainties. Aerodynamic data developed are static characteristics about all axes, control effectiveness, drag, propulsion induced effects and reaction control characteristics. G.Y.

TYPICAL CITATION AND ABSTRACT FROM IAA

NASA SPONSORED . AVAILABLE ON I I MICROFICHE AIAA ACCESSION E A79-10266 • , An experimental study of three-dimensional NUMBER .__-j turbulent boundary layer and turbulence characteristics inside a turbomachinery rotor passage. A. K. Anand and B. Lakshminarayana AUTHORS (Pennsylvania State University, University Park, TITLE Society of Mechanical Engineers, Gas Turbine Conference and Products Show, London, England, Apr. 9. 13, .1978, Paper AUTHOR'S TITLE OF 78-GT-1 14.) ASME, Transactiç. , Journal of Engineering for Power, AFFILIATION 676'687; Discussion, 688-690. 19 refs. PFRIflOICAL ______[vol. 100, Oct., 97,8. p. p. Grant No. NGL-9-009-O07. PUBLICATION Three-dimensional boundary layer and turbulence measurements DATE of flow inside a rotating helical channel of a turbomachinery rotor are described. The rotor is a four-bladed axial flow inducer operated at large axial pressure gradient. The mean velocity profiles, turbu- lence intensities and shear Stresses, and limiting stream-line angles are measured at various radial and chordwise locations, using rotating triaxial hot-wire and conventional probes. The radial flows in the rotor channel are found to be higher compared to those at zero or small axial pressure gradient. The radial component of turbulence intensity is found to be higher than the streamwise component due to the effect of rotation. Flow near the annulus wall is found to be highly complex due to the interaction of the blade boundary layers and the annulus wall resulting in an appreciable radial inward flow, and a large defect in the mainstream velocity. Increased level of turbulence intensity and shear stresses near the midpassage are also observed near this radial location. (Author(

tx AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 116)

DECEMBER 1979

In the present paper, conformal mapping is applied to the derivation of equations for calculating the lift coefficient, the moment coefficient, and the coordinates of the aerodynamic center and center of pressure for a wing profile in incompressible flow and the velocity at the wing surface. The high accuracy of she formulas is IAA ENTRIES illustrated by examples. V.P.

A79-47001 On a smooth approximation method and its application to mathematical description of wing aerodynamic charac- A79-46995 Surface-effect components of aerodynamic teristics. V. A. Ovchinnikov, V. D. Osorgin, V. G. Pavlov, and E. Ia. characteristics of air-cushion vehicle with ram pressurization. M. A. Fedorov. (Aviatsionnaia Tekhnika, vol. 21, no. 2, 1978, p. 62-65.) Gur'ianov. (Aviatsionnala Tekhnika, vol. 21, no. 2, 1978, p. 17-29.) Soviet Aeronautics, vol. 21, no. 2, 1978, p. 48-51. Translation. Soviet Aeronautics, vol. 21, no. 2, 1978, p. 10-19. 8 refs. Translation. A79-47002 Solution of the inverse aerodynamics problem In the present paper, the general laws of gasdynamics (laws of by the random search method. G. D. Peshatov and lu. N. Novoselov, total pressure, flow rate, and momentum conservation in the gas (Aviatsionnaia Tekhnika, vol. 21, no. 2. 1978, p. 68-73,) Soviet stream) are used as a basis to derive formulas which relate the skirt Aeronautics, vol. 21, no. 2, 1978, p. 54-58. 7 refs. Translation. components of the aerodynamic characteristics to the parameters A computer-aided method is proposed for designing subsonic defining the geometry and position of the skirts. The interaction and supersonic wing profiles for a given pressure distribution. An force of the oncoming flow is taken into consideration only at the optimization procedure for designing a simply connected contour inner surface of the skirts. The latter are configured as a pi-shaped from she constraints on its shape is outlined, and its block diagram is half-tunnel. It is shown that this geometry is characterized by a high discussed. V.P. L/D ratio and high stability with respect to pitch. V.P

A79-47009 Harmonic oscillations of annular wing in A79-46996 Statistical diagnostics of aircraft engines. lu . steady ideal fluid flow. Z. N. Shesternina. (Aviatsionnaia Tekhnika, V. Kozhevnikov. (Aviatsionnaia Tekhnika, vol. 21, no. 2, 1978, p. vol. 21, no. 2, 1978, p. 115-121.) Soviet Aeronautics, vol. 21, no. 2, 30-35.) Soviet Aeronautics, vol. 21, no. 2, 1978, 20-25. 5 refs. p. 1978, p. 93-98. 7 refs. Translation. Translation. Existing methods of solving problems concerning the harmonic The present paper deals with the linear statistical problem of vibrations of wings in translational flow are based on the substitution aircraft engine parametric diagnostics for a given set of stable modes of a system of attached ring vortices for the wing. The methods of operation. Some diagnostics problems with respect to one or more reduce to the solution of a system of Fredholm integral equations of parameters are analyzed and solved. V. P. the first kind. In the method proposed in the present paper, use is made of she same substitution, however, by using the properties of the single-layer potential and a somewhat modified impermeability A79.46997 Optimal thermogasdynamic design of gas tur- condition, the problem is reduced to a system of Fredholm integral bine engines using element prototypes. I. lu. V. Kozhevnikov, V. 0. equations of the second kind with respect to the density of the Borovik, V. S. lvanov, V. A. Talyzin, I. N. Agliullin, and lu. V. attached vortices. The detailed formalism of these equations made it Meluzov, (Aviatsionnaia Tekhnika, vol. 21, no. 2, 1978, p. 36-43.) possible to prove she uniqueness of the solution, to satisfy the Soviet Aeronautics, vol. 21, no. 2, 1978, p .26-32. Translation. Chaplygin-Joukowski condition, and to determine the influence of The problem of optimal thermogasdynamic designing on the the wing profile configuration on the convergence of the iterations. basis of a mathematical model of a gas-turbine engine, containing the V. P. characteristics of prototype engine elements in similarity parameters is analyzed. Optimality criteria are derived for a two-spool bypass A79-47012 Overall aerodynamic characteristics of caret turbojet engine, making allowance for the engines modes of and delta wings at supersonic speeds. lu. P. Gun'ko and I. I. Mazhul'. operation. V. P. (Aviatsionnaia Tekhnika, vol. 21, no. 2, 1978, P. 129-132.) Soviet Aeronautics, vol. 21, no. 2, 1978, p. 107-110. 6 refs. Translation. A79-46999 Selection of geometric parameters and loca- tion of nose flap on swept wing root profile from tunnel test data. I. A. I. Matiazh, V. A. Sterlin, V. A. Popov, V. V. lsaev, and G. A. A79-47014 Selecting the passenger airplane fuselage. lu . Cheremukhin. (Aviatsionnaia Tekhnika, vol. 21. no. 2, 1978, p. N. Egorov, (Aviatsionnaia Tekhnika, vol. 21, no. 2, 1978, p. 49-54.) Soviet Aeronautics, vol. 21, no. 2, 1978, p. 37-41. 5 refs, 135-138.) Soviet Aeronautics, vol. 21, no. 2, 1978, p. 114-116. Translation. Translation, Weight and drag criteria are presented for the fuselages of passenger aircraft, with consideration of the space required for A79-47000 Analytic formulas for wing profile aero- passenger accomodations. An expression is obtained relating the dynamic characteristics in incompressible flow. N. M. Monakhov. surface area, diameter and length of a fuselage for purposes of (Aviatsionnaia Tekhnika, vol. 21, no. 2, 1978, P. 55-61.) Soviet weight. and drag-optimal design. Relationships between weight and Aeronautics, vol. 21, no. 2, 1978, p. 42.47. Translation. aspect ratio are also examined. B. J.

601 A79-47093

A79-47093 * Some observations on four current subjects of pressure position, the load distribution and the wake characteris- related to aeroelastic stability. H. Ashley (Stanford University, tics are in good agreement with the experimental results particularly Stanford, Calif.). (Israel Annual Conference on Aviation and Astro- for the rectangular wings. Finally, it is noted that the computer time nautics, 20th, Tel Aviv and Haifa, Israel, Feb. 22, 23, 1978.) Israel required is a function of the number of cells into which the wings are Journal of Technology, vol. 16, no. 1-2, 1978, p. 3.22. 63 refs. divided. M.E.P. Grants No. AF-AFOSR .74. 2712; No. NGL05-020-243. After introductory comments on the literature and the purposes A79-47119 # A method of the theory of airfoil profiles with of this paper, a table is presented summarizing the author's views on a jet flap (Ob odnom metode v teorii profilia so struinym some currently solved vs partially unsolved problems related to zakrylkom). I. T. Selezov and I. E. Kornilov (Akademiia Nauk aeroelastic stability. The term 'solved' is used in the practical sense Ukrainskoi SSR, Institut Gidromekhaniki, Kiev, Ukrainian SSR). that engineers are able to cope confidently with that problem during Gidromekhanika, no, 39, 1979, p. 3-6. In Russian. the process of structural design. Selected entries in the table are Sato (1973) has proposed a discrete vortex method for reviewed, partially to motivate the topics in the rest of the paper. calculating flows past jet-flapped wings, which is based on classical The 'four current subjects' are chosen both for timeliness and conformal mapping of the wing into a unit circle. In the present because they are among the ongoing interests of the Stanford group. paper, Sato's method is subjected to a rigorous analysis. It is shown The first involves the prediction of linearized unsteady aerodynamic that introduction of a certain correction term leads to a shift in the loads due to arbitrary motions of streamlined shapes. Some position of the jet and a redistribution of the pressure over the wing, contributions by Edwards are refined, which were motivated by the which provide a better agreement with the experiment. V. P. requirements of active control system design. The second subject is nonlinear unsteady aerodynamics for the transonic regime. After describing a few useful developments from locally-linear theory and A79-47302 # High-performance reinforced plastic structures computational fluid dynamics, there is suggested an empirical for civil aviation (Les structures hautes performances en plastiques procedure for interim-analysis purposes. The third and fourth renforcés pour l'aviation civile), M. E. Heitz. Verre Textile, Plastiques subjects concern recent discoveries regarding the aeroelastic stability Renforcds, vol. 17, Mar. 1979, p. 37-45. In French. of large-aspect-ratio wings and wind turbines. The former work is mainly that of Petre and Boyd. The latter includes some of the author's own preliminary discoveries about the performance and dynamics of vertical-axis machines. (Author) A79.47341 • # Experiments of shock associated noise of supersonic jets. J. M. Seiner and T. D. Norum (NASA, Langley Research Center, Hampton, Va.). American Institute of Aeronautics A79-47098 Analysis of optimal loop and split.S by energy and Astronautics, Fluid and Plasma Dynamics Conference, 12th, state modeling. J. Shinar (Technion - Israel Institute of Technology. Williamsburg, Va., July 23-25 1979, Paper 79-1526. 16 p. 17 refs. Haifa, Israel), D. Yair, and Y. Rotman. (Israel Annual Conference on The paper examines the aeroacoustics associated with model Aviation and Astronautics, 20th, Tel Aviv and Haifa, Israel, Feb. 22, nozzles operating supersonically. In particular, the shock structure 23, 1978.) Israel Journal of Technology, vol. 16, no. 1 . 2, 1978, p. and radiated shock noise of Mach 1.5 and 2.0 nozzles are compared 70-82. 13 refs. with those of a convergent nozzle over a wide nozzle pressure ratio Maneuverability in the vertical plane has great importance in range corresponding to a fully expanded Mach number between performance assessment of high-thrust aircraft. In the paper two unity and 2.37. The nozzles were operated unheated both with and basic vertical turning maneuvers are analyzed as minimum-time without a tab for screech tone suppression. The measurements show optimal control problems with terminal constraint. To avoid the differences between the shock cell spacing of convergent and complexity of the solution of a TPBVP a reduced order model, based convergent-divergent nozzles, and the scaling relation appears to be a on energy-state approximation, is proposed. This approach is the function of the exit-to-throat velocity ratio of each nozzle type. The implementation of the 'maximum maneuver concept' in the vertical acoustic measurements indicate the extent of the pressure ratio range plane and leads to the solution of a more simple initial value where a C-ID nozzle achieves a noise reduction benefit. At the design problem. Moreover, the solution can be expressed in a feedback point of the Mach 1.5 nozzle, the total integrated sound power from form, calling for an eventual real-time airborne application. The this nozzle is 6 dB less than a convergent nozzle operating at the results of the approximation compare very well to the solution of the same pressure ratio and thrust. (Author) original TPBVP. Though the reduced order model identifies only a part of the admissible optimal trajectories, it provides a useful tool to performance comparison and an important insight into the problem A79-47342 # Fully conservative numerical solutions for of optimal vertical turning maneuvers. (Author) unsteady irrotational transonic flow about airfoils. R. Chipman (Grumman Aerospace Corp., Bethpage, N.Y.) and A. Jameson (New York University, New York, N.Y.). American Institute of Aero- nautics and Astronautics, Fluid and Plasma Dynamics Conference, A79-47099 The calculation of non-linear aerodynamic 12th, Williamsburg, Va., July 23-25, 1979, Paper 79-1555. 10 p. 19 characteristics of wings and their wakes in subsonic flow. C. R. Zorea refs. and J. Rom )Technion . Israel Institute of Technology, Haifa, Israel). Numerical difference schemes are presented for the computation (Israel Annual Conference on Aviation and Astronautics, 20th, Tel of unsteady transonic flows about airfoils. A first-order system of Aviv and Haifa, Israel, Feb. 22, 23, 1978.) Israel Journal of equations in conservation form is developed for irrotational (full Technology, vol. 16, no. 1 . 2, 1978, p. 83-96. 32 refs. Grant No. potential) flow and solved by finite difference methods. To enable AF-AFOSR-71-21 45. the boundary conditions to be imposed directly on the airfoil The paper presents a method for calculating the nonlinear surface, a time-varying sheared-rectilinear coordinate transformation characteristics of wings of rectangular and delta planforms for high is used. Explicit differencing schemes are used to solve both lifting down to low aspect ratios in the subsonic speed range. This method and non-lifting cases. Additionally, an alternating direction implicit can be used to calculate the characteristics of the wings and its wake (ADO scheme has been coded for efficient solutions in the as a unified system. The numerical calculations are based on the non-lifting case. Calculated time-accurate solutions for several cases discretization of the vortex sheet into line vortices, and the are compared with the results of other unsteady transonic codes. numerical problems due to this discretization are discussed. Calcula- Good correlation is shown with results produced by the more exact tions are performed for rectangular wings with aspect ratios of 5.33, but computationally slower ,Euler.equations codes. Shock location is 1.0, and 0.25 and for triangular wings with ratios of 1.0, 1.5, and demonstrated to be better predicted than by small-perturbation or 2.0. The results obtained for the aerodynamic coefficients, the center quasi-conservative schemes. (Author)

602 A79-47535

A79-47345 # Experimental measurements of shock/ (Rolls-Royce, Ltd., Combustion Research Dept., Derby, England). boundary-layer interaction of a supercritical airfoil. K. P. Burdges AIAA, SAE, and ASME, Joint Propulsion Conference, 15th, Las (Lockheed-Georgia Co., Marietta, Ga.). American Institute of Aero- Vegas, Nev., June 18-20, 1979, A FAA Paper 79-1196. 11 p. nautics and Astronautics, Fluid and Plasma Dynamics Conference, The possibility of reducing emissions from gas turbine engines, 12th, Williamsburg, Va., July 23-25, 1979, Paper 79-1499. 11 p. 12 by means of small swirl modules, is investigated. Attention is given to refs. combustor design variables and the conflicts which arise between A recent investigation of the shock/boundary-layer interaction factors such as operating cost, engine integrity, short length, and region of a state-of-the-art supercritical airfoil in the Lockheed- altitude restarting. Design constraints for low emission combustors Georgia Compressible Flow Wind Tunnel is summarized. The test discussed are: (1) rich primary zone followed by rapid quench, (2) apparatus is a half airfoil model mounted on the floor of the tunnel lean primary zone, and 131 fuel staging between two zones each which provides a boundary layer with proper upstream history from optimized for opposite extremes in the range of operation. Other stagnation point through the shock wave to the trailing edge. A areas covered are multiple fuel injection modules, and the economic four-tube probe traversed the boundary layer in the vicinity of the advantages of modular combustors which include simplified test shock wave. Measurements were made at all flow boundaries to procedure and design modification. In addition, as an example the provide boundary conditions for Navier-Stokes calculations of the development of a staged combustor for the Rolls Royce RB.21 1 entire flow field. (Author) engine is described. M.E.P.

A79-47346 # Wing aerodynamic loading caused by jet- A79-47428 i! Nozzles for vectored thrust jet engines (Sopla induced lift associated with STOL-OTW configurations. U. von Glahn vozdushno.reaktivnykh dvigatelei s otkloniaemym vektorom tiagi). and D. Groesbeck (NASA, Lewis Research Center, Cleveland, Ohio). K. N. Popov, V. D. Sokolov, and N. I. Khvostov. Moscow, American Institute of Aeronautics and Astronautics, Atmospheric lzdatel'stvo Mash inostroenie, 1979. 144 p. 25 refs. In Russian. Flight Mechanics Conference, Boulder, Cob., Aug. 6-8, 1979, Paper The book deals with the gasdynamic design of nozzles for 79. 1664. 38 p. 5 refs. gassurbine-driven VTOL aircraft. The effectiveness of vectored thrust Surface pressure distributions were obtained with model-scale in vertical takeoff and landing is demonstrated. Some representative STOL-OTW configurations using various nozzles designed to promote powerplant systems for VTOL aircraft are examined. V. P. flow attachment to the wing-flap surface. The nozzle configurations included slot-types and both circular and slot nozzles with external A79-47433 # Fuels, lubricants and other fluids used in flow deflectors. The wing aerodynamic loading caused by the aviation )Aviatsionnye goriuche-smazochnye materialy I spetsial'nye jet-induced lift is presented in conventional terms of delta p/q as a zhidkosti). I. N. Shishkov and V. B. Belov. Moscow, Izdatel'stvo function of chordwise surface distance in the nozzle centerline plane Transport, 1979. 248p. 18 refs. In Russian. as well as outboard of the nozzle centerline. Included in the The properties of fuels, lubricants and other fluids are ex- geometric variables affecting the wing loading are nozzle roof/ amined, and their fundamental applications in aviation and ground- deflector angle, chordwise location of the nozzle, wing size, and flap based technologies are discussed. Chemical and physical character- deflection angle. (Author) istics, production methods and quality control techniques of hydrocarbon fuels for piston and gas turbine engines, including A79-47347 # Performance of a V/STOL tilt nacelle inlet piston engines with spark ignition, piston engines with ignition from with blowing boundary layer control, A. L. Johns, R. C. Williams compression and jet engines, are considered. The production and )NASA, Lewis Research Center, Cleveland, Ohio), and H. C. properties of motor oils are discussed, with attention given to oils for Potonides (Grumman Aerospace Corp., Bethpage, N.Y.). AIAA, aircraft piston engines, turbojet engines, turboprop engines, carbur- SAE, and ASME, Joint Propulsion Conference, 15th, Las Vegas, etor engines and diesel engines. Consistent greases and solid Nev., June 18-20, 1979, A FAA Paper 79-1163. 11 p. 5 refs. lubricants are discussed, and cooling, hydraulic, anti-icing and A scale model of a V/STOL tilt nacelle fitted to a 0.508 m tingle cleaning fluids are examined. A.L.W. stage fan was tested in the NASA Lewis low speed wind tunnel to determine the effect of diffuser blowing on the inlet aerodynamics and aeromechanical performance. The test was conducted over a A79-47520 The inner regions of annular jets. N. W. M. Ko range of freestream speeds (up to 120 knots) and angles-of attack (up and W. T. Chan (University of Hong Kong, Hong Kong). Journal of to 1 20 deg). In general, diffuser blowing had a beneficial affect on all Fluid Mechanics, vol. 93, Aug. 14, 1979, p. 549-584.31 refs. performance parameters. The angle-of-attack range for a separation- Further experiments on the detailed study of annular jets are free flow substantially increased, and the fan face distortion reduced described in which the mean and fluctuating properties in the inner with a corresponding increase in total pressure recovery. Discrete region have been measured. The experiments in the conical jet have narrow band blade stress peaks which were common to the shown, besides the jet vortices in the outer mixing region, another nonblowing (baseline) configuration were eradicated with diffuser train of vortices in the inner region. This train of vortices is due to blowing. V.T. the wake formed by the boundary layer on the surface of the conical bullet. The experiments in the inner region of the basic annular jet have similar mean velocity profiles to those in the internal A79-47348 # New versus existing engines for new helicopter recirculating region. Good correlation is found for the location of the systems - A life cycle Cost view. G. I. Walker (General Electric Co., vortex center, the location of reattachment, the minimum and Aircraft Engine Business Group, Lynn, Mass.). AIAA, SAE, and maximum mean static pressure and their locations with the non- ASME, Joint Propulsion Conference, 15th, Las Vegas, Nev., June dimensional available pressure Mo/AiPatm for entrainment behind 18-20, 1979, AIAA Paper 79-1316. 6 p. the interface. A train of wake vortices is generated in the internal The use of life cycle cost analysis as a tool for decision making recirculating region and a train of jet vortices is found in the inner in system selection with respect to new helicopter system develop- mixing region. Both types of vortices in the inner region seem to ment and acquisition is examined. The tradeoff in choosing an decay fairly rapidly within a distance of one outer diameter Do existing engine or a completely new engine as a power plant for a downstream. The disturbances associated with the wake vortices in new helicopter is studied. Emphasis is given to the analysis of the inner region seem to excite the outer mixing region. (Author) derivative twin versus new twin engines using parameters for disk loading, rotor solidity ratio, rotor tip speed, and equivalent flat plate A79-47535 # Some early experiments in the development of areas, C.F.W. a flying platform for aerodynamic testing. S. M. Ramachandra (Hindustan Aeronautics, Ltd., Bangalore, India). Revue Roumaine A79-47349 # The application of multiple swirl modules in des Sciences Techniques, Série de Mécanique Appliquée, vol. 24, the design and development of gas turbine combustors. B. Jones Jan-Feb. 1979, p. 109-117.

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The flying aerodynamic platform reported in this paper offers The boundary value problems are derived describing first-order an attractive method of interference free aerodynamic testing using a corrections of two-dimensional transonic small disturbance equations suitably instrumented airplane or glider as the model carrier. The low to two-dimensional flow about a lifting swept wing at freestream cost of glider operation coupled with reasonable operating times and Mach number less than unity. The method of matched asymptotic satisfactory model scales makes the flying platform inexpensive for expansion of the transonic small disturbance equations for x aerodynamic testing and is liable to considerable development. determining the correction is used. The three-dimensional transonic (Author) small disturbance theory boundary value problem for a lifting yawed wing is formulated and the methods of Van Dyke and of Cook and A79-47606 Development of V/STOL aircraft - 1950 to Cole for high aspect ratio are examined. C.F.W. 1970. J. P. Campbell (Joint Institute for Advancement of Flight Sciences, Hampton, Va.). American Helicopter Society, Journal, vol. 24, June 1979, p. 7-16. 14 refs. A79-47844 The principles of hovercraft, powering and In the period from 1950 to 1970 many significant V/STOL propulsion. Hovering Craft and Hydrofoil, vol. 18, June-July 1979, aircraft were built and flown and important advances were made in p. 10-14. the development of V/STOL technology. This chronological account The principles, history and development of hovercraft are of V/STOL aircraft starts with the early work on propeller and outlined, together with design aspects, resistances, powering and turbojet vertical-attitude VTOL concepts, and then covers the much propulsion. Some types of hovering craft are discussed, as well as the more extensive work on horizontal-attitude concepts in separate historical development of amphibious and nonamphibious craft, and sections devoted to propeller, turbojet and turbofan, lift-fan, ejector their sealing arrangements such as skirts and sidewalls. In addition, augmentor and rotor V/STOL aircraft. B. J. some basic theory is provided for understanding the hovering principle, and the mechanisms by which this is achieved. Finally, lift A79-47607 V/STOL Technology - Where do we stand. R. and propulsive devices are reviewed, as well as their design aspects, F. Siewert (U.S. Navy, Naval Air Systems Command, Washington, resistances acting, and trends. M.E.P. D.C.). American Helicopter Society, Journal, vol. 24, June 1979, p. 17-29. 16 refs. A broad survey of those aspects of the basic airframe technolo- A79.47845 Gas turbines for ACV's and hydrofoils. gies that directly impact V/STOL aircraft configurations is presented. Hovering Craft and Hydrofoil, vol. 18, June-July 1979, p. 17-20.. Configurations, aerodynamics, structures, propulsion and flight Attention is given to the principles of marine gas turbines and control are addressed. The dominant problem in developing any their applications in hydrofoils and hovercraft. The turbine gas cycle V/STOL aircraft is to optimally integrate the propulsion system and is discussed along with design features such at single or two shaft the airframe to achieve performance consistent with the aircraft machines, heat exchangers, open or closed cycle preheating, and axial mission requirements. Therefore, focus is on hover and low speed or rotary compressors. Fuels are also covered. Finally, applications flight characteristics including propulsion induced effects, flight for naval boost propulsion, merchant ship propulsion and naval ship control requirements, and the characteristics of propulsion systems propulsion are considered. M.E.P. as lifting and/or control devices. Based on this survey, and recognizing that while there are still problems that must be solved, it is concluded that in light of the many technological solutions which exist and are constantly being expanded and improved, V/STOL A79-47847 Jet propulsion for ACV's and hydrofoils. technology is adequate to permit the development of viable and Hovering Craft and Hydrofoil, vol. 18, June-July 1979, p. 30, 31. useful V/STOL aircraft. (Author) Attention is given to the basic theory and design of waterjet propulsion. Formulas are presented for thrust, waterjet propulsive A79-47608 Recent,.. V/STOL aircraft designs. W. H. efficiency, specific speed, and suction specific speed for cavitation. Deckert (NASA, Ames Research Center, V/STOL Aircraft Tech- Inlets for waterjets are also discussed, noting three types: (1) ram nology Div., Moffett Field, Calif.). American Helicopter Society, inlets or scoops, (2) scoop or variable area inlets, and (3) flush inlets Journal, vol. 24, June 1979, p. 30.37. (normally on planing hulls). Waterjet applications discussed include The paper reviews the V/STOL aircraft designs pursued by the Boeing Jetfoil, the Italian Swordfish, and the American Enter- industry from 1971 to 1978, with emphasis on the 1975.1973 prise. Finally, air jet propulsion is covered, noting that while high period. Consideration is given to those designs pertaining to velocity turbojets are not suitable for hovercraft speeds and are too vertical-attitude and horizontal-attitude V/STOL types. These are noisy, ducting air from the fans to propulsive nozzles at the rear has divided into such concepts as tilting jet engine, lift/cruise engine, lift advantages such as low noise level and the fact that one powerplant engine, lift/cruise fan, ejector augmentor, tilt rotor, stowed rotor, serves both lift and propulsion. - M.E.P. and rotor wing. B. J.

A79-47654 # Developments in gear analysis and test tech- A79.47873 # Experimental investigation of helicopter flight niques for helicopter drive systems. C. Albrecht (Boeing Vertol Co., modes on helicopter-generated noise (Ersperimental'nye issledovaniia Philadelphia, Pa.). American Society of Mechanical Engineers, Design rezhimov poleta vertoletov na sozdavaemyi imi shum). B. N. Engineering Conference and Show, Chicago, Ill., May 7 . 10, 1979, Mel'nikov (Gosudarstvennyi Nauchno-lssledovatel'skii Institut Paper 79-DE-15. 16 p. 16 refs. Grazhdanskoi Aviatsii, Moscow, USSR). Akusticheskii Zhurnal, vol. Improvements in helicopter transmission gearing analysis and 25, May-June 1979, p. 450-453. 5 refs. In Russian. test techniques have been developed for the high-precision, light- The establishment of a theoretical relationship between heli- weight gears used on the Heavy Lift, UTTAS and CH-47C and 0 copter flight velocity and noise is highly complicated by the helicopter drive systems. The use of finite element analyses for complexity of the mechanism of excitation and propagation of performing gear stress and natural frequency calculations: transmis- helicopter noise and by the multitude of factors that affect the noise. sion vibration/noise methodology; damage tolerance concepts and In the experiments described, an attempt is made to establish the failure detection methods are discussed. (Author) noise characteristics and the relationship of velocity to noise for the Mi-2, Mi-6, Mi-8, and Ka-26 helicopters. V. P.

A79-47750 Lifting-line theory for a swept wing at tran- sonic speeds. L. P. Cook (California, University, Los Angeles, Calif.). A79-47876 fi The effects of configuration changes on spin Quarterly of Applied Mathematics, vol. 37, July 1979, p. 177.202. and recovery characteristics of a low-wing general aviation research 13 refs. airplane. H. P. Stough, III and J. M. Patton, Jr. INASA, Langley

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Research Center, Hampton, Va.). American Institute of Aeronautics application of recently developed flight test techniques to accom- and Astronautics, Aircraft Systems and Technology Meeting, New plish the program's optimistic objectives. Test results are discussed, York, N. Y., Aug. 20-22 1979, Paper 79. 1786. 13 p.9 refs. including the successful demonstration of lift augmentation and A fully instrumented, low-wing, single-engine general aviation significant STOL performance. (Author) airplane has been spin tested. Several tail configurations, wing leading-edge modifications, fuselage modifications, moment-of- A79-47881 # Compass Cope airframe design history. R. B. inertia variations, center-of-gravity positions, and control inputs have Brown (Boeing Commercial Airplane Co., Product Development Div., been tested to determine their effect on spinning and spin recovery. Renton, Wash.). American Institute of Aeronautics and Astronautics, Results indicate that wing airfoil design can significantly influence Aircraft Systems and Technology Meeting, New York, N. Y., Aug. airplane spin and recovery characteristics and can overpower the 20-22, 1979, Paper 79-1792. 10 p. effects of tail design. Results also point out a need to determine Preliminary design decisions on the project phase (1971-1973( limitations of such factors as Reynolds number in model spin test and flight tests (1973-1974( of the Compass Co pe remotely piloted techniques and high angle-of-atack aerodynamics. (Author) vehicle are discussed. Mission-related decisions are presented along with engine and power plant, wing, landing gear, body, empennage, A79-47878 • # Flight control systems development of highly and flight control design decisions. Wind-tunnel and flight-test results maneuverable aircraft technology /HiMAT/ vehicle. K. L. Petersen are discussed. It is noted that the podded single-engine airplane (NASA, Flight Research Center, Edwards, Calif.). American Institute arrangement utilized can be considered as a potential standard for of Aeronautics and Astronautics, Aircraft Systems and Technology future single-engine high-altitude surveillance designs, manned or Meeting, New York, N. Y., Aug. 20-22, 1979, Paper 79-1789. 20 p. 5 unmanned. The airframe design features discussed also include a refs. composite and bonded primary structure with maximum use of The-highly maneuverable aircraft technology (HiMAT) program honeycomb and fiberglass as well as integral wing fuel containment was conceived to demonstrate advanced technology concepts within a honeycomb basic structure. V. T. through scaled-aircraft flight tests using a remotely piloted tech- nique. Closed-loop primary flight control is performed from a A79-47882 # Manned strategic system concepts 1990-2000. ground-based cockpit, utilizing a digital computer and up/down C. D. Wiler and D. P. Raymer (Rockwell International Corp., North telemetry links. A backup flight control system for emergency American Aircraft Group, Los Angeles, Calif.). American Institute of operation resides in an onboard computer. The onboard systems are Aeronautics and Astronautics, Aircraft Systems and Technology designed to provide fail-operational capabilities and utilize two Meeting, New York, N. Y., Aug. 20-22 1979, Paper 79-1793. 15 p. microcomputers, dual uplink receiver/decoders, and redundant Contract No. F33615-77-C-01 15. hydraulic actuation and power systems. This paper discusses the Manned strategic system concept designs are discussed, requiring design and validation of the primary and backup digital flight control the development of new technologies in the areas of aerodynamics, systems as well as the unique pilotand specialized systems interfaces. propulsion, structures, controls, and stealth. A total of 34 innovative (Author) concepts were prepared using the advanced technologies. Concepts were designed to a strategic 'high-low-low-high' missions, with several // Some results from the use of a control A79.47879 exceptions, and can be grouped into four major categories: (1) augmentation system to study the developed spin of a light plane. T. low-cost simplistic, (2) minimum weight, (3) supersonic penetration, C. O'Bryan, K. E. Glover (NASA, Langley Research Center, Flight (4) laser defended. The concepts were qualitatively rated to select Dynamics and Control Div., Hampton, Va.), and T. E. Edwards (U.S. the best two or three concepts in each category. These remaining Army, Structures Laboratory, Hampton, Va.). American Institute of candidate concepts were then subjected to a preliminary sizing Aeronautics and Astronautics, Aircraft Systems and Technology exercise to select one baseline per category. The baselines were sized, Meeting, New York, N. Y., Aug. 20-22, 1979, Paper 79-1790. 9 p. configurated, analyzed, and reconfigurated. VT. A control augmentation system consisting of hydrogen peroxide rockets mounted on the wing tips of a light airplane has been A79-47883 /1 Identifying desirable design features for the developed and used to study spin recovery characteristics. Recovery C-XX aircraft - A systems approach. W. T. Mikolowsky, S. G. from spins that were unrecoverable with aerodynamic controls was Thompson, and E. W. Caldwell (Lockheed-Georgia Co., Marietta, accomplished in less than one turn at maximum thrust in about three Ga.). American Institute of Aeronautics and Astronautics, Aircraft turns at minimum thrust. The rocket system at maximum thrust Systems and Technology Meeting, New York, N. Y., Aug. 20-22, produced spin recovery characteristics similar to those obtained using 1979, Paper 79-1796. 11 p. 14 refs. Contract No. a parachute. An advantage of using the control augmentation system F33615-78-C-0122. on any airplane being used in a spin test program is its capability to The paper describes Lockheed's approach to the development of demonstrate configuration effects on stall/spin characteristics at very information needed to assess pertinent design features of an high angles of attack and clearly determine the existence of all advanced technology military/commercial transport known as C-XX. possible spin modes. (Author) The first element is a qualitative assessment that focuses on identifying the most significant features and associated design options, such as basic performance, ground interface, airfield compatibility, cargo compartment, inflight refueling, etc. A quantita- A79.47880 # Flight testing the circulation control wing. A. tive analysis examines the configurational effects of the selected J. Pugliese (Grumman Aerospace Corp., Flight Test Dept., Bethpage, design options as well as their military cost-effectiveness and N.Y.) and R. J. Englar (U.S. Naval Material Command, David W. commercial economics. The results of the analysis were incorporated Taylor Naval Ship Research and Development Center, Bethesda, into the LGA-144-400, the latest version of the baseline aircraft, Md.). American Institute of Aeronautics and Astronautics, Aircraft which serves as a point of departure for the analysis of cargo- Systems and Technology Meeting, New York, N. Y., Aug. 20-22, compartment height, passenger provisions, service life specification, 1979, Paper 79-1791. 18 p and other design features. V.T. The Grumman A-6A was modified and flight tested to demon- strate the high lift and STOL capability of the Circulation Control Wing (CCW) concept, which employs a circular trailing edge blown by engine bleed air. The test program included a ground test series A79-47884 # Recent progress in aircraft sink rate measure- for calibration, adjustment, and checkout of the blowing system, ment G. E. Clarke and K. L. Merson (U.S. Navy, Naval Air Test followed by a limited duration flight program to measure blown lift Center, Patuxent River, Md.). American Institute of Aeronautics and enhancement and resulting STOL improvements. The paper describes Astronautics, Aircraft Systems and Technology Meeting, New York, the test program, emphasizing flight safety considerations and N. Y., Aug. 20-22 1979, Paper 79-1798. 5 p.

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Efforts to reduce dependency on manually read emulsion film results of this with respect to accuracy, contributions of otherwise for determination of aircraft sink rate have resulted in test unobtainable information, cost effectiveness, and problems en- development of faster and more consistent techniques. The two countered. During the evaluation of several prototype and produc- methods undergoing more extensive development are: (1) onboard tion aircraft, classic stability and control maneuvers and stability doppler radar and (2) laser theodolite tracking. These two methods derivative extraction (STABDEX) maneuvers were conducted. It is have been tested concurrently with existing sideline and centerline noted that test planning can effect a reduction in flight test time, ballistic camera systems with emphasis on accuracy and time while the total flight test time can be reduced nearly 75% by the correlation of the various methods. The doppler radar appears to give application of STABDEX techniques. The ability to model relatively the best instantaneous sink rate information at touchdown although small changes in the aircraft's response characteristics due to changes location on the aircraft can affect overall accuracy. The laser in the aircraft's shape or configuration is outlined. V.T. theodolite increases the number of significant parameters that can be monitored in real time by the test engineer permitting immediate confirmation of the most significant landing parameters. (Author) A79-47889 # New materials for future commercial aircraft. D. T. Lovell and R. V. Carter (Boeing Commercial Airplane Co., Seattle, Wash.). American Institute of Aeronautics and Astronautics, A79-47885 # An improved method for load survey flight Aircraft Systems and Technology Meeting, New York, N. Y., Aug. testing. A. Rosende, Jr. (Lockheed-Georgia Co., Marietta, Ga.). 20-22 1979, Paper 79-1804. 5 p. American Institute of Aeronautics and Astronautics, Aircraft New structural graphite-epoxy composites and aluminum alloys Systems and Technology Meeting, New York, N.Y., Aug. 20-22, will be used on new model commercial airplanes built during the 1979, Paper 79-1799. 5 p. 1980's. The graphite-epoxy composite system will be used for the In the conduct of load survey flight testing, two methods are principal flight control structures; i.e., elevators, rudder, and ailerons, generally used to obtain inflight load variations: (1) trims, turns and with weight savings exceeding 30% in some components. The new pushdowns, or (2) roller-coaster maneuvers. In either case, maneuver aluminum alloys will be used for primary structures; i.e., upper and requirements call for smooth, quasi-static load factor variations with lower wing skins and stiffeners with strength improvements from 5% minimum variations in airspeed and altitude. The conduct of these to 12%. The graphite-epoxy composite system will be reviewed with maneuvers often exceeds pilot capability to provide the necessary emphasis on design for environmental durability. A review of the data quality, and substantial re-flying becomes necessary. A new aluminum alloy material and durability characteristics will be given. mechanical method has been developed which produces roller-coaster (Author) maneuvers with minimum variation in airspeed and altitude. This paper presents the results achieved using this new system. (Author)

A79.47886 # Dutch roll excitation and recovery techniques A79-47890 # Design of advanced titanium structures. C. A. on a C-141A Starlifter. R. E. Hart (USAF, Flight Test Center, Paez and R. Gordon (Grumman Aerospace Corp., Bethpage, N.Y.). Edwards AFB, Calif.) and D. G. Picha (U.S. Air Force Academy, American Institute of Aeronautics and Astronautics, Aircraft Colorado Springs, Cob.). American Institute of Aeronautics and Systems and Technology Meeting, New York, N. V., Aug. 20-22 Astronautics, Aircraft Systems and Technology Meeting, New York, 1979, Paper 79-1805. 1-2 p.Contract No. F33615-77-3109. N. Y., Aug. 20-22, 1979, Paper 79-1801. 5 p. An application of superplastic forming/diffusion bonding The Air Force has experienced several incidents of severe (SPF/DB) techniques to. a Mach 2.0-class aircraft (ATS/BLAST) is C-141A Starlifter dutch roll problems at cruise altitude. A test discussed. Consideration is given to high-temperature environment program was implemented to develop dutch roll recovery procedures due to aerodynamic and engine heating; loads and dynamic analyses; for use by low time C-141A pilots in all weather conditions. The fracture mechanics analyses of SPF/DB structures; detail design of flight test program consisted of evaluating over 100 dutch roll major components; and concept evaluation. Emphasis is placed on maneuvers. Pilot ratings using Cooper-Harper scale were used to maintainability and reliability assessment and weight and cost evaluate various recovery techniques. Procedures arrived at can be analyses of advanced concepts. Optimization techniques, joint used safely by low time pilots. C-141A flight restrictions at high details, and design/process/tooling interactions are outlined. Atten- cruise altitude/gross weight combinations were lifted as a result. tion is given to potential problem areas and future appliëations of (Author) this new design /fabrication method. V. T.

A79-47887 # Some flight data extraction techniques used A79-47891 # Design development of an advanced composite on a general aviation spin research aircraft. S. M. Sliwa (NASA, aileron. C. F. Griffin (Lockheed-California Co., Burbank, Calif.). Langley Research Center, Flight Dynamics and Control Div., American Institute of Aeronautics and Astronautics, Aircraft Hampton, Va.). American Institute of Aeronautics and Astronautics, Systems and Technology Meeting, New York, N. V., Aug. 20-22, Aircraft Systems and Technology Meeting, New York, N. Y., Aug. 1979, Paper 79-1807. 8 p. Contract No. NAS1-15069. 20-22, 1979, Paper 79-1802. 9 p. 11 refs. This paper summarizes the design development of an advanced Some methods for obtaining flight data from a highly instru- composite inboard aileron for the L-1011 commercial transport mented general aviation spin research aircraft are developed and aircraft. Design details of the composite aileron are reported. Results illustrated. The required correction terms for the measurement of of tests which substantiate the structural integrity of the design are body accelerations, body velocities, and aircraft orientation are also presented. The composite aileron is a multi-rib assembly with presented. In addition, the equations of motion are utilized to derive graphite/epoxy tape-syntactic core sandwich covers, a graphite/ total aerodynamic coefficients for comparison with model tests and epoxy tape front spar, and graphite/epoxy fabric ribs. This structure for analysis. Flight test experience is used to evaluate the utility of is a direct replacement for the current metal aileron with a weight various instruments and calculation techniques for spin research. savings of 28.7 percent (40.3 lb.). Engineering cost estimates, indicate (Author) that the composite structure will be cost competitive with the metal structure it is replacing. (Author) A79-47888 # AFFTC parameter identification experience. D. P. Maunder (USAF, Performance and Flying Qualities Branch, Edwards AFB, Calif.(. American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Meeting, New York, N. V., Aug. 20-22, 1979, Paper 79-1803. 6 p. 5 refs. A79-47892 # Simplified analysis spectrum for joints ex- An overview of the Air Force Flight Test Center experience with posed to complex continuously varying stresses. B. M. Shah automated parameter identification is presented along with the major (Lockheed-Georgia Co., Marietta, Ga.). American Institute of Aero-

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nau tics and Astronautics, Aircraft Systems and Technology Meeting, dynamic pressure fields, and advent of the supersonic fighter are New York, N. V., Aug. 20-22, 1979, Paper 79-1808. 6 P. 9 refs. discussed. The flight research aircraft such as the Bell X-1 and the USAF-supported research. Douglas-558, the century series models, reconnaissance aircraft, the The stress response of aerospace structures to continuous multimission tactical fighter, and the current generation fighters such in-flight turbulence is a complex series of axial/shear stress time- as F-16 and F-18 are described. The SCAT program is considered, histories which have random phasing relationships. Analytically along with supersonic developments in Great Britain, France, and simplified simulation to obtain durability estimates of 'real-world' USSR. It is concluded that the sonic boom still appears to be an experience has been a challenge in-so-far as obtaining reasonably inherent problem of supersonic flight that particularly affects accurate representation. Due to the complexity of this phasing overland commercial flight, and efforts continue for increased problem no unified analytical simulation spectrum has been test- efficiency for economic and performance gains and increased safety verified as representative for durability evaluations of the actual for military and civilian aircraft. A. T. experience. An available empirical procedure of defining discrete axial-shear stress phasing relationships is utilized in this paper to develop an equivalent analytical representation spectrum that can be A79-47896 9 From HIMAT to future fighters. M. R. Robin- utilized for flight-by-flight durability analyses and tests of structural son and S. M. Silverman (Rockwell International Corp., North joints. The essential features of the equivalent spectrum are: American Aircraft Div., Los Angeles, Calif.). American Institute of axial-shear stress phasing relationships; lo-hi sequence within a Aeronautics and Astronautics, Aircraft Systems and Technology mission segment; application of infrequently occurring stresses; and Meeting, New York, N. Y., Aug. 20-22, 1979, Paper 79-1816. 8 p.6 mission segment-to-segment transitions. Test verification in terms of refs. rate of crack growth demonstrates excellent correlation between the The NATO/U.S. Air Force requirements call for high- real-world axial-shear stress histories and the derived equivalent performance aircraft, in substantial numbers, and at a low unit cost. analytical representative stress spectrum. (Author) The objectives of the HiMAT (Highly Maneuverable Aircraft Tech- nology) program are to investigate and demonstrate in-flight high-risk interdisciplinary technologies as applied to a high-performance A79-47893 # The nonaxisymmetric nozzle . it is for real. F. fighter design at the lowest possible price. These technologies form J. Capone (NASA, Langley Research Center, High-Speed Aerody- she basis for other advances in high-performance aircraft design. namics Div., Hampton, Va.). American Institute of Aeronautics and Forward swept wing (FSW( is one of the more promising concepts in Astronautics, Aircraft Systems and Technology Meeting, New York, this category. Several technologies that are common to both N. Y., Aug. 20-22, 1979, Paper 79-1810. 18 p. 82 refs. programs are outlined: aerodynamics and aeroelastic tailoring, A review is made of the current status of the nonaxisymmetric advanced structures, and close-coupled canards. These and control nozzle from a technology standpoint. Some of the potential payoffs systems and low observables will dictate the specific concepts and attributed to this class of nozzles installed on twin-engine high combat characteristics that can be attained for future fighters. V. T. performance fighter aircraft are addressed. These payoffs include a reduction in cruise drag through improved integration and an A79-47898 # Radar cross section fundamentals for the increase in aircraft maneuverability and agility through the applica- aircraft designer. H. A. Stadmore. American Institute of Aeronautics tion of thrust vectoring and reversing. Improved takeoff and landing and Astronautics, Aircraft Systems and Technology Meeting, New characteristics also are expected through the use of thrust vectoring York, N. Y., Aug. 20-22, 1979, Paper 79-1818. lOp. 8 refs. Research and reversing. Stealth and survivability aspects of the aircraft can be supported by the Grumman Aerospace Corp. and NASA. increased through a reduction of nozzle infrared signature and radar Various aspects of radar cross-section (RCS) techniques are cross section. (Author) summarized, with emphasis placed on fundamental electromagnetic phenomena, such as plane and spherical wave formulations, and the A79-47894 II Performance evaluation of an air vehicle utilizing non-axisymmetric nozzles. J. A. Laughrey (USAF, Flight definition of RCS is given in the far-field sense. The basic Dynamics Laboratory, Wright-Patterson AFB, Ohio), D. J. Drape, relationship between electronic countermeasures and a signature level and P. E. Hiley (McDonnell Aircraft Co., St. Louis, Mo.). American is discussed in terms of the detectability range of a target vehicle. Institute of Aeronautics and Astronautics. Aircraft Systems and Fundamental radar-signature analysis techniques, such as the Technology Meeting, New York, N. Y., Aug. 20-22 1979, Paper physical-optics and geometrical-optics approximations, are presented along with examples in terms of aircraft components. Methods of 79-1811. 12 p. 5 refs. An extensive non-axisymmetric nozzle design and performance analysis based on the geometrical theory of diffraction are consid- data base was utilized to evaluate the performance of a vehicle ered and various wave-propagation phenomena are related to local designed for an air-to-air mission. Performance was evaluated through vehicle geometry, Typical vehicle components are also discussed, comparative sizing analysis for selected non-ax isymmetric nozzle together with their contribution to total vehicle RCS and their installations versus a baseline axisymmetric nozzle installation. The individual signature sensitivities. V. T. non-axisymmetric nozzle/vehicle with a single external expansion ramp was found to be lighter in takeoff gross weight (TOGW) than the axisymmetric baseline. The lighter TOGW was due primarily to A79-47900 • 9 Full-scale wind tunnel study of nacelle shape the low weight and low installation drag of the non-axisymmetric on cooling drag. V. R. Corsiglia, J. Katz (NASA, Ames Research nozzle, plus the use of thrust vectoring for reduced drag at the Center, Moffett Field, Calif.), and R. A. Kroeger (Michigan, transonic maneuver condition used for engine sizing. (Author) University, Ann Arbor, Mich.). American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Meeting, New York, N. Y., Aug. 20-22, 1979, Paper 79-1820. 10 p. 7 refs. Tests were made in the NASA-Ames 40- by 80 Foot Wind A79-47895 # Historical development of worldwide super- Tunnel of a wing semispan with a nacelle (no propeller) from a sonic aircraft. M. L. Spearman (NASA, Langley Research Center, typical, general aviation twin-engine aircraft. Measurements were Aeronautical Systems Div., Hampton, Va.). American Institute of made of the effect on drag of the cooling air flow through she Aeronautics and Astronautics, Aircraft Systems and Technology nacelle. Internal and external nacelle pressures were measured. It was Meeting, New York, N. Y., Aug. 20-22, 1979, Paper 79-1815. 15 p. found that the cooling flow accounts for about 13% of the estimated Aerodynamic problems in the development of supersonic airplane drag and about 42% of the cooling flow drag is associated aircraft, their solutions, and innovative design features are presented. with the internal flow. It was concluded that improvements could be Studies of compressibility, introduction of jets, supersonic phenome- made by relocating both the inlet and the outlet of the cooling air. na, transonic drag and lift, longitudinal and directional stability, (Author)

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A79-47901 # Real time weather display in the general close-coupled horizontal canard added, are presented with emphasis aviation cockpit. G. M. Kirkpatrick (GMK Consulting Services, North on demonstrating the beneficial aerodynamic interaction of the Syracuse, N.Y.). American Institute of Aeronautics and Astronautics, canard with the wing, empennage, and other aircraft control surfaces. Aircraft Systems and Technology Meeting, New York, N. V., Aug. These data show that a properly configured three-surface configura- 20.22, 1979, Paper 79-1821.4 p. tion can provide significantly increased performance and an effective Weather radar is currently available for installation in many six-degree-of-freedom maneuvering capability. (Author) general aviation aircraft including the single engine category. The voice channels of the VOR navigation facilities might be used for narrow-band digital transmission. Airborne radar can be expected to A79-47905 II Winglet toe out angle optimization for the be complementary to the relayed radar charts, since the airborne Gates Learjet Longhorn Wing. N. E. Conley (Gates Learjet Corp., units are partially able to overcome the limitations created by the Wichita, Ken.). American Institute of Aeronautics and Astronautics, curvature of the earth and can provide a closeup view of severe Aircraft Systems and Technology Meeting, New York, N. Y., Aug. weather for penetration flight paths. The Cost of digital storage and 20-22, 1979, Paper 79-1831. 8 p. 9 refs. processing circuitry has decreased in recent years to the extent that The Gates Learjet Model 28 Longhorn was the first turbojet to the display, when used with an existing VOR receiver should cost less be certified with winglets. It has now been joined by the stand-up than an airborne weather radar. S. D. cabin Model 55 in applying NASA advanced technology to American business jet aircraft. This paper describes the effect of tailoring toe A79-47902 # A cheap, effective icing detector for general out (incidence) angle for best winglet performance. A winglet with aviation aircraft. J. F. Marchman, Ill (Virginia Polytechnic Institute little or no twist must be toed out to reduce separation at the root and State University, Blacksburg, Va.) and D. Manor. American on the upper surface because of the large inflow angles near the Institute of Aeronautics and Astronautics, Aircraft Systems and upper surface of the wing at the tip. The need for toe out disappears Technology Meeting, New York, N. Y., Aug. 20.22, 1979, Paper rapidly with radial distance from the chord of the wing tip due to the 79. 1823. 6 p. reduction in local flow angles to free stream flow angles. Results of A icing detector device that measures near instantaneous ice wind tunnel testing, computational aerodynamic methods and flight buildup on aircraft wings is presented and various wind tunnel and testing will be presented and their relative merits weighed. Some flight tests are studied. Existing de-icing techniques and ice detectors criteria for useful winglet design will be suggested. (Author) such as a differential pressure type sensor, a beta radiation detector, and vibrating rods are examined and it is found that these devices are A79.47906 II All electric subsystems for next generation not only expensive but, due to their mechanical or electrical systems, transport aircraft. J. W. Phillips (Lockheed Georgia Co., Flight they are very undependable. A probe, consisting of a streamlined Sciences Div., Marietta, Ga.) and N. E. Wood (AiResearch Manufac- extruded tubing, with a 1 inch width, 2.4 inch chord and 6 inch turing Company of California, Torrance, Calif.). American Institute height, was tested at the VPI wind tunnel and then on a flight in of Aeronautics and Astronautics, Aircraft Systemi and Technology 8000 ft during rime icing conditions. Results showed that the ice Meeting, New York, N. Y., Aug. 20-22 1979, Paper 79-1832. 12 p. detector system employing a pilot-static device was found to be A technology assessment study conducted to evaluate the accurate, reliable and inexpensive. C.F.W. applicability of an all-electric airplane concept to transport aircraft is presented. The study compared two all-electric variations of the Lockheed medium advanced transport aircraft (ATA) with the A79-47903 # Engine-aircraft afterbody interactions existing ATA that utilizes advanced structures, aerodynamics, and Recommended testing techniques based on YF. 17 experience. A. E. engines, but conventional secondary power systems. The results of Fanning (USAF, Aero Propulsion Laboratory, Wright- Patterson AFB, reconfiguration tradeoff studies conducted on the primary and Ohio) and E. J. Lucas (ARO, Inc., Arnold Air Force Station, Tenn.). secondary flight controls, engine start, environmental control, American Institute of Aeronautics and Astronautics, Aircraft secondary power generation and distribution, and the landing-gear Systems and Technology Meeting, New York, N. V., Aug. 20.22 brakes are considered. Maintainability, reliability, and weight anal- 1979, Paper 79. 1829. 12 p. 8 refs. yses are outlined. V. T. The fundamental technical aspects of interactions between propulsion system flows and external aerodynamics are discussed. Installation losses are identified as deviation of these interactions A79-47907 # The Beech Model 77 'Skipper' spin program. from idealized values. The objectives and approach of an effort to M. L. Holcomb (Beech Aircraft Corp., Wichita, Kan.). American reduce the uncertainties introduced by the methods used to predict Institute of Aeronautics and Astronautics, Aircraft Systems and these losses are presented. The test techniques used during this effort Technology Meeting, New York, N. V., Aug. 20-22 1979, Paper are presented with data to substantiate their validity. The results of 79-1835.7 p.7 refs. testing two different scale, wind tunnel models are used to define the An economical 2-place general aviation airplane has been effects of characteristic Reynolds number and model scale. The developed for pilot training, including developed spins up to 6 turns. techniques used to correct wind tunnel data to free flight conditions The aerodynamic design of the airplane incorporates many features are presented and the results compared to flight test data. Compari- aimed at providing for adequate spin and spin recovery characteris- sons of surface static pressure distributions and integrated axial tics. To verify early in the development program that the airplane pressure forces are included. Based on these comparisons, recommen- would have acceptable spin characteristics both free flight radio- dations are made. (Author) control model and spin tunnel tests were employed. This was followed by comprehensive full scale airplane flight tests which resulted in certification for the FAA 6-turn acrobatic spin require- ment. (Author) A79-47904 # Benefits of aerodynamic interaction to the three surface configuration. J. W. Agnew and J. R. Hess, Jr. A79.47908 Exploratory study of the influence of wing (McDonnell Aircraft Co., St. Louis, Mo.). American Institute of leading-edge modifications on the spin characteristics of a low-wing Aeronautics and Astronautics, Aircraft Systems and Technology single-engine general aviation airplane. D. J. DiCarlo and J. L. Meeting, New York, N. V., Aug. 20-22 1979, Paper 79-1830. 9 p. Johnson, Jr. (NASA, Langley Research Center, Hampton, Va.). The three-surface configuration and active flight controls will American Institute of Aeronautics and Astronautics, Aircraft permit the next generation of fighter aircraft to capitalize on the Systems and Technology Meeting, New York, N. V., Aug. 20-22 performance and maneuverability benefits of horizontal canards 1979, Paper 79-1837. 15 P. 11 refs. while retaining the stability and control advantages of horizontal A wide variety of model and airplane tests were conducted to tails. Recent wind tunnel data for a contemporary fighter, with a explore the effects of wing leading-edge modifications on the stalling

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and spinning characteristics of a low-wing general aviation research software used is the Lockheed Computer-Graphics Augmented airplane configuration.- The results presented herein discuss the Design and Manufacturing (CADAM) system and the IRAD program effects of leading-edge airfoil modifications applied to the full wing CADATA. CADAM provides a common data base of the selected span and to partial-span locations. The results obtained in the study vehicle design for all user disciplines: preliminary design, loft, indicate that the wing modifications can produce large effects (both production design, tool design, numerical control part programming, favorable or unfavorable) on spin resistance, developed spin charac- quality control, and product support. Examples of the use of teristics, and spin recovery. (Author) CADAM and CADATA are given to illustrate the cost savings and reduced time spans achieved, VT,

A79-47909 # Design of the circulation control wing STOL demonstrator aircraft. R. J. Englar, R. A. Hemmerly (U.S. Naval A79.47913 * # The characteristics of a lift cruise fan V/STOL Material Command, David W. Taylor Naval Ship Research and configuration in near proximity to a small deck with finite edge Development Center, Bethesda, Md.), W. H. Moore, V. Seredinsky, positions, V. R. Stewart (Rockwell International Corp., Columbus, Ohio). W. Valckenaere, and J. A. Jackson (Grumman Aerospace Corp., American Institute of Aeronautics and Astronautics, Aircraft Bethpage, N.Y.). American Institute of Aeronautics and Astro- Systems and Technology Meeting, New York, N. V., Aug. 20-22, nautics, Aircraft Systems and Technology Meeting, New York, N. V., 1979, Paper 79-1854. 8 p. NASA-supported research. Two V/STOL model configurations utilizing lift-cruise-fans for Aug. 20-22, 1979, Paper 79-1842. 12 p.9 refs. A testbed aircraft design and modification and a flight demon- the propulsion system have been tested in the presence of a small stration program have been conducted to confirm the short takeoff landing platform with finite deck edge positions. Results and analysis and landing characteristics of the circulation-control-wing (CCW) of these tests are presented. The model was tested at both static concept on an A-6A flight demonstrator. Wind tunnel, engine bleed, (zero velocity) and forward speed conditions with several heights and and flight tests investigations have verified that the test aircraft can deck edge positions. Configurations utilizing three fans and four fans double the lifting capabilities of the A-BA by using existing bleed were investigated. Incremental forces and moments induced by the flow. A trimmed lift coefficient of 3.60 produced a 67-knot airspeed various deck edge positions are analyzed as relating to the model for the demonstrator, and indicated that maximum lift coefficients height above the ground and the thrust velocity relationships. The predicted by tunnel results were obtainable by the manned aircraft. test and analysis show she induced forces to be relatively unaffected by deck edge. The program's proof-of-concept objectives are accomplished, and the (Author) potential payoffs of a CCW-configu ratedhigh-performance naval aircraft are identified. S. D. A79.47914 * # Aerodynamic effects of an attitude control vane on a tilt-nacelle V/STOL propulsion system. M. D. Betzina (NASA, Ames Research Center, Moffett Field, Calif.( and R. Kita A79-47910 # Geometric data transfer. W. L. Howard (Rock- (Grumman Aerospace Corp., Bethpage, N.Y.). American Institute of well International Corp., El Segundo, Calif.). American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Aeronautics and Astronautics, Aircraft Systems and Technology Meeting, New York, N. Y., Aug. 20-22, 1979, Paper 79 . 1855. 11 p. Meeting, New York, N. V., Aug. 20-22, 1979, Paper 79-1844, 5 p. One possible technique for obtaining longitudinal control on a Coordination of an engineering-manufacturing agreement as to tilt-nacelle V/STOL aircraft is the use of a variable attitude vane data format, procedures, and schedules for geometric data transfer assembly mounted in the propulsion system exhaust. Deflecting the within two separate companies is shown. Consideration is given to vane produces large forces and moments without depending on the methods used in gaining agreement, examples of problems forward speed of the aircraft. Tests are carried out in the Ames 40 by overcome, and procedures used to document and implement solu- 80 ft wind tunnel on a large-scale tilt-nacelle V/STOL propulsion tions. Sample model drawings were constructed and then redrawn system with and without a variable attitude control vane assembly. several times in accordance with requirements of design management Aerodynamic characteristics are analyzed in terms of nacelle aero- and manufacturing. Manual drawing release and automated drawing dynamics, vane aerodynamics, and vane-induced effects on the release are discussed with emphasis placed on the use of the CADAM nacelle aerodynamics. It is shown that the aerodynamic forces due to model, V. T. the nacelle without the vane can be a significant part of the total forces produced by the propulsion system. The control vane effectively produces large changes in pitching moment which are accompanied by significant changes in total lift and drag. The vane A79-47911 # Engineering and manufacturing communica- has a substantial effect on the propulsion-system aerodynamics. tion via the computer data base. E. N. Nilson (United Technologies Other pertinent results are also given. S. D. Corp., Pratt and Whitney Aircraft Group, East Hartford, Conn.). American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Meeting, New York, N. V., Aug. 20-22, A79-47918 # Energy efficient aircraft engines. R. Chamber- 1979, Paper 79-1845. 8 p. 12 refs. lin and B. Miller (NASA, Lewis Research Center, Energy Con- The most substantial reductions in lead time and cost to be servative Engines Office, Cleveland, Ohio). American Institute of realized across the design/manufacturing interface come from inte- Aeronautics and Astronautics, Aircraft Systems and Technology grated interactive CAD/CAM. The computer data base performs the Meeting, New York, N. V., Aug. 20-22 1979, Paper 79-1861. 11 p. fundamental communication function. The present status of this The three engine programs that constitute the propulsion technology, the extent of its utilization, its implementation, portion of NASA's Aircraft Energy Efficiency Program are described, examples of applications, potential benefits to be derived, implemen- their status indicated, and anticipated improvements in SFC dis- tation problems and solutions, and the developing CAD/CAM cussed. The three engine programs are: (1) engine component technology are the subject of this paper. (Author) improvement, directed at current engines, (2) energy efficient engine, directed at new turbofan engines, and (3) advanced turboprops, A79.47912 # CADAM data handling from conceptual design directed at technology for advanced turboprop-powered aircraft with through produce support. S. J. Smyth (Lockheed-Calitornia Co., cruise speeds to Mach 0.8. Unique propulsion system interactive ties Burbank, Calif.). American Institute of Aeronautics and Astro- to the airframe resulting from engine design features to reduce fuel nautics, Aircraft Systems and Technology Meeting, New York, N. Y., consumption are discussed. Emphasis is placed on the advanced Aug. 20-22, 1979, Paper 79-1846. 8 p. turboprop since it offers the largest potential fuel savings of the three The use of interactive computer graphics for data handling in propulsion programs and also has the strongest interactive ties to the aircraft design, manufacturing, and product support is discussed. The airframe. (Author)

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A79-47919 # Air buoyant vehicles - Energy efficient air- schedules, avionics configuration changes, changing customer require- craft. V. H. Paviecka (Airships International, Inc., Tustin, Calif.). ments, etc. Other areas covered include the planned phase-in of American Institute of Aeronautics and Astronautics, Aircraft customer personnel, and the reliability improvement warranty Systems and Technology Meeting, New York, N. Y., Aug. 20-22, (RIW). M.E.P. 1979, Paper 79-1862. 7 p. Energy and overall economic considerations of airplane and two airships in terms of a cost intensity parameter indicate that Metalclad A79-47924 # High-performance wings with significant airships can now be constructed and operated with an economic leading-edge thrust at supersonic speeds. A. W. Robins and H. W. superiority to wide-body jet transports. Comparisons are based on Carlson (NASA, Langley Research Center, High-Speed Aerodynamics computer printouts of actual flights of 747F and on design studies of Div., Hampton, Va.). American Institute of Aeronautics and Astro- MC-80 and MC-100. B. J. nautics, Aircraft Systems and Technology Meeting, New York, N. V., Aug. 20-22, 1979, Paper 79-1871.6 p. ii refs. A79-47920 # Laminar flow stabilization by surface cooling A new class of curved-leading-edge wings with which significant on hydrogen fueled aircraft. J. G. Theisen (Lockheed-Georgia Co., levels of leading-edge thrust may be achieved at moderate supersonic Marietta, Ga.), G. D. Brewer, and L. R. Miranda (Lockheed- speeds is suggested. A recent analysis of the factors limiting such California Co., Burbank, Calif.). American Institute of Aeronautics leading-edge thrust has led to a new method for the prediction of and Astronautics, Aircraft Systems and Technology Meeting, New attainable leading-edge thrust from subsonic through supersonic York, N.Y., Aug. 20-22, 1979, Paper 79-1863. 12 p. 30 refs. speeds for wings of arbitrary planform. Recent supersonic tests of a Research supported by Lockheed-California Independent Research new wing shape, which largely meets design criteria given by the new and Development Funds. prediction method, give evidence of significant levels of leading-edge The feasibility of delaying the transition from laminar to thrust. The consequent unusually high levels of aerodynamic turbulent flow over aerodynamic surfaces by cooling those surfaces, performance should renew interest in supersonic-cruise vehicle design to decrease friction and increase fuel economy of aircraft, is in general and in cruise-speed selection in particular. (Author) discussed. For the 'energy crisis', hydrogen is being considered as an alternate fuel, so its cryogenic properties may be used for cooling A79-47925 3 Aerodynamics of spoiler control devices. M. D. below the 280 deg R known to stabilize boundary layers. Equations Mack, H. C. Seetharam, W. G. Kuhn, and J. T. Bright (Boeing for the stability analysis of a two-dimensional, compressible, laminar Commercial Airplane Co., Flight Controls Technology Research boundary layer are presented, including heat transfer and adverse Group, Seattle, Wash.). American Institute of Aeronautics and pressure gradient effects which constitute the principal new techno- Astronautics, Aircraft Systems and Technology Meeting, New York, logical contribution of this study, for near-cruise flight. Preliminary N. Y., Aug. 20-22, 1979, Paper 791873. 19 p. 28 refs. systems analysis for an advanced commercial transport shows drag Experimental and computational studies of the aerodynamics of reductions near 27% and lower direct operating costs (DOC) by over spoilers are discussed. Aerodynamic nonlinearities and dead bands 21%. (Author) are described, scale effect problems shown, and a preliminary design method reviewed. Two-dimensional experimental data for single. and multi-element airfoils with spoilers is presented. Details of the wake A79-47921 # The aerial relay system - An energy-efficient behind a spoiler and spoiler induced tail buffet are discussed. solution to the airport congestion problem. A. C. Kyser (NASA, Computational results for an airfoil with deflected spoiler are Langley Research Center, Hampton, Va.), American Institute of presented. The separation of the turbulent boundary layer ahead of Aeronautics and Astronautics, Aircraft Systems and Technology the spoiler's hinge line and reattachment on the face of the spoiler, Meeting, New York, N.Y., Aug. 20-22, 1979, Paper 79-1865. 23 p. 7 and calculation of the flow around a multi-element airfoil with a refs. spoiler are discussed. (Author) The aerial relay system concept, which was developed as a means of exploiting inflight transfer, utilizing large 'cruise liner' A79-47926 3 Boundary layer control on wings using sound aircraft that fly continuously along their routes and dock periodical- and leading edge serrations, F. G. Collins (Tennessee, University, ly with short-haul 'feeder' aircraft for payload exchanges, is Tullahoma, Tenn.). American Institute of Aeronautics and Astro- discussed. The system employs two distinctly different kinds of nasitics, Aircraft Systems and Technology Meeting, New York, N. V., aircraft, one for takeoff and landing and one for cruising, with Aug. 20-22, 1979, Paper 79. 1875. Ii p. 25 refs. NSF Grant No. provisions for the routine inflight transfer of passengers, baggage, GK-42133. fuel, etc. The liner design consists of a module of 320 ft span and 80 Three techniques for improving the lifting characteristics of low ft chord with an 800 seat capacity and capable of cruising at 0.75 M, speed wings were experimentally examined in a wind tunnel, namely while the feeder is a relatively conventional short-haul transport leading edge serrations, external sound, and sound emitted through aircraft with a modified fuselage to accommodate special docking periodically spaced holes near the wing leading edge. Serrations and transportation operations. It is concluded that this concept increased the lift curve slope by 12% for an NACA 0015 airfoil and could alleviate present inadequacies in an extremely cost-effective 22% for an NACA 2412 airfoil (chord Reynolds numbers to 6 x 10 and fuel-efficient way, and could be expanded indefinitely to to the 5th). Drag was not measurably increased by the serrations. become a high-quality, high-capacity national system. C.F.W. Sound of certain frequencies emitted from periodically spaced holes could reattach stalled flow and suppress stall-flutter. External sound also improved the airfoil stall characteristics. (Author)

A79-47923 3 F-16 Avionics Intermediate Shop /AIS/ Interim Contractor Support initiatives. W. A. Moch (General Dynam- A79.47928 # Flow patterns and aerodynamic characteristics ics Corp. Fort Worth, Tex.). American Institute of Aeronautics and of wing with strake, L. Mou-Jie (Peking Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Meeting, New York, Astronautics, Peking, Communist China). American Institute of N. Y., Aug. 20-22, 1979, Paper 79-1868. 7 p. Aeronautics and Astronautics, Aircraft Systems and Technology The paper surveys the F-16 Avionics Interim Contractor Meeting, New York, N. V., Aug. 20-22, 1979, Paper 79-1877. 12 p. Support (AICS) and the Avionics Intermediate Shop (AIS) which it 14 refs. supports. Aspects of the AIS discussed include the maintenance Surface oil flow visualizations, force tests and pressure measure- concept, a hardware description, F-i 6 AIS integration testing, and an ments were conducted at low, transonic and supersonic speeds. Four F-16 AIS development/production plan. Attention is given to the flow types of a wing with strake at low speed have been found. The AICS background and program objectives which address the needs of surface flow is affected and controlled mainly by the formation, concurrent development and support in she face of such problems as development and breakdown of the strake vortices. The differences

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in flow patterns are reflected in the force and moment results. The An estimation algorithm for nonlinear transient operation of lift increment comes from the effect of the strake vortex not only on multivariable gas turbine engines was developed and evaluated. the inner panel but also on the outer panel. The causes of the Kalman methodology and model-mismatch compensation procedures nonlinear variation of the pitching moment and ways of reducing it were employed in defining the filtering logic. The estimation are discussed. The lift increment is decreased with an increase in algorithm was evaluated by application to noise-corrupted measure- Mach number at transonic speeds, primarily because the flow over ment data generated by a nonlinear digital dynamic F100/F401 the wing without strake changes from leading-edge separation to engine simulation. Estimation of unmeasurable as well as measurable leading-edge attached flow with shock-induced separation. An key engine variables from (1) nominal-engine data, (2( degraded. increase in the lift-drag ratio is due to the lift increase at low speed engine data, and (3) engine data with off-nominal noise statistics was and the drag decrease at supersonic speeds. (Author) evaluated. Results obtained indicate that the nonlinear estimation algorithm provides a viable approach to estimating key engine variables under realistic operating conditions. (Author) A79-47939 Predictive guidance for interceptors with time delays. C. Hecht (Aerospace Corp., Guidance Analysis Dept., El Segundo, Calif.) and A. Troesch (Southern California, University, A79-47959 Nonlinear decoupled control synthesis for Los Angeles, Calif.). In: 1978 Conference on Decision and Control, maneuvering aircraft S. N. Singh (Santa Maria, Universidade Federal, 17th, San Diego, Calif., January 10-12, 1979, Proceedings. Santa Maria, Brazil( and A. A. Schy (NASA, Langley Research New York, Institute of Electrical and Electronics Center, Flight Dynamics and Control Div., Hampton, Va.(. In: 1978 Engineers, Inc., 1979, p. 88-94. 5 refs. Contract No. Conference on Decision and Control, 17th, San Diego, Calif., F4701-77-C-0078. January 10. 12, 1979, Proceedings. New York, Predictive guidance equations for systems with time delays are Institute of Electrical and Electronics Engineers, Inc., 1979, p. developed using optimal control theory to obtain interceptor steering 360.370. 14 refs. gains. Previously, predictive guidance and proportional navigation, A control law for decoupling roll rate, angle of attack and which are essentially the same, employed a steering policy based on sideslip in rapid, nonlinear airplane maneuvers is derived. For instantaneous interceptor response. In this paper the time response simplicity, only moments caused by ailerons, rudder and elevator are of the interceptor is approximated by a linear first order time lag, considered, and control forces are neglected. Simulated responses of and the optimal steering gain is evaluated using a quadratic penalty the closed loop system, including the control forces, show that the function. The optimal control for interception is determined to be a neglected forces have no significant effects and that large, simultane- linear function of the predicted position error and the acceleration ous lateral and longitudinal maneuvers can be precisely performed. error. The gains are functions of only the time-to-go and the The violent divergences which occur in open-loop maneuvers of this interceptor time constant. An application with computer simulations type are eliminated by the decoupling. The control law showed little is included for interception of a non-maneuvering target. The sensitivity to 20 percent perturbation in three important stability simulations demonstrate a significant improvement of interceptor derivatives. (Author) performance using the optimum gains in comparison to the conven- tional gain of proportional navigation. (Author) A79-47960 Analytic redundancy for flight control sensors on the Lockheed L-1011 aircraft. E. Y. Shapiro and H. E. Decarli (Lockheed California Co., Burbank, Calif.(. In: 1978 Conference on A79-47943 Application of bifurcation analysis and catas- Decision and Control, 17th, San Diego, Calif., January 10. 12, 1979, trophe theory methodology /BACTM/ to aircraft stability problems Proceedings. New York, Institute of Electrical at high angles-of-attack. R. K. Mehra and J. V. Carroll (Scientific and Electronics Engineers, Inc., 1979, p. 371-376. 5 refs. Systems, Inc., Cambridge, Mass.). In: 1978 Conference on Decision The implementation and flight test results of an analytic- and Control, 17th, San Diego, Calif., January 10-12, 1979, Proceed- redundancy approach employing operational sensors to reconstruct ings. New York, Institute of Electrical and signals of failed sensors is described. This method evolves from the Electronics Engineers, Inc., 1979, p. 186. 192. 15 refs. Contract No. concept of Luenberger Observers. The system is intended for use in a N00014-76-C-0780. dual or triple redundant environment, and takes maximal advantage Aircraft dynamic behavior at high angles of attack is highly of all existing functional and dynamic relationships among the nonlinear and, in the past, there has been a lack of suitable variables sensed by dissimilar sensors. In this paper a brief discussion techniques for analyzing the global behavior of nonlinear systems. In on the use of Luenberger Observers as a means for the attainment of this paper, an approach based on bifurcation analysis and catastrophe analytic redundancy is provided. The structure and parameters of the theory methodology (BACTM( has been applied to specific jump, failed sensor signal - reconstructor is developed. Flight test data of the hysteresis and limit cycle phenomena such as roll-coupling, pitch-up, Lockheed L-101 1 aircraft are exhibited. (Author) wing rock, buffeting, departure and divergence. Four different aircraft have been considered for comparison purposes, and it has A79-47961 The enhancement of aircraft parameter identi- been shown how different types of instabilities and families of limit fication using linear transformations. K. S. Govindaraj and E. G. cycles arise as the control variables are varied. A complete representa- Rynaski (Calspan Advanced Technology Center, Buffalo, N.Y.). In: tion of the aircraft equilibrium and bifurcation surfaces is given in a 1978 Conference on Decision and Control, 17th, San Diego, Calif., nine-dimensional space consisting of velocity, roll rate, pitch rate, January 10-12, 1979, Proceedings. New York, yaw rate, angle-of-attack, sideslip angle, elevator, aileron and rudder Institute of Electrical and Electronics Engineers, Inc., 1979, p. deflections. The use of BACTM for understanding spin entry, spin 377.384. Research supported by Calspan Corp. prevention, spin recovery and stability augmentation at high angles An approach is developed to identify the equations of motion of of attack are also discussed. (Author( an aircraft using linear transformations. The equations of motion are transformed into the phase variable form, the identification is carried out in the phase variable domain and transformed back into the equations of motion form to get the stability and control derivatives. A79-47957 Estimation for advanced technology engines. This identification procedure is very useful for the identification of F. A. Farrar and G. J. Michael (United Technologies Research the stability and control derivatives of an aeroelastic airplane. The Center, East Hartford, Conn.(. In: 1978 Conference on Decision and accuracy of stability and control derivatives obtained through a Control, 17th, San Diego, Calif., January 10-12, 1979, Proceedings. phase variable transformation is verified by comparing the results of New York, Institute of Electrical and Electronics this procedure with the results obtained from the identification in Engineers, Inc., 1979, p. 342-347. 8 refs. Contract No. the equations of motion form for the same data on the USAF Total N00014-76-C-0710. In-Flight Simulator (TIFS(. The phase variable method of identifica.

611 A79-47962 tion was felt to yield results as accurate as the results obtained from The singular perturbation theory (SPT( approximation of the identification in the equations of motion form. (Author) optimal feedback control laws is presented and methods for on-line application of these approximations are discussed. It is demonstrated that SPT control laws break down when the current state is near the A79-47962 • A multiple objective optimization approach to terminal target state. The use of continuation methods to improve - aircraft control systems design. D. Tabak, A. A. Schy, K. G. Johnson the accuracy of the SPT approximation and to obtain global (NASA, Langley Research Center, Hampton, Va.), and D. P. Giesy solutions of two-point boundary value problems is also discussed. As (NASA, Langley Research Center; Vought Corp., Hampton, Va.). In: an illustration, consideration is given to the minimum-time control of 1978 Conference on Decision and Control, 17th, San Diego, Calif., a supersonic aircraft for a three-dimensional intercept problem. B. J. January 10. 12, 1979, Proceedings. New York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. 385, A79-48000 Digital adaptive control laws for VTOL air- 386. craft. G. L. Hartmann and G. Stein (Honeywell Systems and The design of an aircraft lateral control system, subject to Research Center, Minneapolis, Minn,(. In: 1978 Conference on several performance criteria and constraints, is considered. While in Decision and Control, 17th, San Diego, Calif., January 10-12, 1979, the previous studies of the same model a single criterion optimiza- Proceedings. New York, Institute of Electrical tion, with other performance requirements expressed as constraints, and Electronics Engineers, Inc., 1979, p. 1103, 1104. Contract No. has been purejed, the current approach involves a multiple criteria NAS1-14921. optimization. In particular, a Pareto optimal solution is sought. Honeywell has designed a digital self-adaptive flight control (Author) system for flight test in the VALT Research Aircraft (a modified CH-47). The final design resulted from a comparison of two different A79-47971 Failure detection in signal processing and adaptive concepts: one based on explicit parameter estimates from a sensing in flight control systems. R. Onken and N. Stuckenberg real-time maximum likelihood estimation algorithm and the other (Deutsche Forschungs. und Versuchsanstalt fur Luft- und Raumfahrt, based on an implicit model reference adaptive system. The two Institut für Flugführung, Braunschweig, West Germany). In: 1978 designs are compared on the basis of performance and complexity. Conference on Decision and Control, 17th, San Diego, Calif., B.J. January 10. 12, 1979, Proceedings. New York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. 449.454 A79-48051 A novel technique for obtaining aerodynamic For the signal processing part of a flight control system a data using simple, free flight trajectory measurements. R. L. Pope definition of the system integrity function is given in order to enable and R. E. Dudley (Weapons Research Establishment, Salisbury, comparative evaluation of different design approaches with respect Australia). Aeronautical Journal, vol. 83, June 1979, p. 224-229. 6 to the system integrity and mission survival. Two main failure refs. detection methods are analytically investigated, the passive failure A free flight testing technique for missiles is presented, together detection. and the selfdiagnosing active failure detection. For the with the results of a preliminary test. The technique consists of firing tensing part of a flight control system a sensor failure detection and a projectile across a field and monitoring the trajectory with three elimination concept is presented, based on doubled sensors and ballistic cameras sited downrange. The simplicity and low cost are deterministic observers. This system equals the fail-operational stressed, noting that the output from the experiments repays the properties of a triplex-system. (Author) resources used to carry Out the trial and data analysis. It is concluded that results from the initial test of the trial technique and the data A79-47987 # Estimation of aircraft target motion using analysis show that the method is feasible and accurate estimates of pattern recognition orientation measurements. J. D. Kendrick (USAF, Technical Applications Center, Patrick AFB, Fla.), P. S. aerodynamics parameters can be obtained. M.E.P. Maybeck, and J. G. Reid (USAF, Institute of Technology, Wright- Patterson AFB, Ohio). In: 1978 Conference on Decision and Control, 17th, San Diego, Calif., January 10 . 12, 1979, Proceedings. A79.48052 Aircraft longitudinal motion at high incidence. New York, Institute of Electrical and Electronics A. W. Babister (Glasgow, University, Glasgow, Scotland). Aeronauti- Engineers, Inc., 1979, p. 953.959. 16 refs. ca/Journal, vol. 83, June 1979, p. 230-232. A new approach to estimating motion of a highly maneuvering The paper studies longitudinal symmetric motion of constant aircraft target in an air-to-air tracking scenario is presented. An speed and height and determines simple control laws for an autopilot interactive filter system is developed which provides an improved which would prevent a superstall occurring. An equation is presented estimate of target motion states by conditioning kinematic filter for pitching motion and analysis with fixed elevator and T-tailed estimates upon target aspect angle data. Pattern recognition tech- aircraft is made. Finally, the prevention of superstalled flight is niques used with an electro-optical tracker are presumed to provide discussed and it is concluded that a simple 5 linear feedback control this target aspect information. A target orientation filter processes can be used to prevent superstalled flight. M.E.P. the aspect angle measurements by statistically weighting measured aspect angles with the current best estimate of target kinematics. The A79-48311 # Handbook on aircraft materials and their aerodynamic lift equation is used to relate approximate angle of application technology (Spravochnik p0 aviatsionnym materialam i attack to target velocity and acceleration. A novel statistical model tekhnologii ikh primeneniia). V. G. Aleksandrov and B. I. Bazanov. for aircraft target normal acceleration is also developed to better Moscow, Izdatel'stvo Transport, 1979. 263p. 18 refs. In Russian. represent unknown target accelerations. Simulation results of The handbook covers characteristics and properties of steels, realistic three-dimensional scenarios are presented to evaluate the nonferrous materials, bearings, plastics, adhesives, elastomeric and performance of the interactive filter system. (Author) textile materials, and leather. Sealing and gasketing materials, fuel filters, varnish coatings, fuel, lubricants, and hydraulic fluids are A79-47991 Application of singular perturbation tech- covered. Various materials used in aircraft and safety methods are niques ISPT/ and continuation methods for on-line aircraft trajectory described. A.T. optimization. R. B. Washburn, R. K. Mehra, and S. Sajan (Scientific Systems, Inc., Cambridge, Mass.). In: 1978 Conference on Decision A79.48495 Influence of gas turbine engine combustion and Control, 17th, San Diego, Calif., January 10 . 12, 1979, Proceed- chamber geometric parameters on mixture formation characteristics. ings. New York, Institute of Electrical and P. P. Grigorenko, lu. A. Spiridonov, and A. V. Talantov, (Aviatsion- Electronics Engineers, Inc., 1979, p. 983-990. 13 refs. Contract No. naia Tekhnika, vol. 21, no. 3, 1978, p. 30-37.) Soviet Aeronautics, NAS1-151 13. vol. 21, no. 3, 1978, p. 20-24. 6 refs. Translation.

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In the experiments described, the mixing of hot gas jets injected A79-48505 Analysis design of complex systems. II, T. K, into a cross-flow of cold air was studied as a function of some Sirazetdinov and A. I. Bogomolov. (Aviatsionnaia Tekhnika, vol. 21, chamber parameters. It is shown that the flow rate increases and the no. 3, 1978, p. 85-91.) Soviet Aeronautics, vol. 21, no. 3, 1978, p. quality of mixing improves when the mixer aperture and number of 61-65. 16 refs. Translation. holes is increased. A diagram is proposed for selecting optimal mixer In the present paper, the problem of analytically designing parameters with respect to the minimization of temperature-field complex systems is formulated and is placed in proper perspective nonuniformity. V. P. with respect to the general process of systems design. An approach, based on control theory, is proposed to the analytical designing of complex systems. The application of this approach is demonstrated by examples. V. P. A79-48497 On the question of selecting the characteristic quantity governing fuel self-ignition in a stream. V. N. Gruzdev, N. A. Malishevskaia, and M. D. Tavger. (Aviatsionnaia Tekhnika, vol. 21, no. 3, 1978, p. 42-45.) Soviet Aeronautics, vol. 21, no. 3, 1978, p. 28-30. Translation. A79-48507 Experimental study of the turbulent wake In the experiments described, the self-ignition of kerosene TS-1 downstream of a fan jet, 0. A. Khachaturian, (Aviatsionnaia in a flow of nonequilibrium combustion products was studied to Tekhnika, vol. 21, no- 3,1978, p. 100-107.) Soviet Aeronautics, vol. determine the degree to which the ignition delay characterizes the 21, no. 3, 1978, p. 72-77. 10 refs, Translation. process as a whole. The ignition time is found to decrease with The velocity and temperature distributions in developing wakes increasing flow temperature and increasing density of active centers. of fan-shaped lets were studied in a cylindrical wind tunnel. It is It is proposed to use she critical flow velocity (which forms the shown that the wake flow is analogous to the wake behind bluff upper bound of the possible range of self-ignition) as the criterion of bodies of revolution. Relations for calculating the temperature and self-ignition. V. P. velocity in any wake cross section from the initial parameters of a fan-shaped jet are proposed. V. P.

A79.48498 Experimental study of the gasdynamic charac- teristics of a stator cascade with cooling air discharge through the vane surface. 0. N. Emin, I. I. Kutysh, and P. I. Shvartsman. A79.48517 Long-life GTE operation based on technical (Aviatsionnaia Tekhnika, vol. 21, no. 3, 1978, P. 46-53.) Soviet condition. A. A. Mukhin, A. A. Kovalev, and A. A. Kornoukhov. Aeronautics, vol. 21, no. 3, 1978, p. 31-36. 8 refs. Translation. (Avmatsionnaia Tekhnika, vol. 21, no. 3, 1978, P. 153-156,) Soviet Aeronautics, vol. 21, no. 3, 1978, p. 116-118. Translation. The service life of a gas-turbine engine depends primarily on the endurance of the turbine blades, which depends on the gasdynamic and centrifugal stresses, the nonuniformity of the temperature field, A79.48500 Determination of turning angle of a jet the gas temperature, the atmospheric conditions, and seasonal impinging on a bucket with visor. L. M. Kotliar, S. G. Margulis, and effects. In the present paper, the endurance of first-stage blades E. D. Nesterov. (Aviatsionnaia Tekhnika, vol. 21, no. 3, 1978, p. prepared from ZhS6KP alloy is analyzed for the actual operating 58-62.) Soviet Aeronautics, vol. 21, no. 3, 1978, p. 40-43. 6 refs. conditions of a modern long-range airliner, involving temperature Translation. variations ranging from -55 to +45 C and pressure variations from The flow inside a symmetrical target-type thrust reverser is 725 to 775 torr. Methods of evaluating the technical state of turbine analyzed under the assumption of an imponderable fluid. The blades are discussed. V. P. reverser ejection angle is calculated by Chaplygin's method of singular points. A technique for determining the ejection angle as a function of the deflector parameters is proposed. V. P. A79.48518 Use of the method of variable directions for numerical study of the temperature states of a turbine disk with blades. A. M. Poliakov, V. S. Petrovskii, and V. I. Krichakin. A79-48501 Most rational linearization of nonlinear un- (Aviatsionnaia Tekhnika, vol. 21, no. 3, 1978, P. 156-160.) Soviet steady heat conduction problems. N. L. Men'shikh. (Aviatsionnaia Aeronautics, vol. 21, no. 3, 1978, p. 119-122. Translation. Tekhnika, vol. 21, no. 3, 1978, p. 63-67.) Soviet Aeronautics, vol. In the present paper, an economical scheme of integrating over 21, no. 3, 1978, p. 44.47. 5 refs. Translation. two space variables is applied to the solution of the unsteady-state A proof is obtained for the correspondence between nonlinear thermal problem for an axial-flow turbine disk with blades having and linearized unsteady heat-conduction problems from the point of elongated roots. The problem is reduced to a system of two- view of similarity theory. This correspondence is used as a basis to dimensional unsteady-state heat equations for the blades and disk. develop a 'most rational' method of linearizing nonlinear unsteady The disk profile is defined by means of arbitrary functions which heat conduction problems, owing to a dependence of the thermo- delimit the contour of the lateral surfaces. By means of linear- physical properties on the temperature and radiant transfer. The fractional transformation, the curvilinear contour of the disk is method is illustrated by some practical examples. V. P. transformed into a rectangle. The problem then can be solved for coupled rectangular blade and disk regions connected by the boundary conditions. V. P.

A79.48503 On the influence of relative pitch in the subsonic turbine cascade. V. G. Nesterenko and G L. Podvidz. A79.48519 Characteristics of afterburning bypass turbojet (Aviatsionnaia Tekhnika, vol. 21, no. 3, 1978, p. 75-80.) Soviet engine with oxygen injection into the afterburner chamber. B. D. Aeronaujçs vol. 21, no. 3, 1978, p. 53-56. 8 refs, Translation. Fishbein, (Aviatsionnaia Tekhnika, vol. 21, no. 3, 1978, p. 160-164.) The influence of varying the pitch/chord ratio from 0.8 to 1.5 Soviet Aeronautics, vol. 21, no. 3, 1978, p. 123-126, 6 refs. on the performance of a subsonic cascade of turbine airfoils is Translation. analyzed for large flow angles. The flow of an ideal compressible In the present paper, the thermodynamic effectiveness of thrust fluid in the aperture between two blades is calculated and compared augmentation by supplying oxygen to the afterburner of a turbojet with the experiment. Two types of separated flow are identified bypass engine is calculated for various modes of flight. The which may arise at pitch/chord ratios above the critical value. V. P. thermodynamic characteristics of air, air-oxygen mixtures, and

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combustion products of kerosene in air and in air-oxygen mixtures Present-day UHF airborne communications links are susceptible are tabulated. It is shown that for minimum excess oxidant to jamming interference. Frequency hopping, spread spectrum (air-oxygen) ratio, an oxygen supply of 10 to 20 percent of the rate signals, and adaptive antenna arrays are among the methods that can of airflow results in thrust augmentation by factors of 1.18 to 1.2 at be used to provide antijamming capabilities. The adaptive antenna M = 0, and by factors of 1.8 to 2.2 at M = 3.2. The total specific fuel approach is the only one that can be implemented without replacing consumption increases by factors of 2.4 to 4.4 at M = 0, and by or modifying the existing UHF radios. The requirements, tradeoffs, factors of 2.0 to 2.8 at-M = 3.2. V. P. and hardware configurations involved in an adaptive array design are discussed. S. D.

A79-48602 Preprocessing for advanced image matching techniques. J. E. Berry and J. K. Yoo (Goodyear Aerospace Corp., Akron, Ohio). In: NAECON 1979; Proceedings of the National A79-48572 Aerodynamic excitation forces of blade vibra- Aerospace and Electronics Conference, Dayton, Ohio, May 15.17, tions in axial Wrbomahinery as a result of interference from nearby cascades (Aerodynamische Erregungskrafte von Schaufelschwing- 1979. Volume 1. New York, Institute of Electrical and Electronics Engineers, Inc., 1979, ungen in axialen Turbomaschinen infolge der lnterferenz benachbar- p. 86-91. Grant No. DAAK40-77-C-0107. tar Schaufelgitter). W. Lienhart. Ingenieur.Archiv, vol. 48, no. 4, Preprocessing that enables accurate matching of two images 1979, p. 239-258. 17 refs. In German. The paper presents the calculation of the unsteady blade forces taken by range measuring sensors located at different points in space and moments caused by the interaction of adjacent cascades by and at different times is presented. Separation between the sensors means of an approximation of incompressible plane unsteady results in perspective changes that appear as geometric distortion. potential flow. The results of vibration stimuli for a number of There are also variations in image element intensities as a result of changes in position and time. The preprocessing used to remove double cascade configurations are presented as examples. Attention position dependent distortion and to circumvent the effect of is given to the influence of the axial clearance between the cascades, intensity variations are described. This includes descriptions of the of the profile shape, of the different pitches of adjacent cascades, sensor data format, the rationale for the preprocessing approach and and of the ratio of peripheral speed to isentropic stage velocity. transformations used to implement the approach. Examples compar- Finally, a simple formula is given for the influence of axial clearance ing images before and after preprocessing are shown. between the blade rows. M.E.P. (Author)

A79.48603 Synthetic aperture radar map matching for navigation. E. R. Hiller (Raytheon Co., Missile Systems Div., 479-48596 Multiband antenna. F. W. Vortmeier Bedford, Mass.). In: NAECON 1979; Proceedings of the National (McDonnell Aircraft Co., St. Louis, Mo.). In: NAECON 1979; Aerospace and Electronics Conference, Dayton, Ohio, May 15-17, Proceedings of the National Aerospace and Electronics Conference, 1979. Volume 1. New York, Institute of Dayton, Ohio, May 15-17, 1979. Volume 1. New Electrical and Electronics Engineers, Inc., 1979, p. 92-100. Contract York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. No. F04701-76-C-0002. 35.42. Contract No. N62269-77-C-01 38. The location of preselected features in synthetic aperture radar With the introduction of a new generation of radio communica- (SAR) images by map matching with reference templates can provide tion equipment which is capable of operating at VHF-FM (30-76 fix data for navigation. A procedure- for map matching has been MHz), VHF-AM (108. 156 MHz) and UHF (225-400 MHz) from a developed that encodes the reference feature shape in a binary single radio unit, the requirement existed to develop an antenna to reference template which is utilized to provide an adaptive normali- match this capability. Such an antenna was developed for conformal zation and slicing of the radar image, followed by simple binary mounting on tactical Naval aircraft with the approach being to add correlation. The procedure offers a significant reduction in computa- capability to an existing antenna. This makes it possible to provide tional complexity compared to traditional cross correlation pro- with one antenna the capability formerly provided with two or three cessing and has the capability to acquire reference features with high antennas. This paper describes the work performed, the successful probability in the presence of other competing features. Analysis of results obtained and substantiating data. Data measured consisted of the theoretical performance characteristics of this map matching impedance measurements on a full scale model, pattern measure- procedure is presented. Examples of results obtained with the ments of fourth and fifth scale models, power measurements and procedure utilizing SAR imagery are also included. (Author) gain comparison measurements. (Author) A79.48606 Microcomputer applications in strapdown 479-48597 Small lightweight electronically steerable heading and attitude reference system. A. Halamandaris and E. N. cylindrical antenna successfully utilized in an air traffic management Jackson (Litton Industries, Guidance and Control Systems Div., system. J. A. Acoraci (Bendix Corp., Communications Div., Balti- Woodland Hills, Calif.). In: NAECON 1979; Proceedings of the more, Md.). In: NAECON 1979; Proceedings of the National National Aerospace and Electronics Conference, Dayton, Ohio, May Aerospace and Electronics Conference, Dayton, Ohio, May 15-17, 15-17, 1979. Volume 1. New York, Institute of 1979. Volume 1. New York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. 145.151. Electrical and Electronics Engineers, Inc., 1979, p. 43-49. Grant No. Recent developments in LSI technology have made a very DAAB07-77-C-2 176. dramatic change in the digital system design of an all-attitude Bendix Communications Division has designed, fabricated and strapdown heading and reference system. With the advent of tested a brassboard model lightweight electronic scan interrogator microcomputers it is now possible to design a system with antenna for use in air traffic management. The antenna is a Butler distributed processing techniques. The purpose of this paper is to matrix-fed multimode electronically scanned cylindrical array. A present the design approach of two microcomputer controlled brief description of the total system and a detailed technical modules within the Litton Heading Attitude Reference System description of the antenna are presented. S. D. (HARS). The HARS is a single unit containing inertial sensors, instrument support electronics, BITE electronics, power supply, 479-48598 Adaptive array tradeoffs for existing airborne system I/O electronics and distributed microcomputers. (Author) UHF radios. D. A. Sweeney )E-Systems, Inc., St. Petersburg, Fla.). In: NAECON 1979; Proceedings of the National Aerospace and Electronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 1. New York, Institute of Electrical and Electronics A79.48608 # Microprocessor-based digital autopilot devel- Engineers, Inc., 1979, p. 50-57. opment for the XBQM. 106 Mini-RPV. 0. D. Koger, D. E. Tietz, and

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G. B. Lamont (USAF, Institute of Technology, Wright-Patterson AFB, Ohio). In: NAECON 1979; Proceedings of the National AFB, Ohio). In: NAECON 1979; Proceedings of the National Aerospace and Electronics Conference, Dayton, Ohio, May 15-17, Aerospace and Electronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 1. New York, Institute of 1979. Volume 1. New York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. 237-245. Con- Electrical and Electronics Engineers, Inc., 1979, p. 157-167. 52 refs. tract No. F33615-78-C-2018. Contemporary integrated circuit technology permits the em- This paper presents the Phase I results of a two phase study ployment of microprocessors in the design of small remotely piloted program which addresses the integration of advanced power system vehicles. The development of a microprocessor based autopilot for control technologies into a reliable and fault tolerant system. The the XBOM-106 Mini-Remotely Piloted Vehicles (RPV) is described in advanced control technologies integrated include electric engine this paper. With ultra-low component cost as a primary goal, the start, automatic load management, microprocessor control imple- autopilot design uses the RCA CDP-1802 microprocessor. The digital mentations, design techniques for providing 'no-gap' power and an all autopilot was developed through the breadboard state with perfor- 'solid state' electric power distribution system. Electric system mance testing accomplished via hybrid simulation. Aircraft transfer performance requirements are established and preliminary designs of functions were first derived from aerodynamic wind tunnel data. an integrated 'baseline' control system for single and a multiengine Then a complete control analysis was made of the existing analog aircraft for the 1990 operational time period are presented. Finally, autopilot, sensors, actuators, and aircraft dynamics. This was stability analysis requirements and procedures are established for followed by synthesis of the digital control algorithms from the each of the two designs. (Author) digitization of the analog control laws. Hardware was selected based on system requirements, and software to execute the digital A79-48615 Advanced RPV electrical systems. F. L. Miller algorithms was developed. The results of testing by hybrid simulation (Teledyne Ryan Aeronautical, San Diego, Calif.). In: NAECON indicates that the performance of the digital autopilot is very 1979; Proceedings of the National Aerospace and Electronics comparable to the existing analog autopilot. Sources of minor Conference, Dayton, Ohio, May 15-17, 1979. Volume 1. discrepancies are discussed. (Author) New York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. 246-253. The paper surveys the'possible improvements that can be made in the electrical power systems (EPS) of remotely piloted vehicles A79-48609 A status report on the advanced FIREFLY )RPV). It is noted that off the shelf hardware, which is commonly assessment program. D. E. Longmire )Northrop Corp., Avionics used due to cost considerations, is becoming inadequate for the tasks Systems Analysis Dept., Los Angeles, Calif.). In: NAECON 1979; and is causing operational difficulties. Attention is given to the EPS Proceedings of the National Aerospace and Electronics Conference, design philosophy and some specific problems such as the lack of New Dayton, Ohio, May 15-17, 1979. Volume 1. adequate generated power, interconnection difficulties, reliability York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. and maintainability problems such as those associated with batteries 170-175. and high life cycle costs. Several types of RPVs are described such as FIREFLY studies have shown the potential for significant the HALE RPV, the mini RPV, and the TEDS. Technological increases in aircraft effectiveness and survivability offered by improvements considered include: rare earth permanent magnets, flat integration of the fire and flight control functions during weapons wire and printed Circuit cable, and fiber optics. M.E.P. delivery. A modularized characterization of an integrated fire/flight control system eliminates the costly and extensive analysis that has A79-48616 Electrical power system for new-technology heretofore resulted from conventional, separate, fire and flight transport power-by-wire airplane. E. T. Reiquam (Boeing Aerospace control logic. FIREFLY has as its primary goal the design, Co., Seattle, Wash.). In: NAECON 1979; Proceedings of the National development and utilization of a digital simulation of such an Aerospace and Electronics Conference, Dayton, Ohio, May 15-17, integrated fire/flight control system that would yield meaningful 1979. Volume 1. New York, Institute of tactical versatility when used for the analysis and evaluation of a Electrical and Electronics Engineers, Inc., 1979, p. 254-261. specific aircraft and weapon. )Author) A design of the electrical power system for a new-technology aircraft in which the electrical system is the only secondary power system extracting power from the engines is presented. All flight A79-48610 Multisensor integration for defensive fire con- control surface actuation is accomplished by electro-mechanical trol surveillance. C. L. Bowman )VERAC, Inc., San Diego, Calif.). In: actuators and hydraulic systems are eliminated. The air conditioning NAECON 1979; Proceedings of the National Aerospace and Elec- system prime mover is an electric motor that drives a bootstrap tronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 1. air-cycle pack which permits more efficient engine shaft power New York, Institute of Electrical and Electronics extraction than less efficient bleed air extraction. The power Engineers, Inc., 1979, p. 176-184. 8 refs. Contract No. generation system has quadruple redundancy established for the F33616-78-C-1576. flight control system. Power for the flight control actuator system is This paper develops a multisensor integration )MSI) concept for at 270 V dc and avionics, lighting, engine controls, and instrumenta- defensive fire control surveillance. Multisensor, multitarget, maxi- tion are powered from 115/200 V 400-Hz, 28 V 400-Hz, and 28 V mum likelihood track correlation and minimum variance MSI track dc buses. A.T. filtering algorithms are designed. Due to computational and timing requirements, as well as system reliability and flexibility considera- A79-48617 E-413 mission electrical power. M. E. tions, sensor-level track files are selected to provide the measure- Kleinmann and A. A. Stewart (Boeing Co., Seattle, Wash.). In: ments for MSI algorithms. The benchmark algorithm derivations NAECON 1979; Proceedings of the National Aerospace and Elec- therefore differ from those standard in the multitarget tracking tronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 1. literature, because of the autocorrelations in the track file errors New York, Institute of Electrical and Electronics which arise from she sensor track filters. Candidate suboptimal MSI Engineers, Inc., 1979, p.262-269. algorithms are derived in accordance with the sensor characteristics An overview of the mission power distribution system designed and tracking requirements of a high energy laser )HEL) fire control. for the E-4B version of the Boeing 747 aircraft is presented. The (Author) requirements and criteria established for mission power distribution are given along with a general description of the system, including interfaces with the basic 1200-kVA electrical power generation system The E-413 power system is characterized by the ability to A79.48614 Electric power system control techniques. J. automatically shed selected mission loads in the event that multiple R. Perkins, D. E. Lautner, A. J. Marek (Vought Corp., Dallas, Tex.), generator failures require a reduction in load. Mission power and D. Fox )USAF, Aero Propulsion Laboratory, Wright-Patterson distribution control and monitoring is provided at the mission

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technical control station. From this station 32 dedicated-load and Corp., Bethpage, N.Y.). In: NAECON 1979; Proceedings of the general-purpose mission buses are controlled, and their status National Aerospace and Electronics Conference, Dayton, Ohio, May monitored. The system also provides 28-V dc; 10-V dc; and 115-V. 15-17, 1979. Volume 1. New York, Institute of single-phase, 60-Hz power to mission loads throughout the plane. Electrical and Electronics Engineers, Inc., 1979, p. 311-318. 8 refs. V.T. The ASSET (Advanced Skewed Sensory Electronic Triad) system flight test configuration consists of two sets of six skewed rate sensors. One set consists of conventional spring-restrained rate A79-48618 Digital simulation of a three-phase generator. gyros, while the other is composed of vibrating beam rate sensors. P. J. Leong and I. S. Mehdi (Boeing Aerospace Co., Seattle, Wash.). Flight test results are presented for a redundant arrangement of In: NAECON 1979; Proceedings of the National Aerospace and skewed angular rate sensors and associated failure detection and Electronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 1. isolation algorithms designed for digital fly-by-wire control applica- New York, Institute of Electrical and Electronics tions. The separation of the sensors in the skewed array demonstrat- Engineers, Inc., 1979, p. 270-278. ed the concept of survivability through sensor separation. The A technique is presented for dynamically modeling a brushless redundancy data management software demonstrated that computer three-phase ac generator on a digital computer. A simplification in technology can reliably perform isolation and signal selection which the mathematical description of the generator is obtained by using can be processed within the iteration time constraints of aircraft the Park's transformation which defines a new set of variables in control laws. Specific conclusions are drawn. S. D. terms of the actual winding variables. The model equations are set up in the state-space method and the flux linkages are the state A79-48623 variables. One of the problems encountered in the digital simulation A microprocessor system for flight control of synchronous generators is the determination of saturation. In this research. J. C. Seat (USAF, Williams AFB, Ariz.), G. E. Miller, and R. F. Stengel (Princeton University, Princeton, N.J.). In: NAECON model, a table lookup routine handles the nonlinear saturation 1979; Proceedings of the National Aerospace and Electronics effect. The equations describing the generator also cover the rotating Conference, Dayton, Ohio, May 15-17, 1979. Volume 1. exciter. The generator model is part of a complete system simulation of an aircraft generating system. The simulation determines stability New York, Institute of Electrical and Electronics Engineers, Inc., 1979, and power quality during steady-state and transient operating p. 319-326. Contract No. N00014-78-C-0257. A digital flight control system based on microprocessor tech- conditions. (Author) nology has been designed, developed, and flight tested in Princeton's Variable-Response Research Aircraft (VRA). The Micro-DFCS works A79-48620 # Avionics computer software operation and in conjunction with the VRA's existing fly-by-wire control system, support cost estimation. D. V. Ferens and R. L. Harris (USAF, and it is programmed to provide command and stability augmenta- Avionics Laboratory, Wright-Patterson AFB, Ohio). In: NAECON tion control laws formulated through modern Control theory. The 1979; Proceedings of the National Aerospace and Electronics Model 1 Micro-DFCS hardware and software are described, and Conference, Dayton, Ohio, May 15-17, 1979. Volume 1. initial flight test results are presented. (Author) New York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. 296-300. 9 refs. This paper describes many current models and methods available for predicting computer software operational and support costs and A79-48625 # Synthesis of digital flight Control tracking discusses she limitations of available models and methods as useful systems by the method of entire eigenstructure assignment. J J. tools. This paper also discusses in detail the Air Force Avionics D'Azzo and T. A. Kennedy (USAF, Institute of Technology, Laboratory's current effort to develop a model that will help the Wright-Patterson AFB, Ohio). In: NAECON 1979; Proceedings of the engineer or cost analyst accurately predict operational and support National Aerospace and Electronics Conference, Dayton, Ohio, May costs of avionics systems computer software being maintained at Air 15-17, 1979. Volume 1. New York, Institute of Electrical and Electronics Engineers, Inc., 1979, Force Air Logistics Centers. (Author) p. 343-347. 12 refs. The paper is concerned with the use of entire eigenstructure assignment (Moore, 1976; D'Azzo, 1978) in the synthesis of tracking A79-48621 Built in test of AID converters - Present systems which are •required to track a command input vector approaches and recommendations for improved BIT effectiveness. R. containing piecewise constant signals. The method is demonstrated J. McCabe (Westinghouse Electric Corp., Baltimore, Md.). In: by application to a digital aircraft flight control system required to NAECON 1979; Proceedings of the National Aerospace and Elec- produce a constant climb rate at constant velocity. The controllable tronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 1. system is represented in the continuous-time domain by linear New York, Institute of Electrical and Electronics multivariable matrix state and output equations. S. D. Engineers, Inc., 1979, p. 301-307. This paper treats the problems of developing effective BIT A79-48629 Analysis and evaluation of current MIL-STD- approaches for A/D converters to be used in airborne radar systems, 1553 digital avionics architecture as the basis for advanced architec- and recommends new directions for improving the effectiveness of tures using MIL-STD-1553B. C. R. Turner and M. B. McCall (Boeing A/D BIT. Present A/D approaches are comprised of one or more of Aerospace Co., Seattle, Wash.). In: NAECON 1979; Proceedings of three basic types of BIT: critical circuit verifications, end-to-end the National Aerospace and Electronics Conference, Dayton, Ohio, system level tests, and front-to-back hardware level tests. Each of May 15-17, 1979. Volume 1. New York, these approaches is described and the merits and shortcomings of Institute of Electrical and Electronics Engineers, Inc., 1979, p. each approach are summarized. New requirements for processing of 426-432. radar target data and the introduction of new hardware technologies This paper is presented in two major sections. The first section motivate a shift toward hardware level A/D BIT. Recommendations presents a comparison of current MIL-STD-1553 multiplex systems. for improved BIT effectiveness are given, and include improved test These systems are compared as to their application areas, architec- parameters, microprocessor-based measurement techniques, and fur- tures and system control approaches. The second section is a ther development of A/D system modeling techniques. (Author) discussion section which presents the conclusions drawn from our study of current systems, as well as presenting areas identified as needing further study. The areas discussed are: problems of A79-48622 Flight test verification of the ASSET system. MIL-STD-1553(USAF) and MIL-STD-1553P, which were solved by S. T. Donley (U.S. Naval Material Command, Naval Air Development -15538, predicting the future from the past, what advances are Center, Warminster, Pa.) and R. D. Solomon (Grumman Aerospace needed, and what the payoff is. (Author)

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A79-48630 F/A.18 Hornet display system. R. A. Juergens The paper summarizes existing military standards and Air Force (McDonnell Aircraft Co., St. Louis, Mo.). In: NAECON 1979; regulations applicable to both inhouse quality assurance (GA) efforts Proceedings of the National Aerospace and Electronics Conference, and independent verification and validation (V&V) activities. The Dayton, Ohio, May 15-17, 1979. Volume 1. New need for additional GA and V&V standards are discussed and some York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. potential standards are suggested. An effective software quality 434442 assurance plan describing the important parts of a developer's quality The F/A-i 8 cockpit display system consists of a Head Up assurance activities is described and the major sections of the plan are Display (HUD), two Multipurpose Display Indicators (MDIs(, and analyzed including scope, applicable documents, and organization. either a Multipurpose Display Repeater Indicator (MDRI) or a C.F.W. Horizontal Situation Display (HSD). The MDI, MDRI, and HUD were developed by Kaiser Electronics while the HSD was developed by Bendix/Ferranti. These four units provide an integrated display A79-48652 Power hybridization - Key to reducing avionics system with the functional redundancy necessary to provide a high power supply weight and volume. R. C. Newton, Jr. and D. G. Frey probability of mission success. Each MDI is able, under aircraft (Westinghouse Electric Corp., Baltimore, Md.). In: NAECON 1979; computer direction, to provide all necessary display information to Proceedings of the National Aerospace and Electronics Conference, itself and to either the MDRI/HSD, the HUD, or both. With the Dayton, Ohio, May 15-17, 1979. Volume 2. New exception of the optics, the HUD, HSD and MDRI are functionally York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. similar. Internally, the MDls consist of the MDRI modules plus a 698-703. processor comprised of an input/output (I/O) section, a central It is shown that the use of power hybrid packages (PHP) for display processor, and two independent but identical symbol both linear series regulators and switching power supplies results in generators. This paper discusses the display system organization and large savings in she system power supply weight (over 30 percent) details the processor operation. (Author) and volume (over 46 percent). The use of PHP technology has other advantages, such as improvements in reliability, producibility, and maintainability. It is apparent that the potential for commonality of the PHP building blocks is large for both linear and switching A79-48640 A simple integrated navigation based on mul- regulators. In addition, there is evidence to support the prediction tiple DME. U. Brokof (Deutsche Forschungs . und Versuchsaristalt fur that life cycle costs will be significantly reduced. V. P. Luft- und Raumfahrt, Institut für Flugfiihrung, Braunschweig, West Germany). (Deutsche Gesel/schaft für Luft- und Raumfahrt and Deutsche Gesel/schaft für Ortung und Navigation, Symposium über A79-48656 Low cost inertial aiding for NAVSTAR/GPS F/iegen im F/ugha fen- Nahbereich, Hamburg, West Germany, Apr. receivers in naval ship navigation. V. S. Sarnant, B. G. Gardner 24-26, 1979, DGLR Paper 79-041.) In: NAECON 1979; Proceedings (Orincon Corp., La Jolla, Calif.), and R. Akita (U.S. Navy, Naval of the National Aerospace and Electronics Conference, Dayton, Ordnance Systems Command, San Diego, Calif.(. In: NAECON 1979; Ohio, May 15-17, 1979. Volume 2. New York, Proceedings of the National Aerospace and Electronics Conference, Institute of Electrical and Electronics Engineers, Inc., 1979, p. Dayton, Ohio, May 15-17, 1979. Volume 2. New 591-599. 5 refs. Translation. York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. A simple integrated navigation system is described, consisting of 726-737. a dead reckoning system using the intrinsic velocity and the compass The paper considers the problem of accurately determining heading. The system is supported by range measurements to various position and velocity of naval ships using GPS signals. An extended DME ground stations by means of a Kalman filter. The state vector Kalman filtering algorithm was adequate for achieving 10 m and 0.2 contains, besides the elements for dead reckoning, the systematic rn/sec accuracies in ship position and velocity in the absence of errors of the ground stations. The operation of the system is disturbing sea motion, but this filter is divergent in moderate and discussed in the light of test flight results with an HFB 320. P.T.H. stormy sea-state environments. Inertial navigation configurations to measure the ship motion, algorithms for estimating the disturbance motion, and a disturbance motion compensation technique are A79-48641 Quaternion matching in transfer alignment for discussed. The disturbance sea motion estimates are used to SAR motion compensation. D. J. Schmidt and G. A. Bendor compensate GPS measurements to maintain the filter performance (Westinghouse Electric Corp., Baltimore, Md.). In: NAECON 1979; within desired limits, and was shown that actual at sea results Proceedings of the National Aerospace and Electronics Conference, confirmed the simulation results of velocity error sensitivities due to Dayton, Ohio, May 15-17, 1979. Volume 2. New sea motion. A. T. York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. 600-604. 15 refs. A79-48657 A real-time sequential filtering algorithm for The paper presents the initial results of an on-going study to GPS low-dynamics navigation system. T. N. Upadhyay (Charles Stark develop a system for motion compensation in SAR signal processing. Draper Laboratory, Inc., Cambridge, Mass.) and J. N. Damoulakis In the proposed configuration, a high cost, high performance, low (Texas Instruments, Inc., Dallas, Tex.). In: NAECON 1979; Proceed- data rate master IMU is located at a convenient vehicle station; also a ings of the National Aerospace and Electronics Conference, Dayton, low cost low performance, high data rate, strapdown slave IMU is Ohio, May 15-17, 1979. Volume 2. New York, located at a remote station. It is noted that despite structural Institute of Electrical and Electronics Engineers, Inc., 1979, p. deformation and large slave IMU errors, adequate accuracy is 739-749. 20 re/s. Contracts No. F04701-78-0181; No. achieved in the slave by Kalmanized transfer alignment with the F3361 5-78-C-1430. master. Finally, covariance analysis indicates that accelerometer This paper describes the design, implementation, and perfor- attitude matches (i.e., quaternion matches) are needed along with mance of a real-time estimation algorithm, referred to in this paper as other types of matches if slave strap'ilown inertial sensors of tactical the Sequential Piecewise Recursive )SPWR) algorithm, for the guidance quality are to be used in this application. M.E.P. Global-Positioning System )GPS( low-dynamics navigation system. The SPWR algorithm is based on the extended Kalman filter. It, however, differs from the conventional Kalman filter in that it A79.48648 The effect of standardization of avionics soft- computes error covariance and filter gains at a slower rate than the ware quality assurance. B. J. Rubey (Softech, Inc., Waltham, Mass.). state measurement update, and it uses U-D factor formulation to In: NAECON 1979; Proceedings of the National Aerospace and perform covariance computations. Thus, the SPWR algorithm saves Electronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 2. real-time processing requirements without appreciable degradation of New York, Institute of Electrical and Electronics filter performance, and it alleviates the numerical accuracy problems Engineers, Inc., 1979, p. 656-662. generally associated with the Kalman filter. Another important

617 A79-48664 feature of the SPWR algorithm is that it incorporates range and Avionics software and their support packages have progressed to range-rate data from each GPS satellite sequential for navigation the point where verification of onboard computations can be solution. Numerical results are presented. (Author) accomplished totally by computer simulation. A test method is proposed which provides dynamic inputs, via the off-line simulation, to a support software package capable of executing onboard code A79-48664 Radar signal processing development for appli- and comparing results of the onboard algorithms with anticipated cation of VHSI. J. D. Grimm and G. L. Bair (Texas Instruments, Inc., results. It is now possible to modify and verify onboard computa- Radar and Digital Systems Div., Dallas, Tex.). In: NAECON 1979; tions without the facilities of a software bench. Generation of the Proceedings of the National Aerospace and Electronics Conference, test inputs to the support software is achieved by a FORTRAN Dayton, Ohio, May 15-17, 1979. Volume 2. New program that uses a two-tier approach to simulate flight paths for an York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. interceptor and up to 10 maneuverable targets. After simulating the 796-805. onboard code, the FORTRAN interface routine gathers outputs of Advances in component technology leading to the development the operational flight program and returns to the upper tier. This of very high speed integration promise revolutionary progress in the allows accurate assessment of nonlinearities, parameter uncertainties, next decade of radar signal processing. The paper examines mission and modeling errors. S. D. requirements that place demands on future equipment design. To quantify future signal processing requirements, a baseline is estab- lished by describing a current developmental signal processor for an A79-48670 Computer Monitor and Control - A flexible, airborne coherent multimode radar. Operational requirements for cost-effective implementation. J. A. Rey and R. K. Thompson future processor development are outlined consistent with projected (Northrop Corp., Aircraft Group, Hawthorne, Calif.). In: NAECON mission capabilities. Signal processor parameters are derived from 1979; Proceedings of the National Aerospace and Electronics these operational requirements. Equipment mechanization to meet Conference, Dayton, Ohio, May 15-17, 1979. Volume 2. projected requirements is accomplished by developing architectures New York, Institute of Electrical and Electronics that lend themselves to application of revolutionary device tech- Engineers, Inc., 1979, p. 840-844. nology. (Author) This paper describes the Performance and Design Requirements Analysis for a test set, often referred to as a Computer Monitor and A79-48665 Millimeter airborne radar target detection and Control Unit )CMAC) to be used during verification and validation of selection techniques, L. M. Novak and F. W. Vote (MIT, Lexington, Operational Flight Programs )OFP) of Tactical Aircraft. Discussed Mass.). In: NAECON 1979; Proceedings of the National Aerospace are the requirements for data acquisition, methcds of capture and and Electronics Conference, Dayton, Ohio, May 15-17, 1979. post-processing of acquired data. The intent of this CMAC is to allow Volume 2. New York, Institute of Electrical and the test operator/OFP programmer to set a breakpoint, loop, Electronics Engineers, Inc., 1979, p. 807-817. 12 refs. USAF- monitor, trace, and otherwise test the OFP in its hosted environment DARPA-Army sponsored research. in real-time without any special test-oriented code within the OFP. A Results of a study of candidate target detection and selection specific case of an OFP host processor )AN/AYK-14) will be techniques for use in millimeter airborne radar systems are presented. discussed and its implementation with a laboratory software develop- Improved target and ground clutter models are developed and the ment situation, (Author) implications of these mathematical models on target detection and selection performance is discussed. (Author) A79-48666 A79-48671 Evolving methods for reducing avionics data in An analysis of SAPPHIRE image parameters as an AISF environment. C. Bierbaum )USAF, Air Logistics Center, a function of processing parameters. R. E. Morden (Goodyear Robins AFB, Ga.), M. Elowitz (TRW Defense and Space Systems Aerospace Corp., Litchfield Park, Ariz.) and R. L. With man )USAF, Group, Redondo Beach, Calif.), and J. Kennoy, Jr. (TRW Defense Aeronautical Systems Div., Wright-Patterson AFB, Ohio). In: and Space Systems Group, Warner Robins, Ga.). In: NAECON 1979; NAECON 1979; Proceedings of the National Aerospace and Elec- Proceedings of the National Aerospace and Electronics Conference, tronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 2. Dayton, Ohio, May 15-17, 1979. Volume 2. New New York, Institute of Electrical and Electronics York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. Engineers, Inc., 1979, p. 818-824. Contract No. F33657-74-C-0604. 845.852 SAPPHIRE (Synthetic Aperture Precision Processor, HIgh RE- The concept and scope of the F-15 data reduction and analysis liability) is a special-purpose digital processor capable of synthetic system (DRAS) are described. Attention is given to the avionics aperture processing of data from an AN/APD-10 coherent side- integration support facility (AISF) and its requirement for data looking radar at real-time rates with full resolution. The processor reduction, covering such areas as the DSS dynamic simulation was designed to perform a variety of parameter tradeoff experiments to aid in determining performance requirements for future systems. system, and flight test support aircraft. The DRAS concept discus- The paper presents an analysis of clutter return in imagery produced sion covers the software involved, a timeline summary, timeline by SAPPHIRE from two passes over a specified site, with special analysis, and a parameter listing. Finally, the DRAS state of development is described and the future evolution of the DRAS and emphasis on an analysis of radar image parameters as a function of the AISF is extrapolated. processing parameters. The two passes represent a moderate (16 deg) M.E.P. and a relatively low (5 deg) depression angle. The results compare measured clutter histograms with those predicted by theory and also compare two different methods of performing parameter tradeoffs. A79-48672 Microcomputer control of a test facility. J. A. S. D. Carretto, Jr. (USAF, Avionics Laboratory, Wright-Patterson AFB, Ohio). In: NAECON 1979; Proceedings of the National Aerospace and Electronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 2. New York, Institute of Electrical and A79.48667 Verification of operational flight programs by Electronics Engineers, Inc., 1979, p. 853-858. simulation. C. D. Williams and C. Nemec (Westinghouse Defense and The paper discusses a unique method of placing the data Electronic Systems Center, Baltimore, Md.). In: NAECON 1979; collection and processing equipment of a test facility under the Proceedings of the National Aerospace and Electronics Conference, control of a microcomputer. The specific facility is she AF Avionics Dayton, Ohio, May 15-17, 1979. Volume 2. New Laboratory's Mobile Evaluation Laboratory (MEL), a collection of York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. test and data processing equipment used in the evaluation of 826-828. navigation systems. The paper includes a general physical and

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functional description of the MEL, its development, and the Systems Center, Baltimore, Md.(. In: NAECON 1979; Proceedings of rationale for reorganizing the system under microcomputer control. the National Aerospace and Electronics Conference, Dayton, Ohio, The advantages of integrating the microcomputer as the system May 15-17, 1979. Volume 3. New York, controller are presented from both the hardware and software Institute of Electrical and Electronics Engineers, Inc., 1979, p. viewpoints. The modifications necessary for this are presented in 1033-1039. 9 refs. detail. Specific problems encountered, and their solutions are also A transfer alignment formulation is presented and illustrated by discussed. (Author) the nonrigid case with no unobstructed optical path between master and slave IMU, a full validation of the formulation is also presented. The approach is straightforward; only the interpretation requires some sophistication, since the formulation accounts for an extensive A79.48676 Operational experience with the AN/ARN-131 ft array of strapdown errors not often addressed explicitly in other Omega Navigation Set. H. W. Underwood and D. W. Keen (USAF, analyses. Aeronautical Systems Div., Wright-Patterson AFB, Ohio(. In: B.J. NAECON 1979; Proceedings of the National Aerospace and Elec- tronics Conference, Dayton, Ohio, May 15. 17, 1979. Volume 3. A79-48680 The alpha-beta-gamma tracking filter in the New York, Institute of Electrical and Electronics Z-domain. R. E. Wilcox (Emerson Electric Co., Electronics and Space Div., St. Louis, Mo.(. In: NAECON 1979; Proceedings of the Engineers, Inc., 1979, p. 1006-1013. The paper discusses (1) problems encountered in using the National Aerospace and Electronics Conference, Dayton, Ohio, May 15. AN/ARN-131 Omega Navigation Set on the C . 130 Hercules aircraft, 17, 1979. Volume 3. New York, Institute of (2) the Omega Task Group efforts, and (3) the subsequent follow-on Electrical and Electronics Engineers, Inc., 1979, p. 1042. 1046. 14 refs. test and evaluation results. It is found that fixes determined as a result of the Omega Task Group effort were effective. To date the The classic linear third order tracking filter also known as the fixes which have been approved for implementation by the Air Force alpha-beta-gamma filter will track an accelerating target with a are antenna relocation, minimum/maximum range deselect, 15-deg position error which converges to zero. If this filter is implemented angular deselect, modal interference deselect, and 5-min wind time in the digital domain, then solutions for the filter output as a constant. B.J. function of time must be carried out in the Z . transform formalism not using she continuous s or Laplace transform approach. This paper studies the linear third order tracking filter in the Z-domain A79-48677 The DG-800 - A rugged, high performance with the objective of deriving and documenting the general solutions heading reference unit. D. A. Zomick and M. J. Lanni (Bendix Corp., for the estimated position, position rate and position acceleration Guidance Systems Div., Teterboro, N.J.(. In: NAECON 1979; outputs as functions of modeling parameters. An algorithmic outline Proceedings of the National Aerospace and Electronics Conference, is presented for calculating the noise bandwidths for the filter Dayton, Ohio, May 15. 17, 1979. Volume 3. New outputs and the paper includes a numerical example describing the York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. tracking of an incoming accelerating aircraft. (Author) 1015-1022. A directional gyro (DG-800) incorporating a single inertial grade A79-48681 Complex quaternion notation in coordinate liquid bearing sensor has been designed, fabricated, and tested. The transformations. F. G. Saylor (TRW Defense and Space Systems unit is unusually rugged and its hydrostatic bearing and power pivot Group, Redondo Beach, Calif.( and W. A. Jarvinen (USAF, Warner provide exceptionally good performance for the size of its angular Robins Air Logistics Center, Robins AFB, Ga.). In: NAECON 1979; momentum. Considerable interest has been expressed in the concept Proceedings of the National Aerospace and Electronics Conference, and the Army has contracted for preproduction units for its CV-HRS Dayton, Ohio, May 15 . 17, 1979. Volume 3. New program. This paper gives a performance synopsis and discusses York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. design/performance considerations. B .J. 1047 . 1051. 8 refs. This paper addresses the use of complex quaternion notation in coordinate system transformations among launch aircraft and simu- A79-48678 Expanding the region of convergence for lated missile coordinate systems. Complex quaternion differential SITAN through improved modelling of terrain nonlinearities. L. D. equations describing the transformation from the earth to missile Hostetler and R. C. Beckmann (Sandia Laboratories, Albuquerque, coordinate systems are stated. A brief introduction to real quater- N. Mex.). In: NAECON 1979; Proceedings of the National Aerospace nions as a lead-in to the use of complex notation and an example of a and Electronics Conference, Dayton, Ohio, May 15. 17, 1979. coordinate transformation using complex quaternions are given. The Volume 3. New York, Institute of Electrical and advantages of using the complex notation over direction cosine Electronics Engineers, Inc., 1979, P. 1023. 1030. 13 refs. Research techniques are discussed. Complex quaternion solutions to dynamic supported by the U.S. Department of Energy. coordinate system transformations can often reduce time and storage The SITAN (Sandia Inertial Terrain-Aided Navigation( system space required for FORTRAN programs when compared to direction was originally developed to provide continuous updating of an cosine methods. (Author) inertial navigation system by using radar altimeter measurements of the terrain in conjunction with prestored topographic data in an extended Kalman filter. The basic algorithm performs satisfactorily for limited initial position uncertainties, but can diverge when the position uncertainty is so great that terrain linearity assumptions are A79-48682 ft Pave Low Ill. J. E. Clifford (USAF, Aeronauti- significantly violated. An improvement to the basic system is cal Systems Div., Wright-Patterson AFB, Ohio). In: NAECON 1979; described which considerably increases the region of convergence. Proceedings of the National Aerospace and Electronics Conference, The improvement is accomplished by modelling the terrain nonlin- Dayton, Ohio, May 15 . 17, 1979. Volume 3. New earities as Gauss-Markov measurement noise whose statistics and York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. frequency content are adaptively varied as the uncertainty region 1054-1062. evolves with time. Theoretical development of this modification is Various aspects of the Pave Low Ill program for night/adverse given and results of flight test experiments are presented which verify weather rescue are reviewed. The success of the program is attributed the ability of this modification to significantly increase SITAN's to the people and their philosophy. This is followed by a discussion region of convergence. (Author( of the hardware, with emphasis on the equipment selection process for the prototype. Detailed subsystem capabilities, integration A79-48679 Transfer alignment for precision pointing ap- requirements, and evolved system capabilities/limitations are also plications. J. L. Farrell (Westinghouse Defense and Electronic discussed. B.J.

619 A79-48683

A79-48683 User requirements for future combat search A79-48687 Test implementation through support software and rescue vehicles. D. H. Sattler (USAF, Military Airlift Command, - A FIT translator. G. L. Alker and S. M. Stennett (Westinghouse Scott AFB, III.). In: NAECON 1979; Proceedings of the National Defense and Electronic Systems Center, Baltimore, Md.). In: Aerospace and Electronics Conference, Dayton, Ohio, May 15.17, NAECON 1979; Proceedings of the National Aerospace and Elec- 1979. Volume 3. New York, Institute of tronics Conference, Dayton, Ohio, May 15.17, 1979. Volume 3. Electrical and Electronics Engineers, Inc., 1979, p. 1063-1067. New York, Institute of Electrical and Electronics The mission of a combat rescue vehicle is aircrew recovery in Engineers, Inc., 1979, p. 1098.1104. hostile territory in daylight or darkness and under visual or The paper considers a hardware environment in which an instrument meteorological conditions. In order to accomplish this embedded computer executes fully automated fault isolation tests mission, the vehicle must have superior performance, a high degree of (FIT) on an airborne radar system. External test equipment is not survivability, systems reliability, transportability, and easy maintain- utilized. Complete FIT of this system requires translation of test ability. The aircraft must have equipment which allows operation designer input into a language that will run on the embedded with search and rescue task force or singly in a convert mode. The computer. The information transfer is intricate and prone to error aircraft must be designed with threat avoidance as the primary due to weaknessess common to documentation and verbal communi- method of operation and with threat defeat secondary. B.J. cation. As a solution to this problem, the paper describes a FIT translator which is easily adapted to a variety of systems. B.J.

A79-48684 # H.X combat search and rescue avionics study results. C. L. Zelasco and A. L. Leathan )USAF, Aeronautical A79-48689 Automatic test software for calibrating strap- Systems Div., Wright-Patterson AFB, Ohio). In: NAECON 1979; down systems. L. P. Stave (Rockwell International Corp., Autonetics Proceedings of the National Aerospace and Electronics Conference, Strategic Systems Div., Anaheim, Calif.) and A. P. Andrews (Rockwell International Science Center, Thousand Oaks, Calif.). In: Dayton, Ohio, May 15. 17, 1979. Volume 3. New NAECON 1979; Proceedings of the National Aerospace and Elec- York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. tronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 3. 1069-1078. New York, Institute of Electrical and Electronics The objective of the present study was to perform the necessary Engineers, Inc., 1979, p. 1111-1116. tradeoffs required to define an avionics suite which will satisfy U.S. An integrated system of software was developed for calibration Air Force requirements for a night/adverse weather combat rescue of the Rockwell N73 Strapdown Inertial Navigation System. The capability in an H-60 class (medium life helicopter). The results of software includes an interactive monitor for interfacing with produc- this study showed the practicality of incorporating this type of tion personnel, so that use of the software does not require trained capability in an H-60 helicopter. The study team arrived at this or skilied operators. The calibration software also controls and conclusion by defining a representative point design for the H.X monitors all test equipment, including the MIL-STD-1553A Data Bus avionics. This design, which evolved from an iterative tradeoff which is the primary link to the navigator. The test computer uses process, identified specific representative avionics equipments which the Data Bus to load and execute special-purpose programs in the satisfy the performance requirements. B.J. navigation computer, for diagnosis and calibration of the navigator. The calibration software also performs data management of all calibration and test data, providing traceability for all calibration A79-48685 Multifunction CO2 heterodyning laser radar parameters. This soft-ware system has been evaluated and modified for low level tactical operations. R. L. Del Boca (U.S. Army, Fort for human factors in the factory environment, and is now in use in Monmouth, N.J.) and R. J. Mongeon (United Technologies Research production. (Author) Center, East Hartford, Conn.). In: NAECON 1979; Proceedings of the National Aerospace and Electronics Conference, Dayton, Ohio, A79-48690 Automatic test program generation selection. May 15-17, 1979. Volume 3. New York, D. B. Day (Support Systems Associates, Inc., Northport, N.Y.). In: Institute of Electrical and Electronics Engineers, Inc., 1979, p. NAECON 1979; Proceedings of the National Aerospace and Elec- 1079. 1088. 8 refs. tronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 3. Analysis of tactical scenarios indicates that a number of radar New York, Institute of Electrical and Electronics requirements are optimally solvable with low power 10.6-micron Engineers, Inc., 1979, p. 1117-1121. laser systems. Exploratory development efforts by the U.S. Army This paper examines the use of ATE to test electronic devices and the United Technologies Research Center have been directed at and the generation of test programs for digital electronic assemblies. the advancement of the state of the art in airborne CO2 heterodyne Three methods of generating test programs, using manual, simula- laser radar systems. This paper examines the design considerations, tion, and automatic stimulus generation programs, are presented. The hardware configurations, and test results of flyable breadboard B-i and F-16 Automatic Test Program Generation (ATPG( selections models which have demonstrated the feasibility of using CO2 are studied in detail, noting the difficulties of the selection processes. scanning laser systems for wire detection, precision hover, Doppler The results of these processes for both the B-i and F-16 favored the navigation, and terrain following. B. J. D-4 LASAR system becuase of its high (80%) fault detection capability. C. F.W. A79-48686 Terrain-following radar - Key to low-altitude flight. A. C. Woodward and J. B. Lagrange (Texas Instruments, Inc., A79-48691 The impact of software in automatic test Radar and Digital Systems Div., Dallas, Tex.). In: NAECON 1979; equipment. R. G. Slavkin (Westinghouse Electric Corp., Baltimore, Proceedings of the National Aerospace and Electronics Conference, Md.). In: NAECON 1979; Proceedings of the National Aerospace and Dayton, Ohio, May 15. 17, 1979. Volume 3. New Electronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 3. York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. New York,. Institute of Electrical and Electronics 1089-1096. Engineers, Inc., 1979, p. 1122-1127. Terrain following radar (TFR( is discussed as a chief factor in The paper examines an automated test tool for the evaluation of aircraft survivability during low-altitude flight. The basic principles a radar analog to digital converter (AID). The present manual test of IF techniques applied in current operational radars such as the method for the A/D is imprecise in identifying pass/fail criteria AN/APO-126, -146, and . 158, are described. Past and current TFR because any irregularities in the transfer function of a digital to operational environments are compared to examine survivability and analog converter cause nonlinearities and tend to distort these cost. Projections are made as to the direction of FTR state of the art measurements. To overcome these problems, automated A/D test to meet operational requirements by the Air Force for fixed- and equipment utilizing quantative statistical analysis in software is rotary-wing aircraft. B.J. developed. The A/D parameters that must be characterized to insure

620 A79-48702 radar system performance such as the linearity of the A/D transfer A79-48695 A deterministic investigation of strapped down function, the 'Random Triangle' test included in the automated test navigation System accuracy. P. Motyka (Charles Stark Draper set to measure these parameters, and a noise measurement technique Laboratory, Inc., Cambridge, Mass.). In: NAECON 1979; Proceed- known as the 'RMS Noise' test are discussed. The microcomputer ings of the National Aerospace and Electronics Conference, Dayton, hardware is considered, and it is concluded that automatic equip- Ohio, May 15-17, 1979. Volume 3. New York, ment software allows ease of data handling, complex calculations, Institute of Electrical and Electronics Engineers, Inc., 1979, p. efficiency of manipulation, and detailed analysis of the unit in 1172-1178. 5 refs. Contract No. F33615-78-C-1563. question. A. T. The results of a study which assesses the effects of sensor errors and structural modes upon the accuracy of strapped down navigation systems are presented. These results are significant since the accuracy achieved with state-of-the-art navigation systems is not adequate for present and future high-performance aircraft. The sensors considered A79-48692 Guidance accuracy considerations for the are navigation quality laser and two degree-of-freedom gyros and microwave landing system L-band precision DME. P. J. Kelly and E. accelerometers. The major sensor errors are considered individually F. C. LaBerge (Bendix Corp., Communications Div., Baltimore, Md.). as wellas in combination. Time histories of the navigation errors, for In: NAECON 1979; Proceedings of the National Aerospace and a one-hour flight trajectory which includes many features of a typical Electronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 3. tactical fighter aircraft profile, are presented and analyzed. (Author) New York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. 1130-1141. 26 refs. U.S. Department of Transportation Contract No. FA72ViIA-2801. The microwave landing system )MLS) L-band precision distance A79-48696 Application of instrument rotation in the N73 measuring equipment (PDME) must: (1) satisfy the CTOL Category standard inertial navigation system. A. P. Truban (Rockwell Inter- II decision height and Category III flare maneuver accuracy national Corp., Autonetics Strategic Systems Div., Anaheim, Calif.). requirements (100 feet, 2 sigma) when combined with the appro- In: NAECON 1979; Proceedings of the National Aerospace and priate elevation data, and (2) for VTOL applications provide accurate Electronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 3. range (+ or - 40 feet, 2 sigma) and range information )+ or - 2 knots, New York, Institute of Electrical and Electronics 2 sigma) to permit IRF decelerated approaches to within 500-feet Engineers, Inc., 1979, p. 1179-1185. range of hover. These specifications must be satisfied in the presence Rotation of inertial instruments for reducing the effect of of large signal attenuation caused by ground multipath interference aircraft flight-profile-dependent error sources on strapdown inertial and signal time-of-arrival errors induced by lateral multipash (han- navigation systems is considered. The N73 strapdown inertial gars, etc.). Consideration is given to a consistent accuracy specifica- navigation system with electrostatic gyros uses instrument rotation; tion suitable for MLS operational requirements and a PDME the effect of rotation on electronic characteristics is considered in implementation common for CTOL, STOL, and VTOL. V.T. the mechanization of the rotational technique. The N73 system, the electrostatic gyro, the system mechanization considerations, and A79-48693 The ATCBI.5 beacon interrogator, G. L. Vogt system errors are discussed, noting substantial reduction in the (Bendix Corp., Communications Div., Baltimore, Md.). In: NAECON system sensitivity to internal and environmental error sources and 1979; Proceedings of the National Aerospace and Electronics the achievement of long-term calibration stability. Error sensitivity is Conference, Dayton, Ohio, May 15-17, 1979. Volume 3. discussed, and laboratory and flight test data from the N73 are New York, Institute of Electrical and Electronics presented which show the improvement in error sensitivity and Engineers, Inc., 1979, p. 1142-1146. calibration stability. A. T. A new beacon interrogator has recently been introduced into the nation's air traffic control system by the Federal Aviation A79-48697 Rapid reaction time techniques for a strap Administration. The interrogator, the ATCBI .5 is installed at down navigator employing electrostatic gyro technology. B. E. Bona terminal radar sites, enroute radar sites, and enroute beacon only and R. M. duPlestis (Rockwell International Corp., Autonetics sites. The ATCBI . 5 offers significant improvements over previous Strategic Systems Div., Anaheim, Calif.). In: NAECON 1979; interrogators, such as improved reliability, higher output power, Proceedings of the National Aerospace and Electronics Conference, improved receiver capabilities, compatibility with military interroga- Dayton, Ohio, May 15-17, 1979. Volume 3. New tions modes, and others. In its first year of operation, this equipment York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. has demonstrated more than double the mean time between 1186-1192. equipment outages as compared to its most recent predecessor. Fast reaction techniques for a strapdown system employing (Author) electrostatic gyro technology are described. Induction heating for rotor warmup and accurate gapsetting are used for gyro startup. A A79.48694 Dynamic simulator teat and evaluation of a scheme for aligning the spin axis and the rotor major principal axis is JTIDS relative navigation system, S. Welt (ITT, ITT Avionics Div., presented. Gyrocompassing function is accomplished using a staged- Nutley, N.J.). In: NAECON 1979; Proceedings of the National gain filter to estimate attitude and drift errors. The filter is designed Aerospace and Electronics Conference, Dayton, Ohio, May 15-17, for rapid detection of large initial errors, especially in heading. The 1979. Volume 3. New York, Institute of gyrocompass loop is closed through the filter in such a way that the Electrical and Electronics Engineers, Inc., 1979, p. 1162-1169. 5 response of the closed loop is precisely as desired. V. T. refs. The Joint Tactical Information Distribution System (JTIDS( is a spread spectrum command-control-communication system designed to operate in the Lx-Band (960-1215 MHz) and provide the military A79'48702 A real time video bandwidth reduction system services with a secure anti-jam communication, navigation and based on a CCD Hadamard transform device. D. J. Spencer and J. M. identification capability in the tactical environment of the 1980's. Anderson (TRW Defense and Space Systems Group, Redondo Beach, This paper describes the design and implementation of the AN/USM- Calif.). In: NAECON 1979; Proceedings of the National Aerospace 440 JTIDS Environment Simulator (JES( being developed for the and Electronics Conference, Dayton, Ohio, May 15-17, 1979. Naval Air Development Center by ITT Avionics Division. The JES is Volume 3. New York, Institute of Electrical and a real time computer controlled dynamic simulator which provides a Electronics Engineers, Inc., 1979, p. 1218-1231. 7 refs. realistic RF environment and inertial navigation system signals when A low-cost video bandwidth compression system, VIDAP, which required which are used to test and evaluate the anti-jam and relative operates in real time with standard sensors and displays, is described. navigation performance of a wide variety of JTIDS user terminals. The VIDAP is bated upon the 8 x , 8 Hadamard transform and a full (Author) frame (512 x 512 x 6) memory and employs a LSI device

621 A79-48705

implemented in digital charge coupled device )DCCD( technology. Institute of Technology, Wright-Patterson AFB, Ohio). In: NAECON Compression of the video bandwidth is achieved in three ways: (1) 1979; Proceedings of the National Aerospace and Electronics frame reduction, (2) statistical redundancy removal, and (3) spatial Conference, Dayton, Ohio, May 15-17, 1979. Volume 3. fidelity reduction (subsampling). These three factors may be traded New York, Institute of Electrical and Electronics off to obtain any given data rate at the expense of temporal or Engineers, Inc., 1979, p. 1328-1333. spatial distortion. The system provides multiple synchronization The performance of a pulse decode circuit is examined through modes for use with either sensor-based or modem-based timing and Monte Carlo simulation for various types of signal interference. The makes it possible to use small (less than 200 parts), low-power (20 received signals represent environments of many non-coherent W) transmitters for avionics applications. V.T. correct replies with none dominant, many non-coherent friendly replies with one dominant, and noise jamming with no valid reply A79-48705 # Digital sensor simulation at the Defense Map- present. The performance of the receiver was determined by studying ping Agency Aerospace Center, M. B. Faintich (U.S. Defense the effects of an envelope detected version of the received signal on Mapping Agency, Aerospace Center, St. Louis Air Force Station, the decoder circuit, and the results indicate that many types of Mo.). In: NAECON 1979; Proceedings of the National Aerospace and deterministic pulse formats will cause the decoder to respond at its Electronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 3. maximum decode rate. In terms of random, noise-only types of New York, Institute of Electrical and Electronics interference, the decoder is most vulnerable to signals whose Engineers, Inc., 1979, p. 1242-1246. bandwidths are at least the overall RF bandwidth of the receiver, but The primary objective of the digital sensor simulation investi- for the signal-plus-noise case the simulation results show that once gations being conducted at the Defense Mapping Agency Aerospace the interference power reaches a certain value, increases in the power Center )DMAAC) is to establish an editing and analysis capability for of the valid reply will not improve the decoder performance, A. T. digital culture and terrain data bases. These data bases are being produced by DMAAC to support advanced aircraft simulators by A79-48715 JTIDS relative navigation ' Architecture, error providing an improved low level radar training capability offered by characteristics and operational benefits. W. R. Fried (Hughes Aircraft digitally generated radar landmass images. As a result of the Co., Fullerton, Calif.). In: NAECON 1979; Proceedings of the technology developed for aircraft simulator support, sensor guidance National Aerospace and Electronics Conference, Dayton, Ohio, May reference scenes, visual, and microwave scenes are also being digitally 15-17, 1979. Volume 3. New York, Institute of generated. Currently, intensive studies are underway to gierate Electrical and Electronics Engineers, Inc., 1979, p. 1344-1349. 7 synthetic input data bases with apparent resolutions finer than in the refs. original data bases, using supportive data base information. Highly The paper examines the relative navigation (RELNAV) function realistic sensor simulations have been generated, and the continuing of the joint tactical information distribution system )JTIDS) which emphasis is on modeling new tensors as well as improving resolution provides high-accuracy absolute and relative position information without increasing data base production costs. (Author) and time synchronization. The RELNAV function is obtained through the addition of software only to the JTI DS terminal's operational computer program. Each member determines his posi- tion, velocity, and time offset through sequential passive time-of- A79.48711 II Integrated CNI avionics. D. G. Botha )USAF, arrival measurements with respect to other members, using appro- Avionics Laboratory, Wright-Patterson AFB, Ohio). In: NAECON priate source selection algorithms and extrapolation with dead 1979; Proceedings of the National Aerospace and Electronics reckoning data by means of a recursive filter mechanization. The Conference, Dayton, Ohio, May 15-17, 1979. Volume 3. basic system architecture, software functions, the error sources, and New York, Institute of Electrical and Electronics operational benefits, including the availability of the navigational Engineers, Inc., 1979, p. 1314-1317. USAF-supported research. data in geodetic and arbitrary grid coordinates and operation in a In the context of integrated avionics the concept of multi- high jamming environment without reliance on critical nodes, are function multiband airborne radio system has evolved. This concept discussed. A.T. recognizes the synergistic relationship between radio navigation and inertial tensor measurements which lead to the designation of an integrated CNI avionics as a subset of integrated avionics. The paper describes a conceptual approach to the airborne CNI function in this higher-level integration context. The findings of a definition phase A79-48716 - System configuration and algorithm design of are discussed, architectural approaches to implementation of the CNI the inertially aided JTIDS Relative Navigation function. W. R. Fried function are described, and further efforts addressing realization of (Hughes Aircraft Co., Fullerton, Calif.) and R. Loeliger (Intermetrics, the conceptual goals are postulated. S. D. Inc., Long Beach, Calif.). In: NAECON 1979; Proceedings of the National Aerospace and Electronics Conference, Dayton, Ohio, May A79-48712 Real time compression of video signals. D. 15-17, 1979. Volume 3. New York, Institute of Ludington (General Electric Co., Aircraft Equipment Div., Utica, Electrical and Electronics Engineers, Inc., 1979, p. 1350-1356. N.Y.). In: NAECON 1979; Proceedings of the National Aerospace USAF-sponsored research, and Electronics Conference, Dayton, Ohio, May 15-17, 1979. The system configuration for implementing the Relative Naviga- Volume 3. New York, Institute of Electrical and tion )RELNAV) function in the JTIDS Hughes Improved Terminal Electronics Engineers, Inc., 1979, p. 1318-1321. USAF-supported (HIT) is presented. The integration options for interfacing the LN-31 research. Inertial Navigation Set with the HIT are discussed and the selected The paper deals with a video bandwidth compression system interface is described. The RELNAV operational modes, control and which uses CCD5 to implement a two-dimensional cosine transform display requirements, and major software functions are discussed. A in real time at a resolution of 512 pixels per TV line. The system is description is given of the selected RELNAV filter algorithm and the composed of an airborne encoder and a ground-based decoder. The associated timing and sequencing design. The filter extrapolation, the decoder accepts compressed data from the encoder and converts it inertial processing and the source selection algorithms are discussed. back into video. A data frame is first assembled in a memory and is Some simulation results are presented. (Author) then read Out to an inverse quantizer and the inverse cosine transform while a parallel memory is being loaded. The output of the A79-48717 # Tactical electronic reconnaissance sensor. P. transform is a video signal which, after filtering, is available for W. Poet (USAF, Tactical Air Warfare Center, Eglin AFB, Fla.). In: display on a standard 525-line monitor. V.T. NAECON 1979; Proceedings of the National Aerospace and Elec- tronics Conference, Dayton, Ohio, May 15-17, 1979. Volume 3. A79-48713 # Performance of a pulse-decode circuit in the New York, Institute of Electrical and Electronics presence of interference. G. S. Douple and S. R. Robinson )USAF, Engineers, Inc., 1979. 8 p.

622

A79-48873

The ALQ-125 tactical electronic reconnaissance (TERECI sensor measured by the iodine number and the increase in vapor pressure detects, identifies, and locates radar emitters and reports them to due to cracking is demonstrated for the fuels AT, TS-1, T-8B and ground terminals via narrowband data link. The sensor, which is 1.6. Values of the temperature derived from the 'hardness factor' at internally mounted in the RF-4C aircraft, uses left and right side the iodine number defined as the point of initial thermal decomposi- interferometer antenna arrays to determine direction of arrival tion are shown to agree fairly well with thermal decomposition (DOA) of radar emissions. Locations of tactical emitters such as initiation temperatures calculated from kinetic equations and the radars associated with surface-to-air missile systems are computed dependence of iodine number on temperature. It is concluded that using triangulation techniques as the aircraft flies along a base leg. the 'hardness factor' allows the prediction of the extent of thermal The TEREC sensor measures the frequency, pulse repetition interval decomposition at various temperatures and heating times as well as (PRI), pulse width, and (On a preprogrammed optional basis( scan the computation of thermal decomposition initiation temperatures. rate, and compares these with the preprogrammed parameters for up A.L.W. to nine priority emitter types in the airborne computer. All TEREC.collected data is stored on magnetic tape for postflight data A79-48858 N Changes in the quality of T. 6 fuel upon reduction using the TER EC portable exploitation processor (T.PEP). prolonged storage (lamenenie kachestva topliva T-6 pri dlitel'nom (Author) khranenii). N. I. Melent'eva, I. V. Malysheva, N. N. Kalitina, and L. N. Savin. Khimiia i Tekhnologiia Topliv i Masel, no. 8, 1979, p. 22-24. 7 refs. In Russian. The values of fuel quality indicators measured at six-month A79-48849 N Subsonic and transonic flows on a variable sweep wing (Ecoulements subsoniques et transsoniques sur une aile a intervals before, during and after the storage of jet fuel 1-6 in large flèche variable). V. Schmitt and F. Manie (ONERA, Chftillon . sous- steel tanks at elevated pressures are compared. After 20 months of Bagneux, Hauts-de-Seine, France). La Recherche Aérospatiale, July- storage, it is found that the acidity, actual tar content, sediment Aug. 1939, p. 219-237. 24 refs. In French. content and dissolved tars exhibit a slight decline in quality, while Detailed experiments were performed on models of a variable the remaining technical indicators (density, distillation temperature sweep wing emphasizing in particular flow separation and develop- range, viscosity, aromatic hydrocarbon content, smokeless flame ment of vortex structures in the whole speed range and, in addition, height, iodine number, total sulfur content, ash content, technical the shape of shock waves at transonic speeds. The results of these impurities and crystallization temperature) remained unchanged. tests have been compared with those of calculations made with Results of qualification tests, thermal stability tests, corrosion tests available codes such as an incompressible panel method for un- and chemical stability tests also indicate that 1-6 fuel can be stored separated flows and an unsteady method based on a point discretiza. for up to two years with no decline in quality. A.L.W. tion of the vortex vector for separated flows. Transonic flows were calculated using different relaxation methods: one based on the A79-48859 # Method of determining mechanical-impurity perturbation theory, two others on the full potential equation. contents in jet fuels (Metody opredeleniia soderzhaniia mekhani- (Author) cheskikh primesei v reaktivnykh toplivakh). V. N. Zrelov, N. G. Postnikova, L. V. Krasnaia, E. N. Zhuldybin, M. V. SaI'nikova, and I. I. Zimina. Khimiia i Tekhnologiia Topliv i Masel, no. 8, 1979, p. A79-48856 N The tendency of jet fuels to form deposits on 51-53. 7 refs. In Russian. a heated surface (Skionnost' reaktivnykh topliv k obrazovaniiu Two methods based on nitrocellulose filtration for determining otlozhenii na nagretoi poverkhnosti). E. P. Seregin, V. G. Gorodet. the contents of mechanical impurities in jet fuels are presented. The skii, N. P. Golenev, and V. N. Prokudin. Khimiia i Tekhno/ogiia graphical-analytical method which determines impurity content from Top/iv iMasel, no. 8, 1979, p. 17 . 20. 8 refs. In Russian. the slope of the relation of the mass of deposit collected on the The tendencies of various standard commercial jet fuels to form nitrocellulose column to the volume of fuel passed through the deposits of oxidation products on heated surfaces are investigated. column after the period of tar adsorption, may require up to 15 I of Temperatures at which deposits start to form, relationships between fuel. The improved method, derived from the GUST 10577-63 and the amount of test deposit formed and a standard (the thermostabil. ASTM D 2276 standard test and designated GOST 10577-78 or ity index) and thermal stabilities were determined for the fuels T-1, Method B, requires only 5 I of fuel and relies on a coefficient of 0.7 TS-1, AT and 1. 6 by means of various procedures. The statistical to account for tar accumulation. The results of Method B deter- methods employed (LSART and TSRT-2) are found capable of minations are shown to agree well with those of the graphical providing information about total oxidation product formation, but method, and duplicate determinations of jet fuel impurities contents are unable to distinguish thermostability indices, while DTS.1 by Method B are shown to differ by no more than 0.06 mg/I, with a indicates rates of filter obstruction and only DTS. 2 is capable of mean deviation of 0.02 to 0.03 mg/I. The method, employing on-site determining deposit-formation and adhesion parameters. The filtration by two number 5 filters, is considered suitable for airport thermostability indices of the fuels, and thus their tendencies to as well as laboratory use. A.L.W. form deposits on heated engine parts, are found to decrease in the order T-1, TS-1, AT to 1-6, and temperatures of deposit initiation to range between 85 and 100 C for T-1 and TS-1, 135 and 180 C for AT A79-48870 N A Navy plan for the development of a practi- and 180 and 190 C for T-6. The fuel deposit formation properties cal computer-aided programming /CAP/ system for analog circuit test obtained are attributed to relative contents of hetero.organic and design. F. Liguori (U.S. Navy, Naval Air Engineering Center, oxidizable compounds. A.L.W. Lakehurst, N.J.). In: AUTQTESTCON '78; International Automatic Testing Conference, San Diego, Calif., November 28-30, 1978, Conference Record. New York, Institute of A79-48857 Evaluation of the temperature of the initiation N Electrical and Electronics Engineers, Inc., 1978, 24-27. of jet fuel decomposition by means of the 'hardness factor' (Otsenka p. temperatury nachala razlozheniia reaktivnykh topliv po 'faktoru zhestkosti'). A. K. Bukharkin and G. I. Kovalev. Khimiia i Tekhno- /ogiia Topliv i Masel, no. 8,1979, p. 20-22. In Russian. A79-48873 N E-3A sentry /AWACS/ ATPG. M. S. Martin The application of the pyrolysis 'hardness factor' derived by (USAF, Software Support Center, Robins, AFB, Ga.). In: AUTO- Linden (1951) as a measure of the extent of cracking in a TESTCON '78, International Automatic Testing Conference, San hydrocarbon and consisting of the product of the temperature and Diego, Calif., November 28-30, 1978, Conference Record. the 0.06th power of the holding time at that temperature, to the New York, Institute of Electrical and Electronics calculation of the temperature at which the thermal decomposition Engineers, Inc., 1978, p. 39, 40. of jet fuels begins is examined. A linear correspondance between the The selection of software aids to provide an organic depot 'hardness factor' and the extent of thermal decomposition as capability for certain items of the Air Force E-3A sentry aircraft is

623 A79-48878 examined. Seventeen automatic test pattern generators (ATPG) of navigation, and update II and Ill systems are discussed. The test set digital type were examined and five, including LOGOS and G- and hardware station stimulus and measurement capabilities are summar- D-LASAR systems, were selected for further examination. In the ized, and integrated logistics support plan, test program set develop- analog area, thirteen different circuit analysis programs were studied ment, including test program information, program printouts, CAD and it was found that SYSCAP-2 would be the most cost effective. printouts, and patchcard and cable information are listed. The Atlas C.F.W. impact and test program set production are examined, and it is concluded that the support of the P-3 by automatic test equipment permitted transition from prime equipment manufacturer to depot support, and illustrated the ability of a company specializing in A79-48878 # Air Force modular automatic test equipment integrated logistics support to produce the ATE and test program. development program. C. M. Wheelock (USAF, Washington. D.C.). A.T. In: AUTOTESTCON '78; International Automatic Testing Confer- ence, San Diego, Calif., November 28-30, 1978, Conference Record. A79-48887 # Can avionic testability requirements be en- New York, Institute of Electrical and Electronics forced. R. Brocchi (U.S. Navy, Naval Air Engineering Center, Engineers, Inc., 1978, p. 119-121. Lakehurst, N.J.). In: AUTOTESTCON '78; International Automatic The paper examines the Air Force modular automatic test Testing Conference, San Diego, Calif., November 28-30, 1978, equipment (MATE) development program. It is noted that problem Conference Record. New York, Institute of areas with automatic test equipment (ATE) are the proliferation of Electrical and Electronics Engineers, Inc., 1978, 282-285. different configurations, software incompatibilities, erroneous test p. Theoretically avionic testability can be specified, levied con- results, late deliveries of new equipment and high development costs. tractually, designed and integrated into hardware, and demonstrated. The MATE family will permit interchangeable modules (hardware The intent of this paper is not to identify how it is possible to and software) to be used at all levels of maintenance, thereby achieve testability but how it is possible to get the maximum reducing the problem of units passing tests at one level of testability that is practical by a methodology of enforcement and maintenance and failing at another. Attention is given to the control from the time the avionics procurement is envisioned objectives of the MATE program which include reducing the life through the design, development, and acceptance. The review and cycle cost of weapon system support, reduce proliferation of ATE, concurrence in testability is accomplished through the data submit- and improve ATE procurement practices. In conclusion it is stressed tals from the avionics supplier. Enforcement is directly related to the that a commitment to supply the necessary resources to the program type of data required, when it is required, the formats specified, and office must be made by the highest levels of the policy-making the ability to get exactly what was contractually required. The machinery. M.E.P. optimum method of achieving this end is to have support engineering personnel participate through the stages of data preparation, review, and resubmittal. The participation is via concurrent reviews in conjunction with the avionics design review cycle, and by directing A79-48883 # ATE and aircraft mechanical diagnostics. T. C. the contractor to include specific testability requirements for each Belrose (U.S. Army, Aviation Research and Development Command, UUT on a case by case basis. - (Author) St. Louis, Mo.). In: AUTOTESTCON '78; International Automatic Testing Conference, San Diego, Calif., November 28-30, 1978, Conference Record. New York, Institute of A79-48888 Avionics design for testability - An aircraft. Electrical and Electronics Engineers, Inc., 1978, p. 176-181. 12 refs. contractor's viewpoint. J. M. Roche (McDonnell Aircraft Co., St. The Army is committed to fielding a family of automatic test Louis, Mo.). In: AUTOTESTCON '78; International Automatic support systems (ATSS) to support all Army materiel. The current Testing Conference, San Diego, Calif., November 28-30, 1978, plan is to field the AN/USM .410 'third generation' ATE. The Army Conference Record. New York, Institute of has also sponsored a significant amount of work aimed at achieving Electrical and Electronics Engineers, Inc., 1938, p. 286-293. an 'on condition' maintenance philosophy for major aircraft subsys- Designing avionics for testability is the inclusion of design tems by monitoring turbine engine performance, engine mechanical provisions in the avionics to enable test of the performance condition, health of various rotating dynamic components, hydraulic capability of the avionics, to isolate avionic malfunctions to systems, and structural integrity of the aircraft. The objective is to replaceable elements, and to permit adjustment and alignment of the investigate the viability of accomplishing the aircraft condition avionics as may be required. The effective implementation of monitoring and diagnostic task using ATE. Significant points are the testability provisions in the design of the Air Vehicle Equipment following: nonintrusive monitoring of aircraft mechanical systems is (AVE) and the Ground Support Equipment )GSE) that comprise the possible; impressive benefits can be attributed to this approach, but avionics can improve equipment reliability and , availability while several attempts at fielding such a system have been terminated reducing equipment weight and cost. Accordingly, the operational because of excessive initial investment costs; and mechanical diag- readiness of the weapon system can be improved by effectively nostics is not a simple extension of a measurement capability. designing the avionics for testability. The aircraft contractor's (Author) viewpoint of designing avionics for testability is presented along with the methods and techniques employed by the aircraft contractor to effectively include testability provisions in the avionics. (Author)

A79.48884 AN/USM-449/V/ ATE for worldwide support A79-48889 Avionics design for testability - A vendor's of the P3 Orion. P. M. Knapp (AAI Corp., Baltimore, Md.). In: viewpoint. D. C. Byerly (General Electric Co., Binghamton, N.Y.). AUTOTESTCON '78; International Automatic Testing Conference, In: AUTOTESTCON '78; International Automatic Testing Con- San Diego, Calif., November 28-30, 1978, Conference Record. ference, San Diego, Calif., November 28-30, 1978, Conference New York, Institute of Electrical and Electronics Record. New York, Institute of Electrical and Engineers, Inc., 1978, p. 235-241. Electronics Engineers, Inc., 1978, p. 294-299. 6 refs. The update of the AAI 5500 ATE to the AN/USN-449(V) GE experience with the testability of new avionics systems is configuration and the extension of the test program to P-313 and reviewed with particular reference to the F-18 program. It is found ASN-124 TAC/NAV and P-3C configurations are considered. The that testability assessment and enhancement efforts will have AN/USN-449(V) introduced the latest computer configuration, minimal adverse impact on the development program for a new updated peripherals, included ATLAS test language, and added a avionics system if these efforts are performed at the beginning of the second test port to the 5500 ATE for dynamic digital testing. The design phase by a separate team of testability/maintainability planned installations including Conus sites and Naval Avionics engineering specialists working in parallel with the system design Rework facilities are listed, and communications, data systems, team. Early generation of test requirement document data submittals

624 A79-49054 provide a highly visible means of measuring and reviewing testability Existing design testers are being extensively utilized through update for each UUT in an avionic system. B. J. and improvement modifications, with the vast majority of the development work concentrated in the Test Packages (Interface Test Adapters (ITAs( and test programs). This paper describes the A79.48890 Testability, the key to economical and oper- acquisition management techniques used and the various ATE and ationally effective avionic test software. M. B. Weber (Harris Corp., software development aids selected to date. The test package PRO Electronics Div., Syosset, N.Y.). In: AUTOTESTCON '78; development effort is described. Our approach to supporting International Automatic Testing Conference, San Diego, Calif., EPROM/PROM ICs is presented. Configuration management is November 28-30, 1978, Conference Record. discussed. Finally, a look at the program future is given. (Author) New York, Institute of Electrical and Electronics Engineers, Inc., 1978, P. 300.304. A79-48896 A new U.U.T./test statiou interface, M. B. Testability, in the context of this paper, is defined as the Hosking (General Dynamics Corp., Electronk_ Div., San Diego, optimum automatic fault detection and isolation capability per- Calif.). In: AUTOTESTCON '78; International Automatic Testing mitted by the avionic hardware design and economically reflected in Conference, San Diego, Calif., November 28-30, 1978, Conference the design of the test program set (TPS) for a given automatic test Record. New York, Institute of Electrical and equipment (ATE) system. The paper addresses the major elements of Electronics Engineers, Inc., 1978, p. 346-350. the total avionic/support system (avionic UUT/ATE/TPS, where The modular UUT/test station interface was designed specifi- UUT unit under test) and the key characteristics of these elements cally for a combination of LRU and SRU testing. Its advantages as they relate to and affect the development economics and include ease of maintenance, long life, simplified field maintenance, operational effectiveness of TPSs. The discussion presented reveals proven high reliability, and a substantial reduction in signal degrada- how UUT design data derived during the development process of the tion due to excessive lengths of interface cabling. Moreover, interface avionics can be utilized to establish a testability baseline for the adapter complexity and weight are minimized. B. J. UUT/ATE as well as effect-added efficiency in the UUT test software development process. S. D. A79-48945 Achieving consistency in the production of critical jet engine components by means of press forging. F. Turner (Cameron Iron Works, Ltd., Livingston, Scotland). In: High tempera- A79.48891 Techniques for fault isolation ambiguity re- ture alloys for gas turbines; Proceedings of the Conference, Liege, duction. A. L. McCoIIor (Support Systems Associates, Inc., North- Belgium, September 25-27, 1978. Barking, port, N.Y.) and N. M. Clark (U.S. Navy, Naval Air Engineering Essex, England, Applied Science Publishers, Ltd., 1978, p. 893-899. Center, Lakehurst, N.J.). In: AUTOTESTCON '78; International In recent years, manufacturers of aircraft engine components Automatic Testing Conference, San Diego, Calif., November 28-30, have placed increased emphasis on quality control and inspection 1978, Conference Record. ' New York, Institute procedures. A major reason for this emphasis is the engine builder's of Electrical and Electronics Engineers, Inc., 1978, p. 305.310. requirement of consistency in the fabrication of components. In the The specification requirements for avionics testability and test access are reviewed, noting that in general, the requirements are not present paper, the ingredients of consistency in manufacture are stringent enough to meet the needs of the ATE operator or avionics identified as a combination of good quality control and the nature repair person. Attention is given to some frequent causes of excess and reliability of the manufacturing equipment. Two examples of how well consistency has been achieved in an industrial plant, as PCOF ambiguities and erroneous PCOF's. Means of eliminating such measured by mechanical property data, are presented. V. P. deficiencies in future equipment designs and test programs are described. Finally, recommendations are made for specification revisions and future vendor and contractor responsibilities. M.E.P. A79.49052 • LDV measurements on propellers. J. P. Sullivan (Purdue University, West Lafayette, Ind.). In: Laser velocim. A79.48894 # F-16 avionics maintenance concept and multi- etry and particle sizing; Proceedings of the Third International national aspects. G. L. Vickery (USAF, Systems Command, Washing- Workshop, West Lafayette, Ind., July 11-13, 1978. ton, D.C.). In: AUTOTESTCON '78; International Automatic Washington, D.C., Hemisphere Publishing Corp., 1979. Testing Conference, San Diego, Calif., November 28-30, 1978, p. 531-534. NASA-supported research. Conference Record. New York, Institute of Laser Doppler velocimeter (LDV) measurements of the flow Electrical and Electronics Engineers, Inc., 1978, p. 336-339. velocity around high-efficiency propeller blades for high disk loading The paper describes the three level avionics maintenance turboprop propulsion systems are reported. The wind-tunnel flow concept for the F-16, organization, intermediate, and depot. This around sets of eight straight and swept propeller blades with the concept has been tailored to the F-16 weapons system by an iterative same twist and chord distributions was measured using a conven- process. It is shown that decisions are made based on the best tional two-color dual scatter LDV system. The measurements of the economic approach, yet test capability is retained that allows a axial flow velocities a small distance in front of the propeller blade, reversal in those instances where the phased maturation of the between the blade row, and downstream of the propeller are shown weapons system dictates a change. Finally, it is stressed that since the to provide information necessary for the determination of overall F-16 will carry the defense forces of many Countries into the next performance, swirl angle distribution, blade loading distributions, century, the development of a workable maintenance concept is a local lift and drag coefficients, interference effects, shock location, critical element of logistics support planning for ensuring that local induced velocities, wake characteristics and stall pattern. A.L.W. defense capability. M.E.P. A79-49054 # Effect of tip shape on blade loading character- A79-48895 # F-16 depot automatic test equipment. D. B. istics for a two-bladed rotor in hover, J. D. Ballard, K. L. Orloff Day (USAF, Aeronautical Systems Div., Wright-Patterson AFB, (NASA, Ames Research Center, Moffett Field, Calif.), and A. B. Ohio), In: AUTOTESTCON '78; International Automatic Testing Luebs (Gates Learjet Corp., Wichita, Kan,). In: American Helicopter Conference, San Diego, Calif., November 28-30, 1978, Conference Society, Annual National Forum, 35th, Washington, D.C., May Record. New York, Institute of Electrical and 21-23, 1979, Proceedings. Washington, D.C., Electronics Engineers, Inc., 1978, p. 340-345. American Helicopter Society, 1979. 9 p. 14 refs. (AHS 79-1) General Dynamics Corporation, Fort Worth Division (GD/FW) is A laser velocimeter has been used to study the flow surrounding currently developing the F-16 depot level Automatic Test Equipment a 2.13-m-diameter, two-bladed, teetering model-scale helicopter rotor (ATE) system under the direction of the F-16 System Program operating in the hover condition. The rotor system employed Office (SPO) located at Wright-Patterson Air Force Base, Ohio. interchangeable blade tips over the outer 25% radius. A conventional

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rectangular planform and an experimental ogee tip shape were integrations of the unsteady chord-wise pressure distribution. It was studied. The radial distribution of the blade circulation was obtained found that sweep delays the onset of dynamic stall and generally by measuring the velocity tangent to a closed rectangular contour reduces the magnitude of the unsteady load variation about the mean around the airfoil section at a number of radial locations. A response as a function of the pitch displacement. A noteworthy relationship between local circulation and bound vorticity is invoked aspect of this research program was the ability to estimate the to obtain the radial variations in the sectional lifting properties of the unsteady drag force using only those contributions due to pressure blade. The tip vortex-induced velocity was also measured im- forces. This approximation is especially valid over the stalled portion mediately behind the generating blade and immediately before the of the cycle where the viscous drag contribution is relatively small. encounter with the following blade. The mutual influences between (Author) blade loading, shed vorticity, and the structure of the encountered vortex are quantified by the results presented and are discussed A79-49058 An integrated analytical and experimental comparatively for the rectangular and ogee planforms. The experi- investigation of helicopter hub drag, A. H. Logan, R. Marthe (Hughes mental loading for the rectangular tip is also compared with Helicopters, Culver City, Calif.), D. R. Clark (Analytical Methods, predictions of existing rotor analysis. (Author) Inc., Bellevue, Wash.), and A. Phelps (U.S. Army, Structures Laboratory, Hampton, Va.). In: American Helicopter Society, Annual National Forum, 35th, Washington, D.C., May 21-23, 1979, Proceedings. Washington, D.C., American Heli- A79-49055 Helicopter performance methodology at Bell copter Society, 1979. 16 p . 8 refs. (AHS 79-5) Helicopter Textron. F. D. Harris, J. D. Kocurek, T. T. McLarty, and This paper describes an integrated program which uses a viscous T. J. Trept, Jr. (Bell Helicopter Textron, Fort Worth, Tex.). In: wing/body computer code to analyze low drag concepts of a current American Helicopter Society, Annual National Forum, 35th, Wash- helicopter. Based on this analysis, full-scale wind tunnel models are ington, D.C., May 21-23, 1979, Proceedings. fabricated and tested. The resulting experimental data are then compared to predictions and areas of agreement are defined. The Washington, D.C., American Helicopter Society, 1979. 48 p. 23 refs. (AHS 79-2) viscous wing/body computer code is Program DRAG which includes Forward flight helicopter performance methodology is reviewed engine inflow/exhaust modeling and main rotor hub representation. with emphasis placed on the two key aspects of the power required The full-scale experimental model represents the YAH-64 and the calculation, pitch attitude for trim and rotor aerodynamics. The testing was conducted in the NASA/Langley V/STOL tunnel. The modeling approach to trim is described along with contrasts among data presented and discussed indicate that Program DRAG is airframe component and rotor forces and moments. It is shown that acceptable for designing hub/pylon modifications. In addition, it is improved correlation results from a more physical treatment of the shown that engine air flow has a significant effect on model pylon blade sip loss model used in combination with unsteady, three- drag. The development of typical hub/pylon fairings and the dimensional blade element aerodynamics. The sensitivity of the importance of sealing are discussed. (Author) performance calculation to airfoil data and blade elastic motion are discussed, and the accuracy of simple momentum theory for prediction of power required in low speed flight is outlined. V. T. A79-49059 Helicopter obstacle strike tolerance. L. T. Burrows (U.S. Army, Applied Technology Laboratory, Fort Eustis, A79-49056 A lifting-surface method for hover/climb air- Va.), J. E. Brunken (Bell Helicopter Textron, Fort Worth, Tex.), and loads. J. M. Summa and D. R. Clark (Analytical Methods, Inc., B. P. Gupta (Hughes Helicopters, Culver City, Calif.(. In: American Bellevue, Wash.). In: American Helicopter Society, Annual National Helicopter Society, Annual National Forum, 35th, Washington, D.C., Forum, 35th, Washington, D.C., May 21-23, 1979, Proceedings. May 21-23, 1979, Proceedings. Washington, Washington, D.C., American Helicopter Society, D.C., American Helicopter Society, 1979. 11 p. Army-supported 1979. 12 17 refs. Grant No. DAAJ02-76-C-0069. (AHS 79-3) p. research. (AHS 79-7) The development of a lifting-surface method for hover/climb Design concepts for improving the tolerance of helicopters to airloads and its application in the prediction of hovering rotor in-flight obstacle strikes are derived for the main rotor, tail rotor, performance are described. The method includes both a prescribed fuselage and landing gear (fixed system), and main rotor hub and and a relaxed wake representation. Unique features of wake controls. Selected concepts are comparatively analyzed based on modeling developed for the method include the wake segmentation, their functional, operational, and aircraft integration characteristics, a new far-wake model, and a model of the tip vortex shedding across and on their strike damage cost-reduction potential. Detailed the blade chord. In addition, new techniques for wake relaxation, definition of the in-flight obstacle strike problem provided a sound such as a numerical method for the calculation of wake velocities due basis for the derivation and selection of the design concepts having to curved vortex filaments, a more representative core model, and a the greatest potential for improving helicopter strike tolerance. new method of integration for new wake shapes are discussed. Problem definition included determination of the types of obstacles Calculated results demonstrate that the fundamental explanation for struck and frequency; areas of helicopter struck and frequency; cost discrepancies in hovering rotor airloads predicted by lifting-line and of strikes; and diameter and type of trees and wires for which current lifting-surface methods is the wake shedding model. Finally, hovering systems have reasonable strike tolerance. Obstacle strike tolerance performance correlations for converged relaxed wake calculations design criteria for future systems are proposed, as are suggestions for with experimental data are analyzed. (Author) improving she obstacle strike protection of current systems through retrofit, (Author)

A79-49057 The influence of sweep on the aerodynamic A79-49060 # A system for interdisciplinary analysis . A key loading of an oscillating NACA 0012 airfoil, A. 0. Saint Hilaire, F. to improved rotorcraft design. A. W. Kerr (U.S. Army, Research and 0. Carta (United Technologies Research Center, East Hartford, Technology Laboratories, Moffett Field, Calif.) and J. M. Davis (U.S. Conn.), and W. D. Jepson (United Technologies Corp., Sikorsky Army, Aeromechanics Laboratory, Moffett Field, Calif.(. In: Ameri- Aircraft Div., Stratford, Conn.(. In: American Helicopter Society, can Helicopter Society, Annual National Forum, 35th, Washington, Annual National Forum, 35th, Washington, D.C., May 21-23, 1979, D.C., May 21-23, 1979, Proceedings. Washing- Proceedings. Washington, D.C., American Heli- ton, D.C., American Helicopter Society, 1979. 15 p. 16 refs. (ANS 79-8) copter Society, 1979. 10 p. 10 refs. (AHS 79-4) An experimental study was conducted to determine the effect Development of the Second Generation Comprehensive Heli- of sweep on the unsteady aerodynamic load characteristics of an copter Analysis System (2GCHAS( is being initiated by the U.S. NACA 0012 airfoil oscillating in pitch about the quarter chord. The Army Research and Technology Laboratories. This system provides unsteady data for these comparisons were obtained from numerical the capability to model the total helicopter to predict performance,

626 A79-49068 loads, vibration, aeroelastic stability, stability and control, and Independent investigations, a NASA-funded study on helicopter acoustics characteristics This interdisciplinary, analysis system is a aerial applications of materials, and flight spraying tests conducted basic tool required to support the rotorcraft design process. Aspects by BHT are discussed. Agricultural (AG) helicopter systems are of this system which affect its application as a design tool are investigated by computer analysis for parametric effects on swath addressed. A primary consideration in the development of the system widths. Standards and productivity indices for a rating system are is the manner in which component parts of the helicopter are generated from operational costs, payloads, cruise speeds, and swath combined analytically to represent the total vehicle system. The widths. Dollar/acre costs are reviewed for establishing Ag helicopter results of a workshop conducted to discuss formulation of equations capabilities. The NASA study on the current technology of heli- and related issues are summarized. Requirements to make the system copters, equipment and systems and their inherent limitations form easy to use are explored, including the manner in which it is the background for this work. Designs are synthesized from this and applicable through all phases of aircraft design and development other criteria derived in previous studies. These aircraft (three sizes from conceptual analysis through flight test and detailed modifica- and three missions) are exercised for design potential, cost improve- tion support. (Author) ments, and changes in dollars/acre. Advantages of a 'lofted swath' spraying technique and potentials for ultrawide swaths are indicated. A79-49061 Composite helicopter tail booms, H. J. Brown Conclusions and recommendations are presented. (Author( (Fiber Science Corp., Salt Lake City, Utah). In: American Helicopter Society, Annual National Forum, 35th, Washington, D.C., May 21 . 23, 1979, Proceedings. Washington, D.C., American Helicopter Society, 1979. 7 p. (AHS 79.9) A79-49065 Meeting the challenge of precise navigation Two different design concepts for helicopter tail booms made during nap-of-the-earth flight. S. P. Rogers and K. D. Cross (Anacapa from advanced composites are discussed. Cost, structural design and Sciences, Inc., Santa Barbara, Calif.). In: American Helicopter manufacturing factors are presented using the experiences gained Society, Annual National Forum, 35th, Washington, D.C., May from these two tail booms as examples. One tail boom was test flown 21-23, 1979, Proceedings. Washington, D.C., after extensive static and dynamic testing to prove feasibility. Labor American Helicopter Society, 1979.9p. 7 refs. (AHS 79-12) Costs using the wet filament winding process plus 1980 material Navigation during nap-of-the-earth (NOE) flight is one of the prices for graphic fiber and epoxy resin are presented as justification most demanding tasks ever required of an aviator. The difficulty that production of composite tail booms is reasonable today. imposed by a limited view of surrounding terrain is augmented by (Author) the complexity of map interpretation. Nevertheless, aviators are expected to navigate to an accuracy of 100 meters. In order to help A79-49062 Crashworthy armored crewseat for the UH- meet the challenge of such precise navigation, two major efforts are 604 Black Hawk. S. P. Desjardins, D. H. Laananen, R. L. Taylor underway. First, special courses in map interpretation and terrain (Simula, Inc., Tempe, Ariz.), and R. J. Dummer (Norton Co., analysis have been constructed to instruct pilots in these vital skills. Industrial Ceramics Div., Worcester, Mass.). In: American Helicopter The lessons include extensive cinematic simulation exercises to teach Society, Annual National Forum, 35th, Washington, D.C., May the interpretation of symbology, effects of map scale, cartographic 21-23, 1979, Proceedings. Washington, D.C., practices and other critical information. Second, a research program American Helicopter Society, 1979. 13 p. 6 refs. (AHS 79-10) is being conducted to support the development of a computer- In addition to the typical operational features of adjustment and generated topographic display. Such a display is capable of providing comfort, the crewseat for the UH-60A Black Hawk has been designed enormous advantages over conventional maps. The effectiveness of to provide protection from both ballistic fire during operation and the system depends greatly upon the research performed to crash hazards during accidents. It is the first production seat to be adequately define the display content and format. (Author) designed entirely in accordance with MIL-S-58095(AV(, the Army specification which specifies the degree of crash protection in terms A79-49067 Multiplex technology applied to helicopters. of structural strength and energy absorption as well as the means for L. A. Frazer and J. H. Emery (Bell Helicopter Textron, Fort Worth, evaluation. This paper includes a discussion of the requirements Tex.). In: American Helicopter Society, Annual National Forum, imposed on the seat design, a description of the seat system with 35th, Washington, D.C., May 21-23, 1979, Proceedings. emphasis on its unique features, and a presentation of qualification Washington, D.C., American Helicopter Society, 1979. test results. (Author) 8 p. )AHS 79-14) A multiplex system is an information transfer system that time-shares a single transmission medium with multiple information 479.49063 Designing with experimental mechanics. J. sources and receivers. The application of the multiplex technology Cernosek (Bell Helicopter Textron, Fort Worth, Tex.). In: American can greatly enhance the helicopter mission performance, providing Helicopter Society, Annual National Forum, 35th, Washington, D.C., more versatility in the design and making possible the optimization May 21-23, 1979, Proceedings. Washington, of the avionics system. The paper familiarizes the reader with D.C., American Helicopter Society, 1979. 8 p. (AHS 79-11) multiplex technology concepts and terminology, and introduces the Three-dimensional photoelasticity was modified and developed idea of the multiplex system as a tool with which to integrate into a relatively inexpensive tool for accurate stress analysis of helicopter subsystems. The application of the multiplex technology complicated helicopter parts. The typical design process of helicopter to helicopters has been made possible by the advances in electronics dynamic components is presented along with model methods of technology, primarily in the area of microprocessors and large-scale experimental mechanics. The method of aluminum-filled epoxy integration (LSI( techniques. S. D. models, stress freezing three-dimensional photoelasticity, and a new A79-49068 Antennas for the Black Hawk helicopter. M. L. model material based on epoxy resin are discussed. Consideration is Parent (United Technologies Corp., Sikorsky Aircraft Div., Stratford, given to model casting, curing, and loading and evaluation of stress Conn.). In: American Helicopter Society, Annual National Forum, distribution. The main rotor grip of the 412 model was designed 35th, Washington, D.C., May 21-23, 1979, Proceedings. using a three-dimensional photoelastic model to evaluate the stress level. V.T. Washington, D.C., American Helicopter Society, 1979. 13 p. (AHS 79-15) The Black Hawk is the Army's troop transport helicopter for the A79.49064 Agricultural helicopters. H. E. Lemont (Bell 1980s and beyond. This helicopter incorporates flush antennas with Helicopter Textron, Fort Worth, Tex.(. In: American Helicopter no protrusions on the bottom to be damaged in rough-area landings. Society, Annual National Forum, 35th, Washington, D.C., May The paper outlines the design and development program for these 21-23, 1979, Proceedings. Washington, D.C., antennas. Attention is given to a discussion of design objectives, American Helicopter Society, 1979. 12p. 5 refs. (AHS 79-60) initial antenna designs and installation, the antenna test program, and

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resulting antenna improvements for production. The design objec- compare experimental and analytical results, correlations of some tives for Black Hawk antenna include compliance with overall experimental measurements with calculations from an existing blade performance, mechanical, environmental, EMI, reliability, maintain- modes computer program based on a Holzer- Myklestad procedure are ability, and weight requirements, along with meeting design-to-cost presented, and the differences between the results are discussed. The requirements. The final development tasks have been successfully experimental and analytical natural frequencies were generally in completed and the flush antennas are being delivered to the Army on good agreement as were the principal components of the modal production Black Hawk helicopters. S. D. deflections for the flap and lag modes. The torsion mode shape indicated disagreement between the measured and calculated results in regard to the amount of flap and lag motions present in this mode, A79-49069 Advances in decelerating steep approach and while the spanwise variations of the measured and calculated landing for helicopter instrument approaches. P. S. Demko and J. H. torsional components were in agreement. (Author) Boschma (U.S. Army, Fort Monmouth, N.J.). In: American Helicop- ter Society, Annual National Forum, 35th, Washington, D.C., May A79-49072 Dynamics requirements for an Advanced 21-23, 1979, Proceedings. Washington, D.C., Scout Helicopter /ASH/. D. P. Schrage and B. A. Wolfe (U.S. Army, American Helicopter Society, 1979. 13 p. (AHS 79-16) Aviation Research and Development Command, St. Louis, Mo.). In: The instrument decelerating steep approach and landing tech- American Helicopter Society, Annual National Forum, 35th, Wash- nique which extended the helicopter capability into instrument ington, D.C., May 21-23, 1979, Proceedings. meteorological conditions (IMC( domain is considered. This cap- Washington, D.C., American Helicopter Society, 1979. 8 p. 9 refs, ability permits the helicopter pilot to guide it along a precise steep (AHS 79.19) angle approach course and to perform a normal deceleration to a safe The paper presents modified detailed requirements specified for approach termination within a confined landing zone, without visual recent helicopter development programs and their potential applica- reference to the outside world. This method uses microwave landing bility to the requirements for the Advanced Scout Helicopter (ASH) guidance system with precision DME, 4-cue/4-axis flight director design. The recommended ASH System Specification (SS) require- (FD) and autopilot (AP) system. The deceleration maneuver, ments for dynamics are considered, and it is shown how they are and approach profile and rate, the microwave landing system controls should be verified through the Airworthiness Qualification program and equipment, the decelerating steep approach and landing (DSAL) )AQP(. Attention is given to aeroelastic stability, mechanical flight director and controls are discussed, and performance of the stability, engine, shaft, and rotor resonances/instabilities, and air- IMC OSAL maneuver is illustrated by a flight from 1000 and 200 ft frame vibration. A mast-mounted sight (MMS), true nap-of-the-earth intercept altitudes, along 6 and 12 deg glideslopes by the pilot )NOE) flight, and maneuverability are outlined along with their through the FD, or by the autopilot, to a stable hover over the effects on the dynamics requirements discussed. V.T. desired landing point. A. T. A79-49073 Theoretical flap-lag damping with various dynamic inflow models. D. A. Peters (Washington University, St. Louis, Mo.) and G. H. Gaonkar (Indian Institute of Science, A79-49070 Helmet mounted display and sight develop- Bangalore, India). In: American Helicopter Society, Annual National ment. C. J. G. Lewis (Marconi Avionics, Inc., Atlanta, Ga.). In: Forum, 35th, Washington, D.C., May 2123, 1979, Proceedings. American Helicopter Society, Annual National Forum, 35th, Wash- Washington, D.C., American Helicopter Society, . 23, 1979, Proceedings. ington, D.C., May 21 1979. 11 p. 13 refs. )AHS 79-20) Washington, D.C., American Helicopter Society, 1979. 14 p. (AHS The effects of dynamic inflow perturbations are incorporated 79-17) into a flap-lag stability analysis of a rigid blade. The concept of Three helmet mounted systems to provide data to the pilot equivalent Lock number, previously used to model the effect of flying head up in nap of the earth (NAP) and at night are examined. quasi-steady inflow for flapping only, is extended to the case of The pipelite system avoids the mass, thermal and high voltage coupled flap-lag motions by the addition of an equivalent profile disadvantages of mounting a cathode ray tube system directly on the drag coefficient. Plots of flap and lead-lag damping are presented for helmet by an airframe cathode ray tube and optics, and data is various inflow assumptions including: no dynamic inflow, quasi- projected into a coherent fiber optic bundle which brings the light to steady momentum theory, unsteady momentum theory, empirical an optic mounted on the pilot's helmet. The helmet optical position inflow, and equivalent Lock number and drag coefficient. The results sensing system, HOPS, uses pulsed infrared emitting diodes mounted show that dynamic inflow has a large effect on blade damping for the on the helmet. Their output is detected by airframe mounted, charge regressing mode. In some instances, this effect can be modeled by the coupled devices using V/slit pinhole cameras. The system is free from equivalent Lock number and drag coefficient. (Author) electromagnetic interference and provides half degree line of sight accuracies. Data for simple sighting and management tasks is provided with a visor projection optics and a high brilliance light emitting diode (LED) addressable matrix with a large viewing A79-49074 Evaluation of the practical aspects of vibration aperture. A. T. reduction using structural optimization techniques. H. W. Hanson (Bell Helicopter Textron, Fort Worth, Tex.) and N. J. Calapodas (U.S. Army, Aviation Research and Development Command, Fort A79-49071 Experimental measurements of the rotating Eustis, Va.). In: American Helicopter Society, Annual National frequencies and mode shapes of a full scale helicopter rotor in a Forum, 35th, Washington, D.C., May 21-23, 1979, Proceedings. vacuum and correlations with calculated results. B. L. Lee (NASA, Washington, D.C., American Helicopter Society, Langley Research Center, Hampton, Va.). In: American Helicopter 1979. 13 p. 6 refs. Grant No. DAAK51-78-C-001 1. )AHS 79-21) Society, Annual National Forum, 35th, Washington, D.C., May The results of a practical evaluation of two structural optimiza- 21-23, 1979, Proceedings. - Washington, D. C., tion techniques for vibration reduction, the Vincent circle method American Helicopter Society, 1979. 14 p. 5 refs. )AHS 79-18) and the forced response strain energy method, are discussed. An This paper presents results of an experimental program con- elastic line mathematical model of the AH . 1G helicopter was used ducted to obtain data which can be used for correlations of rotor for initial comparison studies of she two methods and for evaluating blade dynamic analyses. Measurements were made of the rotating the Vincent circle method with respect to mass changes and damping frequencies and mode shapes of a representative full-scale, two- effects. The forced response strain energy method was selected for bladed helicopter rotor in a vacuum. The blades were cantilevered to vibration reduction of a large complex built-up Nastran AH-1G the hub. Mode shape data were obtained optically using a system of model through structural stiffness optimization. It is noted that cameras developed specifically for this purpose. Excitation of the while the Vincent circle method is useful in predicting optimum rotor was provided by vertical oscillatory motion of the hub. To locations of dynamic absorbers for vibration reduction, for more

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detailed analysis the damp forced response strain energy method has changes using simple hand calculations. A computer program is the potential benefit of rapid evaluation and optimization of discussed which allows the user to select from a variety of helicopter structural vibratory response. V.T. and control system math models and presents output in either the time or frequency domain. Finally, correlation with flight test data is shown, and results of control cross coupling and gust sensitivity studies are presented, M.E.P. A79-49075 Full scale ground and air resonance testing of the Army-Boeing Vertol Bearingless Main Rotor. J. A. Staley, R. A79-49078 • # Piloted simulator investigation of helicopter Gabel (Boeing Vertol Co., Philadelphia, Pa.), and H. I. MacDonald control systems effects on handling qualities during instrument (U.S. Army, Applied Technology Laboratory, Fort Eustis, Va.). In: flight R. D. Forrest (FAA, Washington, D.C.), R. T. N. Chen, R. M. American Helicopter Society, Annual National Forum, 35th, Wash- Gerdes, T. S. Alderete, and D. R. Gee (NASA, Ames Research ington, D.C., May 21 . 23, 1979, Proceedings. Center, Moffett Field, Calif.). In: American Helicopter Society, Washington, D.C., American Helicopter Society, 1979. 14 p. 10 refs. Annual National Forum, 35th, Washington, D.C., May 21-23, 1979, )AHS 79-23) Proceedings. Washington, D.C., American Heli- This paper presents ground and air resonance test results for full copter Society, 1979. 27 p. 12 refs. (AHS 79-26) scale tests of the Boeing Vertol . Army Bearingless Main Rotor )BMR) An exploratory piloted simulation was conducted to investigate flown on a 136 . 105 helicopter. The BMR has the advantage of the effects of the characteristics of helicopter flight control systems simplicity due to elimination of the pitch bearing and the flap and on instrument flight handling qualities. This joint FAA/NASA study lag hinges used in articulated rotor designs. This results in potential was motivated by the need to improve instrument flight capability. A improvements in performance, reliability and life cycle costs. The near-term objective is to assist in updating the airworthiness criteria aircraft was tested for ground and air resonance damping at for helicopter instrument flight. The experiment consisted of conditions which were expected to be critical, including level flight, variations of single-rotor helicopter types and levels of stability and climbs, descents, maximum power dives, and autorotations; in control augmentation systems (SCAS). These configurations were addition, testing during loads evaluations included banked turns, evaluated during an omnirange approach task under visual and pull-ups, and push-overs. The aircraft encountered no air resonance instrument flight conditions. The levels of SCAS design included a mode instabilities during any of these flight conditions. Initial testing simple rate damping system, collective decoupling plus rate damping, disclosed that ground resonance mode damping had to be improved and an attitude command system with collective decoupling. A by stiffening the existing landing gear skid. Analytical results are also limited evaluation of stick force versus airspeed stability was presented which were used in developing the rotor design and in accomplished. Some problems were experienced with control system preparing the flight test procedures. Model rotor test results are also mechanization which had a detrimental effect on longitudinal shown which gave an accurate preview of what was to have been stability. Pilot ratings, pilot commentary, and performance data (Author) expected during full scale flight testing. related to the task are presented. )Author)

A79-49079 Development of a fly-by-wire elevator for the Bell Helicopter Textron 214ST. S. W. Ferguson and K. E. Builta (Bell 479-49076 Spirit helicopter handling qualities design and Helicopter Textron, Fort Worth, Tex.). In: American Helicopter development. G. P. Wright and N. Lappos (United Technologies Society, Annual National Forum, 35th, Washington, D.C., May Corp., Sikorsky Aircraft Div., Stratford, Conn.). In: American 21-23, 1979, Proceedings. Washington, D.C., Helicopter Society, Annual National Forum, 35th, Washington, D.C., American Helicopter Society, 1979. 19 p. )AHS 79-27) May 21 .23, 1979, Proceedings. Washington, The Bell 214ST helicopter is an extended version of the D.C., American Helicopter Society, 1979. 12 p. )AHS 79-24) single-engine Bell 214 and is powered by two General Electric CT7-2 The design and development of the Spirit (S-76) helicopter are engines. A fly-by-wire (FBW) elevator system is developed for the reviewed. A design and development program included preliminary 214ST helicopter. Considerable insight is gained in handling qualities, design, developmental model and wind tunnel testing, computer testing techniques, and elevator-related aerodynamics during the simulation, and a developmental flight test program. Particular design development of the 214ST FBW elevator. Significant handling features, such as a fixed, low horizontal stabilizer, main rotor qualities improvements, as compared with those available in Bell pitch/flap coupling, pitch bias actuator, mechanical control coupling, helicopters using conventional elevator control systems, are demon- and stability augmentation are described. It is shown that the strated in pitch attitude control, longitudinal static stability, trim helicopter handling quality design depended heavily on simulation change with power, and damping of long-period longitudinal oscilla- model results. Reliance on simulation resulted in few developmental tions. The availability of a pilot-controlled elevator mode during changes after the first flight. Test data accumulated for the testing provided the opportunity to acquire previously unavailable simulation model, and simulation correlation with tests are also static and dynamic stability derivative data. Other valuable data presented. V.T. allowed further understanding of the airframe-elevator aerodynamic relationship, as well as the aerodynamic characteristics of the elevator pitching moment. S. D.

A79-49077 Improved method of predicting helicopter 479-49080 Advanced Scout Helicopter flying qualities control response and gust sensitivity. F. White and B. B. Blake requirements - How realistic are they. D. M. Pitt and F. E. Heacock (Boeing Vertol Co., Philadelphia, Pa.). In: American, Helicopter (U.S. Army, Aviation Research and Development Command, St. Society, Annual National Forum, 35th, Washington, D.C., May Louis, Mo.). In: American Helicopter Society, Annual National 21-23, 1979, Proceedings. Washington, D.C., Forum, 35th, Washington, D.C., May 21-23, 1979, Proceedings. American Helicopter Society, 1979. 12 p. 6 refs. )AHS 79-25) Washington, D.C., American Helicopter Society, The paper presents the results of studies performed using 1919. 14 p. 24 refs. )AHS 79-28) recently devIoped analytical models correlated with flight test data The proposed mission profile and handling qualities require- to better understand the effects of rotor and aircraft configuration ments for the Army's Advanced Scout Helicopter )ASH) are on flying qualities. Attention is given to low speed control trim examined. The results of the AAH and UTTAS competitive testing change, gust sensitivity and interaxis coupling. A theory is given are used as a basis to define the state-of-the-art helicopter handling which has been developed to predict rotor trim changes resulting qualities, and what can realistically be expected from the ASH. from nonuniform downwash effects. It is shown that the approach Results of testing of various Army helicopters in simulated ASH combines fixed wing lifting line theory with simple classical rotor maneuvers are used to justify the ASH postulated handling qualities equations and allows rapid estimation of parametric effects and trim requirements. Army testing of ASH-type mission equipment and

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requirements on fielded Army helicopters and their effects on the A79.49084 Determining the contour of helicopter rotor stability of the know', helicopter are used to rationalize expected blades automatically using electro-optical techniques. A. Pellman ASH stability. (Author) (Dreyfus-Pellmsn Corp., Stamford, Conn.( and T. J. Pojeta (U.S. Army, Aviation Research and Development Command, St. Louis, A79-49081 Handling quality and display requirements for Mo.), In: American Helicopter Society, Annual National Forum, low speed and hover in reduced flight visibility. R. H. Hoh and I. L. 35th, Washington, D.C., May 21 . 23, 1979, Proceedings. Ashkenas (Systems Technology, Inc., Hawthorne, Calif.). In: Ameri- Washington, D.C., American Helicopter Society, 1979. can Helicopter Society, Annual National Forum, 35th, Washington, 17 p. Grant No. DAAK50-78. C.0008. (AHS 79.32) D.C., May 21-23, 1979, Proceedings. Washing- The design of a noncontacting electrooptical system that ton, D.C., American Helicopter Society, 1979. 13 p. 24 refs. (AHS automatically measures the contour of helicopter blades is presented. 79.29) An experimental model of an electrooptical range finder was also A classification scheme has been developed to account for designed, fabricated, and tested. To test contouring accuracy, outside visual cues and cockpit displays in determining the required measurements were made electrooptically at eighty-seven points on equivalent system forms for low speed and hover. Tentative criteria the surface of four sample helicopter rotor blades. In order to check are presented in terms of a visibility scale which quantifies the accuracy of these noncontact electrooptical contour measure- environmental conditions for the intended mission in a more ments, mechanical-contact gauge measurements were also made on fine-grained manner than simply specifying IMC or VMC. There are the same sample rotor blades. Contouring test measurements were indications that rate and attitude systems may be used for partial also made on partially painted translucent fiberglass and black- IMC conditions but that a translational rate command (TAC) system rubber-coated rotor blades in order to determine how light penetra- is required for low speed and hover in zero visibility. In general, most tion at the rotor surface and low reflectance would affect contour experiments indicate that advanced displays are not a substitute for measu rements. V.T. augmentation. Tentative limiting conditions are defined for rate and attitude systems, but more data are required to define handling qualities for TAC systems. Since the existing data base is primarily A79.49085 Superplastic forming diffusion bonding of oriented toward command/response characteristics, definition of the titanium helicopter airframe components. B. A. Burroughs (Rockwell limiting conditions for turbulence and large discrete wind shears also International Corp., Military Aircraft Div., El Segundo, Calif.) and N. requires more data. (Author) J. Mocerino (Hughes Helicopters, Culver City, Calif.). In: American Helicopter Society, Annual National Forum, 35th, Washington, D.C., May 21-23, 1979, Proceedings. Washington, D.C., American Helicopter Society, 1979. 6 p. (AHS 79-33) A79-49082 Role of Numerical Control Design in the Titanium fabrication combining superplastic forming (SPF( with computer aided design/manufacturing interface at Sikorsky. G. 0. concurrent diffusion bonding (DB( to reduce fabrication costs and Pranspill (United Technologies Corp., Sikorsky Aircraft Div., Strat- titanium helicopter airframe weight is considered. Superplasticity in ford, Conn.(. In: American Helicopter Society, Annual National titanium which produces large tensile elongations without local Forum, 35th, Washington, D.C., May 21 . 23, 1979, Proceedings. thinning is discussed, noting the application of the SPF/DB process Washington, D.C., American Helicopter Society, for multiple sheet fabrication of the 5 by 8 ft expanded sandwich 1979. 9 p. (AHS 79.30) B. 1 aircraft engine access door. The cost and weight savings of this The evolution of Numerical Control Design (Engineering) process led to production-type helicopter components for advanced function from its beginningsin graphic lofting/lines layout/master helicopter YAH-64 with a part count reduction up to 30% and dimensions to its current pivotal position within the aircraft proportional cost savings. Three candidates were selected for SPF/DB design/manufacturing process is described. The development and design evaluation: (1) the aluminum H/C bonded catwalk bridge application of many sophisticated computerized hardware and assembly over the engine driveshaft, (2) the aluminum skin/stringer software systems currently in operation are outlined. These include mechanically fastened engine-nacelle door/work platform, and (3) interactive graphics, automated drafting and digitizing, demand batch the primary engine firewall, which is currently a built-up titanium processing and a greatly enhanced APT III system for design/draft- sheet-stiffener assembly with mechanically fastened engine mounts. ing/lofting. The integration of sheet metal layout and template/tool Further design optimization is expected to increase cost/weight design within the Numerical Control Design function is shown savings, prior to initial production fabrication. A.T. resulting in the output of a wide variety of tool drawings for downstream manufacturing requirements which are illustrated. How these improved interfaces with preliminary and production design A79-49086 Metal-matrix composite structures. R. L. and with manufacturing operations and quality assurance coupled Pinckney (Boeing Vertol Co.. Philadelphia, Pa.), In: American with the increased efficiencies of the above systems have resulted in Helicopter Society, Annual National Forum, 35th, Washington, D.C., substantial cost and lead time savings in the development of May 21 .23, 1979, Proceedings, Washington, prototype and production aircraft are demonstrated, (Author) D.C., American Helicopter Society, 1979. 8 p. 6 refs, Army- supported research. )AHS 79.34) A design engineering program and fabrication technology development to produce and evaluate complex, high-modulus, A79-49083 Model 206L composite litter door. D. Crist fiber-stabilized cast magnesium structure is presented. The intro- (Bell Helicopter Textron, Fort Worth, Tex.(. In: American Helicop- duction of an aluminum oxide, continuous-length, high-modulus ter Society, Annual National Forum, 35th, Washington, D.C., May fiber and its physical and chemical compatibility with molten 21-23, 1979, Proceedings. Washington, D.C., aluminum and magnesium alloys made feasible a new direct-casting American Helicopter Society, 1979. 11 p. (AHS 79.31) method of producing high-modulus metal-matrix composite ma- This paper describes a program to design and manufacture a terials. Structural load tests of the CH-47 helicopter main transmis- composite door. The door selected was the litter door of the Bell sion case produced by this method demonstrated that lower Model 206L. A new manufacturing process was developed for curing deflections under load are achievable. Analysis of the results indicate the door in a single cure cycle in a closed cavity tool by using air that better control of component location should provide increased pressure inside the hollow sections, but without an internal pressure life, reduced vibration and attendant noise. It was shown that new bag. The composite door developed is an all-Keviar/epoxy design magnesium investment-casting technology can produce void-free which is cured in a Kevlar/epoxy bond tool. The resulting composite composites containing aligned and cross-plied continuous fibers up to door is 37 percent lighter than the baseline aluminum door. Cost, 55% by volume, and that direct-cast metal-matrix composite Struc- weight, appearance and manufacturing aspects are discussed and tures can be fabricated and effectively used to stiffen complex compared to the production aluminum door. (Author) helicopter structures. A. T.

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A79.49087 Automatic scanning inspection of composite May 21 . 23, 1979, Proceedings. Washington, helicopter structure using an advanced technology fluoroscopic D.C., American Helicopter Society, 1979. 9 p. 8 refs. (AHS 79-38) system. R. H. Porter and B. J. Hunter (Bell Helicopter Textron, Fort This paper discusses the performance benefits and limitations of Worth, Tex.). In: American Helicopter Society, Annual National a rotorshaft torquemeter, surveys some methods of measuring Forum, 35th, Washington, D.C., May 21-23, 1979, Proceedings. rotorshaft torque and presents some thoughts on using the rotorshaft Washington, D.C., American Helicopter Society, torque measurement. The performance benefits follow from re- 1979. 6 P. )AHS 79.35) moving the power penalty imposed by using engine torque measure- This paper discusses the fluoroscope system that was recently ment to limit rotor torque. Engine torque measurement provides no installed at Bell Helicopter Textron (BHT). Included are some of the information of-i power diversion to accessories or the tail rotor. The capabilities of the image intensifying tube and the video image greatest performance benefits occur during high-power high- processor that enhances the image signal prior to presentation on gross-weight hover situations, such as pickup and delivery of heavy sling three different monitors; a high resolution black and white monitor, loads. Four currently-used methods of torque measurement in a pseudo three-dimension image monitor and a color monitor with helicopters are reviewed including hydraulic pressure, toothed wheel variable color density slicing features. This fluoroscope system has all phase displacement, material property change and telemetered strain of the video image enhancement features incorporated to compen- gage systems. The p ilots' workload and skill requirement can be sate for the slight losses of sensitivity and resolution still inherent in reduced by using a rotorshaft sorquemeter to produce an audible the image intensifying tubes of today. (Author) warning signal, to provide maximum continuous power to the rotor, to accumulate torque/time events and to limit the maximum torque that can be applied. )Author)

A79.49088 Computer-assisted high-speed balancing of T53 and T55 power turbines. T. J. Pojeta (U.S. Army, Aviation Research A79-49091 Self-contained grease lubrication systems for and Development Command, St. Louis, Mo.) and T. J. Walter aircraft applications. A. S. Irwin, C. F. Iriglee, and J. W. Lenski, Jr. (Mechanical Technology, Inc., Latham, N.Y.). In: American Heli- (Boeing Vertol Co., Philadelphia, Pa.). In: American Helicopter copter Society, Annual National Forum, 35th, Washington, D.C., Society, Annual National Forum, 35th, Washington, D.C., May May 21 . 23, 1979, Proceedings. Washington, 21-23, 1979, Proceedings. Washington, D.C., D.C., American Helicopter Society, 1979. 9 p. 9 refs. NASA- American Helicopter Society, 1979. 7 p. IAHS 79-391 supported research. (AHS 79-36) The need for add-on, self-sufficient systems, together with Standard overhaul procedures for U.S. Army helicopter engines simplified existing helicopter components that are lighter in weight require operational vibration acceptance testing after rebuild. En- and require less maintenance, create an effort directed toward gines frequently experience vibrations which exceed allowable ingenious concepts. This paper directs attention toward one such overhaul work requirement limits. The rework/retest cycle for these add-on, an infrared suppressor and its self-contained bearing/grease engines constitute a significant cost penalty to the overhaul center. lubrication system. Against the requirements for self-contained This paper reviews both analytical and test data which indicate lubrication systems in helicopter and aircraft bearing support bending critical speeds within the operating speed range of the applications, the design principles and concepts, development, and low-speed power turbine rotor as the cause of most test cell demonstration of grease cavities for antifriction bearings are de- rejections. High-speed balancing techniques are applicable and are scribed. (Author) capable of significantly reducing this reject rate. A complete prototype computer-assisted high-speed balancing system for as- sembled T53 and T55 power turbine rotors is described. (Author)

A79-49092 Ground test vehicle testing. H. D. Jones (U.S. Army, Aviation Research and Development Command, St. Louis, Mo.). In: American Helicopter Society, Annual National Forum, A79.49089 The influence of engine/fuel control design on 35th, Washington, D.C., May 21-23, 1979, Proceedings. helicopter dynamics and handling qualities. W. A. Kuczynski, D. E. Washington, D.C., American Helicopter Society, 1979. Cooper, W. J. Twomey, and J. J. Howlett (United Technologies 4 p. (AHS 79-40) Corp., Sikorsky Aircraft Div., Stratford, Coon.). In: American The paper discusses the philosophy behind the requirements for Helicopter Society, Annual National Forum, 35th, Washington, D.C., GTV (ground test vehicle) testing and objectives and the value of May 21-23, 1979, Proceedings. Washington, GTV testing. It is shown that not only is the GTV used for the D.C.-Am * erican Helicopter Society, 1979. 14 p. 7 refs. )AHS 79.37) purpose of qualifying certain subsystems, but also to perform The aper examines the compatibility of the engine/fuel control investigative or design support tests on a particular subsystem prior with helicopter rotor and airframe dynamics in the torsional sense at to or during flight testing. It is noted that while bench testing only frequencies below the rotor rotational speed. Consideration is given tests the individual components, GTV testing qualifies the to the characteristics: torsional stability, transient response (droop) components on the system /subsystem level, thus exposing potential and handling qualities of the helicopter. Studies have shown that the problem areas before actual flight tests begin. Finally, it is concluded transient response in the rotor speed degree of freedom is affected by that GTV testing is an essential part of the total aircraft qualification the state of the rotor aerodynamics during the condition of high effort. M.E.P. torque demand. It is also shown that she engine/fuel control system can influence the damping in the aircraft handling qualities modes. These interactions are described, drawing upon both flight test A79-49093 Application of finite-element and holographic experience and analysis. A flight dynamics simulation, GENHEL, is techniques in the design of tu rboshaft engine components. P. S. Kuo used for this analysis and results are presented which show the (Avco Corp., Avco Lycoming Stratford Div., Stratford, Conn.). In: potential of using body state feedback to the fuel control to enhance American Helicopter Society, Annual National Forum, 35th, M.E.P. aircraft handling qualities and rotor droop characteristics. Washington, D.C., May 21-23, 1979, Proceedings. Washington, D.C., American Helicopter Society, 1979. 13 p. 7 refs. (AHS 79-41) A comprehensive finite element method using various types of A79-49090 Rotorshaft torquemeter. R. B. Bossier, Jr elements and approaches to model a vast variety of engine )Kaman Aerospace Corp., Bloomfield, Conn.). In: American Heli components is described. Illustration includes the vibration and stress copter Society, Annual National Forum, 35th, Washington, D.C. analyses of the centrifugal impeller, compressor and turbine blades,

631 A79-49094 mechanical gearing and rotor disk assembly. Facilitated by the Tests and operation of a composite horizontal stabilizer for the automated 2D/3D model generators and the graphic presentation of Sikorsky Spirit helicopter are reviewed. Stabilizer materials and the results, a rapid evaluation of candidate designs is achieved. Construction are described, noting that the skins are Kelvar/epoxy Holography has been utilized as an effective means to determine the over Nomex honeycomb, with graphite/epoxy spar Caps and a dynamic behavior, the natural frequency and mode shape of the Kelvar/epoxy torque tube. Complete assemblies consisting of a components; it consequently provides a verification for designs when stabilizer assembly, stabilizer support fitting, and intermediate gear hardware is available. Examples of holograms are given herein to be support fitting were tested. Following accelerated fatigue testing, compared with the theoretical results. (Author) stabilizers were loaded statically to failure. During 1050 flight-test hours the stabilizer was exposed to a hot, humid climate and extreme A79.49094 Development of a 'no adjustment' turboshaft cold temperatures. The test results show that the Spirit stabilizer has engine control system. J. J. Curran and A. M. Levine (General an unlimited life with high static residual strengths. V. T. Electric Co., Aircraft Engine Group, Lynn, Mass.). In: American Helicopter Society, Annual National Forum, 35th, Washington, D.C., A79-49098 Design and development of a hybrid com- May 21 .23, 1979, Proceedings. Washington, posite rotor blade for the circulation control rotor system. G. A. D.C., American Helicopter Society, 1979. 11 p. (AHS 79-42) McCoubrey (Kaman Aerospace Corp., Bloomfield, Conn.). In: The paper describes the T700-GE-700 gas turbine engine which American Helicopter Society, Annual National Forum, 35th, Wash- has been designed to eliminate the need for traditional adjustments ington, D.C., May 21-23, 1979, Proceedings. and riggings to provide aircraft/engine/control system matching. Washington, D.C., American Helicopter Society, 1979. 10 p. (AHS Attention is given to the adjustments that have been eliminated; 79-46) these are: topping, ground idle, power turbine speed governing, load The paper presents the design and development of a hybrid sharing, torque computation, power available spindle, load demand composite (graphite and S-glass) circulation control rotor blade spindle, variable geometry rigging, and specific gravity adjustment. (CCR). The CCR system requires rotor blades with a thin slot located Finally, a review of factory and field experience and acceptability of on the upper surface near the trailing edge. The blade design the 'no adjustment' system is presented. M.E.P. characteristics, structural dynamic properties, blade materials, manu- facturing process, hybrid composites, and structural testing are discussed. It is shown that by utilizing the additional design freedom A79-49095 Certification of composites in civil aircraft. R. provided by the hybrid composite (i.e. fiber orientation, mix ratio, Allen and J. R. Soderquist (FAA, Engineering and Manufacturing and level of interleaving), it is possible to satisfy strength, bending Div., Washington, D.C.). In: American Helicopter Society, Annual stiffness, torsional stiffness, weight, and fabrication process con- National Forum, 35th, Washington, D.C., May 21 .23 1979, Proceed- straints. It is concluded that hybrid composite construction permits ings. Washington, D.C., American Helicopter advances in design optimization for accomodation of engineering and Society, 1979. 7 p. 5 refs. (AHS 79.43) manufacturing constraints. A.T. Certification of composite structure for use on civil rotary wing aircraft involves showing compliance with Federal Aviation Regula- tions, FAR 29 for transport rotorcraft and FAR 27 for small A79-49100 The Sikorsky elastomeric rotor. R. C. Rybicki rotorcraft, with guidance material provided in the FAA Advisory (United Technologies Corp., Sikorsky Aircraft Div., Stratford, Circular 20. 107. The requirements of primary concern in the civil Conn.). In: American Helicopter Society, Annual National Forum, certification of composite rotary wing structure are discussed in 35th, Washington, D.C., May 21-23, 1979, Proceedings. detail. The paper provides examples of civil applications of com- Washington, D.C., American Helicopter Society, 1979. posites and summarizes the overall in-service performance with these 14 P. (AHS 79-48) applications. S. D. The paper surveys the development of the Sikorsky elastomeric rotor. Attention is given to improvements made in the design and arialyit techniques employed for elastomeric bearings. It is noted that finite element methods have been developed which can handle the A79-49096 Qualification program of the composite main large strain, non-linear material, non-axisymmetric loading problems rotor blade for the Model 214B helicopter. D. J. Reddy (Bell involved. Developments are the resulting improvements are discussed, Helicopter Textron, Fort Worth, Tex.). In: American Helicopter as well as testing procedures. Finally it is stressed that initial field Society, Annual National Forum, 35th, Washington, D.C., May problems have been minimal. M.E.P. 21-23, 1979, Proceedings. Washington, D.C., American Helicopter Society, 1979. 9 p. (AHS 79-44) Extensive fatigue testing of coupons and structural elements and A79-49101 Helicopter component environmental vibra- full scale blade testing were accomplished for a composite main rotor tion testing - The poor man's fatigue test. S. T. Crews (U.S. Army, blade of the Model 214B helicopter. Data from the coupon and Aviation Research and Development Command, St. Louis, Mo.). In: element tests were used to establish S.N curve shapes, environmental American Helicopter Society, Annual National Forum, 35th, Wash- effects, and fatigue strength data for such materials as S-glass and ington, D.C., May' 21-23, 1979, Proceedings. E-glass introduced in the blade. Also, a statistical analysis was Washington, D.C., American Helicopter Society, 1979. 8 p. (AHS performed on coupon and element data to find minimum scatter 79-49) reduction for these materials. The mean S-N curves established by It is found that the Army can no longer rely on the current the results of testing the full scale blade fatigue test specimens were version of MIL-STD-810 for helicopter environmental vibration reduced for scatter and an additional reduction for environmental qualification testing of major helicopter equipment. The Systems effects was taken as indicated by the results of the coupon and Development and Qualification Division of AVRADCOM, in con- structural element tests. It is shown that the coupon tests provided junction with several manufacturers, has recently developed specific reliable strength values compared with the full scale test data. V. T. component environmental vibration qualification tests for major pieces of equipment. These tests were derived from the results of A79-49097 Operation and test of composite horizontal preliminary flight testing of these components. B.J. stabilizer for the Sikorsky Spirit helicopter. J. D. Ray (United Technologies Corp., Sikorsky Aircraft Div., Stratford, Conn.). In: American Helicopter Society, Annual National Forum, 35th, Wash- A79-49102 Realization of a helicopter-oriented real-time ington, D.C., May 21-23, 1979, Proceedings. data system for research, experimental, and prototype flight testing. Washington, D.C., American Helicopter Society, 1979. 12 p. (AHS K. Lunn, C. Hutchinson (Boeing Vertol Co., Philadelphia, Pa.), and J. 79-45) Obbard (Raytheon Service Co., Boston, Mass,). In: American

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Helicopter Society, Annual National Forum, 35th, Washington, D.C., Textron, Fort Worth, Tex.), J. A. Weiberg (NASA, Ames Research May 21-23, 1979, Proceedings. Washington, Center, Moffett Field, Calif.(, and L. G. Schroers (U.S. Army, D.C., American Helicopter Society, 1979. 13 p. (AHS 79-50) Aeromechanics Laboratory, Moffett Field, Calif.). In: American A real-time data analysis system currently operational in the Helicopter Society, Annual National Forum, 35th, Washington, D.C., helicopter flight test industry is considered. The paper discusses the May 21-23, 1979, Proceedings. Washington, developments over a 20-year period which culminated in a combina- D.C., American Helicopter Society, 1979. 12 p. (AHS 79-54) tion of airborne and ground-based data systems for computational The XV-15 Tilt Rotor Research Aircraft Project involves design, analyses to produce plots, tabulations, and summaries for report fabrication, and flight testing of two aircraft. This program is purposes. The evolution of the STAR (simulation and test analysis in currently in the test phase for concept evaluation and substantiation real time) system, appropriate software, and increases in productiv- of design. As part of this evaluation, one of the aircraft was tested in ity, and the data base which stores calculated engineering values for a the NASA-Ames 40- by 80-foot wind tunnel. The status of testing to flight test program, and allows merging cross-plotting, and fatigue date and some of the results of the wind tunnel and flight tests are damage calculations to be performed by an engineer operating from a presented. (Author) remote terminal, are described. It is concluded that the real-time data system, combined with an airborne data acquisition system, resulted in improved flight test productivity, data quality, and reduced cost, and used as a multipurpose computer, benefits can be attained in A79-49106 Analytical and experimental investigation of simulation, engineering batch, and terminal job entry. A.T. V-type empennage contribution to directional control in hover and forward flight. C. F. Freeman and W. T. Yeager, Jr. (U.S. Army, Structures Laboratory, Hampton, Va.). In: American Helicopter Society, Annual National Forum, 35th, Washington, D.C., May A79.49103 The circulation control rotor flight demonstra- 21-23, 1979, Proceedings. Washington, D.C., tor test program. J. B. Wilkerson (U.S. Naval Material Command, American Helicopter Society, 1979. 8 P. 12 refs. (AHS 79-56) David W. Taylor Naval Ship Research and Development Center, Experimental investigations were conducted to determine the Carderock, Md.), D. R. Barnes, and F. A. Bill (Kaman Aerospace source of direction control problems of single main-rotor helicopters Corp., Bloomfield, Conn.(. In: American Helicopter Society, Annual operating at low speeds and possible means to alleviate them were National Forum, 35th, Washington, D.C., May 21-23, 1979, Proceed- examined. Tests proved that the V-type empennage presents signifi- ings, Washington, D.C., American Helicopter cant low speed directional control advantages over conventional tail Society, 1979. 15 p.7 refs. IAHS 79-511 surface arrangements while providing comparable levels of static The circulation control rotor (CCR) technology demonstrator, stability in both high- and low-speed flights. It was concluded that XH-2/CCR, has undergone many phases of structural, pneumatic, (1) the aerodynamic characteristics of V-tails are affected by and aerodynamic tests, leading to the flight demonstration. A low-aspect-ratios and 121 that the nonsymmetric V-tail surfaces description of XH-2/CCR is provided with brief descriptions of the decrease the tail rotor power required at low advance ratios by using major tests conducted. Results of pneumodynamic tests of the the rotor-wake swirl to induce a torque counter to the main rotor compressor and control system are presented. Emphasis is placed on torque. C.F.W. performance results from the whirl stand and from the NASA Ames 40- by 80-foot wind tunnel. Correlation between wind tunnel data and theory is also shown. A good agreement was evident over the A79-49107 Design, analysis, and testing of a new genera- flight spectrum for the first full-scale CCR. (Author) tion tail rotor. K. W. Harvey and C. W. Hughes )Bell Helicopter Textron, Fort Worth, Tex.). In: American Helicopter Society, Annual National Forum, 35th, Washington, D.C., May 21-23, 1979, A79-49104 # Flight investigation of helicopter IFR Proceedings. Washington, D.C., American Heli- approaches to oil rigs using airborne weather and mapping radar. J. S. copter Society, 1979. 11 p. 8 refs. )AHS 79-57) Bull, D. M. Hegarty, J. D. Phillips, W. R. Sturgeon (NASA, Ames The development of a two-bladed teetering tail rotor without Research Center, Moffett Field Calif.), A. W. Hunting, and D. P. Pate pitch-change bearings is described. The design uses a fiberglass (FAA, Flight Standards National Field Office, Oklahoma City, twist-Strap flexure to accommodate collective pitch control, and Okla.). In: American Helicopter Society, Annual National Forum, features the elimination of the shear-reaction device for counter- 35th, Washington, D.C., May 21-23, 1979, Proceedings. acting the pitch link load. The design of the rotor was based on the Washington, D.C., American Helicopter Society, 1979. results of earlier model tests and stability analyses. Wind tunnel tests 10 P. (AHS 79-52) were conducted with the rotor installed on a flightworthy tailboom. Airborne weather and mapping radar is a near-term, economical The design concept was demonstrated satisfactorily by testing the method of providing 'self-contained' navigation information for tail rotor through the entire flight spectrum of the Jetftanger test approaches to offshore oil rigs and its use has been rapidly expanding vehicle. )Author) in recent years. A joint NASA/FAA flight test investigation of helicopter IFR approaches to offshore oil rigs in the Gulf of Mexico A79-49108 Ten years of Aérospatiale experience with the was initiated in June 1978 and conducted under contract to Air fenestron and conventional tail rotor. R. Mouille (Société Nationale Logistics. Approximately 120 approaches were flown in a Bell 212 Industrielle Aérospatiale, Marignane, Bouches-du-Rhône, France(. In: American Helicopter Society, Annual National Forum, 35th, Wash- helicopter by 15 operational pilots during the months of August and September 1978. The purpose of the tests was to collect data to (1) ington, D.C., May 21-23, 1979, Proceedings. support development of advanced radar flight director concepts by Washington, D.C., American Helicopter Society, 1979. 10 p. (AHS NASA and 121 aid the establishment of Terminal Instrument 79-58) Procedures (TERPS) criteria by the FAA. The flight test objectives The improvements which have been made during the past few were to develop airborne radar approach procedures, measure years in the design of both fenestron and conventional tail rotors are tracking errors, determine accpetable weather minimums, and deter- reviewed. For conventional tail rotors, novel airfoils and high twist mine pilot acceptability. Data obtained will contribute significantly values have resulted in an increase in figure of merit from 0.5 to to improved helicopter airborne radar approach capability and to the above 0.7. For fenestron rotors, higher efficiencies have been support of exploration, development, and utilization of the Nation's obtained, owing to improved aerodynamics, resulting from optimiza- tion of airfoils and blade twist angles and revised shroud designs. V.P. offshore oil supplies. (Author)

A79-49105 Wind tunnel and flight test of the XV-15 Tilt A79-49109 Interactional aerodynamics - A new challenge Rotor Research Aircraft R. L. Marr, S. Blackman (Bell Helicopter to helicopter technology. P. F. Sheridan (Boeing Vertol Co.,

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Philadelphia, Pa.) and R. P. Smith )U.S. Army, Applied Technology Institute of Aeronautics and Astronautics, Aircraft Systems and Laboratory, Fort Eustis, Va.). In: American Helicopter Society, Technology Meeting, New York, N. Y., Aug. 20-22, 1979, Paper Annual National Forum, 35th, Washington, D.C., May 21-23, 1979, 79-1795. 19 P. Contract No. NAS1-14742. Proceedings. Washington, D.C., American Heli- The energy and economic benefits of low-speed aerodynamic copter Society, 1979. 16 p. 5 refs. )AHS 79.59) system technology applied to a modern 200-passenger, 20001nmi The paper describes the field of interactional aerodynamic range, twin engine jet transport are reviewed. Results of a new phenomena, classifies the problems into categories, such as down- method to design flap systems at flight Reynolds number are stream, localized, ground proximity, external interaction, and wing summarized. The study contains the airplane high lift configuration related category, and establishes a matrix of interactions and drag characteristics and design selection charts showing the effect of problems. Specific interactions are analyzed where sufficient data is flap technology on the airplane size and performance. The study available. These include the rotor/hub/fuselage/ empennage, rotor/ areas include: wing and flap geometry, climb and descent speed fuselage, main-rotor/fin/tail-rotor, rotor/ground, rotor/fuselage/ schedules with partial flap deflection, flap system technology, and ground, and tail rotor/main/rotor/ground interactions. Evident augmented stability. The results compare the improvements in trends such as flow simulation, are discussed and conclusions drawn payload from a hot, high elevation airport. (Author) regarding significant physical mechanisms. Finally, further research is recommended to expand the data base, to foster theory develop- ment, and to develop meaningful design guidelines. M.E.P. A79.49335 # Application of Lagrange Optimization to the A79.49223 The DC-9 Super 80 - Much more than a simple drag polar utilizing experimental data. J. S. Kohn (Grumman Aerospace Corp., Bethpage, N.Y.). stretch. J. P. Geddes. Interavia, vol. 34, Sept. 1979, p. 865869. American Institute of Aeronautics The general characteristics and design features of the DC-9 and Astronautics, Aircraft Systems and Technology Meeting, New Super-80 aircraft are presented. The DC-9-80 has a modified wing, a York, N. Y., Aug. 20-22, 1979, Paper 79-1833. 15 p. 14 refs. greatly improved powerplant, and a major redesign in the cockpit The Lagrange Optimization, used with linear aerodynamic using the latest avionic technology. Passenger capacities have been theory to define optimum aircraft geometry, is shown to have increased from 80 to 155 for economy class passengers and other application to the determination of optimum control surface aircraft versions have been designed, powered by two ten ton deflections as a function of angle of attack necessary to provide engines, capable of carrying up to 170 economy class passengers. maximum trimmed L/D for a multi-plane aircraft configuration. Fuselage improvements, like the horizontal stabilizer root extension Linear aerodynamic theory suggests a semi-empirical drag polar employing an anti-float tab, increase stabilizer effectiveness when the equation well suited to the optimization task. The equation is shown aircraft is in landing configuration. The layout of the instrument to correlate well with experimental data near aircraft cruise conditions. Such correlations are shown for selected aft and forward panel is given along with diagrams of the wings and flap setting. Other detailed changes in the compressor, the modular design of the swept configurations up to 0.9 Mach number both in terms of total fan, and low pressure rotor are noted and an overall performance drag and drag increments due to control deflections and angle of report is described. C.F.W. attack. Optimum trimmed configurations are defined using experi- mental data and the subject Optimization procedure. (Author)

A79-49224 Lockheed urges hydrogen fuel. Intera via, vol. 34, Sept. 1979, p. 872, 873. A79. The use of hydrogen as a future aircraft propellant is discussed 49336 # XV-15 flight test results compared with design and some advantages and disadvantages of using methane as another goals. K. G. Wernicke (Bell Helicopter Textron, Fort Worth, Tex.( alternate source are examined. Although hydrogen is seen as a and J. P. Magee (NASA, Ames Research Center; U.S. Army, Aeromechanics Laboratory, Moffett Field, Calif.). dangerous fuel source, its advantages clearly outweigh its disadvan- American Insti- tute of Aeronautics and Astronautics, Aircraft Systems and Technol- tages. First, it is noted that because hydrogen is lighter than air, a fire ogy Meeting, New York, N. Y., Aug. 20-22, 1979, Paper 79-1839. 11 ignition would tend to roar upward and not expand sideways like a p. 10 refs. liquid fuel fire. Second, hydrogen burns cleanly and consistently, Aircraft No. 2 is presently in the midst of flight envelope providing considerable benefits in the design of future power plants. expansion. Noise and safety design goals have been demonstrated; Last, its exhaust consists mainly of water and therefore a hydrogen- preliminary results indicate that performance and component life fueled engine would create even less air pollution than the cleanest of modern petroleum-burning turbofans. The only disadvantage noted goals may also be met. Hovering power indicates a standard hover ceiling of 7,000 feet. After 18.0 hours of flight, a true airspeed of here is the apparent danger because of its high combustibility, and it is concluded that hydrogen may be the best alternative to many 207 knots has been reached. The goal is a 300-knot cruise speed. So present-day energy problems. C.F.W. far, XV- 15 flight tests indicate no reason why the tilt rotor concept should not fulfill its promise to provide a major step forward in air vehicle flexibility and in rotary wing performance. (Author)

A79-49232 Blown wings from Kiev. Air International, vol A79-49337 # Design criteria for airline operation. W. J. 17, Sept. 1979, p. 140-142, 151. Overend (Delta Air Lines, Inc., Atlanta, Ga.). American Institute of The Soviet Antonov AN-72 STOL short haul transport aircraft is Aeronautics and Astronautics, Aircraft Systems and Technology examined. The aircraft employs a high lift system that resembles the Meeting, New York, N. Y., Aug. 20-22, 1979, Paper 79-1849. 7 p. upper surface blowing )USB) system adopted by Boeing for its This paper provides some of the basic airline concepts of design YC. 14 prototypes. Specifications covered include a 16,500 lb methodology and illustrates how they may be applied to the payload and a required runway length of 4000 ft. Attention is given selection of a new aircraft for service in the 1980's. Two funda- to the wing configuration which uses a combination of double- mental criteria for aircraft design are noted: (1) the optimization of slotted and triple-slotted flaps on the trailing edge and full span passenger transportation and (2) predominance of safety over leading edge slots. However, it is noted that she primary considera- operating economics. Baseline aircraft, performance capability, and engine selection are considered to give the best possible design for tion in locating the engines above the wing was the operation from providing the public with an aircraft designed for efficient airline unimproved runways. Finally, cargo loading arrangements are dis- operation. C.F.W. cussed. M.E.P.

A79.49332 # The size and performance effects of high lift system technology on a modern twin engine jet transport. R. L. A79-49338 # What the FAA would like in airworthiness Sullivan (Boeing Commercial Airplane Co., Seattle, Wash.). American standards. C. R. Foster (FAA, Washington, D.C.). American Institute

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of Aeronautics and Astronautics, Aircraft Systems and Technology Program used in the studies are discussed. Evaluation studies utilizing Meeting, New York, N. V., Aug. 20 .22, 1979, Paper 79-1851. 7 p. three convection and two combined conduction-convection problems The paper surveys the areas in which the FAA deems future are then presented and discussed. Additionally, the computational work desirable. These include the development of standards for light time saving offered by the finite element procedure is considered for transport aircraft used in commuter operations, and for advance a practical combined conduction-convection problem, V. T. types of control configured vehicles. Attention is also given to improved crashworthiness, improved engine capability to resist A79.49344 NASA/Princeton digital avionics flight test damage due to ingestion of foreign objects, and the development of facility. D. R. Downing, W. H. Bryant (NASA, Langley Research standards for operation of helicopters in IFR and icing conditions. Center, Flight Electronics Div., Hampton, Va.), and R. F. Stengel Other topics discussed are the development of wet runway stopping (Princeton University, Princeton, N.J.). Institute of Electrical and criteria, reduction of general aviation accident rate, the development Electronics Engineers and American Institute of Aeronautics and of improved standards for composite and damage tolerant structures, Astronautics, Digital Avionics Systems Conference, 3rd, Fort Worth, and the development of standards for the verification and validation Tax., Nov. 6-8, 1978, Paper. 7 p. 10 refs. of digital avionics. M.E.P. This paper describes a general-aviation digital avionics flight-test facility being jointly developed by the Flight Dynamics Laboratory of Princeton University and NASA/Langley Research Center. This facility consists of the Princeton avionics research aircraft (ARA) and A79.49339 # Effect of nozzle spacing on ground interfer- NASA/Langley's digital avionics research (DARE) system. The ARA ence forces for a two jet V/STOL aircraft. W. G. Hill, Jr. and R. C. is a fully instrumented five-degree-of-freedom fly-by-wire aircraft. Jenkins (Grumman Aerospace Corp., Bethpage, N.Y.(. American The DARE system contains a state-of-the-art flight computer system Institute of Aeronautics and Astronautics, Aircraft Systems and and receiving equipment that permits use of the NASA/Wallops Technology Meeting, New York, N.Y., Aug. 20-22, 1979, Paper Flight Center's position-tracking ground-based display-generation and 79-1856. 13 p. 20 refs. Contract No. NAS2-10097. ground-to-air digital-data-link equipment. The DARE/ARA system The effect of nozzle spacing on ground interference forces was will be used for flight evaluation of advanced control, guidance, and investigated for a two jet V/STOL aircraft design. The need for display concepts developed as part of NASA/Langley Research information on the effect of jet spacing arises because of the tradeoff Center's general aviation terminal area operations program. (Author) between mechanical complexity, which calls for close spacing, and roll control moments, which call for wider spacing. The ground A79-49345 # Characterization of a swept-strut hydrogen interference forces on a two jet V/STOL aircraft model were fuel-injector for scramjet applications. G. B. Northam, C. A. Trexler, measured for a range of nozzle spacings. Interference forces showed a and G. Y. Anderson (NASA, Langley Research Center, Hampton, complicated behavior with nozzle spacing, fuselage geometry, and Va.), Joint Army-Navy-NASA-Air Force, Interagency Propulsion height above ground. For some conditions a slight change in nozzle Committee Combustion Meeting, 15th, Newport, RI., Sept, 1978, spacing resulted in a fourfold change in the interference force from Paper. 19 p. 5 refs. 3% to 12% of the basic jet thrust. An understanding of the observed Results of an experimental investigation of a swept-strut aircraft force behavior was developed using detailed measurements of hydrogen fuel-injector simulating the center strut of a three strut the upwash flow properties, along with force and pressure measure- scramjet module at Mach 6 flight conditions are presented. Detailed ments on a series of two dimensional fuselage representations. wall pressure distributions from over 100 separate tests with overall (Author) fuel flow from 0,1 to 1.3 times stoichiometric and test gas stagnation temperature from 1100 to 2400 K were recorded. The distance for A79-49341 # Wing geometry effects on leading-edge vor- pressure rise from the point of injection was found to increase with tices, R. M. Kulfan (Boeing Commercial Airplane Co., Seattle, increasing test stagnation temperature. This trend indicates that American Institute of Aeronautics and Astronautics, Aircraft Wash.). chemical kinetics in the immediate region of perpendicular injection Systems and Technology Meeting, New York, N.Y., Aug. 2022, are not likely to be the mechanism controlling the onset of pressure 1979, Paper 79-1872. 38 45 refs. p. rise. A fluid dynamic mechanism is suggested involving separation of Leading-edge vortices that form at off-design conditions can profoundly influence the aerodynamic characteristics of highly swept the boundary layer downstream of injection which is forced slender wings. A straightforward method that can predict wing upstream from the trailing edge by pressure rise due to combustion geometry effects on the progressive spariwise development of occurring in the base region of the strut. The results obtained leading-edge vortices is presented. This method, which can account indicate that the swept-strut fuel-injector concept can be adapted to for sweep, camber, twist, airfoil shape, flap deflections, and planform a wide range of flight conditions by varying the amount of perpendicular fuel injection. shape, is shown to be a useful tool for aerodynamic design studies. It (Author) is shown that suppressing the leading-edge vortex, particularly over the inboard portion of the wing, can cause considerable reduction in A79-49348 Evaluation of airfield pavement materials drag due to lift. Results of wing geometry parametric studies are based on synthetic polymers. C. J. Hilado, D. P. Brauer (San shown. (Author) Francisco, University, San Francisco, Calif.), and R. C. Corlett (Washington, University, Seattle, Wash,). (International Conference on Fire Safety, 4th, University of San Francisco, San Francisco, Calif., Jan. 15-19, 1979.) Journal of Fire and Flammability, vol. 10, A79-49343 Evaluation of finite element formulations for July 1979, p. 207-215. Navy-supported research. transient conduction forced-convection analysis. E. A. Thornton Two samples of experimental airfield pavement materials were (Old Dominion University, Norfolk, Va.) and A. R. Wieting (NASA, evaluated for ignition, fire spread, smoke, and toxic gas evolution. Langley Research Center, Hampton, Va.). National Conference on The materials consisted of fiberglass-reinforced polyester surface Numerical Methods in Heat Transfer, College Park, Md., Sept. 24-26, sheets laminated to and supported by a high density polyurethane 1979, Paper. 26 p. 13 refs, Grant No. NsG-1321. rigid foam core. Both samples exhibited resistance to ignition and Numerical studies clarifying the advantages and disavantages of fire spread in this limited study. The effect of these pavement conventional versus upwind convective finite elements are presented materials on the fire spread of a large pool of burning aircraft fuel along with lumped versus consistent formulations for practical would appear to be negligible. (Author) conduction forced-convection analysis. A finite-element procedure for treatment of negligible capacitance fluid nodes is presented. The procedure is based on procedures used in finite-element structural A79-49376 Utilization of alternative fuels for transporta- dynamics to treat nodes with negligible structural mass. Two tion; Proceedings of the Symposium, University of Santa Clara, Santa finite-element programs and a finite-difference lumped-parameter Clara, Calif., June 19-23, 1978. Symposium sponsored by the U.S.

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Department of Energy. Edited by M. Newman and J. Grey A79-49486 II A design perspective on new technologies for (American Institute of Aeronautics and Astronautics, Inc., New general aviation. J. B. McCollough (FAA, Aircraft Flight Safety York, N.Y.). New York, American Institute of Aeronautics and Branch, Washington, D.C.). Astronautics and Aeronautics, vol. 17, Astronautics, Inc. )AIAA Aerospace Assessment Series. Volume 2), Sept. 1979, p. 48-53. 1979. 244 p. $15. Technologies that benefit the design of general aviation aircraft are ranked in terms of safety, performance, utility, and cost. Test This overview of alternative fuel development deals with such criteria in order of importance were: safety, reliability, performance, issues as energy supply and fuel manufacturing/processing and cost, customer acceptance, efficiency, operational ease and utility, storage and distribution. Attention is given to fuels for both road maintenance, weight, and environment. Areas rated were: aero- vehicles and nonroad vehicles (e.g., aircraft and trains). Finally, dynamics powerplant, structures, materials, and fabrication, avionics, discussions on impacts and institutional issues are presented. B.J. instrumentation, airframe and system design, and human factors and operations. It is noted that, in many ways, commercial aircraft design is a Conservative process, since safety is a first consideration. Among A79-49381 # Alternative fuels in aviation. J. G. Borger (Pan the conclusions is that social and political pressures will also American World Airways, Inc., New York, N.Y.). In: Utilization of influence the future of the general aviation industry. M.E.P. alternative fuels for transportation; Proceedings of the Symposium, Santa Clara, Calif., June 19. 23, 1978. New York, American Institute of Aeronautics and Astronautics, Inc., 1979, p. 129-142. A79-49530 * # Recent applications of theoretical analysis to The state of the art and expected future advances of alternative V/STOL inlet design. N. 0. Stockman (NASA, Lewis Research fuels in aviation are discussed. Consideration is given to uses of liquid Center, Cleveland, Ohio). U.S. Navy, Workshop on V/STQL Aero- hydrogen and methane, broadening of turbine fuel specifications, dynamics, Monterey, Calif., May 16-18, 1979, Paper. 16 p. 17 refs. increased aromatics, decreased flashpoint, increased freeze point, A brief description of the axisymmetric potential flow and thermal stability, synthetic fuels, and the refinery process. It is noted boundary layer analysis methods used at the NASA Lewis Research that major fuel efficiency improvements resulting from the NASA Center, is presented. Application of this method to inlet problems ACEE program probably will not appear before the late 1980s. B.J. arising from both tilt-nacelle and fixed-nacelle V/STOL aircraft configurations is illustrated. A three-dimensional inlet analysis computer program is described and the preliminary results presented. A79-49456 Numerical solution of the problem of un- Finally, a suggested approach to optimum design of inlets for high steady supersonic flow around the front part of the wings with a angle-of-attack operation is discussed. M.E.P. detached shock wave. G. P. Voskresenskii )Akademiia Nauk SSSR, Institut Prikladnoi Matematiki, Moscow, USSR). Computer Methods A79-49541 # The feasibility of modern dirigibles (Faisabilité in Applied Mechanics and Engineering, vol. 19, Aug. 1979, p. des dirigeables modernes). J. Bouttes and C. La Burthe (ONERA, 257. 275. 7 refs. Chétillon-sous-Bagneux, Hauts-de-Seine, France). (Co//oque Inter- The object of this paper is to describe a numerical method for national sur l'Economie et Technologie des Aéronefs Alleges, Paris, the solution of the problem of unsteady supersonic flow around the France, Mar. 28-30, 1979.) ONERA, TP no. 1979-93, 1979. 17 p. In front part of the wings with a detached shock wave. The velocity French. vector of the free stream is directed in an arbitrary direction but Through an analysis of the major constraints on dirigible without flow separation. The problem is formulated for the operation and configuration, a design methodology capable of three-dimensional hyperbolic system of equations of unsteady supporting the development of an optimal airship is obtained. inviscid chemically reactive gas flow in a mixed subsonic and Attention is given to the equilibrium properties of the gas compart- supersonic domain. It is solved by a finite difference implicit ment at altitude, means of weight compensation, including mooring, second-order method with the use of the time-dependent stationing vertical lift engines and aerostatic effects, for various dirigible principle. A curvilinear coordinate system it introduced in which the applications (surveillance, cargo, utility operations), steering and numerical domain becomes a simple rectangle. The coordinate control laws and apparatus. Research on interlocking rotors and the system is time-dependent and adapted for the planform of the wing thermal balance of a hot-air balloon presently under way at ONE RA and the free-stream parameters. The planform of the wing and the is outlined, and a weight distribution optimization loop illustrating velocity vector of the free stream may be changed in the time- the design methodology adopted is presented. The importance of a dependent stationing process. The flow field is computed around the multidisciplinary integrated approach to dirigible design is also front part of wings which have an elliptical planform and an aspect noted. A.L.W. ratio not greater than 2 for selected freestream Mach numbers betweeen 1.5 and 5 (Author) A79-49543 # Aerodynamic interaction on a close-coupled canard-wing configuration (Interaction aérodynamique entre un A79.49478 Helicopter noise rules . Are they appropriate canard proche et une voilure). Y. Brocard and V. Schmitt )ONERA. and reasonable. C. R. Cox (Bell Helicopter Textron, Fort Worth, Chatillon-sous. Bagneux, Hauts-de-Seine, France). (NATO, AGARD, Tex.). Marconi Review, vol. 42, 1st Quarter, 1979, p. 16.21. Symposium on Aerodynamic Characteristics of Controls, Naples, Consideration is given to proposed governmental regulations Italy, May 14-17, 1979.) ONERA, TP no. 1979-95, 1979. 12 p. 14 concerning helicopter noise and their effects. Problems with the refs. In French. Research supported by the Direction des Recherches, proposed PAA and ICAO standards are shown to stem from two Etudes et Techniques. inadequacies: (1) they are patterned after fixed wing regulations with Half-model tests were performed on a close-coupled canard-wing little or no consideration of differences in operation, and (2) the configuration in the low speed, pressurized wind tunnel Fl at the economic impact of implementing these standards has not been new ONE RA Center Le Fauga-Mauzac. The main lifting surface is the adequately assessed in terms of the cost that must be passed on to rectangular cylindrical, wall mounted, half wing AFV-D in a 60 deg the individual user. Other areas discussed include the impact on new back sweep configuration. The chordwise wing section has a 5 designs, on derived and existing designs, on safety and reliability, and percent thickness ratio and a large leading-edge radius. The canard on the probability of certification. Different approaches are pro- surfaces are similar in shape and section to the main wing. posed including operational restraints and flight path control. In Experimental results are presented in terms of longitudinal aero- conclusion it is stressed that inappropriate regulations could result in dynamic characteristics and pressure distribution on the main wing. serious adverse consequences on an industry composed predominant- The effect of canard deflexion and of Reynolds number variation ly of small business operators. M.E.P. were investigated. (Author)

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A79-49554 Airborne microwave ECM. D. J. Steer (Royal A79-49567 # A report on the Sperry Dome Radar. L. Aircraft Establishment, Farnborough, Hants., England). In: Military Schwartzman and P. M. Liebman (Sperry Rand Corp., Sperry microwaves '78; Proceedings of the First Conference, London, Gyroscope, Great Neck, N.Y.). In: Military microwaves '78; Proceed- England, October 25-27, 1978. Sevenoaks, Kent, ings of the First Conference, London, England, October 25-27, 1978. England, Microwave Exhibitions and Publishers, Ltd., 1979, p. Sevenoaks, Kent, England, Microwave Exhibi- 29.38. tions and Publishers, Ltd., 1979, p. 167-176. The paper examines techniques currently used in airborne ECM. The paper describes the Sperry Dome Radar equipment, system It covers the philosophy of jamming and gives details of the various operation, and target tracking experiences to-date. The equipment types of jammers used against specific radar systems. Jammer description includes the dome antenna which design provides transmitters are discussed and a brief survey of the power output of capability to scan a volume of 3 pi steradians, and provides travelling wave tubes (TWT) is included. This leads to an assessment maximum gain at an angle of 90 deg with respect to the zenith. For of the jammer powers likely to confront Western radar designers. The shipboard installations this meant continuous radar surveillance and general design features of a responsive noise jammer are presented tracking for ship roll and pitch as severe as 30 deg. Automatic and it is suggested that this type of jammer is the basis of mulsitarget tracking over wide scan angles, which has been demon- selfscreening )SSJ) escort )EJ) and standoff jamming )SOJ). The strated by the Sperry Dome Radar is described. Radar tracking tests paper ends with a brief mention of chaff. (Author) have been performed at various levels, namely simulated target injections, simulated target transmissions from external test towers, live skin tracks of targets-of-opportunity and skin tracks of several A79-49555 Performance of current radar systems in an controlled aircraft. Some of the track test results are presented. EW environment J. R. Prior and N. Woodward (Royal Signals and (Author) Radar -Establishment, Malvern, Worcs., England). In: Military micro- waves '78; Proceedings of the First Conference, London, England, October 25-27, 1978. Sevenoaks, Kent, England, A79-49568 , A new three-dimensional surveillance radar. M. Microwave Exhibitions and Publishers, Ltd., 1979, p. 39-50. F. Radford )GEC-Marconi Electronics, Ltd., Marconi Research The paper will start by considering the more important ECCMs Laboratories, Great Baddow, Essex, England) and A. D. Stevens incorporated into radars. It considers the effects of EW against (Marconi Radar Systems, Ltd., Stanmore, Middx., England). In: various types of radar systems. Long range early warning (ADGE) Military microwaves '78; Proceedings of the First Conference, radars, airborne early warning, SAM acquisition tracking radars and London, England, October 25-27, 1978. Seven- airborne intercept radars are considered. For each of these systems oaks, Kent, England, Microwave Exhibitions and Publishers, Ltd., typical present day characteristics are defined, their vulnerability to 1979, p. 193-200. 6 refs. Research supported by the Ministry of the EW threat discussed and the benefits to be obtained from various Defence (Procurement Executive). ECCMs, both technical and operational, are considered. An indica- The paper is concerned with a new fully transportable three- tion is given of the future trends in the design of such systems where dimensional surveillance radar, called Martello, which gives height relevant to their operation in ECM and the role of the more modern data with every target plot. It can use its elevation discrimination to antijamming aids arising from new technologies is described. separate targets from clutter or from each other. The clutter spectra (Author) are narrower, so that the loss of targets in the MTI is minimized. Moreover, a three-dimensional radar is less degraded by jamming, A79-49565 # Combined X/Ka'band tracking radar, L. J. since main beam obscuration is confined to the elevation of the Klaver (Hollandse Signaalapparaten, Hengelo, Netherlands). In: jammer instead of covering the whole elevation sector. The paper Military microwaves '78; Proceedings of the First Conference, shows how the configuration of the Martello radar has been chosen, London, England, October 25-27, 1978. Seven- and describes some of the technological advances incorporated in the oaks, Kent, England, Microwave Exhibitions and Publishers, Ltd., design. S. D. 1979, p. 147-156.6 refs. The paper surveys the development of the Dutch SIGNAAL combined X/Ka-band tracking radar. Attention is given to the effects A79-49574 Recent advances in radome design. A. M. of atmospheric conditions, such as rain and sea clutter. It is shown Munro (Royal Signals and Radar Establishment, Malvern, Worcs., that in this system target detection is performed by a normal search England), B. V. A. Wickenden, F. S. Ward, and P. H. Dowsett radar, after which the acquisition process is executed with the (Plessey Materials, Towcester; Plessey Connectors, Ltd., Kingsthorpe, X.barsd tracking radar. As soon as video quality permits, target Northants., England). In: Military microwaves '78; Proceedings of tracking is performed in the Ka-band. Also discussed are the practical the First Conference, London, England, October 25-27, 1978. problems experienced when tracking low-flying targets by radar and Sevenoaks, Kent, England, Microwave Exhibi- M.E.P. how SIGNAAL overcomes them. tions and Publishers, Ltd., 1979, p. 246-258. The paper deals with aberration caused by A-type sandwich A79-49566 # The A.I. tracking problem. B. B. English radomes whose shapes may be conical or ogival with high fineness (Ferranti, Ltd., Hollinwood, Lancs., England). In: Military micro- ratios. Three methods for reducing radome aberration are presented. waves '78; Proceedings of the First Conference, London, England, The artificial dielectric approach produces a radome whose per- October 25-27, 1978. Sevenoaks, Kent, England, formance is comparable to that of a solid laminate. The wire-loading Microwave Exhibitions and Publishers, Ltd., 1979, p. 157-163. technique is capable of making a marked reduction in aberration, Research supported by the Ministry of Defence (Procurement although a slight increase in attenuation results. As yet, the Executive). asymmetric design has not been used in a practical case. The use of Attention is given to the problems arising from using radar to RP1 2 polyester resin for the construction of laminate radomes gives provide target information to other aircraft subsystems such as the an improved bandwidth, due to the near-constant permittivity and weapons aiming computer. The two main problems considered are low loss over a wide temperature range. It is a unique method of (1) aircraft motion which disturbs the radar end of the line of sight, constructing high-performance radomes for high-speed aircraft and and (2) glint, which introduces noise into the measurement of target missiles. S. D. behavior. A description is given of an approach which treats aircraft motion and glint as independent problems and is then used to A79-49580 # Ellipsoidal modelling of aircraft targets for generate a set of desirable servo characteristics. An actual radar evaluation of electronic fuzes. L. Svard and N.-A. Nilsson )L. M. system is described along with how well it satisfies the ideal Ericsson Telephone Co., Molndal, Sweden). In: Military microwaves requirements. Finally, possible performance improvements provided '78; Proceedings of the First Conference, London, England, October by the availability of practical airborne digital computing are 25-27, 1978. Sevenoaks, Kent, England, Micro- covered. M.E.P. wave Exhibitions and Publishers, Ltd..,1979 p. 304-309.

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This paper describes a computer model for the evaluation of returns with a delay proportional to the aircraft height. The radar proximity fuzes. The target is described by a number of application of this system for military use is examined for three ellipsoids and limiting planes. Cavities are also described by ellip- different altitude ranges: 5000, 10,000 and 70,000 ft and its soids. In this case correction factors are used to adjust the radar implementation for fighters, missiles, hydrofoils, and helicopter is cross-section. The contributions from the various ellipsoids are reviewed. C.F.W. computed by methods of geometrical optics. Shadowing is also considered in this computation. The computer program calculates A79-49590 # The application of pulsed 'G' band radio the received signal with the aid of the radar equation, applies the altimeters to modern military aircraft, R. J. L. Pardoe (Smiths processing of the fuse and determines the output signal. The output Industries, Ltd., Aviation Div., Basingstoke, Hants., England). In: may alternatively be the triggered point in space. A large number of Military microwaves '78; Proceedings of the First Conference, calculations have been performed using this model. The results have London, England, October 25-27, 1978. Seven- been compared with full-scale measurements on a target drone and oaks, Kent, England, Microwave Exhibitions and Publishers, Ltd., ultrasonic tank measurements on drone and fighter aircraft models in 1979, p. 426.430. Research supported by the Ministry of Defence the X. band. These comparisons show that the standard deviation of (Procurement Executive). the trigger point difference is less than 0.6 m. (Author) The paper demonstrates the way an assessment can be made of the slant range accuracy of the pulsed altimeter system. Specifica- A79.49584 # Distributed TDMA - An approach to JTIDS tions of the G band radio altimeter reviewed include altitude range, phase II. J. Rubin (ITT, Avionics Div., Nutley, N.J.). In: Military accuracy, track rate, search rate, and maneuverability, and total microwaves '78; Proceedings of the First Conference, London, system weight. In addition, the pulse echo function and video pulse England, October 25-27, 1978. Sevenoaks, Kent, shape are covered. The results of this assessment are shown to agree England, Microwave Exhibitions and Publishers, Ltd., 1979, p. with Ministry of Defence sponsored trials of equipment in a wide 341-345. Contract No. N62269-76-C-0105. range of military fixed wing and rotary wing aircraft and therefore A distributed TDMA )DTDMA) system for increased perfor- justify the specified performance. M.E.P. mance to meet expanding multiservice future requirements is presented. In addition to existing Tacan and 1FF channels, and the TDMA channel, the joint tactical information distribution system A79.49604 Automated tracking for aircraft surveillance (JTIDS)/DTDMA terminals provide multiple demand access channels radar systems. R. M. O'Donnell and C. E. Muehe (MIT, Lexington, for A/J digital voice, and command access channels for command Mass.). (NATO, AGARD, Meeting on Strategies for Automatic Tract and control communications. The DTDMA technique employs low Initiation, Monterey, Calif_ Oct. 16, 17, 1978). IEEE Transactions duty cycle pulses, pseudo-randomly distributed in the time- on Aerospace and Electronic Systems, vol. AES. 15, July 1979, p. frequency-phase code domain, and because of its flexible channel 508-517. 17 refs. U.S. Department of Transportation Contracts No. design, variable information parameters such as message length and FA72WAI.242; No. FATO-679 Contract No, F19628-78.C.002. rate, access type, and coding requirements are readily achieved. The An improved moving target' detector (MTD) (a digital signal JTIDS integrated system, the fundamental signal/channel JTIDS Processor) has been designed, constructed, and tested which success- architecture, and performance capabilities are discussed. It is fully rejects all forms of radar clutter while providing reliable concluded that JTIDS/DTDMA can be used for EW computational detection of all aircraft within the coverage of the radar. The MTD is burden distribution, RPV based active ECM, real-time reconnaissance being tested on both terminal and enroute surveillance radars for the data collection, and coordination of communications jamming. A.T. FAA. This processor has been integrated with automatic tracking algorithms to give complete rejection of ground clutter, heavy A79-49587 # Navstar user equipment for civil and military precipitation, and angels (birds). (Author) applications. S. G. Allen, P. J. Hargrave, K. Buckley, J. C. Greenwood, and P. K. Blair (Standard Telecommunication Labora- tories, Ltd., Harlow, Essex, England). In: Military microwaves '78; Proceedings of the First Conference, London, England, October A79.49605 Small signal compensation of magnetic fields 25. 27, 1978. Sevenoaks, Kent, England, Micro- resulting from aircraft maneuvers. S. H. Bickel (Atlantic Richfield wave Exhibitions and Publishers, Ltd., 1979, 405-409. p. Co., Los Angeles, Calif.). IEEE Transactions on Aerospace and High performance and basic Navstar receivers are described Electronic Systems, vol. AES-15, July 1979, p. 518-525. 6 refs. along with an experimental receiver. The experimental receiver uses a Contract No. N62269-75-C-0210, switching-type code tracking loop and is capable of receiving C/A It is noted that Tolles and Lawson (1950) identified three code spread spectrum signals. Pseudorandom measurement was permanent, five induced, and eight eddy-current fields as sources of conducted by comparing the difference between 1023 code epochs magnetic interference associated with airframe maneuvers. The of the locally generated code with a one-millisecond epoch derived present paper uses small signal approximations to separate the from the 10 MHz stable reference. Signal strength measurement was eddy-current terms and thus decouple the sixteen equations into two made of the received signal-to-noise ratio from the Navstar satellites sets of eight equations. It is found that a singularity exists in the and compared with predictions. The application of Navstar receivers small signal equations for the permanent and induced terms. It is to both civil and military navigation is discussed. V.T. shown that the ambiguity thus caused among three of the coeffi- cients can be resolved mathematically by resorting to large maneu- vers. In addition, flight test data are presented which exhibit a large A79.49589 # The servoed modulation FMCW radar altime- amount of Magnetic hysteresis and it is shown that the magnetic ters in military applications. J.-P. Tomasi )Télécommunications anomality detector (MAD) equipped aircraft will not remain com- Radioelectriques et Téléphoniques, Le Plessis-Robinson, Hauts-de- pensated from one flight to the next. Finally, it is found that both Seine, France). In: Military microwaves '78; Proceedings of the First optimal frequency filtering and altitude compensation can be used to Conference, London, England, October 25 . 27, 1978. improve the figure of merit )FOM) resulting from pilot maneuvers. Sevenoaks, Kent, England, Microwave Exhibitions and M. E. P. Publishers, Ltd., 1979, p. 421-425. A method of receiving and detecting a radar signal, by matching the signal to the receiver and adjusting the modulation of the transmission to the target distance so that the signal is perfectly A79-49608 Multiradar tracking system using radial veloci- adapted to the receiver is presented. A FMCW radar altiri,eter is used ty measurements. A. Farina and S. Pardini (Selenia S.p.A., Rome, to transmit a signal with a frequency modulated by a symmetrical or Italy). IEEE Transactions on Aerospace and Electronic Systems, vol. asymmetrical sawtooth and is then reflected, by the ground, and AES-15, July 1979, p. 555-563. 14 refs.

638 A79-49866

Multiradar tracking using both position and radial velocity Society. Symposium on A New Generation of Civil Helicopters, measurements is discussed. The measurement of two or more London, England, Feb. 7, 1979.) Aeronautical Journal, vol. 83, July different radial velocity components allows the calculation of 1979, p. 245.249. rectangular velocity components. The measurement noise of the The Aérospatiale AS.350 and AS.355 helicopters are surveyed. velocity components it filtered using a Kalman filter in the same way Attention is given to design features such as the structure made of as the Cartesian position components. Before the conversion of press stamped parts, and a cabin made up of heat formed velocity components from radial to Cartesian coordinates, the radial polycarbonate shells, the rotor blades and rotor head of fiber glass, velocities are aligned on a time scale to account for the time shift of showing how the objectives of quality, comfort, performance, and the radar measurements. In order to compare multiradar tracking low cost were achieved. Other features discussed include a simplified system performance with and without radial velocity, some simula- gearbox, engine availability, the beam type tail rotor. Substantial tion tests have been performed for typical paths. The simulation cots reductions are also shown to have been achieved through the use results show a significant improvement when radial velocity is used of high volume production items from the automotive industry, and for tracking. (Author) assembly line production methods. Finally, the introduction of the twin engine AS.355 is noted along with how it differs from the single engine AS.350. M.E.P. A79-49718 # An approach for estimating vibration charac- teristics of nonuniform rotor blades. K.-W. Lang and S. Nemat-Nasser A79-49815 Design and development of she Agusta A 109 (Northwestern University, Evanston, Ill.). AIAA Journal, vol. 17, helicopter. B. Lovers )Costruzioni Aeronautiche Giovanni Agusta A., Milan, Italy). (Royal Aeronautical Society, Symposium on A Sept. 1979, p. 995. 1002. 25 refs. Grants No. DAAG29-77-G-0034; S. p. No. DAAG29-78-G-0149. New Generation of Civil Helicopters, London, England, Feb. 7, A method is presented for determining the vibration character- 1979.) Aeronautical Journal, vol. 83, July 1979, p. 250-256. istics of a rotating blade whose cross-sectional dimensions or The Agusta A 109 helicopter, considered the forerunner of the mechanical properties may vary sharply or even discontinuously generation of civil helicopters introduced in the seventies, it along its length. The coupled flapwise bending, chordwise bending, examined. The A 109 design objectives and certification basis are and torsional vibration of the blade is analyzed by the method of the discussed. Attention is also given to performance aspects, safety new quotient which is based on a variational statement proposed by aspects, and passenger comfort aspects. Operational aspects con- Nemat-Nasser. In this approach, the nonuniform blade properties sidered include: helicopter loading, external noise, and IFR capa- may be approximated by step (piecewise constant) functions. Two bility. In addition, auxiliary installations, climatic tests, and oper- illustrative examples are given, and the results are compared with ating costs are covered. Finally, future developments are discussed. available experimental data and other numerical solutions. The M.E.P. comparison shows that the method of the new quotient yields very good results. (Author) A79-49816 The Bell Model 222. J. R. Garrison (Bell Helicopter Textron, Fort Worth, Tex.). (Royal Aeronautical Society, A79-49806 Fault diagnosis of gas turbine engines by Symposium on A New Generation of Civil Helicopters, London, means of component characteristics determination (Fehier- England, Feb. 7, 1979.) Aeronautical Journal, vol. 83, July 1979, p. Iokalisiewng an Einkreis-TL-Triebwerken durch Bestimmung der 257-268. Bauteilkenngrossen(. G. Dahl )Branschweig, Technische Universität, The design and performance characteristics of the Bell Model Braunschweig; Bodenseewerk Gerätetechnik GmbH, Uberlingen, 222 are surveyed. Design details covered include she main rotor hub West Germany). Zeitschrift für Flugwissenschaf ten und We/traum. which it designed for reduced maintenance, safety, and long forxhung, vol.3, July-Aug. 1979, p. 216 . 229. 37 refs. In German. component fatigue lives, the main rotor blade, the tail rotor, and A method to calculate the component characteristics of single rotor drive system. Attention is also given to the main transmission, spool jet engine has been developed by using ,measured engine data. the nodal beam's isolation of drivetrain vibrations, the power reserve Lacking data are replaced by characteristics of different components provided by the twin Lycoming engines, and the impact resistant fuel of the healthy engine. By comparing the results for these different cells. It is shown that the cockpit has an instrument panel capable of assumptions the actual conditions of the engine components could being equipped with an IFR instrumentation array -while retaining be determined. A large number of different faults has been simulated good visibility for the VFR operator. Finally, flight tests, fatigue experimentally on a J-65 engine. The application of the present tests and noise measurements are described. M.E.P. methods led to a correct fault diagnosis in all cases. The method is capable to localize single and multiple faults of arbitrary kind and A79-49818 Flight experiments to evaluate the effect of magnitude. (Author) wing-tip sails on fuel consumption and handling characteristics. J. J. Spillman, H. Y. Ratcliffe, and A. McVitie (Cranfield Institute of Technology, Cranfield, Beds., England). Aeronautical Journal, vol. A79-49807 Variables characterizing the wind effects on an 83, July 1979, p. 279.281. aircraft (Grbssen zur Bevthreibung des Windeinflusses auf das The results of experiments performed with a Paris MS 760 Flugzeug). R. Brockhaus )Braunschweig, Technische Universitét, aircraft modified with wing tip sails to reduce vortex drag are Braunschweig, West Germany). Zeitschrift für Flugwissenschaften presented. Specifications and test procedures are described and it is und Weltraumforschung, vol. 3, July-Aug. 1979, p. 229-234. 6 refs. shown that fuel flow rate and engine speed are uniquely linked. In German. Attention is given to handling characteristics such as the aircraft's A series of Euler angles between the aerodynamic and the flight ability to take-off up to 10 knots sooner than without sails. In path coordinates, very similar to those defined by Krauspe and addition there appeared to be increased damping in roll with the roll Klenner, is proposed. These angles allow a very comprehensive rate relatively unaffected. It is concluded that the total drag at lift description of the wind effect on an aircraft. The present definition coefficients above 0.22 is reduced because the lift dependent drag is has the advantage that the Euler angles are related in a positive sense reduced by 27%. The fuel saving is about 4.5% at a typical lift to the components of the wind velocity vector. In addition, exact coefficient of 0.35 rising tb almost 11% at a lift coefficient of 0.8. and approximate relations are presented between the wind velocity M.E.P. components in the principal coordinate systems and those variables which are measurable on board the aircraft. (Author) A79-49866' # Active external store flutter suppression in the YE-17 flutter model. E. Nissim and I. Lottati (Technion - Israel A79-49814 Aérospatiale AS.350 and AS.35. J. Boulet Institute of Technology, Haifa, Israel). Journal of Guidance and (Société Nationale Industrielle Aérospatiale, Division l-(élicoptères, Control, vol. 2, Sept.-Oct. 1979, p. 395-401. 22 refs. Grant No. Marignane, Bouches-du-Rhbfle, France). (Royal Aeronautical NsG-7072.

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A single activated trailing-edge (T.E.) control system (spanning The complex motion of an amphibious hovercraft suffering skirt 7% of each Wing) IS applied to the YF-17 flutter model with the tuck-under, plough-in, and hull contact has been simplified to the object of suppressing the external store flutter of three different beam-on hull contact phase of the roll motion of a craft with a store configurations. The control law is derived by the use of the simple flat planing surface at the hull edge. The motion is restricted aerodynamic energy concept and its gains are maintained constant to two degrees of freedom sideslip and roll, but the nonlinear for all three configurations. The results obtained show that the characteristics are incorporated using the SLAM digital simulation activated T.E. control system leads to very significant increases in the technique. Overturn is assumed if significant roll rate remains after flutter dynamic pressures O(OF) of all three configurations; these the roll angle has appreciably exceeded that for the deck to submerge increases range between 160-240% increase in O)DF(. These increases (20 to 30 deg), The neutral stability boundary is established as a in Q(DF) are maintained over a very wide range of flight altitudes function of center of gravity height and hull planing surface angle for and flight velocities. (Author) varying hull thickness/beam, and skirt depth/beam ratios. (Author) A79-49905 Performance predictions for open ocean air cushion vehicles and surface effect ships. J. A. Tremills (Defence A79-49867 II On single-degree-of-freedom flutter induced by Research Establishment Atlantic, Dartmouth, Nova Scotia, Canada), activated controls. E. Nissim and I. Lottati )Technion - Israel In: Air cushion technology; Proceedings of the Twelfth Canadian Institute of Technology, Haifa, Israel). Journal of Guidance and Symposium, Toronto, Canada, September 25-27, 1978, Control, vol. 2, Sept.-'Oct. 1979, p. 402-406. 8 refs. Grant No. Ottawa, Canadian Aeronautics and Space Institute, NsG-7373. 1978, p. 75. 103. 12 refs, It is shown that activation of the trailing-edge control of an airfoil leads to single-degree-of-freedom type instabilities which span A79-49906 Small hovercraft design - Evolution to sim- over a very wide region of reduced frequencies k, including high plicity. A. Bliault. In: Air cushion technology; Proceedings of the values of k (unlike the nonactivated system). These instabilities are Twelfth Canadian Symposium, Toronto, Canada, September 25-27, shown to be sensitive to changes in pitching axis location, control 1978, Ottawa, Canadian Aeronautics and Space deflection phase angle, and values of the reduced frequency. These Institute, 1978, p. 104. 124. 12 refs. sensitivities of the single-degree-of-freedom system cause the acti- The paper reviews the development of small amphibious ACVs vated airfoil to be potentially sensitive to changes in flight of capacity 0.1 - 2.0 tons from the early 1960s to the present. conditions, and may be the source of the many difficulties Changes in structural design, power train and propulsion systems, encountered in suppressing classical multi-degree-of-freedom flutter together with improvements in skirt technology, enable the design of by means of active controls. The results presented herein relate to efficient simple craft at present using a single engine and fan for lift zero Mach number and to a 20% trailing-edge control surface. and propulsion. The design developments described result in the (Author) capability to produce ACVs equivalent to such vehicles as jeeps and androvers in their rugged reliability, while having the additional A79-49869 # Linearization of the boundary-layer equations ability to traverse water, marshy, and soft sand terrains. The of the minimum time-to-climb problem. M. D. Ardema (NASA, development of simple, rugged, and inexpensive small ACVs is now Ames Research Center, V/STOL Systems Office, Moffett Field, possible and has begun in Europe. Design data presented illustrate Calif.). Journal of Guidance and Control, vol. 2, Sept.-Oct. 1979, p. these modern techniques and the craft designs which result from 434-436, 6 refs. their use. (Author) Ardema (1974) has formally linearized the two-point boundary value problem arising from a general optimal control problem, and A79-49907 Hovercraft skirt design requirements, J. E. has reviewed the known stability properties of such a linear system. Rapson )Hovercraft Development, Ltd., Southampton, England), In: In the present paper, Ardema's results are applied to the minimum Air cushion technology; Proceedings of the Twelfth Canadian time-to-climb problem. The linearized zeroth-order boundary layer Symposium, Toronto, Canada, September 25-27, 1978. equations of the problem are derived and solved. V. P. Ottawa, Canadian Aeronautics and Space Institute, 1978, p. 125-149. 8 refs. A79-49873 # Comment on 'active flutter control using The reason for using a hovercraft and the duties that it is generalized unsteady aerodynamic theory'. R. Vepa (National Aero- required to perform are considered as the basis for the work of the nautical Laboratory, Bangalore, India), Journal of Guidance and hovercraft designer and more particularly, the skirt designer. General Control, vol. 2, Sept-Oct. 1979, p. 446, 447; Reply, p. 447, 448, 7 skirt requirements are discussed and analyzed in relation to various refs. types of craft. By analyzing the power absorption of several craft, it is shown that a response skirt is of prime importance. The relationship of various skirt configurations is shown and opinions are A79-49882 # Solution of a mixed boundary value problem expressed on their relative performance capabilities. Due to its for flow past a thin delta wing (Reshenie smeshannoi kraevoi zadachi versatility the open loop and segment system is singled out for obtekaniia tonkogo treugol'nogo kryla). A. M. Antonova and L. I. special attention and design, and testing techniques are described. Dzvonik )Kievskii Gosudarstvennyi Universitet, Kiev, Ukrainian Finally the result of work on skirt section stability, nonscooping SSR), Matematicheskaia Fizika, no. 25, 1979, p. 74-80. In Russian. skirts, and cushion control systems are summarized. (Author) A mapping method is presented for hypersonic flow past a thin delta wing at small angles of attack. A series of transformations makes it possible to formulate a Riemann-Poincare problem for the A79-49909 Characteristics of an Air Cushion Landing pressure function. Nontrivial solutions in the form of Fourier series System incorporating an inelastic trunk. A. B. Boghani, K. M. are obtained for the problem along with recursive relations for the Captain (Foster-Miller Associates, Inc., Waltham, Mass.), and D. N. flow coefficients, shock profiles, and integral representations for Wormley (MIT, Cambridge, Mass.), In: Air cushion technology; velocity components. B.J. Proceedings of the Twelfth Canadian Symposium, Toronto, Canada, September 25. 27, 1978. Ottawa, Canadian Aero- A79-49904 A simulation of amphibious hovercraft over- nautics and Space Institute, 1978, p. 168-189. 8 refs. Contract No, turning, D. M. Waters and R. A. Prasad )Loughborough University of NAS1 -12403, Technology, Loughborough, Leics., England). In: Air cushion tech- A series of static and dynamic tests performed on an Air nology; Proceedings of the Twelfth Canadian Symposium, Toronto, Cushion Landing System (ACLS) incorporating inelastic trunk are Canada, September 25-27, 1978. Ottawa, Cana- described. The tests were performed on an apparatus which had dian Aeronautics and Space Institute, 1978, p. 54-74. 13 refs. provisions to isolate heave-pitch and roll motion on the prototype

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cushion. The results of the test show that the sides of the trunk of the Twelfth Canadian Symposium, Toronto, Canada, September behave differently from the trunk ends. The tests also demonstrate 25-27, 1978. Ottawa, Canadian Aeronautics and that the current ACLS designs suffer from low heave damping, low Space Institute, 1978, p. 358-378. roll stiffness and fan stall problems. (Author) A method for determining cushion flows over water and over land is discussed, and a new non-dimensional lift-air coefficient is A79-49910 Road fleet operation of air cushion assisted proposed. Propulsion using winched cables, applied to low-speed vehicles- An evaluation of technical and economic problems. D. Eyre ACV ferries, is outlined and developments of surface contacting (Saskatchewan Research Council, Saskatoon, Canada) and A. A. devices are discussed along with the theoretical and experimental Jones (A. A. Jones and Associates, Ltd., La Ronge, Saskatchewan, prediction of minimum air flows and over-water drags for cushions Canada). In: Air cushion technology; Proceedings of the Twelfth containing segmented skirts. Emphasis is placed on the development Canadian Symposium, Toronto, Canada, September 25-27, 1978. of a modular structure concept which defines a modular system as Ottawa, Canadian Aeronautics and Space Insti- consisting of rectangular boxes with triangular perimeter, units that tute, 1978, p. 190-213. 5 refs. can be assembled together to form a series of craft capable of The paper summarizes the results of a detailed evaluation of the payloads from about 40 to 300 tons. V.T. economics and technical problems of air-cushion-assisted vehicles in on-road applications, conducted from 1977 to 1978. The results show that air-cushion-assisted vehicles are not economically competi- tive or technically practicable in fleet operations. This indicates the A79-49921 # Drag reduction by cooling in hydrogen-fueled importance of a paper evaluation prior to the development and aircraft, E. Reshotko (Case Western Reserve University, Cleveland, application of the technology. It is noted that air-cushion-assisted Ohio). Journal of Aircraft, vol. 16, Sept. 1979, p. 584-590. 28 refs. vehicles cannot compete economically with conventional wheeled Drag reductions are possible for cryo-fueled aircraft by using vehicles and cannot satisfy the existing braking regulations. The fuel to cool selected aerodynamic surfaces on its way to the engines. effect on road maintenance is shown to be minimal, and the energy This is because cooled laminar boundary layers in air at subsonic and efficiency to be considerably lower than in the conventional vehicles. low supersonic speeds are more stable than adiabatic boundary layers V. T. and therefore more resistant to transition to turbulent flow. Calculations for M 0.85 hydrogen-fueled transport show that drag A79-49911 A combined air-cushion and endless belt trans- reductions in cruise of about 20% are within reason. The weight of portation system. D. Train and C. Melancon )Hydro-Quebec, the fuel saved is well in excess of the weight of the required cooling Institute of Research, Varennes, Quebec, Canada). In: Air cushion system. These results suggest that the hydrogen fueled aircraft technology; Proceedings of the Twelfth Canadian Symposium, employing surface cooling is quite attractive as an energy conserva- Toronto, Canada, September 25 .27, 1978. Otta- tive aircraft and warrants more detailed study. (Author) wa, Canadian Aeronautics and S pace Institute, 1978, p. 214-224. The paper describes an air-cushion system for the transportation of loads up to 150 T. The system consists of a pallet and an air-cushion assembly of eight 36-in. castors. Each castor is sur- A79-49922 # Correlation technique for ambient effects on rounded by a flexible but impermeable endless belt which enables oxides of nitrogen. R. M. Washam and A. M. Mellor )Purdue the air-cushions to be used on floor surfaces having discontinuities University, West Lafayette, Ind.). Journal of Aircraft, vol. 16, Sept. such as drains, cracks, and recessed rails. This technique also prevents 1979, p. 626-631. 19 refs. Research supported by the U.S. the compressed air from escaping downward when used on semi- Environmental Protection Agency. porous surfaces such as asphalt, gravel, etc. The system was Aircraft gas turbine engine testing requires large air flow rates developed in order to eliminate damage to the floor when using a and this is accomplished with ambient air. Daily changes in conventional air-cushion system. A major advantage of the new atmospheric air temperature, pressure, and humidity lead to varia- system is that it is less sensitive to irregularities in the floor surface, tions in NOxEI )g NOx/kg fuel). A new scheme is proposed to and the air castors are less prone to puncture due to swarf, screws, correlate engine data and minimize this scatter due to changes in etc. V. T. ambient conditions. The scheme is derivable from first principles; example calculations are shown for several Pratt and Whitney JT9D A79-49912 Iceater I - Air cushion ice breaker in commer- engines. The correlation technique is explained in detail, and the cial operations. W. B. Stocking (Arctic Systems, Ltd., Houston, resulting scaling relations is discussed. (Author) Tex.). In: Air cushion technology; Proceedings of the Twelfth Canadian Symposium, Toronto, Canada, September 25-27, 1978. Ottawa, Canadian Aeronautics and Space Insti- tute, 1978, p. 237-246. A79-49925 # Comment on 'Flight test of stick force stabil- The paper presents the results of full-scale testing of the Arctic ity in attitude-stabilized aircraft'. W. 0. Breuhaus (Institute for System Limited Air Cushion Craft, Iceater I, which was conducted Defense Analyses, Arlington, Va.). Journal of Aircraft, vol. 16, Sept. on Thunder Bay, Ontario, during the winters of 1975-76 and 1979, p. 639, 640; Authors' Reply, p. 640. 6 refs. 1976-77. Iceater I was initially developed as an overland transporter and work platform. The craft was also adapted to use over water and in almost all aspects it performed satisfactorily when limited to the special operations and close supervision provided by the test environment. In several other aspects, it was deficient as an A79-49995 Injuries in air transport emergency evacua- over-water or in-water craft. Some of the more important of these tions. D. W. Pollard (FAA, Protection and Survival Laboratory, aspects are discussed: (1) stability in the floating mode; (2) Oklahoma City, Okla.). Aviation, Space, and Environmental Medi- unwatering/deballasting capability; (3) hovering power plant reliabil- cine, vol. 50, Sept. 1979, p.943.947. 7 refs. ity; (4) craft control and security (including anchoring and landing); Eleven accident histories pertaining to air transport emergency (5) hovering system maintenance over water; (6) host ship interfaces; evacuations are reviewed because they are representative of types of a (7) long-range mobility. V.1. evacuations. A twelfth history was selected because the passenger load consisted of trained personnel, and hence is unique. Factors influencing survival in emergency evacuations are presented and described in tabular form: configuration, procedure, environment, A79-49915 Current Canadian developments related to and biobehavior. The discussion focuses on the .conf igurational and low-speed heavy lift ACV. R. W. Dyke (Hoverlift Systems, Ltd., procedural factors. The environmental factor, while significant in Calgary, Alberta, Canada). In: Air cushion technology; Proceedings high-impact and/or toxic-agent-producing accidents, is relatively

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unimportant in less severe accidents. The biobehavioral factors A79-50165 An investigation of the rolling stability deriva- cannot be controlled and are therefore not emphasized in this paper. tives of a T-tail fighter configuration at high angles-of-attack. W. A. S. D. Thor (USAF, Aeronautical Systems Div., Wright-Patterson AFB, Ohio). Society of Flight Test Engineers, Journal, vol. 1. Jan. 1979, p. 21-25. The F-104 high-load-factor stability problem was studied with a A79.50109 Lusaka accident report. J. M. Ramsden. Flight wind tunnel model. As the angle of attack for the model with a clean International, vol. 116, Aug. 25, 1979, p. 595, 596, 601-607. wing is increased near the stall, the roll damping drops off abruptly A study of the Lusaka accident of a Boeing 707 is examined in and the yaw due to roll increases negatively (adverse yaw). This detail with emphasis on the detached stabilizer and the cause of its characteristic was more pronounced when the wing was in the dislodging. Postaccident tests, a total of nine, using theoretically high-lift configuration of 12 deg leading-edge flap and 13 deg derived loads were examined over a range of four conditions. Other trailing-edge flap, due to the lift-curve slope's decreasing at an earlier tests including fatigue and failsafe tests were conducted by US and angle of attack for the flapped wing. The wing fences, slats, and UK agencies and a failsafe design philosophy is discussed. It was strakes had a favorable effect on the roll damping and adverse yaw, concluded that insufficient consideration had been given to the and they are considered to be the simplest and most effective design and certification stage and to the stress distribution of the aerodynamic modification to increase the roll damping at high angles horizontal stabilizer spar structure following a top chord failure in of attack without degrading the longitudinal characteristics. The the region outboard of the closure rib. C.F.W. wing tip end plates decreased the roll damping at angles of attack below stall. V.T.

A79-501 10 Duct noise radiation through a jet flow. H. E. Plumblee (Lockheed-Georgia Co., Marietta, Ga.) and P. E. Doak A79-50166 Ultrasonic method of gun gas detection. R. L. (Southampton, University, Southampton, England). Journal of Grant (McDonnell Aircraft Co., St. Louis, Mo.). Society of Flight Sound and Vibration, vol. 65, Aug. 22, 1979, p.453-491. 53 refs. Test Engineers, Journal, vol. 1, Jan. 1979, p. 26-32. The radiation of internal (or core) noise for aircraft turbojet or Gun-gas sensing systems using ultrasonic sensors are described. turbofan engines is studied analytically. The geometry of a typical Three systems were constructed: two of them employed multiple engine is simplified for analytical considerations to a hemispherical sensors, whereas the third was a single-sensor prototype system. The shell with a jet flow and internal sound emanating through a circular control unit, tailored in each case to a particular data system hole on the axis. A linearized theory is used to derive a flow requirement, provided an independent pulse-code-modulated output modified spherical wave equation. A forced separation technique is containing the reduced sensor data and various system status used to produce a modified Legeridre equation describing the angular indicators. The single-sensor system was tested in an actual flight variation of the acoustic radiation field. Then a numerical technique environment during the F-15 gunfire program. Data were also is described for obtaining a general field solution by progressively collected on sensor performance during ground tests of the 20-mm imposing continuity of pressure across hemispherical shells as the gun used on the F-is. Conclusive test data supporting the quantita- solution is marched from near field to the far field. In a companion tive performance of the sensor were limited to laboratory tests paper, numerical results are presented and compared with experi- although a limited amount of data exists that indicates a correlation mental results from a test configuration identical to that described with sampling bottle data taken during actual gunfire. It is noted that by the theory. (Author) the response time of the ultrasonic sensor is significantly faster than that of catalytic sensors. V.T. A79-50163 High sink-rate landing testing of Navy aircraft. G. E. Clarke (U.S. Naval Air Test Center, Patuxent River, Md.). A79-50167 Performance modelling methods. W. M. Olson Society of Flight Test Engineers, Journal, vol. 1, Jan. 1979, p. 2-9. (USAF, Flight Test Center, Edwards AFB, Calif.). Society of Flight Sink-rate measurement systems for Navy aircraft are reviewed Test Engineers, Journal, vol. 1, May 1979, p. 2-12. including photo-optical systems, the Ryan sink-rate radar, a touch- Two different directions a performance program can take are down rate-of-descent indicator (TROD I), and a laser theodolite. The discussed. The first is a program in which accelerations are used to Ryan radar offers a high potential for development into an accurate generate acceleration performance, etc. The other extreme is a measuring system. A near-term effort is being made to improve the program in which maneuvers are designed solely to generate drag data readout available from this radar so that the inherent system polars and thrust and fuel flow maps. Five basic performance accuracy might be realized. Goals are to reduce or eliminate reader modeling methods which utilize drag and thrust models are outlined: variability and to generate report quality data. The long-term (1) predicted minimum drag method; (2) predicted thrust method; solution to accurate sink-rate measurement is a laser theodolite with (3) predicted thrust fuel model; (4) complete reliance on the in-flight digitized output fed to an onboard minicomputer capable of thrust calculation; and (5) partial reliance on the in-flight thrust real-time computation and display of sink rate and engaging speed. calculation. The preferred program should be designed primarily to V.T. generate the model, but 'conventional' maneuvers should be used in this determination, V.T. A79-50164 Dynamic test techniques- Concepts and prac- tices. K. Rawlings, Ill, J. M. Cooper, and D. L. Hughes. Society of Flight Test Engineers, Journal, vol. 1, Jan. 1979, p. 10-20. The concepts involved in dynamic performance testing represent A79-50168 A computer system for identifying aircraft a philosophy of developing a single, coherent performance model characteristics, T. J. Galbraith, T. J. Petersen, and C. E. Roth (Boeing using thrust and drag modeling. It is shown that if all thrust drag Commercial Airplane Co., Renton, Wash.). Society of Flight Test interactions, maneuver rates, and instrumentation are taken into Engineers, Journal, vol. 1, May 1979, p. 13-30.6 refs. consideration, it is possible to generate a lift/drag model which is The parameter identification (P1) concept is presented as a capable of predicting performance from nearly any maneuver. mathematical scheme for estimating stability and control derivatives Although this capability is dependent on the ability to calculate gross from dynamic flight testing. A parameter identification system thrust adequately, the engines can be calibrated through static thrust composed of six computer programs is described along with a runs and the thrust computation procedures verified in flight. The kinematic and sensor-dynamics )KASD) program added to the capability of generating a consistent lift/drag model in considerably system for identifying sensor inconsistencies or errors. The P1 less time than conventional performance methods is demonstrated. concept employs the classical six-degree-of-freedom kinematic rela- V.T. tions, modeled sensor errors, and an estimator to produce a

642 A79-50240

consistent set of sensor time histories. A flaps-up, lateral-directional system noise. Other noise reducing features discussed are the low tip flight record for a large subsonic transport aircraft was analyzed to speed fans and a carefully selected number of fan blades and vanes identify the linear stability, control derivatives, and sensor errors. with adequate spacing between them. Attention is also given to the The same record was then processed through KASD. The purpose of development of a low emissions combustor, and reduction of fan this experiment was to determine the impact of more detailed sensor frame weight, through the use of graphite/epoxy material. The error identification on the estimation of the linear stability and YC. 15 engine also employs variable pitch fans to provide thrust control derivatives. V. T. reversal, thus saving weight. Finally, it is rioted that the tests have proven that the engines could be configu rated to meet the needs of a A79-50169 The T & E simulator - A comparison with powered lift system without excessively compromising performance flight test results. J. M. Rebel (U.S. Naval Air Test Center, Patuxent or weight, M.E.P. River, Md.(. Society of Flight Test Engineers, Journal, vol. 1, May 1979, p. 31-36. A79-50209 Factors controlling stability of swirling flames Development of an automatic carrier landing capability for the at diffusers in gas turbines. V. M. Domkundwar, V. Sriramulu, and F-14A aircraft is presented. The models of the aircraft and automatic M. C. Gupta (Indian Institute of Technology, Madras, India(. carrier landing system (ACLS( were constructed with information Institute of Energy, Journal, vol. 52, Mar. 1979, p. 17-20. 7 refs. that included flight test data. The simulator was then 'tuned.' First, The paper deals with experimental studies aimed at determining standard aircraft maneuvers, such as pitch and bank steps, were run the effect of diffuse angles on flame-stability characteristics and to on the simulator, time histories of these maneuvers were compared relate stability data to inlet flow conditions, diffuser angles, and with flight test data, and corrections to the models were made. Next, equivalence ratios. The blowoff data obtained for different diffusers a pilot who had recently flown the aircraft was asked to 'fly' the show that if diffuser angles are increased, flame stability is improved. simulator and comment on its fidelity. Based on comparison of The flame-stabilization mechanism is explained by using a recircu- measured aircraft frequency response data, touchdown statistics, and lation model. It is concluded that the blowoff velocity increases as the pilot opinion the F-14 ACLS simulation has been shown to be a the diffuser angles increase. . V. T. valid model that is capable of predicting flight test results. V. T.

A79.50236 # The aeroacouttics of advanced turbopropel- lers. D. B. Hanson (United Technologies Corp., Hamilton Standard A79-50206 Derivative engines for the 1980s will help limit Div., Windsor Locks, Conn.(. International Union of Theoretical and acquisition and maintenance costs. J. E. Worsham (General Electric Applied Mechanics, International Commission on Acoustics, and Co., Commercial Engine Div., Cincinnati, Ohio(. ICAO Bulletin, vol. AIAA, Symposium on Mechanics of Noise Generation Fluid Flows, 34, Apr. 1979, p. 14.17. Gdttingen, West Germany, Aug. 28-31, 1979, Paper. 12 p. 10 refs. It is noted that the projected increase in commercial aviation Advanced turbopropellers (prop-fans( are being developed in the will lead to greater demand for new aircraft and thus new engines. United States to improve the fuel economy of future transport The industry is shown to be emphasizing derivative engines. aircraft. To study their noise, various noise prediction systems have Attention is given to the advantages of such development such as been developed via the acoustic analogy and a helicoidal source rapid maturity of the design resulting in a reduced shop visit rate, model. A time domain formulation and two frequency domain and reduced acquisition costs. As an example the CFM56 engine, formulations are presented. Wind tunnel test data are presented to suitable for re-engineering narrow body aircraft such as the B-707, substantiate the theory and to show its limitations. Shadowgraphs DC-B, and DC-9, utilizes the core of a high performance engine and near field microphone signals for straight blades operating at previously developed for the U.S. Government. It is concluded that supersonic speeds indicate the presence of detached bow waves that meeting costs continues to be a major challenge for the airlines, the cannot be predicted from the acoustic analogy. Nonlinear effects aircraft companies, and the engine manufacturers, M,E.P. appear to be confined to a region within two chords of the blade tips and are greatly relieved by blade sweep. It is shown that noise of highly swept blades can be predicted with good accuracy using linear A79-50207 Aircraft engine developments centre on im- source theory. (Author) proved performance, higher efficiency. W. H. Sens (United Technolo- gies Corp., Commercial Products Div., East Hartford, Conn.). ICAO Bulletin, vol. 34, Apr. 1979, p. 18-23. Improvements that can be made to reduce the fuel consumption A79-50237 # Supersonic transport aircraft noise, problems of current engines are reviewed as well as for new production of noise reduction and establishment of standards (Shum sverkhzvu- versions of current engines. In addition, the potential fuel savings kovykh transportnykh samoletov, voprosy ego normirovaniia i with advanced turbofan engines are discussed. Four ways to improve snizheniia). B. N. MeI'nikov, Itogi Nauki / Tekhniki, Sari/a Vozdus.h- fuel consumption are covered: improvement in component perfor- nyl Transport. vol. 7, 1979, p. 5. 37, 42 refs. In Russian, mance, improved maintenance procedures that reduce the amount of Noise and sonic boom standards for supersonic transport aircraft engine performance deterioration with operational use, improvement are presented. Noise characteristics of supersonic transports equipped in the power plant cycle, and by designing the engine to be less with different types of high-temperature jet engines are outlined. sensitive to factors causing performance deterioration. Modification Research results and comparative analysis of noise characteristics of to current engines can improve fuel consumption by 5%. It is first-generation supersonic transports are given along with evaluation concluded that the advanced turbofan configuration has the poten- of the expected noise characteristics of second-generation supersonic tial of providing a 20% reduction in fuel burned relative to today's transport aircraft. Consideration is given to methods of noise designs for a high bypass ratio turbofan for 1990. M.E.P. reduction for the second-generation aircraft, including engine im- provement, implementation of exhaust systems for jet suppression, A79-50208 • QCSEE . The key to future short-haul air and implementation of specific takeoff and approach techniques. transport. C. C. Ciepluch (NASA, Lewis Research Center, Quiet, V. T. Clean, Short-Haul Experimental Engine Project Office, Cleveland, Ohio( and W. S. Willis (General Electric Co., Aircraft Engine Group, West Lynn, Mass.(. ICAO Bulletin, vol. 34, Apr. 1979, p. 24-29. A79-50240 # Current status of airport terminal complex The paper describes the design and test procedure for the development abroad (Sovremennoe sos-toianie razvitiia aerovokzal'- QCSEE (quiet, clean, short-haul experimental engine(. The engines nykh kompleksov za rubezhom). V. N. lvanov and M. G. Piskov, designed for the YC-14 and YC-15 STOL aircraft, both use a very Itogi Nauki I Tekhniki, Serila Vozdushnyi Transport, vol. 7, 1979, p. low fan pressure ratio to keep jet-flap noise about 3 dB below total 159-224. 26 refs. In Russian,

643 A79-50306

Airport terminal complex development before and after 1970 is The book contains an introductory-level discussion of basic fluid considered with attention given to finger, drive-in, gate room, and mechanics and thermodynamics. The contents are divided among pipe schemes, parking places, and baggage handling and loading- three major areas: flow fields for which the density may be assumed unloading concepts. Five passenger service system approaches are constant; flow fields for which the variations in density are presented: (1) flight check-in, (2) common check-in, (3) gate important; and topics with general application both to incompress- check-in, (4) drive-in and drive-to-your-gate, and (5) shuttle. Prin- ible and compressible aerodynamics. Discussions of the effects of ciples of transportation between airport terminals and aircraft are viscosity, compressibility, shock-boundary layer interactions, turbu- outlined including busing and plane mate techniques. Airport lence, and other practical aspects of contemporary aerodynamic terminal planning and design, curb space planning, and means of theory and design are also presented. Attention is given to passenger access to aircraft are discussed. Emphasis is placed on the characteristic parameters for airfoil and wing aerodynamics, two- use of mathematical models for calculating airport terminal capaci- dimensional incompressible flows around thin airfoils and about ties. V. T. wings of finite span, and subsonic and transonic flows. V.T.

A79-50306 A computer program for aircraft identification and derivative extraction. R. Hector, D. P. Maunder (USAF, Flight A79-50421 # Gas turbines for flight vehicle engines: Theory, Test Center, Edwards AFB, Calif.), and E. M. Cliff (Virginia design, and calculation fThird review and enlarged edition/ )Gazovye Polytechnic Institute and State University, Blacksburg, Va.). Society turbiny dvigatelei letatel'nykh apparatov: Teoriia, konstruktsiia I of Flight Test Engineers, Journal, vol. 1, Sept. 1979, 8-15. p. raschet /Third revised and enlarged edition/). V. I. Lokai, M. K. A computer program developed for the investigation of stability, Maksutova, and V. A. Strunkin. Moscow, Izdatel'stvo Mashino- control and performance derivatives of aircraft from flight test data stroenie, 1979. 448 p.42 refs. In Russian. is presented. The program involves the development of a maximum The book deals with the theory, calculation and projection likelihood technique with greater flexibility and accuracy, the methods, and designs of gas turbines used in aircraft gas-turbine and development of a new linearized set of equations of motion, and the liquid rocket engines as well as in auxiliary aircraft power plants. use of advanced programming technology for minimizing errors and Consideration is given to the physics of gas flows in channels as well reducing maintenance costs. The design permits operation in both as the thermo- and gas dynamics of turbines. Emphasis is placed on the batch and interactive graphic mode. Attention is given to problems of cooling gas turbines. A classification of cooling systems parameter identification which provides tools for She efficient use of for gas turbines is given along with calculation methods for different data in the estimation of constants appearing in mathematical models parts of gas turbines. Losses in gas turbines, gas turbine character- and for aiding in modeling of phenomena. C.F.W. istics, and operational processes parameters under cooling conditions are evaluated. Typical designs of the major components and units of gas turbines are presented along with strength and vibrational test methods for disks, blades, and shafts. V.T. A79-50307 Flight testing and simulator flight fidelity. R. T. Galloway (U.S. Naval Air Test Center, Patuxent River, Md.). Society of Flight Test Engineers, Journal, vol. 1, Sept. 1979, p. 22-31. 6 refs. A79-50427 The Swedish approach to escape system test- The paper outlines the role of the NAVAIRTESTCEN in ing. G. Niss (Saab-Scania AB, Linkoping, Sweden). In: Why flight simulator testing, simulator test experience, and fidelity problem test; Proceedings of the Ninth Annual Symposium, Arlington, Tex., areas. The major elements of the Navy test policy are outlined, October 4-6, 1978. Lancaster, Calif., Society of including assistance in specification preparation, proposal evaluation, Flight Test Engineers, 1978, p. 1-1 to 1-12. participation in in-plant acceptance testing, and adjusting hardware The paper deals with methods of obtaining maximum safety in and software to achieve proper flight fidelity. It is shown that the use current fighter aircraft escape systems and producing reliable test of NAVAIRTESTCEN flight test expertise has helped to maximize results. The test aircraft, a modified night fighter version of the the flight fidelity of recent major aviation training devices within the Lansen; seat and dummy pilot installation; and the test site where U.S. Navy and Marine Corps. Furthermore, test experience has most tests are performed at 500 ft and higher above the ground and shown that meaningful data can be obtained with simple hand-held in the 270 to 1150 km/h speed range are described. Seat and dummy instrumentation, and that the test pilot must refamiliarize himself acceleration during the drive phase, the effect of wind blast on pilot with the subtle aircraft characteristics during the evaluation period. and equipment and effectiveness of the restraint system are C.F.W. evaluated, and initial stability of the man-seat combination, stabilizer chute, the separation between the seat and the pilot, clearance between the dummy-parachute combination and the seat are A79-50368 Combined environment reliability test of the discussed. Parachute deployment sequence, the trajectory from common strategic Doppler system. J. F. Wagner, Ill (USAF, Flight ejection point till the dummy is in a fully deployed parachute, and Dynamics Laboratory, Wright-Patterson AFB, Ohio). In: Learning to inspection of dummy, dress, and equipment are described, and it is use our environment; Proceedings of the Twenty-fifth Annual concluded that changes required at high speed mutt be based on full Technical Meeting, Seattle, Wash., April 30-May 2, 1979. scale flight testing. A. T. Mount Prospect, III., Institute of Environmental Sciences, 1979, p. 574-577. 6 refs. A recently completed development program for a new common strategic Doppler system made use of preproduction combined A79-50428 An evaluation of sidestick force/deflection environment reliability testing to provide data for the source characteristics on aircraft handling qualities. S. B. Smith and C. M. selection process. This test was used instead of the previously Miller (USAF, Flight Test Center, Edwards AFB, Calif.). In: Why planned MIL-STD-781B reliability tests in order to subject the flight test; Proceedings of the Ninth Annual Symposium, Arlington, vendors' equipment to more realistic environmental conditions. This Tex., October 4-6, 1978. Lancaster, Calif., paper will discuss the effectiveness of the combined environment test Society of Flight Test Engineers, 1978, p. 2-1 to 2-17. 9 refs. in the competitive procurement process. (Author) A study of a variable force and motion sidestick controller programmed to simulate the handling characteristics of a high- A79-50375 Aerodynamics for engineers. J. J. Bertin (tex- performance stability fighter aircraft is presented. Precision air-to-air as, University, Austin, Tex.) and M. L. Smith (U.S. Air Force tracking of a target aircraft during level and windup turns, gross Academy, Colorado Springs, Cob.). Englewood Cliffs, N.J., acquisition and tracking involving large pilot inputs, and landings Prentice-Hall, Inc., 1979. 424 p. 123 refs. $28. were evaluated. The ratio of stick force to stick deflection and the

644 A79-50436 ratio of stick force to aircraft response, and the effect of sidestick Flight Research Center, Edwards AFB, Calif.). In: Why flight test; controller pre-filter characteristics were investigated. It was con- Proceedings of the Ninth Annual Symposium, Arlington, Tex., cluded that for very small displacements the range of stick October 4-6, 1978. Lancaster, Calif., Society of force/response gradients is' restricted, that there is a region of Flight Test Engineers, 1978, p. 10. 1 to 10-36. 13 refs, moderate stick displacement where performance is insensitive to This paper discusses the application of a maximum likelihood variations in force/response gradients, and that moderate stick estimator to dynamic flight-test data. The information presented is motion coupled with light to moderate stick force gradients results in based on the experience in the past twelve years at the NASA the best tracking performance. A. T. Dryden Flight Research Center of estimating stability and control derivatives from over 3,000 maneuvers from 32 aircraft. The overall A79-50429 Separation testing of large weapons from the approach to the analysis of dynamic flight-test data is discussed. B-i bomber. R. E. Little (Rockwell International Corp., El Segundo, Detailed requirements for data and instrumentation are discussed and Calif.). In: Why flight test; Proceedings of the Ninth Annual several examples of the types of problems that may be encountered Symposium, Arlington, Tex., October 4-6, 1978. are presented. (Author) Lancaster, Calif., Society of Flight Test Engineers, 1978, p. 4-1 to 4-14. This paper covers the flight test techniques and data analysis methods in use on the weapon separation test program for the B-i. A79-50434 AFFTC parameter identification experience. Weapon trajectory test results together with prediction methods are D. P. Maunder (USAF, Performance and Flying Qualities Branch, shown, and the importance of estimating methods and test instru- Edwards AFB, Calif.). In: Why flight test; Proceedings of the Ninth mentation is discussed. Weapon launch and trajectory parameters are Annual Symposium, Arlington, Tex., October 4-6, 1978. covered with comparisons taken from analytical wind tunnel and Lancaster, Calif., Society of Flight Test Engineers, flight test results. Weapon accuracy error budgets are presented in 1978, p. 11-1 to 11-18. Srefs. relation to Current capabilities of space positioning equipment, and The AFFTC experience With parameter identification and aircraft/weapon accuracy requirements. (Author) results of this application with respect to accuracy, contributions of otherwise unobtainable information, and cost effectiveness are presented. Parameter identification techniques in aircraft flight A79-50430 INACT . Interactive test data analysis. D. R. testing obtain aerodynamic, structural, and performance character- Haiwes (Bell Helicopter Textron, Fort Worth, Tex.). In: Why flight istics to assess control system performance and establish design test; Proceedings of the Ninth Annual Symposium, Arlington, Tex., criteria. The technique was used to provide mathematical description October 4-6, 1978. Lancaster, Calif., Society of of aircraft stability and control characteristics such as improved Flight Test Engineers, 1978, p. 6. 1 to 6-18. verification of performance criteria and improved dependability of The capability of interactive test data analysis (INACT) for high extrapolated flight characteristics. Parameter identification experi- speed data programs is based on new mini-computers. INACT was ence including test optimization, accuracy, flight test parameter developed to provide flight test engineers an on-line computer access identification comparisons with wind tunnel, and parameter identifi- during flight and laboratory vibration testing, and to command data cation and configuration effects are discussed. It is concluded that acquisition, analysis, and display on a graphics terminal in a parameter identification provided reduction and optimization of telemetry or the vibration control room. INACT can analyze up to 8 flight test programs, better verification of performance Criteria, channels of analog data from telemetry during flight testing, analog enhanced system development, and optimization of vehicle perfor- tape playback, or during ground vibration testing. Input command mance. A. T. form and conventions, examples of data analysis, and the use of INACT for flight testing are discussed, and it is concluded that A79-50435 Flight test technology development - A pre- INACT provides capabilities for data acquisition, time history view of DyMoTech. J. W. Hicks (USAF, Flight Test Center, Edwards displays, harmonic analysis, spectral analysis, damping estimation AFB, Calif.). In: Why flight test; Proceedings of the Ninth Annual using the complex exponential approximation, and transfer function Symposium, Arlington, Tex., October 4 .6, 1978. computation. A. T. Lancaster, Calif., Society of Flight Test Engineers, 1978, p. 12-1 to 12-11. 8refs. A79-50432 Estimation of longitudinal aircraft character- The scope of dynamic modeling technology (DyMoTech) for istics using parameter identification techniques. R. C. Wingrove instrumentation systems, flight test maneuvers, and performance (NASA, Ames Research Center, Aircraft Guidance and Navigation modeling techniques is presented. The purpose of DyMoTech is to Branch, Moffett Field, Calif.(. In: Why flight test; Proceedings of the develop dynamic flight test techniques and modeling to define the Ninth Annual Symposium, Arlington, Tex., October 4-6, 1978, aircraft performance characteristics, and to conduct an inflight Lancaster, Calif., Society of Flight Test Engi- comparison of four methods of extracting flightpath accelerations neers, 1978, p. 9-1 to 9-24. 22 refs. simultaneously from separate measurement systems on the test This study compares the results from different parameter aircraft. Four instrumentation systems will be compared during identification methods used to determine longitudinal aircraft takeoff and landing, Climbs, level accelerations, wind-up turns, and characteristics from flight data. In general, these comparisons have split-S maneuvers. It is concluded that DyMoTech seeks to develop a found that the estimated short-period dynamics (natural frequency, total approach to dynamic flight testing to save flight test time and damping, transfer functions) are only weakly affected by the type of program cost, provide a more complete definition of the perfor- identification method, however, the estimated aerodynamic coeffi- mance envelope, and greater model utility and versatility in which it cients may be strongly affected by the type of identification method. can predict both standard-day and non-standard day performance The estimated values for aerodynamic coefficients were found to data, flight manual preparation, mission analysis, and performance depend upon the type of math model and type of test data used with simulation. A. T. each of the identification methods. The use of fairly complete math models and the use of long data lengths, combining both steady and nonsteady motion, are shown to provide aerodynamic coefficient A79-50436 Evaluation of the radar altimeter reference values that compare favorably with the results from other testing method for determining altitude system positioning errors. J. D. methods such as steady-state flight and full-scale wind-tunnel Dinkel (Grumman Aerospace Corp., Calverton, N.Y.). In: Why flight experiments. (Author) test; Proceedings of the Ninth Annual Symposium, Arlington, Tax., October 4-6, 1978. Lancaster, Calif., Society of Flight Test Engineers, 1978, p. 13-1 to 13-18. A79-50433 • Considerations in the analysis of flight test The radar altimeter reference method for determining altitude maneuvers. K. W. Iliff, R. E. Maine, and T. D. Montgomery (NASA, system position errors which can reduce the number of flights

645 A79-50437

required to calibrate a system, manpower and supporting equipment the C-5A, L-1011, C-141A, and YC-141 B aircraft is presented. A is presented. The method has the advantages of instrumentation and study of the C-5A flight results showed that this specification was equipment in the test aircraft, coverage over a wide range of Mach too stringent in seven sections which were compared with flight test numbers and attack angles. In addition, it is independent of wind results in this investigation: phugoid stability, short-period response, speed and air temperature measurements, has high data productivity elevator control force gradient, lateral directional damping, roll mode per maneuver and flight, and its telemetry compatible system enables time constant, sideslip excursions, and roll control effectiveness. It determination of answers in real time. The radar altimeter reference was shown that: (1) sections dealing with lateral control, roll mode, method consists of runway flyover, atmosphere calibration, and sideslip excursions, and roll control effectiveness are too stringent for altitude pressure system calibration. The radar altimeter and pneu- Level 1 conditons; (2) phugoid stability, short period response, and matic altimeter, the flight test method, software, and test procedures control forces in maneuvering flight warrant adjustment in Level 1 were evaluated, and computer software was developed. It was requirement boundaries; and (3) the lateral directional damping concluded that the radar altimeter reference method provides a Section is too restrictive forLevel 2 conditions. A. T. viable means for determining altitude system position errors. A. T.

A79-50440 A simplified gross thrust computing technique A79-50437 ARIA takeoff performance flight test pro- for an afterburning turbofan engine. M. J. Hamer (Computing gram, H. A. Lebovitz (USAF, Directorate of Flight Test Engineering, Devices Co., Ottawa, Canada) and F. J. Kurtenbach (NASA, Flight Wright-Patterson AFB, Ohio). In: Why flight test; Proceedings of the Research Center, Propulsion Controls Branch, Edwards AFB, Calif.). Ninth Annual Symposium, Arlington, Tex., October 4-6, 1978. In: Why flight test; Proceedings of the Ninth Annual Symposium, Lancaster, Calif., Society of Flight Test Engi- Arlington, Tex., October 4-6, 1978. Lancaster, neers, 1978, p. 15-1 to 15-13. Calif., Society of Flight Test Engineers, 1978, p. 22-1 to 22-20. 8 The verification and subsequent testing to reduce the impact of refs, Research sponsored by the United States/Canada Defence the extended takeoff roll on the advanced range instrumented Production Sharing Program. aircraft (ARIA) is presented. Two EC-135N ARIA. aircraft experi- A simplified gross thrust computing technique extended to the enced a takeoff ground roll greater than predicted by the flight F100-PW-100 afterburning turbofan engine is described. The tech- manual. Since in the event of an engine failure at or near the critical nique uses measured total and static pressures in the engine tailpipe engine failure speed, the aircraft would be incapable of aborting the and ambient static pressure to compute gross thrust. Empirically takeoff or continuing it, a hazard report was prepared recommending evaluated calibration factors account for three-dimensional effects, action to verify the takeoff performance. The verification test the effects of friction and mass transfer, and the effects of indicated that the extended ground roll is due to an interaction of simplifying assumptions for solving the equations. Instrumentation the enlarged nose radome and the ground resulting in a large increase requirements and the sensitivity of computed thrust to transducer in drag. Ground/radorne interaction tests were made, and it was errors are presented. NASA altitude facility tests on F100 engines concluded that the EC-135N aircraft exhibit an extended ground run (computed thrust versus measured thrust) are presented, and 15% greater than predicted, aircraft subsystems were functioning calibration factors obtained on one engine are shown to be applicable properly, and the extended ground run appears to be due to a to the second engine by comparing the computed gross thrust. It is ground/radome interaction. A. T. concluded that this thrust method is potentially suitable for flight test application and engine maintenance on production engines with A79-50438 The evolution of the high-angle-of-attack a minimum amount of instrumentation. A. T. features of the F-16 flight control system. C. K. Clark, J. E. Walker, and J. K. Buckner )General Dynamics Corp., .Fort Worth, Tex,), In: A79-50441 J85-CAN-15 compressor stall and flameout Why flight test; Proceedings of the Ninth Annual Symposium, investigation. W. L. Macmillan (Department of National Defence, Arlington, Tex., October 4-6, 1978, Lancaster, Directorate of Aeronautical Engineering and Simulators, Ottawa, Calif., Society of Flight Test Engineers, 1978, p. 17-1 to 17-21. Canada), R. M. McGimpsey (Aerospace Engineering Test Establish- 'Eves-out-of-the-cockpit' air combat maneuvering achieved ment, CFB Cold Lake, Alberta, Canada), and K. D. Nelson. In: Why through the use of angle-of-attack and structural-load-limiting fea- flight test; Proceedings of the Ninth Annual Symposium, Arlington, tures of the flight control system is presented. Spin-tunnel results Tex., October 4-6, 1978. Lancaster, Calif., revealed a fast-flat spin mode that required an unacceptable number Society of Flight Test Engineers, 1978, p. 23-1 to 23-16. of turns to recover, and a no-spin condition resulted when flaperons An investigation of the J85-CAN-15 compressor inlet tempera- were deflected to roll in the direction of the spin. A yaw-rate limiter ture sensing system to prevent compressor stall and flameout during was designed that automatically prevented spins by positioning the flight operations is presented. Engine testing and stall analysis which flaperon and rudder in the direction defined by the spin tunnel to demonstrated the compressor inlet temperature sensitivity of the prevent the spin. Flight testing showed that departures may develop engine, the flight test program to determine engine and sensing from high angle-of-attack sideslips and rolling maneuvers. A rudder system performance, and flight test techniques are described showing fadeout was designed which prevented yaw departures from full- that there were errors in the T2 sensing system. It was shown that rudder side-slips, a roll-rate command limiter was installed, pitch-axis the compressor inlet temperature )T2) sensing systems on the modifications were made in the flight control system, and a J85-CAN-15 operate at temperatures warmer than the compressor rudder-pedal command limiter was designed. It was concluded that inlet total temperature (CIT), that the T2 cutback does not occur in these systems improved the high angle-of-attack handling qualities of accordance with that predicted by the engine CFTO's, T2 cutback the F-16 and allow the pilot to fly 'eye-out-of-the-cockpit' air- can be observed on cockpit instruments, insulating the T2 duct did combat maneuvering with maximum command inputs and without not significantly reduce the T2 sensing system error, and engine fear of departure. A. T. anti-ice provides an effective means of reducing compressor discharge pressure during afterburner initiation. A. T.

A79-50439 Evaluation of selected class Ill requirements of A79-50444 Testing the F-18 at the U.S. Naval Air Test MIL-F-878513 /ASG/. 'Flying Qualities of Piloted Airplanes'. C. C. Center. J. L. Dunn (U.S. Naval Air Tess Center, Patuxent River, Withers )Lockheed-Georgia Co., Marietta, Ga.). In: Why flight test; Md.). In: Why flight test; Proceedings of the Ninth Annual Proceedings of the Ninth Annual Symposium, Arlington, Tex., Symposium, Arlington, Tex., October 4-6, 1978. October 4-6, 1978. Lancaster, Calif., Society of Lancaster, Calif., Society of Flight Test Engineers, 1978, p. 26-1 to Flight Test Engineers, 1978, p. 19-1 to 19-18. 5 refs. 26-11. A comparison of the requirements of the military specification The U.S. Navy is procuring the F-18 as a replacement for the 'Flying Qualities of Piloted Airplanes' with flight test results from F-4 and A-7 aircraft starting in 1983. The F-18 evolved from the

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YF-17 prototype which was a part of the U.S. Air Force Light The aeronautical information data subsystem (AIDS) is pre- Weight Fighter Competition in 1974. F-18 design advancements sented as a means to help alleviate the problems facing air traffic include control-by-wire digital flight control system, cockpit control at present. The method employs a data base that interlinks designed for one man operability, state-of-the-art avionics integration radar, flight plan and progress, and information data, and is also capable of simultaneous retrieval for multiple users. It is suggested by software/multiplex techniques, and a high use of composite materials. From the Navy viewpoint, the unique aspect of the F-18 that this system be implemented as the third vital data category in Full Scale Development (FSD) program is that it will be principal order to close the air traffic control data processing function loop. sited at the Naval Air Test Center (NAVAIRTESTCEN), Patuxent Such an implementation would improve air safety by increased River, Maryland. Present plans for the FSD program are based on 11 responsiveness of the air traffic services to pilots requests for test aircraft and 3100 test flights with first flight scheduled for late operational flight information availability of vital and important September 1978. NAVAIRTESTCEN involvement to date has system data to air traffic controllers, and other air navigation services consisted of participation in the design review process, Navy operators. C.F.W. Integrated Test and Evaluation Working Group, Aircrew Systems Advisory Panel, and participation in simulation evaluations in St. Louis. The On-site preparation phase has consisted of establishing a A79-50921 Modern systems for air traffic control. P. A. management plan, ensuring that adequate facilities, support aircraft, Jorgensen (Selenia SpA, Rome, Italy). (International Federation of airspace, and data and instrumentation systems are available. Air Traffic Controllers' Associations, Annual Conference, 18th, (Author) Brussels, Belgium, Apr. 23-27, 1979.) The Controller, vol. 18, Sept. 1979, p. 35-37. A79-50499 # Airport power supply (Elekirosnabehenie The paper deals with air traffic systems and equipment which aeroportov). I. S. Gladysh and P. L. Andreev. Moscow, ldatel'stvo can conveniently be put into operation, within a reasonable amount of time in order to upgrade present flaws. Attention is given to Transport, 1979. 248 p. In Russian. The book deals with the basic principles and instrumentation of distributed intelligence, where the various tasks and functions can airport power supply. Characteristics of power consumers and clearly be defined and divided to be performed by dedicated techniques for reducing power consumption are discussed. General computers, each placed where the task or function may best be problems of power supply are considered, including electric network performed. The typical system structure of a computer and its radar design, methods of design-power selecting, and determining wire and links is shown, depicting the interface between the radar data cable cross sections in accordance with heating and voltage-loss processor and the display processor, radar head processor, and flight requirements. The electric power equipment and relay protection data processor. With this system, it is found that error detection devices for airport transformers and power stations are described capability is better than 80% within aircraft identification range, and along with their design and circuitry. Attention is given to the number of false alarms can be kept to 10 to the minus 8th. automatics and telemechanics of electric power networks, methods C.F.W. for calculating short-circuit current and selecting power, relay protection, and grounding equipment. The electrotechnic laboratory (ETL-1 M) is also described. V.T. A79-50925 Laser velocimeter applied to the study of circular distortion effects in a low speed compressor. J. Labbe (ONE RA, Chätillon-sous-Bagneux, Hauts-de-Seine, France(. (Sym- A79-50606 Radiation from quarter-wavelength monopoles posium on Measuring Techniques in Transonic and Supersonic on finite cylindrical, conical, and rocket-shaped conducting bodies. Cascade Flow, Leatherhead, Surrey, England, Mar. 22, 23, 1979.) N. N. I. Fahmy (Cairo University, Cairo, Egypt; Riyadh, University, ONERA, TP no. 1979-30, 1979. 20 p. Riyadh, Saudi Arabia) and A. Z. Botros (Cairo University, Cairo, In order to investigate the capabilities of laser velocimetry for Egypt). IEEE Transactions on Antennas and Propagation, vol. AP-27, the study of perturbations due to circular distortions in an axial Sept. 1979, p. 615-623. 14 refs. compressor, preliminary experiments have been performed on a low A theoretical-numerical technique, based on Maue's integral speed compressor. The instrument used is a back-scattered Doppler equation, is applied for the determination of radiation patterns of velocimeter designed by ONERA. It is equipped with a 1400 mW airborne antennas comprising one or more quarter-wavelength argon ion laser used in its green line. Signals, picked up by monopoles, straight or bent, on finite cylindrical, conical, and synchronous sampling, are recorded by a frequency counter. Veloci- rocket-shaped conducting airframes. The induced surface currents on ty (average 15 m/sec) and turbulence components are computed the conducting body are first determined whence the total radiation off-line. Three locations were investigated, namely upstream, in the fields are obtained. In the cases of a single monopol y on a conducting mid-interbiade channels and downstream of the impeller. Results body, the surface currents and radiation patterns are studied in view obtained by LDV show deformations of the velocity vector and are of varying the geometrical parameters of the body as well as the in good agreement with average values deduced from previous position and relative orientation of the monopol y . For the case of experiments performed with pressure probe techniques. (Author( two diametrically opposite monopoles on a finite cylinder, the effect of varying the relative phasing is studied. A physical interpretation of the variation with various parameters of the surface currents and the radiation fields is endeavored wherever feasible, and important results are concluded. Experimental investigation of radiation from one of the theoretically treated models, namely that of a bent monopole on a finite frustum of a cone, showed excellent agreement with computed results. This establishes the validity of the theoretical-numerical technique as well as the computed radiation patterns for various cases. (Author)

A79-50920 Aeronautical information data subsystems /AIDS/. F. W. Fischer (Studiengemeinschaft für Flugsicherung, Westerngrund, West Germany). The Controller, vol. 18, Sept. 1979, p- 30-33.

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Systems Acquisition Review Council (DSARC) reviews as well as other cost reviews. This report provides a detailed documenta- tion of the cost-estimating relationships (CERs) developed from FY-77 data. In addition, the report has been significantly enhanced in order to serve as a handbook and training aid for Op-96D aircraft analysts. For each cost element in the structure, this report provides: (1) a definition; (2) discussion of the definition and other aspects of how, where, and why these costs are incurred, points of contact including organizational codes and telephone numbers, historical data, and sources for planning data; (3) cost-estimating relationship, including all computational STAR ENTRIES procedures, regression statistics for the CER, and the data base; (4) an alternative CER (in many cases) with the same detail as above; and, (5) an example calculation. GRA

N7930138*# Rail Co.. Baltimore, Md. N79-30141# Information Spectrum, Inc.. Warminster, Pa. MAINTENANCE COST STUDY OF ROTARY WING AIR- MAINTENANCE IMPROVEMENT: AN ANALYSIS AP- CRAFT, PHASE 2 Interim Report PROACH INCLUDING INFERENTIAL TECHNICAL DATA Aug. 1979 34 p Final Report. 27 Dec. 1977 - 15 Mar. 1919 (Contract NAS2-9143) Milton Clyman, Philip S. Grenetz. and Raymond R. Mellott (NASA-CR-152291( Avail: NTIS HC A03/MF AOl CSCL 15 Mar. 1979 322 p 02A (Contract M0A903-78-C-01 76) The Navy's maintenance and materials management data (AD-A068382; lSl-W-7958-02C( Avail: NTIS base was used in a study to determine the feasibility of predicting HC A14/MF AOl CSCL 01/3 unscheduled maintenance costs for the dynamic systems of Tables of input information and output data which were military rotary wing aircraft. The major operational and design used in assessment of the economic impact (cost and downtime) variables were identified and the direct maintenance man hours of potentially avoidable maintenance actions are presented for per flight hour were obtained by step-wise multiple regression the F-14A fire control. A-7E and S-3A bombing navigation, and analysis. Five nonmilitary helicopter users were contacted to supply the S-3A landing gear. A.R.H. data on which variables were important factors in civil applications. These uses included offshore oil exploration and support, police and fire department rescue and enforcement, logging and heavy N7930143*# National Aeronautics and Space Administration. equipment movement, and U.S. Army military operations. The Ames Research Center, Moffett Field, Calif. equations developed were highly effective in predicting unsched- UPPER-SURFACE MODIFICATIONS FOR C SUB I MAX uled direct maintenance man hours per flying hours for military IMPROVEMENT OF SELECTED NASA 6-SERIES AIRFOILS aircraft, but less effective for commercial or public service C. A. Szelazek and Raymond M. Hicks Aug. 1979 79 p refs helicopters, probably because of the longer mission durations Prepared in cooperation with Computer Information Systems, Cupertino, Calif. and the much higher utilization of civil users. A.R.H. (NASA-TM-78603; A-7889( Avail: NTIS HC A05/MF AOl CSCLO1A National Aeronautics and Space Administration. N7930139*# The thickness of the upper surface of 64 airfoils was increased Hugh L. Dryden Flight Research Center, Edwards, Calif. from the leading edge to the position of maximum thickness. PERFORMANCE EVALUATION METHOD FOR DISSIMILAR The modifications were generated using a numerical optimization AIRCRAFT DESIGNS routine coupled with an aerodynamic analysis code. The type of Harold J. Walker Sep. 1979 72 refs p modification presented can be used for aircraft design or for the (NASA-RP-1042: H-1064( Avail: NTIS HC A04/MF AOl CSCL retrofit of current aircraft to improve the stall characteristics 02A and climb performance. The coordinates of the modified airfoils A rationale is presented for using the square of the wingspan are presented with plots of the forward 45% of the profiles and rather than the wing reference area as a basis for nondimensional pressure distributions for both the modified and unmodified comparisons of the aerodynamic and performance characteristics sections at an angle of attack of 14 degrees. of aircraft that differ substantially in planform and loading. Working K. L. relationships are developed and illustrated through application to several categories of aircraft covering a range of Mach numbers N7930145*# Bihrle Applied Research, Inc.. Jericho, N. V. from 0.60 to 2.00. For each application, direct comparisons of ROTARY BALANCE DATA FOR A TYPICAL SINGLE-ENGINE drag polars, lift-to-drag ratios, and maneuverability are shown GENERAL AVIATION DESIGN FOR AN ANGLE-OF-ATTACK for both nondimensional systems. The inaccuracies that may arise RANGE OF 8 DEG TO 90 DEG. 1: HIGH-WING in the determination of aerodynamic efficiency based on MODEL B reference area are noted. Span loading is introduced independently William Bihrle. Jr and Randy S. Hultberg Sep, 1979 497 p in comparing the combined effects of loading and aerodynamic refs efficiency on overall performance. Performance comparisons are (Contract NAS1-14849( made for the NACA research aircraft, lifting bodies, century-series (NASA-CR-3097l Avail NTIS HC A21/MF AOl CSCL 01A fighter aircraft. F- il 1A aircraft with conventional and supercriti- Aerodynamic characteristics obtained in a rotational flow cal wings, and a group of supersonic aircraft including the B-58 environment utilizing a rotary balance located in a spin tunnel and XB-70 bomber aircraft. An idealized configuration is included are presented in plotted form for a 1/6.5 scale, single engine, in each category to serve as a standard for comparing overall high wing, general aviation airplane model. The configurations efficiency. Author tested included the basic airplane, various wing leading-edge devices, tail designs, and rudder control settings as well as airplane N79-30140# Administrative Sciences Corp.. Alexandria, Va. components. Data are presented without analysis for an angle NAVAL AIRCRAFT OPERATING AND SUPPORT COST- of attack range of 8 deg to 90 deg and clockwise and E1MAtING MODEL FY 1977 REVISION counter-clockwise rotations covering an omega b/2V range from 0 to 0.85. Author Feb. 1979 199 p refs Revised (Contract N00014-77-C-0180( (AD-A068175; ASC'R-120; ASC-R-1 16-RevI Avail: NTIS N7930147*# National Aeronautics and Space Administration. HC A09/MF AOl CSCL 05/1 Langley Research Center, Hampton, Va. In fiscal year 1974, Administrative Science Corp. developed FLOW VISUALIZATION STUDIES OF A GENERAL RE- a parametric cost-estimating model which has been updated and SEARCH FIGHTER MODEL EMPLOYING A STRAKE-WING documented several times and used to support numerous Defense CONCEPT AT SUBSONIC SPEEDS

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James M. Luckring Aug. 1979 93 p view of a representative test model configuration; detailed sketches (NASA-TM-80057; L-12673( Avail: NTIS HC A05/MF AOl of the pertinent configurations changes; and the relevant CSCL O1A aerodynamic data. A systematic wind tunnel study was conducted in the Langley GRA high-speed 7 by 10 foot tunnel to document, by oil-flow photographs, the surface flow patterns for configurations N79-30151# Naval Ship Research and Development Center, incorporating strake-wing geometries indicative of current and Bethesda, Md. Aviation and Surface Effects Dept. proposed maneuvering aircraft. The configurations employed A FLOW FIELD STUDY FOR TOP MOUNTED INLETS ON combinations of strakes with reflexed planforms having exposed FIGHTER AIRCRAFT CONFIGURATIONS Final Report, Oct. spans of 10 percent. 20 percent. and 30 percent of the reference 1977 - Sep. 1978 wing span and wings with trapezoidal planforms having leading- Steven W. Prince Jan. 1979 61 p refs edge sweep angles of approximately 30 deg. 44 deg. and 60 deg. (F41421000) Tests were conducted at Mach numbers of 0.3 and 0.5 and at (AD-A069732; DTNSRDC/ASED . 79/03( Avail: NTIS angles of attack ranging from approximately 5 deg to 30 deg in HC A04/MF AOl CSCL 20/4 5 deg increments at 0 deg sideslip. The configurations incorpora- A flow visualization study was conducted for top mounted ting the strake-wing geometries exhibited more organized flow inlets on fighter aircraft. A generic fighter model was tested at patterns with smaller asymmetries to higher angles of attack low speed in a wind tunnel with a tuft grid mounted on the than the corresponding configurations incorporating the wing-alone upper fuselage. Tuft patterns were photographed in four geometries did. Author longitudinal positions from 0 to 39 deg angle of attack and from 0 to 30 deg sideslip. Various configurations were tested N79-30148# Northrop Corp.. Hawthorne, Calif. Aircraft with a high or low delta wing. two leading edge extensions and Group. two canards. The results indicate that the downwash from leading ANALYSIS OF WIND TUNNEL DATA PERTAINING TO HIGH edge extensions or canards can produce fairly smooth and straight ANGLE OF ATTACK AERODYNAMICS. VOLUME 1: flow to high angles of attack and moderate angles of sideslip TECHNICAL DISCUSSION AND ANALYSIS OF RESULTS for an inlet mounted on the upper fuselage surface, GRA Progress Report, Jun. 1977 - Apr. 1978 Jack W. Headley Jul. 1978 180 p 2 Vol. (Contract F33615-77-C-3062; AF Proj. 24041 N79-30161# Deutsche Forschungs- und Versuchsanstalt fuer (AD-A069646; NOR-78-69-Vol-1; AFFDL-TR-78-94-Vol-1) Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer Avail: NTIS HC A09/MF AOl CSCL 20/4 Aerodynamik. This report provides a technical discussion and analysis of THEORETICAL ESTIMATION OF NONLINEAR LONGITUDI- wind tunnel data obtained from tests conducted on a family of NAL CHARACTERISTICS OF WINGS WITH SMALL AND Northrop fighter aircraft. These tests were performed mainly in MODERATE ASPECT RATIO BY THE VORTEX-LATTICE the Northrop Low Speed Wind Tunnel, and cover the time period METHOD IN INCOMPRESSIBLE FLOW between 1966 and 1976. This report concentrates on data in Wolfgang Schroeder Sep. 1978 82 p refs In GERMAN; the stall post-stall region, and for convenience is provided in ENGLISH summary Report will also be announced as translation two sections. This volume presents the results of the analysis (ESA-TT-585) of wind tunnel data which concentrates on the high angle of IDLR-FB-78. 26l Avail: NTIS HC A05/MF AOl; DFVLR, Cologne attack regime, and on three major aircraft components. These DM 31,80 components are the nose and forebody, the wing leading edge A nonlinear vortex-lattice method is described applying a extension, and the vertical tail. The effects of geometric force-free condition to the vortex sheet giving the trailing, side- changes in these components on the aircrafts' high angle of and leading edges, respectively. In extensive test runs various attack aerodynamics are analysed. Wherever possible design influences on the numerical stability of the iterative rolling-up guidelines which identify the sensitivity of aerodynamic character- process were studied such as the force-free condition of the istics to geometric parameter variations are presented. Geometric wake, the number of horseshoe vortices, the panel distribution changes or effects which were configuration dependent are also along span and chord, the representation of the wakes by chains discussed. The second volume. Volume 2: 'Data base.' contains of straight vortex elements of different length and number, and summaries of the wind tunnel tests which were selected to the introduction of an artificial friction parameter. Because of provide data for the analysis. GRA numerical difficulties the slender delta wing itself could not be treated completely. These numerical difficulties resulting from the singular behavior of line vortices are described and ways of N79.30149# Northrop Corp.. Hawthorne, Calif. Aircraft overcoming them are suggested. Author (ESAI Group. ANALYSIS OF WIND TUNNEL DATA PERTAINING TO HIGH N79-30162# National Technical Information Service, Springfield, ANGLE OF ATTACK AERODYNAMICS. VOLUME 2: DATA Va. BASE Progress Report. Jun. 1977 - Apr. 1978 LIGHTER THAN AIR VEHICLES. CITATIONS FROM THE Jack W. Headley Jul. 1978 571 p refs 2 Vol NTIS DATA BASE Progress Report. 1964 - Mar. 1979 (Contract F33615-77-C-3052; AF Prol. 2404) Guy E. Habercom, Jr. May 1979 256 p Supersedes (AD-A069647; NOR-78-69-Vol-2 AFFDL-TR-78-94-Vol-2) NTIS/PS-78/0409; NTIS/PS-77/0374 Avail: NTIS HC A24/MF AOl CSCL 20/4 (NTIS/PS. 79/047 1/7; NTIS/ PS-78/0409; NTIS/PS-77/0374( This volume presents, in summary form, the geometric and Avail: NTIS HC $28.00/MF $28.00 CSCL 01C aerodynamic data used as a basis for the design guidelines Designs and applications of balloons, dirigibles, and airships presented in Volume 1. The summaries have been divided into are investigated in this Government sponsored research. Passenger eight sections, the first seven being the low speed tests, which or cargo transport. timbering, tethering. and fabric selection are include almost all the configuration development studies and discussed. Meteorological balloons are excluded. This updated most of the high AOA testing. Data summaries for the transonic bibliography contains 250 abstracts, 16 of which are new entries and supersonic testing form the eighth and last section. Because to the previous edition. GRA of the considerable quantity of data available from all the testng (some test reports containing as much as thirteen volumes), it N79-30163# National Technical Information Service, Springfield, is not practical to include the summaries in all the basic Va. aerodynamic data available. In general, only the main aerody- LIGHTER THAN AIR VEHICLES. CITATIONS FROM THE namic effects are presented or summarized, and for more detailed ENGINEERING INDEX DATA BASE Progress Report. information on a particular configuration, reference should be 1970 - Apr. 1979 made to the actual wind tunnel report. All the data summaries Guy E. Habercom,Jr. May 1979 88 p Supersedes NTIS/PS.78/ are presented in a similar way, and include the following 0410; NTIS/PS-77/0375 information: a data sheet including the test report title, a (NTIS/PS-79/0472/5; NTIS/PS-78/041 0; NTIS/PS.77/0375( summary of the report, and the test conditions; a general three Avail: NTIS HC $28.00/MF $28.00 CSCL 01C

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Design and applications of balloons, dirigibles, and airships Washington GPO 1978 285 p refs Hearings on S. 3363 are investigated. Passenger or cargo transport, timbering, tethering, before the Subcomm. on Aviation of the Comm. on Commerce. and fabric selection are discussed. Meteorological balloons are Sc.. and Transportation. 95th Congr., 2d Sess., 22-24 Aug. excluded. This updated bibliography contains 82 abstracts. 8 of 1978 which are new entries to the previous edition. GRA (GPO-34-912) Avail: Subcomm. on Aviation. Testimony was given and arguments were heard to amend N79-30164 Fordham Univ.. New York, N. Y. the Federal Aviation Act of 1958 in order to promote competition FINANCING THE CAPITAL REQUIREMENTS OF THE US in International Air Transportation, provide greater opportunities AIRLINE INDUSTRY IN THE 1980'S Ph.D. Thesis for United States air carriers, create a structure and establish Robert William Mandell 1979 245 p goals for developing United States International .Aviation Avail: Univ. Microfilms Order No. 7918290 negotiating policy, and for other purposes. M.M.M. The study presented estimated capital requirements from the close of this decade to the close of the maximum fleet replacement N79-30169# Technology/ Scientific Services, Inc., Dayton, Ohio. cycle in 1994, under alternative assumptions. It also forecasted ATMOSPHERIC ELECTRICITY HAZARD (AEH) Final Report, internally generated funds and reasonable amounts of additional 11 Jul. - 30 Sep. 1978 debt which can be summoned to meet those needs It was Arturo V. Serrano Dec. 1978 168 p refs concluded that in order for the industry to approach meeting (Contract F33601-78-D-0042; AF Proj. 2202) the projected levels of demand for air travel. the following (AD-A069338; T/SSI-0140-01: AFFO L-TR-78- 164) Avail: measures are imminently required: (1) liberalization of the NTIS NC A08/MF AOl CSCL 01/3 investment tax credit with respect to the purchase of new aircraft; A literature survey relating to the survivability of aircraft (2) swift deregulation of the industry; and (3) permit mergers transparencies and electrical circuits embedded within them was between airlines with complementary route structures. performed. The types of materials used in transparencies and Dissert. Abstr. their edge construction were identified. the electrical properties of interest were defined along with test methods in use or available, N79-301 65*# Lightning Technologies, Inc., Pittsfield, Mass. the availability of electrical properties for the materials of interest THE FEASIBILITY OF INFLIGHT MEASUREMENT OF was determined, the physiological hazards were documented, LIGHTNING STRIKE PARAMETERS and analytical methods for evaluation of transparency systems K. E. Crouch and J. A. Plumer Oct. 1978 91 p refs were identified. As a result of this study it was concluded that ontract NAS1-15216( the electrical parameters of interest are affected by temperature, (NASA-CR-158981) Avail: NTIS HC A05/MF AOl CSCL frequency and exposure and that data for the materials of interest O1C are not generally available over the ranges of interest for these The appearance of nonmetallic structural materials and parameters. It was also concluded that insufficient information microelectronics in aircraft design has resulted in a need for is currently available for evaluation of the physiological hazards. better knowledge of hazardous environments such as lightning Finally, analytical models for evaluation of transparency systems and the effects these environments have on the aircraft. This in an electromagnetic environment were found available that feasibility study was performed to determine the lightning could be used to analyze transparency designs. However, these parameters in the greatest need of clarification and the perform- methods need to be computerized and validated. Recommenda- ance requirements of equipment necessary to sense and record tions are made to eliminate existing data gaps by tests and these parameters on an instrumented flight research aircraft. It analyses. GRA was found that electric field rate of change, lightning currents, and induced voltages in aircraft wiring are the parameters of N79-30173'# National Aeronautics and Space Administration. greatest importance. Flat-plate electric field sensors and resistive Langley Research Center. Hampton, Va. current shunts are proposed for electric field and current sensors, RADIO-CONTROLLED MODEL DESIGN AND TESTING to provide direct measurements of these parameters. Six bit TECHNIQUES FOR STALL/SPIN EVALUATION OF GENER- analog-to-digital signal conversion at a 5 nanosecond sampling AL-AVIATION AIRCRAFT rate, short-term storage of 85000 bits and long term storage of Sanger M. Burk, Jr. and Calvin F. Wilson. Jr. (Piper Aircraft 5 x 10 to the 7th power bits of electric field, current and Corp.. Lock Haven, Penn.) 1975 63 p refs Presented at the induced voltage data on the airplane are proposed, with readout 1975 SAE NaN. Business Aircraft Meeting, Wichita. Kansas, and further analysis to be accomplished on the ground. A 8-11 Apr. 1975 NASA F-106B was found to be suitable for use as the research (NASA-TM-80510( Avail: NTIS NC A04/MF AOl CSCL aircraft because it has a minimum number of possible lightning 01C attachment points, space for the necessary instrumentation, and A relatively inexpensive radio-controlled model stall/spin test appears to meet operational requirements. Safety considerations technique was developed. Operational experiences using the are also presented. F.O.S. technique are presented. A discussion of model construction techniques, spin-recovery parachute system, data recording system, and movie camera tracking system is included. Also discussed are a method of measuring moments of inertia, N79-30167# National Transportation Safety Board, Washington, scaling of engine thrust, cost and time required to conduct a D. C. Bureau of Technology. program, and examples of the results obtained from the flight SPECIAL INVESTIGATION REPORT: WING FAILURE OF tests. K. L. BOEING 747-131 NEAR MADRID, SPAIN, 9 MAY 1976 6 Oct. 1978 41 p refs Committee on Armed Services (U. S. House). (NTSB-AAR-78-12( Avail: NTIS NC A03/MF AOl N79-30174 On May 9. 1976, an Imperial Iranian Air Force Boe- ENFORCER AIRCRAFT ing 747-131 crashed as it approached Madrid, Spain. Witnesses Washington GPO 1978 154 p refs Hearing before the observed lightning strike the aircraft followed by fire, explosion, Research and Development Subcomm. of the Comm. on Armed and separation of the left wing. The report includes fire pattern Services, 95th Congr., 2d Sess., 22 Jun. 1978 studies, structural failure descriptions, trajectory analysis. fuel (GPO-32-569; HASC-95-86( Avail: Research and Development flammability calculations, gust loading analysis, and an analytical Subcomm. G.Y. The utility of a privately developed Enforcer-type aircraft as treatment of several hypotheses. a tank killer in either the battlefield interdiction or close air support is assessed with emphasis on lethality and vulnerability. Characteristics are compared to those of the A-10 aircraft. A.R.H. N79-30168 Committee on Commerce. Science. and Transporta- tion (U. S. Senate). N7930175*# Foster-Miller Associates, Inc., Waltham, Mass. INTERNATIONAL AIR TRANSPORTATION COMPETITION HEAVE-PITCH-ROLL ANALYSIS AND TESTING OF AIR ACT OF 1978 CUSHION LANDING SYSTEMS Final Report

651 N79-30176

A. B. Boghani, K. M. Captain, and D. N. Wormley Feb. 1978 Raymond B. Smith, George M. Yamakawa, John R. Niemann, 205 refs p Joseph C. Watts. and Jerry A. Guin May 1979 33 p (Contract NAS1-12403) (AD-A069827; tJ5AAEFA-78-07) Avail: NTIS (NASA-CR-2917( Avail: NTIS HC A10/MF AOl CSCL 01C HC A03/MF AOl CSCL 01/2 The analyical tools (analysis and computer simulation) needed The United States Army Aviation Engineering Flight Activity to explain and predict the dynamic operation of air cushion landing conducted takeoff performance tests on an OV-1C aircraft, serial systems (ACLS) is described. The following tasks were performed: number 67-18918, from 11 April through 19 July 1978. The the development of improved analytical models for the fan and aircraft was tested at Edwards Air Force Base )field elevation the trunk; formulation of a heave pitch roll analysis for the 2273 feet) and South Lake Tahoe. California (field elevation complete ACLS: development of a general purpose computer 6262 feet). Twelve flights totaling 6.9 productive flight hours simulation to evaluate landing and taxi performance of an ACLS were conducted. Takeoff performance tests were conducted on eauipøed aircraft; and the verification and refinement of the the OV-1C to substantiate the performance data currently analysis by comparison with test data obtained through lab testing incorporated in the operator's manual. Tests were conducted of a prototype cushion. Demonstration of simulation capabilities using two normal takeoff techniques and a minimum run takeoff through typical landing and taxi simulation of an ACLS aircraft technique at each of three gross weights. All takeoffs were made are given. Initial results show that fan dynamics have a major from hard, dry, paved level runways. Test results show that the effect on system performance. Comparison with lab test data estimated data for normal takeoff is satisfactory but the data (zero forward speed) indicates that the analysis can predict most for the minimum run technique in the operator's manual —Is- of the key static and dynamic parameters (pressure, deflection, optimistic. GRA acceleration. etc.) within a margin of a 10 to 25 percent. A.W.H. N79-30179// Textron Bell Helicopter, Fort Worth, Tex. HELICOPTER OBSTACLE STRIKE TOLERANCE CONCEPTS N79-30176'# National Aeronautics and Space Administration. ANALYSIS Final Report, Sep. 1977 - Jun. 1978 Hugh L. Dryden Flight Research Center, Edwards. Calif. Bharat P. Gupta Apr. 1979 183 p refs SIMILITUDE REQUIREMENTS AND SCALING RE- (Contract DAAJ02-77-C-0049; DA Proj. 1 L2-62209-AH-76( LATIONSHIPS AS APPLIED TO MODEL TESTING (AD-A069877; BHT-699-099-096; USARTL-TR-78-46) Avail; Chester H. Wolowicz, James S. Brown, Jr.. and William P. Gilbert NTIS HC A09/MF AOl CSCL 01/3 Aug. 1979 64 p refs Prepared jointly with NASA. Langley A large number of obstacle strikes have Occurred during Res. Center Army helicopter combat missions and nap-of-the-earth (NOE) (NASA-T p -1435; H-1022) Avail: NTIS HC A04/MF AOl CSCL training missions. Obstacle strike tolerance becomes particularly 01C Important for NOE flights in areas containing many obstacles, The similitude requirements for the most general test such as western Europe. This report defines the obstacle strike conditions are presented. These similitude requirements are problem, particularly for tree and wire strikes. Only a small Considered in relation to the scaling relationships, test technique, percentage of obstacle strikes produce accidents, but these test conditions (including supersonic flow), and test objectives. accidents account for a high proportion of helicopter damage Particular emphasis is placed on satisfying the various similitude costs. Tree strikes are more common than wire strikes, but the requirements for incompressible and compressible flow conditions. wire strikes are more likely to cause accidents. Generally, the For free flying models tests, the test velocities for incompressible main and tail rotors are most commonly struck, but a high flow are scaled from Froude number similitude requirements and proportion of wire strikes also occur on the fuselage. Helicopter those for compressible flow are scaled from Mach number obstacle strike tolerance designs for rotors, fuselage, and controls similitude requirements. The limitations of various test techniques are analyzed and the most promising concepts are selected for are indicated, with emphasis on the free flying model. A.W.H. both existing and future helicopter systems. In addition, obstacle strike tolerance design criteria are defined. GRA

N79-30177# Army Aviation Engineering Flight Activity, Edwards N79-30180# Sikorsky Aircraft, Stratford, Conn. AFB, Calif. HELICOPTER DRIVE SYSTEM R AND M DESIGN GUIDE AH-1G HELICOPTER. 19-ROUND LIGHTWEIGHT AIR- Final Report BORNE LAUNCHER JETTISON ENVELOPE DETERMINA- K. R. Cormier Apr. 1979 91 p ref TION Final Report (Contract DAAJ02-76-C-0047; DA Proj. 1 L2-62209-AH-76) (AD-A069835; SER-50997; USARTL-TR-78-50( Avail: NTIS Gary L. Skinner and Frederick S. Doten Mar. 1979 30 p refs (AD-A069828; USAAEFA-78- 10) Avail: NTIS HC A05/MF AOl CSCL 01/3 HC A03/MF AOl CSCL 19/7 This report is a reliability and maintainability design guide The United States Army Aviation Engineering Flight Activity for helicopter drive systems. While not containing 'how to' design conducted a limited evaluation of a 19-round prototype launcher information, the guide points Out those areas of design which to determine a safe jettison envelope for the 19-round lightweight can be troublesome in the reliability and maintainability of airborne rocket launcher. The evaluation was conducted from helicopter drive systems. Besides containing information on the 25. May 1978 to 6 June 1978 at Edwards Air Force Base, various drive system components, a management section is California. Ten flights using an AH-1G helicopter were conducted included that outlines some practices which design managers totaling 3.5 flight hours. This evaluation defined a safe jettison may employ to insure that reliability and maintainability are given envelope in coordinated (ball-centered) level flight to 120 knots proper emphasis during a design program. The final section is calibrated airspeed (KCAS) and in autorotation at 70 KCAS. devoted to a step-by-step procedure for hazard function analysis, Establishment of a jettison envelope equivalent to that of the which may be used to predict the reliability of a gearbox during M159 and M200 launcher will require 75 7-round and 75 the design stage. GRA 19-round lightweight airborne rocket launchers and 744 2.75-inch Model M229 rockets. Five reliability and maintainability launcher N79-30181# United Technologies Corp.. Stratford, Conn. shortcomings were identified during the evaluation of the HEUCOPTER DRIVE SYSTEM R AND M DESIGN GUIDE prototype launcher. GRA Final Report K. A. Cormier and B. Trustee Apr. 1979 138 p refs (Contract DAAJ02-76-C-0047; DA Proj. 1 L2-62209-AH-76( (AD-A069691; SER-5 10012; USARTL-TR-78-5 1) Avail: NTIS HC A07/MF AOl CSCL 01/3 N79-30178# Army Aviation Engineering Flight Activity, Edwards This report covers the investigations conducted during the AFB, Calif. Helicopter Drive System R and M Design Guide program. The AIRWORTHINESS AND FLIGHT CHARACTERISTICS TEST, report discusses the present state of transmission reliability and OV-1C TAKEOFF PERFORMANCE Final Report, 11 Apr. - how reliability and maintainability are dealt with during the design 19 Jul. 1978 and development of a helicopter drive system. Other topics

652 N79-30188 discussed include the effect of quality control on drive system N79.30185*# Pratt and Whitney Aircraft Group. East Hartford. reliability, drive system maintainability problems, diagnostics, and Conn. the likely effect of advanced design concepts on the reliability AERODYNAMIC AND ACOUSTIC INVESTIGATION OF and maintainability of future drive systems. Two different types INVERTED VELOCITY PROFILE COANNULAR EXHAUST of reliability prediction techniques, hazard function analysis and NOZZLE MODELS AND DEVELOPMENT OF AERODYNAMIC probabilistic design, are discussed, and the strengths and AND ACOUSTIC PREDICTION PROCEDURES. COMPRE- weaknesses of each are outlined. Test planning and maintainability HENSIVE DATA REPORT, VOLUME 1 analysis are included as separate appendices. GRA Richard S. Larson, Douglas P. Nelson, and Bradley S. Stevens Jun. 1979 312 p 2 Vol. N79-30182# Sandia Labs.. Albuquerque. N. Mex. (Contract NAS3-20061( DRIFTDOWN CALCULATIONS FOR THE FH1227D AIR- (NASA-CR- 159515; PWA-5550- 16-Vol-i) Avail: NTIS HC A14/MF AOl CSCL 21E CRAFT The experimental data necessary to establish aerodynamic L. A. Bertram Feb. 1979 79 p refs (Contract EY-76-C-04-0789( and acoustic prediction systems for coannular exhaust nozzles (SAND-78-1807( Avail: NTIS HC A05/MF AOl with inverted velocity profiles are presented in graphical form. Two codes are described: USIM, which simulates FH-227D R.E.S. flights with an enroute engine loss, and UNDRIFT, which locates the maximum takeoff weights satisfying driftdown terrain clearance N79-30186# Pratt and Whitney Aircraft Group, East Hartford, and landing weight limits as well as falling within the climb Conn. capability of the aircraft. These codes are presented in a form AERODYNAMIC AND ACOUSTIC INVESTIGATION OF suitable for use at a remote terminal using the NOS timeshar- INVERTED VELOCITY PROFILE COANNULAR EXHAUST ing system for the Sandia CDC 6600 computer and user NOZZLE MODELS AND DEVELOPMENT OF AERODYNAMIC instructions and examples are given. Some weaknesses in the AND ACOUSTIC PREDICTION PROCEDURES, COMPRE- FAA-approved driftdown analysis procedure are noted and HENSIVE DATA REPORT, VOLUME 2 discussed, but it is the approved procedure which is implemen- Richard S. Larson, Douglas P. Nelson. and Bradley S. Stevens ted in the codes. DOE Jun. 1979 225 p refs (Contract NAS3-20061( (NASA-CR-159516; PWA-5550-17-Vol-2) Avail: NTIS HC A1O/MF AOl CSCL 21E N79-30183# Deutsche Forschungs- und Versuchsanstalt fuer The experimental data necessary to establish aerodynamic Luft- und Raumfahrt. Oberpfaffenhofen (West Germany(. Inst. and acoustic prediction systems for coannular exhaust nozzles fuer Dynamik der Flugsysteme. with inverted velocity profiles are presented in tabular form. The INVESTIGATIONS ON THE DESIGN OF ACTIVE VIBRATION acoustic data are corrected to a 'theoretical day' and scaled to ISOLATION SYSTEMS FOR HELICOPTERS WITH RIGID full engine size. R.E.S. AND ELASTIC MODELING OF THE FUSELAGE Gerd Schulz Mar. 1978 72 p refs In GERMAN; ENGLISH summary Report will also be announced as translation N79-301 81# National Aeronautics and Space Administration. (ESA-TT-556) Lewis Research Center, Cleveland, Ohio (DLR-FB-78-04( Avail. NTIS HC A04/MF AOl; DFVLR, Cologne EFFECT OF STEADY-STATE TEMPERATURE DISTORTION DM 25.70 AND COMBINED DISTORTION ON INLET FLOW TO A Different methods for the design of controllers for active TURBOFAN ENGINE vibration isolation on helicopters are investigated. Based on the Ronald H. Soeder and George A. Bobula Aug. 1979 43 p special structure of the controller, compensation for the rotor refs blade harmonic disturbance vibrations is achieved, guaranteeing (NASA-TM-79237; E-143) Avail: NTIS HC A03/MF AOl CSCL good trim behavior during maneuvers. For the first controller 21E design, done for a rigid helicopter fuselage with a modified Riccati Flow angle, static pressure, total temperature and total design, different sensor configurations are investigated. A pressure were measured in the inlet duct upstream of a turbofan possibility for sensitivity reduction for rotor speed variations is engine operating with temperature distortion or combined shown. For the second controller design for an elastic helicopter pressure-temperature distortion. Such measurements are useful fuselage the modified Riccati design, the design by means of in the evaluation of analytical models of inlet distortion. A rotating Nyquist plots and pole assignment are investigated, especially gaseous-hydrogen burner and a circumferential 180 degrees- with respect to the applicability for higher order systems. extent screen configuration mounted on a rotatable assembly Author (ESA( generated the distortions. Reynolds number index was main- tained at 0.5 and engine corrected low-rotor speeds were held at 6000 and 8600 rpm. The measurements showed that at the N79-30184# McDonnell Aircraft Co.. St. Louis, Mo. entrance to the engine, flow angle was largest in the hub region. RESEARCH ON VISUAL DISPLAY INTEGRATION FOR As flow approached the engine, yaw angle (circumferential ADVANCED FIGHTER AIRCRAFT Final Technical Report, variation( increased and pitch angle (radial variation) decreased. 13 Jul. 1977 - 13 Aug. 1978 The magnitude of static-pressure distortion measured along the George S. Mills, Marshall A. Grayson, Susan L. Loy. and Richard inlet-duct and extended bullet nose walls increased exponentially A. Jauer, Jr. Wright-Patterson AFB, Ohio AMRL Nov. 1978 as flow approached the engine. Author 162 p refs (Contract F33615-77-C-0536: AF Proj. 7184) (AD-A069605; MDC-A5425; AMRL-TR-78-97( Avail: NTIS NC A08/MF AOl CSCL 01/3 N79-301 88*# National Aeronautics and Space Administration. This 'Visual Display Integration' study was conducted to 1Lewis Research Center, Cleveland, Ohio. determine the display integration options projected available for A SUMMARY OF NASA/AIR FORCE FULL SCALE ENGINE inclusion in an attack/fighter aircraft crew station design in the RESEARCH PROGRAMS USING THE F100 ENGINE 1985-1990 time. A second objective was the definition of an W. J. Deskin (Pratt and Whitney Aircraft Group, West Palm evaluation framework that would permit evaluation of the Beach, Fla.( and H. G. Hurrell 1979 24 p refs Presented at selected display options during future related studies. Summarizing 15th Joint Propulsion Conf., Las Vegas, Nev., 18-20 Jun. 1979; the results, it is clearly evident that the CAT, as Option 1, will Sponsored by AIAA. Am. Soc. of Mech. Engr. retain its preeminence as the multifunction display unit for (NASA-TM-79267;E-183( Avail. NTIS NC A02/MF AOl CSCL 1985-1990. Option 2 is the flat-panel plasma display. Option 3 21E is the flat-panel liquid crystal display. and Option 4 is the A full scale engine research (FSER( program conducted with electroluminescent thin-film-transistor display. It was concluded the F100 engine is presented. The program mechanism is that man-in-the loop simulations provide the best opportunity described and the F100 test vehicles utilized are illustrated. for evaluating these display options in future related work. GRA Technology items were addressed in the areas of swirl augmenta-

653 N79-30189 tion, flutter phenomenon, advanced electronic control logic NOISE GENERATION BY JET-ENGINE EXHAUST DEFLEC- theory, strain gage technology and distortion sensitivity. The TION associated test programs are described. The FSER approach utilizes Burkhard Gehlhar, Werner Dobrzynski. and Bernhard Fuhrken Sep. existing state of the art engine hardware to evaluate advanced 1978 56 p refs In German; ENGLISH summary Report will technology concepts and problem areas. Aerodynamic phenom- be also announced as translation (ESA-TT-553) enon previously not considered by design systems were identified (DLR-FB-78-21( Avail: NTIS HC A04/MF AOl; DFVLR, Cologne and incorporated into industry design tools. A.W.H. DM 23,30 Noise radiation by jet-engine exhaust-flow-interaction with N7930189*# Pratt and Whitney Aircraft Group, East Hartford, blast deflectors was investigated by means of model-experiments Conn. Commercial Products Div. of scale 0.1; the investigations pertained to a specific deflector ENERGY EFFICIENT ENGINE FLIGHT PROPULSION configuration. Noise spectra and directivity characteristics for SYSTEM PRELIMINARY ANALYSIS AND DESIGN REPORT various power-settings and configuration changes were determined Progress Report, Mar. 1978 - Feb. 1979 and used for the prediction of noise generation by full-scale W. B. Gardner Apr. 1979 480 p refs configuration. The investigation shows that the particular deflected (Contract NAS3-20646) gives rise to higher noise levels than those of the corresponding (NASA-CR- 159487: PWA-5594-49( Avail: NTIS engine noise alone, when the distance between exhaust nozzle HC A21/MF AOl CSCL 21E and deflector is loss than 10 nozzle-diameters. Author (ESA) A flight propulsion system preliminary design was established that meets the program goals of at least a 12 percent reduction in thrust specific fuel consumption, at least a five percent reduction N7930193* # Massachusetts Inst. of Tech.. Cambridge. Lab. in direct operating cost, and one-half the performance deterioration for Information and Decision Systems. rate of the most efficient current commercial engines. The engine VTOL CONTROLS FOR SHIPBOARD LANDING provides a high probability of meeting the 1978 noise rule goal. M.S. Thesis Smoke and gaseous emissions defined by the EPA proposed Christopher Graham McMuldroch Aug. 1979 198 p refs standards for engines newly certified after 1 January 1981 are (Contract NGL-22-009-124( met with the exception of NOs. despite Incorporation of all known (NASA-CR- 162140; LIDS-TH-928( Avail: NTIS NOx reduction technology. F.0.S. HC A09/MF AOl CSCL 01C The problem of landing a VTOL aircraft on a small ship in N79-30190# Michigan Univ., Ann Arbor. Dept. of Aerospace rough seas using an automatic controller is examined. The Engineering. controller design uses the linear quadratic Gaussian results of CRITICAL ASSESSMENT OF EMISSIONS FROM AIRCRAFT modern control theory. Linear time invariant dynamic models PISTON ENGINES Final Report, Jun. 1974 - May 1978 are developed for-the aircraft. Ship, and wave motions. A hover W. Mirsky, J. A. Nicholls, R. Pace, H. Ponsonby. and D. E. controller commands the aircraft to track position and orientation Geister Jun. 1979 163 p refs of the ship deck using only low levels of control power. Commands (Contract DOT-FA74NA- 1102) for this task are generated by the solution of the steady state (AD-A071002; FAA-RD-78-82: FAA-NA-78-166) Avail. NTIS linear quadratic gaussian regulator problem. Analytical perform- HC A08/MF AOl CSCL 21/7 ance and control requirement tradeof's are obtained. A landing A comprehensive mathematical analysis for evaluating the controller commands the aircraft from stationary hover along a measured emissions from piston type general aviation aircraft smooth, low control effort trajectory, to a touchdown on a engines is presented and discussed. The analysis is used to predicted crest of ship motion The design problem is formulated calculate the fuel-air ratio, molecular weight of the exhaust and solved as an approximate finite-time linear quadratic products, and water correction factor. A sensitivity analysis is stochastic regulator. Performance and control results are found presented which shows the effects of emission measurement by Monte Carlo simulations. K. L. errors on calculated fuel-air ratio. The test facility is briefly described and the associated emissions instrumentation is discussed in detail. The experimental results obtained in this N7930194*# Scientific Systems, Inc.. Cambridge, Mass. facility on the AVCO-Lycoming LlO-320 engine are presented. A STUDY OF THE APPLICATION OF SINGULAR PERTUR- This includes baseline and lean-out emissions data and the BATION THEORY Final Report influence of sampling probe location in the exhaust pipe. The Raman K. Mehra, Robert B. Washburn, Salim Sajan, and James influence of leaks in the exhaust system or emissions console V. Carroll Aug. 1979 339 p refs are investigated and evaluated in terms of the mathematical (Contract NAS1-15113( model. A.W.H. )NASA-CR-3167) Avail: NTIS HC A15/MF AOl CSCL 01C A hierarchical real time algorithm for optimal three dimen- N7930191*# National Aeronautics and Space Administration. sional control of aircraft is described. Systematic methods are Lewis Research Center, Cleveland, Ohio. developed for real time computation of nonlinear feedback controls PERFORMANCE OF TWO-STAGE FAN WITH A FIRST- by means of singular perturbation theory. The results are applied STAGE ROTOR REDESIGNED TO ACCOUNT FOR THE to asix state, three control variable, point mass model of an PRESENCE OF A PART-SPAN DAMPER F-4 aircraft. Nonlinear feedback laws are presented for computing William T. Gorrell and Donald C. Yrasek Sep. 1979 72 p the optimal control of throttle, bank angle, and angle of attack. refs Real Time capability is assessed on a TI 9900 microcomputer. (NASA-TP- 1483; E-9786; AVRADCOM-TR-79- 10) Avail: NTIS The breakdown of the singular perturbation approximation near HC A04/MF AOl CSCL 21E the terminal point is examined Continuation methods are examined The NASA two-stage fan was tested with a redesigned to obtain exact optimal trajectories starting from the singular first-stage rotor. The redesign included a new design approach perturbation solutions. AWN to account for the presence of a part-span damper. At design speed the fan achieved a peak efficiency of 0.803, which is N79-30195# Rockwell International Corp., Columbus, Ohio. 1.9 percentage points higher than the original design. The peak Aircraft Div. efficiencies of the first stage and first rotor were 0.789 and FLUIDICS: FEASIBILITY STUDY ELECTRO/HYDRAULIC/ 0.821. respectively. An improvement in efficiency of up to FLUIDIC DIRECT DRIVE SERVO VALVE Final Report, 5 percentage points in the damper region was achieved over 11 Apr. - 29 Dec. 1978 the original large damper version. The stall margin, based on Louis P. Biafore and Bernie Holland Washington NASC Mar. flow conditions at peak efficiency, was 10 percent at design 1979 74 refs speed. p Author (Contract N62269-78-C-0176; WF41400000( (AD-A069798; NR78H-126, NADC-78-033-60( Avail: NTIS N79-30192# Deutsche Forschungs- und Versuchsanstalt fuer HC A04/MF AOl CSCL 13/7 Luft- und Raumfahrt. Brunswick (West Germany). Abt. Technische The feasibility of providing a fluidic back-up control for the Akustik., Navy's Advanced flight control actuation system (AFCAS( was

654 N79-30203 investigated and potential design concepts were evaluated. A Joseph C. Tirre In AGARD The Guidance and Control of prelim. spec. for an electro/hydraulic/fluidic direct drive servo Helicopters and V/STOL Aircraft at Night and in Poor Visibility valve was proposed. Technical data and supplier hardware was May 1979 5 p reviewed. A design concept for an electro/hydraulic/fluidic servo Avail: NTIS HC Al 1/MF AOl control valve was selected and a prelim. design drawing was In an attempt to defy the law of physics as it pertains to having prepared. The Study confirms the feasibility of providing a fluidic two or more bodies occupy the same space at the same time. back-up for the AFCAS direct drive servo valve. GRA NAP-of-the Earth (NOEl was developed. The problems of night, weather, and NOE flying discussed include: (1) navigation; (2) N79-30196# Boeing Vertol Co., Philadelphia, Pa. communication; 131 aircraft control; (4) wire detection; and (5) EVALUATION OF PYLON FOCUSING FOR REDUCED target acquisition/engagement. S.E.S. HELICOPTER VIBRATION Final Report, Aug. 1977 - May 1978 N79-30200// Smiths Industries Ltd.. Cheltenham (England). R. Gabel and D. Reed Apr. 1979 96 p refs THE DEVELOPMENT AND IN-FLIGHT EVALUATION OF A (Contract DAAJ02-77-C-0034; DA Proj. 1 L2-62209-AH-76) TRIPLEX DIGITAL AUTOSTABILIZATION SYSTEM FOR A (AD-A069712; D210-11390-1; USARTL,-TR-79-6) Avail: NTIS HELICOPTER NC A05/MF AOl CSCL 01/3 J. Meadows and P. Robinson (RAE. Farnborough, Engl.) In A wind tunnel model test program was conducted to AGARD The Guidance and Control of Helicopters and V/STOL investigate the effectiveness of a focused isolation system in Aircraft at Night and in Poor Visibility May 1979 22 refs reducing the transmission of rotor-induced vibratory loads for a p four-bladed hingeless rotor. The model consisted of a four-bladed Avail: NTIS HC A11/MF AOl hingeless rotor and a simulated transmission mounted on a focal The program and the triplex autostabilization system and its isolation system having pitch and roll degrees of freedom. installation in the aircraft were reviewed. The final stages of Analytical considerations indicate that there is no single focus development, with particular emphasis on the major contribution which will simultaneously isolate both hub moments and inplane afforded by a comprehensive systems rig, both to the hardware loads. For the four-bladed hingeless rotor with large vibratory and software development program are discusseo. The results hub moments, the optimum focus lies close to the combined of in-flight evaluation program including performance under rotor/transmission center of gravity. Model test results indicated fault-free and simulated runaway conditions. A number of problem two configurations with reasonable moment isolation. One was areas encountered during the initial phases of the flight trials an upward focus near the combined rotor/transmission center and means to overcome these are presented. S.E.S. of gravity. The second, which had an effective downward focus, produced high lateral and longitudinal loads. GRA N19-30201# Marconi-Elliott Avionic Systems Ltd.. Rochester (England). SOME ASPECTS OF THE DESIGN AND DEVELOPMENT N79-30197# Deutsche Forschungs- und Versuchsanstalt fuer OF THE MARITIME AUTOPILOT MODES FOR THE Luft- und Raumfahrt. Oberpfaffenhofen (West Germany(. Inst. WESTLAND LYNX HELICOPTER fuer Dynamik der Flugsysteme. K. S. Snelling and M. V. Cook (Cranfield Inst. of Technol.) In AN IN-FLIGHT CONTROLLER INSENSITIVE TO PARAME- AGARD The Guidance and Control of Helicopters and V/STOL TERS VARIATION Aircraft at Night and in Poor Visibility May 1979 18 p refs Gerhard Kreisselmeier and Reinhold Steinhauser May 1978 80 p refs In GERMAN; ENGLISH summary Report will also Avail: NTIS NC Al 1/MF AOl be announced as translation (ESA-TT-565) The stability augmentation system and the transistion (DLR-FB-78-07) Avail: NTIS HC A05/MF AOl; DFVLR, Cologne autopilot mode were reviewed. The requirement for Sea State DM 30.30 filtering of the height control signal is discussed. The design A design method, based on a systematic approach to and development of the Cable Angle and Cable Height hold aircraft attitude control parameters, was developed and tried on autopilot modes that together provide sonar modes for stabilizing the design of a pitch controller for the Do28D Skyservant aircraft. the position of a dunking sonar. S.E.S. The method takes into consideration the entire range of in-flight requirements posed by the guidance characteristics of the aircraft, N7930202*# National Aeronautics and Space Administration. including appropriate response (damping) to air turbulence. The Langley Research Center, Hampton, Va. controller is independent of radical changes in flight conditions DESIGN AND TESTING OF A REDUNDANT SKEWED and thus responds to the special problem of low speed elevator INERTIAL SENSOR COMPLEX FOR INTEGRATED NAVIGA- control as a harmonic progression of the elevator deflection angle. TION AND FLIGHT CONTROL The influence of an onboard computer on flight behavior is R. E. Ebner (Litton Systems, Inc.. Woodland Hills. Calif.) and W. examined and flight test results are compared with computer E. Howell In AGARD The Guidance and Control of Helicopters simulation results. Author (ESA) and V/STOL Aircraft at Night and in Poor Visibility May 1979 13 p refs Avail: NTIS HC A11/MF AOl CSCLO1C Requirements for a redundant strapdown inertial sensor N79-30198# Advisory Group for Aerospace Research and complex applied to V/STOL aircraft as developed by NASA are Development, NeulIly-Sur-Seine (France). presented. Flight test data of a redundant, skewed axis strapdown THE GUIDANCE AND CONTROL OF HELICOPTERS AND inertial system are given, demonstrating the feasibility of the V/STOL AIRCRAFT AT NIGHT AND IN POOR VISIBILITY primary design aspects. This data consisted of parity equation May 1979 237 p refs Partly in ENGLISH and FRENCH responses through various flight conditions, showing residual noise Papers presented at the Guidance and Control Panel Symp., levels on redundant gyro and accelerometer comparisons as a The Hague, 9-12 Oct. 1978 measure of minimum failure-level detectability, plus failure (AGARD-CP-258; ISBN-92-835-0238-8( Avail: NTIS isolation and navigation performance through several simulated HC Al 1/MF AOl instrument failures. S.E.S. The following topics are discussed: (1) operational require- N79-30203# Dornier-Werke G.m.b.H., Friedrichshafen (West ments; (2) controls and displays; 131 forward looking sensors; Germany). (4) man/machine aspects; 151 landing operations and systems; SCAN CONVERTER AND RASTER DISPLAY CONTROLLER and (6) system implementation. FOR NIGHT VISION DISPLAY SYSTEMS H. W. Killian and W. Voswinckel In AGARO The Guidance and Control of Helicopters and V/STOL Aircraft at Night and in N79.30199# Army Training and Doctrine Command, Fort Poor Visibility May 1979 10 p Monroe, Va. ADDING THE CHALLENGE OF NAP-OF-THE-EARTH Avail: NTIS NC Al l/MF AOl

655 N79-30204

A modular Raster Display System and its functional modules N79-30207# Ferranti Ltd.. Edinburgh )Scotland). Radar are described. Digital scan conversion of images of electro-optical Group. sensors and digital storage of images with several gray tones A HELICOPTER HIGH DEFINITION ROTOR BLADE RA- are allowed. With the help of the digital symbol generator digital DAR information is converted into adequate symbology which again C. M. Steward In AGARD The Guidance and Control of can be superimposed on the sensor image. Superposition of Helicopters and V/STOL Aircraft at Night and in Poor Visibility two sensor images is performed with the same equipment. Some May 1979 10 p ref technical features are discussed which exceed the common modes of current display systems and may help to support missions of Avail; NTIS HC Al 1/MF AOl military helicopters flying low level at poor visibility conditions. By installing a radar aerial within the rotor blade, a sensor S.E.S. having unique capabilities for the operation of helicopters in darkness or bad weather can be provided. A description of such a system is given outlining the factors affecting the choice of the principal radar parameters and their interaction with the helicopter rotor design. Examples of the high definition pictures from the display are shown with the appropriate section of map N79-30204# Army Avionics Research and Development Activity, for comparison and some suggestions are made on operational Fort Monmouth, N. J. roles where such a radar system would have particular advan- APPLICATIONS OF PATTERN RECOGNITION SYSTEMS tages. Author FOR DAY/NIGHT PRECISION AIRCRAFT CONTROL AGARD The Guidance and Control of Helicopters Alfred Kleider In N79-30208// . Naval Air Development Center. Warminster, Pa. and V/STOL Aircraft at Night and in Poor Visibility May 1979 DESIGN PROCEDURE FOR AIRCREW STATION, LABELING 7 p refs SELECTION AND ABBREVIATION Avail; NTIS HC A11/MF AOl Patrick M. Curran and Norman E. Lane In AGARD The Guidance The philosophical and practical foundations for the utilization and Control of Helicopters and V/STOL Aircraft at Night and in of advanced technological developments in lasers and Charge Poor Visibility May 1979 16 ref' Coupled Devices (CCD) to provide light weight, low cost solutions p to theise problems in day/night operations are explored. The Avail; NTIS HC All/MF AOl special case of weather limited visibility is presented and projected Methods are described of preparing the functional statements operational parameters are discussed relative to near term of what, where, when, and how the operator should act upon availability of infrared devices (IRCCD). The concept of feature gathering information on a characteristic of a system/ subsystem extraction is explored using the complimentary one dimensional or component. The usage of common labeling of associated characteristics of wire/wire-like obstacles and a 1728 linear CCD controls and displays is presented as well as specific procedures Array as the foundation of the Wire Obstacle Warning System for abbreviating display/control labels. M.M.M. (WOWS) presently in development. In this instance the appropriate geometrical. optical, and electronic capatibilities were combined to provide a real time automatic pattern recognition system for Royal Aircraft Establishment, Farnborough Nap-of-the-Earth I NOEl helicopter operations. S.E.S. N79-30209# (England). Flight Systems Dept. SUBJECTIVE ASSESSMENT OF A HELICOPTER APPROACH SYSTEM FOR IFR CONDITIONS H. Howells In AGARD The Guidance and Control of Helicopters N19-30205# Army Avionics Research and Development Activity, and V/STOL Aircraft at Night and in Poor Visibility May 1979 Fort Monmouth, N. J. 7 p refs HETERODYNING CO2 LASER RADAR FOR AIRBORNE Avail; NTIS HC Al 1/MF AOl APPLICATIONS The contribution of subjective assessment techniques used R. L. DelBoca and R. J. Mongeon (United Technol. Res. Center) in the flight evaluation of 3 azimuth approach guidance laws In AGARD The Guidance and Control of Helicopters and V/STOL presented on crosspointers of electromechanical instruments in Aircraft at Night and in Poor Visibility May 1979 17 p refs a fully stabilized helicopter is outlined. The pilots were instructed to confine their attention to monitoring the instruments within Avail; NTIS HC Al 1/MF AOl the cockpit as a safety pilot was carried. The use of subjective The design considerations, hardware configuration, and test assessment techniques, in conjunction with the interpretation of results of flyable breadboard models are discussed which have radar plots and comments of an airborne trials observer, provide demonstrated the feasibility of employing CO2 scanning laser a type of information not obtainable from other sources. The systems for wire detection, precision hover. Doppler navigation, technique, although used here on electromechanical instruments, and terrain following. S.E.S. would be equally applicable to an assessment of electro-optical displays. M.M.M. N79-30206# Standard Elektrik Lorenz AG., Stuttgart (West Germany), A SELF CONTAINED COLLISION AVOIDANCE SYSTEM FOR N79-30210# Army Avionics Research and Development Activity, HELICOPTERS Fort Monmouth, N. J. S. Bloch, G. Hoefgen. and D. zurHeiden In AGARD The Guidance THE IMPACT OF A MULTI-FUNCTION PROGRAMMABLE and Control of Helicopters and V/STOL Aircraft at Night and in CONTROL DISPLAY UNIT IN AFFECTING A REDUCTION Poor Visibility May 1979 6 p refs OF PILOT WORKLOAD Bernard S. Gurman In AGARD The Guidance and Control of Avail; NTIS HC A11/MF AOl Helicopters and V/STOL Aircraft at Night and in Poor Visibility A proposed solution to the problem of obstacle detection May 1979 8 p refs and collision warning pertaining to the operation of helicopters at low altitude and within a formation is described. A simple Avail; NTIS HC Al 1/MF AOl yet effective algorithm is used in order to assess the collision Three digitally-addressed Multi-Legend Display Switches hazard posed by stationary obstacles as well as other helicopters )MLD/S) which employ different mechanizations, and the in the proximity of the protected aircraft. The raw data needed incorporating of these MLD/S's in a multi-purpose, programmable (range and closing speed) is provided by a 35 GHz versatile Control Display Unit )CDU) are described. Several programs are low-cost FM/CW-radar that was originally developed for the cited which logically led to the development of the Multi-Legend protection of road vehicles. With the exception of the antenna Display Switches and the CDU. These programs and that possible assembly only minor modifications are needed in order to make applications are presented. Developments that lead to the this radar fit the requirements of an airborne anti-collision reduction of pilot workload and improve overall pilot/vehicle system. Author performance are pointed out. M.M.M.

656 N79-30217

N79-30211# GIE ISPENA. Paris (France). N79-30214# McDonnell-Douglas Corp.. St. Louis, Mo. Electron- THE EQUIPMENT-SYSTEM INTERFACE IN AN ANTITANK ics Branch. HELICOPTER AT NIGHT [ETUDE DINTERFACE EQUIPAGE SIMULATION AND STUDY OF V/STOL LANDING AIDS FOR SYSTEME DANS UN HELICOPTERE ANTI-CHAR DE USMC AV-8 AIRCRAFT NU IT] W. E. Bode, R. A. Kendrick, and E. J Kane In AGARD The G. Ferlet and J. L. Mascle In AGARD The Guidance and Guidance and Control of Helicopters and V/STOL Aircraft at Control of Helicopters and V/STOL Aircraft at Night and in Poor Night and in Poor Visibility May 1979 16 p Visibility May 1979 10 p In FRENCH Avail: NTIS NC Al l/MF AOl Avail: NTIS HC Al 1/MF AOl Motion base simulations, flown by USMC Harrier pilots, in A direct consequence of the growing complexity of modern which 600 low speed IFR approaches to a forward site and aircraft missions is the increase of equipment workloads, which ship were made. Glideslope angles from 3 degrees to 9 degrees can reach a critical level in many cases. It is important to consider were simulated and flown both head up and head down. An this problem from the beginning of the aircraft definition stage attitude hold autopilot was evaluated and flight director steering so that some really integrated solutions which guarantee 'iaximum was studied. The effects of crosswind, turbulence, sea state and operational efficiency can be proposed for the equipment-system system errors were included in the simulation. Visual landing interface. Such a step requires the adoption of a rigorous, aids for ships and forward sites were devised and aircraft and systematic work method that is capable of accounting for ground/ship based equipment se jected. At the heart of the study diverse data such as technological constraints or operational was the evaluation by the pilots of the degree of improvement requirements, in order to obtain optimal solutions. A methodology offered by the simulated landing aids. M.M.M. used in the study of the equipment-system interface for an antitank helicopter capable of performing its mission by day as well as by night is presented. The technique distinguishes five stages in N79-30215# Dornier-Werke G.m.b.H., Friedrichsbefen (West the iterative process, thus permitting progressive improvement Germany). - in the definition of the interface, as a function of the difficulties IMPLEMENTATION OF FLIGHT CONTROL IN AN INTE- considered at different stages. Transl. by A.R.H. GRATED GUIDANCE AND CONTROL SYSTEM H. J. Bangen, W. Hoffmann. and W. Metzdorff In AGARD The Guidance and Control of Helicopters and V/STOL Aircraft at Night and in Poor Visibility May 1979 11 p refs

N79-30212# Naval Air Systems Command, Washington, D. C. Avail: NTIS HC Al l/MF AOl Advanced Aircraft Development and Systems Objectives Office. The hardware and software technology is presented as it is PROJECT NAVTOLAND (NAVY VERTICAL TAKEOFF AND required to solve the control problem in the integrated helicopter LANDING CAPABILITY DEVELOPMENT) guidance and control system. M.M.M. Thomas S. Momiyama In AGARD The Guidance and Control of Helicopters and V/STOL Aircraft at Night and in Poor Visibility N79-30216# Societe de Fabrication d'Instruments de Mesure refs May 1979 20 p SFIM. Massy (France). STABILIZING ELECTRO-OPTICAL SYSTEMS ON HELICOP- Avail: NTIS HC Al 1/MF AOl TERS [STABILISATION DES SYSTEMES ELECTRO- The U.S. Navy's integrated systems approach to improve OPTIQUES SUR HELICOPTERES] the helicopter and fixed-wing VSTOL aircraft operational Dominique dePonteves In AGARD The Guidance and Control capabilities at sea and in tactical sites is described. The current of Helicopters and V/STOL Aircraft at Nightand in Poor Visibility capability is limited to generally 400 foot ceiling and one mile May 1979 5 In FRENCH; ENGLISH summary visibility to 200 foot and 1/2 mile weather minima due to p elementary flight control systems or lack of precision approach Avail: NTIS NC Al 1/MF AOl and landing guidance. Inability to cope with ship motions limits The stabilization of both the APX-BEZU M260 gyrostabilized the small air capable ship operations generally to Sea State 3. sights used for surveillance and the aiming of antitank missiles, The NAVTOLAND project goals are zero ceiling and 1/8 mile and the APX M397 sight, used with an IR goniometer to aim visibility weather minima and Sea State 5 operation. An integrated the HOT missile, is implemented by a mechanical relation between development of the aircraft flight . control and display systems to a mirror and a conventional gyro. The development of infrared provide flying qualities with satisfactory level of pilot workload sensors needing large optical aperture led to the design and and the shipboard and tactical site installed guidance systems implementation of a two-axis, tuned gyro which can be used and visual landing aids to effect precision in touchdown is applied either as a free gyro or as a rate gyro. Its performance allows toward improvement of the helicopter and AV-8 HARRIER the stabilization of the most performing optical sensors with a operations and toward development of all-weather and rough MTF degradation of not more than 15 percent. Preliminary flight sea operations of all future Navy and Marine Corps VSTO L tests were performed on an electro-optical system which combines aircraft. M.M.M. a TV camera with a very high focal length, a laser range finder, and a twin-focal FUR in order to determine its feasibility for aiming a weapon aiming system suing 8 to 13 microns band. Transfer functions are discussed. A.R.H. N79-30213# Bodenseewerk Geraetetechnik G.m.b.H., Ueberlin- gen (West Germany). GCU, THE GUIDANCE AND CONTROL UNIT FOR ALL N79-30217# Rockwell International Corp., Cedar Rapids, Iowa. WEATHER APPROACH Collins Government Avionics Div. Hartmut Boehret In AGARD The Guidance and Control of AN ADVANCED GUIDANCE AND CONTROL SYSTEM FOR Helicopters and V/STOL Aircraft at Night and in Poor Visibility RESCUE HELICOPTERS May 1979 11 p refs Kenneth W. McElreath In AGARD The Guidance and Control of Helicopters and V/STOL Aircraft at Night and in Poor Visibility Avail: NTIS NC Al 1/MF AOl May 1979 17 p The guidance and control unit GCU development by Boden- Avail: NTIS NC Al 1/MF AOl seewerk and sponsored by the German Ministry of Defense, After identifying the tasks in accomplishing a search and demonstrated in flight test the improvements of future landing rescue mission, Rockwell-Collins established guidelines and procedures. The short-captured steep approach paths generated priorities for designing and integrating the system elements. The by the GCU can be flown manually with the flight director development of the avionics system architecture is reported and instrument due to the high accuracy of signal processing by the features of each element which contribute to the adverse means of Kalman filter techniques. The technical equipment is weather capability of the integrated system are described, presented and the flight test results are discussed. M.M.M. M.M.M.

657 N79-30218

N79-30218# Advisory Group for Aerospace Research and John H. Watson and Willie S. , Bennett In AGARD Stability Development, Neuilly- Sur- Seine (France). and Control May 1979 13 p refs STABILITY AND CONTROL May 1979 359 p refs In ENGLISH and FRENCH Presented Avail: NTIS HC A16/MF AOl at the Flight Mech. Panel Symp. on Stability and Control, Ottawa, The performance of the modern fighter aircraft and its flight 25-28 Sep. 1978 systems is discussed. Improvement in effectiveness through proper (AGARD-CP-260; ISBN-92-835-0239-6) Avail: NTIS functional integration of the pilot, his crew station, and the flight HC A16/MF AOl systems is emphasized. The incorporation of advanced control The fundamental relationship between the use of advanced modes, the integration of avionic systems and the flight control control concepts and appropriate aircraft design is considered. systems, and the unification of all aircraft functions under the Experiences in stability and control, the application of active control of a flight management system are among the factors control and the general problems concerning its use, including considered. J.M.S. those of mathematical models, and results obtained with control configured vehicles are discussed. Criteria for satisfactory behavior N19-30224# Societe Nationale Industrielle Aerospatiale, of aircraft with advanced stability and control systems and the Toulouse (France). participation of the pilot are includea. RESULTS RELATED TO SIMULATED AND IN-FLIGHT EXPERIMENTATION WITH AN ELECTRIC FLIGHT CON- TROL SYSTEM THAT CAN BE GENERALIZED [RESULTATS N79-30219// National Aeronautics and Space Administration, RELATIFS A L'EXPERIMENTATION SUR SIMULATEUR ET Washington, D. C. EN VOL DUN SYSTEME DE COMMANDES DE VOL SYSTEMS IMPLICATIONS OF ACTIVE CONTROLS ELECTRIQUES GENERALISABLES] Peter A. Kurzhals In AGARD Stability and Control May 1979 A. Cazenave and J. Irvoas In AGARD Stability and Control 16 p refs May 1979 21 p In FRENCH Avail: NTIS HC A16/MF AOl Control configured vehicle design and system considerations Avail: NTIS HC A16/MF AOl are outlined and representative applications of active control for Studies of the performance of a transport aircraTt with fighter and transport aircraft are summarized. Specific examples slender airfoils whose longitudinal stability is assured by the include relaxed static stability and angle of attack limiting on use of elevators show the advantage of moving back the center the F-16, envelope limiting and ride smoothing on the F-8, of gravity in order to improve finesse at low speeds; the Optimal maneuver load and control and relaxed static stability on the centering is located beyond the operationally acceptable rear L-101 1, load alleviation for the C-5, and B-i ride control. Principal limit for handling with classical flight controls. An electric flight features, problem areas, and mechanization trends for these and control system which permits control under conditions of projected future active control applications are outlined. J.M.S. pronounced instability across the control stick was designed, used in a simulator, and then flight tested on the T.S.S. Concorde. The form of the control laws considered is described as well as N79-30220# Lockheed Missiles and Space Co.. Sunnyvale. Calif. the improvements made after the simulation. Characteristics and A SUMMARY OF AGARD FDP MEETING ON DYNAMIC the results obtained in flight are presented and compared to STABILITY PARAMETERS predictions. L. E. Ericsson In AGARD Stability and Control May 1979 Transl. by A.R.H. 23 p refs Avail: NTIS HC A16/MF AOl N79-30225# Northrop Corp., Hawthorne. Calif. Aircraft Corp. Wind tunnel and flight testing techniques, analytical tech- IMPROVEMENT OF FIGHTER AIRCRAFT MANEUVERABIL- niques, including motion analysis and nonlinear formulations were ITY THROUGH EMPLOYMENT OF CONTROL CONFIGURED covered along with sensitivity and simulator studies to assess VEHICLE TECHNOLOGY the importance of the various dynamic stability parameters, Janusz Stalony-Dobrzanski and Naren Shah In AGARD Stability including cross coupling effects between lateral and longitudinal and Control May 1979 22 p refs degrees of freedom. The extent to which the practice of decoupling lateral and longitudinal degrees of freedom must be abandoned Avail: NTIS RC A16/MF AOl was addressed. It was decided that when describing the vehicle The control configured vehicle (CCV) design concept employ- dynamics of advanced aircraft and aerospace vehicles, which ing concurrently the traditional disciplines as well as fufi authority perform sustained operations at high angles of attack, the cross automatic control system design, is shown to offer a very large coupling effects are usually significant, and lateral and longitudinal combat performance improvement over conventional design degrees of freedom must be considered together. J.M.S. approach. This improvement is due primarily to the freedom,. under CCV concept, of designing statistically longitudinally unstable configurations. The configuration selected for the N79-30221# Office National d'Etudes et de Recherches evaluation is a tailless clipped delta employing advanced Aerospatiales, Paris (France). structure and engine technologies. The performance gains are STRUCTURAL ASPECTS OF ACTIVE CONTROLS achieved simultaneously with decreased aircraft and fuel weight Roger Destuynder In AGARD Stability and Control May 1979 for the same mission. The feasibility of designing a stability and 12 refs In FRENCH; ENGLISH summary p command augmentation (SCAS) for the statically unstable configurations is demonstrated. The full authority SCAS provides Avail: NTIS HC A16/MF AOl excellent flying qualities in general flying and target tracking Various papers presented at the specialists meeting sponsored modes. The departure prevention feature permits true 'head-out-of- by the Structures and Materials Panel in Lisbon (1977) are cockpit' flying without the pilot having ever to consult flight summarized. Emphasis is placed on the following main points: instruments for safety. The system was evaluated extensively on (1) the use of preliminary simple calculations to cover the a moving base simulator. The practical iimitations to the degree different configurations and the possible control laws; of static instability are discussed. J.M.S. (2) improvement with the help of corrections obtained by wind tunnel tests; and (3) proof, through flight test or wind tunnel test, of the validity of the solution. Progress in flutter suppression N79-30226# Royal Aircraft Establishment, Farnborough obtained at ONERA is also reported. A.R.H. (England). Flight Systems Dept. LATERAL STABILITY AT HIGH ANGLES OF ATTACK, PARTICULARLY WING ROCK A. Jean Ross In AGARD Stability and Control May 1979 19 p refs N79-30223# General Dynamics/Fort Worth, Tex. Avail: NTIS HC A16/MF AOl ENHANCED FIGHTER MISSION EFFECTIVENESS BY USE The Gnat aircraft exhibits wing rock at high subsonic Mach OF INTEGRATED FLIGHT SYSTEMS numbers, but the onset of wing rock is delayed to higher angles

658 N79-30235 of attack if fuel tanks are carried on the wings. Flight responses N79-30231# Air Force Flight Dynamics Lab., Wright-Patterson of Dutch roll and wing rock oscillations in steady turns were AFB, Ohio. analyzed to give the variation of the stability derivatives with DESIGN CONSIDERATIONS FOR RELIABLE FBW FLIGHT angles of attack at various Mach numbers for both aircraft CONTROL configurations. The results show that the onset of wing rock James K. Ramage and James W. Morris In AGARD Stability occurs when the damping of the Dutch roll mode is zero, due and Control May 1979 15 p refs mainly to loss in damping-in-roll derivative at high angle of attack. The stability derivatives from flight tests were compared Avail: NTIS HC A16/MF AOl with wir&tunnel results, and show the same trends witii angle Critical design considerations which both aircraft designers of attack. The values of the linear derivatives were used as a and flight control systems engineers must bear in mind in the basis for evaluating the effects of various added aerodynamic design and implementation of fly by wire flight control systems nonlinearities, both to explore the possible mechanisms for the are presented. R.E.S. limit cycle type of wing rock responses, and to calculate the changes in response due to an idealized stability augmentation system. Author N79-30232# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer N19-30227# Hochschule der Bundeswehr, Munich. (West Flugmechanik. Germany). OPEN/CLOSED LOOP IDENTIFICATION OF STABILITY AND STALL BEHAVIOUR EVALUATION FROM FLIGHT TEST CONTROL CHARACTERISTICS OF COMBAT AIRCRAFT RESULTS R. Koehler and M. Marchand In AGARD Stability and Control G. Sachs and H. Wuennenberg (Dornier-Werke G.m.b.H.. May 1979 11 p Avail: NTIS HC A16/MF AOl Friedrichshafen( In AGARD Stability and Control May 1979 General aspects of assessing flying qualities of augmented 9 p refs Avail: NTIS HC A16/MF AOl aircraft using system identification methods are discussed. The By comparing the dynamic stall behavior of a combat aircraft aircraft under test was equipped with a stability augmentation with a simulation, a special type of discrepancy in roll was system which had a complex dynamic behavior. The dynamics found. The simulation was based on the best wind tunnel data influenced the flying qualities as well as the applicability of available. The examination leads to the conclusion, that the investigation methods. Therefore, the influence and recognizability aircraft is disturbed by random-type 'fluctuation' forces and of the stability augmentation system dynamics on handling quality moments. The order of magnitude was estimated from the evaluations and system identifications were inquired and scattering region of the wind tunnel data beyond C sub L max. pilot-in-the-loop investigations were made using the system identification results. R.E.S. By introducing these effects into the mathematical model it was possible to simulate the pilot in the loop dynamic stall behavior with the aid of a simple mathematical pilot model. For a general N79-30233# Deutsche Forschungs- und Versuchsanstalt fuer application in the design stage of a new project, new wind Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer tunnel test techniques including the measurement of the time Flugmechanik. dependent parameters will be necessary. Author DYNAMIC WINDTUNNEL SIMULATION OF ACTIVE CONTROL SYSTEMS P. G. Hamel and B. Krag In AGARD Stability and Control N79-30229# Technische Hogeschool, Delft (Netherlands). Dept. May 1979 10 p refs of Aerospace Engineering. AIRCRAFT RESPONSE TO WINDSHEARS AND DOWN- Avail: NTIS HC A16/MF AOl DRAUGHTS Research studies were conducted to demonstrate the J. C. vanderVaart In AGARD Stability and Control May 1979 application potential of dynamic simulation in a wind tunnels 16 p refs test facility. Elastic mode control and ride smoothing systems Avail: NTIS HC A16/MF AOl were scaled to model frequency and tested in a 3 m subsonic After a short review of current methods of modelling low gust windtunnel. An open loop active control ride Smoothing altitude random atmospheric turbulence and variations of mean system was optimized for the Dornier-TNT light transport aircraft wind with altitude (windshears), a description is given of an experimental program. Dynamic wind tunnel flight tests of this analytical method to find deterministic wind or turbulence time program were successfully completed. R.E.S. histories that cause largest deviations of aircraft motion variables. Some numerical examples illustrate that small variations of wind, in particular of horizontal wind, may cause relatively large deviations relative to a desired aircraft trajectory. Finally, it is N79.30234# Messerschmitt-Boelkow-Blohm G.m.b.H., Otto- shown that the problem of finding 'worst case' response to brunn (West Germany). Military Aircraft Div. determ:nistic changes in wind can be reduced to that of the STABILITY AND CONTROL ASPECTS OF THE CCV-F104C statistics of a random white noise driven linear system. Author H. Beh, U. Korte, and G. Loebert In AGARD Stability and Control May 1979 18 p refs N79-30230# Aeritalia S.p.A., Torino (Italy). Combat Aircraft Group. Avail: NTIS HC A16/MF AOl GUST ALLEVIATOR FEASIBILITY STUDY FOR G91Y The control configured vehicle and its implementation, and R. CarbelIi In AGARD Stability and Control May 1979 12 p the design of the control laws are described. The superior flight ref performance of the control configured vehicle-flight control system Avail: NTIS HC A16/MF AOl is compared with that of the basic F 104G on the basis of A feasibility study was carried out of an active system to simulator results. The validity of these results was demonstrated alleviate the turbulence effects on a light attack aircraft during by comparison of the principal characteristics of longitudinal and the penetration phase of a ground attack mission. The study lateral motion measured in flight with the corresponding predicted was tailored to the G91 Y and the conclusions were that values. R.E.S. proceeding through an experimental research by developing a flying prototype would be preferable. The risks implicit in the N79-30235# Air Force Flight Dynamics Lab., Wright-Patterson achiment of the required accuracy in measuring the gust AFB, Ohio. velocity were very high. The proposed system works on two DESIGN GUIDANCE FROM FIGHTER CCV FLIGHT EVALUA- axes. An open loop subsystem driven by the normal component TIONS of the gust velocity on the pitch axis and a roll damper on the Frank R. Swortzel and Jack D. McAllister (Gen. Dyn./Ft. Worth lateral is indicated as an adequate solution to meet profitable Tex.) In AGARD Stability and Control May 1979 21 p reft cockpit 'g' reductions and weapon delivery accuracy improvement as well. R.E.S. Avail: NTIS HC A16/MF AOl

659 N79-30236

Flight control of the Fighter Control Configuration Vehicle N79-30239# Naval Air Systems Command, Washington, 0. C. (CCV) marked the first exploitation of six degree-of-freedom flight ARE TODAY'S SPECIFICATIONS APPROPRIATE FOR control concepts for a new way to fly. An 87 flight. 125 flight TOMORROW'S AIRPLANES? hour test was conducted on a modified YF-16. Validation of the R. C. AHarrah, W. J. Lamanna (McDonnell Aircraft Co.. St. Louis, new control concepts was accomplished and significant capabili- Mo.). and J. Hodgkinson In AGARD Stability and Control ties to improve overall mission effectiveness of fighter aircraft May 1979 12 p refs were demonstrated. The program also included pilot evaluation of the CCV control modes applied to air-to-air and air-to-ground Avail: NTIS HC A16/MF AOl mission oriented tasks. Resulting control features included direct An approach for taking any system of a higher order that is force control, independent fuselage aiming and translation, addressed in the current specifications, and producing an maneuver enhancement and gust alleviation. Performance benefits equivalent system of an appropriate order, which is directly of relaxed static stability were also evaluated. G.Y. relatable to the specification parameters is presented. Example applications of the equivalent systems approach to various higher order systems are presented: the insights of this approach to N79-30236# Lockheed-California Co., Burbank. the newest fighter aircraft design are discussed; and very 1-1011 ACTIVE CONTROLS, DESIGN PHILOSOPHY AND preliminary results are presented on a flight program which EXPERIENCE investigates equivalent systems. David M. Urie In AGARD Stability and Control May 1979 G.Y. 9 p refs Avail: NTIS HC A16/MF AOl N79-30240# National Aerospace Lab., Amsterdam (Netherlands). Aircraft active control can be defined as control effectors A SIMULATOR INVESTIGATION OF HANDLING QUALITY activated by sensors through computers without pilot commands. CRITERIA FOR CCV TRANSPORT AIRCRAFT A certificated commercial transport airplane, the Lockheed L- 1011. H. A. Mooij, W. P. deBoer, and M. F. C. vanGool In AGARD currently employs several highly sophisticated systems satisfying Stability and Cbntrol May 1979 14 p refs Sponsored in this definition. The experience gained through development cooperation with Netherlands Agency for Aerospace Programs flight testing, commercial flight operation, and flight simulation and Dept. of Civil Aviation of the Netherlands research on active control applications is presented with the Avail: NTIS HC A16/MF AOl intent of relating design philosophy and results. G.Y. The introduction of CCV (Control Configured Vehicle) concepts in the design of certain categories of future transport aircraft N79-30237# Deutsche Forschungs- und Versuchsanstalt fuer requires definition of handling quality criteria for such aircraft. Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer These criteria should be applicable to guidance in flight control Flugmechanik. system design as well as in airworthiness certification. In an IN-FLIGHT HANDLING QUALITIES INVESTIGATION OF attempt to contribute new insight in this matter, approach and VARIOUS LONGITUDINAL SHORT TERM DYNAMICS AND landing flight simulation investigations were performed using a DIRECT LIFT CONTROL COMBINATIONS FOR FLIGHT moving base flight simulator. The conceptual aircraft was a jet PATH TRACKING USING DFVLR HFB 320 VARIABLE transport aircraft developed around the relaxed static stability STABILITY AIRCRAFT concept and equipped with a primary flight control system of D. Hanke and H.-H. Lange In AGARD Stability and Control the rate-command/attitude-hold type for pitch and roll control. May 1979 10 p refs Based on measured pilot/aircraft performance, pilot ratings and pilot commentary, boundary values for satisfactory handling Avail: NTIS HC A16/MF AOl qualities for the parameters investigated were established. G.Y. An in-flight investigation of DLC for wide body transport aircraft was carried Out using DFVLR 320 variable stability aircraft which incorporates an advanced all digital model following system. N79-30242# Office National d'Etudes et de Recherches The aircraft/DLC configuration parameters was investigated in Aerospatialex, Paris (France). an altitude compensatory tracking task in which the pilot has to ONERA'S MODEL OF THE PILOT IN DISCRETE TIME [LE minimize the error between commanded and actual altitude. To MODELE DE PILOTE EN TEMPS DISCRET DE L'ONERAJ determine the influence of motion cues, the tracking task is Daniel Cavalli In AGARD Stability and Control May 1979 carried out both on the ground and in-flight. Using the HFB 320 11 p refs In FRENCH as a fixed base and an in-flight simulator, an ideal situation for comparing the fixed base and in-flight simulation results exists. Avail: NTIS HC A16/MF AOl In addition pilot-in-the-loop analysis for flight path tracking with Numerical simulation of pilot performance provides a tool DLC is performed. The results are given in the form of subjective for evaluating the efficiency of pilot-aircraft systems and permits pilot effort ratings and pilot-aircraft performance measures. The the study of the handling quality of new aircraft from the concept results are further compared with a flight path tracking criter- stage. Pilot performance is considered as a discreet time process ion. G.Y. in which decision making has a sequential character. The development of the ONERA model is described and its originality demonstrated by comparison with already existing models. N79-30238# British Aerospace Aircraft Group. Wanton (England). Results obtained during application of the model in a study of FLYING QUALITIES AND THE FLY-BY-WIRE AEROPLANE performance degradation when the static margins of the simulated J. C. Gibson In AGARD Stability and Control May 1979 aircraft were decreased are presented. Transl. by A.R.H. 8 p refs Avail: NTIS HC A16/MF AOl The tornado flight control system was designed to give good N7930243*# National Aeronautics and Space Administration. stability, damping, and resistance to external disturbances. This Ames Research Center, Moffett Field, Calif. was achieved by optimization of feedback gains and filters. FLIGHT EXPERIENCE WITH ADVANCED CONTROLS AND Response to pilot inputs was then shaped by stick commands DISPLAYS DURING PILOTED CURVED DECELERATING gains and filters. This process resulted in generally excellent APPROACHES IN A POWERED-LIFT STOL AIRCRAFT flying qualities. Pilots reported a high level of confidence inspired W. S. I-Iindson (NatI. Rex. Council of Can., Ottawa) and G. H. by the easy and precise control with extremely good circuit Hardy In AGARD Stability and Control May 1979 12 p handling and instrument flight characteristics. However, some refs deficiencies were noted associated in some cases with nonaircraft- Avail: NTIS HC A16/MF AOl like responses and these were eliminated by modifications to A program to assess the feasibility of piloted STOL approaches the command shaping. This experience emphasized that a along predefined, steep, curved, and decelerating approach profiles specification which ensures entirely satisfactory flying qualities was carried Out with a powered-lift STOL aircraft. To reduce does not eist. Several areas where requirements are deficient the pilot workload associated with the basic control requirements or absent are illustrated. G.Y. of a powered-lift aircraft equipped with redundant controls and

660 N79-30332 operating on the backside of the power curve, separate stability 589K (600 Fl are described. Major tasks included: quality augmentation systems for attitude and speed were provided, as assurance development: materials and process development; well as a supporting flight director and special electronic cockpit specification verification; fiat panel fabrication; stiffened panel displays. The control, display, and procedural features are described fabrication; honeycomb panel fabrication; chopped fiber moldings; for the flight experiment that led to the conclusion that, given and- demonstration component fabrication. Materials, processing. an adequate navigation environment, such constrained approaches and quality assurance documents were prepared from experimen- may be feasible from a pilot acceptance point of view. G. Y. tally derived data. Structural elements consisting of flat panels, corrugated stiffeners. I-beams, hat stiffeners, honeycomb panels, and chopped fiber moldings were made and tested. Property N79-30246# New Mexico Univ., Albuquerque. Civil Engineering data from 219K (-65 F) to 589K (600 F) were obtained. All Research Facility. elements were made in a production environment. The size of AN EVALUATION OF ASPHALT-RUBBER MIXTURES FOR each element was sufficient to insure production capability and USE IN PAVEMENT SYSTEMS Final Report, Apr. 1977 - structural component applicability. Problems associated with Feb. 1979 adhesive bonding, laminate and structural element analysis, Dale S. Decker, Donald F. Griffin, and John P. Nielsen Tyndall material variability, and test methods were addressed. J.M.S. AFB, Fla. Civil and Environ. Eng. Develop. Office Apr. 1979 83 p refs (Contract F29601-76-C-0015; AF Proj. 2104) N7930315*# National Aeronautics and Space Administration. (AD-A069448; CEEDO-TR-79-02) Avail: NTIS Langley Research Center, Hampton, Va. HC A05/MF AOl CSCL 13/3 FATIGUE AND FRACTURE The design and construction of airfield pavements have not Walter IlIg and Richard A. Everett, Jr. (Army Res. and Technol. been developed sufficiently to provide pavements that will not Labs.) In its Graphite/ Polyim ide Composites Aug. 1979 crack. Cracking is a response to traffic and environmental p 259-272 - conditions or to the Construction material. For many years, rubber Avail: NTIS HC A19/MF AOl CSCL liD in several different forms has been added to asphalt with limited The effects of the load/temperature environment of the shuttle success in reducing pavement cracking. This report reviews the on the fatigue life of the body-flap were investigated by conducting efforts to control cracking by incorporating rubber and asphalt real time and accelerated flight-by-flight tests up to 500 flights for application as membrane interlayers, surface seal coats, on coupons containing holes. On the fracture side, much is known crack fillers, and joint sealers. The extensive literature review about the sensitivity of the tensile strengths of composites to indicates that conflicting conclusions have been reached regarding holes and other flaws, predominantly at room temperature. The varied applications of the asphalt-rubber material. Of the effects of notches were assessed for graphite/polyimides at the asphalt-rubber products available, those with high percentages expected temperature extremes of the body-flap: 117K (-250 F) of rubber (20 to 30 percent by weight) appear to be the most to 589K (600 F). Results indicate that the shuttle temperature promising for airfield pavements, although the effectiveness of extremes may affect fatigue properties HTS/PMR-15. There is asphalt-rubber in controlling or reducing pavement cracking has no significant effect of temperature on notch-strength Tensile not been conclusively demonstrated. No superiority of one strengths for specimens with holes and slots are equal. S.E.S. asphalt-rubber product was indicated in the literature. Because of the danger of loose aggregate chips, the literature indicates that chip seal applications should not be used on facilities where N79-3031 7# National Aeronautics and Space Administration. loose chips could be a problem. Therefore, the membrane interlayer Langley Research Center, Hampton, Va. is the only application of asphalt-rubber that should be considered MECHANICAL AND THERMOPHYSICAL PROPERTIES OF for military runways at this time. GRA GRAPHITE/POLYIMIDE COMPOSITE MATERIALS Donald R. Rummier and Ronald K. Clark In its Graphite/Polyimide N79-30247# European Space Agency. Paris (France). Composites Aug. 1979 p 289-302 refs WALL CORRECTIONS IN TRANSONIC WIND TUNNEL: EQUIVALENT POROSITY Avail: NTIS HC A19/MF AOl CSCL liD Xavier Vaucheret May 1979 135 p refs Transl. into ENGLISH An on-going program to characterize advanced composites of 'Corrections de Parois en Soufflerie Transsonique Porosite for up to 50.000 hours of exposure to simulated supersonic Equivalente', Rept. ONERA-P-1977-3 ONERA, Paris. 1977 cruise environments is summarized. Results are presented for )ESA-TT-545; ONERA-P- 1977-3) Avail: NTIS up to 25.000 hours of thermal exposure and 10.000 hours of HC A07/MF AOl flight simulation at temperatures up to 560K (550 F) with A method for calculating wall effect corrections is presented emphasis on HTS/7 10 graphite/polyimide composite material. for the present design of transonic wind tunnel test Sections Results to date indicate that the maximum use temperature for with perforated horizontal walls and for the dimensions of complete HTS/710 may be reduced to 505K (450 F) for long-time models or two dimensional profiles currently used in industrial (1000 hours) application such as the supersonic transport. testing. The calculations are performed using the concept of Preliminary thermophysical properties data for H TS/ PM R 15 constant equivalent porosity on the walls, assuming symmetrical graphite/polyimide were generated. These data include thermal operation of the two walls in three dimensional flow and conductivity, thermal expansion, and specific heat from 115K asymetrical operation in two dimensional flow. The experimental (-252 F) to 590K (600 F) and emittance at room temperature methods of determining the equivalent porosity are described. and 590K (600 F). The purpose in generating these data was Finally, test section/model configurations are investigated in an to validate use of state-of-the-art property measurement methods attempt to minimize the wall effects. Author )ESA( for advanced graphite fiber reinforced resin matrix composites. Based on results to this point, thermal expansion measurements for composites are most difficult to perform A high degree of N7930301*# Boeing Aerospace Co., Seattle, Wash. caution in conducting thermal expansion tests and analyzing results DEVELOPMENT AND DEMONSTRATION OF MANUFAC- is required to produce reliable data. Author TURING PROCESSES FOR FABRICATING GRAPHITE/PMR-15 POLYIMIDE STRUCTURAL ELE- MENTS C. H. Sheppard, J. T. Hoggatt. and W. A. Symonds In NASA. N79-30332# Naval Research Lab., Washington, D. C. Langley Res. Center Graphite/Polyimide Composites Aug. 1979 HIGH PERFORMANCE COMPOSITES AND ADHESIVES p 61-84 FOR V/STOL AIRCRAFT Annual Report, 1 Sep. 1977 - (Contract NAS1-1 5009) 30 Nov. 1978 Avail: NTIS HC A19/MF AOl CSCL liD Luther B. Lockhart, Jr. 23 May 1979 163 p The procössirig requirements for graphite/PMR-15 polyimide (SF54502001) composites developed to demonstrate the structural integrity of (AD-A06961 1; NRL-MR-4005; AR-3) Avail: NTIS polyimide composite structural elements at temperatures up to MC A08/MF AOl CSCL 11/2

661 N79-30334

An interdisciplinary program has been undertaken to address DLR-FB-77-63, 8 Aug. 1978 Original report in GERMAN the composite and adhesive materials requirements of V/STOL previously announced as ESA-90854 Original German report aircraft. The primary tasks are to develop and characterize high available from DFVLR, Cologne DM 43,40 modulus, high toughness resins with use temperatures of 350 F (ESA-TT-521; DLR-F8-77-63) Avail: NTIS HC A05/MF AOl to 450 F or higher, to develop fabrication technology of newly The shear modulus, the stress at 1% shear-strain, the shear developed resin matrices for graphite-fiber reinforced composites, strength, the strain at fracture, and the appertaining shear to develop composite failure criteria for design optimization and stress-strain diagrams were analyzed for ten aircraft structural to establish appropriate quality control parameters. This report adhesives. These values are calculated from the measured is the third annual review of the program, covering the period load-deflection behavior of the adhesive in the bond line of lap 1 September 1977 to 30 November 1978. The reporting period joints with a thick adherend and a small overlap length, as well was extended to permit completion of an important phase of as from the torsion pendulum testing of cast adhesives. The the task on fracture behavior of composites. During the reporting measurements are made before and after a long exposure to period, two of the original tasks. Resin Synthesis and Radiation warmth, cold, moisture, warmth combined with moisture, and Curing, were terminated but related work is being continued changes between cold and combined warmth and moisture. The under other in-house projects to follow up leads developed in environmental effects on the adhesion between adherend and this program. Among recent accomplishments are the demonstra- adhesives as observed in the-tests-are described. Author (ESA) tion that resin fracture energy can affect composite interlaminar toughness in fiber-reinforced composites, the development of quality control methodology for phthalocyanine precursor resins, N79-30490# Civil ueromedical Inst., Oklahoma City, Okla. the successful fabrication of phthalocyanine/graphite fiber ELECTRICAL INSULATION FIRE CHARACTERISTICS. composites from prepreg, and the completion of room temperature VOLUME 2: TOXICITY Final Report, Jul. 1976 - Jul. 1978 fracture tests of NARMCO 5208/T300 composite over four Charles A. Crane, Boyd A. Endecott, Donald C. Sanders. and quadrants of load space and Hexcel F178/T300 composite in John K. Abbott Dec. 1978 102 p refs one quadrant and further verification of the ability to use this (Contracts DOT/TSC-RA-77- 15; DOT/T5C-RA-77- 16) data to predict failure in a box-beam structure. GRA (PB-294841/2; UMTA-MA-06-0025; DOT-TSC-UMTA-78-48-11) Avail: NTIS HC A06/MF AOl CSCL 13F N79-30334# Grumman Aerospace Corp., Bethpage, N.Y. The relative inhalation toxicity of the thermal degradation METALLIC COATINGS FOR GRAPHITE/EPDXY COM- products or gaseous pyrolysis of selected types of electrical wiring POSITES Final Report, 1 May 1977 - 31 Oct. 1978 insulations was determined. The specific materials to be evaluated Christian J. Staebler, Jr. and Bonnie F. Simpers May 1979 were selected from a much larger population on the basis of 91 p refs prior testing of properties other than toxicity. The relative toxicities (Contract N00019-77-C-0250l of the combustion products of 14 electrical wiring insulations IAD-A069871l Avail: NTIS HC A05/MF AOl CSCL 11/2 were evaluated using animal incapacitation as a measure of Metallic coating systems for graphite/epoxy laminated aircraft toxicity. One gram insulation samples were pyrolyzed in a quartz structures were developed to provide protection against moisture combustion tube connected in-line with a 12.6 liter exposure penetration, electromagnetic interference (EMI), paint strippers chamber by an air recirculation assembly to form a closed and lightning strikes. Foil coatings and metal-filled resin coatings exposure system. Each material was pyrolyzed under three thermal were evaluated to assess the protection ability in each of these degradation conditions and the time to incapacitation for the areas. The foil coatings provided a significant reduction in the shortest time condition was used to rank the materials in order moisture penetration and the associated strength loss of the of their relative potential toxicity. GRA laminate after exposure to humidity and humidity-thermal spiking. Two techniques were developed for the application of foil coatings to graphite/epoxy laminates. Solid aluminum foil was applied to N79-30555# Timken Co., Canton, Ohio. cured laminates in a secondary bonding operation. Perforated TAPERED ROLLER BEARING DEVELOPMENT FOR AIR- aluminum foil was bonded to the laminate in a co-curing operation. CRAFT TURBINE ENGINES Final Report, 8 Mar. 1976 - The co-curing application required that the laminate be prebled 8 Mar. 1979 prior to application of the foil and final co-curing to obtain the Peter S. Divas and G. J. Pressler Wright-Patterson AFB, Ohio optimum strength and thickness of the laminate. GRA AFAPL Mar. 1979 102 p refs (Contract F33615-76-C-2019; AF Proj. 3048) (AD-A069440; AFAPL-TR-79-2007) Avail: NTIS N79-30335// General Dynamics/Convair. San Diego, Calif. HC A06/MF AOl CSCL 13/9 ULTRA-HIGH-MODULUS GRAPHITE-EPDXY CONICAL Finite element methods were used to structurally analyze SHELL DEVELOPMENT, SUPPLEMENT Final Report, 1 Dec. various potential cage designs for tapered roller bearings operating 1976 - 30 May 1978 at 3.5 million DN. The race guided Z design exhibited the greatest Julius Hertz, Edward E. Spier. and Norman A. Adsit Apr. 1979 strength. Short duration evaluation tests verified these findings. 73 p refs Performance tests were conducted to determine bearing loss (Contract DAAG46-76-C-0008; DA Proj. 1W1-621 13-A-661) characteristics and oil-off survival. Parameters investigated, which (AO-A069795; CASD-ASC-78-001 AMM RC-TR-78-38-Suppl) influence losses (torque or heat generation), were speed, load, Avail: NTIS HC A04/MF AOl CSCL 11/2 lubricant properties, lubricant flow rate and lubricant distribution. The work reported herein represents a preliminary evaluation Oil-off survival tests were successfully run at 1.5 and 2.0 million of support ring concepts for an advanced terminal interceptor ON. The bearing fatigue life tests conducted at 3 million ON (ATI). An ultra-high-modulus grahite/epoxy subscale cone was showed a high degree of life scatter. The 90 percent survival fabricated and a wedge shaped ring was secondary bonded level was 2.78 times the unadjusted catalog life expectancy. internally. The cone and ring were successfully tested beyond G RA ultimate load at both AT and 325F. A unique helicoil attach- ment concept for transferring load into the ring was demon- N7930876*# Air Force Flight Dynamics Lab., Wright-Patterson strated. GRA AFB, Ohio. LIGHTNING HAZARDS OVERVIEW; AVIATION REQUIRE- N79-30391# European Space Agency, Paris (France). MENTS AND INTERESTS THE INFLUENCE OF THE ENVIRONMENT ON THE Phillip B. Corn In NASA. Marshall Space Flight Center Proc.: ELASTOPLASTIC PROPERTIES OF ADHESIVES IN METAL Workshop on the Need for Lightning Observations from Space BONDED JOINTS Jul. 1979 p 126-135 refs Walter Althof, Gerhard Klinger, Gerhard Neumann, and Johanna Schlothauer Feb. 1979 89 p refs Transl. into ENGLISH of Avail: NTIS HC Al2/MF AOl CSCL 04A 'Klimaeinfluss auf die Kennwerte des elasto-plastischen Verhaltens A ten-year history of USAF lightning incidents is presented von Klebstoffen in Metallklebungen', DFVLR Brunswick Report along with a discussion of the problems posed by lightning to

662 N79-31143 current aircraft, and the hazards it constitutes to the electrical John L. McCloud, III Aug. 1979 36 p refs and electronic subsystems of new technology aircraft. Lightning (NASA-TM-78621; A-7955) Avail: NTIS HC A03/MF AOl technical protection technical needs, both engineering and CSCL O2A operational, include: (1) in-flight data on lightning electrical Several types of rotors which employ multicyclic control are parameters: (2) tech base and guidelines for protection of advanced reviewed and compared. Their differences are high-lighted and systems and structures; (3) improved laboratory test techniques; their potential advantages and disadvantages 0re discussed. The (4) analysis techniques for predicting induced effects; (5) lightning flow field these rotors must operate in is discussed, and it is strike incident data from general aviation; (6) lightning detection shown that simultaneous elimination of vibration and oscillatory systems; (7) pilot reports on lightning strikes; and (8) better blade loads is not an inherent solution to the roughness training in lightning awareness. A.R.H. problem. The use of rotor blades as energy absorbers is proposed Input-output relations are considered and a gain control for A 0 MU LAN, a m ulticyclic controlling computer program, is introduced Implications of the introduction of multicyclic N79-30959# Computer Sciences Corp., Silver Spring, Md. A.W.H. Systems Sciences Div. systems into helicopters are discussed. CENTRAL FLOW CONTROL SOFTWARE DESIGN DOCU- N79-31138# Textron Bell Aerospace Co., New Orleans, La. MENT. VOLUME 1: OPERATIONAL SOFTWARE COMPLEX MARITIME PATROL AIRSHIP CONCEPT STUDY Final Final Report Report, 18 Apr. - 31 Oct. 1978 Jan. 1979 542 p refs James C. Bell, James D. Marketos. and A. D. Topping 16 Nov. (Contract DOT-FA77WA-3955) 1978 242 p refs (AD-A070973; CSC/SD-78/6172-Vol-1; FAA-RD-79-33-Vol-111 (Contract N62269-78-M-6956) Avail: NTIS HC A23/MF AOl CSCL 09/2 (AD-A070131: NADC-78074-60; Rept-7575-927030) Avail: The Central flow control )CFC) software system functional NTIS HC All/ME AOl CSCLO1/3 requirements established in the Federal Aviation Administra- Results of a preliminary conceptual parametric design study tion's (FAA) computer program functional specifications are for a maritime patrol airship to be used by the U. S. Coast translated into implemented software programs. The exact Guard or Navy are presented. Eight different Coast Guard mission configuration of the computer programs produced for CFC profiles are considered, and an optimum airship point design is software system is described. A complete technical description developed for each. The report discusses mission requirements, of the software functions, structures, operating environment, data airship operational requirements, the conceptual design ap- organization, visual table of contents, program listings, and data proach, and the parametric design study which uses a computer and module cross references is provided. The operational complex program to assist in optimizing the critical parameters for each which Operates in real time mode and is comprised of the airship mission design. The study includes airship sizes from executive, database, simulation, and applications subsystems is 220,000 cu ft 18.000 lb vertical takeoff weight to described. J.M.S. 3,000.000 cu ft 230,000 lb vertical takeoff weight. Results show the unique features of the Bell unballasted, reversible thrust N79-30960# Computer Sciences Corp., Silver Spring, Md. airship design and the critical need for design optimiztion, owing Systems Sciences Div. to the sensitivity of the airship design parameters. The computer CENTRAL FLOW CONTROL SOFTWARE DESIGN DOCU- design program shows airship conceptual differences and design MENT. VOLUME 2: SUPPORT SOFTWARE COMPLEX Final trends rather than absolute design configurations, since it uses Report the preliminary subsystem weight relationships developed for Jan. 1979 593 p recent airship parametric studies. Although the study design trends (Contract DOT-FA77WA-3955) should remain valid, additional studies are recommended to (AD-A070771; CSC/SD-78/6172-Vol-2; FAA-RD-79-33-Vol-2) establish better subsystem weight estimates and to incorporate Avail: NTIS HC A25/MF AOl CSCL 09/2 life-cycle costing. GRA The support complex )SPCX) which operates in an off-line mode and is comprised of the system development, system generation, system test, and system analysis subsystems is N791141*# National Aeronautics and Space Administration. described. J.M.S. Langley Research Center, Hampton, Va. POWERED LOW-ASPECT-RATIO WING IN GROUND EFFECT (WIG) AERODYNAMIC CHARACTERISTICS James L. Thomas, John W. Paulson, Jr., and Richard J Margason N7931136*# National Aeronautics and Space Administration, Jul. 1979 49 p refs Washington, 0 C. )NASA-TM-78793) Avail: NTIS 'IC A03/MF AOl CSCL A COMPARISON OF PREDICTIONS OBTAINED FROM O1A WIND TUNNEL TESTS AND THE RESULTS FROM CRUIS- A wing-in-ground effect configuration was investigated. The ING FLIGHT: AIRBUS AND CONCORDE configuration used large diameter, low pressure ratio fans mounted J. Berger Aug. 1979 71 p refs Transl. into ENGLISH of about 0.76 wing chord ahead of the wing leading edge to achieve "Comparison entre les resultats de vol en croisiere: Airbus et a power augmented ram wing during operation in ground effect. Concorde", AGARD . CP-242, Rept-20 Presented at Flight Tests of both in and Out of ground effect aerodynamic transition Mechanics Panel Specialists Meeting on Performance Prediction characteristics from very low speeds to cruise speeds are Methods. Paris, France. 11-13 Oct. 1977 Original language described. The investigation provided a number of conclusions document was announced as N78-26074 Transl. by Kanner concerning the aerodynamic/ propulsive performance interaction (Leo) Associates. Redwood City. Calif. Original doc. prep. by While power augmented lift is required for low speed flight, Aerospatiale (France) there is a thrust loss when the efflux is trapped under the wing (Contract NASw-3199) which reduced the effective thrust to weight available for (NASA-TM-75238; AGARD-CP-242. Rept-20) Avail: NTIS acceleration by about a third of the installed thrust to weight NC A04/MF AOl CSCL 02A ratio. A.W.H. Following a summary of the methods used to establish aerodynamic data and propulsion data, a comparison was made N79-31 143*# Old Dominion Univ, Norfolk, Va. in the form of the drag (or thrust) difference between flight SUBSONIC WIND-TUNNEL INVESTIGATION OF LEADING- results and predictions made on the basis of these data. Certain EDGE DEVICES ON DELTA WINGS (DATA REPORT) hypothesis and improvements on aerodynamic data were M. Rao Dhanvada and Thomas D. Johnson. Jr Aug. 1979 presented in order to explain the slight deficit found on Airbus 131 p refs and Concorde. M.M.M. (Grant NGR-47-003-052) (NASA-CR-159120) Avail: NTIS HC A07/MF AOl CSCL N7931137*# National Aeronautics and Space Administration O1A Ames Research Center, Moffett Field, Calif The drag reduction potential of leading edge devices on THE PROMISE OF MULTICYCLIC CONTROL delta wings at high lift is presented. Fences, pylon type vortex

663 N79-31144

generators. chordwise slots, and sharp plate extensions were translations normal to the aerodynamic surface and surface tested on wing models with 60 and 74 degree swept blunt slopes that are parallel and perpendicular to the free stream leading edges at angles of attack to 32 degrees. Six component direction. Five different interpolation methods are available, balance and leading edge surface pressure measurements were A.W.H. taken with various geometry and spanwise arrangements of the devices. Tables listing the data, without analysis, are presented. 148*/f A.W.H. N79-31 Boeing Commercial Airplane Co., Seattle. Wash. A PROGRAM TO COMPUTE THREE-DIMENSIONAL N79-31 144// Boeing Commercial Airplane Co.. Seattle, Wash. SUBSONIC UNSTEADY AERODYNAMIC CHARACTERIS- DYNAMIC LOADS ANALYSIS SYSTEM (DYLOFLEX) TICS USING THE DOUBLET LATTICE METHOD. L216 (DUBFLEX). VOLUME 2: SUPPLEMENTAL SYSTEM SUMMARY. VOLUME 1: ENGINEERING FORMULATION DESIGN AND MAINTENANCE DOCUMENT Topical Report, R. D. Miller, R. I. Kroll, and R. E. Clemmons Sep. 1979 88 p refs 2 Vol. May 1975 - May 1977 (Contract NAS1-13918( B. A. Harrison and M. Richard Washington NASA Sep. 1979 75 refs 2 Vol. (NASA-CR-2846- 1;06 . 44455 . Vol- 1) Avail: NTIS p HC A05/MF AOl CSCL 01A (Contract NAS1-13918( The DYLOFLEX computer program system expands the (NASA-CR-2850; D6-44459( Avail: NTIS NC A04/MF AOl aeroelastic cycle from that in the FLEXSTAB computer program CSCL O1A system to include dynamic loads analyses involving active controls. The information necessary for execution of the digital Two aerodynamic options exist within DYLOFLEX. The analyst computer program L216 on the CDC 6600 is described. L216 can formulate the problem with unsteady aerodynamics calculated characteristics are based on the doublet lattice method. Arbitrary using the doublet lattice method or with quasi-steady aerody- aerodynamic configurations may be represented with combinations namics formulated from either FLEXSTAB or doublet lattice steady of nonplanar lifting surfaces composed of finite constant state aerodynamics with unsteady effects approximated by indicial pressure panel elements, and axially summetric slender bodies lift growth functions. The equations of motion are formulated composed of constant pressure line elements. Program input assuming straight and level flight and small motions. Loads are consists of configuration geometry, aerodynamic parameters, and calculated using the force summation technique. DYLOFLEX modal data; output includes element geometry, pressure consists of nine standalone programs which can be linked with difference distributions, integrated aerodynamic coefficients, each other by magnetic files used to transmit the required data stability derivatives, generalized aerodynamic forces, and aerody- between programs. . Author namic influence coefficient matrices. Optionally, modal data may be input on magnetic field (tape or disk(, and Certain geometric and aerodynamic output may be saved for subsequent use. N79-31 145*/f Boeing Commercial Airplane Co., Seattle, Wash. DYNAMIC LOADS ANALYSIS SYSTEM (DYLOFLEX) A.R.H. SUMMARY. VOLUME 2: SUPPLEMENTAL SYSTEM DESIGN INFORMATION R. D. Miller. R. I. Kroll. and R E. Clemmons Sep. 1979 60 p N79-31 149w/f Bihrle Applied Research, Inc., Jericho, N. V. refs 2 Vol. ROTARY BALANCE DATA FOR A TYPICAL SINGLE-ENGINE (Contract NAS1-13918( GENERAL AVIATION DESIGN FOR AN ANGLE-OF-ATTACK (NASA-CR-2846-2; D6-44455-VoI-2( Avail: NTIS RANGE OF 8 DEG TO 90 DEC. 2: HIGH-WING HC A04/MF AOl CSCL 01A MODEL A Contents: execution of the DYLOFLEX program system; William Mulcay and Robert Rose Washington NASA Sep. magnetic file format; DYLIB - the DYLOFLEX alternate subroutine 1979 116p refs library; and prefaces for DYLIB subroutines. A.R,H. (Contract NAS1-14849( (NASA-CR-3101( Avail: NTIS HC A06/MF AOl CSCL 01A N79-31 146/f Aeronautical Research Labs., Melbourne (Australia(. Aerodynamic characteristics obtained in a rotational flow LATERAL AERODYNAMICS EXTRACTED FROM FLIGHT environment utilizing a rotary balance located in the Langley TEST USING A PARAMETER ESTIMATION METHOD spin tunnel are presented in plotted form for a 1/5-scale. R. A. Feik Oct. 1978 45 p refs single-engine, high-wing, general aviation airplane model. The (ARL-AERO-NOTE-380; AR-001 -311) Avail: NTIS configurations tested included various tail designs and fuselage HC A03/MF AOl shapes. Data are presented without analysis for an angle of Flight data from a 60 deg delta wing aircraft was analyzed attack range of 8 to 90 degrees and cIockwise,and counter- using a modified Newton-Raphson parameter estimation clockwise rotations covering an Omega b/2 v range from 0 to procedure. The model equations used for the analysis were 0.85. M.M.M. extended to account for sideslip vane errors and for lateral accelerometer position error. Lateral derivatives extracted from the data were compared with wind tunnel measurements and N7931151*/f National Aeronautics and Space Administration. theoretical estimates and areas of agreement and disagreement Langley Research Center, Hampton, Va. identified. The method was also applied to the analysis of fin WIND-TUNNEL INVESTIGATION OF AN ARMED MINI loads measured in flight and some tentative conclusions reached. REMOTELY PILOTED VEHICLE The results confirm the effectiveness of the parameter identifica- Arthur E. Phelps, III Sep. 1979 62 refs Prepared in tion procedure in flight test analysis and its ready applicability p cooperation with Army Aviation Research and Development to a variety of related problems. M.M.M. Command, St. Louis. Mo. (DA Proj. 11-1-61 102-AH-45( N79-31 147*/f Boeing Commercial Airplane Co.. Seattle. Wash (NASA-TM-80132; L-13026; AVRADCOM-TR-79-4 1( Avail: MODAL INTERPOLATION PROGRAM, L215(INTERP). NTIS NC A04/MF AOl CSCL 01A VOLUME 2: SUPPLEMENTAL SYSTEM DESIGN AND A wind tunnel investigation of a full scale remotely piloted MAINTENANCE DOCUMENT vehicle (RPV( armed with rocket launchers was conducted. The M. Y. l-lirayama and R. I. Kroll Washington NASA Sep. 1979 model had unacceptable longitudinal stability characteristics at 69 p refs negative angles of attack in the original design configuration. (Contract NAS1-13918( The addition of a pair of fins mounted in a V arrangement on (NASA-CR-2848; D6-44457( Avail: NTIS HC A04/MF AOl the propeller shroud resulted in a configuration with acceptable CSCL O1A longitudinal stability characteristics. The addition of wing mounted The design, structure, and usage of the modal interpolation external stores to the modified configuration resulted in a slight program L215 are presented. The program uses modal data reduction in the longitudinal stability. The lateral directional sets of arrays containing interpolation coefficients The interpola- characteristics of the model were generally good, but the model tion arrays are used to determine displacements at various had low directional stability at low angles of attack. Aerodynamic aerodynamic control points. The displacements Consist of control power was very strong around all three axes. A.W.H.

664 N79-31163

N7931152*# Bihrle Applied Research. Inc.. Jericho, N. V. and rotational accelerations, velocities, and displacements; ROTARY BALANCE DATA FOR A SINGLE-ENGINE (2( panel aerodynamic forces: (3( net panel forces: and (4( shears, TRAINER DESIGN FOR AN ANGLE-OF-ATTACK RANGE bending moments, and torsions. J.M.S. OF B DEG TO 90 DEG Paul Pantason and Waldo Dickens Washington NASA Aug. N79-31156# ARO. Inc.. Arnold Air Force Station, Tenn. 1979 327 p A FORCE AND MOMENT TEST OF A 1/24-SCALE F-ill (Contract NAS1-14849( MODEL AT MACH NUMBERS FROM 0.7 TO 1.3 Final (NASA-CR-3099( Avail: NTIS HC A15/MF AOl CSCL 01A Report Aerodynamic characteristics obtained in a rotational flow C. G. Burchfield AEDC 2 Mar, 1979 17 p refs environment utilizing a rotary balance located in the Langley (AD-A070192: AEDC-TSR.79-P1 4( Avail: NTIS spin tunnel are presented in plotted form for a 1/6 scale, single HC A02/MF AOl CSCL 01/3 engine trainer airplane model. The configurations tested included A test program was conducted in the Propulsion Wind Tunnel the basic airplane, various wing leading edge devices, elevator, 16 T to determine forces and moments on a 1/24-scale F-ill aileron and rudder control settings as well as airplane components. model Data were obtained at Mach numbers from 0.7 to 1.3 Data are presented without analysis for an angle of attack range at total pressures of 1200 and 2000 psfa. Model angle of attack of 8 to 90 degrees and clockwise and counter-clockwise was varied from 2 to 20 deg at 0 deg sideslip. Sideslip angles rotations. Author were varied from -10 to 10 deg at 10 and 15 deg angles of attack. GRA N7931153*# Boeing Commercial Airplane Co.. Seattle. Wash. EQUATION MODIFYING PROGRAM. 1219 (EQMOD). N79-31157# Purdue Univ., Lafayette. Ind. School of Aeronautics VOLUME 2: SUPPLEMENTAL SYSTEM DESIGN AND and Astronautics. MAINTENANCE DOCUMENT Topical Report, May 1975 - FLUTTER ANALYSIS OF TWO-DIMENSIONAL AND May 1977 TWO-DEGREE-OF-FREEDOM AIRFOILS IN SMALL- M. V. Hirayama, R. E. Clemmons, and R. D. Miller Washington DISTURBANCE, UNSTEADY TRANSONIC FLOW Final NASA Sep 1979 65 p refs Report, Nov. 1977 - Oct. 1978 (Contract NAS1-13918( T. Y. Yang, Alfred G. Striz. and P Guruswamy Dec. 1978 (NASA-CR-2856: D6-44465-Vol-2( Avail: NTIS 116 p refs HC A04/MF AOl CSCL CiA (Grant AF-AFOSR-3523-78: AF Proj. 2307( A digital computer program. L219 (EQMOD(, available for (AD-A069223: AFFDL-TR-78-202( Avail: NTIS execution on the CDC 6600 is described. The program modifies HC A06/MF AOl CSCL 20/4 matrices according to card input instructions and prepares Flutter analyses are performed for a NACA 64AO06 and a magnetic files of matrices suitable for use in the linear systems NACA 64A010 airfoil by simultaneously using two transonic analysis program (OR) and the random harmonic analysis aerodynamic computational codes: (l( STRANS2 and UTRANS2 program L221 (TEV156(. The particular field of application of based on the relaxation method and (2( LTRAN2 based on the the program is the modification of the theoretical equations of indicial and time-integration methods. Flutter results are obtained motion and load equations generated in DYLOFLEX by the as plots of flutter speeds and the corresponding reduced equation of motion program (L21 7) and the load equation program frequencies versus one of the four parameters: airfoil-air mass (L218(. respectively. J.M.S, ratio: position of the mass center; position of the elastic asia. and free stream Mach number. On each figure, several sets of N7931154*# Boeing Commercial Airplane Co., Seattle, Wash. curves for different values of plunge-to-pitch frequency ratios TIME HISTORY SOLUTION PROGRAM. 1225 (TEV126). are shown simultaneously. The flutter results obtained by using VOLUME 2: SUPPLEMENTAL SYSTEM DESIGN AND relaxation and the indicial methods are, in general, in good MAINTENANCE DOCUMENT Topical Report, May 1975 - agreement. The present flutter results for a special case of a May 1977 thin parabolic airfoil at a low transonic Mach number of 0.7 A. Tornallyay, R. E. Clemmons. and A. I. Kroll Washington compare favorably with that obtained by using linear flat plate NASA Sep. 1979 34 p refs theory. The trend of each flutter curve and the effect of each (Contract NAS1-13918( parameter are discussed in detail. GRA (NASA-CR-2860: D6-44469-VoI-2( Avail. NTIS NC A03/MF AOl CSCL 01A The time history solution program L225 (TEV1 26( is described. N79-31 159# Advisory Group for Aerospace Research and The program calculates the time responses of a linear system Development. Neuilly- Sur- Seine (France(. by convoluting the impulsive response functions with the time EXPERIMENTAL DATA BASE FOR COMPUTER PROGRAM dependent excitation. The convolution is performed as a ASSESSMENT: REPORT OF THE FLUID DYNAMICS PANEL multiplication in the frequency domain. Fast Fourier transform WORKING GROUP 04 techniques are used to transform the product back into the time May 1979 609 p refs Avail: NTIS domain to obtain response time histories. The design and structure (AGARD-AR- 138: ISBN-92-835-1323-1) of the program is presented. A W.H. HC A99/MF AOl The acquisition of highly reliable wind tunnel test data for aircraft design was investigated. Boeing Commercial Airplane Co.. Seattle, Wash. N79-31155# N79-31160# Deutsche Forschungs- urid Versuchsanstalt fuer A PROGRAM FOR CALCULATING LOAD COEFFICIENT Luft- und Raumfahrt. Goettingen (West Germany(. MATRICES UTILIZING THE FORCE SUMMATION METHOD. INTRODUCTION AND OVERVIEW OF CONFIGURATIONS 1218 (LOADS). VOLUME 2: SUPPLEMENTAL SYSTEM Juergen Barche In AGARD Exptl. Data Base for Computer DESIGN AND MAINTENANCE DOCUMENT Topical Report, Program Assessment May 1979 5 p May 1975 - May 1977 L. R. Anderson and R. D. Miller Washington NASA Sep. Avail NTIS HC A99/MF AOl 1979 94 p refs An overview of the application of two- and three- (Contract NAS1-13918) dimensional transonic flows to aircraft design is presented. The (NASA- CR -2854: D6-44463-Vol-2) Avail. NTIS criteria for two-dimensional, three-dimensional, and body-alone HC A05/MF AOl CSCL 01A configurations are tabulated. F 0 S. The LOADS computer program L218 which calculates dynamic load coefficient matrices utilizing the force summation method is described The load equations are derived for a flight N7931163*# National Aeronautics and Space Administration, vehicle in straight and level flight and excited by gusts and/or Washington, D. C. control motions. In addition, sensor equations are calculated for SUPERSONIC TRANSPORT VIS-A-VIS ENERGY SAVINGS use with an active control system. The load coefficient matrices G. Cormery Sep. 1979 27 p Transl. into ENGLISH from are calculated for the following types of loads: (1) translational Aeron. Astronaut (Paris(. vol. 69. no. 2. 1978 p 3-14 Original

665 N79-31164

language document was announced as A78-35893 Transl. by The primary objectives of the fire tests are: (1) conduct full Kanner (Leo) Associates. Redwood City. Calif. scale test with 737 fuselages by the end of 1980; (2( demon- (Contract NASw-3 199) strate evacuation time increase to five minutes minimum; (NASA-TM-75464( Avail: NTIS NC A03/MF AOl CSCL (3( show that exterior fire will not penetrate an intact cabin for 01C five minutes; (4) show that closed cabin will not have excess The energy and economic saving modifications in super- smoke or temperatures above 400 F: and (5) demonstrate that sonic transportation are studied. Modifications in the propulsion fire in cabin opening will not propagate throughout cabin. The systems and in the aerodynamic configurations of the Concorde test program has three phases. A test schedule and status of aircraft to reduce noise generation and increase fuel efficiency required materials are presented. G. Y. are discussed. The conversion of supersonic aircraft from fuel oils to synthetic fuels is examined. A.W.H. N7931168*# National Aeronautics and Space Administration. Lyndon B. Johnson Space Center, Houston, Tex. N7931164*# Boeing Vertol Co.. Philadelphia, Pa. SEAT TEST PROGRAM DEVELOPMENT OF CRASHWORTHY PASSENGER SEATS Richard W. Bricker In FOR GENERAL-AVIATION AIRCRAFT NASA. Ames Rex. Center Conf. on Fire Resistant Mater. Jul. 1979 p 13-26 M. J. Reilly and A. E. Tanner Aug. 1979 112 p refs (Contract NAS1-14637( Avail: NTIS HC A13/MF AOl CSCL 01C (NASA-CR-159100, D210-11336-1) Avail: NTIS The test program has the objectives to (1) evaluate severity HC A06/MF AOl CSCL O1C of newspaper ignition source with contemporary seats (determine Two types of energy absorbing passenger seat concepts weight loss, visual damage, and if ignition source is severe enough suitable for installation in light twin-engine fixed wing aircraft to show improvement with new material configurations); were developed. An existing passenger seat for such an aircraft (2) compare damage with jet A-i ignition source; and was used to obtain the envelope constraints. Ceiling suspended 3) determine if materials for seat tests pass FAR 25 and obtain and floor supported seat concept designs were developed. A LOl. Test configurations, data acquired, material test results, restraint system suitable for both concepts was designed. Energy seat test results, and conclusions are presented. absorbing hardware for both concepts was fabricated and tension G. Y. and compression tests were conducted to demonstrate the stroking capability and the force deflection characteristics. Crash impact N7931169*# Southwest Foundation for Research and Educa- analysis was made and seat loads developed. The basic seat tion, San Antonio, Tea. structures were analyzed to determine the adequacy of their RECENT ADVANCES IN MATERIALS TOXICOLOGY strength under impact loading. R.E.S. Dane M. Russo In NASA. Ames Res. Center Conf. on Fire Resistant Mater. Jul 1979 p 27-43 N79-31 165# National Transportation Safety Board, Washington, D. C. Avail: NTIS NC A13/MF AOl CSCL 01C AIRCRAFT ACCIDENT REPORT: SWIFT AIRE LINES, INC., An overview of the fire toxicology program, its principal NORD 262, N418SA, MARINA DEL REY, CALIFORNIA, objectives and approach, is outlined The laboratory methods of MARCH 10, 1979 assessing pyrolysis product toxicity for two experiments are 16 Aug. 1979 32 p presented The two experiments are' a comparison of test end (NTSB-AAR-79-13( Avail NTIS NC A03/MF AOl points; and an evaluation of operant techniques. A third experiment On March 10, 1979, Flight 235, A-Nord 262, ditched in is outlined for a comparison of full-scale and laboratory toxicity the Santa Monica Bay near Marina Del Rey, California, shortly tests, with the purpose of determining animal survivability in after takeoff from Los Angeles International Airport. Flight 235 full-scale tests. Future research plans are also outlined. G. Y. was a scheduled commuter airline passenger flight from Los Angeles, California, to Santa Maria. California. with four passengers N7931170*# National Aeronautics and Space Administration and three crewmembers on board. The probable cause of the Lyndon B. Johnson Space Center. Houston, Tex. accident was determined to be the flightcrew's mismanagement STATUS OF CANDIDATE MATERIALS FOR FULL-SCALE of an emergency procedure following an autofeather of the right TESTS IN THE 737 FUSELAGE propeller which resulted in their shutting down the remaining Daniel Supkis In NASA. Ames Res. Center Conf. on Fire engine. Contributing to the accident was the unavailability of Resistant Mater. Jul. 1979 p 45-69 vital restart information to the crew. A.W.H. Avail NTIS HC A13/MF AOl CSCL 01C N79-31 166* # National Aeronautics and Space Administration. The test program has the objectives to: (1) increase passenger Ames Research Center, Moffett Field, Calif. evacuation time to a minimum of five minutes from commercial CONFERENCE ON FIRE RESISTANT MATERIALS: A aircraft in case of a fire; (2) prevent an external fire from entering COMPILATION OF PRESENTATIONS AND PAPERS closed cabins for five minutes by using fire barrier materials in Demetrius A. Kourtides. ed. and Gerald A Johnson. ed. (Boeing the exterior wall; 3) demonstrate that a closed cabin will not Com. Airplane Co., Seattle, 'Wash.) Jul. 1979 287 p Conf. reach 400 F; and (4) prove that a fire near a cabin opening held in Seattle, 1-2 Mar, 1979 will not propagate through the cabin for a minimum of five )NASA-CP . 2094: A-7894) Avail: NTIS NC A13/MF AOl CSCL minutes. The materials status is outlined for seat cushions. 011C upholstery and associated seat materials, wall and ceiling panels. The proceedings of the NASA IRE Resistant Materials floor panels, carpet and carpet underlay, windows, cargo bay Engineering (FIREMEN) Program held at Boeing Commercial liners, insulation bagging, and thermal acoustical insulation. G.Y. Airplane Company, Seattle, Washington. on March 1-2. 1979 are reported The conference was to discuss the results of research N7931171*# Solar Turbines International. San Diego. Calif by the National Aeronautics and Space Administration in the DEVELOPMENT OF FIRE-RESISTANT, LOW SMOKE field of aircraft fire safety and fire-resistant materials. The program GENERATING, THERMALLY STABLE END ITEMS FOR topics include the following: (1) large-scale testing: (2) fire COMMERCIAL AIRCRAFT AND SPACECRAFT USING A toxicology: )3) polymeric materials; and )4) fire modeling. BASIC POLYIMIDE RESIN John Gagliani In NASA. Ames Res. Center Conf. on Fire Resistant Mater. Jul 1979 p 71-92 N7931167*# National Aeronautics and Space Administration Lyndon B. Johnson Space Center, Houston. Tea. Avail: NTIS HC A13/MF AOl CSCL 01C AIRPORT FLAMMABILITY, FULL SCALE FIRE TESTS Experimental data pertinent to flexible resilient foams, low Richard W. Bricker In NASA. Ames Res. Center Conf. on density wall panels, high strength floor panels and thermal Fire Resistant Mater. Jul 1979 p 1.12 acoustical insulation are presented. An evaluation of the effect of the heterocyclic diamine component on the compression set Avail: NTIS NC A13/MF AOl CSCL 01C of the foams was carried Out. Processes and Compositions for

666 N79-31186 fabricating wall panels were evaluated. Thermal acoustical N79-311785# Boeing Commercial Airplane Co., Seattle, Wash. po!yimide materials were developed to replace conventional glass FIREMEN PROGRAM Status Report batting insulation. To reduce the thermal stresses and improve Roy A. Anderson and Gerald A. Johnson In NASA. Ames the burn through resistance, cross linked polyimide foams were Res. Center Conf. on Fire Resistant Mater. Jul. 1979 p 183-222 developed but not evaluated. G V. Avail: NTIS HC A13/MF AOl CSCL 01C N7931172*# Jet Propulsion Lab., Calif. Inst. of Tech.. Pasadena. An overview of the program to improve fire retardant interior GLOBAL ENCLOSURE FIRE MODELING WITH APPLICA- panels is presented. The sandwich panel makeup for different TIONS components, and the burn test results are presented. F.O.S. Jay William Stuart In NASA. Ames Res. Center Coot, on Fire Resistant Mater, Jul. 1979 p 93-101 N7931183*# Isovolta Co.. Wiener Neudorf (Austria). THE FLUORENONE POLYESTER ISO FPE OF ISOVOLTA Avail: NTIS HC A13/MF AOl tSCL 01C COMPANY, AUSTRIA A brief review of LERC (Limiting Energy Release Criteria) is H. Weber In NASA. Ames Flea. Center Conf. on Fire Resistant presented. Application of LERC to JSC/Boeing ignition source Mater. Jul. 1979 p 271-282 full-scale tests and to JSC/Dacfir math-model validation tests is outlined. It is concluded that: (1) a complete LERC application Avail: NTIS NC A13/MF AOl CSCL 01C to the JSC/Boeing tests verifies the fuel load criterion as the Methods for the synthesis of ISO-FPE are described, and limiting constraint, (2) the variability of magnitude and form of the mechanical properties are given. The industrial production of the results of repeated tests with and without small variations powder and film is discussed. F.0.S. in parameters emphasizes the significance of the local flow, species concentration, and heat transfer distribution: and (3) weight loss N79-31184# Air Force Engineering and Services Center. Tyndall measurements of recent JSC tests show consistent results with AF8, Fla prior methods, fuel load constrained G. Y. AN EVALUATION OF THE BIRD AIRCRAFT STRIKE HAZARD AT HILL AFB. UTAH (AFIC) N79-31 173*# Jet Propulsion Lab., Calif. Inst. of Tech.. Pasadena. Jeffrey J. Short, James S. Kent, Ardrah L. Buddin, Ill, and William ENCLOSURE FIRE DYNAMICS MODEL H. Niemeier Jan. 1979 45 p refs Josette Bellan In NASA, Ames Res. Center Conf. on Fire (AD-A070459; AFESC-TM-1 -79) Avail: NTIS Resistant Mater. Jul. 1979 p 103-116 HC A03/MF AOl CSCL 01/2 Hill Air Base was surveyed from 30 September to 12 October Avail' NTIS HC A13/MF AOl CSCL OIC 1978 and from 28 to 30 January 1979 by the Air Force A practical situation of an enclosure fire is presented and Engineering and Services Center Bird/Aircraft Strike Hazard Bash why the need for a fire dynamic model is addressed. The difficulties Team Insect populations, vegetation, bird activity and local in establishing a model are discussed, along with a brief review geography were studied to assess the impact of birds on flying of enclosure fire models available. The approximation of the operations at the base GRA practical situation and the model developed are presented C.V. N79-31 185*# National Aeronautics and Space Administration. N7931175*# Jet Propulsion Lab., Calif. Inst. of Tech., Pasadena. Lewis Research Center, Cleveland, Ohio. FUSELAGE VENTILATION UNDER WIND CONDITIONS UHF COPLANAR-SLOT ANTENNA FOR AIRCRAFT-TO- Jay William Stuart in NASA. Ames Res. Center Conf. on Fire SATELLITE DATA COMMUNICATIONS Resistant Mater. Jul. 1979 p 127-134 Royce W. Myhre 1979 21 p refs Presented at the Printed Circuit Antenna Technol. Workshop, Las Cruces, N. Mex., Avail NTIS HC A13/MF AOl CSCL 01C 17-19 Oct. 1979: sponsored by New Mexico State Univ. and To determine realistic fuselage ventilation rates for post- the Army Flea. Office Physical Lab. crash fires and full-scale fire tests, the effects on wind-about (NASA-TM-79239; E-146( Avail: NTIS NC A02/MF AOl CSCL fuselage ventilation rate of various parameters were studied. The 178 parameters investigated were fuselage size and shape, fuselage A lightweight low drag coplanar slot antenna was developed orientation and proximity to ground. fuselage-opening and for use on commercial jet aircraft that will provide upper location, and wind speed and direction. F.O.S. hemisphere coverage in the UHF band at frequencies of 402 and 468 MHz is described. The antenna is designed to transmit meteorological data from wide body jet aircraft to ground users N79-31 1 76*// National Aeronautics and Space Administration. via synchronous meteorological data relay satellites. The low Ames Research Center, Moffett Field, Calif. profile antenna (23.5 cm wide by 38.1 cm long slot by 1.9 cm FIRE RESISTANT AIRCRAFT SEAT PROGRAM high) is a conformal antenna utilizing the coplanar approach Larry A. Fewell In its Conf. on Fire Resistant Mater. Jul. with the advantages of broad frequency bandwidth and improved 1979 p 135-166 electrical integrity over wide range of temperature. The antenna Avail: NTIS HC A13/MF AOl CSCL 01C is circular polarized, has anon axis gain of near +2.5 dB, and a Foams. textiles, and thermoformable plastics were tested to HPBW greater than 90 deg. Areas discussed include antenna determine which materials were fire retardant, and safe for aircraft design, radiation characteristics, flight testing, and system passenger seats. Seat components investigated were the performance. K. L. decorative fabric cover, slip covers, fire blocking layer, cushion F.O.S. N79-31 186'# National Aeronautics and Space Administration. reinforcement, and the cushioning layer. Langley Research Center. Hampton. Va. FLIGHT PERFORMANCE OF THE TCV B-737 AIRPLANE N7931177*# Boeing Commercial Airplane Co.. Seattle. Wash. AT KENNEDY AIRPORT USING TRSB/MLS GUIDANCE A REVIEW OF BOEING INTERIOR MATERIALS AND FIRE William F. White and Leonard V. Clark Jul. 1979 29 p refs TEST METHODS DEVELOPMENT PROGRAMS )NASA-TM-80148) Avail: NTIS NC A03/MF AOl CSCL Eugene Bara In NASA Ames Res. Center Conf. on Fire 17G Resistant Mater. Jul. 1979 p 167-181 The terminal configured vehicle (TCV) B 737 was flown in demonstration of the time reference scanning beam/microwave Avail: NTIS HCA13/MF AOl CSCL01C landing system (TRSB/MLS). The flight performance of the TCV Total materials systems requirements, and government and airplane during the demonstration automatic approaches and industry programs are outlined along with a new fire test landings while utilizing TRSB/MLS guidance is reported. The methodology, and the potential decrease in post crash fire hazards. TRSB/MLS is shown to provide the terminal area guidance The flammability, smoke and toxicity goals, and the scope of necessary for flying curved automatic approaches with short materials systems are tabulated. F. 0. S. finals. A.W.H.

667 N79-31189

N79-31 189# Naval Postgraduate School, Monterey, Calif. N7931195*# Lockheed-Georgia Co., Marietta. A DEVELOPMENTAL COMPUTER MODEL FOR INVESTIGA- CORRELATION OF DATA RELATED TO SHOCK-INDUCED TIONS OF AIR TRAFFIC MANAGEMENT PROBLEMS: A TRAILING-EDGE SEPARATION AND EXTRAPOLATION TO CASE INVESTIGATING TWO DECISION STRATEGIES FLIGHT REYNOLDS NUMBER M.S. Thesis J. F. Cahill and P. C. Connor Washington NASA Sep. 1979 John Thomas Malokas, Jr. and Arvid Paul Pederson Mar. 1979 82 refs 133 refs p p (Contract NAS2-9331) (AD-A071075) Avail: NTIS HC A07/MF AOl CSCL 17/7 (NASA-CR-3178) Avail: NTIS HC A05/MF AOl CSCL 01C A computer simulation model designed to help solve regional Pressure data from a number of previous wind tunnel and air traffic scheduling problems was developed. Bases, mission flight investigations of high speed transport type wings were areas, and aircraft were modeled using the simulation language analyzed with the intent of developing a procedure for extrapolating SIMSCRIPT. Events in the simulation included takeoffs, depar- tures, enroutes, missions, arrivals at Initial Approach Fixes (lAFs) low Reynolds number data to flight conditions. These analyses produced a correlation of the development of trailing-edge and landings. To demonstrate potential use of the model, the problem of rescheduling Strategic Air Command (SAC) aircraft separation resulting from increases in Mach number and/or angle upon base closures was addressed. Two strategies for the diversion of attack and show that scale effects on this correlated separation of such aircraft were developed, implemented and the results development and the resulting shock location changes fall into a regular and apparently universal pattern. Further studies appear compared on the basis of impact on final destination bases and warranted to refine the correlation through a detailed consideration average aircraft airborne time. Strategy 1 entailed the rerouting of boundary layer characteristics, and to evaluate scale effects of aircraft to designated alternate bases or to the nearest open on supercritical wings. base without constraint. Strategy 2 involved the selection of an Author alternate base by insuring that parking spaces and appropriate maintenance support were available. Finally, extensions to the model and recommendations are discussed GRA N79-31197# Dougla Aircraft Co.. Inc.. Long Beach. Calif. EFFECT OF TRANSPORT/ BOMBER LOADS SPECTRUM ON CRACK GROWTH Final Technical Report, Sep. 1976 - Sep. N79-31 1 92// Lockheed-California Co.. Burbank. 1978 TESTING AND ANALYSIS OF DUAL-MODE ADAPTIVE P. R. Abelkis Nov. 1978 217 p refs LANDING GEAR, TAXI MODE TEST SYSTEM FOR YF-12A (Contract F336 1 5-76-C-3 116) Max A. Gamon Sep 1979 54 p refs Sponsored by NASA (AD-A069287; AFFDL-TR-78- 134) Avail. NTIS (NASA . CR- 144884: LR-28776( Avail NTIS HC A10/MF AOl CSCL 01/3 HC A04/MF AOl CSCL 01C This program investigated analytically and experimentally the The effectiveness of a dual mode adaptive landing gear system effect of transport/ bomber loads spectrum variations on crack in reducing the dynamic response of an airplane during ground growth. The spectrum represented a STOL transport (C- 15) wing taxiing was studied. The dynamic- taxi tests of the YF-12A research lower surface loading. The 1 16 spectrum variations were airplane are presented. A digital computer program which generated, grouped in the following categories: (1) baseline simulated the test conditions is discussed. The dual mode system spectra. (2) mission mix. (3) sequence of missions. (4) individual as tested provides dynamic taxi response reductions of 25 percent flight length, (5) flight segments. (6) exceedances spectra. (7) at the cg and 30 to 45 percent at the cockpit. A.W.H. design stress level. (8) valley/peak coupling, (9) low load truncation, (10) high infrequent loads, (ii) clipping of large N79. 31193*# Rockwell International Corp.. Los Angeles, Calif. loads. (12) miscellaneous variations, and (13) combined variations Aircraft Div. Spectra were generated as random cycle-by-cycle, flight- by-flight RIDE QUALITIES CRITERIA VALIDATION/PILOT PER- sequences. Analyses and tests were performed on 7475-T7651 FORMANCE STUDY: FLIGHT TEST RESULTS Final aluminum, to .25 inches, starting with an initial through-the- Report thickness 0.03-inch crack out of a 1/4-inch diameter hole. Louis U. Nardi, Harry Y. Kawana. and David C. Greek Sep. Crack growth analysis predictions were made for all 116 spectra 1979 69 p refs using the linear model. Crack growth tests were performed with (Contract NAS4-2542) 33 of these spectra. Good correlation was obtained between (NASA-CR . 144885, NA-78-897( Avail: NTIS analysis and test results in all cases except with spectra dealing HC A04/MF AOl CSCL OiC with increased frequency and magnitude of high infrequent loads Pilot performance during a terrain following flight was studied and spectra which were drastically changed from a wing-type for ride quality criteria validation. Data from manual and automatic to a vertical tail-type spectrum. Largest effects on crack growth terrain following operations conducted during low level penetra- life, as measured in flight hours, was due to flight length, mission, tions were analyzed to determine the effect of ride qualities on mission mix, and design Stress level variations. Based on the crew performance. The conditions analyzed included varying levels results of this program, fleetwide crack growth variations by a of turbulence, terrain roughness, and mission duration with a factor of 100 and 10 could be experienced, depending on whether ride smoothing system on and off. Limited validation of the B-i it was short-term or long-term variation, GRA ride quality criteria and some of the first order interactions between ride qualities and pilot/vehicle performance are N79-31198# Douglas Aircraft Co.. Inc.. Long Beach, Calif. highlighted. An earlier B-i flight simulation program correlated A USER'S MANUAL FOR A COMPUTER PROGRAM TO well with the flight test results. A.W.H. GENERATE FATIGUE SPECTRUM LOADING SEQUENCES Final Technical Report, Sep. 1976 - Sep. 1978 N79-31 194# Aeronautical Research Labs.. Melbourne (Australia). P. R. Abelkis, P. M Lee, and B. P. Tate Nov. 1978 246 p LOAD SPECTRUM MEASURING EQUIPMENT. PART 1: refs DETAILS OF MK 1 SYSTEM PRESENTLY USED TO ACQUIRE (Contract F336 1 5-76-C-3 116) DATA IN WESSEX MK 318 HELICOPTERS (AD-A069288; AFFDL-TR-78-1 36) Avail: NTIS K. F. Fraser and U. R. Krieser Aug. 1978 54 p refs HC A1l/MF AOl CSCLO1/3 (ARL-MECI-4-ENG-NOTE-371 AR-001-301) Avail: NTIS The report contains, in the form of a user's manual, the HC A04/MF AOl listing and complete description of a computer program to generate Measuring equipment was developed which uses a set of fatigue spectrum loading sequences. The program is specifically electromechanical counters to indicate the integrated time in tailored for the development of random cycle-by-cycle, flight-by- seconds for which torque loading on a transmission component flight loading sequences typical of aircraft structures. However. falls within each of a number of bands. Separation of the torque Its general features allow the development of any type spectrum. level into bands is made possible using a single transducer, an The random sequence of cycles and flights is produced by a amplifier with zero and gain adjustments for setting the extremes random number generator. Alternate non-random flight sequences of the torque range of interest, an analogue to digital converter can also be generated. The basic input data consists of loads and decoder to separate the torque range into bands and counters exceedances spectra or data to calculate such spectra by the to totalize contributions in each band. Author program The program contains the following spectrum editing

668 N79-31204 features: (1) truncation - elimination of cycles as a function of transparency materials have been devised from both military and range and Fl, peak or valley, (2) clipping - loads below or above commercial aircraft with major attention directed to the topics a specified clipping value are set equal to that value. (3) all of bird impact resistance, structural design integration, systems loads in the spectrum are multiplied by a constant. The output integration, and design for maintainability and reliability. The is a valley, peak sequence of the loads spectrum. The spectrum authors and Air Force Flight Dynamics Laboratory FEW agree may be read into a magnetic tape to be used in other analyses that the various disciplines and essential technical design concepts GRA represented, including associated reports noted in Section IV, or in testing. should all be utilized in arriving at an optimum design of the canopy system for any production aircraft. GRA N79-31199# Air Force Inst. of Tech.. Wright-Patterson AFB, Ohio. School of Engineering. INVESTIGATION OF ROLL PERFORMANCE FOR A HIGHLY N79-31202# Dayton Univ., Ohio. Research Inst. NON LINEAR STATICALLY UNSTABLE FIGHTER-TYPE FUEL TANK SURVIVABILITY FOR HYDRODYNAMIC RAM AIRCRAFT M.S. Thesis INDUCED BY HIGH VELOCITY FRAGMENTS. PART 1: Paul L. Vergez Mar. 1979 101 p refs EXPERIMENTAL RESULTS AND DESIGN SUMMARY Final (AD-A069301: AFIT/GGO/ EE/79-4) Avail: NTIS Report, Sep. 1977 - Oct. 1978 HG A06/MF AOl CSCL 01/3 S. J. Bless Wright-Patterson AFB, Ohio AFFDL Jan. 1979 A linearized model of a fighter-type aircraft with significant 127 p refs roll-pitch inertial coupling, including its full flight control system (Contract F33615-77-C-2082; AF Proj. 2402) is required in order to conduct a comparative analysis between (AD-A070113, UDR-TR-78-1 1 5 . Pt-1 AFFDL-TR-78-182-Pt-1( body axis rolls and velocity (stability) axis rolls. The stability of Avail: NTIS HC A07/MF AOl CSCL 01/3 the aircraft is checked at various roll rates for both body axis Failure data, displacement data, and pressure data were and velocity axis rolls. This is done by examining the signs of obtained from laboratory experiments. Panels were made from the eigenvalues of the linearized model-positive for unstable and 7075- T6 and 2024- T3 aluminum and from graphite epoxy negative for stable. It is found that at various angles of attack panel thicknesses were 1.6 to 6.35 mm. Protection included the velocity axis rolls prove to be at least as stable and, in 10 mm ballistic foam and stiffeners. Projectiles were 5.6 g and most cases, more stable than body axis rolls. The stability is 11.7 g spheres and cubes Failures were always catastrophic. also observable for various combinations of flight control systems. and failure thresholds were always abrupt. When cracks formed, In developing a nonlinear coupled equation solver, a single they ran across the panels, except when stiffeners were present. equation with known solutions is considered first. This is done In thin panels, cracks initiated at the corners of the perforation to show a simplified version of what the nonlinear program is when cubical fragments were used. The entrance panel damage required to do. Next, a pair of nonlinear coupled equations is was primarily induced by the shock wave generated by the impact. analyzed. The development of the program for the single equation The very high shock pressure resulted in impulsive loading of :ase proves to be successful, but certain problems arise when the panels that caused prompt crack formation. Cracks were working with a pair of coupled equations. This thesis provides a propagated by the displacement field. GRA good foothold on a method of analysis known as Bifurcation Analysis and Catastrophe Theory which can be used to solve the nonlinear coupled aircraft equations. This thesis presents some N79-31203# Air Force Flight Dynamics Lab., Wright-Patterson . GRA AFB, Ohio. of the problems which could be encountered. EVALUATION OF F-ill WEAPON BAY AERO.ACOUSTIC AND WEAPON SEPARATION IMPROVEMENT TECH- N79.31200fl Dayton Univ. Research Inst., Ohio. NIQUES Final Technical Report, 1 May 1976 - 1 Aug. FUEL TANK 'SURVIVABILITY FOR HYDRODYNAMIC RAM 1978 INDUCED BY HIGH VELOCITY FRAGMENTS. PART 2: Rodney L. Clark Feb. 1979 150 p refs NUMERICAL ANALYSES Final Report, Oct. 1977 - Oct. )AF Proj. 2404) 1978 (AD-A070253; AFFDL-TR-79-3003( Avail. NTIS Sheldon H. Schuster and Jack S. Macales Wright-Patterson HG A07/MF AOl CSCL 01/3 AFB, Ohio AFFDL Feb 1979 104 p Prepared by California Several aero-acoustic suppression devices have been Research and Technology, Inc., Woodland Hills evaluated which were considered feasible for installation on an (Contract F33615-77-C-2082; AF Proj. 2402) F-i 11 aircraft for flight test evaluation. The most promising (AD .A0701 28; AFFDL-TR-78- 182-Pt-2) AvaiL NTIS modification consists of a saw tooth spoiler mounted at the HG A06/MF AOl CSCL 01/3 leading edge of the weapon bay. This device would be erected Numerical finite difference CRALE and finite element NONSAP to a 90 degree position during the bay doors opening sequence. calculations of the behavior of fuel tank front panels, penetrated The spoiler is folded flush with the fuselage during all other by steel fragments impacting at velocities of 1.0-2.0 km/sec flight conditions. Wind tunnel tests have shown that this spoiler were used to explain the phenomena observed in an accompanying improves the aero-acoustic environment within the open weapon experimental program Part I of this report. Analytic expressions bay and improves the weapon separation characteristics over for the variation of peak pressure and impulse along the panel the Mach range of .95 to 1.3 investigated during the drop test as functions of fragment size, velocity. and panel areal density phase. GRA were derived from the finite difference runs and used as boundary conditions in the finite element calculations of panel failure and N79-31204// Argonne National Lab., III. displacements. GRA ANALYSIS OF PLUME RISE FROM JET AIRCRAFT A. J. Yamartino, J. Lee. S. Bremer, D. Smith, and J. Calman N79-31201# Douglas Aircraft Co.. Inc., Long Beach, Calif. 1979 7 p refs Presented at the 4th Symp. on Turbulence. WINDSHIELD TECHNOLOGY DEMONSTRATOR PRO- Diffusion and Air Pollution, Boston. 15-18 Jan. 1979 Sponsored GRAM-CANOPY DETAIL DESIGN OPTIONS STUDY Final in part by FAA and Air Force Prepared in cooperation with Report, Feb. 1977 - Sep. 1978 Environmental Research and Technology, Lexington. Mass. M. J. Coker, J. B. Hoffman. and J. J. Lawrence, Jr. Wright- (Contract W-3 1-1 O9-eng-38( Patterson AFB, Ohio AFFOL Sep 1978 352 p refs (CONF-790142-1( Avail: NTIS HG A02/MF AOl (Contract F33615-75-C-3105; AF Proj. 2202) Preliminary results of an investigation of the behavior of (AD-A070376; MDC-J7176; AFFDL-TR-78-1 14) Avail: NTIS buoyant jet engine exhaust plumes in a crosswind are discussed HC A16/MF AOl CSCL 01/3 and attempts are made to identify the degree to which the This report documents the work accomplished for the plume rise can be described by relationships developed for other Windshield Technology Demonstrator Program. The studies, types of sources At least four factors were found to affect the analyses, testing, and development accomplished during this rate of dilution of jet exhaust before it reached receptors adjacent program involved a total system approach required for aircraft to taxiways or runways: (1) turbulent mixing of the jet exhaust canopies in the context of the continuing Air Force generic wind at the engine exit; (2) buoyant plume rise; (3) advective dilution; shield development programs. State-of-the-art applications of new and (4) dispersion by ambient turbulence. DOE

669 N79-31205

N79-31205# Arinc Research Corp.. Annapolis, Md. W. 0. Gaffin ' 8 Jun. 1979 66 p ref RELIABILITY IMPROVEMENT WARRANTY TERMS AND (Contract NAS8.20630( CONDITIONS FOR THE INTEGRATED AVIONICS CONTROL (NASA-CR- 159661; PWA-55 1 5-87C( Avail: NTIS SYSTEMS (IACS) Final Report. Jan. - Mar. 1979 HC A04/MF AOl CSCL 21E Larry Cox May 1979 44 p The JT9D-70/59 high pressure turbine active clearance (Contract DAAB07-78-A-6606) control system was modified to provide reduction of blade tip (AD-A069454; Rept-1 573-01 -1-1927) Avail: NTIS clearance when the system is activated during cruise operation. HC A03/MF AOl CSCL 01/3 The modification increased the flow capacity and air impinge- The Advanced Systems Division of the U.S. Army Avionics ment effectiveness of the cooling air manifold to augment turbine Research and Development Activity at Fort Monmouth, New case shrinkage capability, and increased responsiveness of the Jersey, has issued Engineering Development (ED) contracts to airseal clearance to case shrinkage. The simulated altitude engine two contractors for the Integrated Avionics Control System (IACS(. testing indicated a significant improvement in specific fuel One of the features of the ED progam will be a complete consumption with the modified system. A 1000 cycle engine logistics support analysis (LSA) of Reliability Improvement endurance test showed no unusual wear or performance Warranty (RIW( as an alternative to Army organic support. ARINC deterioration effects on the engine or the clearance control system. Research Corportion assisted the IACS Project Office in the Rig tests indicated that the air impingement and seal support development of draft RIW terms and conditions on which the configurations used in the engine tests are near optimum. K. L. LSA will be based. This report presents the activities that were performed and describes the draft RIW and conditions that were N79-31209# National Aviation Facilities Experimental Center. developed. GRA Atlantic City. N. J. EXHAUST EMISSION TRAVERSE INVESTIGATION OF A JT3D-1 TURBOFAN ENGINE Final Report, Jan. 1975 - Aug. N7931206*# National Aeronautics and Space Admirvstration, 1978 Washington, D C. Gerald R. Slusher Jun. 1979 55 p refs INVESTIGATION OF AIR STREAM FROM COMBUSTOR- (FAA Proj. 201-521-100) LINER AIR ENTRY HOLES, 3 (AD-A072019; FAA-RD-79-23; FAA-NA-79-10( Avail: NTIS Tetsuro Aiba and Tokuji Nakano Aug. 1979 37 p refs Transl. HC A04/MF AOl CSCL 21/5 into ENGLISH of Ko fuka nenshoki no kukiko kara no nagare The emissions in the exhaust plume of a JT3D-1 turbofan ni tsuite, 3" NatI. Aerdspace Lab., Tokyo, NAL-TR-369, 1974 engine were investigated to Optimize the shape, size. and location 23 p Original language document was announced as N75-17358 of fixed probes for acquiring representative emission samples. Transl. by Scientific Translations Service, Santa Barbara. Calif. Traverse measurements of 153 points over the exhaust nozzle (Contract NASw-3 198) were accomplished with the sample points located in the corners (NASA-TM-75430; NAL-TR-369( Avail: NTIS of two inch squares forming a traverse grid. The average emission HC A03/MF AOl CSCL 21E levels, contours, and profile distributions were determined. The Jets flowing from air entry holes of the combustor liner of predicted performances of area weighted cruciform and diamond a gas turbine were investigated. Cold air was supplied through probe designs were calculated from interpolations of the traverse the air entry holes into the primary hot gas flows The mass contours. A.W.H. flow of the primary hot gas and issuing jets was measured, and the behavior of the air jets was studied by the measurement of N79,31210*# National Aeronautics and Space Administration. the temperature distribution of the gas mixture. The air jets Lewis Research Center. Cleveland, Ohio. flowing from three circular air entry holes, single streamwise AN OVERVIEW OF NASA RESEARCH ON POSITIVE long holes, and two opposing circular holes, parallel to the primary DISPLACEMENT TYPE GENERAL AVIATION ENGINES flow were studied along with the effects of jet and gas stream E. E. Kempke and E A. Willis 1979 40 p refs Presented at velocities, and of gas temperature. The discharge coefficient, the the Aircraft Systems and Technol. Meeting N. Y., 20-22 Aug. maximum penetration of the jets, the jet flow path, the mixing 1979; sponsored by AIAA of the jets, and temperature distribution across the jets were (NASA-TM-79254; E-165; AIAA-79-1824( Avail: NTIS investigated. Empirical expressions which describe the characteris- HC A03/MF AOl CSCL 21E tics of the jets under the conditions of the experiments were The general aviation positive displacement engine program formulated. A.W.H. encompassing conventional, lightweight diesel, and rotary combustion engines is described. Lean operation of current N79-31207 5 # General Electric Co., Cincinnati, Ohio production type spark ignition engines and advanced alternative EXPERIMENTAL CLEAN COMBUSTOR PROGRAM (ECCP). engine concepts are emphasized. J.M.S. PHASE 3 Final Report C. C. Gleason and D W. Bahr 1 Jun. 1979 201 p refs N79-3121 (Contract NAS3-19736( 1# National Aviation Facilities Experimental Center, Atlantic City, N J. (NASA-CR-135384: R79AEG41 0) Avail: NTIS HC A10/MF AOl CSCL 21E EXHAUST EMISSIONS CHARACTERISTICS FOR A - A double annular advanced technology combustor with low GENERAL AVIATION LIGHT AIRCRAFT TELEDYNE CONTINENTAL MOTORS TSIO . 360-C PISTON ENGINE pollutant emission levels was evaluated in a series of CF6-50 Final Report engine tests. Engine Iightoff was readily obtained and no difficulties Eric E. Becker May 1979 78 refs were encountered with combustor staging Engine acceleration p (FAA Proj. 201-521-100) and deceleration were smooth, responsive and essentially the (AD-A070010; FAA-RD-79-14; FAA-NA-79-3) Avail NTIS same as those obtainable with the CF6 . 50 combustor. The HC A05/MF AOl CSCL 21/2 emission reductions obtained in carbon monoxide, hydrocarbons. and nitrogen oxide levels were 55. 95, and 30 percent, The TSIO-360-C engine (S/N 300244) was tested to develop respectively, at an idle power setting of 3.3 percent of takeoff an exhaust emissions data base This data base consists of currents power on an EPA parameter basis. Acceptable smoke levels of current production baseline emissions characteristics, lean-out emissions data, effects of leaning-out the fuel schedule on cylinder were also obtained. The exit temperature distribution of the head temperatures, and data showing ambient effects on exhaust combustor was found to be its major performance deficiency. In emissions and cylinder head temperatures. The engine operating all other important combustion system performance aspects, the with its current full-rich production fuel schedule could not meet combustor was found to be generally satisfactory. K. L. the proposed Environmental Protection Agency (EPA) standard for carbon monoxide (CO) and unburned hydrocarbons (HC( under N7931208*# Pratt and Whitney Aircraft, East Hartford, Conn. sea level standard-day conditions. The engine did, however, meet Commercial Products Div. the proposed EPA standard for oxides of nitrogen (NOM under JT913-70/59 IMPROVED HIGH PRESSURE TURBINE the same sea level conditions. The results of engine testing ACTIVE CLEARANCE CONTROL SYSTEM under different ambient conditions )essentially sea level standard

670 N79-31217 day to sea level hot day) are also presented, and these results by stall at the positive setting angles and by choke at the show a trend toward higher levels of emissions Output for CO negative angles. At design the calculated static thrust along the and HC while producing slightly lower levels of NOX. J.M.S. operating line varied from 68 to 114 percent of that obtained at design-setting angle. Author N79-312125 # United Technologies Corp.. East Hartford, Conn. AERODYNAMIC AND ACOUSTIC INVESTIGATION OF N79-312155 # National Aeronautics and Space Administration. INVERTED VELOCITY PROFILE COANNULAR EXHAUST Langley Research Center, Hampton, Va. NOZZLE MODELS AND DEVELOPMENT OF AERODYNAMIC CONCEPTUAL STUDY OF A TURBOJET/RAMJET INLET AND ACOUSTIC PREDICTION PROCEDURES Final John P. Weidner Washington Sep. 1979 25 p refs Report (NASA-TM-80141 L-13036) Avail: NTIS HC A02/MF AOl Richard S. Larson, Douglas P. Nelson, and Bradley S. Stevens CSCL 21A Washington NASA Aug. 1979 223 p refs An inlet concept for separate turbojet and ramjet engines (Contract NAS3-2006 1) was defined and compared with an equivalent inlet for a (NASA-CR . 3 168: PWA-5550-8( Avail: NTIS wraparound turboramjet engine The comparison was made for HC A1O/MF AOl CSCL 21E a typical high altitude hypersonic cruise vehicle where the turbojet Five co-annular nozzle models, covering a systematic variation inlet capture area was required to be half as large as the ramjet of nozzle geometry, were tested statically over a range of exhaust inlet capture area at cruise. The use of a shorter nacelle having conditions including inverted velocity profile (IVP) (fan to primary substantially lower cooling requirements at cruise for the inlet stream velocity ratio > 1) and non IVP profiles. Fan nozzle pressure concept for separate turbojet and ramjet engines is suggested. ratio (FNPR) was varied from 1.3 to 4.1 at primary nozzle pressure The separate engine concept better isolates the turbojet from ratios (PNPR( of 1.53 and 2.0. Fan Stream temperatures of the ram(et, requires no special close off mechanisms within the 700 K (1260 deg RI and 1089 K(1960 deg RI were tested turbojet, and avoids the circumferential heat load imposed by a with primary stream temperatures of 700 K (1260 deg R), wraparound ramjet. A more variable geometry is required. 811 K (1460 deg R). and 1089 K (1960 deg R). At fan and A.W.H. primary stream velocities of 610 and 427 rn/sec (2000 and N79-31216# North Carolina State Univ. at Raleigh. Engineering 1400 ft/sec(. respectively, increasing fan radius ratio from 0.69 Design Center. to 0.83 reduced peak perceived noise level (PNL) 3 dB, and an AN ACTUATOR DISK ANALYSIS OF AN ISOLATED ROTOR increase in primary radius ratio from 0 to 0.81 (fan radius ratio WITH DISTORTED INFLOW Progress Report, Jan. 1976 - constant at 0.83) reduced peak PNL an additional 1.0 dB. Dec. 1978 There were no noise reductions at a tan stream velocity of John N. Perkins 31 Mar. 1979 31 p Prepared in cooperation 853 m/sec (2800 ft/sec(. Increasing fan radius ratio from 0.69 with United Technologies Research Center, E. Hartford. Conn. to 083 reduced nozzle thrust coefficient 1.2 to 1.5% at a PNPR IContract F44620-76-C-0055( of 1,53, and 1.7 to 2.0% at a PNPR of 2.0. The developed (AD-A069884: NCSU/EDC-74- 1) Avail: NTIS acoustic prediction procedure collapsed the existing data with HC A03/MF AOl CSCL 21/5 standard deviation varying from 4 or - 8 dB to + or - 7 dB. An analytical study of the passage of distorted flow through The aerodynamic performance prediction procedure collapsed an isolated, high hub-tip ratio axial compressor is reported. The thrust coefficient measurements to within 4- or - .004 at a analysis involves the coupling of the unsteady blade row FNPR of 40 and a PNPR of 2.0. Author aerodynamic response (with the flow immediately upstream of the blade row prescribed) with the unsteady duct flow both N7931213*# National Aeronautics and Space Administration. upstream and downstream of the blade row under the influence Lewis Research Center, Cleveland, Ohio. of the blade row loading. The numerical solution uses a starting AERODYNAMIC PERFORMANCE OF 1.38-PRESSURE- procedure which does not require the inlet plane to be far enough RATIO, VARIABLE-PITCH FAN STAGE upstream to be unaffected by the presence of the blade row. Royce D. Moore and Walter M. Osborn Sep. 1979 71 p Hence any experimentally determined distortion at any arbitrary (NASA-TP-1502: E-9700( Avail: NTIS HC A04/MF AOl CSCL distance upstream of the blade row can be modelled. The 21E results obtained indicate that the predicted pressure profile at The performance of a variable pitch fan stage tested over a the blade row exit is strongly dependent on the experimentally range of blade setting angles, speeds, and flows is presented. determined steady-state loss and exit;low angle curves, but is The fan was designed for a tip speed of 289.6 rn/sec and a almost independent of the magnitude of the first order lag flow of 29.6 kg/sec. The measured performance agreed reasonably coefficient used to represent the boundary layer time delay through well with the design point. The stall margin was only 5 percent. the blade passages. GRA Static thrust values along an operating line ranged from less than 15 to over 115 percent of that at design angle as the blade setting angle was varied from 25 degrees (closed) to N79-31217# RAND Corp., Santa Monica. Calif. -8 degrees (opened). The use of casing treatment increased the AIRCRAFT TURBINE ENGINE MONITORING EXPERIENCE: stall margin to 20.6 percent but decreased efficiency by IMPLICATIONS FOR THE F100 ENGINE DIAGNOSTIC 4 percentage points. A.W.H. SYSTEM PROGRAM Interim Report. 1977 - 1978 J. L. Birkler and J. R. Nelson Apr. 1979 45 p refs (Contract F49620-77-C-0023( N79.31214*# National Aeronautics and Space Administration. (AD-A069282: RAND/R-2391-AF) Avail: NTIS Lewis Research Center, Cleveland, Ohio. HC A03/MF AOl CSCL 20/5 AERODYNAMIC PERFORMANCE OF AXIAL-FLOW FAN This briefing report examines the experience gained from STAGE OPERATED AT NINE INLET GUIDE VANE AN- several aircraft turbine engine monitoring systems used over the GLES last decade and a half and the implications of that experience Royce D. Moore and Lonnie Reid Sep. 1979 43 p refs for a new monitoring system--the Engine Diagnostic System-- (NASA-TP-1510; E-9714( Avail: NTIS HC A03/MF AOl CSCL under development for the F100 engine on the F-15 and F-16 21E tactical fighter aircraft. The examination reveals that two different The overall performance of a fan stage with nine inlet guide approaches to engine monitoring have evolved in attempts to vane angle settings is presented. These data were obtained over achieve the goal of improved engine operations, maintenance, the stable flow range at speeds from 60 to 120 percent of and management while reducing support costs. The first design for vane setting angles from -25 to 42.5 degrees. At concentrates on short-term operations and maintenance aspects design speed and design inlet guide vane angle, the stage has and is usually accomplished by recording inflight data in a a peak efficiency of 0.892 at a pressure ratio of 1.322 and a snapshot mode, i.e.. a few seconds of data either at predefined flow of 25.31 kg/s. The stall margin based on peak efficiency performance windows or when certain engine operating limits and stall was 20 percent. Based on an operating line passing are exceeded. The second approach focuses on long-term through the peak efficiency point at the design setting angle, design-oriented benefits through improved knowledge of the the useful operating range of the stage at design speed is limited engine operating environment. To achieve the design-oriented

671 N79-31218

benefits, data must be recorded continuously on at least a few A compilation and an analysis of helicopter handling qualities aircraft at each operational location. GRA data are presented. Multiloop manual control methods are used to analyze the descriptive data, stability derivatives, and transfer functions for a six degrees of freedom, quasi static model. A N79-31218# Air Force Aero Propulsion Lab., Wright-Patterson compensatory loop structure is applied to coupled longitudinal, AFB, Ohio. lateral and directional equations in such a way that key handling AMBIENT CORRECTION FACTORS FOR AIRCRAFT GAS qualities features are examined directly. TURBINE IDLE EMISSIONS Technical Report, Jan. 1975 - A.W.H. Oct. 1978 N7931223*# National Aeronautics and Space Administration. William S. Blazowski and Joel W. Marzeski Mar. 1979 67 p Langley Research Center, Hampton, Va. refs Presented at the ASME Gas Turbine Conf., New Orleans, THEORETICAL AND EXPERIMENTAL INVESTIGATION OF Mar. 1976 GROUND-INDUCED EFFECTS FOR A LOW-ASPECT-RATIO (AF Proj. 3048) HIGHLY SWEPT ARROW-WING CONFIGURATION (AD-A069240; AFAPL-TR-79-201 9) Avail: NTIS HC A04/MF AOl CSCL 20/5 Paul L. Coe, Jr. and James L. Thomas Washington Sep. 1976 102 p refs Recent investigations have indicated that aircraft engine (NASA-TP-1508; L-13088) Avail: NTIS HC A06/MF AOl exhaust emissions are sensitive to ambient conditions. This paper CSCL O1C reports on combustor rig testing intended to evaluate variations An investigation was conducted in a V/STOL tunnel to due to ambient temperature and pressure with special emphasis determine the influence of ground proximity on the aerodynamic on idle engine operating conditions. Empirically determined Co. characteristics of a low-aspect-ratio highly swept arrow-wing C sub x. H sub y, and NO sub x correction factors--the ratio of configuration. The experimental results showed that as the height the pollutant emission index value obtained during standard day above the ground decreases, the configuration experiences operation to that resulting during actual ambient conditions--are substantial increases in lift and reductions in induced drag. presented. The effects of engine idle cycle pressure ratio, primary Although a significant percentage of these ground-induced zone fuel-air ratio, and fuel type were investigated. Ambient performance improvements are lost due to trim requirements, temperature variations were seen to cause substantial emission the net performance improvement remains quite favorable. The changes: correction factors in excess of 2.0 were determined in tests also showed that decreasing ground height results in a some cases. Ambient pressure variations were found to be less substantial increase in the horizontal-tail contribution to longitu- substantial. A previously published NO sub x emission model dinal stability. Comparison of the experimental results with and a simplified hydrocarbon combustion analysis are shown to results predicted by a planar vortex-lattice theoretical model shows be in general agreement with the empirical results. GRA that the theoretical model provides a good estimate of the N79-31 220*# National Aeronautics and Space Administration. ground-induced effect on lift, drag, and longitudinal stability for Hugh L. Dryden Flight Research Center, Edwards, Calif. the wing-body combination. However, the theoretical model does ANALYSIS OF A LATERAL PILOT-INDUCED OSCILLATION not adequately predict either the zero lift pitching moment or EXPERIENCED ON THE FIRST FLIGHT OF THE YF-16 the horizontal-tail downwash characteristics. Author AIRCRAFT John W. Smith Sep. 1979 53 p refs N79-31224# Air Force Inst. of Tech., Wright-Patterson AFB, )NASA-TM-72867) Avail: NTIS HC A04/MF AOl CSCL Ohio. School of Engineering. 01C THE DESIGN OF DIGITAL CONTROLLERS FOR THE In order to compare and assess potential improvements. two C-141 AIRCRAFT USING ENTIRE EIGENSTRUCTURE control systems were modeled: the original first flight or prototype ASSIGNMENT AND THE DEVELOPMENT OF AN INTERAC- aircraft system, and a modification of the prototype system, which TIVE COMPUTER DESIGN PROGRAM M.S. Thesis essentially reduced the overall gain for the takeoff and landing Thomas A. Kennedy Mar. 1979 194 p refs phase. In general, the overall system gain reduction of the modified (AD-A069192; AFIT/GGC/EE/79- 1) Avail: NTIS flight control system was sufficient to avoid lateral pilot-induced HC A09/MF AOl CSCL 01/2 oscillation tendencies. Lowering the system gain reduced the In this report, a deadbeat tracker and regulator are developed tendency to rate saturate, which resulted in correspondingly higher for the C-141 aircraft for three different flight conditions using critical pilot gains for the same control input. Author the method of entire eigenstructure assignment. A heuristic iterative method is presented for determining an 'optimal' sampling N7931221*# Honeywell Systems and Research Center, time for deadbeat controllers by using the controllability matrix. Minneapolis, Minn. In order to perform the above designs and to evaluate them HELICOPTER HIGH GRAIN CONTROL Final Report through a continuous-time simulation, a computer aided design Thomas B. Cunningham and Edwin C. Nunn Jul. 1979 171 p program is developed. This program allows the complete design refs and simulation of regulator, tracker, and disturbance rejection )Contract NAS1-14789) control systems with full-order observers. In addition, the program (NASA-CR- 159052: HON EYWELL-79SRC33) Avail. NTIS permits complete state-space analysis of the system being HC A08/MF AOl CSCL O1C designed, including both discrete and continuous-time responses. High gain control is explored through a design study of the A user's manual and programmer's guide are provided for further CH-478 helicopter. The plans are designed to obtain the maximum development of the program. GRA bandwidth possible given the hardware constraints. Controls are designed with modal control theory to specific bandwidths and N79-31225# Air Force Inst. of Tech.. Wright-Patterson AFB, closed loop mode shapes. Comparisons are made to an earlier Ohio. School of Engineering. complementary filter approach. Bandwidth improvement by INVESTIGATION OF INVERSE VANDERMONDE MATRIX removal of limitations is explored in order to establish hardware CALCULATION FOR LINEAR SYSTEM APPLICATIONS and mechanization options. Improvements in the pitch axis control M.S. Thesis system and in the rate gyro sensor noise characteristics in all Donald Paul Seyler Mar. 1979 178 p refs axes are discussed The use of rotor state feedback is assessed. (AD'A069241: AFIT/GGC/EE/79-2) Avail: NTIS A.W.H. HC A09/MF AOl CSCL 12/1 Efficient inversion of a 2n x 2n Vandermonde matrix is a N7931222*# Systems Technology, Inc.. Mountain View. Calif key requirement of a new algorithm developed for parameter A COMPILATION AND ANALYSIS OF HELICOPTER identification in linear time-invariant systems. It has features very HANDLING QUALITIES DATA. VOLUME 2: DATA desirable for application to large systems with many unknown ANALYSIS parameters, such as adaptive flight control systems. A generalized Robert K. Heffley Aug. 1979 176 p refs algorithm for inverting the Vandermonde matrix was proposed. (Contract NAS2-9344) It was chosen for study because its Structure parallels that of )NASA-CR-3 145: TR- 1 087-2-Vol-2) Avail: NTIS the first algorithm. The algorithm was coded into a computer NC A09/MF AOl CSCL 01C subroutine called 'VANINV'. and 43 eigensystems were used to

672 N79-31233 test its computational accuracy and efficiency. Four potential N79-31229# Deutsche Forschungs- und Versuchsanstalt fuer problem areas tested were: large system orders, eigenvalues near Luft- und Raumfahrt, Goettingen (West Germany(. each other, eigenvalues near zero, and eigenvalues with large CONTRIBUTIONS TO EXPERIMENTAL FLUID MECHANICS magnitude differences. For a comparison, the Vandermonde matrix EBEITRAGE ZUR EXPERIMENTELLEN STROMUNGSMEC- for each system was also inverted using routines from the HANIK] International Mathematical and Statistical Library (IMSL). Test 1977 216 p refs In GERMAN results indicated that VANINV is not quite as fast or as accurate Avail: NTIS HC A10/MF AOl as the IMSL routines. However, the tests were limited to systems Various aspects of the reconstruction of aerodynamics testing with real distinct eigenvalues because the IMSL routines cannot facilities in West Germany following World War 2 are described handle other types. VANINV in its present form can handle systems in this festschrift honoring Dr. Hubert Ludwieg. His contributions having any combination of complex and/or repeated elgenvalues. in the development of the high-speed wind tunnel, the lm x Therefore, recommendations for further research and several 1 m wind tunnel, and the transonic turbine nozzle are stressed. possible means of improving VANINV are outlined. GRA Experiments in spiral flow stability and the application of heated surface elements (films( to measure shear stress on the wall in the three dimensional boundary layer are also discussed. A N79-31226# Honeywell, Inc.. St. Louis Park, Minn. Avionics biography of the scientist a. I a list of his scientific publications Div. is included. A.R.H. PROGRAM FOR THE CRITICAL COMPONENTS OF A FLY-BY-TUBE BACKUP FLIGHT CONTROL SYSTEM. N79-31230# National Aeronautics and Space Administration, PART 1 Final Report. 1 Jan. - 15 Dec. 1978 Washington, D. C. Walter M. Posiogies 15 Jan. 1979 121 p WIND TUNNELS WITH ADAPTED WALLS FOR REDUCING (Contract N62269-78-C-0003( WALL INTERFERENCE (AD-A070387: W0471-FR1-Pt-1: NADC-77197-60-Pt-1( Avail: U. Ganzer Aug. 1979 14 p refs Transl. into ENGLISH of Z. NTIS HC A06/MF AOl CSCL 01/3 fur Flugwissenchaften und Weltraumforschung (West Germany). This report presents the results of a program to develop v 3. no. 2, 1979 p 129-133 Transl. by Kanner (Leo( Associates. two of the critical components in an advanced fluidic backup Redwood City, Calif. Original doc. prep. by Aero-Space Inst. of primary flight control system defined as the fly-by-tube concept. Berlin (West Germany( Components developed include an input transducer, which (Contract NASw-3199( converts pilot commands into hydraulic differential pressure (NASA-TM-75501( Avail: NTIS HC A02/MF AOl CSCL signals, and fluidic resistor networks that sum these hydraulic 148 signals together to provide the required servoactuator commands. The basic principle of adaptable wind tunnel walls is Results show that this concept which uses signal levels up to explained. First results of an investigation carried Out at the 400 PSID is accurate, linear, quiet, simple, low cost, relatively Aero-Space Institute of Berlin Technical University are presented insensitive to changes in fluid viscosity, and has a stable null for two dimensional flexible walls and a NACA 0012 airfoil. with adequate response. GRA With five examples exhibiting very different flow conditions it is demonstrated that it is possible to reduce wall interference and N79-31227# Systems Control, Inc., Palo Alto, Calif. to avoid blockage at transonic speeds by wall adaptation. Author PATH CONTROLLERS: UNIFICATION OF CONCEPTS AND COMPARISON OF DESIGN METHODS Final Technical Report, Sep. 1977 - Sep. 1978 N79-31231# Federal Aviation Administration, Washington, D. C. J. E. Jones and J. S. Karmarkar Dec. 1978 123 p refs POTENTIAL CLOSURE OF AIRPORTS (Contract F33615-77-C-3079: AF Proj. 2403( Jan. 1978 40 p (AD-A070252: AFFDL-TR-78- 178) Avail: NTIS Avail: NTIS HC A03/MF AOl HC A06/MF AOl CSCL 01/3 Airports which are expected to be converted to nonaviation This report documents the basic theme of a series of seminars use are identified and measures are suggested to forstall this in presented to the Air Force Flight Dynamics Laboratory concerning cases where the airports involved could help meet transportation the role of modern control theory in advanced aircraft guidance and community objectives. The problems cited for the closings and control concepts. The report discusses a number of optimal are high property taxes. and the high cost of capital improvements guidance and control concepts as cast in a path-control formal and airfield maintenance. Measures examined to aid airports are structure. Trajectory generation concepts include horizontal tax exemptions, zoning and land use controls, and financial aid guidance with and without controlled time of arrival, threat to assist airport development and maintenance. A.W.H. avoidance, performance optimization, and terrain following. Control concepts include linear optimal control and classical techniques. Research areas of high potential payoff are identified. GRA N79-31232# Federal Aviation Administration, Washington, D. C. ADVISORY CIRCULAR. THE PLANNING GRANT PROGRAM FOR AIRPORTS 31 Jan. 1979 75 p N7931228* National Aeronautics and Space Administration. (AC150/5900-1B( Avail: NTIS HC A05/MF AOl Langley Research Center, Hampton, Va. The process for applying for grants to prepare airport system SEAT CUSHION TO PROVIDE REALISTIC ACCELERATION plans and airport master plans is dcribed as well as the CUES TO AIRCRAFT SIMULATOR PILOT Patent administrative procedures to be followed in performing planning Billy R. Ashworth. inventor (to NASA) Issued 14 Aug. 1979 projects. R.E.S. 10 p Filed 26 Jul. 1978 Supersedes N78-30821 (16 - 21 p 2857) Continuation-in-part of abandoned US Patent AppI. N79-31233# Naval Air Engineering Center, Lakehurst, N.J. SN-829314, filed 31 Aug. 1977 SURVEYS OF GROOVES IN 19 BITUMINOUS RUNWAYS (NASA. Case-LAR-12149-2, US-Patent-4,164-079: Final Report US-Patent-Appl-SN-8293 14: US-Patent-Appl-SN-928 131: Richard Melone Mar. 1979 60 p refs US-Patent-Class-35-12E; US-Patent-Class-35-12 H) Avail: US (Contract FA74WAI .423: FAA Proj. 082-431-02) Patent and Trademark Office CSCL 148 (AD-A069889: FAA-RD-79-28; NAEC'TD-Misc-R8( Avail. Seat cushions, each including an air cell with a non- NTIS HG A04/MF AOl CSCL 01/5 compressible surface, are disclosed. The apparatus are p,:ovided The extent and frequency of problems, such as chipping, for initially controlling the air pressure in the air cells to allow cracking, rounding, wearing, distorting, and contaminating of the the two main support areas of the simulator pilot to touch the runway grooves were determined A total of ten different problem non-compressible surface and thus begin to compress the flesh areas was identified during the survey with wear, running together near these areas During a simulated flight the apparatus control (closing(, and rubber deposits being the most serious of the ten. the air pressure in the cells to simulate the events that occur in In general, the grooves were in satisfactory condition and did a seat cushion during actual flight. Author not result in abnormal deterioration of runway surfaces. Three

673 N79-31234

of the 19 runways surveyed appeared in need of resurfacing N79-31237# National Bureau of Standards, Washington, D. C. and/or regrooving. Groove depths averaged less than the required Fluid Engineering Div. 1/4 inch, while groove width and pitch measured close to A LOW-VELOCITY AIRFLOW CALIBRATION AND RE- specified dimensions. M.M.M. SEARCH FACILITY Final Technical Note L. P. Purtell and F. S. Klebanoff Mar. 1979 26 p refs N79-31234# Mitre Corp., McLean. Va. METREK Div. (Contract Dl-BM-H0-133024) RUNWAY CONFIGURATION MANAGEMENT SYSTEM (PB-294501/2; NBS-TN-989) Avail; NTIS HC A03/MF AOl CONCEPTS Final Report CSCL 14B A. N. Sinha and R. L. Fain May 1979 20 p refs A low velocity airflow facility suitable for the calibration of (Contract DOT-FA79WA-4 184) wind speed measuring instruments and research in aerodynamics (AD-A069960; MP-79W0001 8) Avail; NTIS is described. The flow facility is of the open return type with a HC A02/MF AOl CSCL 01/5 test section 20 feet long, and nominally 3 x 3 feet in cross Airport congestion is a problem at the busy airports in the section. Special attention was given to obtaining an air stream U. S. today. Even under moderate growth projections, the problem with a high degree of spatial uniformity and low turbulence of increasing delays will worsen at these busy airports, and will with excellent speed control over the range from 10 to 3300 feet spread to other airports which would approach saturation per minute. Laser-optical methods with appropriate signal conditions. While long term relief to the congestion problem processing electronics were employed to establish a primary would be provided by technological improvements, it is essential standard for the measurement of very low velocities. Detailed to fully and efficiently utilize the existing facilities to avoid performance characteristics of flow facility and the laser velocity excessive delays in the near term. This paper addresses the standard are presented. GRA problem of selecting optimal runway configurations to minimize delays through the use of a Runway Configuration Management System. Three concepts of this system are developed to represent N7931354*// Boeing Commercial Airplane Co.. Seattle, Wash the full range of static and dynamic configuration selection DEVELOPMENT OF AIRCRAFT LAVATORY COMPART- processes. The basic model, representing the first level concept, MENTS WITH IMPROVED FIRE RESISTANCE CHARACTER- has been developed for Chicago O'Hare International Airport. ISTICS. PHASE 2: SANDWICH PANEL RESIN SYSTEM The applicaton of the model at O'Hare and its possible extensions DEVELOPMENT Final Report are also discussed. GRA R. A. Anderson, D. B. Arnold, and G. A. Johnson 1979 284 p refs (Contract NA52-8700( N79-31235# Decision Science, Inc.. San Diego, Calif. (NASA. CR- 152120; D6-46839( Avail; NTIS TACTICAL PERFORMANCE CHARACTERIZATION BASIC HC A13/MF AOl CSCL liD METHODOLOGY Final Report, Dec. 1977 - Sep. 1978 A NASA-funded program is described which aims to develop Michael J. Walsh, George H. Burgin. and Lawrence J. Fogel a resin system for use in the construction of lavatory wall panels, May 1979 65 p refs sidewall panels, and ceiling panels possessing flammability, smoke (Contract F33615-78-C-001 1) and gas emission, and toxicity (FS&T( characteristics superior to )AD-A069297; AFHRL-TR-78-94( Avail; NTIS the existing epoxy resin. Candidate resins studied were phenolic, HC A04/MF AOl CSCL 05/9 polyimide, and bismaleimide. Based on the results of a series of This effort is to develop new methods of characterizing FS&T as well as mechanical and aesthetic property tests, a important features of tactical performance for display at an phenolic resin was chosen as the superior material. Material instructor/operator station of a flight simulator. In particular, the and process specifications covering the phenolic resin based work included developing a technique for computing the weight materials were prepared and a method of rating sandwich panel or importance that a pilot assigns to various performance criteria. performance was developed. A. R. H. The work documented here represents the first of a two-phase program. Phase 1 involved developing the basic techniques and methods without collecting extensive pilot data. Phase 2 involves N79-31357# Naval Weapons Center, China Lake, Calif. applying the methods to real pilot data collected on the Simulator THERMAL CHARACTERISTICS OF 3501 . 6/AS AND for Air-to-Air Combat. The approach was based upon a previously 5208/1300 GRAPHITE EPDXY COMPOSITES Research developed Adaptive Maneuvering Logic (AML( program. This Report. Feb. - Sep. 1978 program operates one-on-one against a real opponent to provide Robert F Kubin May 1979 24 p practice in combat flying. It operates by computing a 'score' for (AD-A071067; NWC-TP.6 104) Avail; NTIS each of several alternative next-moves and then executing the HC A02/MF AOl CSCL 11/4 move rated highest. The score consists of a sum of weights The thermal characteristics of two graphite epoxy composites assigned to each of the various criteria that would be satisfied for use as aircraft structural components have been investigated. if the move in question were chosen. The weights are fixed in The activation energies and heats of reaction for pyrolysis of the AM L program. Thus, the program uses a fixed set of the composites were found to be 19.7 kcal/mole and . 18.4 cal/g weights to produce a simulated performance. for 3501-6/AS and 25.0 kcal/mole and -20.4 cal/g for GRA 5208/T300, respectively. The kinetic parameters enable prediction of thermal degradation at flight temperatures. In fire fighting, bulk material temperatures must be reduced well below 300 C N79-31236# General Electric Co.. Daytona Beach, Fla. Ground to prevent continuation of exothermic pyrolysis reactions. It was Systems Dept. also found that differential scanning calorimetry provides a more LABORATORY DEVELOPMENT OF COMPUTER GENER- sensitive test of composite cure than reflectance infrared ATED IMAGE DISPLAYS FOR EVALUATION IN TERRAIN measurements. GRA FLIGHT TRAINING Final Report Roland F. Pester 21 Feb. 1979 22 p refs (Contract DAHC1 9-77-C-0006; DA Proj. 2Q7-63743-A-772( N79-31461# (AD-A070065; ARI-RN-79-8) Avail; NTIS HC A02/MF AOl Carleton Univ., Ottawa (Ontario). Dept. of Systems CSCL 05/9 Engineering and Computing Science. A NOVEL APPROACH TO THE DESIGN OF AN ALL DIGITAL This report describes the formulation of a digital data base AERONAUTICAL SATELLITE COMMUNICATION SYSTEM and the equipment utilized to display computer generated images M. E. Ulug In AGARD Digital Commun. in Avionics Jun. of the resultant terrain scenes. Real time and nonreal time 1979 16p refs equipment equipment is described. Necessary input data for Avail; NTIS HC A20/MF AOl CSCL 17B formulation of digital data bases is delineated. Resulting scene data is to be utilized as stimulus material for evaluation of CGI The design of an all digital aeronautical satellite communica- systems to determine their effectiveness as a medium for training tion system based on the transparent intelligent network (TI-NET) navigators and pilots. is described. The novel features of the system, namely a 9.6 kb/s Author (GRA( ground to aircraft link which provides a TDMA operation and

674 N79-31482 the statistical multiplexing of the encoded voice and data were were based on known characteristics of some helicopter-installed experimentally tried Out using 12-14 GHz satellite link between systems and classical treatment of multipath radio wave Carleton University. in Ottawa. Canada and the NASA AMES propagation over a smooth sea. The probability of achieving a Research Center in Palo Alto. California using Hermes (CTS) particular grade of service was considered as the arithmetical satellite. Other unique features of the system are the trading off product of several independent statistical parameters. Some of of the satellite up-down delay with the packet formation delay, these were related to the temporal and spatial variability of multi-polling and multiaddressing capability, and the complete radio wave propagation; others reflected the almost random transparency to the user's protocol. In addition, the system has orientation of the aircraft under operational conditions affecting a turn around time of 22.5 ms. which is most useful in making the signal received via the aircraft's radiation pattern. A method quick changes in the polling sequence, as well as producing of statistical analysis based on approximate Gaussian frequency fast re-transmissions. A polling algorithm which meets the distribution functions was applied to the experimental data. particular needs of the aircraft in high, medium, and low density Performance predictions are presented in terms of time availability areas is described. The terrestrial network connecting the for selected bit error rates. communication centers and ground stations in North America is R.E.S also discussed and its associated interfaces and protocols are 'N79-31478# Technische Universitaet, Brunswick (West defined. It is believed that the proposed system will result in a Germany). more efficient use of the communication channels, greater MULTIPATH PROPAGATION MEASUREMENT BY DOPPLER immunity against noise, and a less complex airborn computer TECHNIQUE with smaller memory. Although the system design is based on P. Form, R. Springer, H. Bothe. and K. Klein In AGARD Digital a set of hypothetical traffic data, the model can be readily modified Commun. in Avionics Jun. 1979 23 p refs Prepared in to perform at a higher or lower traffic level. In this connection cooperation with DFVLR, Brunswick another system using a 4.8 kb/s ground-aircraft link is described and its performance compared with that of the proposed model. Avail: NTIS HC A20/MF AOl J.M.S. Some microwave landing system features are discussed with respect to multipath propagation. For illustration of specific multipath effects, a Doppler-shift measurement technique with N79-31463# Eurocontrol Agency. Maastricht (Netherlands). high angle resolution is presented, which needs simple antennas A DIGITAL COMMUNICATION SYSTEM AS GATEWAY and equipment and offers easy interpretation. BETWEEN ADJACENT COMPUTERIZED AIR TRAFFIC M.M.M. CONTROL CENTRES N79-31480# Technische Universitaet, Brunswick (West M. Baum In AGARD Digital Commun. in Avionics Jun. 1979 Germany). Inst. fuer Nachrichtentechnik. 14 p refs INVESTIGATION ON INFORMATION ERROR CAUSED BY Avail: NTIS HC A20/MF AOl TRAFFIC LOADING IN APPROACH AND LANDING A practical approach to improve data communication between SYSTEMS adjacent computerized air traffic control centers is described. Wolfgang Skupin In AGARD Digital Commun. in Avionics The applied concept is communication procedure conversion by Jun. 1979 15 p which systems with incompatible transmission procedures can Avail: NTIS HC A20/MF AOl communicate with each other via a gateway system. Procedure For the evaluation of a required approach and landing systems conversion meets the basic requirement which is not to intervene with statistical interrogation ALSSI serving capacity, a traffic in the functioning of the involved local networks and not to model was developed. This model is based on the operational require modifications of locally used procedure envelopes. The requirements and gives a defined standard traffic volume for a transit function is realized by conversion of the procedure specific ALSSI. For investigating the reply efficiency and the accuracy message type and priority on one hand and of address information of an ALSSI several methods can be employed. By means of on the other hand. A flexible table mechanism is chosen instead probability calculations the reply efficiency can be determined of fixed coding. Outstanding problems are an efficient link with comparatively low expense. For the determination of the failure processing and an envisaged attachment of a circuit accuracy it is useful to carry Out real world system tests with a switching function to the message switching principle. J.MS. test a/c. Because of less expense the traffic load is simulated with these tests by pulse generators. More flexibility can be achieved by employing a software simulation. For this a computer N79-31468# Standard Elektrik Lorenz AG.. Stuttgart (West model of the traffic loading has to be installed as well as a Germany). computer model of the system to be investigated. Some results AN ASYNCHRONOUS DATA TRANSMISSION SYSTEM achieved by employing these methods are presented. M.M.M. WITH LOW ERROR PROBABILITY FOR THE SETAC LANDING AID N79-31481# Rome Air Development Center, Griffiss AFB, N.Y. Wolfgang Beier In AGARD Digital Commun. in Avionics Jun. NEW DEVICES FOR DIGITAL COMMUNICATIONS IN 1979 5p AVIONICS Avail: NTIS HC A20/MF AOl F. I. Diamond, H. J. Bush, and J. A. Graniero In AGARD A serial code which is used in the TACAN compatible landing Digital Commun. in Avionics Jun. 1979 9 p refs aid SETAC is described. Its features are optimized for the expected error rate and types of errors as well as for the data transmission Avail: NTIS HC A20/MF AOl rate and the accepted error rate after correction. Technological advances in microelectronics to improve R.E.S. capabilities and reduce complexity of digital communication systems in the aircraft industry are assessed. M.M.M.

N79-31476# Royal Aircraft Establishment. Farnborough N79-31482# California Univ., San Diego. La Jolla. (England). Radio and Navigation Dept. TRANSFORM DOMAIN PROCESSING FOR DIGITAL PERFORMANCE PREDICTIONS AND TRIALS OF A COMMUNICATION SYSTEMS USING SURFACE ACOUSTIC HELICOPTER UHF DATA LINK WAVE DEVICES R. M. Harris In AGARD Digital Commun. in Avionics Jun. L. B. Milstein, D. R. Arsenault, and P. Des In AGARD Digital 1979 17 p refr, Commun. in Avionics Jun. 1979 16 p refs Prepared in Avail: NTIS HC A20/MF AOl cooperation with Rensselaer Polytech. Inst. A combination of theoretical and experimental studies Avail: NTIS HC A20/MF AOl conducted in order to estimate the bit error rate performance of A surface acoustic wave receiver is presented. This device a digital communication system are reviewed. The system is is light and small enough to be used on board aircraft and can proposed for the transmission of binary digital data over dedicated receive continuous time-digital signals accurately and securely. simplex UHF radio links between helicopters, and between The detection of digital signals in the presence of Gaussian helicopters and ships. Initial predictions of system performance noise and interference using this device is studied. M.M.M.

675 N79-31487

N79-31487# Rensselaer Polytechnic Inst., Troy, N. Y. Electrical layers, laminar suction wings, heat transfer and boundary layer and Systems Engineering. transition, and Reynolds number effects are covered. STATE OF THE ART IN DIGITAL SIGNAL PROCESSING WITH APPLICATIONS TO MULTIPLE ACCESS SYSTEMS Lester A. Gerhardt In AGARD Digital Commun. in Avionics Jun. 1979 9 p refs N79-31 533*# Douglas Aircraft Co.. Inc.. Long Beach, Calif. A NEW APPROACH TO THE SOLUTION OF LARGE, FULL Avail: NTIS HC A20/MF AOl MATRIX EQUATIONS: A TWO-DIMENSIONAL POTENTIAL Advanced developments and trends in the fields of digital FLOW FEASIBILITY STUDY Final Report signal processing and digital communications were reported. The R. M. James and R. W. Clark Washington NASA Sep. 1979 effects of microprocessors and minicomputers in this development 83 p refs were addressed. The availability of new devices, device technology, (Contract NAS1-14892( and directions are summarized with respect to the emphasis on (NASA-CR-3173( Avail: NTIS HC A05/MF AOl CSCL 20D speed. A discussion of CDM. CDMA. SSMA. and TDMA was An approach to the solution of matrix problems resulting reported. The Joint Tactical Information Distribution System from integral equations of mathematical physics is presented. was described as a system concept. M.M.M. Based on the inherent smoothness in such equations, the problem is reformulated using a set of orthogonal basis vectors, leading to an equivalent coefficient problem which can be of lower order N79-31491# Mitre Corp.. Bedford, Mass. without significantly impairing the accuracy of the solution. This IMPLEMENTING JTIDS IN TACTICAL AIRCRAFT approach was evaluated using a two-dimensional Neumann David R. McMillan In AGARD Digital Commun. in Avionics problem describing the inviscid. incompressible flow over an airfoil. Jun. 1979 13 p Two different kinds of mode functions were investigated, namely Avail: NTIS I-IC A20/MF AOl eigenfunction series and Fourier series. The method using Fourier The implementation of a high capacity, secure, jam-resistant series was found preferable. It uses all of the coefficients from time division multiple access information system for providing a Fast Fourier Transform algorithm in an approximate method integrated communications, navigation, and identification capabili- which exploits the known structure of the transformed coefficient ties is discussed. Major characteristics of the joint tactical matrix and very promising results for the flow over a realistic information distribution system (JTIDSI in tactical aircraft are airfoil are obtained. On the basis of the results presented here, summarized and relevant elements of the JTIDS program plan an order of magnitude reduction in this computer time can be are highlighted. The context for specific requirements to be expected for such problems as compared with the time for a satisfied with aircraft installations are established in terms of direct matrix solution. M.M.M. operational functions, sources and sinks of information which support those functions, and current information distribution systems and man-machine interfaces which mechanize the transfer to and from tactical aircraft and their crews. The relative benefit N79-31624# Boeing Commercial Airplane Co., Seattle, Wash. of JTIDS over present solutions to operational information needs ATLAS, AN INTEGRATED STRUCTURAL ANALYSIS AND is established in this context. An overview of key elements of DESIGN SYSTEM. VOLUME 5: SYSTEM DEMONSTRATION the tactical aircraft implementation challenge is included. A.R.H. PROBLEMS R. A. Samuel, ed. Jul. 1979 271 p refs (Contracts NAS1 -12911; DAAG46-75-C-0072( N79-31524# Deutsche Forschungs- und Versuchsanstalt fuer (NASA-CR- 159045; D6-25400-0005-Vol-5( Avail: NTIS Luft- und Raumfahrt, Goettingen (West Germany). HC Al2/MF AOl CSCL 20K CONTRIBUTIONS TO FLUID MECHANICS IBEITRAEGE One of a series of documents describing the ATLAS System ZUR STREMUNGSMECHANIK] for structural analysis and design is presented. A set of problems 1978 184 p refs In GERMAN is described that demonstrate the various analysis and design Avail: NTIS I-IC A09/MF AOl capabilities of the ATLAS System proper as well as capabilities Ten articles are presented which cover a wide spectrum of available by means of interfaces with other computer programs. research in the field of theoretical and experimental fluid Input data and results for each demonstration problem are mechanics. The titles of the articles are: (1) Development of discussed. Results are compared to theoretical solutions or Data Acquistition and Processing Systems for a 3 mm Wind experimental data where possible. Listings of all input data are Tunnel; 121 Airfoil Lift in Compressible Subsonic Flow with included. G.Y. Separation; 131 Sound Generation in an Induction Motor Fan; 141 The Hypersonic Vacuum Tunnel; (5) Remarks on a Hydraulic Ram; 161 Experimental and Theoretical Pressure Distribution on N7931628*# Rockwell International Corp.. bowney, Calif. the Ellipsoid of Revolution; 171 Theoretical Study of the Effect ACTIVELY COOLED PLATE FIN SANDWICH STRUCTURAL of the Pressure Fluctuation Component in Three Dimensional PANELS FOR HYPERSONIC AIRCRAFT Final Report Turbulent Boundary Layers; 181 Variations of a Parallel Flow L. M. Smith and C. S. Beuyukian Washington NASA Aug. Along a Flat Plate Due to a Normally Directed Free Jet; 191 Effects 1979 172 p refs of Solid Boundary Surface in a Flow about a Profile with (Contract NAS1-13382( Separation; and 1101 Introduction to the Electronic Data Processing (NASA-CR-3 159; SD-78-AP-0074( Avail: NTIS to Improve Cataloging in the Library of the Aerodynamic Testing HC A08/1VIF AOl CSCLO1C Facilities in Goettingen. G.Y. An unshielded actively cooled structural panel was designed for application to a hypersonic aircraft. The design was an all aluminum stringer-stiffened platefin sandwich structure which used N79-31530# Von Karman Inst. for Fluid Dynamics. Rhode-Saint- a 60/40 mixture of ethylene glycol/water as the coolant. Eight Genese (Belgium). small test specimens of the basic platefin sandwich concept MECHANICS OF BOUNDARY LAYER TRANSITION, and three fatigue specimens from critical areas of the panel PART 2: INSTABILITY AND TRANSITION TO TURBU- design was fabricated and tested (at room temperature). A test LENCE panel representative of all features of the panel design was Mark V. Morkovin (Martin Co., Baltimore, Md.( Feb. 1968 febricated and tested to determine the combined thermal/ 176 p refs Lecture held at Rhode-Saint-Genese, Belgium mechanical performance and structural integrity of the system. 3 Vol. The overall findings are that; (11 the stringer-stiffened platefin (VKI -Lecture -Series-3-Pt-2( Avail: NTIS HC A09/1VIF AOl sandwich actively cooling concept results in a low mass design Instability and transition from laminar to turbulent shear layers that is an excellent contender for application to a hypersonic is discussed. Topics include advances in understanding the vehicle, and (2) the fabrication processes are state of the art transition and contradictions in transition research. Transition but new or modified facilities are required to support full scale correlations for hypersonic wakes, three dimensional boundary panel fabrication. R.E.S.

676 N79-32054

N79-31681# Consiglio Nazionale delle Rcerche. Rome (Italy). Servizio Attivita Spaziali. TRANSATLANTIC FLIGHTS OF STRATOSPHERIC BAL- LOONS lIES VOLS TRANSATLANTIQUES DES BALLONS STRATOSP HE R IOU E SI G. P. Cecchini and M. Malavasi In ESA European Sounding Rocket, Balloon and Related Res.. with Emphasis on Expt. at High Latitudes Jun. 1978 p 377-381 In FRENCH; ENGLISH summary Avail: NTIS HC A23/MF AOl The use of high altitude balloons as Spacelab complementary low cost research tools is discussed. The economic factors are reviewed and the payload capacity is analyzed, showing that a weight of 1500 kg at a height equivalent to 1.5 millibar is typical of Spacelab conditions. The Milo launching facility (Italy) is described. It is concluded that balloon flights are well suited for pretesting Spacelab payloads. Author (ESA)

N79-31691# Centre National d'Etudes Spatiales. Toulouse (France). PREVISIONS AND EXPERIMENTAL RESULTS IN OPEN BALLOON CONTROLLED DESCENT [PREVISION ET DEPOUILLEMENTS DE VOLS DE BALLONS OUVERTS EN DESCENTE PILOTE] M. Romero, M. Rougeron. and C. Tockert In ESA European Sounding Rocket, Balloon and Related Res.. with Emphasis on Expt. at High Latitudes Jun. 1978 p 397-402 refs In FRENCH

Avail. NTIS HC A23/MF AOl Balloon flight remote control by means of a pole located relief valve and ballast reduction is discussed. A computerized simulation was performed and four balloon flights were executed in 1977. Results show that the proposed flight control method permits a controlled descent or a leveling-off in a simple manner. Author )ESA)

N79-32054# Boeing Vertol Co.. Philadelphia. Pa. STUDY OF DESIGN CONSTRAINTS ON HELICOPTER NOISE Harry Sternfeld. Jr. and Carl W. Wiedersum Jul. 1979 91 p refs (Contract NAS1-15226) (NASA-CR-159118) Avail: NTIS HC A05/MF AOl CSCL 20A A means of estimating the noise generated by a helicopter main rotor using information which is generally available during the preliminary design phase of aircraft development is presented. The method utilizes design charts and tables which do not require an understanding of acoustical theory or computational procedures in order to predict the perceived noise level, a weighted Sound pressure level, or C weighted sound pressure level of a single hovering rotor. A method for estimating the effective perceived noise level in forward flight is also included. In order to give the designer an assessment of the relative rotor performance, which may be traded off against noise, an additional chart for estimating the percent of available rotor thrust which must be expended in lifting the rotor and drive system, is included as well as approach for comparing the subjective acceptability of various rotors once the absolute sound pressure levels are predicted. A.R.H.

677 SUBJECT INDEX AERONAUTICAL ENGI NEERING / A Continuing Bibliography (Suppl. 116) DECEMBER 1979 Typical Subject Index Listing

SUBJECT TITLE::]^ EXTENSION AERODYNAMIC LOADS _____F'" rSupersonic unstalled flutter --- aerodynamic ADHESIVES loading of thin airfoils induced by cascade motion The influence of the environment on the I(NASA-TM-79001] N79-11000 elastoplastic properties of adhesives in metal bonded joints --- In aircraft structures [ESA-TT-521] N79-30391 AERIAL RECONNAISSANCE REPORT SiOIJ Tactical electronic reconnaissance sensor _[H] NUMBER F^.U radar emission detection J A79-48717 AEROACOUSTICS Experimental investigation of helicopter flight The title is used to provide a description of the subject matter. When the title is modes on helicopter-generated noise insufficiently descriptive of the document content, a title extension is added. A79-47873 The aeroacoustics of advanced turbopropellers separated from the title by three hyphens. The NASA or AIAA accession number A79-50236 5 included in each entry to assist the user in locating the abstract in the abstract Evaluation of F-ill weapon bay aero-acoustic and section of this supplement. If applicable, a report number is also included as an weapon separation improvement techniques aid in identifying the document [AD-A070253] 1479-31203 Aerodynamic and acoustic investigation of inverted velocity profile coannular exhaust nozzle models and development of aerodynamic and acoustic prediction procedures [NASA-CR-3168] 579-31212 A AERODYNARICBALANCE A-300 AIRCRAFT Helicopter performance methodology at Bell A comparison of predictions obtained from wind Helicopter Textron tunnel tests and the results from cruising [ABS 79-2] A79-I49055 flight: Airbus and Concorde --- conferences AERODYNAMIC CHARACTERISTICS [NASA-TN-75238] N79-31136 Surface-effect components of aerodynamic ABERRATION characteristics of air-cushion vehicle with ram Recent advances in radoute design pressurization A79-49574 A79-46995 ACCIDENT INVESTIGATION Analytic formulas for wing profile aerodynamic Special investigation report: wing failure of characteristics in incompressible flow Boeing 747-131 near Madrid, Spain, 9 May 1976 A79-47000 [NTSB-AAR-78-12] 579-30167 On a smooth approximation method and its ACCURACY application to mathematical description of wing Guidance accuracy considerations for the microwave aerodynamic characteristics landing system L-band precision DNE A79-47001 A79-48692 Overall aerodynamic characteristics of caret and ACOUSTIC DUCTS delta wings at supersonic speeds Duct noise radiation through a Jet flow A79-l47012 A79-50110 The calculation of non-linear aerodynamic ACOUSTIC PROPAGATION characteristics of wings and their wakes in Transform domain processing for digital subsonic flow communication systems using surface acoustic A79-47099 wave devices Some early experiments in the development of a N79-31482 flying platform for aerodynamic testing ACOUSTIC VELOCITY A79-47535 Aerodynamic and acoustic investigation of inverted Aerodynamic effects of an attitude control vane on velocity profile coannular exhaust nozzle models a tilt-nacelle V/STOL propulsion system and development of aerodynamic and acoustic [AIRS PAPER 79-1855] A79-47914 prediction procedures, comprehensive data Flow patterns and aerodynamic characteristics of report, volume 1 wing with strake [NASA-CR-159515] 579-30185 [AIAA PAPER 79-1877] 579-47928 Aerodynamic and acoustic investigation of inverted A novel technique for obtaining aerodynamic data velocity profile coannular exhaust nozzle models using simple, free flight trajectory measurements and development of aerodynamic and acoustic 579-48051 prediction procedures, comprehensive data Aircraft longitudinal motion at high incidence report, volume 2 A79-48052 (NASA-CR-159516] 579-30186 A design perspective on new technologies for ACTUATOR DISKS general aviation An actuator disk analysis of an isolated rotor 579-1191486 with distorted inflow Aerodynamic interaction on a close-coupled [AD-A069884] 579-31216 canard-wing configuration ADAPTIVE CONTROL [ONERA, TP NO. 1979-95] A79-49543 Digital adaptive control laws for VTOL aircraft Variables characterizing the wind effects on an A79-48000 aircraft Adaptive array tradeoffs for existing airborne UHF A79-49807 radios Design and development of the Agusta A 109 A79-48598 helicopter Investigation of inverse Vandermonde matrix calculation for linear system applications 579-49815 adaptive flight control systems [AD-5069241] 1479-31225

A-i

AERODYNAMIC COEFFICIENTS SUBJECT INDEX

Performance evaluation method for dissimilar Active external store flutter suppression in the aircraft designs --- using the square of the YF-17 flutter model wing span for nondimensional comparisons of A79-149866 aerodynamic characteristics Performance evaluation method for dissimilar (NASA-RP-102] 879-30139 aircraft designs --- using the square of the Rotary balance data for a typical single-engine wing span for nondinensional comparisons of general aviation design for an angle-of-attack aerodynamic characteristics range of 8 deg to 90 deg. 1: High-wing model B [NASA-RP-1042] N79-30139 [NASA-CR-3097] 879-30145 Analysis of wind tunnel data pertaining to high Flow visualization studies of a general research angle of attack aerodynamics. Volume 2: Data fighter model employing a strake-wing concept at base subsonic speeds --- in the Langley high speed 7- [AD-A069647] 879-30149 by 10-ft wind tunnel A flow field study for top mounted inlets on [NASA-TN-80057] 879-30147 fighter aircraft configurations Analysis of wind tunnel data pertaining to high [AD-A069732] 879-30151 angle of attack aerodynamics. Volume 1: Performance of two-stage fan with a first-stage Technical discussion and analysis of results rotor redesigned to account for the presence of (AD-A069646) 879-30148 a part-span damper Analysis of wind tunnel data pertaining to high [NASA-TP-1483] N79-30191 angle of attack aerodynamics. Volume 2: Data Modal interpolation program, L215(INTERP). Volume base 2: Supplemental system design and maintenance AD-A069647] 879-30149 document --- to calculate displacements at Airworthiness and flight characteristics test, several points on an aerodynamic surface OV-1C takeoff performance [NASA-CH-2848] 879-31147 [AD-A069827] 879-30178 AERODYNAMIC DRAG Dynamic loads analysis system (DYLOFLEX) summary. The influence of sweep on the aerodynamic loading Volume 1: Engineering formulation of an oscillating NACA 0012 airfoil (NASA-CR-2846-1 ] N79-31144 EARS 79-4] A79-49057 Dynamic loads analysis system (DYLOFLEX) summary. An integrated analytical and experimental Volume 2: Supplemental system design information investigation of helicopter hub drag (NASA-CR-2846-2] 879-31145 [ABS 79-51 A79-49058 Lateral aerodynamics extracted from flight test Theoretical flap-lag damping with various dynamic using a parameter estimation method inflow models AHL-AERO-NOTE-380] W79-31146 [ABS 79-20] A79-119073 A program to compute three-dimensional subsonic The size and performance effects of high lift unsteady aerodynamic characteristics using the system technology on a modern twin engine jet doublet lattice method, L216 (DUBFLEX) . Volume transport 2: Supplemental system design and maintenance [AIRA PAPER 79-1795] A79-49332 document Dynamic test techniques - Concepts and practices [NASA-CR-2850] 879-31148 aircraft performance prediction from Rotary balance data for a typical single-engine thrust/lift/drag model general aviation design for an angle-of-attack A79-50164 range of 8 deg to 90 deg. 2: High-wing model A Subsonic wind-tunnel investigation of leading-edge [NASA-CR-3101) 879-31149 devices on delta wings (data report) Rotary balance data for a single-engine trainer conducted in Langley 7- by 10-foot subsonic wind design for an angle-of-attack range of 8 deg to tunnel 90 dug --- conducted in langely spin tunnel [NASA-CR-159120] N79-31143 [NASA-cR-3099] 879-31152 AERODYNAMIC FORCES Aerodynamic and acoustic investigation of inverted A force and moment test of a 1/24-scale F-ill velocity profile coannular exhaust nozzle models model at Mach numbers from 0.7 to 1.3 and development of aerodynamic and acoustic [AD-A070192] 879-31156 prediction procedures AERODYNAMIC INTERFERENCE [NASA-CR-3168] 879-31212 Engine-aircraft afterbody interactions - Theoretical and experimental investigation of Recommended testing techniques based on YF-17 ground-induced effects for a low-aspect-ratio experience highly swept arrow-wing configuration [AIAA PAPER 79-1829] A79-47903 (NASA-TP-1508] 879-31223 Benefits of aerodynamic interaction to the three AERODYNAMIC COEFFICIENTS surface configuration Estimation of longitudinal aircraft [AIAA PAPER 79-1830] A79-47904 characteristics using parameter identification Interactional aerodynamics - A new challenge to techniques helicopter technology A79-50432 (ABS 79-59] A79-49109 Upper-surface modifications for C sub 1 max Effect of nozzle spacing on ground interference improvement of selected NASA 6-series airfoils forces for a two jet V/STOL aircraft (NASA-TN-78603) 879-30143 [AIAA PAPER 79-1856] A79-49339 Aerodynamic and acoustic investigation of inverted AERODYNAMIC LOADS velocity profile coannular exhaust nozzle models Wing aerodynamic loading caused by jet-induced and development of aerodynamic and acoustic lift associated with STOL-OTW configurations prediction procedures, comprehensive data [AIAA PAPER 79-1664] A79-473116 report, volume 1 A lifting-surface method for hover/climb airloads (NASA-CR-159515) 879-30185 [ABS 79-3] A79-49056 Aerodynamic and acoustic investigation of inverted The influence of sweep on the aerodynamic loading velocity profile coannular exhaust nozzle models of an oscillating NACA 0012 airfoil and development of aerodynamic and acoustic (ABS 79-4] A79-49057 prediction procedures, comprehensive data A program for calculating load coefficient report, volume 2 matrices utilizing the force summation method, [NASA-CB-159516] 879-30186 1218 (LOADS). Volume 2: Supplemental system A program for calculating load coefficient design and maintenance document matrices utilizing the force summation method, (NASA-CR-2854] 879-31155 L218 (LOADS). Volume 2: Supplemental system AERODYNAMIC NOISE design and maintenance document Experiments of shock associated noise of [NASA-CR-2854] 879-31155 supersonic jets AERODYNAMIC CONFIGURATIONS fRIAR PAPER 79-1526] A79-1173111 A method of the theory of airfoil profiles with a Study of design constraints on helicopter noise jet flap [NASA-CR-159118] 879-32054 A79-47119 AERODYNAMIC STABILITY Aerodynamics of spoiler control devices Some early experiments in the development of a (AIAA PAPER 79-1873] A79-47925 flying platform for aerodynamic testing A79-47535

A-2

SUBJECT INDEX AIR TRAFFIC CONTROL

Stability and control --- conferences Heave-pitch-roll analysis and testing of air (AGARD-CP-260) N79-30218 cushion landing systems Stall behaviour evaluation from flight test results [NASA-CR-2917] N79-30175 N79-30227 AIR DEFENSE Wind-tunnel investigation of an armed mini Adding the challenge of nap-of-the-earth remotely piloted vehicle --- conducted in N79-30199 Langley V/STOL tunnel AIR FLOW [NASA-TN-80132] N79-31151 Surface-effect components of aerodynamic AERODYNAMIC STALLING characteristics of air-cushion vehicle with ram The effects of configuration changes on spin and pressurization recovery characteristics of a low-wing general A79-46995 aviation research airplane Investigation of air stream from combustor-liner (AIAA PAPER 79-1786] A79-47876 air entry holes, 3 Dutch roll excitation and recovery techniques on a [NASA-TM-751430] N79-31206 C-141A Starlifter Aerodynamic performance of axial-flow fan stage [AIRA PAPER 79-1801) A79-47886 operated at nine inlet guide vane angles --- to Some flight data extraction techniques used on a be used on vertical lift aircraft general aviation spin research aircraft (NASA-TP-1510) N79-31214 [AIAA PAPER 79-1802) A79-47887 AIR INTAKES The Beech Model 77 'Skipper' spin program Investigation of air stream from combustor-liner (AIAA PAPER 79-1835) A79-47907 air entry holes, 3 Radio-controlled model design and testing (NASA-TM-75430] N79-31206 techniques for stall/spin evaluation of AIR JETS general-aviation aircraft Investigation of air stream from combustor-liner (NASA-TN-80510] N79-30173 air entry holes, 3 Stall behaviour evaluation from flight test results [NASA-TN-75430] N79-31206 W79-30227 AIR LAUNCHING AERODYNAMICS Complex quaternion notation in coordinate Aerodynamics for engineers --- Book transformations --- missile launching A79-50375 aircraft-inertial space transformations AEROELASTICITT A79-48681 Some observations on four current subjects related AIR NAVIGATION to aeroelastic stability A simple integrated navigation based on multiple ONE A79-47093 (DGLR PAPER 79-041) A79-48640 Dynamics requirements for an Advanced Scout Expanding the region of convergence for SITAR Helicopter /ASH/ through improved modelling of terrain ABS 79-19) A79-49072 nonlinearities --- Sandia Inertial Terrain Aided On single-degree-of-freedom flutter induced by Navigation activated controls A79-48678 A79-49867 D y namic simulator test and evaluation of a JTIDS Comment on 'active flutter control using relative navigation system --- Joint Tactical generalized unsteady aerodynamic theory' Information Distribution System A79-49873 A79-48694 Dynamic loads analysis system (DYLOFLEX) summary. Navstar user equipment for civil and military Volume 1: Engineering formulation applications (NASA-CR-2846-1 ) N79-31144 A79-49587 Dynamic loads analysis system (DYLOFLEX) summary. Aeronautical information data subsystems /AIDS/ Volume 2: Supplemental system design information A79-50920 [NASA-CR-2846-2] R79-31145 AIR POLLUTION AERONAUTICAL ENGINEERING Correlation technique for ambient effects on Aerodynamics for engineers --- Book oxides of nitrogen --- from combustion products A79-50375 in atmospheric pollution Enforcer aircraft A79-49922 rGPO-32-569) N79-30170 Critical assessment of emissions from aircraft AERONAUTICAL SATELLITES piston engines A novel approach to the design of an all digital (AD-A071002] N79-30190 aeronautical satellite communication system Experimental Clean Combustor Program (ECCP), phase 3 N79-31461 commercial aircraft turbofan engine tests AFTERBODIES with double annular combustor Engine-aircraft afterbcdy interactions - [NASA-CR-135384] N79-31207 Recommended testing techniques based on YP-17 Exhaust emission traverse investigation of a experience JT3D-1 turbofan engine --- to acquire exhaust [AIAA PAPER 79-1829] A79-47903 nozzle emission sample AFTEEBURNING (AD-A072019] N79-31209 Characteristics of afterburning bypass turbojet Ambient correction factors for aircraft gas engine with oxygen injection into the turbine idle emissions afterburner chamber [AD-A0692 140] N79-31218 A79-48519 AIR TRAFFIC A simplified gross thrust computing technique for The aerial relay system - An energy-efficient an afterburning turbofan engine solution to the airport congestion problem A79-50440 using cruise liner aircraft for in-air passenger AGRICULTURAL AIRCRAFT transfer Agricultural helicopters --- test and simulation [AIAA PAPER 79-1865) A79-47921 results Aeronautical information data subsystems /AIDS/ (ABS 79-60) A79-49064 A79-50920 AIR COOLING Runway configuration management system concepts Full-scale wind tunnel study of nacelle shape on [ AD-A069960] N79-31234 cooling drag AIR TRAFFIC CONTROL (ATAA PAPER 79-1820) A79-47900 Small lightweight electronically steerable Experimental study of the gasdynamic cylindrical antenna successfully utilized in an characteristics of a stator cascade with cooling air traffic management system air discharge through the vane surface A79-48597 A79-48498 The ATCBI-5 beacon interrogator --- Air Traffic AIR CUSHION LANDING SYSTEMS Control Beacon Interrogator characteristics of an Air Cushion Landing System A79-48693 incorporating an inelastic trunk Modern systems for air traffic control A79-49909 A79-50921

A-3 AIR TRANSPORTATION SUBJECT INDEX

Central flow control software design document. Volume 1: Operational software complex E-3A sentry /AWACS/ ATPG --- Automatic Test Program Generation automation support to the Air Traffic Control System Command Center A79-48873 AIRCRAFT [AD-A070973] N79-30959 Central flow control software design document. Airport flammability, full scale fire tests Volume 2: Support software complex B79-31167 AIRCRAFT ACCIDENT INVESTIGATION automation support to the Air Traffic Control System Command Center. Lusaka accident report [AD-A070771] N79-30960 A79-50109 A developmental computer model for investigations Aircraft accident report: Swift lire Lines, Inc., Nord 262, N418SA, Marina Del Hey, California, of air traffic management problems: A case March 10, 1979 investigating two decision strategies [AD-A071075] [NTSB-AAR-79-13] N79-31165 N79-31189 AIRCRAFT ACCIDENTS Advisory circular. The planning grant program for airports - A simulation of A m phibious hovercraft overturning [AC150/5900-1B] 179-49904 N79-31232 Special investigation report: Wing failure of A digital communication system as gateway between Boeing 747-131 near adjacent computerized air traffic control centres . Madrid, Spain, 9 May 1976 [NTSB-AAR-78-12] N79-30167 N79-31463 Helicopter obstacle strike tolerance concepts AIR TRANSPORTATION analysis The aerial relay system - An energy-efficient [AD-A069877] solution to the airport congestion problem N79-30179 using cruise liner aircraft for in-air passenger Aircraft accident report: Swift Aire Lines, Inc., transfer Nord 262, N418sA, Marina Del Hey, California, March 10, 1979 (AIAA PAPER 79-1865] A79-47921 [NTSB-AAR-79-13] N79-31165 Injuries in air transport emergency evacuations AIRCRAFT ANTENNAS A79-49995 International Air Transportation Competition Act Multiband antenna --- for tactical naval aircraft of 1978 --- congressional reports A79-48596 [GPO-34-912] Antennas for the Black Hawk helicopter N79-30168 [AHS 79-15] Supersonic transport vis-a-vis energy savings A79-49068 Evaluation of the radar altimeter reference method (NASA-TN-75464] N79-31163 AIRBORNE EQUIPMENT for determining altitude system positioning errors Radar cross section fundamentals for the aircraft designer Radiation from quarter-wavelength monopoles A79-50436on finite cylindrical, conical, and rocket-shaped [AIAA PAPER 79-1818] A79-47898 Real time weather display in the general aviation conducting bodies --- airborne antenna design cockpit A79-50606 A helicopter high definition rotor blade radar [AIAA PAPER 79-1821] A79-47901 Power hybridization - Key to reducing avionics N79-30207 power supply weight and volume UHF coplanar-slot antenna for aircraft-to-satellite data communications A79-48652 [NASA-Tn-79239] Multifunction CO2 heterodyning laser radar for low N79-31185 level tactical operations AIRCRAFT CARRIERS The T &E simulator - A comparison with flight A79-48685 test results Airborne microwave ECM A79-50169 A79-49554 AIRCRAFT COMMUNICATION The A.I. tracking problem --- Airborne Interception Adaptive array tradeoffs for existing airborne UHF A79-49566 radios An in-flight controller insensitive to parameters variation A79-48598 The ATCBI-5 beacon interrogator --- Air Traffic [DLR-FB-78-07] N79-30197 Heterodyning CO2 laser radar for airborne Control Beacon Interrogator applications A79-48693 A report on the Sperry Dome Radar N79-30205 AIRBORNE SURVEILLANCE RADAR A79-49567 UHF coplanar-slot antenna for Built in test of A/D converters - Present aircraft-to-satellite data communications approaches and recommendations for improved BIT [NASA-TN-79239] effectiveness --- in airborne radar systems N79-31185 Performance predictions and trials of a helicopter A79-48621 UHF data link Millimeter airborne radar target detection and selection techniques N79-31476 New devices for digital communications in avionics A new three-dimensional surveillance radar A79-48665 N79-31481 Implementing 7TIDS in tactical aircraft A79-49568 The servoed modulation FNCW radar altimeters in N79-31491 military applications AIRCRAFT COMPARTMENTS Recent advances in materials toxicology A79-49589 Automated tracking for aircraft surveillance radar N79-31169 systems A review of Boeing interior materials and fire test methods development programs A79-49604 AIRBORNE/SPACEBORNE COMPUTERS N79-31177 FIREMEN program Digital adaptive control laws for VTOL aircraft A79-48000 N79-31178 Analysis and evaluation of current MIL-STD-1553 Development of aircraft lavatory compartments with digital avionics architecture as the basis for improved fire resistance characteristics. Phase advanced architectures using MIL-STD-1553B 2: Sandwich panel resin system development (NASA-CE-152120] N79-31354 Computer Monitor and Control - A flexible, A79-48629 AIRCRAFT CONFIGURATIONS cost-effective implementation Recent V/STOL aircraft designs A79-48670 A79-47608 Evolving methods for reducing avionics data in an The effects of configuration changes on spin and AISF environment --- Avionics Integration recovery characteristics of a low-wing general Suppport Facility flight program testing aviation research airplane [AIAA PAPER 79-1786] A79-47876 Manned strategic system concepts 1990-2000 Integrated CR1 avionics --- ECM-resistant A79-48671 [AIAA PAPER 79-1793] Communication, Navigation and Identification A79-47882 A79-48711

1-4 SUBJECT INDEX AIRCRAFT DESIGN

Engine-aircraft afterbody interactions - Design considerations for reliable FEW flight Recommended testing techniques based on Yi'-17 control experience N79-30231 (AIRA PAPER 79-1829] A79-47903 L-1011 active controls, design philosophy and Interactional aerodynamics - A new challenge to experience helicopter technology N79-30236 [ABS 79-59] 879-49109 Flying qualities and the fly-by-wire aroplane Application of Lagrange Optimization to the drag N79-30238 polar utilizing experimental data A simulator investigation of handling quality [AIAA PAPER 79-1833] 879-49335 criteria for CCV transport aircraft Effect of nozzle spacing on ground interference N79-30240 forces for a two let V/STOL aircraft AIRCRAFT DESIGN [AIAA PAPER 79-1856] A79-49339 On a smooth approximation method and its In-flight handling qualities investigation of application to mathematical description of wing various longitudinal short term dynamics and aerodynamic characteristics direct lift control combinations for flight path A79-47001 tracking using DPVLR HFR 320 variable stability Solution of the inverse aerodynamics problem by aircraft the random search method 879-30237 A79-47002 Introduction and overview of configurations Selecting the passenger airplane fuselage for transonic flows A79-47014 N79-31160 Compass Cope airframe design history AIRCRAFT CONSTRUCTION MATERIALS [8188 PAPER 79-1792] 879-47881 High-performance reinforced plastic structures for Manned strategic system concepts 1990-2000 civil aviation [AIAA PAPER 79-1793] 879-47882 A79-47302 Identifying desirable design features for the C-XX Handbook on aircraft materials and their aircraft - A systems approach application technology [8188 PAPER 79-1796] A79-47883 879-48311 Design of advanced titanium structures --- for Metal-matrix composite structures Advanced Tactical Systems aircraft fuselage [ABS 79-34] A79-49086 [8188 PAPER 79-1805] 879-47890 Certification of composites in civil aircraft Historical development of worldwide supersonic [AilS 79-43] 879-49095 aircraft High performance composites and adhesives for [AIAA PAPER 79-1815) 879-47895 V/STOL aircraft From HiMAT to future fighters --- Highly [80-8069611] - N79-30332 Maneuverable Aircraft Technology assessment AIRCRAFT CONTROL [8188 PAPER 79-1816] A79-47896 Some results from the use of a control Radar crcss Section fundamentals for the aircraft augmentation system to study the developed spin designer of a light plane (8188 PAPER 79-1818) A79-47898 (8188 PAPER 79-1790] 879-47879 All electric subsystems for next generation Dutch roll excitation and recovery techniques on a transport aircraft C-1418 Starlifter [AIAA PAPER 79-1832] 879-47906 [AIAA PAPER 79-1801] A79-47886 Exploratory study of the influence of wing Nonlinear decoupled control synthesis for leading-edge modifications on the Spin maneuvering aircraft characteristics of a low-wing single-engine 879-47959 general aviation airplane The enhancement of aircraft parameter [8188 PAPER 79-1837] 879-47908 identification using linear transformations Design of the circulation control wing STOL for stability demonstrator aircraft 879-47961 [AIAA PAPER 79-1842] A79-47909 A multiple objective optimization approach to Geometric data transfer --- for computerized aircraft control systems design aircraft engineering drawings A79-47962 [8188 PAPER 79-1844] 879-47910 Application of singular perturbation techniques Engineering and manufacturing communication via /SPT/ and continuation methods for on-line the computer data base aircraft trajectory optimization [8188 PAPER 79-1845] A79-47911 879-47991 CADAM data handling from conceptual design through Digital adaptive control laws for VTOL aircraft produce support A79-48000 (AIAA PAPER 79-1846] 879-47912 The 00-800 - A rugged, high performance heading Laminar flow stabilization by surface cooling on reference unit --- directional gyro design hydrogen fueled aircraft considerations (8188 PAPER 79-1863) 879-47920 A79-48677 High-performance wings with significant Guidance accuracy considerations for the microwave leading-edge thrust at supersonic speeds landing system L-band precision DME [AjAR PAPER 79-1871] 879-47924 A79-48692 A multiple objective optimization approach to Combined environment reliability test of the aircraft control systems design common strategic Doppler system A79-47962 A79-50368 Handbook on aircraft materials and their An evaluation of sidestick force/deflection application technology characteristics on aircraft handling qualities A79-48311 A79-50428 Analysis design of complex systems. II --- for AFFTC parameter identification experience --- Air simultaneous improvement of all basic prototype Force Flight Test Center aircraft flight testing flight vehicle performance characteristics 879-50434 A79-48505 Applications of pattern recognition systems for Microprocessor-based digital autopilot development day/night precision aircraft control for the XBQN-106 Mini-RPV N79-30204 A79-48608 Stability and control --- conferences A Status report on the advanced FIREFLY assessment [AGARD-CP-260] N79-30218 program Enhanced fighter mission effectiveness by use of 879-48609 integrated flight systems Multisensor integration for defensive fire control N79-30223 surveillance Results related to simulated and in-flight 179-48610 experimentation with an electric flight control Role of Numerical Control Design in the computer system that can be generalized aided design/manufacturing interface at Sikorsky N79-30224 [ABS 79-30] A79-49082

A-5

AIRCRAFT DETECTION SUBJECT INDEX

Self-contained grease lubrication systems for Energy efficient engine flight propulsion system aircraft applications preliminary analysis and design report - [ANS 79-39] A79-49091 [NASA-CR-159487] 879-30189 Design criteria for airline operation Critical assessment of emissions from aircraft (AlMA PAPER 79-1849) 879-49337 piston engines Recent applications of theoretical analysis to AD-A071002] 879-30190 V/STOL inlet design Tapered roller bearing development for aircraft 879-49530 turbine engines Small hovercraft design - Evolution to simplicity AD-8069440] 879-30555 A79-49906 An overview of NASA research on positive Aerodynamics for engineers --- Book displacement type general aviation engines A79-50375 [NASA-TM-79254] N79-31210 Upper-surface modifications for C sub 1 max Aircraft turbine engine monitoring experience: improvement of selected NASA 6-series airfoils Implications for the p ioo engine diagnostic [NASA-T4-78603] 879-30143 system program Stability and control --- conferences [AD-A069282] [AGABD-CP-260] N79-31217 N79-30218 Ambient correction factors for aircraft gas Systems implications of active controls turbine idle emissions N79-30219 [AD-A069240] 879-31218 Improvement of fighter aircraft maneuverability - AIRCRAFT EQUIPMENT through employment of control configured vehicle The feasibility of inflight measurement of technology lightning strike parameters N79-30225 (NASA-CN-158981] 879-30165 L-1011 active controls, design philosophy and Afl-1G helicopter, 19-round lightweight airborne experience launcher jettison envelope determination 879-30236 [AD-A069828] 879-30177 Are today's specifications appropriate for The impact of a multi-function programmable tomorrow's airplanes? control display unit in affecting a reduction of 879-30239 pilot workload Maritime patrol airship concept study [AD-A070131] 879-30210 N79-31138 The equipment-system interface in an antitank Powered low-aspect-ratio Wing In Ground effect helicopter at night (WIG) aerodynamic characteristics --- conducted 879-30211 in Langley V/STOL tunnel Fuel tank survivability for hydrodynamic ram [NASA-TN-78793] 879-31141 induced by high velocity fragments. Part 1: Experimental data base for computer program Experimental Results and Design summary assessment: Report of the Fluid Dynamics Panel [AD-A070113] N79-31202 Working Group 04 AIRCRAFT FUEL SYSTEMS [AGARD-AR-138] 879-31159 The tendency of jet fuels to form deposits on a AIRCRAFT DETECTION heated surface Estimation of aircraft target motion using pattern A79-48856 recognition orientation measurements Drag reduction by cooling in hydrogen-fueled 879-47987 aircraft The alpha-beta-gamma tracking filter in the Z-domain in aircraft tracking AIRCRAFT FUELS -- A79-48680 Fuels, lubricants and other fluids used in aviation Ellipsoidal modelling of aircraft targets for Russian book evaluation of electronic fuzes A79-47433 On the question of selecting the characteristic AIRCRAFT ENGINES quantity governing fuel self-ignition in a stream Statistical diagnostics of aircraft engines A79-48497 A79-46996 Method of determining mechanical-impurity contents Nozzles for vectored thrust jet engines in jet fuels Russian book A79-48859 879-47428 Alternative fuels in aviation Fuels, lubricants and other fluids used in aviation 879-49381 Russian book Supersonic transport vis-a-vis energy savings A79-47433 [NASA-TM-15464] 879-31163 The characteristics of a lift cruise fan V/STOL AIRCRAFT GUIDANCE configuration in near proximity to a small deck Guidance accuracy considerations for the microwave with finite edge positions landing system L-band precision DME [AIRA PAPER 79-1854] 879-47913 879-48692 Energy efficient aircraft engines The Guidance and control of Helicopters and V/STOL (AlMA PAPER 79-1861] A79-47918 aircraft at night and in poor visibility Long-life GTE operation based on technical Condition [AGARD-CP-258] 879-30198 Gas Turbine Engine Subjective assessment of a helicopter approach 879-48517 system for IFR conditions Development of a 'no adjustments turboshaft engine N79-30209 control system The impact of a multi-function programmable [AHS 79-42] 879-99094 control display unit in affecting a reduction of Fault diagnosis of gas turbine engines by Deans of pilot workload component Characteristics determination 879-30210 879-99806 Project NAVTCLAND (Navy vertical takeoff and The Bell Model 222 landing capability development) A79-49816 879-30212 Correlation technique for ambient effects on GCU, the Guidance and Control Unit for all weather oxides of nitrogen --- from combustion products approach in atmospheric pollution N79-30213 A79-L49922 Implementation of flight control in an integrated Duct noise radiation through a jet flow guidance and control system A79-50110 879-30215 Derivative engines for the 1980s will help limit An advanced guidance and control system for rescue acquisition and maintenance costs helicopters A79-50206 N79-30217 Gas turbines for flight vehicle engines: Theory, Path controllers: Unification of concepts and design, and calculation /Third review and comparison of design methods enlarged edition! --- Russian hook [AD-A070252] 879-31227 A79-50421

A-6

SUBJECT INDEX AIRCRAFT PERFORMANCE

AIRCRAFT HAZARDS AIRCRAFT MANEUVERS Helicopter obstacle strike tolerance Analysis of optimal loop and split-S by energy [Ails 79-71 879-49059 state modeling Atmospheric Electricity Hazard (AER) A79-47098 AD-A069338] 879-30169 An improved method for load survey flight testing Helicopter obstacle strike tolerance concepts of military cargo aircraft analysis [AIAA PAPER 79-1799] 879-47885 AD-8069877] 879-30179 Nonlinear decoupled control synthesis for Lightning hazards overview: Aviation requirements maneuvering aircraft and interests A79-47959 N79-30876 Aircraft longitudinal motion at high incidence AIRCRAFT HYDRAULIC SYSTEMS 879-48052 Fluidics: Feasibility study Small signal compensation of magnetic fields electro/hydraulic/fluidic direct drive servo valve resulting from aircraft maneuvers [AD-A069798] 879-30195 879-49605 AIRCRAFT INDUSTRY Considerations in the analysis of flight test Geometric data transfer --- for computerized maneuvers aircraft engineering drawings 879-50433 [8188 PAPER 79-1844] 879-47910 A study of the application of singular Can avionic testability requirements be enforced perturbation theory --- development of a real A79-48887 time algorithm for optimal three dimensional Avionics design for testability - A vendor's aircraft maneuvers viewpoint [NASA-CR-3167] N79-30194 A79-48889 A compilation and analysis of helicopter handling Financing the capital requirements of the US qualities data. Volume 2: Data analysis airline industry in the 1980's NASA-CR-3145] 879-31222 879-30164 AIRCRAFT MODELS AIRCRAFT INSTRUMENTS Ellipsoidal modelling of aircraft targets for A cheap, effective icing detector for general evaluation of electronic fuzes aviation aircraft A79-49580 [AIAA PAPER 79-1823] 879-47902 Radio-controlled model design and testing The application of pulsed . 0' band radio techniques for stall/spin evaluation of altimeters to modern military aircraft general-aviation aircraft A79-'49590 [NASA-TN-80510] N79-30173 Automated tracking for aircraft surveillance radar Similitude requirements and scaling relationships systems as applied to model testing A79-49604 [NASA-TP-1435] 879-30176 ARIA takeoff performance flight test program Wind-tunnel investigation of an armed mini Advanced Range Instrumented Aircraft remotely piloted vehicle --- conducted in A79-50437 Langley V/STOL tunnel Implementation of flight control in an integrated [NASA-TN-80132] N79-31151 guidance and control system AIRCRAFT NOISE N79-30215 Experimental investigation of helicopter flight Reliability improvement warranty terms and modes on helicopter-generated noise conditions for the Integrated Avionics Control A79-47873 Systems (TACS) Helicopter noise rules - Are they appropriate and AD-A069454] 879-31205 reasonable Transform domain processing for digital A79-49478 communication systems using surface acoustic The aeroacoustics of advanced turbopropellers wave devices 879-50236 879-31482 Supersonic transport aircraft noise, problems of AIRCRAFT LANDING noise reduction and establishment of standards Recent progress in aircraft sink rate measurement 879-50237 [AIAA PAPER 79-1798] 879-47884 Study of design constraints on helicopter noise Advances in decelerating steep approach and [NASA-CR-159118) N79-32054 landing for helicopter instrument approaches AIRCRAFT PARTS [AHS 79-16] 879-49069 Most rational linearization of nonlinear unsteady High sink-rate landing testing of Navy aircraft heat conduction problems --- for flight vehicle A79-50163 parts and engines Testing and analysis of dual-mode adaptive landing A79-48501 gear, taxi mode test system for TF-12A AIRCRAFT PERFORMANCE [ NASA-CR-144884] N79-31192 AFFTC parameter identification experience --- for Investigation on information error caused by aircraft flight characteristics traffic loading in approach and landing systems [8188 PAPER 79-1803] A79-47888 N79-31480 Performance evaluation of an air vehicle utilizing AIRCRAFT MAINTENANCE non-axisymmetric nozzles ATE and aircraft mechanical diagnostics [AIAA PAPER 79-1811] A79-47894 A79-48883 Analysis design of complex systems. II --- for AN/USM-449/V/ ATE for worldwide support of the P3 simultaneous improvement of all basic prototype Orion flight vehicle performance characteristics A79-48884 879-48505 F-16 avionics maintenance concept and Blown wings from Kiev --- short takeoff and multinational aspects landing through wing-overblowing A79-48894 A79-49232 F-16 depot automatic test equipment Variables characterizing the wind effects on an 879-48895 aircraft Fault diagnosis of gas turbine engines by means of 879-49807 component characteristics determination Performance modelling methods --- in flight test A79-49806 programs Maintenance cost study of rotary wing aircraft, A79-50167 Phase 2 A computer system for identifying aircraft [NASA-CR-152291] 879-30138 characteristics Naval aircraft operating and support A79-50168 cost-estimating model, FT 1977 revision Evaluation of selected class III requirements of AD-A068175] 879-30140 MIL-F-8785B /ASG/, 'Flying Qualities of Piloted Maintenance improvement: An analysis approach Airplanes' including inferential technical data --- naval 879-50439 aircraft [AD-A068382] 879-30141

A-i AIRCRAFT PILOTS SUBJECT INDEX

Performance evaluation method for dissimilar aircraft designs --- using the square of the AFFTC parameter identification experience --- Air wing span for nondiiaensional comparisons of Force Flight Test Center aircraft flight testing aerodynamic characteristics P.79-50434 An in-flight controller insensitive to parameters (NASA-RP-1042] 879-30139 variation A summary of AGARD EDP meeting on dynamic [DLR-FB-78-07) stability parameters --- advanced aircraft 879-30197 performance at high angle of attack A summary of AGARD FOP meeting on dynamic stability parameters --- advanced aircraft 879-30220 performance at high angle of attack Enhanced fighter mission effectiveness by use of integrated flight systems N79-30220 AIRCRAFT STRUCTURES N79-30223 Some observations on four current subjects related Open/closed loop identification of stability and to aeroelastic stability control characteristics of combat aircraft N79-30232 A79-47093 AIRCRAFT PILOTS Design of advanced titanium structures --- for ONERA's model of the pilot in discrete time Advanced Tactical Systems aircraft fuselage [AIAA PAPER 79-1805] A79-47890 879-30242 Automatic test program generation selection AIRCRAFT RELIABILITY for aircraft structures Analytic redundancy for flight control sensors on the Lockheed L-1011 aircraft A79-48690 Helicopter obstacle strike tolerance A79-47960 CARS 79-7] Failure detection in signal processing and sensing A79-49059 in flight control systems Designing with experimental mechanics three-dimensional photoelastic analysis of A79-47971 helicopter components A status report on the advanced FIREFLY assessment program [AHS 79-11] A79-49063 Superplastic forming diffusion bonding of titanium A79- 48609 helicopter airframe components Terrain-following radar - Key to low-altitude flight [ABS 79-33] A79-49085 A79- 48686 Automatic scanning inspection of composite Development of a 'no adjustment' turboshaft engine control system helicopter structure using an advanced technology fluoroscopic system [ABS 79-42) A79-49094 [AHS 79-35) What the FAA would like in airworthiness standards A79-49087 [AIAA PAPER 79-1851] Helicopter component environmental vibration A79-49338 testing - The poor man's fatigue test Airworthiness and flight characteristics test, [AIlS 79-49] OV-1C takeoff performance P.79-49101 The DC-9 Super 80 - Much more than a simple stretch [AD-A069827] 879-30178 AIRCRAFT SAFETY A79-49223 Lockheed urges hydrogen fuel The influence of the environment on the elastoplastic properties of adhesives in metal A79-49224 bonded joints --- In aircraft structures A review of Boeing interior materials and fire [ESA-TT-521] test methods development programs N79-30391 Development of fire-resistant, low smoke N79-31177 AIRCRAFT SPECIFICATIONS generating, thermally stable end items for commercial aircraft and spacecraft using a basic Evaluation of selected class III requirements of polyimide resin NIL-F-8785B /ASG/, 'Flying Qualities of Piloted Airplanes' N79-31171 The fluorenone polyester iso FPE of Isovolta Company, Austria Are today's specifications appropriate for A79-50439 tomorrow's airplanes? N79-31183 A user's manual for a computer program to generate N79-30239 AIRCRAFT SPIN fatigue spectrum loading sequences [AD-A069288] 879-31198 The effects of configuration changes on spin and AIRCRAFT SURVIVABILITY recovery characteristics of a low-wing general aviation research airplane Helicopter obstacle strike tolerance [ABS 79-7] A79-49059 [AIAA PAPER 79-1786] A79-47876 AIRCRAFT WAKES Some flight data extraction techniques used on a general aviation spin research aircraft The calculation of non-linear aerodynamic characteristics of wings and their wakes in [AIAA PAPER 79-1802] A79-47897 subsonic flow Radio-controlled model design and testing techniques for stall/spin evaluation of P.79-47099 general-aviation aircraft AIRFIELD SURFACE MOVEMENTS Testing and analysis of dual-mode adaptive landing (NASA-TN-80510) 879-30173 AIRCRAFT STABILITY gear, taxi mode test system for YF-12A [NASA-CR-144884] 879-31192 Application of bifurcation analysis and AIRFOIL PROFILES catastrophe theory methodology /BACTR/ to aircraft stability problems at high A method of the theory of airfoil profiles with a angles-of-attack jet flap A79-47119 Nonlinear decoupled control synthesis for A79-47943 Winglet toe out angle optimization for the Gates maneuvering aircraft Learjet Longhorn Wing [AIAA PAPER 79-1831] A79-47905 A79-47959 High-performance wings with significant The enhancement of aircraft parameter identification using linear transformations leading-edge thrust at supersonic speeds for stability [AIRA PAPER 79-1871] P.79-47924 On the influence of relative pitch in the subsonic A79-47961 turbine cascade Analytical and experimental investigation of V-type empennage contribution to directional A79-48503 control in hover and forward flight The influence of sweep on the aerodynamic loading CARS 79-56] of an oscillating NACA 0012 airfoil P.79-49106 (ABS 79-4] Comment on 'Flight test of stick force stability A79-49057 in attitude-stabilized aircraft' Determining the contour of helicopter rotor blades automatically using electro-optical techniques A79-49925 [ABS 79-32] Estimation of longitudinal aircraft P.79-49084 Wing geometry effects on leading-edge vortices characteristics using parameter identification techniques [AIAA PAPER 79-1872] P.79-49341 A79-50432

A-8

SUBJECT INDEX ANNULAR NOZZLES

Flight experiments to evaluate the effect of AIRSPEED wing-tip sails on fuel consumption and handling Adding the challenge of nap-of-the-earth characteristics 679-30199 A79-49818 ALGORITHMS On single-degree-of-freedom flutter induced by A real-time sequential filtering algorithm for '3PS activated controls low-dynamics navigation system 679-49867 679-48657 Comment on 'active flutter control using A study of the application of singular generalized unsteady aerodynamic theory' perturbation theory --- development of a real 679-49873 time algorithm for optimal three dimensional Upper-surface modifications for C sub 1 max aircraft maneuvers improvement of selected NASA 6-series airfoils [NASA-CR-3167] 679-30194 [NASA-TN-78603] 679-30143 ALL-WEATHER AIR NAVIGATION AIRFOILS Pave Low III --- 8-53 helicopter avionics for Fully conservative numerical solutions for night/adverse weather rescue of military aircraft unsteady irrotational transonic flow about A79-48682 airfoils F1-X combat search and rescue avionics study results [6166 PAPER 79-1555] 679-47342 A79-48684 Experimental measurements of shock/boundary-layer ALL-WEATHER LANDING SYSTEMS interaction of a supercritical airfoil GCU, the Guidance and Control Unit for all weather [6166 PAPER 79-1499] 679-47345 approach Aerodynamics for engineers --- Book N79-30213 A79-50375 ALTITUDE CONTROL Flutter analysis of two-dimensional and Adding the challenge of nap-of-the-earth two-degree-of-freedom airfoils in N79-30199 small-disturbance, unsteady transonic flow ALUMINUM OXIDES [AD-6069223] N79-31157 Metal-matrix composite structures Wind tunnels with adapted walls for reducing wall [ABS 79-34] 679-49086 interference AMPHIBIOUS VEHICLES [NASA-TM-755011 679-31 230 The principles of hovercraft, powering and AIRFRAME MATERIALS propulsion Superplastic forming diffusion bonding of titanium A79-47844 helicopter airframe components ANALOG CIRCUITS [ASS 79-33] A79-49085 A Navy plan for the development of a practical AIRFRAMES computer-aided programming /CAP/ system for Metallic coatings for graphite/epoxy composites analog circuit test design (AD-A069871] 679-30334 A79-48870 AIRLINE OPERATIONS ANALOG TO DIGITAL CONVERTERS The aerial relay system - An energy-efficient Built in test of A/U converters - Present solution to the airport congestion problem approaches and recommendations for improved BIT using cruise liner aircraft for in-air passenger effectiveness --- in airborne radar systems transfer 679-48621 [AIAA PAPER 79-1865] A79-47921 The impact of software in automatic test equipment Design criteria for airline operation for evaluation of radar analog to digital [6166 PAPER 79-1849] 679-49337 converter AIRPLANE PRODUCTION COSTS 679-48691 Testability, the key to economical and ANGLE OF ATTACK operationally effective avionic test software Application of bifurcation analysis and A79-48890 catastrophe theory methodology /BACTN/ to Financing the capital requirements of the US aircraft stability problems at high airline industry in the 19806s angles-of-attack N79-30164 A79-47943 AIRPORT BEACONS An investigation of the rolling stability The ATCBI-5 beacon interrogator --- Air Traffic derivatives of a I-tail fighter configuration at Control Beacon Interrogator high angles-of-attack A79-48693 679-50165 AIRPORT PLANNING The evolution of the high-angle-of-attack features Airport power supply --- Russian book of the F-16 flight control system A79-50499 A79-50438 Potential closure of airports Analysis of wind tunnel data pertaining to high 679-31 231 angle of attack aerodynamics. Volume 1: Advisory circular. The planning grant program for Technical discussion and analysis of results airports [ AD-A069646] N79-30148 [AC150/5900-1B] 679-31232 Analysis of wind tunnel data pertaining to high AIRPORTS angle of attack aerodynamics. Volume 2: Data Current status of airport terminal complex base development abroad [AD-A069647] N79-30149 A79-50240 A summary of AGARD PUP meeting on dynamic Potential closure of airports stability parameters --- advanced aircraft N79-31231 performance at high angle of attack Surveys of grooves in 19 bituminous runways 4479-30220 (60-6069889] 679-31233 Rotary balance data for a single-engine trainer Runway configuration management system concepts design for an angle-of-attack range of 8 deg to (60-6069960] N79-31234 90 deg --- conducted in langely spin tunnel AIRSHIPS [NASA-CR-3099] N79-31152 Air buoyant vehicles - Energy efficient aircraft ANGULAR DISTRIBUTION [AIAA PAPER 79-1862] 679-47919 Determination of turning angle of a jet impinging The feasibility of modern dirigibles on a bucket with visor --- for thrust reversers [ONEBA, TP NO. 1979-93] 679-49541 A79-48500 Lighter than air vehicles. Citations from the ANNULAR FLOW NTIS data base The inner regions of annular jets [NTIS/PS-79/0471/7] 679-30162 A79-47520 Lighter than air vehicles. Citations from the ANNULAR NOZZLES Engineering Index data base Aerodynamic and acoustic investigation of inverted (NTIS/PS-79/0472/5] N79-30163 velocity profile coannular exhaust nozzle models Maritime patrol airship concept study and development of aerodynamic and acoustic [AD-A070131] 679-31138 prediction procedures [NASA-CR-3168] 679-31212

A-9

ANTENNA ARRAYS SUBJECT INDEX

ANTENNA ARRAYS ATMOSPHERIC EFFECTS Adaptive array tradeoffs for existing airborne UHF Correlation technique for ambient effects on radios oxides of nitrogen --- from combustion products '479-48598 in atmospheric pollution ANTENNA DESIGN A79-49922 Multiband antenna --- for tactical naval aircraft ATMOSPHERIC ELECTRICITY A79-48596 Atmospheric Electricity Hazard (AEH) Small lightweight electronically steerable [AD-A069338] N79-30169 cylindrical antenna successfully utilized in an Lightning hazards overview: Aviation requirements air traffic management system and interests A79-48597 N79-30876 Antennas for the Black Hawk helicopter ATMOSPHERIC TURBULENCE (AHS 79-15] '479-49068 Aircraft response to windshears and downdraughts A report on the Sperry Dome Radar N79-30229 A79-49567 ATTITUDE CONTROL ANTENNA RADIATION PATTERNS Microcomputer applications in strapdown heading Adaptive array tradeoffs for existing airborne UHF and attitude reference system radios '479-48606 A79-48598 ATTITUDE INDICATORS Radiation from quarter-wavelength monopoles on F/A-18 Hornet display system finite cylindrical, conical, and rocket-shaped '479-48630 conducting bodies --- airborne antenna design ATTITUDE STABILITY A79-50606 Comment on 'Flight test of stick force stability ANTIFRICTION BEARINGS in attitude-stabilized aircraft Self-contained grease lubrication systems for A79-49925 aircraft applications AUTOMATIC CONTROL [AHS 79-39] A79-49091 Automated tracking for aircraft surveillance radar The Sikorsky elastomeric rotor --- helicopter systems rotor bearings '479-49604 [ABS 79-48] A79-49100 Modern systems for air traffic control APPROACH A79-50921 Driftdown calculations for the FH/227D aircraft Structural aspects of active controls [SAND-78-18071 1479-30182 N79-30221 Flight experience with advanced controls and Dynamic windtunnel simulation of active control displays during piloted curved decelerating systems approaches in a powered-lift STOL aircraft N79-30233 1479-302'43 Central flow control software design document. APPROACH CONTROL Volume 1: Operational software complex Advances in decelerating steep approach and automation support to the Air Traffic Control landing for helicopter instrument approaches System Command Center [AilS 79-16] A79-49069 [AD-A070973J 1479-30959 Project NAVTOIAND (Navy vertical takeoff and Central flow control software design document. landin.g capability development) Volume 2: Support software complex 1479-30212 automation support to the Air Traffic Control APPROXIMATION System Command Center. On a smooth approximation method and its AD-A070771] 1479-30960 application to mathematical description of wing AUTOMATIC FLIGHT CONTROL aerodynamic characteristics Piloted simulator investigation of helicopter A79-47001 control systems effects on handling qualities ARCHITECTURE (COMPUTERS) during instrument flight Analysis and evaluation of current MIL-STD-1553 [ABS 79-26] '479-49078 digital avionics architecture as the basis for The evolution of the high-angle-of-attack features advanced architectures using NIL-STD-1553B of the F-16 flight control system A79-48629 A79-50 43 8 Radar signal processing development for Stability and control --- conferences application of VEST AGARD-CP-260) 1479-30218 A79-48664 Systems implications of active controls ARMOR N79-30219 Crashworthy armored crewseat for the UH-60A Black Enhanced fighter mission effectiveness by use of Hawk integrated flight systems [ABS 79-10] '479-490 62 1479-30223 ARRESTING GEAR Improvement of fighter aircraft maneuverability Recent progress in aircraft sink rate measurement through employment of control configured vehicle [AIAA PAPER 79-1798] '479-478 84 technology ARROW WINGS N79-30225 Selection of geometric parameters and location of L-1011 active controls, design philosophy and nose flap on swept wing root profile from tunnel experience test data. I N79-30236 '479-46999 Flight performance of the TCV B-737 airplane at Overall aerodynamic characteristics of caret and Kennedy Airport using TRSB/MLs guidance delta wings at superscnic speeds [NASA-TN-80148] 1479-31186 A79-47012 AUTOMATIC LANDING CONTROL Theoretical and experimental investigation of The I & E simulator - A comparison with flight ground-induced effects for a low-aspect-ratio test results highly swept arrow-wing configuration A79-50169 [NASA-TP-1508] 1479-31223 VTOL controls for shipboard landing ASPECT RATIO [NASA-CR-162140] 1479-30193 The calculation of non-linear aerodynamic AUTOMATIC PILOTS characteristics of wings and their wakes in An improved method for load survey flight testing subsonic flow of military cargo aircraft '479-47099 [AIAA PAPER 79-1799] A79-47885 ASPHALT Microprocessor-based digital autopilot development An evaluation of asphalt-rubber mixtures for use for the XBQM-106 Mini-RPV in pavement systems A79-48608 [AD-A069448] N79-30246 Some aspects of the design and development of the maritime autopilot modes for the Westland Lynx helicopter N79-30201

A-i 0

SUBJECT INDEX BEARINGLESS ROTORS

AUTOMATIC TEST EQUIPMENT A real time video bandwidth reduction system based Test implementation through support software - A on a CCD Hadainard transform device --- for FIT translator --- automated Fault Isolation avionics Tests on airborne radar system A79-48702 879-48687 Integrated CNI avionics --- ECM-resistant Automatic test software for calibrating strapdown Communication, Navigation and Identification systems 879-48711 A79-48689 AN/USN-449/v/ ATE for worldwide support of the P3 Automatic test program generation selection Orion for aircraft structures A79-48884 #79-48690 Can avionic testability requirements be enforced The impact of software in automatic test equipment 879-48887 for evaluation of radar analog to digital Avionics design for testability - An aircraft converter contractor's viewpoint 879-48691 A79-48888 A Navy plan for the development of a practical Avionics design for testability - A vendor's computer-aided programming /CAP/ system for viewpoint analog circuit test design A79-48889 879-48870 Testability, the key to economical and Air Force modular automatic test equipment operationally effective avionic test software development program A79-48890 A79-48878 Techniques for fault isolation ambiguity reduction ATE and aircraft mechanical diagnostics in military avionics A79-48883 A79-48891 AN/USM-449/V/ ATE for worldwide support of the P3 F-16 avionics maintenance concept and Orion multinational aspects A79-48884 A79-48894 Can avionic testability requirements be enforced Helmet mounted display and sight development A79-48887 [8115 79-17] #79-49070 Avionics design for testability - A vendors NASA/Princeton digital avionics flight test facility viewpoint 879-49344 879-48889 Reliability improvement warranty terms and Testability, the key to economical and conditions for the Integrated Avionics Control operationally effective avionic test software Systems (IACS) 879-48890 [80-8069454] 1179-31205 Techniques for fault isolation ambiguity reduction State of the art in digital signal processing with in military avionics applications to multiple access systems A79-48891 1179-31487 F-16 depot automatic test equipment AXIAL FLOR TURBINES A79-48895 Aerodynamic excitation forces of blade vibrations A new U.U.T./test station interface in axial turbomachinery as a result of 879-48896 interference from nearby cascades AVIONICS A79-48572 F-16 Avionics Intermediate Shop /AIS/ Interim Aerodynamic performance of 1.38-pressure-ratio, Contractor Support initiatives variable-pitch fan stage AIAA PAPER 79-1868] 879-47923 [NASA-TP-1502] 1179-31213 Avionics computer software operation and support Aerodynamic performance of axial-flow fan stage cost estimation operated at nine inlet guide vane angles --- to A79-48620 be used on vertical lift aircraft Analysis and evaluation of current MIL-STD-1553 [NASA-TP-1510] 1179-31214 digital avionics architecture as the basis for advanced architectures using NIL-STD-15538 879-48629 B The effect of standardization of avionics software 8-1 AIRCRAFT quality assurance Separation testing of large weapons from the H-i A79-48648 bomber Power hybridization - Key to reducing avionics A79-50429 power supply weight and volume Systems implications of active controls A79-48652 N79-30219 Verification of operational flight programs by BACESCATTERING simulation Radar cross section fundamentals for the aircraft 879-48667 designer Computer Monitor and Control - A flexible, [AIAA PAPER 79-1818] A79-47898 cost-effective implementation BALANCING A79-48670 Computer-assisted high-speed balancing of T53 and Evolving methods for reducing avionics data in an T55 power turbines AIS? environment -- Avionics Integration CABS 79-36] 879-49088 Suppport Facility flight program testing BALLAST (BASS) A79-48671 Previsions and experimental results in open Microcomputer control of a test facility --- for balloon controlled descent avionics N79-31691 A79-48672 BALLOON FLIGHT Operational experience with the AN/ARN-131 Omega Transatlantic flights of stratospheric balloons Navigation Set 1179-31687 A79-48676 Previsions and experimental results in open Pave Low III --- 11-53 helicopter avionics for balloon controlled descent night/adverse weather rescue of military aircraft N79-31691 A79-48682 BALLOONS H-S combat search and rescue avionics study results Lighter than air vehicles. Citations from the 879-43684 NTIS data base Terrain-following radar - Key to low-altitude flight [NTIS/PS-79/0471/7] 1179-30162 A79-48686 Lighter than air vehicles. Citations from the Test implementation through support software - A Engineering Index data base FIT translator --- automated Fault Isolation [NTTS/PS-79/0472/5) N79-30163 Tests on airborne radar system BEARIRGLESS ROTORS A79-48687 Full scale ground and air resonance testing of the Rapid reaction time techniques for a strapdown Army-Boeing Vertol Bearingless Main Rotor navigator employing electrostatic gyro technology [AHS 79-23] 879-49075 A79-48697

A-il

BELL AIRCRAFT SUBJECT INDEX

BELL AIRCRAFT BOUNDARY LAYER TRANSITION Development of a fly-by-wire elevator for the Bell Mechanics of boundary layer transition, part 2: Helicopter Textron 214ST Instability and transition to turbulence CARS 79-27] A79-49079 (VKI-LECTUBE-SERIES-3-PT-2] N79-31530 The Bell Model 222 BOUNDARY LAYERS A79-49816 Experimental measurements of shock/boundary-layer BESSEL FUNCTIONS interaction of a supercritical airfoil Stabilizing electro-optical systems on helicopters [AIAA PAPER 79-1499] A79-47345 N79-30216 BOUNDARY VALUE PROBLEMS BIBLIOGRAPHIES Linearization of the boundary-layer equations of Lighter than air vehicles. Citations from the the minimum time-to-climb problem NTIS data base A79-49869 [RTIS/PS-79/01471/7] N79-30162 Solution of a Riled boundary value problem for Lighter than air vehicles. Citations from the flow past a thin delta wing Engineering Index data base A79-49882 [NTTS/PS-79/0472/5] N79-30163 BUOYANCY BIRD-AIRCRAFT COLLISIONS The feasibility of modern dirigibles An evaluation of the bird aircraft strike hazard [ONERA. TP NO. 1979-93) A79-49541 at Hill APR, Utah (AFLC) [AD-A070459] N79-31184 BLADE TIPS Effect of tip shape on blade loading C-5 AIRCRAFT characteristics for a two-bladed rotor in hover Systems implications of active controls CABS 79-1] A79-49054 N79-30219 The promise of multicyclic control --- to control C-130 AIRCRAFT fatiguing blade loads and rotor vibration Operational experience with the AN/ABN-131 Omega [NASA-TM-78621] N79-31137 Navigation Set BLAST DEFLECTORS A79-48676 Noise generation by jet-engine exhaust deflection C-135 AIRCRAFT [DLR-PB-78-21] N79-30192 ARIA takeoff performance flight test program BLOWING Advanced Range Instrumented Aircraft Performance of a V/STOL tilt nacelle inlet with A79-50437 blowing boundary layer control C-141 AIRCRAFT [AIAA PAPER 79-1163] A79-47347 Dutch roll excitation and recovery techniques on a BODY-WING AND TAIL CONFIGURATIONS C-141A Starlifter Benefits of aerodynamic interaction to the three (AIAA PAPER 79-18011 A79-47886 surface configuration The design of digital controllers for the C-141 (AIBA PAPER 79-18301 A79-47904 aircraft using entire eigenstructure assignment BOEING 707 AIRCRAFT and the development of an interactive computer Lusaka accident report design program A79-50109 (AD-A069192) N79-31224 BOEING 737 AIRCRAFT CALIBRATING Airport flammability, full scale fire tests Automatic test software for calibrating strapdown N79-31167 systems Status of candidate materials for full-scale tests A79-48689 in the 737 fuselage A low-velocity airflow calibration and research N79-31170 facility BOEING 747 AIRCRAFT (P8-294501/2) N79-31237 High-performance reinforced plastic structures for CANARD CONFIGURATIONS civil aviation Benefits of aerodynamic interaction to the three A79-47302 surface configuration Special investigation report: Wing failure of [AIAA PAPER 79-1830] A19-419014 Boeing 747-131 near Madrid, Spain, 9 May 1976 Aerodynamic interaction on a close-coupled (NTSB-AAR-78-12] N79-30167 canard-wing configuration BOBBER AIRCRAFT (ONERA, TP NO. 1979-95] A79-49543 Manned strategic system concepts 1990-2000 CANOPIES [AIAA PAPER 79-1793] A79-47882 Windshield technology demonstrator program-canopy BOBBING EQUIPHENT detail design options study Evaluation of P-ill weapon bay aero-acoustic and (AD-A070376) N79-31201 weapon separation improvement techniques CARBON DIOXIDE LASERS [AD-A070253] N79-31203 Nultifunction CO2 heterodyning laser radar for low BOUNDARY LATER CONTROL level tactical operations Performance of a V/STOL tilt nacelle inlet with A79-48685 blowing boundary layer control Heterodyning CO2 laser radar for airborne [AIAA PAPER 79-1163] A79-47347 applications Plight testing the circulation control wing N79-30205 [AIAA PAPER 79-1791] A79-47880 CARBON FIBER REINFORCED PLASTICS Boundary layer control on wings using sound and Development and demonstration of manufacturing leading edge serrations processes for fabricating graphite/PMR-15 [AIAA PAPER 79-1875] A79-47926 polyimide structural elements --- space shuttle Subsonic wind-tunnel investigation of leading-edge aft body flap devices on delta wings (data report) --- N79-30301 conducted in Langley 7- by 10-foot subsonic wind High performance composites and adhesives for tunnel V/STOL aircraft [NASA-CH-159120] N79-31143 (AD-A069611] 1979-30332 BOUNDARY LAYER EQUATIONS CARET WINGS Linearization of the boundary-layer equations of Overall aerodynamic characteristics of caret and the minimum time-to-climb problem delta wings at supersonic speeds A79-49869 A79-47012 BOUNDARY LAYER SEPARATION CARGO AIRCRAFT Subsonic wind-tunnel investigation of leading-edge Identifying desirable design features for the C-Il devices on delta wings (data report) aircraft - A systems approach conducted in Langley 7- by 10-foot subsonic wind [AIAA PAPER 79-1796] A79-47883 tunnel An improved method for load survey flight testing [NASA-CR-159120] N79-31143 of military cargo aircraft BOUNDARY LAYER STABILITY [AIAA PAPER 79-1799] A19-47885 Mechanics of boundary layer transition, part 2: Blown wings from Kiev --- short takeoff and Instability and transition to turbulence landing through wing-overblowing [VKI-LECTURE-SERIES-3-PT-2] N79-31530 A79-49232

A-12

SUBJECT INDEX COMPETITION

Current Canadian developments related to low-speed Experimental Clean Combustor Program (ECCP), phase 3 heavy lift ACV commercial aircraft turbofan engine tests A79-49915 with double annular combustor CASCADE PLOW [NASA-CR-135384] N79-31207 On the influence of relative pitch in the subsonic COMBUSTION CONTROL turbine cascade The application of multiple swirl modules in the A79-48503 design and development of gas turbine combustors Aerodynamic excitation forces of blade vibrations [AIAA PAPER 79-1196] #79-47349 in axial turbomachinery as a result of Evaluation of airfield pavement materials based on interference from nearby cascades synthetic polymers A79-48572 #79-49348 CATASTROPHE THEORY Aircraft engine developments centre on improved Application of bifurcation analysis and performance, higher efficiency catastrophe theory methodology /BACTN/ to A79-50207 aircraft stability problems at high COMBUSTION EFFICIENCY angles-of-attack The application of multiple swirl nodules in the A79-47943 design and development of gas turbine combustors CH-47 HELICOPTER - [AIAA PAPER 79-1196] #79-47349 Helicopter high grain control COMBUSTION PHYSICS (NASA-CR-159052) 579-31221 Factors controlling stability of swirling flames CHARGE COUPLED DEVICES at diffusers in gas turbines A real time video bandwidth reduction system based A79-50209 on a CCD Hadamard transform device --- for COMBUSTION PRODUCTS avionics Evaluation of airfield pavement materials based on A79-48702 synthetic polymers CHORDS (GEOMETRY) #79-149348 On the influence of relative pitch in the subsonic Correlation technique for ambient effects on turbine cascade oxides of nitrogen --- from combustion products #79-48503 in atmospheric pollution CIRCUIT PROTECTION #79-49922 Airport power supply --- Russian book Ultrasonic method of gun gas detection --- for A79-50499 engine ingestion prevention in F-iS Lightning hazards overview: Aviation requirements A79-50166 and interests Critical assessment of emissions from aircraft 879-30876 piston engines CIRCULATION CONTROL ROTORS (AD-A071002] N79-30190 Flight testing the circulation control wing Electrical insulation fire characteristics. [AJAR PAPER 79-1791] #79-447880 Volume 2: Toxicity Design and development of a hybrid composite rotor [P8-294841/2] 579-30490 blade for the circulation control rotor system Recent advances in materials toxicology CARS 79-46] #79-49098 879-31169 The circulation control rotor flight demonstrator COMMAND AND CONTROL test program E-4B mission electrical power CARS 79-51] 879-49103 #79-48617 CIVIL AVIATION Dynamic simulator test and evaluation of a 3TIDS Aerospatiale AS.350 and AS.355 relative navigation system --- Joint Tactical A79-49814 Information Distribution System CLIMBING FLIGHT #79-48694 A lifting-surface method for hover/climb airloads Distributed TDHA - An approach to JIIDS phase II (ABS 79-3] R79-49056 Time Division Multiple Access Joint Tactical Linearization of the boundary-layer equations of Information Distribution System the minimum time-to-climb problem A79-49584 A79-149869 An advanced guidance and control system for rescue COAL GASIFICATION helicopters Lockheed urges hydrogen fuel 579-30217 #79-49224 COMMERCIAL AIRCRAFT COANDA EFFECT Design criteria for airline operation Flight testing the circulation control wing [AIRA PAPER 79-18(49) A79-49337 [AIAR PAPER 79-1791] #79-47880 Financing the capital requirements of the US Design of the circulation control wing SJOL airline industry in the 1980's demonstrator aircraft 579-30164 [AIAA PAPER 79-1842] A79-447909 Development of fire-resistant, low smoke Blown wings from Kiev --- short takeoff and generating, thermally stable end items for landing through wing-overbiowing commercial aircraft and spacecraft using a basic A79-49232 polyimide resin COCKPITS 879-31171 Real time weather display in the general aviation Experimental Clean Combustor Program (ECCP), phase 3 cockpit commercial aircraft turbofan engine tests (AIAA PAPER 79-1821] #79-47901 with double annular combustor COLLISION AVOIDANCE [RASA-CR-135384] 879-31207 A self contained collision avoidance system for COMMUNICATION EQUIPMENT helicopters Nultiband antenna --- for tactical naval aircraft N79-30206 A79-48596 COMBUSTIBLE FLOW E-4B mission electrical power Experimental study of the turbulent wake #79-48617 downstream of a fan jet COMMUNICATION NETWORKS A79-48507 A digital communication system as gateway between COMBUSTION CHAMBERS adjacent computerized air traffic control centres The application of multiple swirl modules in the 879-31463 design and development of gas turbine combustors Implementing JTIDS in tactical aircraft [AJAR PAPER 79-1196] A79-147349 N79-31491 Influence of gas turbine engine combustion chamber COMPETITION geometric parameters on mixture formation International Air Transportation Competition Act characteristics of 1978 --- congressional reports A79-48495 [GPO-34-912] 879-30168 Investigation of air stream from combustor-liner air entry holes, 3 [NASA-TM-75430] 879-31206

A-13

COMPLEX SYSTEMS SUBJECT INDEX

COMPLEX SYSTEMS CADAM data handling from conceptual design through Analysis design of complex systems. II --- for produce support simultaneous improvement of all basic prototype [AI#A PAPER 79-1846] 879-47912 flight vehicle performance characteristics INACT - Interactive test data analysis --- with A79-48505 minicomputers COMPONENT RELIABILITY A79-50430 F-16 Avionics Intermediate Shop /AIS/ Interim Modern systems for air traffic control Contractor Support initiatives A79-50921 [AIAA PAPER 79-1868] 879-47923 COMPUTER PROGRAMMING Helicopter component environmental vibration A Navy plan for the development of a practical testing - The poor man's fatigue test computer-aided programming /CAP/ system for [AilS 79-49) A79-49101 analog circuit test design Helicopter drive system B and N design guide A79-4887U [AD-8069691] 879-30181 Modal interpolation program, L215(INTERP) . Volume COMPOSITE MATERIALS 2: Supplemental system design and maintenance High-performance reinforced plastic structures for document --- to calculate displacements at civil aviation several points on an aerodynamic surface 879-47302 [NASA-CR-2848] 879-31147 Fatigue and fracture COMPUTER PROGRAMS 879-30315 Avionics computer software operation and support Mechanical and thermophysical properties of cost estimation graphite/polyimide ccmposite materials 879-48620 879-30317 Test implementation through support software - A The fluorenone polyester ISO FPE of Isovolta FIT translator --- automated Fault Isolation Company, Austria Tests on airborne radar system 879-31183 A79-48687 COMPOSITE STRUCTURES The impact of software in automatic test equipment Composite helicopter tail booms for evaluation of radar analog to digital [AHS 79-9] 879-49061 converter Model 206L composite litter door 879-48691 (AilS 79-311 A79-49083 Testability, the key to economical and Automatic scanning inspection of composite operationally effective avionic test software helicopter structure using an advanced A79-48890 technology fluoroscopic system F-16 depot automatic test equipment [AilS 79-35] 879-49087 A79-48895 Certification of composites in civil aircraft Role of Numerical Control Design in the computer [AilS 79-431 879-49095 aided design/manufacturing interface at Sikorsky Qualification program of the composite main rotor [Ails 79-301 A79-49082 blade for the Model 214B helicopter A computer program for aircraft identification and [AilS 79-44] 879-49096 derivative extraction Operation and test of composite horizontal 879-50306 stabilizer for the Sikorsky Spirit helicopter Naval aircraft operating and support (AHS 79-45] A79-49097 cost-estimating model, FT 1977 revision Ultra-high-modulus graphite-epoxy conical shell [AD-A068175] 879-30140 development, supplement Maintenance improvement: An analysis approach [AD-A069795J 879-30335 including inferential technical data --- naval Thermal characteristics of 3501-6/AS and 5208/T300 aircraft graphite epoxy composites [AD-A068382] N79-30141 [AD-A071067] 879-31357 Driftdown calculations for the FH/227D aircraft COMPRESSOR BLADES [SAND-78-1807] R79-30182 Aerodynamic performance of 1.38-pressure-ratio, Dynamic loads analysis system (DYLOFLEX) summary. variable-pitch fan stage Volume 1: Engineering formulation [NASA-TP-1502] 879-31213 [NASA-CR-2846-1 ] N79-31144 COMPRESSOR EFFICIENCY Dynamic loads analysis system (DYLOFLEX) summary. Laser velocimeter applied to the study of circular Volume 2: Supplemental system design information distorsion effects in a low speed compressor [NASA-CR-2846-2] N79-31145 [08888, IP NO. 1979-30] 879-50925 A program to compute three-dimensional subsonic COMPRESSOR MOTORS unsteady aerodynamic characteristics using the Performance of two-stage fan with a first-stage doublet lattice method, L216 (DUBFLEX). Volume rotor redesigned to account for the presence of 2: Supplemental system design and maintenance a part-span damper document [NASA-TP-1483] N79-30191 [NASA-CR-2850] 879-31148 COMPUTATIONAL FLUID DYNAMICS ATLAS, an integrated structural analysis and The calculation of non-linear aerodynamic design system. Volume 5: System demonstration characteristics of wings and their wakes in problems subsonic flow [NASA-CR-159045] N79-31624 A79-47099 COMPUTER SYSTEMS DESIGN Fully conservative numerical solutions for 31105 relative navigation - Architecture, error unsteady irrotational transonic flow about characteristics and operational benefits airfoils Joint Tactical Information Distribution System [AIAA PAPER 79-1555] 879-47342 A79-48715 Aerodynamics of spoiler control devices A computer system for identifying aircraft [AIAA PAPER 79-1873] 879-47925 characteristics An integrated analytical and experimental A79-50168 investigation of helicopter hub drag Modern systems for air traffic control [AilS 79-5] 879-49058 A79-50921 Numerical solution of the problem of unsteady Central flow control software design document. supersonic flow around the front part of the Volume 1: Operational software complex wings with a detached shock wave automation support to the Air Traffic Control A79-49456 System Command Center Dynamic loads analysis system (DYLOFLEX) summary. [AD-A070973] 879-30959 Volume 2: Supplemental system design information Central flow control software design document. (NASA-CE-2846-2] 879-31145 Volume 2: Support software complex COMPUTER GRAPHICS automation support to the Air Traffic Control Geometric data transfer --- for computerized System Command Center. aircraft engineering drawings [AD-A070771] N79-30960 [AIAA PAPER 79-1844] 879-47910

8-14

SUBJECT INDEX CONICAL BODIES

Nodal interpolation program, L215(INTJ4RP). Volume Ellipsoidal modelling of aircraft targets for 2: Supplemental system design and maintenance evaluation of electronic fuzes document --- to calculate displacements at A79-49580 several points on an aerodynamic surface A simulation of amphibious hovercraft overturning [NASA-CE-2848] 4479-311147 A79-49904 Equation modifying program, L219 (EQNOD) . Volume Performance predictions for open ocean air cushion 2: Supplemental system design and maintenance vehicles and surface effect ships document 879-49905 [NASA-CR-2856] 879-31153 A computer system for identifying aircraft Time history solution program, L225 (1EV126). characteristics Volume 2: Supplemental system design and A79-50168 maintenance document for airplane dynamic ONERA'S model of the pilot in discrete time response using frequency response data 879-30242 [NASA-cR-2860) N79-311511 The design of digital controllers for the C-141 A program for calculating load coefficient aircraft using entire eigenstructure assignment matrices utilizing the force summation method, and the development of an interactive computer L218 (LOADS) . Volume 2: Supplemental system design program design and maintenance document AD-A069192] 879-31224 [NASA-CR-2854] 879-31155 Tactical performance characterization basic COMPUTER SYSTEMS PROGRAMS methodology The effect of standardization of avionics software [80-8069297] 879-31235 quality assurance Investigation on information error caused by 879-486148 traffic loading in approach and landing systems Automatic test software for calibrating strapdown 4479-31480 systems CONCORDE AIRCRAFT A79-48689 Results related to simulated and in-flight E-3A sentry /AWACS/ ATPG --- Automatic Test experimentation with an electric flight control Program Generation system that can be generalized A79-48873 N79-30224 Central flow control software design document. A comparison of predictions obtained from wind Volume 1: Operational software complex tunnel tests and the results from cruising automation support to the Air Traffic Control flight: Airbus and Concorde --- conferences System Command Center [NASA-TM-75238] 4479-31136 [AD-A070973] N79-30959 Supersonic transport vis-a-vis energy savings Central flow control software design document. [NASA-TN-75464] 879-31163 Volume 2: Support software complex CONDUCTIVE HEAT TRANSFER automation support to the Air Traffic Control Most rational linearization of nonlinear unsteady System Command Center. heat conduction problems --- for flight vehicle (AD-A070771] 879-30960 parts and engines COMPUTER TECHNIQUES A79-48501 Computer-assisted high-speed balancing of 153 and Evaluation of finite element formulations for T55 power turbines transient conduction forced-convection analysis [MIS 79-361 A79-149088 A79-49343 A simplified gross thrust computing technique for CONFERENCES an afterburning turbofan engine The Guidance and control of Helicopters and V/SIOL A79-50440 aircraft at night and in poor visibility COMPUTERIZED DESIGN AGARD-CP-258] 4479-30198 Solution of the inverse aerodynamics problem by Stability and control --- conferences the random search method [AGAND-CP-260] 4479-30218 A79-47002 A comparison of predictions obtained from wind Engineering and manufacturing communication via tunnel tests and the results from cruising the computer data base flight: Airbus and Concorde --- conferences [AIAA PAPER 79-1885] 879-47911 (NASA-TM-75238] 4479-31136 CADAM data handling from conceptual design through Conference on Fire Resistant Materials: A produce support compilation of presentations and papers [AIAA PAPER 79-1846] 879-87912 [NASA-CP-2094] 4479-31166 Microprocessor-based digital autopilot development CONFIGURATION MANAGEMENT for the XBQM-106 Mini-RPV Identifying desirable design features for the C-XX A79-48608 aircraft - A systems approach A system for interdisciplinary analysis - A key to [AIAA PAPER 79-1796] 879-147883 improved rotorcraft design CADAM data handling from conceptual design through [MIS 79-8] 879-49060 produce support Role of Numerical Control Design in the computer [AIAA PAPER 79-1846] A79-47912 aided design/manufacturing interface at Sikorsky Runway configuration management system concepts [ABS 79-30] 879-449082 [80-8069960] 4479-31234 Application of finite-element and holographic CONFORMAL NAPPING techniques in the design of turboshaft engine Analytic formulas for wing profile aerodynamic components characteristics in incompressible flow [AHS 79-41] A79-49093 Evaluation of finite element formulations for CONGRESSIONAL REPORTS transient conduction forced-convection analysis International Air Transportation Competition Act 879-49343 of 1978 --- congressional reports Recent applications of theoretical analysis to [GPO-34-912] 879-30168 V/STOL inlet design Enforcer aircraft A79-49530 [GPO-32-569] 4479-30174 The design of digital controllers for the C-141 CONICAL BODIES aircraft using entire eigenstructure assignment Overall aerodynamic characteristics of caret and and the development of an interactive computer delta wings at supersonic speeds design program 879-47012 [80-8069192] 4479-31224 Radiation from quarter-wavelength monopoles on COMPUTERIZED SIMULATION finite cylindrical, conical, and rocket-shaped C ADAM data handling from conceptual design through conducting bodies --- airborne antenna design produce support A79-50606 (AIAA PAPER 79-1846] 879-147912 Ultra-high-modulus graphite-epoxy comical shell Verification of operational flight programs by development, supplement simulation [80-8069795] 4479-30335 A79-48667

8-15

CONSISTENCY SUBJECT INDEX

CONSISTENCY Synthesis of digital flight control tracking Achieving consistency in the production of systems by the method of entire eigenstructnre critical jet engine components by means of press assignment forging A79-48625 A79-48945 Piloted simulator investigation of helicopter CONTINUOUS WAVE RADAR control systems effects on handling qualities The servoed modulation PMcW radar altimeters in during instrument flight military applications [AHS 79-26] 1479-49078 A79-49589 An evaluation of sidestick force/deflection CONTOURS characteristics on aircraft handling qualities Determining the contour of helicopter rotor blades 1479-50428 automatically using electro-optical techniques Stbility and control --- conferences (ABS 79-32] 1479-49084 (AGARD-CP-260) 1479-30218 CONTRACT BANAGENENT Structural aspects of active controls Avionics design for testability - An aircraft 1479-30221 contractor -s viewpoint CONTROL STICKS A79-48888 Comment on Plight test of stick force stability CONTRACTORS in attitude-stabilized aircraft F-16 Avionics Intermediate Shop /AIS/ Interim A79-49925 Contractor Support initiatives An evaluation of sidestick force/deflection (AIAA PAPER 79-1868] 1479-47923 characteristics on aircraft handling qualities CONTROL BOARDS 1479-50428 Design procedure for aircrew station labeling CONTROL SURFACES selection and abbreviation Benefits of aerodynamic interaction to the three 1479-30208 surface configuration The impact of a multi-function programmable [AIAA PAPER 79-1830] 1479-47904 control display unit in affecting a reduction of The Dc-9 Super 80 - Much more than a simple stretch pilot workload A79-49223 1479-30210 Wind-tunnel investigation of an armed mini CONTROL CONFIGURED VEHICLES remotely piloted vehicle --- conducted in From HiNAT to future fighters --- Highly Langley V/STOL tunnel Maneuverable Aircraft Technology assessment (NASA-TN-80132] 1479-31151 (AIAA PAPER 79-1816] A79-47896 CONTROL THEORY A microprocessor system for flight control research Analysis design of complex systems. II --- for A79-48623 simultaneous improvement of all basic prototype Application of Lagrange Optimization to the drag flight vehicle performance characteristics polar utilizing experimental data 1479-48505 [AIAAPAPER 79-1833] 1479-49335 VTOL controls for shipboard landing A computer program for aircraft identification and (NASA-CR-162140) 1479-30193 der ivative extraction Helicopter high grain control 1479-50306 [NASA-CH-159052] 1479-31221 Stability and control --- conferences Investigation of inverse Vandermonde matrix [AGARD-c p-260] 1479-30218 calculation for linear system applications Systems implications of active controls adaptive flight control systems 1479-30219 [AD-A069241] 1479-31225 Structural aspects of active controls Path controllers: Unification of concepts and N79-30221 comparison of design methods Enhanced fighter mission effectiveness by use of [AD-A070252] 1479-31227 integrated flight systems CONTROL VALVES 1479-30223 Fluidics: Feasibility study Improvement of fighter aircraft maneuverability electro/hydraulic/fluidic direct drive servo valve through employment of control configured vehicle [AD-A069798] 1479-30195 technology CONTROLLABILITY N79-30225 Spirit helicopter handling qualities design and Stability and control aspects of the cCv-F104c development N79-30234 [AilS 79-24] 1479-49076 Design guidance from fighter ccv flight evaluations Handling quality and display requirements for low 1479-30235 speed and hover in reduced flight visibility A simulator investigation of handling quality [AilS 79-29] A79-49081 criteria for ccv transport aircraft The influence of engine/fuel control design on 1479-30240 helicopter dynamics and handling qualities CONTROL EQUIPMENT (AilS 79-37] 1479-49089 The equipment-system interface in an antitank Flight experiments to evaluate the effect of helicopter at night wing-tip sails on fuel consumption and handling 1479-30211 characteristics Flight experience with advanced controls and 1479-49818 displays during piloted curved decelerating A simulator investigation of handling quality approaches in a powered-lift STOL aircraft criteria for ccv transport aircraft 1479-30243 1479-30240 Helicopter high grain control Bide qualities criteria validation/pilot (NASA-cR-159052] 1479-31221 performance study: Flight test results CONTROL SIMULATION [NASA-CE-144885] 1479-31193 Predictive guidance for interceptors with time Analysis of a lateral pilot-induced oscillation delays experienced on the first flight of the YF-16 1479-47939 aircraft A status report on the advanced FIREFLY assessment [NASA-TM-72867] 1479-31220 program A compilation and analysis of helicopter handling 1479-48609 qualities data. Volume 2: Data analysis Results related to simulated and in-flight (RASA-cR-3145] N79-31222 experimentation with an electric flight control CONTROLLERS system that can be generalized Investigations on the design of active vibration N79-30224 isolation systems for helicopters with rigid and CONTROL STABILITY elastic modeling of the fuselage An improved method for load survey flight testing [DLI4-FB-78-04] 1479-30183 of military cargo aircraft An in-flight controller insensitive to parameters [AIAA PAPER 79-1799] 1479-47885 variation Benefits of aerodynamic interaction to the three [DLR-FB-78-07] N79-30197 surface configuration [AIAA PAPER 79-1830] A79-47904

A-16 DC 9 AIRCRAFT SUBJECT INDEX

CONVERGENT-DIVERGENT NOZZLES CUSHIONS Experiments of shock associated noise of Seat cushion to provide realistic acceleration supersonic jets cues to aircraft simulator pilot N79-31228 [6166 PAPER 79-1526) 679-47341 [NASA-CASE-LAR-12149-2] CONVEYORS CYLINDRICAL ANTENNAS A combined air-cushion and endless belt Small lightweight electronically steerable cylindrical antenna successfully utilized in an transportation system 679-49911 air traffic management system A79-48597 COOLING SYSTEMS Drag reduction by cooling in hydrogen-fueled CYLINDRICAL BODIES Radiation from quarter-wavelength monopoles on aircraft 679-49921 finite cylindrical, conical, and rocket-shaped conducting bodies --- airborne antenna design COORDINATE TRANSFORMATIONS 679-50606 Complex guaternion notation in coordinate transformations --- missile launching aircraft-inertial space transformations 679-48681 CORRECTION DAMPING Wall corrections in transonic wind tunnel: Theoretical flap-lag damping with various dynamic Equivalent porosity inflowmodels [ABS 79-20] A79-49073 [ESA-TT-545] N79-30287 COST EFFECTIVENESS DATA ACQUISITION A cheap, effective icing detector for general Some flight data extraction techniques used on a general aviation spin research aircraft aviation aircraft #79-47887 (AIAA PAPER 79-1823] 679-47902 [AIAA PAPER 79-1802) A computer system for identifying aircraft COST ESTIMATES Air buoyant vehicles - Energy efficient aircraft characteristics A79-50168 [AIAA PAPER 79-1862] A79-47919 Avionics computer software operation and support DATA BASES cost estimation Engineering and manufacturing communication via #79-48620 the computer data base #79-47911 Lockheed urges hydrogen fuel (AIAA PAPER 79-1845] A79-49224 Analysis of wind tunnel data pertaining to high Aircraft engine developments centre on improved angle of attack aerodynamics. Volume 2: Data performance, higher efficiency base A79-50207 (AD-A069647] P79-30149 Maintenance cost study of rotary wing aircraft, DATA COMPRESSION A real time video bandwidth reduction system based phase 2 on a CCD Badamard transform device --- for (NASA-CR-152291] N79-30138 Naval aircraft operating and support avionics A79-48702 cost-estimating model, FT 1977 revision Real time compression of video signals (AD-A068175] N79-30140 protection against jamming COST REDUCTION A79-48712 New versus existing engines for new helicopter systems - A life cycle cost view DATA CORRELATION Correlation of data related to shock-induced [#166 PAPER 79-1316] A79-47348 A Navy plan for the development of a practical trailing-edge separation and extrapolation to computer-aided programming /CAP/ system for flight Reynolds number N79-31195 analog circuit test design [NASA-CR-3178] A79-48870 DATA LINKS Ten years of Aerospatiale experience with the JTIDS relative navigation - Architecture, error fenestron and conventional tail rotor characteristics and operational benefits [AHS 79-58] #79-49108 Joint Tactical Information Distribution System Small hovercraft design - Evolution to simplicity #79-48715 A79-49906 An asynchronous data transmission system with low Derivative engines for the 1980s will help limit error probability for the SETAC landing aid N79-31468 acquisition and maintenance costs A79-50206 Performance predictions and trials of a helicopter Flight test technology development - A preview of UHF data link N79-31476 DysoTech --- dynamic modeling A79-50435 DATA MANAGEMENT Geometric data transfer --- for computerized CRACK PROPAGATION Effect of transport/bomber loads spectrum on crack aircraft engineering drawings #79-47910 growth (AIAA PAPER 79-1844] [AD-A069287] N79-31197 DATA PROCESSING A user's manual for a computer program to generate INACT - Interactive test data analysis --- with fatigue spectrum loading sequences minicomputers A79-50430 (AD-A069288) N79-31198 AFFTC parameter identification experience --- Air CRASH LANDING crashworthy armored crewseat for the UH-60A Black Force Flight Test Center aircraft flight testing A79-50434 Hawk (ASS 79-101 A79-49062 DATA SYSTEMS Fuselage ventilation under wind conditions Realization of a helicopter-oriented real-tine N79-31175 data system for research, experimental, and prototype flight testing CRASHES Special investigation report: Wing failure of (AilS 79-501 #79-49102 Boeing 747-131 near Madrid, Spain, 9 May 1976 Aeronautical information data subsystems /AIDS/ A79-50920 [NTSB-AAR-78-12] N79-30167 DATA TRANSMISSION CRITERIA # simulator investigation of handling quality Distributed TUNA - An approach to3TIDS phase II criteria for ccv transport aircraft Time Division Multiple Access Joint Tactical N79-30240 Information Distribution System A79-49584 CROSS COUPLING Considerations in the analysis of flight test A digital communication system as gateway between adjacent computerized air traffic control centres maneuvers A79-50433 N79-31463 DC 9 AIRCRAFT CRUISING FLIGHT Aircraft longitudinal motion at high incidence The DC-9 Super 80 - Much more than a simple stretch A79-48052 #79-49223

6-17 DEAD RECKONING SUBJECT INDEX

DEAD RECKONING DIGITAL DATA A simple integrated navigation based on multiple DEE State of the art is digital signal processing with [DGLR PAPER 79-0111] 879-48640 applications to multiple access systems DECODERS N79-31487 Performance of a pulse-decode circuit in the DIGITAL NAVIGATION presence of interference Digital adaptive control laws for VTOL aircraft A79-48713 DECODING A79-48000 Microcomputer applications in strapdown heading Performance of a pulse-decode circuit in the and attitude reference system presence of interference A79-48606 179-118713 Microprocessor-based digital autopilot development DECOUPLING for the XBQM-106 Mini-RPV Nonlinear decoupled control synthesis for maneuvering aircraft A79-48608 A simple integrated navigation based on multiple DEE 179-47959 [DGLR PAPER 79-041] DEFENSE PROGRAM #79-48640 JTIDS relative navigation - Architecture, error Enforcer aircraft [GPO-32-569] characteristics and operational benefits N79-30174 Joint Tactical Information Distribution System DEGREES OF FREEDOM 179-48715 On single-degree-of-freedom flutter induced by DIGITAL RADAR SYSTEMS activated controls Built in test of A/D converters - Present A79-49867 approaches and recommendations for improved BIT Flutter analysis of two-dimensional and effectiveness --- in airborne radar systems two-degree-of-freedom airfoils in A79-48621 small-disturbance, unsteady transonic flow Digital sensor simulation at the Defense Mapping [AD-A069223) N79-31157 Agency Aerospace Center DELTA WINGS Overall aerodynamic characteristics of caret and A79-48705 Combined I/Na-band tracking radar delta wings at supersonic speeds A79-49565 879-47012 Automated tracking for aircraft surveillance radar The calculation of non-linear aerodynamic systems characteristics of wings and their wakes in 179-49604 subsonic flow DIGITAL SIMULATION A79-47099 Digital simulation of a three-phase generator Solution of a mixed boundary value problem for flow past a thin delta wing A79-48618 A developmental computer model for investigations A79-49882 of air traffic management problems: A case Subsonic wind-tunnel investigation of leading-edge investigating two decision strategies devices on delta wings (data report) [ AD-A071075] N79-31189 conducted in Langley 7- by 10-foot subsonic wind DIGITAL SYSTEMS tunnel F/A-is Hornet display system [NASA-CE-159120] 879-31143 Lateral aerodynamics extracted from flight test A79-48630 NASA/Princeton digital avionics flight test facility using a parameter estimation method CARL-AERO-NOTE-380] A79-49344 N79-31146 The development and in-flight evaluation of a DESIGN ANALYSIS triplex digital autostabilization system for a Developments in gear analysis and test techniques helicopter for helicopter drive systems [ASME PAPER 79-DE-15] 879-47654 The impact of a multi-function programmable 879-30200 Design, analysis, and testing of a new generation control display unit in affecting a reduction of tail rotor pilot workload [AilS 79-57] A79-49107 Performance of current radar systems in an EW 879-30210 New devices for digital communications in avionics environment --- Electronic Warfare N79-31481 A79-49555 Transform domain processing for digital The Bell Model 222 communication systems using surface acoustic 879-49816 wave devices DIESEL ENGINES N79-31482 An overview of NASA research on positive DIGITAL TECHNIQUES displacement type general aviation engines An analysis of SAPPHIRE image parameters as a (NASA-TM-79254] 879-31210 function of processing parameters --- for DIFFUSERS synthetic aperture radar data processing Factors controlling stability of swirling flames at diffusers in gas turbines 879-48666 The design of digital controllers for the C-141 179-50209 aircraft using entire eigenstructure assignment DIFFUSION WELDING - and the development of an interactive computer Superplastic forming diffusion bonding of titanium design program helicopter airframe components [AD-A069192] CARS 79-33) 879-31224 #79-49085 Laboratory development of computer generated image DIGITAL COMMAND SYSTEMS displays for evaluation in terrain flight training Flight control systems development of highly [AD-1070065] N79-31236 maneuverable aircraft technology /HiNAT/ vehicle DIRECTIONAL CONTROL [AIAA PAPER 79-1789] 179-47878 The DG-800 - A rugged, high performance heading Flight test verification of the ASSET system reference unit --- directional gyro design Advanced Skewed Sensory Electronic Triad considerations A79-48622 A79-48677 A microprocessor system for flight control research Analytical and experimental investigation of #79-48623 V-type empennage contribution to directional Synthesis of digital flight control tracking control in hover and forward flight systems by the method of entire eigenstructure [INS 79-56) 179-49106 assignment DISPLAY DEVICES 179-48625 Real time weather display in the general aviation DIGITAL COMPUTERS cockpit Analysis and evaluation of current MIL-STD-1553 [AIAA PAPER 79-1821] 179-47901 digital avionics architecture as the basis for A real time video bandwidth reduction system based advanced architectures using NIL-STD-1553B on a CCD Hadamard transform device --- for A79-48629 avionics A79-48702

A-18 SUBJECT INDEX DYNAMIC STRUCTURAL ANALYSIS

Real time compression of video signals Subsonic wind-tunnel itivestigation of leading-edge protection against jamming devices on delta wings (data report) A79-48712 conducted in Langley 7- by 10-toot subsonic wind Multiplex technology applied to helicopters tunnel 879-31143 CARS 79-14] 479-49067 [NASA-CR-159120] Handling quality and display requirements for low DUAL THRUST NOZZLES speed and hover in reduced flight visibility The nonaxisymmetric nozzle - It is for real CARS 79-29] 479-49081 fighter aircraft performance viewpoint Research on visual display integration for [4144 PAPER 79-1810] 479-47893 advanced fighter aircraft Performance evaluation of an air vehicle utilizing [40-4069605] 879-30184 non-axisymmetric nozzles Scan converter and raster display controller for [4144 PAPER 79-1811] A79-47894 night vision display systems DUCTED PAN ENGINES 879-30203 The principles of hovercraft, powering and Design procedure for aircrew station labeling propulsion 479-97844 selection and abbreviation 879-30208 DUCTED FANS Project NAVTOLAND (Navy vertical takeoff and Aerodynamic effects of an attitude control vane on landing capability development) a tilt-nacelle V/STOL propulsion system 879-30212 (AIAA PAPER 79-1855] A79-47914 Implementation of flight control in an integrated Energy efficient aircraft engines guidance and control system [4144 PAPER 79-1861] 479-47918 879-30215 DYNAMIC CHARACTERISTICS Flight experience with advanced controls and Estimation of longitudinal aircraft displays during piloted curved decelerating characteristics using parameter identification approaches in a powered-lift STOL aircraft techniques 879-30243 479-50432 Reliability improvement warranty terms and DYNAMIC LCADS conditions for the Integrated Avionics Control Dynamic loads analysis system (DYLOFLEX) summary. Systems (XACS) Volume 1: Engineering formulation 1479-31144 (AD-A0694541 N79-31205 [NASA-CR-2846-1] DISTANCE MEASURING EQUIPMENT Dynamic loads analysis system (DYLOFLEX) summary. A simple integrated navigation based on multiple ORE Volume 2: Supplemental system design information 879-31145 [DGLR PAPER 79-041] 479-48640 [NASA-CR-2846-2] DITCHING (LANDING) DYNAMIC MODELS Aircraft accident report: Swift Aire Lines, Inc., Flight test technology development - A preview of Nord 262, N418SA, Marina Del Rey, California, DyfloTech --- dynamic modeling A79-50435 March 10, 1979 [NTSB-AAR-79-13] N79-31165 Enclosure fire dynamics model 879-31173 DOMES (STRUCTURAL FORMS) A report on the Sperry Dome Radar DYNAMIC RESPONSE A79-49567 Application of bifurcation analysis and DOPPLER RADAR catastrophe theory methodology /BACTM/ to Recent progress in aircraft sink rate measurement aircraft stability problems at high [AIAA PAPER 79-17983 479-47884 angles-of-attack Radar signal processing development for A79-47943 application of VHSI Improved method of predicting helicopter control A79-48664 response and gust sensitivity Combined environment reliability test of the [ARS 79-25] 479-49077 common strategic Doppler system Time history solution program, L225 (TEV126) 479-50368 Volume 2: Supplemental system design and Multipath propagation measurement by Doppler maintenance document --- for airplane dynamic technique response using frequency response data N79-31478 [NASA-CR-2860] 879-31154 Testing and analysis of dual-mode adaptive landing DOWNTIME Maintenance improvement: An analysis approach gear, taxi mode test system for YF-12A including inferential technical data --- naval [NASA-CR-144884] 879-31192 aircraft DYNAMIC STABILITY (AD-A0683823 N79-30141 A summary of AGARD FDP meeting on dynamic stability parameters --- advanced aircraft DRAG The principles of hovercraft, powering and performance at high angle of attack V79-30220 propulsion 479-47844 DYNAMIC STRUCTURAL ANALYSIS DRAG MEASUREMENT Simplified analysis spectrum for joints exposed to The size and performance effects of high lift complex continuously varying stresses system technology on a modern twin engine jet aerospace structures 479-47892 transport [AIAA PAPER 79-1808] [AIAA PAPER 79-1795] 479-49332 Application of bifurcation analysis and Performance modelling methods --- in flight test catastrophe theory methodology /BACTN/ to programs aircraft stability problems at high A79-50167 angles-of-attack A79-47943 DRAG REDUCTION Full-scale wind tunnel study of nacelle shape on Experimental measurements of the rotating cooling drag frequencies and mode shapes of a full scale [4144 PAPER 79-1820] A79-47900 helicopter rotor in a vacuum and correlations Laminar flow stabilization by surface cooling on with calculated results hydrogen fueled aircraft [AilS 79-18] 479-49071 [4144 PAPER 79-1863] A79-47920 Theoretical flap-lag damping with various dynamic Application of Lagrange Optimization to the drag inflow models polar utilizing experimental data [AilS 79-203 479-49073 [4144 PAPER 79-1833] A79-49335 Application of finite-element and holographic Wing geometry effects on leading-edge vortices techniques in the design of turboshaft engine [AIAP. PAPER 79-1672] 479-49341 components Drag reduction by cooling in hydrogen-fueled ABS 79-41] A79-49093 The circulation control rotor flight demonstrator aircraft 479-49921 test program [ABS 79-51] A79-49103

A-19

E-3A AIRCRAFT SUBJECT INDEX

An approach for estimating vibration Advanced BPV electrical systems characteristics of nonuniform rotor blades A79-48615 A79-49718 Electrical power system for new-technology INACT - Interactive test data analysis --- with transport power-by-wire airplane minicomputers A79-48616 A79-50430 Airport power supply --- Russian book Considerations in the analysis of flight test A79-50499 maneuvers ELECTRIC POWER TRANSMISSION A79-50433 Electric power system control techniques ATLAS, an integrated structural analysis and A79-48614 design system. Volume 5: System demonstration Electrical power system for new-technology problems transport power-by-wire airplane [ NASA-CR-159045] 879-31624 A79-48616 ELECTRICAL ENGINEERING Electric power system control techniques E A79-48614 E-3A AIRCRAFT Electrical power system for new-technology E-3A sentry /AWACS/ ATPG --- Automatic Test transport power-by-wire airplane Program Generation A79-48616 A79-48873 ELECTRICAL INSULATION E-4A AIRCRAFT Electrical insulation fire characteristics. E-4B mission electrical power Volume 2: Toxicity A79-48617 [PB-294841/2] 879-30490 ECONOMIC ANALYSIS ELECTRO-OPTICS Road fleet operation of air cushion assisted Determining the contour of helicopter rotor blades vehicles - An evaluation of technical and automatically using electro-optical techniques economic problems [ABS 79-32] A79-49084 A79-49910 Stabilizing electro-optical systems on helicopters ECONOMIC FACTORS 879-30216 International Air Transportation Competition Act ELECTROMAGNETIC PULSES of 1978 --- congressional reports Atmospheric Electricity Hazard (AEH) [GPO-34-912] 879-30168 [AD-A069338] 879-30169 Supersonic transport vis-a-vis energy savings ELECTROMECHANICAL DEVICES (NASA-TN-75464] 879-31163 Load spectrum measuring equipment. Part 1: ECONOMIC IMPACT Details of MK 1 system presently used to acquire Maintenance improvement: An analysis approach data in Wessex BK 318 helicopters including inferential technical data --- naval (ARL-MECH-ENG-NOTE-371] W79-31194 aircraft ELECTRONIC CONTROL (AD-A068382] 879-30141 Small lightweight electronically steerable EDDY CURRENTS cylindrical antenna successfully utilized in an Small signal compensation of magnetic fields air traffic management system resulting from aircraft maneuvers A79-48597 A79-49605 A summary of NASA/Air Force full scale engine RIGENVECTORS research programs using the F100 engine A new approach to the solution of large, full [NASA-TM-79267] 879-30188 matrix equations: A two-dimensional potential ELECTRONIC COUNTERMEASURES flow feasibility study Integrated CNI avionics --- ECM-resistant (NASA-CR-3173] 879-31533 Communication, Navigation and Identification EJECTION SEATS A79-48711 The Swedish approach to escape system testing Airborne microwave ECH A79-50427 A79-49554 ELAS TOME ES Performance of current radar systems in an EN The Sikorsky elastomeric rotor --- helicopter environment --- Electronic Warfare rotor bearings A79-49555 CABS 79-48] A79-49100 Ellipsoidal modelling of aircraft targets for ELASTOPLASTICITY evaluation of electronic fuzes The influence of the environment on the A79-49580 elastoplastic properties of adhesives in metal ELECTRONIC EQUIPMENT bonded joints --- In aircraft structures Automatic test program generation selection [ESA-TT-521] N79-30391 for aircraft structures ELECTRIC CONTROL A79-48690 Electric power system control techniques Performance of current radar systems in an EN A79-48614 environment --- Electronic Warfare Results related to simulated and in-flight A79-49555 experimentation with an electric flight control ELECTRONIC EQUIPMENT TESTS system that can be generalized Built in test of A/D converters - Present N79-30224 approaches and recommendations for improved BIT ELECTRIC GENERATORS effectiveness --- in airborne radar systems Electrical power system for new-technology A79-48621 transport power-by-wire airplane Microcomputer control of a test facility --- for A79-48616 avionics E-4B mission electrical power Al9-48672 A79-48617 Operational experience with the AN/ARN-131 Omega Digital simulation of a three-phase generator Navigation Set A79-48618 A79-48616 ELECTRIC MOTOR VEHICLES A Navy plan for the development of a practical All electric subsystems for next generation computer-aided programming /CAP/ system for transport aircraft analog circuit test design [AIAA PAPER 79-1832] A79-47906 A79-48870 ELECTRIC NETWORKS AN/OSM-449/V/ ATE for worldwide support of the P3 Airport power supply --- Russian book Orion A79-50499 A19-48884 ELECTRIC POWER SUPPLIES Can avionic testability requirements be enforced All electric subsystems for next generation A79-48881 transport aircraft Avionics design for testability - An aircraft [AIAA PAPER 79-1832] A79-47906 contractor's viewpoint Electric power system control techniques A79-48888 A79-48614

A-20

SUBJECT INDEX ENGINE TESTS

Avionics design for testability - A vendor's Derivative engines for the 1980s will help limit viewpoint acquisition and maintenance Costs A79-48889 A79-50206 Techniques for fault isolation ambiguity reduction Aircraft engine developments Centre on improved in military avionics performance, higher efficiency 879-48891 A79-50207 F-16 depot automatic test equipment QCSEE - The key to future short-haul air transport A79-48895 Quiet, Clean, Short-Haul Experimental Engine ELECTRONIC MODULES program Air Force modular automatic test equipment A79-50208 development program Gas turbines for flight vehicle engines: Theory, A79-48878 design, and calculation /Third review and ELECTROSTATIC GYROSCOPES enlarged edition/ --- Russian book Application of instrument rotation in the N73 A79-50421 standard inertial navigation system A summary of NASA/Air Force full scale engine #79-148696 research programs using the P100 engine Rapid reaction time techniques for a strapdown (NASA-TM-79267] 879-30188 navigator employing electrostatic gyro technology Energy efficient engine flight propulsion system 879-148697 preliminary analysis and design report ELEVATORS (CONTROL SURFACES) [NASA-CR-159487] 879-30189 Development of a fly-by-wire elevator for the Bell JT9D-70/59 improved high pressure turbine active Helicopter Textron 214ST clearance Control system --- for specific fuel [ABS 79-27] 879-49079 consumption improvement ENCLOSURES [NASA-CR-159661 ] 879-31208 Global enclosure fire modeling with applications Exhaust emissions characteristics for a general N79-31172 aviation light aircraft Teledyne Continental Enclosure fire dynamics model Motors TSIO-360-C piston engine 879-31173 [AD-A070010] 879-31211 ENERGY CONSERVATION Conceptual study of a turbojet/ramjet inlet Air buoyant vehicles - Energy efficient aircraft [NASA-TM-80141] 819-31215 [AIAA PAPER 79-1862] 879-47919 ENGINE FAILURE Energy efficient engine flight propulsion system Fault diagnosis of gas turbine engines by means of preliminary analysis and design report component characteristics determination NASA-CR-159487] N79-30189 A79-49806 JT9D-70/59 improved high pressure turbine active ARIA takeoff performance flight test program clearance control system --- for specific fuel Advanced Range Instrumented Aircraft consumption improvement A79-50437 [NASA-CR-159661] 4479-31208 385-CAN-15 compressor stall and flameout ENERGY POLICY investigation Supersonic transport vis-a-vis energy savings A79-50441 [NASA-TM-75464] 879-31163 ENGINE INLETS .JT9D-70/59 improved high pressure turbine active J85-CAN-15 compressor stall and flameout clearance control system --- for specific fuel investigation consumption improvement A79-50441 [NASA-CR-159661] 879-31208 A flow field study for top mounted inlets on ENERGY TECHNOLOGY fighter aircraft configurations Utilization of alternative fuels for [AD-A069732] 879-30151 transportation; Proceedings of the Symposium, Conceptual study of a turbojet/ramjet inlet University of Santa Clara, Santa Clara, Calif., [NASA-TM-801141] N79-31215 June 19-23, 1978 ENGINE MONITORING INSTRUMENTS A79-49376 A simplified gross thrust computing technique for ENERGY TRANSFER an afterburning turbofan engine Global enclosure fire modeling with applications A79-50'440 N79-31172 Aircraft turbine engine monitoring experience: ENGINE CONTROL Implications for the P100 engine diagnostic Estimation for advanced technology engines system program A79-47957 [AD-A069282] 879-31217 The influence of engine/fuel control design on ENGINE NOISE helicopter dynamics and handling qualities Duct noise radiation through a jet flow (AHS 79-37) #79-49089 879-50110 Development of a 'no adjustment turboshaft engine Noise generation by jet-engine exhaust deflection control system [DLR-PB-78-21 ] 879-30192 [AHS 79-42] A79-49094 ENGINE TESTING LABORATORIES ENGINE DESIGN A summary of NASA/Air Force full scale engine Optimal thermogasdynamic design of gas turbine research programs using the P100 engine engines using element prototypes. I [NASA-TM-79267] 879-30188 #79-446997 ENGINE TESTS Gas turbines for ACV's and hydrofoils Statistical diagnostics of aircraft engines A79-47845 A79-46996 Jet propulsion for ACV's and hydrofoils Aerospatiale AS.350 and AS. 355 879-478147 A79-49814 Energy efficient aircraft engines Correlation technique for ambient effects on [8188 PAPER 79-1861] 879-47918 oxides of nitrogen --- from combustion products Influence of gas turbine engine combustion chamber in atmospheric pollution geometric parameters on mixture formation A79-49922 characteristics A summary of NASA/Air Force full scale engine A79-48495 research programs using the P100 engine Application of finite-element and holographic NASA-TM-79267] 879-30188 techniques in the design of turboshaft engine Critical assessment of emissions from aircraft components piston engines [-ABS 79-441] #79-49093 [AD-A071002] N79-30190 Development of a 'no adjustment turboshaft engine Experimental Clean Combustor Program (ECCP), phase 3 control system commercial aircraft turbofan engine tests [ABS 79-42] A79-49094 with double annular combustor Characterization of a swept-strut hydrogen [NASA-CR-135384] 879-31207 fuel-injector for scramjet applications Aerodynamic performance of axial-flow fan stage A79-49345 operated at nine inlet guide vane angles --- to be used on vertical lift aircraft [NASA-TP-1510] 879-31214

A-21

ENGINEERING DRAWINGS SUBJECT INDEX

ENGINEERING DRAWINGS Exhaust emissions characteristics for a general Geometric data transfer --- for computerized aviation light aircraft Teledyne Continental aircraft engineering drawings Rotors TSIO-360-C piston engine [8188 PAPER 79-18441 879-47910 (AD-A070010] 879-31211 ENVIRONMENT SIMULATION Ambient correction factors for aircraft gas Dynamic simulator test and evaluation of a JTIDS turbine idle emissions relative navigation system --- Joint lactical [AD-A069240) 879-31218 Information Distribution System EXHAUST NOZZLES 879-48694 Aerodynamic and acoustic investigation of inverted ENVIRONMENTAL TESTS velocity profile coannular exhaust nozzle models Helicopter component environmental vibration and development of aerodynamic and acoustic testing - The poor mans fatigue test prediction procedures, comprehensive data [ABS 79-49] 879-49101 report, volume 1 Combined environment reliability test of the [NASA-CH-159515] 879-30185 common strategic Doppler system Aerodynamic and acoustic investigation of inverted A79-50368 velocity profile coannular exhaust nozzle models The influence of the environment on the and development of aerodynamic and acoustic elastoplastic properties of adhesives in metal prediction procedures, comprehensive data bonded joints --- In aircraft structures report, volume 2 (ESA-TT-521) 879-30391 (NASA-CR-159516) 879-30186 Ambient correction factors for aircraft gas Aerodynamic and acoustic investigation of inverted turbine idle emissions velocity profile coannular exhaust nozzle models [AO-A069240] 879-31218 and development of aerodynamic and acoustic EPDXY RESINS prediction procedures Model 206L composite litter door [NASA-CR-3168] 879-31212 [ABS 79-31) 879-49083 EXHAUST SYSTEMS Ultra-high-modulus graphite-epoxy conical shell Full-scale wind tunnel study of nacelle shape on development, supplement cooling drag [AD-A069795) 879-30335 [AIAA PAPER 79-1820] A79-47900 EQUATIONS OF NOTION EXTERNAL STORE SEPARATION The enhancement of aircraft parameter Separation testing of large weapons from the B-i identification using linear transformations bomber for stability A79-50429 879-47961 EXTERNAL STORES Equation modifying program, L219 (EQNOD). Volume Active external store flutter suppression in the 2: Supplemental system design and maintenance YF-17 flutter model document A79-49866 NASA-CB-2856] 879-31153 A helicopter high definition rotor blade radar Flutter analysis of two-dimensional and N79-30207 two-degree-of-freedom airfoils in EXTERNALLY BLOWN FLAPS small-disturbance, unsteady transonic flow A method of the theory of airfoil profiles with a AD-A069223] N79-31157 jet flap Investigation of roll performance for a highly A79-471 19 nonlinear statically unstable fighter-type EXTREMELY HIGH FREQUENCIES aircraft Combined X/Ka-band tracking radar [AD-A069301] 879-31199 A79-49565 ERROR ANALYSIS Investigation on information error caused by traffic loading in approach and landing systems 879-31480 F-4 AIRCRAFT ERROR CONNECTING CODES A study of the application of singular An asynchronous data transmission system with low perturbation theory --- development of a real error probability for the SETAC landing aid time algorithm for optimal three dimensional 879-31468 aircraft maneuvers ERROR DETECTION CODES [NASA-CR-3167] 879-30194 Built in test of 8/U converters - Present F-S AIRCRAFT approaches and recommendations for improved BIT Analysis of wind tunnel data pertaining to high effectiveness --- in airborne radar systems angle of attack aerodynamics. Volume 1: A79-48621 Technical discussion and analysis or results Evaluation of the radar altimeter reference method AD-A069646] 879-30148 for determining altitude system positioning errors F-B AIRCRAFT A79-50436 Systems implications of active controls ESCAPE SYSTEMS U79-30219 The Swedish approach to escape system testing F-iS AIRCRAFT 879-50427 Evolving methods for reducing avionics data in an ESTIMATING 81SF environment --- Avionics Integration Estimation for advanced technology engines Supp port Facility flight program testing A79-47957 A79-48671 Estimation of aircraft target motion using pattern Ultrasonic method of gun gas detection --- for recognition orientation measurements engine ingestion prevention in F-15 A79-47987 879-50166 EXHAUST DIFFUSERS F-16 AIRCRAFT Self-contained grease lubrication systems for F-16 Avionics Intermediate Shop /AIS/ Interim aircraft applications Contractor Support initiatives (ABS 79-39) 879-49091 [AIAA PAPER 79-1868] 879-47923 EXHAUST GASES F-16 avionics maintenance concept and Ultrasonic method of gun gas detection --- for multinational aspects engine ingestion prevention in F-15 A79-48894 A79-50166 F-16 depot automatic test equipment Critical assessment of emissions from aircraft 879-48895 piston engines The evolution of the high-angle-of-attack features [80-8071002] 879-30190 of the F-16 flight control system Exhaust emission traverse investigation of a A79-50438 JT3D-1 turbofan engine --- to acquire exhaust Systems implications of active controls nozzle emission sample N79-30219 AD-A0720191 879-31209

8-22

SUBJECT INDEX FIGHTER AIRCRAFT

F-17 AIRCRAFT FEASIBILITY ANALYSIS Engine-aircraft afterbcdy interactions - A new approach to the solution of large, full Recommended testing techniques based on YF-17 matrix equations: A two-dimensional potential experience flow feasibility study [AIAA PAPER 79-1829) A79-47903 [14ASA-CR-3173] N79-31533 Active external store flutter suppression in the FEEDBACK CONTROL YF-17 flutter model Estimation for advanced technology engines A79-49866 A79-q7957 F-18 AIRCRAFT Nonlinear decoupled control synthesis for F/A-18 Hornet display system maneuvering aircraft A79-48630 A79-47959 Testing the F-18 at the U.S. Naval Air lest Center A study of the application of singular A79-50444 perturbation theory --- development of a real F-104 AIRCRAFT time algorithm for optimal three dimensional An investigation of the rolling stability aircraft maneuvers derivatives of a I-tail fighter configuration at [NASA-CR-3167] N79-30194 high angles-of-attack Open/closed loop identification of stability and A79-50165 control characteristics of combat aircraft Stability and control aspects of the CCV-F104C N79-30232 N79-30234 Helicopter high grain control F-ill AIRCRAFT [NASA-CR-159052] N79-31221 A force and moment test of a 1/24-scale F-ill FIBER COMPOSITES model at Each numbers from 0.7 to 1.3 Model 206L composite litter door [AD-A070192] N79-31156 CARS 79-31] A79-49083 Evaluation of F-ill weapon bay aero-acoustic and Certification of composites in civil aircraft weapon separation improvement techniques CARS 79-43] A79-49095 [AD-A070253] N79-31203 FIBER OPTICS FAIL-SAFE SYSTEMS Helmet mounted display and sight development Analytic redundancy for flight control sensors on CARS 79-171 A79-49070 the Lockheed L-1011 aircraft FIBER ORIENTATION A79-47960 Metal-matrix composite structures Failure detection in signal processing and sensing CABS 79-34] A79-49086 in flight control systems FIGHTER AIRCRAFT A79-47971 Analysis of optimal loop and split-S by energy FAILURE ANALYSIS state modeling Failure detection in signal processing and sensing A79-47098 in flight control systems Design of advanced titanium structures --- for A79-47971 Advanced Tactical Systems aircraft fuselage Test implementation through support software - A [AIAA PAPER 79-1805] A79-47890 FIT translator --- automated Fault Isolation The nonaxisymmetric nozzle - It is for real Tests on airborne radar system fighter aircraft performance viewpoint A79-48687 [AIAA PAPER 79-1810] A79-47893 Techniques for fault isolation ambiguity reduction From HiMAT to future fighters --- Highly --- in military avionics Maneuverable Aircraft Technology assessment A79-48891 [AIAA PAPER 79-1816] A79-47896 Fault diagnosis of gas turbine engines by means of Benefits of aerodynamic interaction to the three component characteristics determination surface configuration A79-49806 [AIAA PAPER 79-1830] A79-47904 FAILURE NODES User requirements for future combat search and Lusaka accident report rescue vehicles A79-50109 A79-48683 FAIRCHILD-BILLER AIRCRAFT Airborne microwave ECM Driftdown calculations for the FH/227D aircraft A79-49554 [SAND-78-1807) N79-30182 Maintenance improvement: An analysis approach FAST FOURIER TRANSFORMATIONS including inferential technical data --- naval Transform domain processing for digital aircraft communication systems using surface acoustic (AD-A068382) 1179-30141 wave devices Flow visualization studies of a general research N79-31482 fighter model employing a strake-wing concept at A new approach to the solution of large, full subsonic speeds --- in the Langley high speed 7- matrix equations: A two-dimensional potential by 10-ft wind tunnel flow feasibility study (NASA-TM-80057) 1179-301117 [ NASA-CR-3173] N79-31533 A flow field study for top mounted inlets on FATIGUE (MATERIALS) fighter aircraft configurations Lusaka accident report (AD-A069732] N79-30151 A79-50109 Research on visual display integration for FATIGUE LIFE advanced fighter aircraft Long-life GTE operation based on technical condition (AD-A069605] 1179-30184 Gas Turbine Engine Enhanced fighter mission effectiveness by use of A79-48517 integrated flight systems Helicopter component environmental vibration N79-30223 testing - The poor man's fatigue test Improvement of fighter aircraft maneuverability CANS 79-49) A79-49101 through employment of control configured vehicle FATIGUE TESTS technology Qualification program of the composite main rotor N79-30225 blade for the Model 2148 helicopter Lateral stability at high angles of attack, CARS 79-44] A79-49096 particularly wing rock Operation and test of composite horizontal N79-30226 stabilizer for the Sikorsky Spirit helicopter Stall behaviour evaluation from flight test results [ABS 79-45] A79-49097 1179-30227 Helicopter component environmental vibration Open/closed loop identification of stability and testing - The poor man's fatigue test control characteristics of combat aircraft CARS 79-49] A79-49101 N79-30232 Fatigue and fracture Design guidance from fighter CCV flight evaluations N79-30315 1179-30235 Wind-tunnel investigation of an armed mini remotely piloted vehicle --- conducted in Langley V/STOL tunnel (NASA-TN-80132) 1179-31151

A-23

FINANCIAL MANAGEMENT SUBJECT INDEX

Investigation of roll performance for a highly The fluorenone polyester ISO PPE of Isovolta nonlinear statically unstable fighter-type Company, Austria aircraft 579-31183 [90-9069301] N79-31199 FLAME STABILITY Implementing JTIDS in tactical aircraft Factors controlling stability of swirling flames 1479-31491 at diffusers in gas turbines FINANCIAL MANAGEMENT A79-50209 Potential closure of airports FLAMEOUT N79-31231 385-CAR-15 compressor stall and flameout FINITE DIFFERENCE THEORY investigation Fully conservative numerical solutions for 979-50441 unsteady irrotational transonic flow about FLAMMABILITY airfoils Conference on Fire Resistant Materials: A [9199 PAPER 79-1555] 979-47342 compilation of presentations and papers Numerical solution of the problem of unsteady [NASA-CP-2094] 879-31166 supersonic flow around the front part of the Airport flammability, full scale fire tests wings with a detached shock wave 879-31167 A79-49456 Seat test program FINITE ELEMENT METHOD 579-31168 Application of finite-element and holographic Status of candidate materials for full-scale tests techniques in the design of turboshaft engine in the 737 fuselage components N79-31170 [ASS 79-411 979-49093 Development of aircraft lavatory compartments with Evaluation of finite element formulations for improved fire resistance characteristics. Phase transient conduction forced-convection analysis 2: Sandwich panel resin system development A79-49343 [NASA-CR-152120] 879-31354 Tapered roller bearing development for aircraft FLAPS (CONTROL SURFACES) turbine engines Theoretical flap-lag damping with various dynamic [AD-A069440] 879-30555 inflow models FIRE CONTROL [ASS 79-20] 979-49073 A status report on the advanced FIREFLY assessment The size and performance effects of high lift program system technology on a modern twin engine jet 979-48609 transport Multisensor integration for defensive fire control [AIAA PAPER 79-1795] 979-49332 surveillance Development and demonstration of manufacturing A79-48610 processes for fabricating graphite/PNR-15 FIRE FIGHTING polyimide structural elements --- space shuttle Fuselage ventilation under wind conditions aft body flap. N79-31175 579-30301 FIREBREAKS FLIGHT CHARACTERISTICS Conference on Fire Resistant Materials: A AFFTC parameter identification experience --- for compilation of presentations and papers aircraft flight characteristics [NASA-CP-2094] N79-31166 [9199 PAPER 79-1803] 979-47888 FIREPROOFING Winglet toe out-angle optimization for the Gates Conference on Fire Resistant Materials: A Learjet Longhorn Wing compilation of presentations and papers (AIAA PAPER -79-1831] 979-47905 [NASA-CP-2094] 879-31166 A microprocessor system for flight control research Development of fire-resistant, low smoke 979-48623 generating, thermally stable end items for Helicopter performance methodology at Bell commercial aircraft and spacecraft using a basic Helicopter Textron polyinide resin [ABS 79-2] 979-49055 579-31171 Improved method of predicting helicopter control Fire resistant aircraft seat program response and gust sensitivity 579-31176 [ABS 79-25] 979-49077 A review of Boeing interior materials and fire An investigation of the rolling stability test methods development programs derivatives of a F-tail fighter configuration at 879-31177 high angles-of-attack FIREMEN program A79-50165 N79-31178 Evaluation of selected class III requirements of FIRES MIL-F-8785B /ASG/, 'Plying Qualities of Piloted Conference on Fire Resistant Materials: A Airplanes- compilation of presentations and papers A79-50439 [NASA-CP-2094) 579-31166 Similitude requirements and scaling relationships Airport flammability, full scale fire tests as applied to model testing N79-31167 [NASA-TP-1435] 879-30176 Seat test program Aircraft response to windshears and downdraughts N79-31168 H79-30229 Recent advances in materials toxicology Stability and control aspects of the CCV-F104C N79-31169 N79-30234 Status of candidate materials for full-scale tests Flying qualities and the fly-by-wire aeroplane in the 737 fuselage N79-30238 N79-31170 Are today's specifications appropriate for Global enclosure fire modeling with applications tomorrow's airplanes? 879-31172 W79-30239 Enclosure fire dynamics model Flight performance of the TCV B-737 airplane at 579-31173 Kennedy Airport using TRSB/MLS guidance Development of aircraft lavatory compartments with [NASA-TM-80148] 879-31186 improved fire resistance characteristics. Phase FLIGHT CONTROL 2: Sandwich panel resin system development Analytic redundancy for flight control sensors on [NASA-CE-152120] 879-31354 the Lockheed L-1011 aircraft FLAME RETARDANTS 979-47960 Fire resistant aircraft seat program Failure detection in signal processing and sensing N79-31176 in flight control systems A review of Boeing interior materials and fire 979-47971 test methods development programs A status report on the advanced FIREFLY assessment N79-31177 program FIREMEN program A79-48609 879-31178

9-24 SUBJECT INDEX FLIGHT STABILITY TESTS

Synthesis of digital flight control tracking An evaluation of the bird aircraft strike hazard systems by the method of entire eigenstructure at Hill AFB, Utah (AFLC) assignment [AD-A070459] 879-31184 A79-48625 FLIGHT OPTIMIZATION Terrain-following radar - Key to low-altitude flight Analysis of optimal loop and split-S by energy A79-48686 state modeling Analytical and experimental investigation of A79-47098 V-type empennage contribution to directional Verification of operational flight programs by control in hover and forward flight simulation [AHS 79-56] A79-49106 A79-48667 Fluidics: Feasibility study FLIGHT PATHS electro/hydraulic/fluidic direct drive servo valve Analysis of optimal loop and split-S by energy [AD-A069798] 879-30195 state modeling The Guidance and control of Helicopters and V/STOL A79-47098 aircraft at night and in poor visibility The aerial relay system - An energy-efficient [AGARD-CP-258] 879-30198 solution to the airport congestion problem Some aspects of the design and development of the using cruise liner aircraft for in-air passenger maritime autopilot modes for the Westland Lynx transfer helicopter [AIAA PAPER 79-1865] 179-47921 879-30201 A novel technique for obtaining aerodynamic data Design and testing of a redundant skewed inertial using simple, free flight trajectory measurements sensor complex for integrated navigation and A79-48051 flight control Advances in decelerating steep approach and 879-30202 landing for helicopter instrument approaches Subjective assessment of a helicopter approach [AHS 79-16] A79-49069 system for IFE conditions Variables characterizing the wind effects on an 879-30209 aircraft Simulation and study of V/STOL landing aids for A79-49807 USMC AV-8 aircraft Driftdovn calculations for the Fli/227D aircraft 879-30214 (SAND-78-1807] 879-30182 Implementation of flight control in an integrated Path controllers: Unification of concepts and guidance and control system comparison of design methods N79-30215 [AD-A070252] 1179-31227 Structural aspects of active controls FLIGHT RULES 879-30221 Aeronautical information data subsystems /1103/ Stability and control aspects of the CCV-F10I4C A79-50920 879-30234 FLIGHT SAFETY Design guidance from fighter CCV flight evaluations Pave Low III , --- 11-53 helicopter avionics for 879-30235 night/adverse weather rescue of military aircraft In-flight handling qualities investigation of A79-48682 various longitudinal short term dynamics and An evaluation of the bird aircraft strike hazard direct lift control combinations for flight path at Hill AFB, Utah (AFLC) tracking using DFVLR liFE 320 variable stability [AD-A070459] 879-31184 aircraft FLIGHT SIMULATION B79-30237 Simulation and study of V/STOL landing aids for Flying qualities and the fly-by-wire aeroplane USNC AV-8 aircraft N79-30238 879-30214 Flight experience with advanced controls and Dynamic windtnnnel simulation of active control displays during piloted curved decelerating systems approaches in a powered-lift STOL aircraft N79-30233 879-30243 A simulator investigation of handling quality The promise of multicyclic control --- to control criteria for CCV transport aircraft fatiguing blade loads and rotor vibration N79-30240 (NASA-TN-78621] 879-31137 Ride qualities criteria validation/pilot Investigation of roll performance for a highly performance study: Flight test results nonlinear statically unstable fighter-type [NASA-CE-144885] 879-31193 aircraft Tactical performance characterization basic [AD-A069301] 879-31199 methodology Reliability improvement warranty terms and [AD-A069297] 879-31235 conditions for the Integrated Avionics Control FLIGHT SIMULATORS Systems (IACS) Piloted simulator investigation of helicopter (AD-A069454] 879-31205 control systems effects on handling qualities Helicopter high grain control during instrument flight [NASA-CR-159052] 879-31221 [AHS 79-26] A7949078 The design of digital controllers for the C-141 The I & 11 simulator - A comparison with flight aircraft using entire eigenstructure assignment test results and the development of an interactive computer A79-50169 design program Flight testing and simulator flight fidelity [AD-A069192] 879-31224 determination at Naval Air Test Center Investigation of inverse Vandermonde matrix A79-50307 calculation for linear system applications Seat cushion to provide realistic acceleration adaptive flight control systems cues to aircraft simulator pilot 879-31228 [AD-1069241] 879-31225 (NASA-CASE-LAR-12149-2] Path controllers: Unification of concepts and Laboratory development of computer generated image comparison of design methods displays for evaluation in terrain flight training 1179-31236 [AD-A070252] 879-31227 [AD-A070065] FLIGHT CHEWS FLIGHT STABILITY TESTS Design procedure for aircrew station labeling A simulation of amphibious hovercraft overturning selection and abbreviation A79-49904 B79-30208 Comment on Flight test of stick force stability Aircraft accident report: Swift lire Lines, Inc., in attitude-stabilized aircraft- Nord 262, N418SA, Marina Del Rey, California, A79-49925 March 10, 1979 In-flight handling qualities investigation of 879-31165 various longitudinal short term dynamics and [NTSB-AAR-79-13] direct lift control coobinatioüs for flight path FLIGHT HAZARDS The feasibility of inflight measurement of tracking using DFVLR liFE 320 variable stability lightning strike parameters aircraft N79-30237 (NASA-CR-158981] 879-30165

1-25

PLIGHT TEST INSTRUMENTS SUBJECT INDEX

PLIGHT TEST INSTRUNERTS Considerations in the analysis of flight test Flight test verification of the ASSET system maneuvers Advanced Skewed Sensory Electronic Triad A79-50433 A79-48622 Flight test technology development - A preview of High sink-rate landing testing of Navy aircraft DyNoTech --- dynamic modeling A79-50163 A79-50435 Flight test technology development - A preview of Evaluation of the radar altimeter reference method DyNoTech --- dynamic modeling for determining altitude system positioning errors A79-50435 A79-50436 ARIA takeoff performance flight test program The evolution of the high-angle-of-attack features Advanced Range Instrumented Aircraft of the F-16 flight control system A79-50437 A79-50438 PLIGHT TESTS J85-CAR-15 compressor stall and flameout Some early experiments in the development of a investigation flying platform for aerodynamic testing A79-50441 A79-47535 Testing the F-18 at the U.S. Naval Air Test Center Flight testing the circulation control wing A79-50444 [AIAA PAPER 79-1791] A79-47880 Radio-controlled model design and testing An improved method for load survey flight testing techniques for stall/spin evaluation of of military cargo aircraft general-aviation aircraft [AIAA PAPER 79-17991 A79-47885 [NASA-TN-80510] N79-30173 Dutch roll excitation and recovery techniques on a AH-1G helicopter, 19-round lightweight airborne C-141A Starlifter launcher jettison envelope determination [AIAA PAPER 79-1801] A79-47886 [AD-A069828] N79-30177 Some flight data extraction techniques used on a Airworthiness and flight characteristics test, general aviation spin research aircraft OV-1C takeoff performance [AIAA PAPER 79-1802] A79-47887 [AD-A069827] N79-30178 AFPTC parameter identification experience --- for The development and in-flight evaluation of a aircraft flight characteristics triplex digital autostabilization system for a [AIAA PAPER 79-18031 A79-47888 helicopter Ringlet toe Out angle optimization for the Gates N79-30200 Learjet Longhorn Wing GCU, the Guidance and Control Unit for all weather (AIAA PAPER 79-1831] A79-47905 approach Design of the circulation control wing STOL N79-30213 demonstrator aircraft Design guidance from fighter CCV flight evaluations [AIAA PAPER 79-1842] A79-47909 N79-30235 Flight test verification of the ASSET system L-1011 active controls, design philosophy and Advanced Skewed Sensory Electronic Triad experience A79-48622 N79-30236 Operational experience with the AN/ARR-131 Omega A comparison of predictions obtained from wind Navigation Set tunnel tests and the results from cruising A79-48676 flight: Airbus and Concorde --- conferences Realization of a helicopter-oriented real-time [NASA-TN-75238] R79-31136 data system for research, experimental, and Lateral aerodynamics extracted from flight test prototype flight testing using a parameter estimation method (AilS 79-50) A79-49102 [ARL-AERO-ROTE-380] N79-31146 Flight investigation of helicopter IFR approaches Flight performance of the TCV B-737 airplane at to oil rigs using airborne weather and mapping Kennedy Airport using TRSB/NLS guidance radar [NASA-TN-80148] N79-31186 [ABS 79-52] A79-49104 Ride qualities criteria validation/pilot Wind tunnel and flight test of the XV-15 Tilt performance study: Flight test results Rotor Research Aircraft (NASA-CR-144885] N79-31193 (ABS 79-54) A79-49105 PLIGHT TRAINING XV-15 flight test results compared with design goals Dutch roll excitation and recovery techniques on a [AIAA PAPER 79-1839] A79-119336 C-141A Starlifter NASA/Princeton digital avionics flight test facility [AIAA PAPER 79-1801] A79-47886 A79-49344 PLIGHT VEHICLES Flight experiments to evaluate the effect of Gas turbines for flight vehicle engines: Theory, wing-tip sails on fuel consumption and handling design, and calculation /Third review and characteristics enlarged edition/ --- Russian book A79-49818 A79-50421 High sink-rate landing testing of Navy aircraft PLOW CHARACTERISTICS A79-50163 Theoretical estimation of nonlinear longitudinal Dynamic test techniques - Concepts and practices characteristics of wings with small and moderate aircraft performance prediction from aspect ratio by the vortex-lattice method in thrust/lift/drag model incompressible flow A79-50164 [DLR-PB-78-26] N79-30161 Performance modelling methods --- in flight test PLOW DEFLECTION programs Determination of turning angle of a jet impinging A79-50167 on a bucket with visor --- for thrust reversers A computer system for identifying aircraft A79-48500 characteristics PLOW DISTORTION A79-50168 Laser velocimeter applied to the study of circular A computer program for aircraft identification and distorsion effects in a low speed compressor derivative extraction [ONERA, TP NO. 1979-30] A79-50925 A79-50306 PLOW DISTRIBUTION Flight testing and simulator flight fidelity A flow field study for top mounted inlets on determination at Naval Air Test Center fighter aircraft configurations A79-50307 [AD-A069732] N79-30151 Separation testing of large weapons from the B-i Investigation of air stream from combustor-liner bomber air entry boles, 3 A79-50429 [NASA-TN-75430] N79-31206 INACT - Interactive test data analysis --- with PLOW GEOMETRY minicomputers The inner regions of annular jets A79-50430 A79-47520 Estimation of longitudinal aircraft Flow patterns and aerodynamic characteristics of characteristics using parameter identification wing with strake techniques [AIAA PAPER 79-1877] A79-47928 A79-50432

A-26

SUBJECT INDEX FUEL CONTROL

Effect of steady-state temperature distortion and FLY BY WIRE CONTROL combined distortion on inlet flow to a turbofan Flight test verification of the ASSET system engine Advanced Skewed Sensory Electronic Triad [NASA-TM-79237] 879-30187 A79-48622 FLOW MEASUREMENT A microprocessor system for flight control research Experimental study of the turbulent wake A79-48623 downstream of a fan jet Development of a fly-by-wire elevator for the Bell A79-48507 Helicopter Textron 214ST Investigation of air stream from combustor-liner [ABS 79-27] A19-49079 air entry holes, 3 NASA/Princeton digital avionics flight test facility [NASA-TM-75430] 879-31206 A79-49344 FLOW STABILITY The evolution of the high-angle-of-attack features Laminar flow stabilization by surface cooling on of the P-16 flight control system hydrogen fueled aircraft A79-50438 (AIAA.PAPER 79-1863] A79-47920 Results related to simulated and in-flight FLOW THEORY experimentation with an electric flight control Lifting-line theory for a swept wing at transonic system that can be generalized speeds W79-30224 A79-47750 Design considerations for reliable FBW flight Aerodynamics for engineers --- Book control A79-50375 N79-30231 Mechanics of boundary layer transition, part 2: Flying qualities and the fly-by-wire aeroplane Instability and transition to turbulence W79-30238 [VKI-LECTURE-SERIES-3-PT-2] 879-31530 Analysis of a lateral pilot-induced oscillation FLOW VELOCITY experienced on the first flight of the YF-16 LDV measurements on propellers aircraft A79-49052 [NASA-TM-72867) 879-31220 FLOW VISUALIZATION FLYING PLATFORMS Aerodynamics of spoiler control devices Some early experiments in the development of a (AIAA PAPER 79-1873] A79-47925 flying platform for aerodynamic testing LOT measurements on propellers A79-47535 A79-49052 FOILS (MATERIALS) Flow visualization studies of a general research Metallic coatings for graphite/epoxy composites fighter model employing a strake-wing concept at [AD-A069871] 879-30334 subsonic speeds --- in the Langley high speed 7- FORCED CONVECTION by 10-ft wind tunnel Evaluation of finite element formulations for [NASA-TM-80057] 879-30147 transient conduction forced-convection analysis FLUID DYNAMICS A79-49343 Contributions to fluid mechanics FORGING 879-31524 Achieving consistency in the production of FLUID PLOW critical jet engine components by means of press Rotary balance data for a typical single-engine forging general aviation design for an angle-of-attack A79-48945 range of 8 deg to 90 deg. 1: High-wing model B FRACTURE STRENGTH [NASA-CR-3097] 879-30145 Fatigue and fracture FLUID JETS 879-30315 Jet propulsion for ACV's and hydrofoils FRAGMENTS A79-47847 Fuel tank survivability for hydrodynamic ran FLUID MECHANICS induced by high velocity fragments. p art 2: Contributions to experimental fluid mechanics Numerical analyses development of aerodynamics test facilities in [AD-A070128) 879-31200 Germany following World War 2 FREE PLIGHT N79-31229 A novel technique for, obtaining aerodynamic data Contributions to fluid mechanics using simple, free flight trajectory measurements W79-31524 A79-48051 FLUOROSCOPY FREQUENCY MODULATION Automatic scanning inspection of composite The servoed modulation FMCW radar altimeters in helicopter structure using an advanced military applications technology fluoroscopic system A79-49589 [ABS 79-35] A79-49087 FUEL COMBUSTION FLUTTER On the question of selecting the characteristic Some observations on four current subjects related quantity governing fuel self-ignition in a stream to aeroelastic stability A79-48497 A79-47093 Experimental study of the turbulent wake Structural aspects of active controls downstream of a fan jet S79-30221 A79-48507 FLUTTER ANALYSIS FUEL CONSUMPTION Iarmonic oscillations of annular wing in steady Energy efficient aircraft engines ideal fluid flow (AIRA PAPER 79-1861] A79-47918 A79-47009 Alternative fuels in aviation Active external store flutter suppression in the A79-49381 IF-17 flutter model Flight experiments to evaluate the effect of A79-49866 wing-tip sails on fuel consumption and handling Comment on 'active flutter control using characteristics generalized unsteady aerodynamic theory' A79-49818 A79-49 873 Derivative engines for the 1980s will help limit A summary of NASA/Air Force full scale engine acquisition and maintenance costs research programs using the P100 engine A79-50206 (NASA-TN-79267] 879-30188 Aircraft engine developments centre on improved Flutter analysis of two-dimensional and performance, higher efficiency two-degree-of-freedom airfoils in A79-50207 small-disturbance, unsteady transonic flow JT9D-70/59 improved high pressure turbine active [AD-A069223] N79-31157 clearance control system --- for specific fuel FLY BY TUBE CONTROL consumption improvement Program for the critical components of a [NASA-CR-159661] N79-31208 fly-by-tube backup flight control system, part 1 FUEL CONTROL [AD-A070387] 879-31226 The influence of engine/fuel control design on helicopter dynamics and handling qualities CABS 79-373 A79-49089

A-27

FUEL CORROSION SUBJECT INDEX

FUEL CORROSION Nozzles for vectored thrust jet engines Changes in the quality of T-6 fuel upon prolonged Russian book storage A79-47428 A79-48858 Fuels, lubricants and other fluids used in aviation FUEL FLOW Russian book Laminar flow stabilization by surface cooling on A7 9-47433 hydrogen fueled aircraft Gas turbines for AcV's and hydrofoils [AIAA PAPER 79-1863] A79-47920 A79-47845 On the question of selecting the characteristic Estimation for advanced technology engines quantity governing fuel self-ignition in a stream A79-47957 A79-48497 Influence of gas turbine engine combustion chamber FUEL INJECTION geometric parameters on mixture formation Characterization of a swept-strut hydrogen characteristics fuel-injector for scramjet applications A79-48495 A79-449345 Long-life GTE operation based on technical condition FUEL TANKS Gas Turbine Engine Fuel tank survivability for hydrodynamic ran A79-48517 induced by high velocity fragments. Part 2: Development of a no adjustment' turboshaft engine Numerical analyses control system [AD-A070128] N79-31200 (ABS 79-42] A79-49094 Fuel tank survivability for hydrodynamic ram Fault diagnosis of gas turbine engines by means of induced by high velocity fragments. Part 1: component characteristics determination Experimental Results and Design summary A79-49806 [AD-A070113] N79-31202 Duct noise radiation through a jet flow FUEL TESTS A79-50110 The tendency of jet fuels to form deposits on a Factors controlling stability of swirling flames heated surface at diffusers in gas turbines A79-48856 A79-50209 Changes in the quality of T-6 fuel upon prolonged Gas turbines for flight vehicle engines: Theory, storage design, and calculation /Third review and A79-48858 enlarged edition/ --- Russian book Method of determining mechanical-impurity contents A79-50421 in jet fuels Ambient correction factors for aircraft gas A79-48859 turbine idle emissions FULL SCALE TESTS [AD-A069240] N79-31218 Experimental measurements of the rotating GEAR TEETH frequencies and mode shapes of a full scale Developments in gear analysis and test techniques helicopter rotor in a vacuum and correlations for helicopter drive systems with calculated results [ASRE PAPER 79-DE-15] A79-47654 (ABS 79-18] A79-49071 GEARS Full scale ground and air resonance testing of the Helicopter drive system N and N design guide Army-Boeing Vertol Bearingless Rain Rotor (AD-A069835] N79-30180 CARS 79-23] A79-49075 GENERAL AVIATION AIRCRAFT Design, analysis, and testing of a new generation The effects of configuration changes on spin and tail rotor recovery characteristics of a low-wing general (ASS 79-57] A79-49107 aviation research airplane FUNCTIONAL ANALYSIS (AIAA PAPER 79-1786] A79-47876 On a smooth approximation method and its Some flight data extraction techniques used on a application to mathematical description of wing general aviation spin research aircraft aerodynamic characteristics (AIAA PAPER 79-1802] A79-47887 A79-47001 Full-scale wind tunnel study of nacelle shape on FUSELAGES cooling drag Selecting the passenger airplane fuselage [AIAA PAPER 79-1820] A79-47900 A79-47014 Real time weather display in the general aviation Design of advanced titanium structures --- for cockpit Advanced Tactical Systems aircraft fuselage [AIRA PAPER 79-1821] A79-47901 (AIAA PAPER 79-1805] A79-47890 A cheap, effective icing detector for general Investigations on the design of active vibration aviation aircraft isolation systems for helicopters with rigid and [AIAA PAPER 79-1823] A79-47902 elastic modeling of the fuselage The Beech Model 77 'Skipper' spin program [DLR-FB-78-04] N79-30183 [AIAA PAPER 79-1835] A79-47907 Status of candidate materials for full-scale tests Exploratory study of the influence of wing in the 737 fuselage leading-edge modifications on the spin v79-31170 characteristics of a low-wing single-engine Fuselage ventilation under wind conditions general aviation airplane H79-31175 [AIAA PAPER 79-1837] A79-47908 NASA/Princeton digital avionics flight test facility A79-49344 G A design perspective on new technologies for G-91 AIRCRAFT general aviation Gust alleviator feasibility study for G91Y A79-49486 N79-30230 Rotary balance data for a typical single-engine GAS DYNAMICS general aviation design for an angle-of-attack Experimental study of the gasdynamic range of 8 deg to 90 deg. 1: High-wing model B characteristics of a stator cascade with cooling [NASA-cR-3 097] N79-30145 air discharge through the vane surface Radio-controlled model design and testing A79-48498 techniques for stall/spin evaluation of GAS STREAMS general-aviation aircraft On the question of selecting the characteristic [NASA-TN-80510] N79-30173 quantity governing fuel self-ignition in a stream Rotary balance data for a typical single-engine A79-48497 general aviation design for an angle-of-attack GAS TURBINE ENGINES range of 8 deg to 90 deg. 2: High-wing model A Optimal thernogasdynamic design of gas turbine (NASA-CR-3101) 4479-31149 engines using element prototypes. I Development of crashworthy passenger seats for A79-46997 general-aviation aircraft The application of multiple swirl modules in the [NASA-cR-159100] 4479-31164 design and development of gas turbine combustors An overview of NASA research on positive (AIAA PAPER 79-1196] A79-47349 displacement type general aviation engines [NASA-TM-79254] N79-31210

A-28

SUBJECT INDEX HEAD-UP DISPLAYS

Exhaust emissions characteristics for a general A combined air-cushion and endless belt aviation light aircraft Teledyne Continental transportation system Motors TSTO-360-C piston engine A79-49911 [AD-A070010] 1479-31211 Heave-pitch-roll analysis and testing of air Potential closure of airports cushion landing systems 1479-31231 [NASA-CR-2917] 1479-30175 GLASS FIBER REINFORCED PLASTICS GROUND SUPPORT EQUIPMENT Qualification program of the composite main rotor F-16 depot automatic test equipment blade for the Model 21 14B helicopter A79-48895 [AHS 79-144] A79-49096 Airport power supply --- Russian book Evaluation of airfield pavement materials based on A79-50499 synthetic polymers GROUND SUPPORT SISTERS A79-493'48 AN/USM-449/V/ ATE for worldwide support of the P3 GLIDERS Orion Some early experiments in the development of a A79-48884 flying platform for aerodynamic testing GROUND TESTS A79-47535 Full scale ground and air resonance testing of the GLOBAL POSITIONING SYSTEM Army-Boeing Vertol Bearingless Main Rotor A real-time sequential filtering algorithm for GPS [ABS 79-23] A79-49075 low-dynamics navigation system Ground test vehicle testing --- in helicopter A79-48657 development programs GRANTS [ABS 79-40] 879-49092 Advisory circular. The planning grant program for GROUND-AIR-GROUND COMMUNICATIONS airports A novel approach to the design of an all digital [AC150/5900-1B] 1479-31232 aeronautical satellite communication system GRAPHITE N79-31461 High performance composites and adhesives for Investigation on information error caused by V/STOL aircraft traffic loading in approach and landing systems [AD-A069611] 1479-30332 1479-31480 Ultra-high-modulus graphite-epoxy conical shell GUIDANCE (MOTION) development, supplement Predictive guidance for interceptors with time [AD-A069795] 1479-30335 delays GRAPHITE-EPDXY COMPOSITE MATERIALS 819-47939 Composite helicopter tail booms Design guidance from fighter CCV flight evaluations [ABS 79-9] A79-49061 B79-30235 Operation and test of composite horizontal GUIDE VANES stabilizer for the Sikorsky Spirit helicopter Aerodynamic effects of an attitude control vane on [ABS 79-45] A79-49097 a tilt-nacelle V/STOL propulsion system Design and development of a hybrid composite rotor [AIAA PAPER 19-1855] 879-479114 blade for the circulation control rotor system Experimental study of the gasdynamic [ABS 79-46] A79-49098 characteristics of a stator cascade with cooling Metallic coatings for graphite/epoxy composites air discharge through the vane surface [AD-A069871] 1479-30334 A79-481498 Thermal characteristics of 3501-6/AS and 5208/T300 Aerodynamic performance of axial-flow fan stage graphite epoxy composites operated at nine inlet guide vane angles --- to [AD-A071067] 1479-31357 be used on vertical lift aircraft GREASES [NASA-TP-1510] 1479-31214 Self-contained grease lubrication systems for GUNS (ORDNANCE) aircraft applications Ultrasonic method of gun gas detection --- for [ABS 79-39] A79-49091 engine ingestion prevention in F-iS GROOVING A79-50166 Surveys of grooves in 19 bituminous runways GUST ALLEVIATORS [AD-A069889] 1479-31233 Gust alleviator feasibility study for G917 GROUND BASED CONTROL R79-30230 Flight control systems development of highly GUST LOADS maneuverable aircraft technology /HiNAT/ vehicle Improved method of predicting helicopter control [AIAA PAPER 79-17891 A79-47878 response and gust sensitivity GROUND EFFECT (AERODYNAMICS) [ABS 79-25] 879-49077 Surface-effect components of aerodynamic GYROSCOPIC STABILITY characteristics of air-cushion vehicle with ram The DG-800 - A rugged, high performance heading pressurization reference unit --- directional gyro design A79-46995 considerations Powered low-aspect-ratio Wing In Ground effect A79-48677 (WIG) aerodynamic characteristics --- conducted GYROSTABILIZERS in Langley V/STOL tunnel Stabilizing electro-optical systems on helicopters [RASA-TM-78793] 1479-31141 1419-30216 Theoretical and experimental investigation of ground-induced effects for a low-aspect-ratio highly swept arrow-wing configuration I [NASA-TP-1508] 1479-31223 14-53 HELICOPTER GROUND EFFECT MACHINES Pave Low III --- 14-53 helicopter avionics for The principles of hovercraft, powering and night/adverse weather rescue of military aircraft propulsion A79-48682 A79-47844 HARMONIC OSCILLATION Gas turbines for ACV's and hydrofoils Harmonic oscillations of annular wing in steady A79-47845 ideal fluid flow Jet propulsion for ACV5 and hydrofoils 879-47009 A79-478147 HARRIER AIRCRAFT Performance predictions for open ocean air cushion Simulation and study of V/STOL landing aids for vehicles and surface effect ships USNC AV-8 aircraft A79-49905 1479-30214 Characteristics of an Air Cushion Landing System HEAD-UP DISPLAYS incorporating an inelastic trunk F/A-18 Hornet display system A79-49909 A79-148630 Road fleet operation of air cushion as Helmet mounted display and sight development vehicles - An evaluation of technical and [ABS 79-17] 879-49070 economic problems A79-49910

8-29

BEAT RESISTANT ALLOTS SUBJECT INDEX

BEAT RESISTANT ALLOTS Ground test vehicle testing --- in helicopter Achieving consistency in the production of development programs critical jet engine components by means of press (ABS 79-40] A79-49092 forging Design, analysis, and testing of a new generation A79-48945 tail rotor HEAVING [ABS 79-57] A79-49107 Heave-pitch-roll analysis and testing of air Ten years of Aerospatiale experience with the cushion landing systems fenestron and conventional tail rotor [NASA-CR-2917] N79-30175 [ABS 79-58] A79-49108 HELICOPTER CONTROL Interactional aerodynamics - A new challenge to Helicopter performance methodology at Bell helicopter technology Helicopter Textron [ABS 79-59] A79-49109 CARS 79-2] A79-49055 Helicopter noise rules - Are they appropriate and Multiplex technology applied to helicopters reasonable CARS 79-14] A79-49067 A79-49478 Advances in decelerating steep approach and Aerospatiale AS.350 and AS.355 landing for helicopter instrument approaches A79-49814 [ABS 79-16] A79-49069 Design and development of the Agusta A 109 Spirit helicopter handling qualities design and helicopter development A79-49815 CARS 79-24] A79-49076 The Bell Model 222 Improved method of predicting helicopter control A79-49816 response and gust sensitivity Study of design constraints on helicopter noise CARS 79-25] A79-49077 [NASA-CR-159118] 879-32054 Piloted simulator investigation of helicopter HELICOPTER REGIMES control systems effects on handling qualities New versus existing engines for new helicopter during instrument flight systems - A life cycle cost view [ABS 79-26] A79-49078 [AIAA PAPER 79-1316] 879-47348 Advanced Scout Helicopter flying qualities The influence of engine/fuel control design on requirements - How realistic are they helicopter dynamics and handling qualities CARS 79-28] A79-49080 [ABS 79-37] A79-49089 Handling quality and display requirements for low Ground test vehicle testing --- in helicopter speed and hover in reduced flight visibility development programs CARS 79-29] 879-49081 [ABS 79-40] A79-49092 Flight investigation of helicopter IPH approaches Aerospatiale AS.350 and AS.355 to oil rigs using airborne weather and mapping A79-49814 radar HELICOPTER PERFORMANCE CARS 79-523 A79-49104 Experimental investigation of helicopter flight Analytical and experimental investigation of modes on helicopter-generated noise V-type empennage contribution to directional A79-47 873 control in hover and forward flight Helicopter performance methodology at Bell [ABS 79-561 A79-49106 Helicopter Textron The promise of multicyclic control --- to control [ABS 79-2] A79-49055 fatiguing blade loads and rotor vibration Helicopter obstacle strike tolerance [NASA-TM-78621) 879-31137 CARS 79-7] A79-49059 Helicopter high grain control Theoretical flap-lag damping with various dynamic [NASA-CR-159052] 879-31221 inflow models A compilation and analysis of helicopter handling CARS 79-20] 879-49073 qualities data. Volume 2: Data analysis Pull scale ground and air resonance testing of the (NASA-CH-3145] 879-31222 Army-Boeing Vertol Bearingless Main Rotor HELICOPTER DESIGN (ABS 79-23] A79-49075 New versus existing engines for new helicopter Piloted simulator investigation of helicopter systems - A life cycle Cost view control systems effects on handling qualities [AIAA PAPER 79-1316] A79-47348 during instrument flight User requirements for future combat search and CARS 79-26] A79-49078 rescue vehicles Advanced Scout Helicopter flying qualities A79-48683 requirements - Bow realistic are they H-I combat search and rescue avionics study results (ABS 79-28] A79-49080 A79-48684 The influence of engine/fuel control design on Helicopter obstacle strike tolerance helicopter dynamics and handling qualities [ABS 79-7] #79-49059 [ABS 79-37] A79-49089 A system for interdisciplinary analysis - A key to Realization of a helicopter-oriented real-time improved rotorcraft design data system for research, experimental, and [ABS 79-8] #79-49060 prototype flight testing Composite helicopter tail booms [ABS 79-50] 878-49102 (ABS 79-9) A79-49061 Design and development of the Agusta A 109 Designing with experimental mechanics helicopter three-dimensional photoelastic analysis of A79-49815 helicopter components A compilation and analysis of helicopter handling CARS 79-11] A79-49063 qualities data. Volume 2: Data analysis Dynamics requirements for an Advanced Scout [MASA-CE-3145] 879-31222 Helicopter /ASH/ HELICOPTER PROPELLER DRIVE [ABS 79-19] A79-49072 Developments in gear analysis and test techniques Evaluation of the practical aspects of vibration for helicopter drive systems reduction using structural optimization techniques (ASNE PAPER 79-DE-15) A79-47654 [ABS 79-21] A79-49074 Dynamics requirements for an Advanced Scout Spirit helicopter handling qualities design and Helicopter /ASH/ development [ABS 79-19] 879-49072 [ABS 79-24] A79-49076 Metal-matrix composite structures Development of a fly-by-wire elevator for the Bell [ABS 79-34] A79-49086 Helicopter Textron 214ST Ground test vehicle testing --- in helicopter (ABS 79-27] 879-49079 development programs Model 2061 composite litter door [ABS 79-40) A79-49092 [ABS 79-31] A79-49083 The Sikorsky elastomeric rotor --- helicopter Superplastic forming diffusion bonding of titanium rotor bearings helicopter airframe ccmponents [ABS 79-48] 879-49100 [ABS 79-33] A79-49085

8-30

SUBJECT INDEX HYBRID NAVIGATION SYSTEMS

HELICOPTER TAIL ROTORS HOLE DISTRIBUTION (MECHANICS) Design, analysis, and testing of a new geneation Investigation of air stream from combustor-liner tail rotor air entry holes, 3 (ABS 79-571 679-49107. [NASA-TN-75430] N79-31206 HELICOPTER WAKES HOLOGRAPHIC INTERFBEONETEY A lifting-surface method for hover/climb airloads Application of finite-element and holographic (ABS 79-3] 679-49056 techniques in the design of turboshaft engine Interactional aerodynamics - A new challenge to components helicopter technology CARS 79-41] 679-49093 [ABS 79-59] A79-49109 HONEYCOMB STRUCTURES HELICOPTERS Operation and test of composite horizontal Agricultural helicopters --- test and simulation stabilizer for the Sikorsky Spirit helicopter results (ABS 79-45] A79-49097 [ABS 79-60] 679-49064 HORIZONTAL TAIL SURFACES Automatic scanning inspection of composite Operation and test of composite horizontal helicopter structure using an advanced stabilizer for the Sikorsky Spirit helicopter technology fluoroscopic system CARS 79-45] A79-49097 [ABS 79-35) 679-49087 HOT SURFACES Helicopter component environmental vibration The tendency of jet fuels to form deposits on a testing - The poor mans fatigue test heated surface (ABS 79-49) 679-49101 A79-48856 Helicopter obstacle strike tolerance concepts HOVERCRAFT GROUND EFFECT MACHINES analysis P. simulation of amphibious hovercraft overturning [AD-A069877] N79-30179 A79-49904 Helicopter drive system B and N design guide Small hovercraft design - Evolution to simplicity [AD-A069835] 979-30180 A79-49906 Helicopter drive system N and N design guide Hovercraft skirt design requirements [AD-A069691] 979-30181 A79-49907 Investigations on the design of active vibration Iceater I - Air cushion ice breaker in commercial isolation systems for helicopters with rigid and operations elastic modeling of the fuselage A79-49912 (DLR-PB-78-04] N79-30183 Current Canadian developments related to low-speed The Guidance and control of Helicopters and V/STOL heavy lift ACV aircraft at night and in poor visibility A79-49915 (AGARD-CP-258] 979-30198 HOVERING The development and in-flight evaluation of a Effect of tip shape on blade loading triplex digital autostabilization system for a characteristics for a two-bladed rotor in hover helicopter CARS 79-1) 679-49054 N79-30200 A lifting-surface method for hover/climb airloads Some aspects of the design and development of the (ABS 79-3) 679-49056 maritime autopilot modes for the Westland Lynx Handling quality and display requirements for low helicopter speed and hover in reduced flight visibility 979-30201 [ABS 79-29] 679-49081 A self contained collision avoidance system for Analytical and experimental investigation of helicopters V-type empennage contribution to directional 979-30206 control in hover and forward flight An advanced guidance and control system for rescue [ABS 79-56] 679-49106 helicopters HOVERING STABILITY 979-30217 The principles of hovercraft, powering and The promise of multicyclic control --- to control propulsion fatiguing blade loads and rotor vibration 679-47844 [NASA-TN-78621] 979-31137 Wind tunnel and flight test of the XV-15 Tilt Load spectrum measuring equipment, p art 1: Rotor Research Aircraft Details of BK 1 system presently used to acquire [ABS 79-54] A79-49105 data in Wessex BK 31B helicopters XV-15 flight test results compared with design goals [ARL-MECH-ENG-NOTE-37 1] 979-31194 [6166 PAPER 79-1839] A79-49336 A compilation and analysis of helicopter handling HUBS qualities data. Volume 2: Data analysis An integrated analytical and experimental NASA-CP-3145] 979-31222 investigation of helicopter hub drag Performance predictions and trials of a helicopter CARS 79-5] A79-49058 UHF data link HUMAN FACTORS ENGINEERING N79-31476 Research on visual display integration for HELMETS advanced fighter aircraft Helmet mounted display and sight development (AD-A069605) N79-30184 CARS 79-17] 679-49070 The equipment-system interface in an antitank HFB-320 AIRCRAFT helicopter at night In-flight handling qualities investigation of N79-30211 various longitudinal short term dynamics and HUMAN PERFORMANCE direct lift control combinations for flight path Tactical performance characterization basic tracking using DPVLR BPS 320 variable stability methodology aircraft [AD-A069297] 979-31235 N79-30237 HYBRID NAVIGATION SYSTEMS HIGH ALTITUDE BALLOONS Expanding the region of convergence for SITAR Transatlantic flights of stratospheric balloons through improved modelling of terrain H79-31687 nonlinearities --- Sandia Inertial Terrain Aided HIGH FIELD MAGNETS Navigation All electric subsystems for next generation 679-48678 transport aircraft Dynamic simulator test and evaluation of a JTIDS (AIAA PAPER 79-1832) A79-47906 relative navigation system --- Joint Tactical HIGH GAIN Information Distribution System Helicopter high grain control A79-48694 [NASA-CR-159052] N79-31221 System configuration and algorithm design of the HISTORIES inertially aided JTIDS Relative Navigation Historical development of worldwide supersonic function --- Joint Tactical Information aircraft Distribution System [AIAA PAPER 79-1815] #79-47895 A79-48716

6-31

HYBRID STRUCTURES SUBJECT INDEX

HYBRID STRUCTURES IMAGE CONVERTERS Design and development of a hybrid composite rotor Real time compression of video signals blade for the circulation control rotor system protection against jamming (ABS 79-46) A79-49098 A79-48712 HYDRAULIC EQUIPMENT Scan converter and raster display controller for Program for the critical components of a night vision display systems fly-by-tube backup flight control system, part 1 N79-30203 [AD-A070387] 879-31226 IMAGE MOTION COMPENSATION HYDRODYNAMIC RAM EFFECT Quaternion matching in transfer alignment for SAN Fuel tank survivability for hydrodynamic ram motion compensation induced by high velocity fragments. Part 2: 179-48641 Numerical analyses IMAGE PROCESSING [AD-A070128] N79-31200 Preprocessing for advanced image matching techniques Fuel tank survivability, for hydrodynamic ram 179-48602 induced by high velocity fragments. Part 1: Synthetic aperture radar map matching for navigation Experimental Results and Design summary 879-48603 [AD-A070113] 879-31202 An analysis of SAPPHIRE image parameters as a HYDROFOIL CRAFT function of processing parameters --- for Gas turbines for ACV's and hydrofoils synthetic aperture radar data processing 179-47845 A79-48666 Jet propulsion for ACV's and hydrofoils IMAGING TECHNIQUES A79-47847 Digital sensor simulation at the Defense Mapping HYDROGEN FUELS Agency Aerospace center Laminar flow stabilization by surface cooling on A79-48705 hydrogen fueled aircraft Real time compression of video signals [lIlA PAPER 79-1863] 179-47920 protection against jamming Lockheed urges hydrogen fuel A79-48712 879-49224 IMPACT DAMAGE Characterization of a swept-strut hydrogen Helicopter obstacle strike tolerance fuel-injector for scramjet applications CARS 79-7] 879-49059 A79-49345 Crashworthy armored crewseat for the UH-601 Black Drag reduction by cooling in hydrogen-fueled Hawk aircraft [ABS 79-10] 179-49062 879-49921 Helicopter obstacle strike tolerance concepts HYPERSONIC AIRCRAFT analysis Conceptual study of a turbojet/ramjet inlet [AD-A069877] N79-30179 [NASA-TN-80141] 879-31215 IMPACT STRENGTH Actively cooled plate fin sandwich structural Windshield technology demonstrator program-canopy panels for hypersonic aircraft detail design options study [NASA-CR-3159] 879-31628 [AD-A070376] N79-31201 HYPERSONIC FLOW IMPURITIES Solution of a mixed boundary value problem for Method of determining mechanical-impurity contents flow past a thin delta wing in jet fuels 879-49882 A79-48859 HYPERSONIC INLETS IN-FLIGHT MONITORING Conceptual study of a turbojet/ramjet inlet Some flight data extraction techniques used on a (NASA-TN-80141) N79-31215 general aviation spin research aircraft HYPERVELOCITY IMPACT [lIlA PAPER 79-1802] 879-47887 Fuel tank survivability for hydrodynamic ram ATE and aircraft mechanical diagnostics induced by high velocity fragments. Part 2: A79-48883 Numerical analyses Realization of a helicopter-oriented real-time [AD-A070128] N79-31200 data system for research, experimental, and prototype flight testing [ABS 79-50) 879-49102 An in-flight controller insensitive to parameters ICE ENVIRONMENTS variation Iceater I - Air cushion ice breaker in commercial [DLR-FB-78-07] N79-30197 operations INCOMPRESSIBLE FLOW 179-49912 Analytic formulas for wing profile aerodynamic ICE REPORTING characteristics in incompressible flow A cheap, effective icing detector for general A79-47000 aviation aircraft Comment on 'active flutter control using [lIlA PAPER 79-1823] 879-47902 generalized unsteady aerodynamic theory' IDEAL FLUIDS A79-49873 Harmonic oscillations of annular wing in steady INDEPENDENT VARIABLES ideal fluid flow AFFIC parameter identification experience --- Air A79-47009 Force Flight Test Center aircraft flight testing IDENTIFYING A79-50434 The enhancement of aircraft parameter INDICATING INSTRUMENTS identification using linear transformations A cheap, effective icing detector for general for stability aviation aircraft A79-47961 [AAA PAPER 79-1823] A79-47902 A computer program for aircraft identification and INERTIAL NAVIGATION derivative extraction Low cost inertial aiding for NAVSTAR/GPS receivers A79-50306 in naval ship navigation Estimation of longitudinal aircraft A79-48656 characteristics using parameter identification Expanding the region of convergence for SITAR techniques through improved modelling of terrain A79-50432 nonlinearit jes --- Sandia Inertial Terrain Aided IGNITION Navigation Seat test program A79-48678 N79-31168 Transfer alignment for precision pointing IGNITION LIMITS applications --- in inertial navigation systems On the question of selecting the characteristic A79-48679 quantity governing fuel self-ignition in a stream Application of instrument rotation in the 873 A79-48497 standard inertial navigation system A79-48696

A-32

SUBJECT INDEX JET EXHAUST

Rapid reaction time techniques for a strapdown Integrated CR1 avionics --- ECM-resistant navigator employing electrostatic gyro technology Communication, Navigation and Identification A79-48697 A79-48711 System configuration and algorithm design of the INTERCEPTORS inertially aided JTIDS Relative Navigation Predictive guidance for interceptors with time function --- Joint Tactical Information delays Distribution System A79-47939 A79-48716 INTERFERENCE DRAG Design and testing of a redundant skewed inertial Wind tunnels with adapted walls for reducing wall sensor complex for integrated navigation and interference flight control (NASA-TM-75501] N19-31230 R79-30202 INTERNATIONAL RELATIONS INERTIAL PLATFORMS International Air Transportation Competition Act Quaternion matching in transfer alignment for SAN of 1978 --- congressional reports motion compensation [GPO-34-912] R79-30168 A79-48641 ITERATIVE SOLUTION INFORMATION SYSTEMS F-16 avionics maintenance concept and JTIDS relative navigation - Architecture, error multinational aspects characteristics and operational benefits A79-48894 Joint Tactical Information Distribution System A79-48715 Implementing JTIDS in tactical aircraft j N79-31491 J-85 ENGINE INFRARED LASERS 385-CAN-15 compressor stall and flameout Multifunction CO2 heterodyning laser radar for low investigation level tactical operations A79-50441 A79-48685 JAMMING INLET FLOW Adaptive array tradeoffs for existing airborne UHF Performance of a V/STCL tilt nacelle inlet with radios blowing boundary layer control P.79-48598 [AIAA PAPER 79-1163] A79-47347 Real time compression of video signals Recent applications of theoretical analysis to protection against jamming V/STOL inlet design P.19-48712 A79-49530 Performance of a pulse-decode circuit in the Effect of steady-state temperature distortion and presence of interference combined distortion on inlet flow to a turbofan P.79-48713 engine Airborne microwave ECM (NASA-TN-79237] 1479-30187 P.19-49554 INPUT/OUTPUT ROUTINES JET AIRCRAFT Nodal interpolation program, L215(IRTERP) - Volume The size and performance effects of high lift 2: Supplemental system design and maintenance system technology on a modern twin engine jet document --- to calculate displacements at transport several points on an aerodynamic surface [AIAA PAPER 79-1795] P.19-49332 (NASA-CE-2848] N79-31147 Investigation of roll performance for a highly Time history solution program, L225 (TEV126) nonlinear statically unstable fighter-type Volume 2: Supplemental system design and aircraft maintenance document --- for airplane dynamic (AD-A069301) 4479-31199 response using frequency response data Analysis of plume rise from jet aircraft 4479-31204 [NASA-CE-2860] 4479-311514 [CONF-790142-1] INSTRUMENT APPROACH JET AIRCRAFT NOISE Subjective assessment of a helicopter approach Duct noise radiation through a jet flow system for IFR conditions. A79-50110 4479-30209 QCSEE - The key to future short-haul air transport Simulation and study of V/STOL landing aids for Quiet, Clean, Short-Haul Experimental Engine USMC AV-8 aircraft program 4479-30214 P.79-50208 INSTRUMENT COMPENSATION JET ENGINE FUELS Small signal compensation of magnetic fields The tendency of jet fuels to form deposits on a resulting from aircraft maneuvers heated surface A79-49605 A19-48856 INSTRUMENT ERRORS Evaluation of the temperature of the initiation of A deterministic investigation of strapped down jet fuel decomposition by means of the 'hardness navigation system accuracy factors A79-48695 A79-48 857 INSTRUMENT FLIGHT RULES Changes in the quality of T-6 fuel upon prolonged Piloted simulator investigation of helicopter storage control systems effects on handling qualities A79-48858 during instrument flight Method of determining mechanical-impurity contents [ABS 79-26] A79-49078 in jet fuels Flight investigation of helicopter IFR approaches A79-48859 to oil rigs using airborne weather and mapping Lockheed urges hydrogen fuel A79-49224 radar [ABS 79-52] P.79-49104 Alternative fuels in aviation INSTRUMENT LANDING SYSTEMS A79-49381 Advances in decelerating steep approach and JET ENGINES landing for helicopter instrument approaches Achieving consistency in the production of [ABS 79-16] A79-49069 critical jet engine components by means of press The T & E simulator - A comparison with flight forging test results A79-48945 P.79-50169 A flow field study for top mounted inlets on An asynchronous data transmission system with low fighter aircraft configurations error probability for the SETAC landing aid [AD-A069732] R79-30151 4479-31468 Investigation of air stream from combustor-liner INTEGRATED CIRCUITS air entry holes, 3 Radar signal processing development for (NASA-TM-15430) N79-31206 application of VHSI JET EXHAUST A79-48664 Analysis of plume rise from jet aircraft [CONF-790142-1] 1479-31204

A-3 3 JET FLAPS SUBJECT INDEX

Exhaust emission traverse investigation of a LAMINAR FLOW .JT3D-1 turbofan engine --- to acquire exhaust Laminar flow stabilization by surface cooling on nozzle emission sample hydrogen fueled aircraft (AD-A072019] 4479-31209 (AIAA PAPER 79-1863] A79-47920 JET FLAPS LAMINAR FLOW AIRFOILS A method of the theory of airfoil profiles with a Upper-surface modifications for C sub 1 sax jet flap improvement of selected NASA 6-series airfoils A79-47119 [NASA-TM-78603] N79-30143 JET FLOW LANDING AIDS The inner regions of annular jets Simulation and study of V/STOL landing aids for A79-47520 USEC AV-8 aircraft Experimental study of the turbulent wake N79-30214 downstream of a fan jet LANDING GEAR 879-48507 Characteristics of an Air Cushion Landing System JET IMPINGEMENT incorporating an inelastic trunk Engine-aircraft afterbody interactions - A79-49909 Recommended testing techniques based on YF-17 Testing and analysis of dual-mode adaptive landing experience gear, taxi mode test system for TF-12A [AIAA PAPER 79-1829] 879-47903 [NASA-CR-144884] 4479-31192 Determination of turning angle of a jet impinging LANDING INSTRUMENTS on a bucket with visor --- for thrust reversers Flight performance of the TCV B-737 airplane at 879-48500 Kennedy Airport using TPSB/NLS guidance JET LIFT [NASA-TM-80148] N79-31186 Powered low-aspect-ratio Wing In Ground effect LANDING LOADS (WIG) aerodynamic characteristics --- conducted Recent progress in aircraft sink rate measurement in Langley V/STOL tunnel [AIAA PAPER 79-1798] A79-47884 (NASA-TN-78793] N79-311141 Characteristics of an Air Cushion Landing System JET MIXING FLOW incorporating an inelastic trunk Influence of gas turbine engine combustion chamber A79-49909 geometric parameters on mixture formation Testing and analysis of dual-mode adaptive landing characteristics gear, taxi mode test system for YF-12A A79-48495 (NASA-C8-1414884] N79-31192 JET NOZZLES LANDINGMATS Nozzles for vectored thrust jet engines An evaluation of asphalt-rubber mixtures for use Russian book in pavement systems A79-47428 [AD-A069448] 4479-30246 JET PROPULSION LANDING RADAR Jet propulsion for ACV5 and hydrofoils Flight investigation of helicopter IFR approaches 879-47847 to oil rigs using airborne weather and mapping JET THRUST radar Powered low-aspect-ratio Wing In Ground effect [ABS 79-52] 879-49104 (WIG) aerodynamic characteristics --- conducted LANDING SITES in Langley V/STOL tunnel The characteristics of a lift cruise fan V/STOL (NASA-TN-78793] N79-31141 configuration in near proximity to a small deck JETTISON SYSTEMS with finite edge positions AH-1G helicopter, 19-round lightweight airborne [AIAA PAPER 79-1854] A79-47913 launcher jettison envelope determination LANGUAGE PROGRAMMING - [AD-A069828] N79-30177 Test implementation through support software - A JOINTS (JUNCTIONS) FIT translator --- automated Fault Isolation Simplified analysis spectrum for joints exposed to Tests on airborne radar system complex continuously varying stresses A79-48687 aerospace structures LASER DOPPLER VELOCIMETERS [AIAA PAPER 79-1808] A79-47892 LDV measurements on propellers A79-49052 Laser velocimeter applied to the study of circular distorsion effects in a low speed compressor KALMAN FILTERS (ONERA, TP NO. 1979-30] A79-50925 Estimation for advanced technology engines LASER RANGER/TRACKER A79-47957 Recent progress in aircraft sink rate measurement A real-tine sequential filtering algorithm for GPS [AIRA PAPER 79-1798] A79-47884 low-dynamics navigation system LATERAL CONTROL A79-48657 A multiple objective optimization approach to KEROSENE aircraft control systems design On the question of selecting the characteristic A79-47962 quantity governing fuel self-ignition in a stream LATERAL OSCILLATION A79-48497 Analysis of a lateral pilot-induced oscillation KEVLAR (TRADEMARK) experienced on the first flight of the !F-16 Model 2061 composite litter door aircraft EARS 79-31] 879-49083 [NASA-TN-72867] N79-31220 Operation and test of composite horizontal LATERAL STABILITY stabilizer for the Sikorsky Spirit helicopter A summary of AGARD FDP meeting on dynamic [ABS 79-45] 879-49097 stability parameters --- advanced aircraft performance at high angle of attack 4479-30220 L Lateral stability at high angles of attack, L-1011 AIRCRAFT particularly wing rock Analytic redundancy for flight control- sensors on N79-30226 the Lockheed 1-1011 aircraft Lateral aerodynamics extracted from flight test A79-47960 using a parameter estimation method Systems implications of active controls CARL-AENO-NOTE-380] 4479-31146 N79-30219 LATTICES (MATHEMATICS) 1-1011 active controls, design philosophy and Theoretical estimation of nonlinear longitudinal experience characteristics of wings with small and moderate N79-30236 aspect ratio by the vortex-lattice method in LAGRANGE MULTIPLIERS incompressible flow Application of Lagrange Optimization to the drag [DLR-FB-78-26] N79-30161 polar utilizing experimental data [AIRA PAPER 79-1833] A79-49335

A-34

SUBJECT INDEX LONGITUDINAL CONTROL

A program to compute three-dimensional subsonic LIGHT AIRCRAFT unsteady aerodynamic characteristics using the Some results from the use of a control doublet lattice method, L216 (DUBFLEX). Volume augmentation system to study the developed spin 2: Supplemental system design and maintenance of a light plane document [AIRA PAPER 79-1790] A79-47879 [NASA-CE-2850] N7931148 What the FAA would like in airworthiness standards LEADING EDGE SWEEP [AIRA PAPER 79-1851] A79-49338 High-performance wings with significant Dynamic windtunnel simulation of active control leading-edge thrust at supersonic speeds systems [AIAA PAPER 79-1871] A79-47924 B79-30233 The influence of sweep on the aerodynamic loading Development of crashworthy passenger seats for of an oscillating NACA 0012 airfoil general-aviation aircraft CABS 79-4] A79-49057 (NASA-CR-159100] N79-31164 LEADING EDGES Exhaust emissions characteristics for a general Exploratory study of the influence of wing aviation light aircraft Teledyne Continental leading-edge modifications on the spin Motors TSIO-360-c piston engine characteristics of a low-wing single-engine [AD-A070010] 879-31211 general aviation airplane LIGHT EMITTING DIODES [AIAA PAPER 79-1837] A79-47908 Helmet mounted display and sight development Boundary layer control on wings using sound and [ABS 79-17] A79-49070 leading edge serrations LIGHTNING (AIAA PAPER 79-1875 ] A79-47926 The feasibility of inflight measurement of Rotary balance data for a single-engine trainer lightning strike parameters design for an angle-of-attack range of 8 deg to (NASA-CE-158981] 879-30165 90 deg --- conducted in langely spin tunnel Atmospheric Electricity Hazard (AEH) (NASA-cR-3099] 879-31152 [AD-8069338] 879-30169 LIFE CYCLE COSTS Lightning hazards overview: Aviation requirements New versus existing engines for new helicopter and interests systems - A life cycle cost view N79-30876 (AIAA PAPER 79-1316] A79-47348 LINEAR SISTERS Derivative engines for the 1980s will help limit Linearization of the boundary-layer equations of acquisition and maintenance costs the minimum time-to-climb problem A79-50206 A79-49869 Naval aircraft operating and support Time history solution program, L225 (TEV126). cost-estimating model, FY 1977 revision Volume 2: Supplemental system design and [AD-#068175] 879-30140 maintenance document --- for airplane dynamic LIFT response using frequency response data Wing aerodynamic loading caused by jet-induced [T1ASA-cR-2860] 879-31154 lift associated with STOL-OTW configurations Investigation of inverse Vandermonde matrix [AJAR PAPER 79-1664] A79-47346 calculation for linear system applications Lifting-line theory for a swept wing at transonic adaptive flight control systems speeds [AD-A069241] 879-31225 879-47750 LINEAR TRANSFORMATIONS Dynamic test techniques - concepts and practices The enhancement of aircraft parameter aircraft performance prediction from identification using linear transformations thrust/lift/drag model for stability A79-50164 A79-47961 Upper-surface modifications for C sub 1 max LIQUID BEARINGS improvement of selected NASA 6-series airfoils The DG-800 - A rugged, high performance heading [NASA-T8-78603] 879-30143 reference unit --- directional gyro design In-flight handling qualities investigation of considerations various longitudinal short term dynamics and 879-48677 direct lift control combinations for flight path LIQUID PROPELLANT ROCKET ENGINES tracking using DFVLR lIFE 320 variable stability Gas turbines for flight vehicle engines: Theory, aircraft design, and calculation /Third review and N79-30237 enlarged edition/ --- Russian book LIFT AUGMENTATION A79-50421 Flight testing the circulation control wing LOAD DISTRIBUTION (FORCES) [AIAA PAPER 79-1791] A79-47880 An improved method for load survey flight testing LIFT DEVICES of military cargo aircraft Design of the circulation control wing STOL [AIAA PAPER 79-17991 A79-47885 demonstrator aircraft LOAD TESTS [AIAA PAPER 79-1842] A79-47909 An improved method for load survey flight testing The size and performance effects of high lift of military cargo aircraft system technology on a modern twin engine jet [AIAA PAPER 79-1799] A79-47885 transport LOADING MOMENTS (AIAR PAPER 79-1795] A79-49332 Load spectrum measuring equipment. Part 1: Current Canadian developments related to low-speed Details of ME 1 system presently used to acquire heavy lift ACV datain Wessex ME 318 helicopters A79-49915 [ABL-HYCH-ENG-NOTE-371 ] 879-31194 LIFT PANS LOADS (FORCES) Heave-pitch-roll analysis and testing of air A combined air-cushion and endless belt cushion landing systems transportation system [NASAcR*2917] 879-30175 A79-49911 Aerodynamic performance of 1.38-pressure-ratio, Effect of transport/bomber loads spectrum on crack variable-pitch fan stage growth (NASA-TP-1502) 879-31213 (AD-A069287) 879-31197 Aerodynamic performance of axial-flow fan stage A user's manual for a computer program to generate operated at nine inlet guide vane angles --- to fatigue spectrum loading sequences be used on vertical lift aircraft [AD-A069288] 879-31198 [NASA-TP-1510] 879-31214 LOGISTICS MANAGEMENT LIFTING ROTORS Reliability improvement warranty terms and The promise of multicyclic control --- to control conditions for the Integrated Avionics Control fatiguing blade loads and rotor vibration Systems (IACS) (RASA-TM-78621) 879-31137 ( 879-31205 LONGITUDINAL CONTROL Aerodynamic effects of an attitude control vane on a tilt-nacelle V/STOL propulsion system [AIAA PAPER 79-1855] A79-47914

A-35

LONGITUDINAL STABILITY SUBJECT INDEX

Aircraft longitudinal motion at high incidence Comment on 'Plight test of stick force stability A79-48052 in attitude-stabilized aircraft' Comment on Plight test of stick force stability A79-49925 in attitude-stabilized aircraft- The T & E simulator - A comparison with flight A79-49925 test results LONGITUDINAL STABILITY 879-50169 Estimation of longitudinal aircraft Research on visual display integration for characteristics using parameter identification advanced fighter aircraft techniques [AD-A069605] N79-30184 879-50432 Open/closed loop identification of stability and A summary of AGARD FDP meeting on dynamic control characteristics of combat aircraft stability parameters -- advanced aircraft R79-30232 performance at high angle of attack ONERA's model of the pilot in discrete time N79-30220 N79-30242 LOW ALTITUDE MANAGEMENT PLANNING Terrain-following radar - Key to low-altitude flight Financing the capital requirements of the US A79-48686 airline industry in the 1980's Meeting the challenge of precise navigation during N79-30164 nap-of-the-earth flight MANEUVERABILITY [AHS 79-12] 879-119065 Improvement of fighter aircraft maneuverability Ride qualities criteria validation/pilot through employment of control configured vehicle performance study: Plight test results technology (NASA-CE-144885] N79-31193 N79-30225 LOW ASPECT RATIO WINGS MANUAL CONTROL Theoretical estimation of nonlinear longitudinal A compilation and analysis of helicopter handling characteristics of wings with small and moderate qualities data. Volume 2: Data analysis aspect ratio by the vortex-lattice method in [NASA-CR-3145] N79-31222 incompressible flow MANUFACTURING [DLR-FB-78-26) 1179-30161 Role of Numerical Control Design in the computer LOW SPEED aided design/manufacturing interface at Sikorsky Handling quality and display requirements for low [AilS 79-30] 879-49082 speed and hover in reduced flight visibility Model 206L composite litter door [ABS 79-29] 879-49081 [ABS 79-31] #79-119083 Laser velocimeter applied to the study of circular MAP MATCHING GUIDANCE distorsion effects in a low speed compressor Meeting the challenge of precise navigation during [ONERA, TP NO. 1979-30] 879-50925 nap-of-the-earth flight LOW SPEED WIND TUNNELS [AilS 79-121 A79-49065 Aerodynamic interaction on a close-coupled MARINE PROPULSION canard-wing configuration Gas turbines for ICY's and hydrofoils [ONERA, TP NO. 1979-95] 879-49543 A79-47845 LOW VISIBILITY Jet propulsion forACV's and hydrofoils Handling quality and display requirements for low 879-47847 speed and hover in reduced flight visibility MARKET RESEARCH [ABS 79-29] 879-49081 Design criteria for airline operation Project NAVTOLAND (Navy vertical takeoff and [8188 PAPER 79-18119] A79-49337 landing capability development) MARKING B79-30212 Design procedure for aircrew station labeling LUBRICANTS selection and abbreviation Fuels, lubricants and other fluids used in aviation H79-30208 Russian book MATERIALS SCIENCE A79-47433 Handbook on aircraft materials and their LUBRICATION SYSTEMS application technology Self-contained grease lubrication systems for #79-48311 aircraft applications MATHEMATICAL MODELS [ABS 79-39] 879-49091 Optimal thermogasdynamic design of gas turbine engines using element prototypes. I A79-46997 M Performance modelling methods --- in flight test MAGNETIC FIELDS programs Small signal compensation of magnetic fields 179-50167 resulting from aircraft maneuvers ONERA's model of the pilot in discrete time A79-49605 N79-30242 MAGNETOMETERS Global enclosure fire modeling with applications Small signal compensation of magnetic fields N79-31172 resulting from aircraft maneuvers Fuel tank survivability for hydrodynamic ram A79-49605 induced by high velocity fragments. Part 2: MAINTAINABILITY Numerical analyses Helicopter drive system H and N design guide [AD-8070128] 1179-31200 (AD-A069691] 1179-30181 An actuator disk analysis of an isolated rotor MAINTENANCE with distorted inflow F-16 Avionics Intermediate Shop /AIS/ Interim AD-A069884] 1179-31216 Contractor Support initiatives MATRICES (MATHEMATICS) [AIAA PAPER 79-1868] 879-47923 Equation modifying program, L219 (EQNOD) . Volume MAN MACHINE SYSTEMS 2: Supplemental system design and maintenance A deterministic investigation of strapped down document navigation system accuracy [NASA-CR-2856J N79-31153 A79-48695 A program for calculating load coefficient Helmet mounted display and sight development matrices utilizing the force summation method, (AHS 79-17] A79-49070 1218 (LOADS). Volume 2: Supplemental system Piloted simulator investigation of helicopter design and maintenance document control systems effects on handling qualities [NASA-CR-2854] 1179-31155 during instrument flight Investigation of inverse Vandermonde matrix [ABS 79-26] #79-49078 calculation for linear system applications Handling quality and display requirements for low adaptive flight control systems speed and hover in reduced flight visibility [AD-A069241] N79-31225 (ABS 79-291 #79-49081 MAXIMUM LIKELIHOOD ESTIMATES Role of Numerical Control Design in the computer Digital adaptive control laws for VTOL aircraft aided design/manufacturing interface at Sikorsky A79-48000 CARS 79-30) 879-49082

A-36

SUBJECT INDEX MILITARY OPERATIONS

Multisensor integration for defensive fire control MICROWAVE LANDING SYSTEMS surveillance Guidance accuracy considerations for the microwave A79- 48610 landing system L-band precision ORE A computer program for aircraft identification and A79-48692 derivative extraction Advances in decelerating steep approach and A79-50306 landing for helicopter instrument approaches Considerations in the analysis of flight test [ABS 79-16] A79-49069 maneuvers GCU, the Guidance and control Unit for all weather A79-50433 approach U79-30213 MEASURING INSTRUMENTS Analytic redundancy for flight control sensors on Flight performance of the TCV B-737 airplane at the Lockheed L-1011 aircraft Kennedy Airport using TRSB/MLS guidance A79-47960 [NASA-TM-80148] N79-31186 Flight test verification of the ASSET system Multipath propagation measurement by Doppler Advanced Skewed Sensory Electronic Triad technique A79-48622 N79-31478 MECHANICAL DRIVES MICROWAVE SENSORS Rotorshaft torguemeter --- principles and The application of pulsed 'G band radio altimeters to modern military aircraft applications A79-49590 [ABS 79-383 879-49090 Ground test vehicle testing --- in helicopter MICROWAVE TRANSMISSION development programs The servoed modulation FMCW radar altimeters in (ABS 79-40] A79-49092 military applications Helicopter drive system B and H design guide A79-49589 [AD-A069835] 879-30180 MILITARY AIR FACILITIES MECHANICAL PROPERTIES An evaluation of asphalt-rubber mixtures for use An approach for estimating vibration in pavement systems characteristics of nonuniform rotor blades [80-8069448] 879-30246 A79-49718 MILITARY AIRCRAFT Electric power system control techniques Mechanical and thermophysical properties of 879-48614 graphite/polyimide composite materials 879-30317 Advanced NPV electrical systems Development of aircraft lavatory compartments with 879-48615 improved fire resistance characteristics. Phase The effect of standardization of avionics software 2: Sandwich panel resin system development quality assurance A79-48648 [NASA-CB-152120] 879-31354 METAL BONDING Evaluation of selected class III requirements of The influence of the environment on the MIL-F-8785R /ASG/, 'Flying Qualities of Piloted elastoplastic properties of adhesives in metal Airplanes' bonded joints --- In aircraft structures A79-50439 [BSA-TT-521] 879-30391 Naval aircraft operating and support METAL COATINGS cost-estimating model, FT 1977 revision Metallic coatings for graphite/epoxy composites [80-8068175] 879-30140 879-30334 Enforcer aircraft [AD-A069871) 879-30174 METAL MATRIX COMPOSITES [GPO-32-569] Metal-matrix composite structures Design procedure for aircrew station labeling A79-49086 selection and abbreviation [ABS 79-34] 879-30208 METEOROLOGICAL INSTRUMENTS A low-velocity airflow calibration and research GcU, the Guidance and control Unit for all weather approach facility N79-30213 [PB-294501/2] 879-31237 METEOROLOGICAL RADAR MILITARY AVIATION Real time weather display in the general aviation The application of pulsed • G band radio altimeters to modern military aircraft cockpit A79-49590 [AIAA PAPER 79-1821) A79-47901 MR-262 AIRCRAFT MILITARY HELICOPTERS Aircraft accident report: Swift Aire Lines, Inc., Design and development of the Agusta A 109 Nord 262, 841858, Marina Del Bey, California, helicopter A79-49815 March 10, 1979 [NTSB-AAR-79-13) 879-31165 Maintenance cost study of rotary wing aircraft, MICROCOMPUTERS phase 2 Microcomputer applications in strapdown heading [NASA-cR-152291] 879-30138 and attitude reference system AB-1G helicopter, 19-round lightweight airborne A79-48606 launcher jettison envelope determination Microcomputer control of a test facility --- for [80-8069828] 879-30177 avionics A helicopter high definition rotor blade radar A79-48672 N79-30207 MICROELECTRONICS Subjective assessment of a helicopter approach New devices for digital communications in avionics system for IFR conditions 879-31481 N79-30209 The equipment-system interface in an antitank MICROPROCESSORS Microprocessor-based digital autopilot development helicopter at night for the XBQM-106 Mini-RPY 879-30211 A79-48608 Project NAVTOLAND (Navy vertical takeoff and Built in test of A/D converters - Present landing capability development) approaches and recommendations for improved BIT N79-30212 effectiveness --- in airborne radar systems Implementation of flight control in an integrated A79-48621 guidance and control system A microprocessor system for flight control research 879-30215 879-48623 Stabilizing electra-optical systems on helicopters The impact of a multi-function programmable N79-30216 control display unit in affecting a reduction of MILITARY OPERATIONS pilot workload Distributed TDMA - An approach to JTIDS phase II N79-30210 Time Division Multiple Access Joint Tactical Information Distribution System MICROWAVE EQUIPMENT A79-49584 Airborne microwave FcM A79-49554 Tactical performance characterization basic methodology [AD-A069297] 879-31235

A-37

MILITARY TECHNOLOGY SUBJECT INDEX

MILITARY TECHNOLOGY NAVIGATION AIDS Multiband antenna --- for tactical naval aircraft A simple integrated navigation based on multiple DME A79-48596 [DGLR PAPER 79-041] 579-48640 Application of instrument rotation in the N73 Application of instrument rotation in the N73 standard inertial navigation system standard inertial navigation system A79-48696 579-48696 Air Force modular automatic test equipment Meeting the challenge of precise navigation during development program nap-of-the-earth flight - A79-48878 [ABS 79-12) 579-49065 Techniques for fault isolation ambiguity reduction Navstar user equipment for civil and military in military avionics applications A79-48891 579-49587 MILLIMETER WAVES NAVIGATION INSTRUMENTS Millimeter airborne radar target detection and A deterministic investigation of strapped down selection techniques navigation system accuracy A79-48665 A79-48695 MINICOMPUTERS JTIDS relative navigation - Architecture, error INACT - Interactive test data analysis --- with characteristics and operational benefits minicomputers Joint Tactical Information Distribution System 579-50430 A79-48715 MISSILE COMPONENTS System configuration and algorithm design of the Ultra-high-modulus graphite-epoxy conical shell inertially aided JTIDS Relative Navigation development, supplement function --- Joint Tactical Information [AD-A069795] 879-30335 Distribution System MISSILE CONTROL A79-48716 Complex quaternion notation in coordinate NAYSTAR SATELLITES transformations --- missile launching Navstar user equipment for civil and military aircraft-inertial space transformations applications A79-48681 579-49587 MISSION PLANNING NAVY Advanced Scout Helicopter flying qualities Naval aircraft operating and support requirements - How realistic are they cost-estimating model, F! 1977 revision [AHS 79-28) 579-49080 [AD-A068175] 1479-30140 NODAL RESPONSE Maintenance improvement: An analysis approach Experimental measurements of the rotating including inferential technical da t a --- naval frequencies and node shapes of a full scale aircraft helicopter rotor in a vacuum and correlations [AD-A068382] 1479-301141 with calculated results NETWORK SYNTHESIS [ABS 79-18] 579-49071 Performance of current radar systems in an EN MONOPOLE ANTENNAS environment --- Electronic Warfare Radiation from quarter-wavelength monopoles on A79-49555 finite cylindrical, conical, and rocket-shaped NEWTON-RAPHSON METHOD conducting bodies --- airborne antenna design Lateral aerodynamics extracted from flight test 579-50606 using a parameter estimation method MONTE CARLO METHOD [ARL-AERO-NOTE-380] N79-31146 Performance of a pulse-decode circuit in the NIGHT PLIGHTS (AIRCRAFT) presence of interference Pave Low III --- 11-53 helicopter avionics for 579-48713 night/adverse weather rescue of military aircraft MOVING TARGET INDICATORS A79-48682 Automated tracking for aircraft surveillance radar H-I combat search and rescue avionics study results systems A79-48684 A79-49604 The equipment-system interface in an antitank MULTIPATH TRANSMISSION helicopter at might Multipath propagation measurement by Doppler 1479-30211 technique NIGHT VISION N79-31478 Scan converter and raster display controller for Investigation on information error caused by night vision display systems traffic loading in approach and landing systems N79-30203 N79-31480 NITROGEN OXIDES MULTIPLEXING Correlation technique for ambient effects on Multiplex technology applied to helicopters oxides of nitrogen --- from combustion products [ABS 79-14] A79-49067 in atmospheric pollution State of the art in digital signal processing with A79-49922 applications to multiple access systems NOISE GENERATORS N79-31487 Study of design constraints on helicopter noise Implementing .JTIDS in tactical aircraft [NASA-CR-159118] 1479-32054 N79-31491 NOISE INTENSITY Experimental investigation of helicopter flight modes on helicopter-generated noise N A79-47873 NACELLES Noise generation by jet-engine exhaust deflection Performance of a V/STOL tilt nacelle inlet with [DLR-FB-78-21] 1479-30192 blowing boundary layer control NOISE MEASUREMENT (AIAA PAPER 79-1163) 579-47347 The aeroacoustics of advanced turbopropellers Full-scale wind tunnel study of nacelle shape on A79-50236 cooling drag NOISE PROPAGATION [AIAA PAPER 79-1820] A79-47900 QCSEE - The key to future short-haul air transport Recent applications of theoretical analysis to Quiet, Clean, Short-Haul Experimental Engine V/STOL inlet design program A79-49530 579-50208 NASA PROGRAMS NOISE REDUCTION Design and testing of a redundant skewed inertial Helicopter noise rules - Are they appropriate and sensor complex for integrated navigation and reasonable flight control A79-49478 N79-30202 Supersonic transport aircraft noise, problems of NATIONAL AVIATION SYSTEM noise reduction and establishment of standards International Air Transportation Competition Act A79-50237 of 1978 --- congressional reports Supersonic transport vis-a-vis energy savings [GPO-34-912] 1479-30168 [NASA-TM-75464] 4479-31163

A-3 8

SUBJECT INDEX PAPERS

Evaluation of p-ill weapon bay aero-acoustic and NUMERICAL INTEGRATION weapon separation improvement techniques Use of the method of variable directions for [AD-A070253] ii79-31203 numerical study of the temperature states of a NONFLAMMABLE MATERIALS turbine disk with blades Conference on Fire Resistant Materials: A A79-48518 compilation of presentations and papers (NASA-CP-2094) N79-31166 Status of candidate materials for full-scale tests in the 737 fuselage OFFSHORE PLATFORMS N79-31170 Flight investigation of helicopter lYE approaches Fire resistant aircraft seat program to oil rigs using airborne weather and mapping 1479-31176 radar A review of Boeing interior materials and fire [AHS 79-52] A79-49104 test methods development programs OMEGA NAVIGATION SYSTEM N79-31177 Operational experience with the AN/ARN-131 omega FIREMEN program Navigation Set N79-31178 A79-48676 NONLINEAR EQUATIONS OPERATING SYSTEMS (COMPUTERS) Most rational linearization of nonlinear unsteady Modal interpolation program, L215(INTERP). Volume beat conduction problems --- for flight vehicle 2: Supplemental system design and maintenance parts and engines document --- to calculate displacements at A79-98501 several points on an aerodynamic surface NONLINEAR PROGRAMMING [NASA-CE-2848] N79-31147 Optimal thermogasdynamic design of gas turbine OPTICAL HETERODYNING engines using element prototypes. I Multifunction CO2 heterodyning laser radar for low A79-46997 level tactical operations A79-48685 NONLINEAR SYSTEMS Application of bifurcation analysis and OPTICAL PROPERTIES catastrophe theory methodology /BACTM/ to Windshield technology demonstrator program-canopy aircraft stability problems at high detail design options study angles-of-attack [AD-A070376] 1179-31201 A79-47943 OPTICAL RADAR Theoretical estimation of nonlinear longitudinal Multifunction CO2 heterodyning laser radar for low characteristics of wings with small and moderate level tactical operations aspect ratio by the vortex-lattice method in A79-48685 incompressible flow Heterodyning CO2 laser radar for airborne [DLR-FB-78-26] N79-30161 applications Investigation of roll performance for a highly N79-30205 nonlinear statically unstable fighter-type OPTICAL RANGE FINDERS aircraft Determining the contour of helicopter rotor blades [AD-A0693011 N79-31199 automatically using electro-optical techniques A79-49084 NONUNIFORM FLOW [AilS 79-32] An actuator disk analysis of an isolated rotor OPTIMAL CONTROL with distorted inflow Predictive guidance for interceptors with time [AD-A069884] N79-31216 delays A79-47939 ROSE FINS An investigation of the rolling stability A multiple objective optimization approach to derivatives of a I-tail fighter configuration at aircraft control systems design high angles-of-attack A79-47962 A79-50165 Linearization of the boundary-layer equations of NOZZLE DESIGN the minimum time-to-climb problem Nozzles for vectored thrust jet engines A79-49869 Russian book ONERA's model of the pilot in discrete time A79-47428 N79-30292 The nonaxisyinmetric nozzle - It is for real OPTIMIZATION fighter aircraft performance viewpoint Optimal thermogasdynamic design of gas turbine [AIAA PAPER 79-1810] A79-47893 engines using element prototypes. I Performance evaluation of an air vehicle utilizing A79-46997 non-axisymmetriC nozzles Solution of the inverse aerodynamics problem by (AIAA PAPER 79-1811] A79-47894 the random search method A79-47002 NOZZLE FLOW Experimental study of the gasdynamic Application of Lagrange Optimization to the drag characteristics of a stator cascade with cooling polar utilizing experimental data air - discharge through the vane surface [AIAA PAPER 79-1833] A79-49335 A79-48498 OXYGEN Effect of nozzle spacing on ground interference Characteristics of afterburning bypass turbojet forces for a two jet V/STOL aircraft engine with oxygen injection into the (&IAA PAPER 79-1856] A79-49339 afterburner chamber NOZZLE GEOMETRY A79-48519 The nonaxisymmetric nozzle - It is for real fighter aircraft performance viewpoint [AIAA PAPER 79-18101 A79-47893 Aerodynamic and acoustic investigation of inverted P-3 AIRCRAFT velocity profile coannular exhaust nozzle models AN/USM-949/V/ ATE for worldwide support of the P3 and development of aerodynamic and acoustic Orion prediction procedures A79-48884 - (NASA-CE-3168] N79-31212 P-531 HELICOPTER NUMERICAL CONTROL Advanced Scout Helicopter flying qualities Computer Monitor and Control - A flexible, requirements - How realistic are they cost-effective implementation CARS 79-28] 839-49080 A79-48670 PANELS Microcomputer control of a test facility --- for Actively cooled plate fin sandwich structural avionics panels for hypersonic aircraft A79-48672 (NASA-CE-3159) 1179-31628 Role of Numerical Control Design in the computer PAPERS aided design/manufacturing interface at Sikorsky Contributions to fluid mechanics (ARS 79-30) A79-49082 N79-31524

A-39

PARAMETERIZATION SUBJECT INDEX

PARAETEEIZATION An evaluation of sidestick force/deflection AFFTC parameter identification experience --- for characteristics on aircraft handling qualities aircraft flight characteristics A79-50428 [8188 PAPER 79-1803] 879-47888 Subjective assessment of a helicopter approach Similitude requirements and scaling relationships system for IFR conditions as applied to model testing 879-30209 [NASA-TP-1435] 879-30176 Testing and analysis of dual-mode adaptive landing PASSENGER AIRCRAFT gear, taxi mode test system for YF-12A Selection of geometric parameters and location of (NASA-CR-144884) 879-31192 nose flap on swept wing root profile from tunnel Aerodynamic performance of axial-flow fan stage test data. I operated at nine inlet guide vane angles --- to 879-46999 be used on vertical lift aircraft Selecting the passenger airplane fuselage [NASA-TP-1510) 879-31214 879-47014 PERIPHERAL JET FLOW The aerial relay system - An energy-efficient Surface-effect components of aerodynamic solution to the airport congestion problem characteristics of air-cushion vehicle with ram using cruise liner aircraft for in-air passenger pressurization transfer A79-46995 [AIAA PAPER 79-1865) 879-47921 PERTURBATION THEORY Design criteria for airline operation Application of singular perturbation techniques [AIAA PAPER 79-1849] A79-49337 /SPT/ and continuation methods for on-line Fire resistant aircraft seat program aircraft trajectory optimization N79-31176 879-47991 PATTERN RECOGNITION A study of the application of singular Estimation of aircraft target motion using pattern perturbation theory --- development of a real recognition orientation measurements time algorithm for optimal three dimensional A79-47987 aircraft maneuvers Preprocessing for advanced image matching techniques [NASA-CR-3167] N79-30194 A79-48602 PHENOLIC RESINS Synthetic aperture radar map matching for navigation Development of aircraft lavatory compartments with A79-48603 improved fire resistance Characteristics. Phase Applications of pattern recognition systems for 2: Sandwich panel resin system development day/night precision aircraft control [NASA-CR-152120.] N79-31354 W79-30204 PHILOSOPHY PAVEMENTS L-1011 active controls, design philosophy and An evaluation of asphalt-rubber mixtures for use experience in pavement systems N79-30236 [AD-A069448) 879-302116 PHOTOELASTIC ANALYSIS PERFORMANCE PREDICTION Designing with experimental mechanics Air buoyant vehicles - Energy efficient aircraft three-dimensional photoelastic analysis of [8188 PAPER 79-1862) 879-47919 helicopter components Helicopter performance methodology at Bell (ABS 79-11) 879-49063 Helicopter Textron PILOT PERFORMANCE [ABS 79-2] 879-49055 ONERA • s model of the pilot in discrete time Improved method of predicting helicopter control N79-30242 response and gust sensitivity Flight experience with advanced controls and [ABS 79-251 879-49077 displays during piloted curved decelerating The size and performance effects of high lift approaches in a powered-lift STOL aircraft system technology on a modern twin engine jet B79-30243 transport - Ride qualities criteria validation/pilot [8188 PAPER 79-1795] 879-49332 performance study: Flight test results A design perspective on new technologies for [NASA-CR-144885] 879-31193 general aviation A compilation and analysis of helicopter handling A79-49486 qualities data. Volume 2: Data analysis Performance predictions for open ocean air cushion [NASA-CR-a 145] 879-31222 vehicles and surface effect ships PILOT TRAINING A79-49905 Flight testing and simulator flight fidelity Dynamic test techniques - Concepts and practices determination at Naval Air Test Center aircraft performance prediction from A79-50307 thrust/lift/drag model PISTON ENGINES A79-50164 Fuels, lubricants and other fluids used in aviation Performance modelling methods --- in flight test Russian book programs A79-47433 879-50167 Critical assessment of emissions from aircraft PERFORMANCE TESTS piston engines The DG-800 - A rugged, high performance heading (AD-A071002] 879-30190 reference unit --- directional gyro design Exhaust emissions characteristics for a general considerations aviation light aircraft Teledyne Continental A79-48677 Motors TSIO-360-C piston engine A new U.U.T./test station interface [AD-A070010] N79-31211 A79-48896 PITCH (INCLINATION) Crashworthy armored crewseat for the 08-608 Black On the influence of relative pitch in the subsonic Hawk turbine cascade (ABS 79-10] 879-49062 A79-48503 The Sikorsky elastomeric rotor --- helicopter Heave-pitch-roll analysis and testing of air rotor bearings cushion landing systems [AHS 79-48] 879-49100 [NASA-CB-2917] 879-30175 The circulation control rotor flight demonstrator PLASTIC AIRCRAFT STRUCTURES test program Windshield technology demonstrator program-canopy [AHS 79-511 879-49103 detail design options study Ultrasonic method of gun gas detection --- for (AD-A070376] N79-31201 engine ingestion prevention in F-15 PLUMES A79-50166 Analysis of plume rise from jet aircraft Flight testing and simulator flight fidelity [cONF-790142-1] 879-31204 determination at Naval Air Test Center PNEUMATIC EQUIPMENT A79-50307 The circulation control rotor flight demonstrator The Swedish approach to escape system testing test program A79-50427 [ABS 79-51] A79-49103

8-40

SUBJECT INDEX PROPELLER FANS

POINTING CONTROL SYSTEMS Applications of pattern recognition systems for Transfer alignment for precision pointing day/night precision aircraft control applications --- in inertial navigation systems V79-30204 A79-48679 PREDICTION ANALYSIS TECHNIQUES POLLUTION CONTROL Predictive guidance for interceptors with time Experimental Clean Combustor Program (ECCP) , phase 3 delays commercial aircraft turbofan engine tests A79-47939 with double annular combustor Avionics computer software operation and support (NASA-CR-135384] 879-31207 cost estimation POLLUTION MONITORING A79-48620 Exhaust emission traverse investigation of a PREDICTIONS JT3D-1 turbofan engine --- to acquire exhaust Study of design constraints on helicopter noise nozzle emission sample [NASA-CR-159118] 879-32054 [AD-A072019] 879-31209 PRESSING (FORMING) Exhaust emissions characteristics for a general Achieving consistency in the production of aviation light aircraft Teledyne Continental critical jet engine components by means of press Rotors TSIO-360-C piston engine forging [AD-A070010] 879-31211 179-48945 POLYESTER RESINS PRESSURE DISTRIBUTION Evaluation of airfield pavement materials based on Solution of the inverse aerodynamics problem by synthetic polymers the random search method P.79-49348 A79-47002 POLYESTERS PRESSURE EFFECTS The fluorenone polyester ISO FPE of Isovolta Effect of steady-state temperature distortion and Company, Austria combined distortion on inlet flow to a turbofan 879-31183 engine POLYIMIDE RESINS [RASA-TM-79237] 879-30187 Development and demonstration of manufacturing PRESSURE MEASUREMENTS processes for fabricating graphite/PMR-15 Aerodynamic performance of 1.38-pressure-ratio, polyimide structural elements --- space shuttle variable-pitch fan stage aft body flap (NASA-TP-1502] 879-31213 N79-30301 PROBLEM SOLVING Development of fire-resistant, low smoke ATLAS, an integrated structural analysis and generating, thermally stable end items for design system. Volume 5: System demonstration commercial aircraft and spacecraft using a basic problems polyimide resin [RASA-CB-159045] 879-31624 879-31171 PRODUCT DEVELOPMENT POLYMER MATRIX COMPOSITE MATERIALS Compass Cope airframe design history Development and demonstration of manufacturing [AIAA PAPER 79-1792] P.79-47881 processes for fabricating graphite/PNR-15 CABAN data handling from conceptual design through polyimide structural elements --- space shuttle produce support aft body flap [AIAA PAPER 79-1846] P.79-47912 N79-30301 Air Force modular automatic test equipment POLYMERS development program Evaluation of airfield pavement materials based on A79-48878 synthetic polymers Antennas for the Black Hawk helicopter 879-119348 [885 79-15] P.79-49068 POLYURETHANE FOAM The DC-9 Super 80 - Much more than a simple stretch Evaluation of airfield pavement materials based on A79-49223 synthetic polymers A design perspective on new technologies for A79-49348 general aviation POROSITY A79-49486 Wall corrections in transonic wind tunnel: Small hovercraft design - Evolution to simplicity Equivalent porosity A79-49906 (ESA-TT-5 115) 879-30247 Current Canadian developments related to low-speed POSITION (LOCATION) heavy lift ACT Low cost inertial aiding for NAVSTAR/GPS receivers P.79-49915 in naval ship navigation Aircraft engine developments centre on improved 879-48656 performance, higher efficiency POSITION ERRORS A79-50207 Transfer alignment for precision pointing PRODUCTION ENGINEERING applications --- in inertial navigation systems Engineering and manufacturing communication via P.79-48679 the computer data base Evaluation of the radar altimeter reference method [P.111 PAPER 79-1845] P.79-47911 for determining altitude system positioning errors PRODUCTION MANAGEMENT A79-50436 Geometric data transfer --- for computerized POTENTIAL FLOW aircraft engineering drawings Fully conservative numerical solutions for [ATAP. PAPER 79-1844] P.79-47910 unsteady irrotational transonic flow about F-16 Avionics Intermediate Shop /AIS/ Interim airfoils Contractor Support initiatives [ATAl PAPER 79-1555] P.79-47342 [AAA PAPER 79-1868] P.79-47923 POWER SUPPLY CIRCUITS PROGRAM VERIFICATION (COMPUTERS) Power hybridization - Key to reducing avionics Computer Monitor and Control - A flexible, power supply weight and volume cost-effective implementation A79-48652 P.79-48670 POWER TRANSMISSION Evolving methods for reducing avionics data in an E-4B mission electrical power 11SF environment -,- Avionics Integration A79-48617 Suppport Facility flight program testing POWERED LIFT AIRCRAFT A79-48671 Powered low-aspect-ratio Wing In Ground effect Testability, the key to economical and (WIG) aerodynamic characteristics --- conducted operationally effective avionic test software in Langley V/STOL tunnel A79-48890 [NASA-TN-78793] 879-31141 PROPELLER BLADES PRECISION The aeroacoustics of advanced turbopropellers Guidance accuracy considerations for the microwave A79-50236 landing system L-band precision ONE PROPELLER FANS A79-48692 LDV measurements on propellers P.79-49052

A-41

PROPULSION SYSTEM CONFIGURATIONS SUBJECT INDEX

PROPULSION SYSTEM CONFIGURATIONS Determining the contour of helicopter rotor blades The principles of hovercraft, powering and automatically using electro-optical techniques propulsion EARS 79-32] A79-49084 A79-47844 Automatic scanning inspection of composite Engine-aircraft afterbody interactions - helicopter structure using an advanced Recommended testing techniques based on YF-17 technology fluoroscopic system experience CARS 79-35) A79-49087 [AIAA PAPER 79-1829] A79-47903 What the FAA would like in airworthiness standards The characteristics of a lift cruise fan V/STOL [AIAA PAPER 79-1851] A79-49338 configuration in near proximity to a small deck QUATERNIONS with finite edge positions Complex quaternion notation in coordinate [AIAA PAPER 79-1854] A79-47913 transformations --- missile launching Conceptual study of a turbojet/ramjet inlet aircraft-inertial space transformations [NASA-TN-80141) 879-31215 A79-48681 PROPULSION SYSTEM PERPORNAICE QUIET ENGINE PROGRAM Aerodynamic effects of an attitude control vane on QCSEE - The key to future short-haul air transport a tilt-nacelle V/STOL propulsion system Quiet, Clean, Short-Haul Experimental Engine [AIAA PAPER 79-1855] A79-47914 program PROPULSIVE EFFICIENCY A79-50208 Ten years of Aerospatiale experience with the fenestron and conventional tail rotor [ANn 79-58] A79-49108 A Powered low-aspect-ratio Wing In Ground effect RADAR ANTENNAS (WIG) aerodynamic characteristics --- conducted A report on the Sperry Dome Radar in Langley V/STOL tunnel A79-49567 [NASA-TN-78793] N79-31141 RADAR APPROACH CONTROL PROTECTION Flight investigation of helicopter IFR approaches Helicopter obstacle strike tolerance concepts to oil rigs using airborne weather and mapping analysis radar [AD-A069877] 879-30179 EARS 79-52] A79-49104 PROTECTIVE COATINGS A helicopter high definition rotor blade radar Metallic coatings for graphite/epoxy composites 879-30207 [AD-A069871] 879-30334 RADAR BEACONS PROTOTYPES Small lightweight electronically steerable Optimal thermogasdynamic design of gas turbine cylindrical antenna successfully utilized in an engines using element prototypes. I air traffic management system A79-46997 A79-48597 Realization of a helicopter-oriented real-time RADAR CROSS SECTIONS data system for research, experimental, and Radar cross section fundamentals for the aircraft prototype flight testing designer [AHS 79-50] A79-49102 [AIAA PAPER 79-1818] A79-47898 PULSE COMMUNICATION RADAR DATA Performance of a pulse-decode circuit in the Radar signal processing development for presence of interference application of VHSI A79-48713 A79-48664 Distributed TDRA - An approach to JTIDS phase II An analysis of SAPPHIRE image parameters as a Time Division Multiple Access Joint Tactical function of processing parameters --- for Information Distribution System synthetic aperture radar data processing A79-49584 A79-48666 A novel approach to the design of an all digital RADAR EQUIPMENT aeronautical satellite communication system Test implementation through support software - A N79-31461 FIT translator --- automated Fault Isolation A digital communication system as gateway between Tests on airborne radar system adjacent computerized air traffic control centres A79-48687 N79-31463 The impact of software in automatic test equipment - Performance predictions and trials of a helicopter for evaluation of radar analog to digital UHF data link converter 879-31476 A79-48691 PULSE RADAR Performance of current radar systems in an EW The application of pulsed G band radio environment --- Electronic Warfare altimeters to modern military aircraft A79-49555 A79-49590 RADAR IMAGERY PYROLYSIS Preprocessing for advanced image matching techniques Electrical insulation fire characteristics. A79-48602 Volume 2: Toxicity Synthetic aperture radar map matching for navigation [P8-294841/2] 879-30490 A79-48603 Digital sensor simulation at the Defense Rapping Agency Aerospace Center A79-48705 QUALITY CONTROL RADAR NAPS The effect of standardization of avionics software Digital sensor simulation at the Defense Napping quality assurance Agency Aerospace Center A79-48648 A79-48705 A Navy plan for the development of a practical RADAR NEASURENENT computer-aided programming /CAP/ system for Nultiradar tracking system using radial velocity analog circuit test design measurements A79-48870 A79-49608 Avionics design for testability - An aircraft RADAR NAVIGATION contractor's viewpoint Synthetic aperture radar map matching for navigation A79-48888 A79-48603 Techniques for fault isolation ambiguity reduction Flight investigation of helicopter IFR approaches in military avionics to oil rigs using airborne weather and mapping A79-48891 radar Achieving consistency in the production of [AHS 79-52] A79-49104 critical jet engine components by means of press Combined environment reliability test of the forging common strategic Doppler system A79-48945 A79-50368

A-42

SUBJECT INDEX RELIEF MAPS

RADAR TARGETS A real-time sequential filtering algorithm for GPS Millimeter airborne radar target detection and low-dynamics navigation system selection techniques A79-48657 A79-48665 A real time video bandwidth reduction system based Ellipsoidal modelling of aircraft targets for on a CCD Radamard transform device --- for evaluation of electronic fuzes avionics A79-49580 A79-48702 RADAR TRACKING Real time compression of video signals Estimation of aircraft target motion using pattern protection against jamming recognition orientation measurements A79-48712 A79-47987 Realization of a helicopter-oriented real-time The alpha-beta-gamma tracking filter in the Z-domain data system for research, experimental, and in aircraft tracking prototype flight testing A79-48680 (AHS 79-50) A79-49102 The A.I. tracking problem --- Airborne Interception Central flow control software design document. A79-49566 Volume 1: Operational software complex Multiradar tracking system using radial velocity automation support to the Air Traffic Control measurements System Command center A79-49608 [AD-A070973) 879-30959 RADAR TRANSMISSION Central flow control software design document. The servoed modulation FMCW radar altimeters in Volume 2: Support software complex military applications automation support to the Air Traffic Control A79-49589 System Command center. RADAR TRANSMITTERS [AD-A070771] 879-30960 Tactical electronic reconnaissance sensor RECONNAISSANCE AIRCRAFT radar emission detection Compass Cope airframe design history P.79-48717 [AIAA PAPER 79-1792] A79-47881 RADIAL VELOCITY Maritime patrol airship concept study Multiradar tracking system using radial velocity (AD-A070131) N79-31138 measurements RECTANGULAR RINGS P.79-49608 The calculation of non-linear aerodynamic RADIATION PROTECTION characteristics of wings and their wakes in Lightning hazards overview: Aviation requirements subsonic flow and interests A79-47099 4479-30876 REDUNDANT COMPONENTS RADIO ALTIMETERS Analytic redundancy for flight control sensors on A new three-dimensional surveillance radar the Lockheed 1-1011 aircraft P.79-49568 A79-147960 The servoed modulation FMCW radar altimeters in Failure detection in signal processing and sensing military applications in flight control systems P.79-49589 A79-47971 The application of pulsed . G . band radio Program for the critical components of a altimeters to modern military aircraft fly-by-tube backup flight control system, part 1 A79-49590 [AD-A070387] 4479-31226 Evaluation of the radar altimeter reference method REFERENCE SYSTEMS for determining altitude system positioning errors Microcomputer applications in strapdown heading A79-50436 and attitude reference system RADIO ANTENNAS A79-48606 Radiation from quarter-wavelength monopoles on REGIONAL PLANNING finite cylindrical, conical, and rocket-shaped A developmental computer model for investigations conducting bodies --- airborne antenna design of air traffic management problems: A case P.79-50606 investigating two decision strategies UHF coplanar-slot antenna for [AD-A071075] 4479-31189 aircraft-to-satellite data communications REINFORCED PLASTICS [NASA-TM-79239] 4479-31185 High-performance reinforced plastic structures for RADIO COMMUNICATION civil aviation Multiband antenna --- for tactical naval aircraft A79-47302 A19-48596 REINFORCING FIBERS UHF coplanar-slot antenna for High performance composites and adhesives for aircraft-to-satellite data communications V/STOL aircraft [NASA-TM-79239] 4479-31185 [AD-A069611] 4479-30332 RADIO CONTROL RELEASING Radio-controlled model design and testing Global enclosure fire modeling with applications techniques for stall/spin evaluation of 4479-31172 general-aviation aircraft RELIABILITY ANALYSIS [NASA-TM-80510] 4479-30173 Statistical diagnostics of aircraft engines RADIO RECEIVERS A79-46996 Navstar user equipment for civil and military Combined environment reliability test of the applications common strategic Doppler system P.79-49587 P.79-50368 R A DO MRS RELIABILITY ENGINEERING Recent advances in radome design The DG-800 - A rugged, high performance heading A79-49574 reference unit --- directional gyro design RAMJET ENGINES considerations Conceptual study of a turbojet/ramjet inlet A79-48677 [NASA-TM-80141] 4479-31215 User requirements for future combat search and RANDOM PROCESSES rescue vehicles Solution of the inverse aerodynamics problem by A79-48683 the random search method Reliability improvement warranty terms and A79-47002 conditions for the Integrated Avionics Control REACTION TIME Systems (IACS) Rapid reaction time techniques for a strapdown [AD-A0694454] 4479-31205 navigator employing electrostatic gyro technology RELIEF MAPS A79-48697 Meeting the challenge of precise navigation during REAL TIME OPERATION nap-of-the-earth flight Real time weather display in the general aviation [ABS 79-12] A79-49065 cockpit [AIAA PAPER 79-1821) A79-47901

A-43

RELIEF VALVES SUBJECT INDEX

RELIEF VALVES REYNOLDS NUMBER Previsions and experimental results in open Correlation of data related to shock-induced balloon controlled descent trailing-edge separation and extrapolation to 1179-31691 flight Reynolds number REMOTE CONTROL [NASA-CR-3178] 1179-31195 Previsions and experimental results in open RIDING QUALITY balloon controlled descent Ride qualities criteria validation/pilot 1179-31691 performance study: Flight test results REMOTE SENSORS [NASA-CR-144885) 1179-31193 Preprocessing for advanced image matching techniques RIGID ROTOR HELICOPTERS A79-48602 Project NAVTOLAND (Navy vertical takeoff and Multisensor integration for defensive fire control landing capability development) surveillance N79-30212 679-48610 RING WINGS REMOTELY PILOTED VEHICLES Harmonic oscillations of annular wing in steady Flight control systems development of highly ideal fluid flow maneuverable aircraft technology /HINAT/ vehicle A79-47009 [AIAA PAPER 79-1789] A79-47878 ROCKET LAUNCHERS Compass Cope airframe design history Helicopter component environmental vibration [AIAA PAPER 79-1792] 679-47881 testing - The poor man's fatigue test Microprocessor-based digital autopilot development [ABS 79-49] A79-49101 for the XBQM-106 Mini-RPV AB-1G helicopter, 19-round lightweight airborne 679-148608 launcher jettison envelope determination Advanced RPV electrical systems [AD-A069828) 1179-30177 679-448615 ROCKET THRUST Wind-tunnel investigation of an armed mini Some results from the use of a control remotely piloted vehicle --- conducted in augmentation system to study the developed spin Langley V/STOL tunnel of a light plane [NASA-TM-80132] 1179-31151 [AIAA PAPER 79-1790] 679-47879 REPORTS ROLL Contributions to fluid mechanics Heave-pitch-roll analysis and testing of air 1179-31524 cushion landing systems RESCUE OPERATIONS [NASA-CR-2917] 1179-30175 Pave Low III --- 8-53 helicopter avionics for Investigation of roll performance for a highly night/adverse weather rescue of military aircraft nonlinear statically unstable fighter-type A79-48682 aircraft User requirements for future combat search and [60-6069301] N79-31199 rescue vehicles ROLLER BEARINGS A79-48683 Tapered roller bearing development for aircraft H-X combat search and rescue avionics study results turbine engines A79-48684 [AD-A069440) 1179-30555 An advanced guidance and control system for rescue ROTARY STABILITY helicopters Rotary balance data for a typical single-engine N79-30217 general aviation design for an angle-of-attack RESEARCH range of 8 deg to 90 deg. 2: High-wing model A Contributions to fluid mechanics [NASA-CR-3101] 1179-31149 1179-31524 ROTARY WING AIRCRAFT RESEARCH AIRCRAFT A system for interdisciplinary analysis - A key to The effects of configuration changes on spin and improved rotorcraft design recovery characteristics of a low-wing general [AHS 79-8] A79-49060 aviation research airplane Maintenance cost study of rotary wing aircraft, [AIAA PAPER 79-1786] 679-447876 phase 2 Flight control systems development of highly [NASA-CR-152291] 1179-30138 maneuverable aircraft technology /HiNAI/ vehicle ROTARY WINGS [AIAA PAPER 79-1789] A79-47878 Effect of tip shape on blade loading Some flight data extraction techniques used on a characteristics for a two-bladed rotor in hover general aviation spin research aircraft [ABS 79-1] 679-490544 [AIAA PAPER 79-1802] A79-47887 A lifting-surface method for hover/climb airloads A microprocessor system for flight control research [ABS 79-3) A79-49056 A79-48623 The influence of sweep on the aerodynamic loading Performance evaluation method for dissimilar of an oscillating NACA 0012 airfoil aircraft designs --- using the square of the [AHS 79_4] 679-49057 wing span for nonditnensional comparisons of An integrated analytical and experimental aerodynamic characteristics investigation of helicopter hub drag [NASA-RP-1042] 1179-30139 [ASS 79-5] A79-49058 RESEARCH AND DEVELOPMENT Experimental measurements of the rotating Historical development of worldwide supersonic frequencies and node shapes of a full scale aircraft helicopter rotor in a vacuum and correlations [AIAA PAPER 79-1815] 679-47895 with calculated results RESEARCH VEHICLES [ABS 79-18] A79-49071 Design of the circulation control wing STOL Dynamics requirements for an Advanced Scout demonstrator aircraft Helicopter /ASH/ [AIAA PAPER 79-1842] A79-47909 [AHS 79-19] 679-49072 RESONANCE TESTING Theoretical flap-lag damping with various dynamic Full scale ground and air resonance testing of the inflow models Army-Boeing Vertol Bearingless Main Rotor [AHS 79-20] A79-49073 CARS 79-23] 679-49075 Full scale ground and air resonance testing of the RESONANT FREQUENCIES Army-Boeing Vertol nearingless Main Rotor Experimental measurements of the rotating [ABS 79-23] 679-49075 frequencies and mode shapes of a full scale Determining the contour of helicopter rotor blades helicopter rotor in a vacuum and correlations automatically using electro-optical techniques with calculated results [ABS 79-32] A79-49084 [ABS 79-18] 679-49071 Qualification program of the composite main rotor RESONANT VIBRATION blade for the Model 2148 helicopter Full scale ground and air resonance testing of the [AHS 79-44] A79-49096 Army-Boeing Vertol Bearingless Main Rotor The Sikorsky elastomeric rotor --- helicopter [ABS 79-23] 679-49075 rotor bearings [AHS 79-48] 679-49100

A-44

SUBJECT INDEX SERVICE LIFE

The circulation control rotor flight demonstrator SAFETY MANAGEMENT test program Development of crashworthy passenger seats for [ABS 79-51] 179-49103 general-aviation aircraft Helicopter obstacle strike tolerance concepts (NASA-CR-159100) 879-31164 analysis SAILNINGS [AD-A069877] 879-30179 Flight experiments to evaluate the effect of Evaluation of pylon focusing for reduced wing-tip sails on fuel consumption and handling helicopter vibration characteristics [AD-A069712] 879-30196 A79-49818 A helicopter high definition rotor blade radar SANDWICH STRUCTURES H79-30207 Recent advances in radome design Study of design constraints on helicopter noise 179-49574 [NASA-CB-159118] 879-32054 Development of aircraft lavatory compartments with ROTOR AERODYNAMICS improved fire resistance characteristics. Phase Aerodynamic excitation forces of blade vibrations 2: Sandwich panel resin system development in axial turbomachinery as a result of (NASA-CR-152120] 879-31354 interference from nearby cascades SATELLITE NAVIGATION SYSTEMS A79-48572 Low cost inertial aiding for RAVSTAR/GPS receivers Effect of tip shape on blade loading in naval ship navigation characteristics for a two-bladed rotor in hover 179-48656 [ABS 79-1] 179-49054 P. real-time sequential filtering algorithm for GPS An integrated analytical and experimental low-dynamics navigation system investigation of helicopter hub drag A79-48657 (ABS 79-5) 179-49058 SATELLITE TRANSMISSION Ten years of Aerospatiale experience with the A novel approach to the design of an all digital fenestron and conventional tail rotor aeronautical satellite communication system [ABS 79-58] A79-49108 E79-31461 Interactional aerodynamics - A new challenge to SCALE MODELS helicopter technology The Beech Model 77 'Skipper spin program (ABS 79-59] 179-49109 [AIAA PAPER 79-1835] A79-47907 XV-15 flight test results compared with design goals Multiband antenna --- for tactical naval aircraft [lIlA PAPER 79-1839] 179-49336 A79-48596 Laser velocimeter applied to the study of circular Similitude requirements and scaling relationships distorsion effects in a low speed compressor as applied to model testing [ONERA, TP NO. 1979-30] A79-50925 [NASA-TP-1435] 879-30176 Performance of two-stage fan with a first-stage A force and moment test of a 1/24-scale F-ill rotor redesigned to account for the presence of model at Mach numbers from 0.7 to 1.3 a part-span damper [AD-1070192] 879-31156 (NASA-TP-1 1483) 879-30191 SEA ICE The promise of nulticyclic control --- to control Iceater I - Air cushion ice breaker in commercial fatiguing blade loads and rotor vibration operations [NASA-TM-78621] 879-31137 179-49912 ROTOR BLADES (TURBOMACHIEZET) SEAPLANES Design and development of a hybrid composite rotor Powered low-aspect-ratio wing In Ground effect blade for the circulation control rotor system (WIG) aerodynamic characteristics --- conducted (ABS 79-46) 179-49098 in Langley V/STOL tunnel An approach for estimating vibration [NASA-TM-78793] N79-31141 characteristics of nonuniform rotor blades SEATS A79-49718 Crashworthy armored crewseat for the OH-bOA Black Performance of two-stage fan with a first-stage Hawk rotor redesigned to account for the presence of [ABS 79-10] A79-49062 a part-span damper Development of crashworthy passenger seats for [NASA-TP-1483] 879-30191 general-aviation aircraft Aerodynamic performance of 1.38-pressure-ratio, (NASA-CR-159100] 879-31164 variable-pitch fan stage Seat test program [NASA-TP-1502] 879-31213 879-31168 An actuator disk analysis of an isolated rotor Fire resistant aircraft seat program with distorted inflow N79-31176 [AD-A069884] N79-31216 Seat cushion to provide realistic acceleration ROTOR LIFT cues to aircraft simulator pilot A lifting-surface method for hover/climb airloads (RASA-CASE-LAR-12149-2] 879-31228 (ABS 79-31 179-49056 SELECTION ROTORS Millimeter airborne radar target detection and Digital simulation of a three-phase generator selection techniques A79-48618 A79-48665 RUBBER SELF ALIGNMENT An evaluation of asphalt-rubber mixtures for use Transfer alignment for precision pointing in pavement systems applications --- in inertial navigation systems [AD-A069448] 879-30246 A79-48679 RUNWAYS SEPARATED FLOW Evaluation of airfield pavement materials based on Aerodynamics of spoiler control devices synthetic polymers [lIlA PAPER 79-1873] A79-47925 179-49348 Correlation of data related to shock-induced An evaluation of asphalt-rubber mixtures for use trailing-edge separation and extrapolation to in pavement systems flight Reynolds number [AD-A069448] 879-30246 [NASA-CR-3178] 879-31195 Surveys of grooves in 19 bituminous runways SEQUENTIAL CONTROL [AD-A069889] 879-31233 A real-time sequential filtering algorithm for GPS Runway configuration management system concepts low-dynamics navigation system [10-1069960] 879-31234 SERRATIA Boundary layer control on wings using sound and 'S leading edge serrations S-N DIAGRAMS [AIAA PAPER 79-1875] A79-47925 A users manual for a computer program to generate SERVICE LIFE fatigue spectrum loading sequences Long-life GTE operation based on technical condition (AD-A069288) 879-31198 Gas Turbine Engine 179-48517

A-45

SERVOCONTROL SUBJECT INDEX

Designing with experimental mechanics Nultisensor integration for defensive fire control three-dimensional photoelastic analysis of surveillance helicopter components A79-48610 [AHS 79-11] 179-49063 Quaternion matching in transfer alignment for SAE SERVOCONTROL motion compensation Structural aspects of active controls 179-48641 879-30221 Radar signal processing development for Results related to simulated and in-flight application of VHSI experimentation with an electric flight control A79-48664 system that can be generalized Transform domain processing for digital N79-30224 communication systems using surface acoustic Program for the critical components of a wave devices fly-by-tube backup flight control system, part 1 N79-31482 [AD-1070387] 879-31226 State of the art in digital signal processing with SERVONECHANISMS applications to multiple access systems Fluidics: Feasibility study B79-31487 electro/hydraulic/fluidic direct drive servo valve SIGNAL TO NOISE RATIOS (AD-A069798] 879-30195 Small signal compensation of magnetic fields SHAFTS (MACHINE ELEMENTS) resulting from aircraft maneuvers Helicopter drive system A and H design guide A79-49605 (10-1069835] N79-30180 SIGNATURE ANALYSIS SHIPS Radar cross section fundamentals for the aircraft Low cost inertial aiding for NAVSTAR/GPS receivers designer in naval ship navigation [AIAA PAPER 79-1818] A79-47898 A79-48656 SIKORSKY AIRCRAFT VTOL controls for shipboard landing Spirit helicopter handling qualities design and (NASA-CR-162140) 879-30193 development Simulation and study of V/STOL landing aids for (IRS 79-24) A79-49076 USMC AV-8 aircraft SIMILITUDE LAW N79-30214 Similitude requirements and scaling relationships SHOCK WAVE INTERACTION as applied to model testing Experimental measurements of shock/boundary-layer [NASA-TP-1435] 879-30176 interaction of a supercritical airfoil SIMULATION [1111 PAPER 79-1499] 179-473115 The Swedish approach to escape system testing SHOCK WAVE PROPAGATION A79-50427 Experiments of shock associated noise of SKIN (STRUCTURAL MEMBER) supersonic jets Actively cooled plate fin sandwich structural [1111 PAPER 79-1526] A79-47341 panels for hypersonic aircraft Numerical solution of the problem of unsteady [NASA-CR-3159] 879-31628 supersonic flow around the front part of the SKIN FRICTION wings with a detached shock wave Drag reduction by cooling in hydrogen-fueled A79-49456 aircraft SHOCK WAVES 179-49921 Subsonic and transonic flows on a variable sweep SKIRTS wing Performance predictions for open ocean air cushion [08281, TP NO. 1979-102] 179-48849 vehicles and surface effect ships Correlation of data related to shock-induced A79-49905 trailing-edge separation and extrapolation to Hovercraft skirt design requirements flight Reynolds number A79-49907 [NASA-CR-3178] 879-31195 Road fleet operation of air cushion assisted SHORT HAUL AIRCRAFT vehicles - An evaluation of technical and QCSEE - The key to future short-haul air transport economic problems Quiet, Clean, Short-Haul Experimental Engine 179-49910 program SLENDER WINGS A79-50208 Wing geometry effects on leading-edge vortices SHORT TAKEOFF AIRCRAFT [lIAR PAPER 79-1872] 179-49341 Wing aerodynamic loading caused by jet-induced SLOT ANTENNAS lift associated with STOL-OTW configurations UHF coplanar-slot antenna for (AIlA PAPER 79-1664] A79-47346 aircraft-to-satellite data communications Design of the circulation control wing STOL [NASA-TM-79239] 879-31185 demonstrator aircraft SOLID STATE DEVICES [AIAA PAPER 79-1842] 179-47909 The impact of a multi-function programmable Flight experience with advanced controls and control display unit in affecting a reduction of displays during piloted curved decelerating pilot workload approaches in a powered-lift STOL aircraft H79-30210 B79-30243 SOUND PRESSURE Effect of transport/bomber loads spectrum on crack Experiments of shock associated noise of growth supersonic jets [AD-A069287] 879-31197 [lIAR PAPER 79-1526] 179-47341 SIDE-LOOKING RADAR SOUND TRANSMISSION An analysis of SAPPHIRE image parameters as a Duct noise radiation through a jet flow function of processing parameters --- for A79-50110 synthetic aperture radar data processing SPACE SHUTTLE ORBITERS 179-48666 Development and demonstration of manufacturing SIGNAL DETECTION processes for fabricating graphite/PMR-15 Tactical electronic reconnaissance sensor polyimide structural elements --- space shuttle radar emission detection aft body flap A79-48717 N79-30301 SIGNAL DISTORTION SPACECRAFT COMMUNICATION Preprocessing for advanced image matching techniques UHF coplanar-slot antenna for A79-48602 aircraft-to-satellite data communications SIGNAL PROCESSING (NASA-TM-79239] 879-31185 Failure detection in signal processing and sensing SPACECRAFT STRUCTURES in flight control systems Development of fire-resistant, low smoke A79-47971 generating, thermally stable end items for Microcomputer applications in strapdown beading commercial aircraft and spacecraft using a basic and attitude reference system polyimide resin A79-48606 N79-31171

1-46

SUBJECT INDEX STRUCTURAL DESIGN

SPACELAB PAYLOADS STATIC TESTS Transatlantic flights of stratospheric balloons Operation and test of composite horizontal N79-31687 stabilizer for the Sikorsky Spirit helicopter SPAIN CARS 79-45] A79-49097 Special investigation report: Wing failure of STATISTICAL ANALYSIS Boeing 747-131 near Madrid, Spain, 9 May 1976 Statistical diagnostics of aircraft engines [NTSB-AAR-78-12] 879-30167 A79-46996 SPECTRAL SIGNATURES STATORS Effect of transport/bomber loads spectrum on crack Digital simulation of a three-phase generator growth A79-48618 [AD-A069287] 879-31197 STEADY PLOW A users manual for a computer program to generate Harmonic oscillations of annular wing in steady fatigue spectrum loading sequences ideal fluid flow [AD-A069288] 879-31198 A79-47009 SPHERICAL ANTENNAS STEERABLE ANTENNAS A report on the Sperry Done Radar Small lightweight electronically steerable A79-49567 cylindrical antenna successfully utilized in an SPIN air traffic management system Exploratory study of the influence of wing A79-48597 leading-edge modifications on the spin STORAGE STABILITY - characteristics of a low-wing single-engine Changes in the quality of T-6 fuel upon prolonged general aviation airplane storage [AIAA PAPER 79-1837] A79-47908 A79-48858 SPIN DYNAMICS STRAIN ENERGY METHODS Some results from the use of a control Evaluation of the practical aspects of vibration augmentation system to study the developed spin reduction using structural optimization techniques of a light plane [ABS 79-21] A79-49074 [AIAA PAPER 79-1790] A79-47879 STRAKES SPIN TESTS Flow patterns and aerodynamic characteristics of The effects of configuration changes on spin and wing with strake recovery characteristics of a low-wing general [AIAA PAPER 79-1877] A79-47928 aviation research airplane STRAPDOWN INERTIAL GUIDANCE [AIAA PAPER 79-1786] - A79-47876 Microcomputer applications in strapdown heading Some results from the use of a control and attitude reference system augmentation system to study the developed spin A79-48606 of a light plane Transfer alignment for precision pointing [AIAA PAPER 79-1790] A79-117879 applications --- in inertial navigation systems Some flight data extraction techniques used on a A79-48679 general aviation spin research aircraft Automatic test software for calibrating strapdovn [AIAA PAPER 79-1802] A79-47887 systems The Beech Model 77 Skipper spin program A79-48689 [AIAA PAPER 79-1835] A79-47907 A deterministic investigation of strapped down The evolution of the high-angle-of-attack features navigation system accuracy of the F-16 flight control system A79-48695 A79-50438 Application of instrument rotation in the 873 Radio-controlled model design and testing standard inertial navigation system techniques for stall/spin evaluation of A79-48696 general-aviation aircraft Rapid reaction time techniques for a strapdown [NASA-TM-80510] 879-30173 navigator employing electrostatic gyro technology Rotary balance data for a typical single-engine A79-48697 general aviation design for an angle-of-attack Design and testing of a redundant skewed inertial range of 8 deg to 90 deg. 2: High-wing model A sensor complex for integrated navigation and [NASA-CR-3101) 879-31149 flight control Rotary balance data for a single-engine trainer N79-30202 design for an angle-of-attack range of 8 deg to STRESS ANALYSIS 90 deg --- conducted in langely spin tunnel Developments in gear analysis and test techniques [NASA-CR-3099) 879-31152 for helicopter drive systems SPOILERS [ASME PAPER 79-DR-15] A79-47654 Aerodynamics of spoiler control devices Simplified analysis spectrum for joints exposed to [AIAA PAPER 79-1873] A79-147925 complex continuously varying stresses STABILITY DERIVATIVES aerospace structures An investigation of the rolling stability [AIAA PAPER 79-1808] A79-47892 derivatives of a T-tail fighter configuration at Designing with experimental mechanics high angles-of-attack three-dimensional photoelastic analysis of A79-50165 helicopter components A computer program for aircraft identification and [ABS 79-11] A79-49063 derivative extraction ATLAS, an integrated structural analysis and A79-50306 design system. Volume 5: System demonstration Considerations in the analysis of flight test problems maneuvers [NASA-CR-159045] 879-31624 A79-50433 STRUCTURAL ANALYSIS AFFTC parameter identification experience --- Air Some observations on four current subjects related Force Flight Test Center aircraft flight testing to aeroelastic stability A79-50434 A79-47093 A force and moment test of a 1/24-scale F-ill Evaluation of finite element formulations for model at Mach numbers from 0.7 to 1.3 transient conduction forced-convection analysis [AD-A070192] 879-31156 A79-49343 STABILITY TESTS Tapered roller bearing development for aircraft Design, analysis, and testing of a new generation turbine engines tail rotor [AD-A0691140] 879-30555 [ABS 79-57] A79-49107 STRUCTURAL DESIGN STABILIZATION Design of advanced titanium structures --- for Stabilizing electro-optical systems on helicopters Advanced Tactical Systems aircraft fuselage 879-30216 [AIAA PAPER 79-1805] A79-47890 STALLING Composite helicopter tail booms .J85-CAN-15 compressor stall and flameout [ABS 79-91 A79-49061 investigation Design and development of a hybrid composite rotor A79-50441 blade for the circulation control rotor system [AilS 79-46] A79-49098

A-47

STRUCTURAL DESIGN CRITERIA SUBJECT INDEX

Design and development of the Agusta A 109 A low-velocity airflow calibration and research helicopter facility A79-49815 [Pn-294501/2] N79-31237 STRUCTURAL DESIGN CRITERIA SUPERCBITICAL WINGS Dynamics requirements for an Advanced Scout Experimental measurements of shock/boundary-layer Helicopter /ASH/ interaction of a supercritical airfoil [ABS 79-19] A79-149072 [AIAA PAPER 79-1499) A79-47345 Certification of composites in civil aircraft SUPERHICH FREQUENCIES [ABS 79_113] A79-49095 Combined X/Ka-band tracking radar Design criteria for airline operation A79-49565 [AIAA PAPER 79-1849] A79-49337 SUPERPLASTICITY The feasibility of modern dirigibles Superplastic forming diffusion bonding of titanium [ONERA, TP NO. 1979-93] A79-49541 helicopter airframe components Hovercraft skirt design requirements [ABS 79-33] A79-49085 A79-49907 SUPERSONIC AIRCRAFT Characteristics of an Air Cushion Landing System Historical development of worldwide supersonic incorporating an inelastic trunk aircraft A79-49909 [AIRA PAPER 79-1815] A79-47895 Design considerations for reliable FBW flight Application of singular perturbation techniques control /SPT/ and continuation methods for on-line 879-30231 aircraft trajectory optimization Windshield technology demonstrator program-canopy A79-47991 detail design options study SUPERSONIC COMBUSTION RAMJET ENGINES [AD-A070376] 879-31201 Characterization of a swept-strut hydrogen STRUCTURAL ENGINEERING fuel-injector for scramjet applications Wind tunnels with adapted walls for reducing wall A79-49345 interference SUPERSONIC DRAG [NASA-TH-75501] 879-31230 Wing geometry effects on leading-edge vortices STRUCTURAL STABILITY [AIAA PAPER 79-1872] A79-49341 Some observations on four current subjects related SUPERSONIC PLIGHT to aeroelastic stability Overall aerodynamic characteristics of caret and A79-47093 delta wings at supersonic speeds Developments in gear analysis and test techniques A79-47012 for helicopter drive systems SUPERSONIC PLOW [ASNE PAPER 79-DE-15] A79-47654 Numerical solution of the problem of unsteady Dynamics requirements for an Advanced Scout supersonic flow around the front part of the Helicopter /ASH/ wings with a detached shock wave [ABS 79-19] A79-49072 A79-49456 STRUCTURAL VIBRATION Comment on 'active flutter control using Experimental measurements of the rotating generalized unsteady aerodynamic theory' frequencies and mode shapes of a full scale A79-49873 helicopter rotor in a vacuum and correlations SUPERSONIC NOZZLES with calculated results Experiments of shock associated noise of [AHS 79-18] A79-49071 supersonic jets Evaluation of the practical aspects of vibration [AIAA PAPER 79-1526] A79-47341 reduction using structural optimization techniques SUPERSONIC SPEEDS [AHS 79-21] A79-49074 High-performance wings with significant An approach for estimating vibration leading-edge thrust at supersonic speeds characteristics of nonuniform rotor blades [AIAA PAPER 79-1871] 119-47924 A79-49718 SUPERSONIC TRANSPORTS INACT - Interactive test data analysis --- with Supersonic transport aircraft noise, problems of minicomputers noise reduction and establishment of standards A79-50430 A79-50237 ATLAS, an integrated structural analysis and SUPERSONICS design system. Volume 5: System demonstration Supersonic transport vis-a-vis energy savings problems [NASA-TN-75464] 879-31163 (NASA-CE-159045] 879-31624 SURFACE COOLING SUBSONIC FLOW Laminar flow stabilization by surface cooling on The calculation of non-linear aerodynamic hydrogen fueled aircraft characteristics of wings and their wakes in [AIAA PAPER 79-1863] 179-47920 subsonic flow SURFACE EFFECT SHIPS A79-47099 Performance predictions for open ocean air cushion On the influence of relative pitch in the subsonic vehicles and surface effect ships turbine cascade A79-49905 A79-48503 SURFACE NAVIGATION Subsonic and transonic flows on a variable sweep JTIDS relative navigation - Architecture, error wing characteristics and operational benefits [ONERA, TP NO. 1979-102] A79-48849 Joint Tactical Information Distribution System SUBSONIC SPEED A79-48715 Flow visualization studies of a general research SURFACE PROPERTIES fighter model employing a strake-wing concept at Nodal interpolation program, L215(INTERP). Volume subsonic speeds --- in the Langley high speed 7- 2: Supplemental system design and maintenance by 10-ft wind tunnel document --- to calculate displacements at [14ASA-TN-80057] 879-30147 several points on an aerodynamic surface A program to compute three-dimensional subsonic [NASA-CR-2848] 879-31147 unsteady aerodynamic characteristics using the SURVEILLANCE doublet lattice method, L216 (DUBFLEX) . Volume I4ultisensor integration for defensive fire control 2: Supplemental system design and maintenance surveillance document A79-48610 (NASA-cR-2850] N79-31148 SURVEILLANCE RADAR SUBSONIC WIND TUNNELS An analysis of SAPPHIRE image parameters as a Dynamic windtunnel simulation of active control function of processing parameters --- for systems synthetic aperture radar data processing N79-30233 119-48666 Subsonic wind-tunnel investigation of leading-edge SURVEYS devices on delta wings (data report) Surveys of grooves in 19 bituminous runways conducted in Langley 7- by 10-foot subsonic wind [AD-A069889] 879-31233 tunnel [NASA-CF-159120] 879-31143

A-48

SUBJECT INDEX TECHNOLOGY ASSESSMENT

SURVIVAL A design perspective on new technologies for Fuel tank survivability for hydrodynamic ran general aviation induced by high velocity fragments. Part 1: 879-49486 Experimental Results and Design summary Aeronautical information data subsystems /AIDS/ [AD-A070113] 879-31202 879-50920 SWEEP EFFECT Modern systems for air traffic control The influence of sweep on the aerodynamic loading 879-50921 of an oscillating 88CR 0012 airfoil Are today's specifications appropriate for [Ails 79-4] 879-49057 tomorrow's airplanes? SWEPT FORWARD WINGS 879-30239 Application of Lagrange Optimization to the drag polar utilizing experimental data [AIAA PAPER 79-1833] 879-49335 II SWEPT WINGS T TAIL SURFACES Selection of geometric parameters and location of An investigation of the rolling stability nose flap on swept wing root profile from tunnel derivatives of a T-tail fighter configuration at test data. I high angles-of-attack 879-46999 A79-50165 Lifting-line theory for a swept wing at transonic T-53 ENGINE - speeds Computer-assisted high-speed balancing of T53 and A79-47750 T55 power turbines Wing geometry effects on leading-edge vortices [AilS 79-36] 879-49088 [8188 PAPER 79-1872) 879-49341 T-55 ENGINE SWIRLING Computer-assisted high-speed balancing of T53 and The application of multiple swirl modules in the T55 power turbines design and development of gas turbine combustors [AilS 79-36] 879-49088 [8188 PAPER 79-1196] 879-47349 TACAN Factors controlling stability of swirling flames An asynchronous data transmission system with low at diffusers in gas turbines error probability for the SETAC landing aid 879-50209 879-31468 SYNCHRONOUS MOTORS TAIL ASSEMBLIES Digital simulation of a three-phase generator Analytical and experimental investigation of A79-48618 V-type empennage contribution to directional SYNTHETIC APERTURE RADAR control in hover and forward flight Synthetic aperture radar map matching for navigation (ARS 79-56) 879-49106 A79-48603 TAIL ROTORS Quaternion matching in transfer alignment for OAR Ten years of Aerospatiale experience with the motion compensation fenestron and conventional tail rotor 879-48641 [AilS 79-58] 879-49108 An analysis of SAPPHIRE image parameters as a TAKEOFF RUNS function of processing parameters --- for ARIA takeoff performance flight test program synthetic aperture radar data processing Advanced Range Instrumented Aircraft A79-48666 A79-50437 SYNTHETIC FUELS Airworthiness and flight characteristics test, Utilization of alternative fuels for OV-1C takeoff performance transportation; Proceedings of the Symposium, [AD-A069827] 879-30178 University of Santa Clara, Santa Clara, Calif., TARGET RECOGNITION June 19-23, 1978 Estimation of aircraft target motion using pattern A79-49376 recognition orientation measurements SYSTEM EFFECTIVENESS A79-47987 Avionics design for testability - An aircraft Millimeter airborne radar target detection and contractor's viewpoint selection techniques A79-48888 A79-48665 A new U.U.T./test station interface Multiradar tracking system using radial velocity 879-48896 measurements Enhanced fighter mission effectiveness by use of A79-49608 integrated flight systems TASK COMPLEXITY B79-30223 The equipment-system interface in an antitank SYSTEMS ANALYSIS helicopter at night A system for interdisciplinary analysis - A key to 879-30211 improved rotorcraft design TAXIING [AilS 79-81 879-49060 Testing and analysis of dual-mode adaptive landing AFFTC parameter identification experience --- Air gear, taxi mode test system for YF-12A Force Flight Test center aircraft flight testing [NASA-cR-144884] 879-31192 A79-50434 TECHNOLOGICAL FORECASTING Dynamic loads analysis system (DYLOFLEX) summary. All electric subsystems for next generation Volume 1: Engineering formulation transport aircraft [NASA-CR-2846-1] 879-31144 (AIAA PAPER 79-1832] 879-47906 SYSTEMS ENGINEERING User requirements for future combat search and Identifying desirable design features for the c-xx rescue vehicles aircraft - A systems approach 879-48683 [AIAA PAPER 79-1796] 879-47883 TECHNOLOGY ASSESSMENT A multiple objective optimization approach to Recent V/STOL aircraft designs aircraft control systems design A79-47608 A79-47962 Manned strategic system concepts 1990-2000 Analysis design of complex systems. II --- for [AIAA PAPER 79-1793] 879-47882 simultaneous improvement of all basic prototype Historical development of worldwide supersonic flight vehicle performance characteristics aircraft A79-48505 [AIAA PAPER 79-1815] 879-47895 Electric power system control techniques From RIMAT to future fighters --- Highly 879-48614 Maneuverable Aircraft Technology assessment Electrical power system for new-technology [AIAA PAPER 79-1816] A79-47896 transport power-by-wire airplane A status report on the advanced FIREFLY assessment 879-48616 program Tactical electronic reconnaissance sensor A79-48609 radar emission detection Terrain-following radar - Key to low-altitude flight A79-46717 A79-48686 Multiplex technology applied to helicopters [AilS 79-14] 879-49067

8-149 TECHNOLOGY UTILIZATION SUBJECT INDEX

Agricultural helicopters --- test and simulation TERRAIN FOLLOWING AIRCRAFT results Terrain-following radar - Key to low-altitude flight [AMS 79-60) A79-49064 A79-48685 Superplastic -forming diffusion bonding of titanium Meeting the challenge of precise navigation during helicopter airframe components nap-of-the-earth flight EARS 79-33] A79-49085 (ABS 79-12) A79-49065 Lockheed urges hydrogen fuel Ride qualities criteria validation/pilot A79-49224 performance study: Flight test results A design perspective on new technologies for (NASA-CR-144885] 979-31193 general aviation TEST EQUIPMENT A79-49486 Characteristics of an Air Cushion Landing System The feasibility of modern dirigibles incorporating an inelastic trunk (ONERA, VP NO. 1979-93) A79-495141 879-49909 The application of pulsed 'G' band radio A simplified gross thrust computing technique for altimeters to modern military aircraft an afterburning turbofan engine A79-49590 A79-50440 Road fleet operation of air cushion assisted TEST FACILITIES vehicles - An evaluation of technical and Microcomputer control of a test facility --- for economic problems avionics A79-49910 A79-48672 An evaluation of sidestick force/deflection NASA/Princeton digital avionics flight test facility characteristics on aircraft handling qualities A79-49344 A79-50428 THEORETICAL PHYSICS Evaluation of the radar altimeter reference method Contributions to fluid mechanics for determining altitude system positioning errors N79-31524 A79-50436 THERMAL CONDUCTIVITY New devices for digital communications in avionics Most rational linearization of nonlinear unsteady 879-31481 heat conduction problems --- for flight vehicle State of the art in digital signal processing with parts and engines applications to multiple access systems 179-48501 N79-31487 THERMAL DECOMPOSITION TECHNOLOGY UTILIZATION Evaluation of the temperature of the initiation of Advanced BPV electrical systems jet fuel decomposition by means of the 'hardness 879-48615 factor' Radar signal processing development for A79-48857 application of VHSI THERMAL DEGRADATION A79-48664 Electrical insulation fire characteristics. Road fleet operation of air cushion assisted Volume 2: Toxicity vehicles - An evaluation of technical and (P8-294841/2) 879-30490 economic problems THERMAL STABILITY A79-49910 The tendency of jet fuels to form deposits on a TELECOMMUNICATION heated surface State of the art in digital signal processing with A79-48856 applications to multiple access systems THERMAL STRESSES N79-31487 Evaluation of finite element formulations for TELEVISION SYSTEMS transient conduction forced-convection analysis Laboratory development of computer generated image A79-49343 displays for evaluation in terrain flight training THERMODYNAMIC PROPERTIES (AD-A070065) 879-31236 Thermal characteristics of 3501-6/AS and 5208/T300 TEMPERATURE DISTRIBUTION graphite epoxy composites Use of the method of variable directions for [AD-8071067] N79-31357 numerical study of the temperature states of a THERNOPHYSICAL PROPERTIES turbine disk with blades Mechanical and thermophysjcal properties of A79-48518 graphite/polyimide composite materials TEMPERATURE INVERSIONS N79-30317 Effect of steady-state temperature distortion and THIN WINGS combined distortion on inlet flow to a turbofan Solution of a mixed boundary value problem for engine flow past a thin delta wing [NASA-T8-79237] 879-30187 A79-49882 TEMPERATURE MEASUREMENT THRUST Evaluation of the temperature of the initiation of Dynamic test techniques - Concepts and practices jet fuel decomposition by means of the 'hardness aircraft performance prediction from factor' thrust/lift/drag model A79-48857 A79-50164 TERMINAL BALLISTICS THRUST AUGMENTATION Fuel tank survivability for hydrodynamic ran High-performance wings with significant induced by high velocity fragments. Part 1: leading-edge thrust at supersonic speeds Experimental Results and Design summary (AIAA PAPER 79-1871) 179-47924 [AD-A070113] 879-31202 Characteristics of afterburning bypass turbojet TERMINAL CONFIGURED VEHICLE PROGRAM engine with oxygen injection into the Flight performance of the TCV 8-737 airplane at afterburner chamber Kennedy Airport using TRSB/NLS guidance 879-48519 [NASA-TN-80148] 879-31186 A simplified gross thrust computing technique for TERMINAL FACILITIES an afterburning turbofan engine Current status of airport terminal complex A79-50440 development abroad THRUST CONTROL A79-50240 Some results from the use of a control Airport power supply --- Russian book augmentation system to study the developed spin 879-50499 of a light plane TERRAIN ANALYSIS [AIAA PAPER 79-1790) A79-47879 Expanding the region of convergence for SITAR THRUST MEASUREMENT through improved modelling of terrain Performance modelling methods --- in flight test nonlinearities --- Sandia Inertial Terrain Aided programs Navigation A79-50167 879-48678 THRUST REVERSAL Meeting the challenge of precise navigation during Determination of turning angle of a jet impinging nap-of-the-earth flight on a bucket with visor --- for thrust reversers (ABS 79-12] A79-49065 A79-48500

A-50

SUBJECT INDEX TRANSPORT AIRCRAFT

THRUST VECTOR CONTROL TRAJECTORY MEASUREMENT - Nozzles for vectored thrust jet engines A novel technique for obtaining aerodynamic data Russian book using simple, free flight trajectory measurements A79-47428 A79-48051 TILT ROTOR RESEARCH AIRCRAFT PROGRAM TRAJECTORY OPTIMIZATION xv-15 flight test results compared with design goals Application of singular perturbation techniques [8111 PAPER 79-1839] 879-49336 /SPT/ and continuation methods for on-line TIME DIVISION MULTIPLE ACCESS aircraft trajectory optimization Distributed TDNA - An approach to JTIDS phase II A79-47991 Time Division Multiple Access Joint Tactical A study of the application of singular Information Distribution System perturbation theory --- development of a real A79-4958L1 time algorithm for optimal three dimensional Implementing JTIDS in tactical aircraft aircraft maneuvers 879-31991 [NASA-CR-3167] 879-30194 TINE LAG TRANSFER FUNCTIONS Predictive guidance for interceptors with time Stabilizing electro-optical systems on helicopters delays 879-30216 A79-47939 TRANSIENT RESPONSE TIME OPTIMAL CONTROL Estimation for advanced technology engines Application of singular perturbation techniques A79-47957 /SPT/ and continuation methods for on-line TRANSNISSIONS (MACHINE ELEMENTS) aircraft trajectory optimization Helicopter drive system 8 and N design guide A79-47991 [AD-A069835] 879-30180 TINE RESPONSE Helicopter drive system B and N design guide Radar signal processing development for [80-8069691] 879-30181 application of VHSI Evaluation of pylon focusing for reduced A79-48664 helicopter vibration TITANIUM ALLOYS (80-8069712] 879-30196 Design of advanced titanium structures --- for TRANSONIC FLOW Advanced Tactical Systems aircraft fuselage Fully conservative numerical solutions for [AIAA PAPER 79-1805] 879-47890 unsteady irrotational transonic flow about Superplastic forming diffusion bonding of titanium airfoils helicopter airframe ccmponents [8181 PAPER 79-1555] A79-47342 [AIlS 79-33] 879-49085 Subsonic and transonic flows on a variable sweep TORQUE wing Load spectrum measuring equipment. Part 1: [ONERA, TP NO. 1979-102] 179-48849 Details of 8K 1 system presently used to acquire Flutter analysis of two-dimensional and data in Wessex 8K 31B helicopters two-degree-of-freedom airfoils in [ARL-MECH-ENG-NOTE-371] 879-31194 small-disturbance, unsteady transonic flow TO RQ U E METERS [AD-A069223] 879-31157 RotOrshaft torquemeter --- principles and Experimental data base for computer program applications assessment: Report of the Fluid Dynamics Panel [AIlS 79-38] 879-49090 Working Group 04 TOXIC HAZARDS [AGARD-AR-138] 879-31159 Electrical insulation fire characteristics. Introduction and overview of configurations Volume 2: Toxicity for transonic flows [P8-294841/2] 879-30490 N79-31160 TOXICITY Wind tunnels with adapted walls for reducing wall Electrical insulation fire characteristics. interference Volume 2: Toxicity [NASA-TM-75501) 879-31230 [P8-294841/2] 879-30490 TRANSONIC NOZZLES TOXICITY AND SAFETY HAZARD Contributions to experimental fluid mechanics Electrical insulation fire characteristics. development of aerodynamics test facilities in Volume 2: Toxicity Germany following World War 2 [PB-294841/2] 879-30490 N79-31229 TOXICOLOGY TRANSONIC SPEED Recent advances in materials toxicology Lifting-line theory for a swept wing at transonic N79-31169 speeds TRACKING (POSITION) A79-47750 Synthesis of digital flight control tracking Correlation of data related to shock-induced systems by the method of entire eigenstructure trailing-edge separation and extrapolation to assignment flight Reynolds number 179-48625. [NASA-CR-3178] 879-31195 TRACKING FILTERS TRANSONIC WIND TUNNELS The alpha-beta-gamma tracking filter in the S-domain Wall corrections in transonic wind tunnel: in aircraft tracking Equivalent porosity A79-48680 (BSA-TT-545] 879-30247 TRACKING RADAR TRANSPORT AIRCRAFT Combined X/Ka-band tracking radar All electric subsystems for next generation A79-49565 transport aircraft The A.I. tracking problem --- Airborne Interception [AIAA PAPER 79-1832] 879-47906 179-49566 The aerial relay system - An energy-efficient TRAILING EDGES solution to the airport congestion problem Flight testing the circulation control wing using cruise liner aircraft for in-air passenger [AIAA PAPER 79-1791] 179-47880 transfer On single-degree-of-freedom flutter induced by [8181 PAPER 79-1865] 179-47921 activated controls Electrical power system for new-technology A79-49867 transport power-by-wire airplane Correlation of data related to shock-induced A79-48616 trailing-edge separation and extrapolation to What the FAA would like in airworthiness standards flight Reynolds number [AIAA PAPER 79-1851] 179-49338 (NASA-CE-3178] 879-31195 A simulator investigation of handling quality TRAINING AIRCRAFT criteria for CCV transport aircraft The Beech Model 77 'Skipper' spin program N79-30240 [AIAA PAPER 79-18351 A79-47907 Effect of transport/bomber loads spectrum on crack Rotary balance data for a single-engine trainer growth design for an angle-of-attack range of 8 deg to [AD-A069287] 879-31197 90 deg --- conducted in langely spin tunnel [NASA-CR-3099] 879-31152

1-51

TRANSPORTATION ENERGY SUBJECT INDEX

TRANSPORTATION ENERGY Exhaust emission traverse investigation of a Utilization of alternative fuels for JT3D-1 turbofan engine --- to acquire exhaust transportation; Proceedings of the Symposium, nozzle emission sample University of Santa Clara, Santa Clara, Calif., [AD-A072019] 879-31209 June 19-23, 1978 TURBOJET ENGINE CONTROL A79-49376 A summary of NASA/Air Force full scale engine JT9D-70/59 improved high pressure turbine active research programs using the P100 engine clearance control system --- for specific fuel [NASA-TN-79267] 879-30188 consumption improvement TURBOJET ENGINES (NASA-CR-159661] 879-31208 Characteristics of afterburning bypass turbojet TURBINE BLADES engine with oxygen injection into the On the influence of relative pitch in the subsonic afterburner chamber turbine cascade 479-48519 A79-48503 Conceptual study of a turbojet/ramjet inlet Long-life GTE operation based on technical condition [8454-111-80141] 819-31215 Gas Turbine Engine TURBONACRINE BLADES A79-48517 Aerodynamic excitation forces of blade vibrations Use of the method of variable directions for in axial turbomachinery as a result of numerical study of the temperature states of a interference from nearby cascades turbine disk with blades A79-48572 479-48518 TURBONACHINENY TURBINE ENGINES Computer-assisted high-speed balancing of T53 and Energy efficient engine flight propulsion system T55 power turbines preliminary analysis and design report [ABS 79-36] 479-49088 [NASA-CR-159487] 879-30189 TURBOPROP AIRCRAFT Tapered roller bearing development for aircraft The aeroacoustjcs of advanced turbopropellers turbine engines 479-50236 [40-4069440] 879-30555 Driftdown calculations for the FH/227D aircraft Aircraft turbine engine monitoring experience: [SAND-78-1807] 879-30182 Implications for the P100 engine diagnostic TURBOPROP ENGINES system program Energy efficient aircraft engines [40-4069282] 879-31217 [AIAA PAPER 79-1861] 479-47918 TURBINE EXHAUST NOZZLES TURBO S HAP TS Exhaust emission traverse investigation of a Rotorshaft torquemeter --- principles and JT3D-1 turbofan engine --- to acquire exhaust applications nozzle emission sample CARS 79-38) 479-49090 [AD-A072019) 879-31209 Application of finite-element and holographic TURBINE WHEELS techniques in the design of turboshaft engine Use of the method of variable directions for components numerical study of the temperature States of a [ABS 79-411 A19-49093 turbine disk with blades Development of a 'no adjustment' turboshaft engine A79-48518 control system T UN B OCON PNES SONS [ABS 79-42] 479-49094 Laser velocimeter applied to the study of circular TURBULENT BOUNDARY LAYER distorsion effects in a low speed compressor Mechanics of boundary layer transition, part 2: [ONERA, TP NO. 1979-30] 479-50925 Instability and transition to turbulence Aerodynamic performance of 1.38-pressure-ratio, [VKI-LFCTtJRE-SERIES-3-PT-2] 879-31530 variable-pitch fan stage TURBULENT FLOW [NASA-TP-1502] 879-31213 Effect of nozzle spacing on ground interference An actuator disk analysis of an isolated rotor forces for a two jet V/STOL aircraft with distorted inflow [AIAA PAPER 79-1856] 479-49339 AD-A069884] 879-31216 Gust alleviator feasibility study for G91Y TURBOFAN ENGINES E79-30230 Energy efficient aircraft engines Evaluation of F-ill weapon bay aero-acoustic and [4144 PAPER 79-1861] 479-47918 weapon separation improvement techniques The DC-9 Super 80 - Much more than a simple stretch [AD-4070253] 879-31203 479-49223 TURBULENT WAKES Blown wings from Kiev --- short takeoff and Harmonic oscillations of annular wing in steady landing through wing-overblowing ideal fluid flow 479-49232 A79-47009 Derivative engines for the 1980s will help limit Experimental study of the turbulent wake acquisition and maintenance Costs downstream of a fan jet 479-50206 479-48507 Aircraft engine developments centre on improved TURNING FLIGHT performance, higher efficiency A study of the application of singular 479-50207 perturbation theory --- development of a real QCSEE - The key to future short-haul air transport time algorithm for optimal three dimensional Quiet, Clean, Short-Haul Experimental Engine aircraft maneuvers program [NASA-CR-3167] 879-30194 A79-50208 TWO DIMENSIONAL FLOW A simplified gross thrust computing technique for A new approach to the solution of large, full an afterburning turbofan engine matrix equations: A two-dimensional potential 479-50440 flow feasibility study Effect of steady-state temperature distortion and [NASA-CR-3173] 879-31533 combined distortion on inlet flow to a turbofan engine [NASA-TM-79237] 879-30187 U A summary of NASA/Air Force full scale engine UH-60A HELICOPTER research programs using the P100 engine Crashworthy armored crewseat for the 08-604 Black [NASA-T8-79267] 879-30188 Hawk Experimental Clean Combustor Program (ECCP) , phase 3 [ABS 79-10] 479-49062 commercial aircraft turbofan engine tests Antennas for the Black Hawk helicopter with double annular combustor [ABS 79-15] 479-49068 [NASA-CR-135384] 879-31207 ULTRAHIGH FREQUENCIES JT9D-70/59 improved high pressure turbine active Adaptive array tradeoffs for existing airborne UHF clearance control system --- for specific fuel radios consumption improvement A79-48598 [NASA-CN-159661 ] 879-31208

4-52

SUBJECT INDEX VIBRATION ISOLATORS

UHF coplanar-slot antenna for VARIABLE SWEEP WINGS aircraft-to-satellite data communications High-performance wings with significant [NASA-TN-79239] 879-31185 leading-edge thrust at supersonic speeds 179-47924 ULTRASONIC TESTS [AIAA PAPER 79-1871] Ultrasonic method of gun gas detection --- for Subsonic and transonic flows on a variable sweep engine ingestion prevention in F-15 wing A79-50166 [ONERA, TP NO. 1979-102] 679-48849 UNSTEADY FLOW VECTOR ANALYSIS Fully conservative numerical solutions for Complex quaternion notation in coordinate unsteady irrotational transonic flow about transformations --- missile launching aircraft-inertial space transformations airfoils A79-48661 [AIAA PAPER 79-1555] 679-47342 Theoretical flap-lag damping with various dynamic VELOCITY DISTRIBUTION inflow models Aerodynamic and acoustic investigation of inverted (AHS 79-20] A79-49073 velocity profile coannular exhaust nozzle models Numerical solution of the problem of unsteady and development of aerodynamic and acoustic supersonic flow around the front part of the prediction procedures, comprehensive data wings with a detached shock wave report, volume 1 679-49456 [NASA-CR-159515] 879-30185 Aerodynamic and acoustic investigation of inverted UP WA SB Effect of nozzle spacing on ground interference velocity profile coannular exhaust nozzle models forces for a two jet V/STOL aircraft and development of aerodynamic and acoustic [AXAB PAPER 79-1856] 679-49339 prediction procedures, comprehensive data URBAN RESEARCH report, volume 2 Experimental investigation of helicopter flight [NASA-CR-159516] 879-30186 modes on helicopter-generated noise Aerodynamic and acoustic investigation of inverted A79-47873 velocity profile coannular exhaust nozzle models USER MANUALS (COMPUTER PROGRAMS) and development of aerodynamic and acoustic A user's manual for a computer program to generate predicticn procedures fatigue spectrum loading sequences [NASA-CR-3168) 879-31212 [AD-A069288] 879-31198 VELOCITY MEASUREMENT USER REQUIREMENTS Multiradar tracking system using radial velocity User requirements for future combat search and measurements rescue vehicles A79-49608 A79-48683 VENTILATION Can avionic testability requirements be enforced Fuselage ventilation under wind conditions .A79-48887 879-31175 Advanced Scout Helicopter flying qualities VERTICAL FLIGHT requirements - How realistic are they Analysis of optimal loop and split-S by energy A79-49080 state modeling [AHS 79-28] A79-47098 VERTICALLANDING V VTOL controls for shipboard landing 879-30193 V/STOL AIRCRAFT [NASA-CR-162140] Performance of a V/STOL tilt nacelle inlet with VERTICAL TAKEOFF AIRCRAFT blowing boundary layer control Nozzles for vectored thrust jet engines [6116 PAPER 79-1163] 179-47347 Russian book Recent V/STOL aircraft designs A79-47428 A79-47608 Digital adaptive control laws for VTOL aircraft The characteristics of a lift cruise fan V/STOL A79-48000 configuration in near proximity to a small deck Maintenance cost study of rotary wing aircraft, with finite edge positions phase 2 879-30138 (AIAA PAPER 79-1854) 679-47913 [NASA-CR-152291] Aerodynamic effects of an attitude control vane on VTOL controls for shipboard landing a tilt-nacelle V/STOL propulsion system [NASA-CR-162140] 879-30193 [AIAA PAPER 79-1855] A79-47914 Maritime patrol airship concept study Blown wings from Kiev --- short takeoff and [AD-A070131] N79-31138 landing through wing-overblowing Aerodynamic performance of axial-flow fan stage A79-49232 operated at nine inlet guide vane angles --- to Effect of nozzle spacing on ground interference be used on vertical lift aircraft forces for a two jet V/STOL aircraft [NASA-TP-1510] N79-31214 [6116 PAPER 79-18563 A79-49339 VIBRATION Recent applications of theoretical analysis to The promise of multicyclic control --- to control V/STOL inlet design fatiguing blade loads and rotor vibration A79-49530 [NASA-TN-78621] 879-31137 The Guidance and control of Helicopters and V/STOL VIBRATION DAMPING aircraft at night and in poor visibility Dynamics requirements for an Advanced Scout [AGARD-CP-258] 879-30198 Helicopter /ASH/ High performance composites and adhesives for CARS 79-19) A79-49072 V/STOL aircraft Evaluation of the practical aspects of vibration reduction using structural optimization techniques [AD-A069611] 879-30332 Theoretical and experimental investigation of [AHS 79-21) A79-49074 ground-induced effects for a low-aspect-ratio Active external store flutter suppression in the highly swept arrow-wing configuration 12-17 flutter model A79-49866 [NASA-TP-1508] 879-31223 VACUUM TESTS On single-degree-of-freedom flutter induced by Experimental measurements of the rotating activated controls frequencies and mode shapes of a full scale A79-49867 helicopter rotor in a vacuum and correlations Comment on 'active flutter control using generalized unsteady aerodynamic theory' with calculated results A79-49873 [ABS 79-181 179-49071 The promise of multicyclic control --- to control VALVES Program for the critical components of a fatiguing blade loads and rotor vibration fly-by-tube backup flight control system, part 1 [NASA-TN-78621) N79-31137 [60-6070387] 879-31226 VIBRATION ISOLATORS VARIABLE PITCH PROPELLERS Investigations on the design of active vibration Aerodynamic performance of 1.38-pressure-ratio, isolation systems for helicopters with rigid and elastic modeling of the fuselage variable-pitch fan stage N79-30183 [NASA-TP-1502] 879-31213 [DLR-FB-78-04]

A-53 VIBRATION MEASUREMENT SUBJECT INDEX

Performance of two-stage fan with a first-stage WEATHER rotor redesigned to account for the presence of An advanced guidance and control system for rescue a part-span damper helicopters [NASA-TP-1483] 1179-30191 1179-30217 Evaluation of pylon focusing for reduced WEIGHT REDUCTION helicopter vibration Power hybridization - Key to reducing avionics [AD-A069712] N79-30196 power supply weight and volume VIBRATION MEASUREMENT A79-48652 An approach for estimating vibration Antennas for the Black Hawk helicopter characteristics of nonuniform rotor blades [ABS 79-15] A79-49068 A79-49718 Ten years of Aerospatiale experience with the VIBRATION TESTS fenestron and conventional tail rotor Computer-assisted high-speed balancing of T53 and [ABS 79-58] A79-49108 T55 power turbines WIND EFFECTS [ABS 79-36] A79-49088 Interactional aerodynamics - A new challenge to Helicopter component environmental vibration helicopter technology testing - The poor mans fatigue test [ABS 79-59] A19-49109 [ABS 79-49] A79-119101 Variables characterizing the wind effects on an VORTEX GENERATORS aircraft Benefits of aerodynamic interaction to the three A79-149807 surface configuration Fuselage ventilation under wind conditions [AIAA PAPER 79-1830]- A79-47904 M79-31175 Subsonic and transcnic flows on a variable sweep WIND SHEAR wing Aircraft response to windshears and downdraughts [ONERA, TP NO. 1979-102] A79-48849 N79-30229 VORTEX SHEETS WIND TUNNEL APPARATUS The calculation of non-linear aerodynamic Contributions to experimental fluid mechanics characteristics of wings and their wakes in development of aerodynamics test facilities in- subsonic flow Germany following World War 2 A79-47099 N79-31229 Theoretical estimation of nonlinear longitudinal WIND TUNNEL MODELS characteristics of wings with small and moderate Flight experiments to evaluate the effect of aspect ratio by the vortex-lattice method in wing-tip sails on fuel consumption and handling incompressible flow characteristics [DLR-FB-78-26] 1179-30161 A79-49818 VORTICES Flow visualization studies of a general research The inner regions of annular jets fighter model employing a strake-wing concept at A79-47520 subsonic speeds --- in the Langley high speed 7- Rotary balance data for a typical single-engine by 10-ft wind tunnel general aviation design for an angle-of-attack [NASA-TN-80057] 1179-30147 range of 8 deg to 90 deg. 1: Nigh-wing model B Similitude requirements and scaling relationships (NASA-CF-3097] N79-30145 as applied to model testing Rotary balance data for a single-engine trainer [NASA-TP-1435] 1179-30176 design for an angle-of-attack range of 8 deg to WIND TUNNEL TESTS 90 deg --- conducted in langely spin tunnel Selection of geometric parameters and location of [NASA-CR-3099] 1179-31152 nose flap on swept wing root profile from tunnel test data. I A79-46999 W Experimental measurements of shock/boundary-layer WAKES interaction of a supercritical airfoil The inner regions of annular jets [AIAA PAPER 79-1499] A79-47345 A79-47520 Full-scale wind tunnel study of nacelle shape on WALLS cooling drag Wind tunnels with adapted walls for reducing wall [AIAA PAPER 79-1820] A79-47900 interference A cheap, effective icing detector for general (NASA-TM-75501) N79-31230 aviation aircraft WANKEL ENGINES [AIAR PAPER 79-1823) A79-47902 An overview of NASA research on positive Engine-aircraft afterbody interactions - displacement type general aviation engines Recommended testing techniques based on YF-17 [NASA-TN-79254] 1179-31210 experience WARFARE [AIAA PAPER 79-1829] A79-47903 Performance of current radar systems in an EN Winglet toe out angle optimization for the Gates environment --- Electronic Warfare Learjet Longhorn Wing - A79-49555 [AIAA PAPER 79-18311 A79-47905 Tactical performance characterization basic Aerodynamic effects of an attitude control vane on methodology a tilt-nacelle V/STOL propulsion system [AD-A069297] 1179-31235 [AIAA PAPER 79-1855) A79-47914 WARNING SYSTEMS Boundary layer control on wings using sound and A self contained collision avoidance system for leading edge serrations helicopters [AIAA PAPER 79-1875] A79-47926 N79-30206 Experimental study of the turbulent wake WAVE PROPAGATION downstream of a fan jet Nultipath propagation measurement by Doppler A79-48507 technique Subsonic and transonic flows on a variable sweep N79-31478 wing WEAPON SYSTEMS [ONERA, TP NO. 1979-102] A79-148849 Avionics design for testability - An aircraft LDV measurements on propellers contractors viewpoint A79-119052 A79-48888 The influence of sweep on the aerodynamic loading Adding the challenge of nap-of-the-earth of an oscillating NACA 0012 airfoil N79-30199 [ABS 79-4] A79-49057 WEAPONS DELIVER! An integrated analytical and experimental Separation testing of large weapons from the B-i investigation of helicopter hub drag bomber CARS 79-5] A79-49058 A79-50429 The circulation control rotor flight demonstrator Evaluation of P-ui weapon bay aero-acoustic and test program weapon separation improvement techniques [ABS 79-51] A79-119103 [AD-A070253] 1179-31203

A-54

SUBJECT INDEX WINGS

Wind tunnel and flight test of the XV-15 Tilt WING LOADING Rotor Research Aircraft Wing aerodynamic loading caused by jet-induced [ABS 79-541 A79-49105 lift associated with STOL-OTW configurations XV-15 flight test results compared with design goals [AIAA PAPER 79-1664] A79-47346 [AIAA PAPER 79-1839] A79-49336 An investigation of the rolling stability Effect of nozzle spacing on ground interference derivatives of a I-tail fighter configuration at forces for a two jet V/STOL aircraft high angles-of-attack [AIAA PAPER 79-1856] A79-49339 A79-50165 Characterization of a swept-strut hydrogen WING NACELLE CONFIGURATIONS fuel-injector for scranjet applications Blown wings from Kiev --- short takeoff and A79-49345 landing through wing-overblowing Aerodynamic interaction on a close-coupled A79-49232 canard-wing configuration WING OSCILLATIONS [ONERA, TP 110. 1979-951 A79-49543 Harmonic oscillations of annular wing in steady An investigation of the rolling stability ideal fluid flow derivatives of a I-tail fighter configuration at A79-47009 high angles-of-attack Lateral stability at high angles of attack, A79-50165 particularly wing rock The aeroacoustics of advanced turbopropellers N79-30226 A79-50236 WING PLANFOENS The evolution of the high-angle-of-attack features Wing geometry effects on leading-edge vortices of the P-16 flight control system [AIAA PAPER 79-1872] A79-49341 A79-50438 Flow visualization studies of a general research Analysis of wind tunnel data pertaining to high fighter model employing a strake-wing concept at angle of attack aerodynamics. Volume 1: subsonic speeds --- in the Langley high speed 7- Technical discussion and analysis of results by 10-ft wind tunnel [AD-A069646] 1179-30148 [NASA-TM-80057] 1179-30147 Analysis of wind tunnel data pertaining to high WING PROFILES angle of attack aerodynamics. Volume 2: Data Analytic formulas for wing profile aerodynamic base characteristics in incompressible flow [AD-A069647] 1179-30149 A79-47000 Similitude requirements and scaling relationships Solution of the inverse aerodynamics problem by as applied to model testing the random search method [NASA-TP-1435] 1179-30176 A79-47002 Evaluation of pylon focusing for reduced Design of the circulation control wing STOL helicopter vibration demonstrator aircraft [AD-A069712] 1179-30196 [AIAA PAPER 79-1842] A79-47909 Wall corrections in transonic wind tunnel: Numerical solution of the problem of unsteady Equivalent porosity supersonic flow around the front part of the [ESA-TT-545] 1179-30247 wings with a detached shock wave A comparison of predictions obtained from wind A79-49456 tunnel tests and the results from cruising Subsonic wind-tunnel investigation of leading-edge flight: Airbus and Concorde --- conferences devices on delta wings (data report) [NASA-TM-75238] 1179-31136 conducted in Langley 7- by 10-foot subsonic wind Subsonic wind-tunnel investigation of leading-edge tunnel devices on delta wings (data report) [NASA-CR-159120] 1179-31143 conducted in Langley 7- by 10-foot subsonic wind WING SLOTS tunnel Flight testing the circulation control wing [NASA-CR-159120] 1179-31143 [AIAA PAPER 79-1791] A79-47880 Wind-tunnel investigation of an armed mini WING SPAN remotely piloted vehicle --- conducted in Performance evaluation method for dissimilar Langley V/STOL tunnel aircraft designs --- using the square of the [NASA-TM-801321 1179-31151 wing span for nondimensional comparisons of A force and moment test of a 1/24-scale F-ill aerodynamic characteristics model at Mach numbers from 0.7 to 1.3 [NASA-RP-1 042] 1179-30139 [AD-A070192] 1179-31156 WING TIPS Experimental data base for computer program Flight experiments to evaluate the effect of assessment: Report of the Fluid Dynamics Panel wing-tip sails on fuel consumption and handling Working Group 04 characteristics [AGARD-AR-138] N79-31159 A79-49818 WIND TUNNELS RINGLETS Contributions to experimental fluid mechanics Winglet toe out angle optimization for the Gates development of aerodynamics test facilities in Learjet Longhorn Wing Germany following World War 2 [AIAA PAPER 79-1831] A79-47905 1179-31229 WINGS Wind tunnels with adapted walls for reducing wall On a smooth approximation method and its interference application to mathematical description of wing [NASA-TN-75501] 1179-31230 aerodynamic characteristics WIND VELOCITY A79-47001 A low-velocity airflow calibration and research Exploratory study of the influence of wing facility leading-edge modifications on the spin [PB-294501/2] 1179-31237 characteristics of a low-wing single-engine WINDSHIELDS general aviation airplane Atmospheric Electricity Hazard (AEH) [AINA PAPER 79-1837] A79-47908 [AD-A069338] 1179-30169 Boundary layer control on wings using sound and Windshield technology demonstrator program-canopy leading edge serrations detail design options study [AIAA PAPER 79-1875] A79-47926 (AD-A070376] 1179-31201 Flow patterns and aerodynamic characteristics of WING FLAPS wing with strake Selection of geometric parameters and location of [AIAA PAPER 79-1877] A19-47928 nose flap on swept wing root profile from tunnel Special investigation report: Wing failure of test data. I Boeing 747-131 near Madrid, Spain, 9 May 1976 A79-46999 [NTSB-AAR-78-12] 1179-30167 A method of the theory of airfoil profiles with a Correlation of data related to shock-induced jet flap trailing-edge separation and extrapolation to A79-47119 flight Reynolds number [NASA-CR-3178] 1179-31195

A-55

WORKING FLUIDS SUBJECT INDEX

WORKING FLUIDS Fuels, lubricants and other fluids used in aviation Russian book A79-47433 X I RAY INSPECTION Automatic scanning inspection of composite helicopter structure using an advanced technology fluoroscopic system [AIlS 79-35] A79-49087 XV-15 AIRCRAFT Wind tunnel and flight test of the XV-15 Tilt Rotor Research Aircraft CARS 79-54] A79-49105 XV-15 flight test results compared with design goals [AIAA PAPER 79-1839] A79-49336 V YF-12 AIRCRAFT Testing and analysis of dual-mode adaptive landing gear, taxi node test system for YF-12A (NASA-CR-1448841 879-31192 YF-16 AIRCRAFT Analysis of a lateral pilot-induced oscillation experienced on the first flight of the YP-16 aircraft [NASA-T8-72867] 879-31220

A-56 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING 1A Continuing Bibliography (Suppl. 116) DECEMBER 1979

Typical Personal Author Index Listing

NALAUTHOR ACKER, I. W. 1— Aerodynamic and acoustic effects of eliminating ALEKSANDROY, V. G. I core swirl from a full scale 1.6 stage pressure Handbook on aircraft materials and their I ratio fan (QF-5A) application technology I [NASA-TM-78991] 1179-11001 A79-48311 ALKER, G. L. Test implementation through support software - A FIT translator L1PORT I NASA 579-48687 NUMBER ACCESSIONNUMBER ALLEN, B. Certification of composites in civil aircraft [AilS 79-43] 579-49095 ALLEN, S. G. Listings in this index are arranged alphabetically by personal author. The title Navstar user equipment for civil and military of the document provides the user with a brief description of the subject matter. applications The report number helps to indicate the type of document cited e.g.. NASA A79-49587 ALTHOP, N. report, translation. NASA contractor report) The accession number is located The influence of the environment on the beneath and tothe right of the title. e.g. N79-1 1001 Under any one author's elastoplastic properties of adhesives in metal name the accession numbers are arranged in sequence with the /AA accession bonded joints numbers appearing first [ESA-TT-521] 1179-30391 ANDERSON, G. Y. Characterization of a swept-strut hydrogen fuel-injector for scramjet applications A A79-893tt5 ABBOTT, J. K. ANDERSON, J. N. Electrical insulation fire characteristics. A real time video bandwidth reduction system based Volume 2: Toxicity on a CCD Hadamard transform device fPB-294841/2] N79-30490 A79-48702 ABELKIS, P. B. ANDERSON, L. N. Effect of transport/bomber loads spectrum on crack A program for calculating load coefficient growth matrices utilizing the force summation method, [AD-A069287] N79-31197 L218 (LOADS). Volume 2: Supplemental system A user's manual for a computer program to generate design and maintenance document fatigue spectrum loading sequences [NASA-CR-2854] N79-31155 [AD-A069288) 1179-31198 ANDERSON, N. A. ACORACI, J. A. FIREMEN program Small lightweight electronically steerable N79-31178 cylindrical antenna successfully utilized in an Development of aircraft lavatory compartments with air traffic management system improved fire resistance characteristics. Phase A79-48597 2: Sandwich panel resin system development ADSIT, N. N. (NASA-Cft-152120] 1179-31354 Ultra-high-modulus graphite-epoxy conical shell ANDREET, P. L. development, supplement Airport power supply [AD-A069795] 1179-30335 A79-50499 AGLIULLIN, I. N. ANDREWS, A. P. Optimal thermogasdynamic design of gas turbine Automatic test software for calibrating strapdown engines using element prototypes. I systems A79-46997 579-48689 AGNEW, J. N. ANTONOVA, A. N. Benefits of aerodynamic interaction to the three Solution of a mixed boundary value problem for surface configuration flow past a thin delta wing [AIAA PAPER 79-1830] A79-47904 A79-49882 ARARRAN, B. C. ANDREA, N. D. Are today's specifications appropriate for Linearization of the boundary-layer equations of, tomorrow's airplanes? the minimum time-to-climb problem 1179-30239 579-49869 AIBA, T. - ARNOLD, D. B. Investigation of air stream from combustor-liner Development of aircraft lavatory compartments with'. air entry holes, 3 improved fire resistance characteristics. Phase [NASA-TN-75430] N79-31206 2: Sandwich panel resin system development AKITA, B. [NASA-CR-152120] 1179-31354 Low cost inertial aiding for NAVSTAR/GPS receivers ARSENAULT, D. B. in naval ship navigation Transform domain processing for digital A79-48656 communication systems using surface acoustic ALBRECHT, C. wave devices Developments in gear analysis and test techniques 1179-31.482 for helicopter drive systems ASHKENAS, I. L. [ASNE PAPER 79-DE-15] 579-47654 Handling quality and display requirements for low ALDERETE, T. S. speed and hover in reduced flight visibility Piloted simulator investigation of helicopter [ABS 79-29] 579-49081 control systems effects on handling qualities ASHLEY, H. during instrument flight Some observations on four current subjects related [AilS 79-26] A79-49078 to aeroelastic stability A79-47093

B-i ASHWORTH, B. B. PERSONAL AUTHOR INDEX

ASHWORTH, B. B. BERTIN, J. J. Seat cushion to provide realistic acceleration Aerodynamics for engineers cues to aircraft simulator pilot A79-50375 (NASA-CASE-LAR-12149-2] 979-31228 BERTRAM, I. A. Driftdown calculations for the FH/227D aircraft (SAND-78-1807] 979-30182 B BETZINA, N. 0. BABISTEB, A. N. Aerodynamic effects of an attitude control vane on Aircraft longitudinal motion at high incidence a tilt-nacelle V/STOL propulsion system A79-48052 [AIAA PAPER 79-1855] A79-47914 BARR, D. V. BEUTUKIAN, C. S. Experimental Clean Combustor Program (ECCP) , phase 3 Actively cooled plate fin sandwich structural [NASA-CR-135384) 979-31207 panels for hypersonic aircraft BATh, G. L. [NASA-CR-3159] 979-31628 Radar signal processing development for BIAPORE, L. P. application of VHSI Fluidics: Feasibility study A79-48664 electro/hydraulic/fluidic direct drive servovalve BALLABD, J. D. [AD-A069798] 979-30195 Effect of tip shape on blade loading BICKEL, S. H. characteristics for a two-bladed rotor in hover Small signal compensation of magnetic fields [AHS 79-1] A79-49054 resulting from aircraft maneuvers BANGEN, H. J. A79-119605 Implementation of flight control in an integrated BIERBAUM, C. guidance and control system Evolving methods for reducing avionics data in an 979-30215 AISF environment BARk, N. A79-48671 A review of Boeing interior materials and fire BIHBLE, V., JR. test methods development programs Rotary balance data for a typical single-engine N79-31177 general aviation design for an angle-of-attack BARCHE, J. range of 8 deg to 90 deg. 1: High-wing model B Introduction and overview of configurations [NASA-CR-3097] 979-30145 N79-31160 BILL, F. A. BARNES, D. B. The circulation control rotor flight demonstrator The circulation control rotor flight demonstrator test program - test program [AHS 79-51] A79-49103 [AHS 79-51] A79-49103 BIRKLER, J. 1.. BAUM, M. Aircraft turbine engine monitoring experience: A digital communication system as gateway between Implications for the 8100 engine diagnostic adjacent computerized air traffic control centres system program W79-31463 [AD-A069282] 979-31217 BAZANOY, B. I. BLACKMAN, S. Handbook on aircraft materials and their Wind tunnel and flight test of the XY-15 Tilt application technology Rotor Research Aircraft A79-48311 [AilS 79-54] A79-49105 BECKER, N. N. BLAIR, P. K. Exhaust emissions characteristics for a general Navstar user equipment for civil and military aviation light aircraft Teledyne Continental applications Motors TSIO-360-C piston engine A79-49587 (AD-A070010) 979-31211 BLAKE, B. B. BECKMANN, N. C. Improved method of predicting helicopter control Expanding the region of convergence for SITAR response and gust sensitivity through improved modelling of terrain (ABS 79-251 A79-49077 nonlinearities BLAZOVSKI, V. S. A79-48678 Ambient correction factors for aircraft gas REM, H. turbine idle emissions Stability and control aspects of the CCV-F104C [AD-A069240] 979-31218 N79-30234 BLESS, S. J. BEIER, V. Fuel tank survivability for hydrodynamic ram An asynchronous data transmission system with low induced by high velocity fragments. Part 1: error probability for the SETAC landing aid Experimental Results and Design summary 979-31468 [AD-A070113] 979-31202 BELL, J. C. BLIAULT, A. Maritime patrol airship concept study Small hovercraft design - Evolution to simplicity [AD-A070131] 979-31138 - A79-49906 BELLAN, J. BLOCH, S. Enclosure fire dynamics model - A self contained collision avoidance system for 979-31173 helicopters BELOY, V. B. N79-30206 Fuels, lubricants and other fluids used in aviation BOBOLA, G. A. A79-47433 Effect of steady-state temperature distortion and BELROSE, T. C. combined distortion on inlet flow to a turbofan ATE and aircraft mechanical diagnostics engine A79-48883 [NASA-TN-79237] 979-30187 HENDON, G. A. BODE, V. E. Quaternion matching in transfer alignment for SAN Simulation and study of V/STOL landing aids for motion compensation 0 SMC AV-8 aircraft A79-48641 N79-30214 BENNETT, V. S. BOEHRET, H. Enhanced fighter mission effectiveness by use of Gcu, the Guidance and control Unit for all weather integrated flight systems approach N79-30223 979-30213 BERGEN, J. BOGHANI, A. B. A comparison of predictions obtained from wind Characteristics of an Air Cushion Landing System tunnel tests and the results from cruising incorporating an inelastic trunk flight: Airbus and Concorde A79-49909 (NASA-TM-75238] N79-31136 Heave-pitch-roll analysis and testing of air BERN!, J. R. cushion landing systems Preprocessing for advanced image matching techniques [NASA-cR-2917] N79-30175 A79-48602

B-2

PERSONAL AUTHOR INDEX CAPOWE. F. J.

B000NOLOY, A. I. BROWN, N. B. Analysis design of complex systems. II Compass Cope airframe design history A79-48505 [AIAA PAPER 79-1792] A79-47881 BONA, B. B. RRUNKEN, J. E. Rapid reaction time techniques for a strapdown Helicopter obstacle strike tolerance navigator employing electrostatic gyro technology (ABS 79-7] A79-49059 A79-48697 BRYANT, N. H. BORDER, J. G. NASA/Princeton digital avionics flight test facility Alternative fuels in aviation A79-49344 A79-49381 BUCKLEY, K. BOROTIK, V. 0. Navstar user equipment for civil and military Optimal thermogasdynamic design of gas turbine applications engines using element prototypes. I A79-49587 A79-46997 BUCKNER, J. K. BOSCBHA, J. H. The evolution of the high-angle-of-attack features Advances in decelerating steep approach and of the F-16 flight control system landing for helicopter instrument approaches A79-50438 [ABS 79-16] A79-49069 BUDDIN, A. L., III hazard BOSSLEE, B. B., JR. An evaluation of the bird aircraft strike at Bill AFB, Utah (AFLC) Rotorshaft torquemeter 1179-31184 [AIlS 79-38] A79-49090 (AD-A070459] BOTHA, D. G. BUILTA, K. E. Integrated CR1 avionics Development of a fly-by-wire elevator for the Bell A79-48711 Helicopter Textron 214ST BOTHE, H. [ABS 79-27] A79-49079 Multipath propagation measurement by Doppler BUKBARKIR, A. K. technique Evaluation of the temperature of the initiation of 879-311478 jet fuel decomposition by means of the 'hardness BOTROS, A. Z. factor' Radiation from quarter-wavelength monopoles on A79-48 857 finite cylindrical, conical, and rocket-shaped BULL, J. S. conducting bodies Flight investigation of helicopter IFR approaches A79-50606 to oil rigs using airborne weather and mapping BOULET, J. radar Aerospatiale AS.350 and AS.355 [ABS 79-52] A79-49104 A79-49814 BURCHFIELD, C. U. BOUTTES, J. A force and moment test of a 1/24-scale F-ill The feasibility of modern dirigibles model at Mach numbers from 0.7 to 1.3 [ONERA, TP NO. 1979-93] A79-49541 [AD-A070192] 879-31156 BOWNAN, C. L. RURDGES, K. P. Multisensor integration for defensive fire control Experimental measurements of shock/boundary-layer surveillance interaction of a supercritical airfoil A79-48610 (AIAA PAPER 79-1499] A79-47345 BEAUER, D. P. BURGIN, G. H. Evaluation of airfield pavement materials based on Tactical performance characterization basic synthetic polymers methodology A79-493448 [AD-A069297] 879-31235 BRENER, S. BURK, S. N., JR. Analysis of plume rise from jet aircraft Radio-controlled model design and testing [CONF-790142-1] 879-31204 techniques for stall/spin evaluation of BREUHAUS, W. 0. general-aviation aircraft Comment on Flight test of stick force stability (NASA-TM-80510] 879-30173 in attitude-stabilized aircraft' BURROUGHS, B. A. A79- 49 925 Superplastic forming diffusion bonding of titanium BREWER, G. D. helicopter airframe components Laminar flow stabilization by surface cooling on (AHS 79-33] P.79-49085 hydrogen fueled aircraft BURROWS, L. T. [AIAA PAPER 79-1863] P.79-47920 Helicopter obstacle strike tolerance BRICKER, N. N. [ABS 79-7] A79-49059 Airport flammability, full scale fire tests BUSH, H. J. N79-31167 New devices for digital communications in avionics Seat test program 879-311481 879-31168 BYERLY, D. C. BRIGHT, J. T. Avionics design for testability - A vendor's Aerodynamics of spoiler control devices viewpoint (AIAA PAPER 79-1873] A79-47925 A79-48889 BROCARD, Y. Aerodynamic interaction on a close-coupled canard-wing configuration [ONEBA, TP NO. 1979-95] P.79-49543 CAHILL, J. F. BROCCHI, B. Correlation of data related to shock-induced Can avionic testability requirements be enforced trailing-edge separation and extrapolation to A79-48887 flight Reynolds number BROCKHAUS, B. [NASA-CR-3178] 879-31195 Variables characterizing the wind effects on an CALAPODAS, N. J. aircraft Evaluation of the practical aspects of vibration A79-49807 reduction using structural optimization techniques BROKOF, U. [ABS 79-21] P.79-49074 A simple integrated navigation based on multiple DME CALDNELL, B. N. [OGLE PAPER 79-041] A79-48640 Identifying desirable design features for the C-TX BROWN, H. J. aircraft - A systems approach Composite helicopter tail booms [AIP.A PAPER 79-1796] A79-47883 [ABS 79-9] P.79-49061 CALNAN, J. BROWN. J. 5., JR. Analysis of plume rise from jet aircraft Similitude requirements and scaling relationships [CONF-790142-1] 879-31204 as applied to model testing CAPONE, F. J. [NASA-TP-1435] 879-30176 The nonaxisymmetric nozzle - It is for real [AIAP. PAPER 79-1810] P.79-47893

8-3 CAPTAIN, K. N. PERSONAL AUTHOR INDEX

CAPTAIN, K. N. CLARK, R. L. Characteristics of an Air Cushion Landing System Evaluation of F-ill weapon bay aero-acoustic and incorporating an inelastic trunk weapon separation improvement techniques 879-49909 [80-8070253] 1479-31203 Heave-pitch-roll analysis and testing of air CLARK, H. V. cushion landing systems A new approach to the solution of large, full [NASA-CR-2917] 1479-30175 matrix equations: A two-dimensional potential CARABELLI, H. flow feasibility study Gust alleviator feasibility study for G91Y [NASA-CR-3173] 1479-31533 1479-30230 CLARKE, G. B. CARLSON, H. V. Recent progress in aircraft sink rate measurement High-performance wings with significant [AIAA PAPER 79-1798] 879-47884 leading-edge thrust at supersonic speeds High sink-rate landing testing of Navy aircraft [8188 PAPER 79-1871] 879-47924 879-50163 CARRETTO, J. A.., JR. CLENMONS, H. E. Nicrocoinputer control of a test facility Dynamic loads analysis system (DYLOFLEX) summary. A79-48672 Volume 1: Engineering formulation CARROLL, J. V. [NASA-CR-2846-1] 1479-311114 Application of bifurcation analysis and Dynamic loads analysis system (DYLOFLEX) summary. catastrophe theory methodology /BACTM/ to Volume 2: Supplemental system design information aircraft stability problems at high [NASA-CR-28116-2] 1479-31145 angles-of-attack Equation modifying program, L219 (EQNOD) . Volume A79-47943 2: Supplemental system design and maintenance A study of the application of singular document perturbation theory [NASA-CR-2856] 1479-31153 [NASA-CR-3167] N79-30194 Time history solution program, L225 (TEV126). CARTA, F. 0. Volume 2: Supplemental system design and The influence of sweep on the aerodynamic loading maintenance document of an oscillating NACA 0012 airfoil [NASA-C14-2860] 1479-31154 [AHS 79-4] 879-49057 CLIFF, B. N. CAVALLI, D. A computer program for aircraft identification and ONERA's model of the pilot in discrete time derivative extraction 1479-30242 A79-50306 CAZENAVE, A. CLIFFORD, J. E. Results related to simulated and in-flight Pave Low III experimentation with an electric flight control A79-48682 system that can be generalized CLYNAN, N. 1479-30224 Maintenance improvement: An analysis approach CECCHINI, G. P. including inferential technical data Transatlantic flights of stratospheric balloons [AD-A068382] N79-30141 1479-31687 COE, P. L., JR. - CERNOSEK, J. Theoretical and experimental investigation of Designing with experimental mechanics ground-induced effects for a low-aspect-ratio [ABS 79-11] 879-49063 highly swept arrow-wing configuration CHANBERLIN, H. [NASA-TP-1508] 1479-31223 Energy efficient aircraft engines COKER, N. J. [8188 PAPER 79-1861] 879-47918 Windshield technology demonstrator program-canopy CHAR, V. T. detail design options study The inner regions of annular jets [80-8070376] 1479-31201 879-47520 COLLINS, F. G. CR1414, H. T. N. Boundary layer control on wings using sound and Piloted simulator investigation of helicopter leading edge serrations control systems effects on handling qualities [AIAA PAPER 79-1815] 879-47926 during instrument flight CONLEY, N. B. [AsS 79-26] 879-49078 Winglet toe out angle optimization for the Gates CHERENUKUIN, G. A. Learjet Longhorn Wing Selection of geometric parameters and location of (AIAA PAPER 79-1831] A79-47905 nose flap on swept wing root profile from tunnel CONNOB, P. C. test data. I Correlation of data related to shock-induced A79-46999 trailing-edge separation and extrapolation to CHIPNAN, H. flight Reynolds number Fully conservative numerical solutions for [NASA-CR-3178] 1479-31195 unsteady irrotational transonic flow about COOK, L. P. airfoils Lifting-line theory for a swept wing at transonic [8188 PAPER 79-1555] 879-47342 speeds CIEPLUCH, C. C. A79-47750 QCSEE - The key to future short-haul air transport COOK, N. V. 879-50208 Some aspects of the design and development of the CLARK, C. K. maritime autopilot modes for the Westland Lynx The evolution of the high-angle-of-attack features helicopter of the F-16 flight control system N79-30201 879-50438 COOPER, D. E. CLARK, D. R. The influence of engine/fuel control design on A lifting-surface method for hover/climb airloads helicopter dynamics and handling qualities ABS 79-3] 879-49056 [ABS 79-37] 879-49089 An integrated analytical and experimental COOPER, J. N. investigation of helicopter hub drag Dynamic test techniques - Concepts and practices (AHS 79-5] 879-49058 A79-50164 CLARK, I. V. CORLEIT, B. C. Flight performance of the TCV 8-737 airplane at Evaluation of airfield pavement materials based on Kennedy Airport using TRSB/MLS guidance synthetic polymers [ NASA-TM-80148] 1479-31186 879-49348 CLARK, N. N. CORNER!, G. Techniques for fault isolation ambiguity reduction Supersonic transport vis-a-vis energy savings A79-48891 [NASA-TN-75464] N79-31163 CLARK, R. K. CORNIER, K. H. Mechanical and thermophysical properties of Helicopter drive system 14 and N design guide qraphite/polyirnide composite materials [AD-A069835] 1479-30180 N79-30317

B-4

PERSONAL AUTHOR INDEX DRAPE, D. J.

Helicopter drive system R and N design guide DECKER, D. S. (AD-A069691) 879-30181 An evaluation of asphalt-rubber mixtures for use CORN, P. B. in pavement systems Lightning hazards overview: Aviation requirements [80-8069448] 879-30246 and interests DECKERT, N. H. N79-30876 Recent V/STOL aircraft designs CORSIGLIA, V. B. 819-47608 Pull-scale wind tunnel study of nacelle shape on DEL BOCA, R. L. cooling drag Multifunction c02 heterodyning laser radar for low (AIAA PAPER 79-1820) 879-47900 level tactical operations COX, C. N. A79-48685 Helicopter noise rules - Are they appropriate and DELBOCA, H. L. reasonable Heterodyning CO2 laser radar for airborne 879-49478 applications COX, L. N79-30205 Reliability improvement warranty terms and DENKO, P. S. conditions for the Integrated Avionics Control Advances in decelerating steep approach and Systems (IACS) landing for helicopter instrument approaches [AD-A069454] 879-31205 [Ails 79-16] 879-49069 CRANE, C. H. DEPONTEVES, D. Electrical insulation fire characteristics. Stabilizing electro-optical systems on helicopters Volume 2: Toxicity N79-30216 (PB-29 14841/2) 879-30490 DESJARDINS, S. P. CREWS, S. I. Crashworthy armored crewseat for the UH-60A Black Helicopter component environmental vibration Hawk testing - The poor man's fatigue test [Ails 79-10] 879-49062 [ASS 79-49] 879-49101 DESKIN, N. J. CRIST, D. A summary of NASA/Air Force full scale engine Model 206L composite litter door research programs using the F100 engine [ASS 79-31] 879-49083 [NASA-TN-79267] 879-30188 CROSS, K. D. DESTOYNDER, B. Meeting the challenge of precise navigation during Structural aspects of active controls nap-of-the-earth flight 879-30221 CARS 79-12] A79-49065 DHANVADA, N. R. CROUCH, K. E. Subsonic wind-tunnel investigation of leading-edge The feasibility of inflight measurement of devices on delta wings (data report) lightning strike parameters (NASA-CR-159120] 879-31143 [NASA-CR-158981] 879-30165 DIAMOND, P. I. CUNNINGHAM. T. B. New devices for digital communications in avionics Helicopter high grain control N79-31481 (NASA-CR-159052] 879-31221 DICARLO, D. J. CURRAN. J. J. Exploratory study of the influence of wing Development of a 'no adjustment' turboshaft engine leading-edge modifications on the spin control system characteristics of a low-wing single-engine (AilS 79-42] 879-49094 general aviation airplane CURRAN, P. N. [8188 PAPER 79-1837] 879-47908 Design procedure for aircrew station labeling DICKENS, N. selection and abbreviation Rotary balance data for a single-engine trainer N79-30208 design for an angle-of-attack range of 8 deg to 90 deg [NASA-CH-3099] 879-31152 D DINKEL, J. D. DAB!., U. Evaluation of the radar altimeter reference method Fault diagnosis of gas turbine engines by means of for determining altitude system positioning errors component characteristics determination 879-50436 A79-49806 DOAK, P. E. DANOULAKIS, J. N. Duct noise radiation through a jet flow A real-time sequential filtering algorithm for GPS A79-50110 low-dynamics navigation system DOBRZYBSKI, W. A79-48657 Noise generation by jet-engine exhaust deflection DAS, P. [DLR-FB-78-21] N79-30192 Transform domain processing for digital DOMKUWDWAR, V. N. communication systems using surface acoustic Factors controlling stability of swirling flames wave devices at diffusers in gas turbines 879-31482 A79-50209 DAVIS, J. N. DONLEY, S. T. A system for interdisciplinary analysis - A key to Flight test verification of the ASSET system improved rotorcraft design A79-48622 [ASS 79-8] 879-49060 DOTER, P. S. DAY, D. B. AH-1G helicopter, 19-round lightweight airborne Automatic test program generation selection launcher jettison envelope determination 879-48690 [AD-A069828] 879-30177 F-16 depot automatic test equipment DOUPLE, C. S. A79-48895 Performance of a pulse-decode circuit in the DAZZO, J. J. presence of interference Synthesis of digital flight control tracking A79-48713 systems by the method of entire eigenstructure DOWNING, D. B. assignment NASA/Princeton digital avionics flight test facility A79-48625 879-49344 DEBOER, W. P. DOWSETT, P. B. A simulator investigation of handling quality Recent advances in radome design criteria for CCV transport aircraft A79-49574 N79-30240 DRAPE, D. J. DECARLI, H. N. Performance evaluation of an air vehicle utilizing Analytic redundancy for flight control sensors on non-axisymmetric nozzles the Lockheed L-1011 aircraft [AIAA PAPER 79-1811] 879-47894 879-47960

8-5 DUDLEY, R. N. PERSONAL AUTHOR INDEX

DUDLEY, P. E. FAINTICH, N. B. A novel technique for obtaining aerodynamic data Digital sensor simulation at the Defense Mapping using simple, free flight trajectory measurements Agency Aerospace Center A79-48051 A79-48705 DUNNER, B. J. FANNING, A. N. Crashworthy armored crewseat for the UH-60A Black Engine-aircraft afterbody interactions - Hawk Recommended testing techniques based on YF-17 [ABS 79-10) A79-49062 experience DUNN, J. I. [AIAA PAPER 79-1829] A79-47903 Testing the F-18 at the U.S. Naval Air Test Center FARINA, A. P39-50444 Nultiradar tracking system using radial velocity DUPLESSIS, B. N. measurements Rapid reaction time techniques for a strapdown A79-49608 navigator employing electrostatic gyro technology FARRAR, P. A. A79-48697 Estimation for advanced technology engines DYKE, B. N. P.79-47957 Current Canadian developments related to low-speed FARRELL, J. L. heavy lift ACV Transfer alignment for precision pointing A79-49915 applications DZVONIK, L. I. P.79-48679 Solution of a mixed boundary value problem for PEDOBOY, B. IA. flow past a thin delta wing On a smooth approximation method and its A79-49882 application to mathematical description of wing aerodynamic characteristics A79-47001 E PEIK, B. A. EBNER, N. E. Lateral aerodynamics extracted from flight test Design and testing of a redundant skewed inertial using a parameter estimation method sensor complex for integrated navigation and [ARL-AERO-NOTE-380] N79-31146 flight control FERBNS, D. V. H79-30202 Avionics computer software operation and support EDWARDS, T. E. cost estimation Some results from the use of a control A79-48620 augmentation system to study the developed spin FERGUSON, S. N. of a light plane Development of a fly-by-wire elevator for the Bell [AIAA PAPER 79-17901 P.79-47879 Helicopter Textron 2145T EGOROV, IU. N. [ABS 79-27] P.79-49079 Selecting the passenger airplane fuselage FERLET, G. A79-47014 The equipment-system interface in an antitank ELOWITZ, N. helicopter at night Evolving methods for reducing avionics data in an R79-30211 AISF environment FEWELL, L. A. A79-48671 Fire resistant aircraft seat program EMERY, J. H. N79-31176 Multiplex technology applied to helicopters FISCHER, F. V. [ABS 79-14] A79-49067 Aeronautical information data subsystems /AIDS/ ERIN, 0. N. A79-50920 Experimental study of the gasdynamic FISHBEIN, B. D. characteristics of a stator cascade with cooling Characteristics of afterburning bypass turbojet air discharge through the vane surface engine with oxygen injection into the A79-48498 afterburner chamber ENDECOTT, B. N. P.19-48519 Electrical insulation fire characteristics. POGEL, L. J. Volume 2: Toxicity Tactical performance characterization basic [P3-294841/2) N79-30490 methodology ENGLAR, R. J. [AD-A069297) H79-31235 Flight testing the circulation control wing PORN, P. [AIAA PAPER 79-1791] P.79-47880 Multipath propagation measurement by Doppler Design of the circulation control wing STOL technique demonstrator aircraft N79-31478 [AIRA PAPER 79-1842] A79-47909 FORREST, B. D. ENGLISH, B. B. Piloted simulator investigation of helicopter The A.I. tracking problem control systems effects on handling qualities A79-49566 during instrument flight ERICSSON, L. E. [ABS 79-26] A79-49078 A summary of AGARD FDP meeting on dynamic FOSTER, C. B. stability parameters What the FAA would like in airworthiness standards N79-30220 [RIAP. PAPER 19-1851] P.19-49338 EVERETT, B. A., 3R. FOX, D. Fatigue and fracture Electric power system control techniques N79-30315 P.19-48614 BYRE, D. FRASER, K. F. Road fleet operation of air cushion assisted Load spectrum measuring equipment. Part 1: vehicles - An evaluation of technical and Details of MR 1 system presently used to acquire economic problems data in Wessex MR 31B helicopters A79-49910 [ABL-NECH-ENG-NOTE-371] N79-31194 FRAZER, L. A. Multiplex technology applied to helicopters II [ABS 79-14] P.79-49067 FANNY, N. N. I. FREEMAN, C. N. Radiation from quarter-wavelength monopoles on Analytical and experimental investigation of finite cylindrical, conical, and rocket-shaped V-type empennage contribution to directional conducting bodies control in hover and forward flight A79-50606 [ABS 79-56] P.19-49106 FAIN, B. L. FRET, D. G. Runway configuration management system concepts Power hybridization - Key to reducing avionics (AD-A069960] N79-31234 power supply weight and volume P.79-48652

B-6

PERSONAL AUTHOR INDEX GRUZDEV, V. N.

FRIED, N. N. GIESY, D. P. JTIDS relative navigation - Architecture, error A multiple objective optimization approach to characteristics and operational benefits aircraft control systems design A79-48715 A79-47962 System configuration and algorithm design of the GILBERT, V. P. inertially aided JTIDS Relative Navigation Similitude requirements and scaling relationships function as applied to model testing A79-48716 [NASA-TP-1435] 879-30176 FUHEKEN, B. GLADYSH, I. S. Noise generation by jet-engine exhaust deflection Airport power supply [DLR-FB-78-21] N79-30192 A79-50499 GLEASON, C. C. Experimental Clean Combustor Program (ECCP), phase 3 C [NASA-CR-135384] N79-31207 GABEL, N. GLOVER, K. E. Full scale ground and air resonance testing of the Some results from the use of a control Army-Boeing Vertol Bearingless Rain Rotor augmentation system to study the developed spin [AHS 79-23] A79-49075 of a light plane Evaluation of pylon focusing for reduced [AIAA PAPER 79-17901 A79-47879 helicopter vibration GOLENEV, N. P. [AD-A069712] N79-30196 The tendency of jet fuels to form deposits on a GAFFIN, N. 0. heated surface JT9D-70/59 improved high pressure turbine active A79-48856 clearance control system GORDON, N. (NASA-CE-159661] 879-31208 Design of advanced titanium structures GAGLIANI, J. [AIAA PAPER 79-18051 A79-47890 Development of fire-resistant, low smoke GORODETSKII, V. G. generating, thermally stable end items for The tendency of jet fuels to form deposits on a commercial aircraft and spacecraft using a basic heated surface polyinide resin A79-48856 N79-31171 GORRELL, V. T. GALBRAITB. T. J. Performance of two-stage fan with a first-stage A computer system for identifying aircraft rotor redesigned to account for the presence of characteristics a part-span damper A79-50168 [NASA-TP-1483] N79-30191 GALLOWAY, N. T. GOVINDANAJ, K. S. Flight testing and simulator flight fidelity The enhancement of aircraft parameter A79-50307 identification using linear transformations GANON, N. A. A79-47961 Testing and analysis of dual-mode adaptive landing GRANIERO, 3. A. gear, taxi mode test system for YF-12A New devices for digital communications in avionics [NASA-CR-144884) N79-31192 N79-31481 GANZER, U. GRANT, N. I. Wind tunnels with adapted walls for reducing wall Ultrasonic method of gun gas detection interference A79-50166 [NASA-TM-75501] 879-31230 GRAYSON, N. A. GAONKAR, G. B. Research on visual display integration for Theoretical flap-lag damping with various dynamic advanced fighter aircraft inflow models [AD-A069605] N79-30184 [ABS 79-20] A79-49073 GREEK, D. C. GARDNER, B. G. Ride qualities criteria validation/pilot Low cost inertial aiding for NAVSTAR/GPS receivers performance study: Flight test results in naval ship navigation [NASA-CR-144885] N79-31193 A79-98656 GREENWOOD, J. C. GARDNER, N. B. Navstar user equipment for civil and military Energy efficient engine flight propulsion system applications preliminary analysis and design report A79-49587 [NASA-CR-159487] N79-30189 GRENETZ, P. S. GARRISON, J. N. Maintenance improvement: An analysis approach The Bell Model 222 including inferential technical data A79-49816 [AD-A068382] 879-30141 GEDDES, J. P. GREY, J. The DC-9 Super 80 - Much more than a simple stretch Utilization of alternative fuels for A79-49223 transportation; Proceedings of the Symposium, GEE, D. R. University of Santa Clara, Santa Clara, Calif., Piloted simulator investigation of helicopter June 19-23, 1978 control systems effects on handling qualities A79-49376 during instrument flight GRIFFIN, D. F. [ABS 79-261 A79-49078 An evaluation of asphalt-rubber mixtures for use GEHLBAR, B. in pavement systems Noise generation by jet-engine exhaust deflection [ AD-A069448] N79-30246 [DLR-FB-78-21] N79-30192 GRIGOBENKO, P. P. GEISTER, D. E Influence of gas turbine engine combustion chamber Critical assessment of emissions from aircraft geometric parameters on mixture formation piston engines characteristics (AD-A071002] 879-30190 A79-48495 GEBDES, N. N. GRIMM, J. D. Piloted simulator investigation of helicopter Radar signal processing development for control systems effects on handling qualities application of VHSI during instrument flight A79-4866'4 [AHS 79-261 A79-49078 GROESBECK, D. GERHARDT, L. A. Wing aerodynamic loading caused by jet-induced State of the art in digital signal processing with lift associated with STOL-OTW configurations applications to multiple access systems [AIAA PAPER 79-1664] A79-47346 N79-31487 GRUIDET, V. N. GIBSON, J. C. On the question of selecting the characteristic Flying qualities and the fly-by-wire aeroplane quantity governing fuel self-ignition in a stream N79-30238 A79-48497

B-i GUI!, J. B. PERSONAL AUTHOR INDEX

GUIN, J. R. HARRIS, B. N. Airworthiness and flight characteristics test, Performance predictions and trials of a helicopter OV-1C takeoff performance UHF data link [AD-A069827] N79-30178 N79-31476 GUNKO, IU. P. HARRISON, B. A. Overall aerodynamic characteristics of caret and A program to compute three-dimensional subsonic delta wings at supersonic speeds unsteady aerodynamic characteristics using the A79-47012 doublet lattice method, L216 (DUBFLEX). volume GUPTA, B. P. 2: Supplemental system design and maintenance Helicopter obstacle strike tolerance document CARS 79-7] A79-49059 [NASA-CH-2850] N79-31148 Helicopter obstacle strike tolerance concepts HART, R. E. analysis Dutch roll excitation and recovery techniques on a [AD-A069877] N79-30179 C-141A Starlifter GUPTA, N. C. [AIAA PAPER 79-1801] A79-47886 Factors controlling stability of swirling flames HARTNAHN, G. L. at diffusers in gas turbines Digital adaptive control laws for VTOL aircraft A79-50209 A79-48000 GURIANOY, N. A. HARVEY, K. N. Surface-effect components of aerodynamic Design, analysis, and testing of a new generation characteristics of air-cushion vehicle with ram tail rotor pressurization [AHS 79-57] A79-49107 A79-46995 HEACOCK, P. E. GURNAN, B. S. Advanced Scout Helicopter flying qualities The impact of a multi-function programmable requirements - How realistic are they control display Unit in affecting a reduction of [ABS 79-28] A79-49080 pilot workload BEADLE!, J. N. N79-30210 Analysis of wind tunnel data pertaining to high GURUSWAN!, P. angle of attack aerodynamics. Volume 1: Flutter analysis of two-dimensional and Technical discussion and analysis of results two-degree-of-freedom airfoils in [AD-A069646] 879-30148 small-disturbance, unsteady transonic flow Analysis of wind tunnel data pertaining to high (AD-A069223) N79-31157 angle of attack aerodynamics. Volume 2: Data base [AD-A069647] 879-30149 H HECHT, C. BABERCON, C. B., JR. Predictive guidance for interceptors with time Lighter than air vehicles. Citations from the delays NTIS data base A79-47939 [NTIS/PS-79/0471/7] N79-30162 HECTOR, B. Lighter than air vehicles. Citations from the A computer program for aircraft identification and Engineering Index data base derivative extraction [NTIS/PS-79/0472/5] 879-30163 A79-50306 BALANANDARIS, A. HEFPLEY, R. K. Microcomputer applications in strapdown heading A compilation and analysis of helicopter handling and attitude reference system qualities data. Volume 2: Data analysis A79-48606 [NASA-CR-3145] N79-31222 HALVES, D. N. RECANT!, D. N. INACT - Interactive test data analysis Flight investigation of helicopter IFR approaches A79-50430 to oil rigs using airborne weather and mapping HANEL, P. G. radar Dynamic windtunnel simulation of active control [ABS 79-52] A19-49104 systems HEITZ, N. E. N79-30233 High-performance reinforced plastic structures for BAKER, N. J. civil aviation A simplified gross thrust computing technique for A79-47302 an afterburning turbofan engine HENNERL!, R. A. A79-50440 Design of the circulation control wing STOL BANKE, D. demonstrator aircraft In-flight handling qualities investigation of [AIAA PAPER 79-1842] A79-47909 various longitudinal short term dynamics and HERTZ, J. direct lift control combinations for flight path Ultra-high-modulus graphite-epoxy conical shell tracking using DFVLR HFB 320 variable stability development, supplement aircraft [AD-A069795] N79-30335 N79-30237 HESS, J. R., JR. HANSON, D. B. Benefits of aerodynamic interaction to the three The aeroacoustics of advanced turbopropellers surface configuration A79-50236 [AIAA PAPER 79-1830] A79-47904 HANSON, H. N. HICKS, J. N. Evaluation of the practical aspects of vibration Flight test technology development - A preview of reduction using structural optimization techniques DyMoTech [ABS 79-21] 479-49074 A79-50435 HARD!, G. H. HICKS, N. N. Flight experience with advanced controls and Upper-surface modifications for C sub 1 max displays during piloted curved decelerating improvement of selected NASA 6-series airfoils approaches in a powered-lift STOL aircraft [NASA-TM-78603] N79-30143 N79-30243 HILADO, C. J. HARGRAVE, P. J. Evaluation of airfield pavement materials based on Navstar user equipment for civil and military synthetic polymers applications A79-49348 479-49587 RILEY, P. E. HARRIS, F. U. Performance evaluation of an air vehicle utilizing Helicopter performance methodology at Bell non-axisymmetric nozzles Helicopter Textron [AIAA PAPER 79-1811] A79-47894 (AHS 79-2] 479-49055 HILL, N. C., JR. HARRIS, N. L. Effect of nozzle spacing on ground interference Avionics computer software operation and support cost estimation forces for a two jet V/STOL aircraft [AIAA PAPER 79-1856] 479-49339 A79-48620

B-8

PERSONAL AUTHOR INDEX JENKINS, H. C.

BILLER, E. H. HUNTER, B. 3. Synthetic aperture radar map matching for navigation Automatic scanning inspection of composite A79-48603 helicopter structure using an advanced HINDSON, N. S. technology fluoroscopic system Flight experience with advanced controls and [ABS 79-35] A79-49087 displays during piloted curved decelerating HUNTING, A. N. approaches in a powered-lift STOL aircraft Flight investigation of helicopter lEE approaches N79-30243 to oil rigs using airborne weather and mapping HIRATANA, 5.. Y. radar Nodal interpolation program, L215(INTERP). Volume [ABS 79-52) A79-49104 2: Supplemental system design and maintenance HUHRELL, H. G. document A summary of RASA/Air Force full scale engine [NASA-CR-2848) 879-31147 research programs using the FlOG engine Equation modifying program, 1219 (EQNOD) . Volume [NASA-TM-79267] 879-30188 2: Supplemental system design and maintenance BUTCHINSON, C. document Realization of a helicopter-oriented real-time (NASA-CR-2856] 1479-31153 data system for research, experimental, and prototype flight testing H000KINSON, J. A79-49102 Are today's specifications appropriate for [ABS 79-503 tomorrow's airplanes? 879-30239 BOEPGEN, G. A self contained collision avoidance system for 111FF, K. N. helicopters Considerations in the analysis of flight test 879-30206 maneuvers A79-50433 HOPPRAN, J. B. Windshield technology demonstrator program-canopy ILLG, V. Fatigue and fracture detail design options study 879-30315 (AD-A070376) 4479-31201 HOYFMANN, N. INGLEE, C. F. Implementation of flight control in an integrated Self-contained grease lubrication systems for guidance and control system aircraft applications 879-30215 [AilS 79-39] A79-49091 BOGGATT, J. T. IRVOAS, J. Development and demonstration of manufacturing Results related to simulated and in-flight processes for fabricating graphite/PER-15 experimentation with an electric flight control polyimide structural elements system that can be generalized 879-30301 N79-30224 BOB, B. H. IRVIN, A. S. Handling quality and display requirements for low Self-contained grease lubrication systems for speed and hover in reduced flight visibility aircraft applications A79-49091 [ABS 79-29] A79-49081 [AHS 79-391 HOLCORB, 5. L. ISAEV, V. V. The Beech Model 77 Skipper spin program Selection of geometric parameters and location of [AIAA PAPER 79-18351 A79-47907 nose flap on swept wing root profile from tunnel test data. I BOLLARD, B. A79-46999 Fluidics: Feasibility study electro/hydraulic/fluidic direct drive servo valve IVANOV, V. N. [AD-A069798] 879-30195 Current status of airport terminal complex development abroad BOSKING, 5. B. A79-50240 A new U. U.T./test station interface A79-48896 IVANOY, V. S. BOSTETLER, L. U. Optimal thermogasdynainic design of gas turbine Expanding the region of convergence for SITAR engines using element prototypes. I through improved modelling of terrain A79-46997 nonlinearities A79-48678 HOWARD, N. I. J Geometric data transfer JACKSON, E. N. [AIAA PAPER 79-1844] A79-47910 Microcomputer applications in strapdovn heading HOWELL, N. E. and attitude reference system Design and testing of a redundant skewed inertial A79-48606 sensor complex for integrated navigation and JACKSON, J. A. flight control Design of the circulation control wing STOL 879-30202 demonstrator aircraft A79-47909 HOWELLS, H. [AIAA PAPER 79-18421 Subjective assessment of a helicopter approach JAMES, H. N. system for IFE conditions A new approach to the solution of large, full 4479- 30 209 matrix equations: A two-dimensional potential HOWLETT, J. J. flow feasibility study The influence of engine/fuel control design on [NASA-CH-3173] N79-31533 helicopter dynamics and handling qualities JANESON, A. [ABS 79-37] A79-49089 Fully conservative numerical solutions for HUGHES, C. N. unsteady irrotational transonic flow about Design, analysis, and testing of a new generation airfoils A79-47342 tail rotor [AIAA PAPER 79-1555] [ABS 79-57] P.79-49107 JARVINEN, 8. A. Complex quaternion notation in coordinate HUGHES, U. A. Dynamic test techniques - Concepts and practices transformations A79-50164 A79-48681 HULTBERG, H. S. JAUER, B. A., JR. Rotary balance data for a typical single-engine Research on visual display integration for general aviation design for an angle-of-attack advanced fighter aircraft range of 8 deg to 90 deg. 1: High-wing model B [AD-A069605] 879-30184 879-30145 JENKINS, H. C. [NASA-CB-3097] Effect of nozzle spacing on ground interference forces for a two jet V/STOL aircraft [AIAA PAPER 79-1856] P.79-49339

B-9 JEPSON, V. B. PERSONAL AUTHOR INDEX

JEPSON, V. D. KENDRICK, J. D. The influence of sweep on the aerodynamic loading Estimation of aircraft target motion using pattern of an oscillating NACA 0012 airfoil recognition orientation measurements [AHS 79-41 A79-49057 A79-47987 JOHNS, A. L. KENDRICK, H. A. Performance of a V/STOL tilt nacelle inlet with Simulation and study of V/STOL landing aids for blowing boundary layer control USNC AV-8 aircraft [AIAR PAPER 79-1163] A79-47347 R79-30214 JOHNSON, G. A. KENNEDY, T. A. Conference on Fire Resistant Materials: A Synthesis of digital flight control tracking compilation of presentations and papers systems by the method of entire eigenstructure [NASA-CP-2094] R79-31166 assignment FIREMEN program A79-48625 879-31178 The design of digital controllers for the C-141 Development of aircraft lavatory compartments with aircraft using entire eigenstructure assignment improved fire resistance characteristics. Phase and the development of an interactive computer 2: Sandwich panel resin system development design program [NASA-CR-152120] N79-31354 [AD-A069192] N79-31224 JOHNSON, J. 1., JR. KENNOY, J., JR., Exploratory study of the influence of wing Evolving methods for reducing avionics data in an leading-edge modifications on the spin AISF environment characteristics of a low-wing single-engine A79-48671 general aviation airplane KENT, J. S. [AIAA PAPER 79-1837] A79-47908 An evaluation of the bird aircraft strike hazard JOHNSON, K. G. at Hill AFB, Utah (AFLC) A multiple objective optimization approach to [AD-A070459] N79-31184 aircraft control systems design KERR, A. V. A79-47962 A system for interdisciplinary analysis - A key to JOHNSON, T. B., JR. improved rotorcraft design Subsonic wind-tunnel investigation of leading-edge [ABS 79-8] P.79-49050 devices on delta wings (data report) KHACBATUBIAN, 0. A. [NASA-CR-159120) N79-31143 Experimental study of the turbulent wake JONES, A. A. downstream of a fan jet Road fleet operation of air cushion assisted A79-48507 vehicles - An evaluation of technical and KHVOSTOV, N. I. economic problems Nozzles for vectored thrust jet engines A79-49910 A79-47428 JONES, B. KILLIAN, H. V. The application of multiple swirl modules in the Scan converter and raster display controller for design and development of gas turbine combustors night vision display systems [AIAA PAPER 79-1196] A79-47349 R79-30203 JONES, H. D. KIRKPATRICK, C. N. Ground test vehicle terting Real time weather display in the general aviation [AilS 79-401 A79-49092 cockpit JONES, J. E. [AIAA PAPER 79-1821] A79-47901 Path controllers: Unification of concepts and KITA, N. comparison of design methods Aerodynamic effects of an attitude control vane on [AD-A070252] N79-31227 a tilt-nacelle V/STOL propulsion system JORGENSEN, P. A. [AIAA PAPER 79-1855) A79-479114 Modern systems for air traffic control KLAVER, L. J. P.79-50921 Combined I/Ha-band tracking radar JUERGENS, N. A. A79-49565 F/A-18 Hornet display system KLEBANO?P, P. S. A79-48630 A low-velocity airflow calibration and research facility [PB-294501/2] N79-31237 K KLEIDER, A. KALITINA, N. N. Applications of pattern recognition systems for Changes in the quality of T-6 fuel upon prolonged day/night precision aircraft control storage N79-30204 A79-48858 KLEIN, K. KANE, E. J. Multipath propagation measurement by Doppler Simulation and study of V/STOL landing aids for technique USMC AV-8 aircraft N79-31478 N79-30214 KLEINNANN, N. B. KANNARKAR, J. S. E-4B mission electrical power Path controllers: Unification of concepts and P.79-48617 comparison of design methods ELINGEE, G. [AD-A070252] N79-31227 The influence of the environment on the KATZ, J. elastoplastic properties of adhesives in metal Full-scale wind tunnel study of nacelle shape on bonded joints cooling drag [ESA-TT-521] 879-30391 [AIAA PAPER 79-1820] A79-47900 KNAPP, P. N. HAVANA, H. Y. AR/USM-449/V/ ATE for worldwide support of the P3 Ride qualities criteria validation/pilot Orion performance study: Flight test results A79-48884 [NASA-CR-144885] 879-31193 HO, N. V. N. KEEN, D. V. The inner regions of annular jets Operational experience with the AN/ARN-131 Omega A79-47520 Navigation Set KOCUBEK, J. B. A79-48676 Helicopter performance methodology at Bell KELLY, A. J. Helicopter Textron Guidance accuracy considerations for the microwave EARS 79-2] A79-49055 landing system L-band precision DuE HOBBLER, N. A79-48692 Open/closed loop identification of stability and KENPKE, H. E. control characteristics of combat aircraft An overview of NASA research on positive R79-30232 displacement type general aviation engines [NASA-TM-79254] N79-31210

B-10

PERSONAL AUTHOR INDEX LARSON, B. S.

KOGEB, 0. D. KUHN, N. G. Microprocessor-based digital autopilot development Aerodynamics of spoiler control devices for the XBQM-106 Mini-RPV (8188 PAPER 79-1873] A79-47925 A79-48608 KULFAN, B. N. KOUN, J. S. Wing geometry effects on leading-edge vortices Application of Lagrange Optimization to the drag [AIAA PAPER 79-1872] A79-49341 polar utilizing experimental data EDO, P. S. [AIAA PAPER 79-1833] A79-49335 Application of finite-element and holographic KORNILOY, I. N. techniques in the design of turboshaft engine A method of the theory of airfoil profiles with a components jet flap (AilS 79-41] 879-49093 A79-47119 KURTENBACH, P. J. KORNOUKHOV, A. A. A simplified gross thrust computing technique for Long-life GTE operation based on technical condition an afterburning turbofan engine A79-48517 A79-50440 KORTE, U. KUBZHALS, P. R. Stability and control aspects of the CCV-F104C Systems implications of active controls 879-30234 879-30219 KOTLIAB, L. N. KUTYSH, I. I. Determination of turning angle of a jet impinging Experimental study of the gasdynamic on a bucket with visor characteristics of a stator cascade with cooling A79-48500 air discharge through the vane surface K0URTIDES, D. A. A79-48498 Conference on Fire Resistant Materials: A KTSEB A. C. compilation of presentations and papers The aerial relay system - An energy-efficient [NASA-CP-20914] 879-31166 solution to the airport congestion problem KOVALEV, A. A. (AIAA PAPER 79-1865] A79-47921 Long-life GTE operation based on technical condition 879-48517 KOVALEV, G. I. L Evaluation of the temperature of the initiation of LA BOBTHE, C. jet fuel decomposition by means of the 'hardness The feasibility of modern dirigibles factor' (ONERA, TP NO. 1979-93] 879-49541 A79-48857 LAANANEN, D. H. EOZHEVNIKOV, ID. V. Crashworthy armored crewseat for the UH-60A Black Statistical diagnostics of aircraft engines Hawk 879-46996 CARS 79-101 A79-49062 Optimal thermogasdynanic design of gas turbine LABBE, J. engines using element prototypes. I Laser velocimeter applied to the study of circular 879-46997 distorsion effects in a low speed compressor ERAG, B. (ONEBA, TP NO. 1979-30] 879-50925 Dynamic windtunnel simulation of active control LABERGE, E. F. C. systems Guidance accuracy considerations for the microwave 879-30233 landing system 1-band precision DME KNASNAIA, I. V. A79-48692 Method of determining mechanical-impurity contents LAGRANGE, J. B. in jet fuels Terrain-following radar - Key to low-altitude flight A79-48859 A79-48686 KREISSELNEIEB, G. LANANNA, N. J. An in-flight controller insensitive to parameters Are today's specifications appropriate for variation tomorrow's airplanes? (DLR-FB-78-07] 879-30197 N79-30239 KRICHAKIN, V. I. LAMONT, G. B. Use of the method of variable directions for Microprocessor-based digital autopilot development numerical study of the temperature states of a for the XBQM-106 Mini-RPV turbine disk with blades A79-48608 879-48518 LANE, N. E. KRIESNR, U. B. Design procedure for aircrew station labeling Load spectrum measuring equipment. p art 1: selection and abbreviation Details of ME 1 system presently used to acquire N79-30208 data in Wessex ME 31B helicopters LANG, K.-W. ARL-MECHENGNOTE-371] 879-31194 An approach for estimating vibration KROEGEB, R. A. characteristics of nonuniform rotor blades Full-scale wind tunnel study of nacelle shape on A79-49718 cooling drag LANGE, H. H. (8188 PAPER 79-1820] 879-47900 In-flight handling qualities investigation of KEOLL, R. I. various longitudinal short term dynamics and Dynamic loads analysis system (DYLOFLEX) summary. direct lift control combinations for flight path Volume 1: Engineering formulation tracking using DFVLR HER 320 variable stability [NASA-CR-2846- 1] 879-31144 aircraft Dynamic loads analysis system (DELOFLEX) summary. U79-30237 Volume 2: Supplemental system design information LANNI, N. J. (NASACR-2846-2] 879-31145 The DG-800 - A rugged, high performance heading Modal interpolation program, L215(IRTERP). Volume reference unit 2: Supplemental system design and maintenance A79-48677 document LAPPOS, N. (NASA-CR-2848] 879-31147 Spirit helicopter handling qualities design and Time history solution program, 1225 (TEV126) development Volume 2: Supplemental system design and [AIlS 79-24] 879-49076 maintenance document LARSON, B. S. [NASA-CR-2860] 879-31154 Aerodynamic and acoustic investigation of inverted KUBIN, R. F. velocity profile coannular exhaustnozzle models Thermal characteristics of 3501-6/AS and 5208/T300 and development of aerodynamic and acoustic graphite epoxy composites prediction procedures, comprehensive data [AD-8071067] 879-31357 report, volume 1 KUCZTNSKI, N. A. (NASA-CE-159515] 879-30185 The influence of engine/fuel control design on helicopter dynamics and handling qualities CABS 79-37] 879-49089

B-il

LAUGBREY, J. A. PERSONAL AUTHOR INDEX

Aerodynamic and acoustic investigation of inverted LOGIN, A. B. velocity profile coannular exhaust nozzle models An integrated analytical and experimental and development of aerodynamic and acoustic investigation of helicopter hub drag prediction procedures, comprehensive data [ABS 79-5] A79-49058 report, volume 2 LOKAI, V. I. [NASA-cR-159516] N79-30186 Gas turbines for flight vehicle engines: Theory, Aerodynamic and acoustic investigation of inverted design, and calculation /Third review and velocity profile coannular exhaust nozzle models enlarged edition! and development of aerodynamic and acoustic A79-50421 prediction procedures LONGRIRE, D. E. [NASA-CR-3168] N79-31212 A status report on the advanced FIREFLY assessment LAUGUREY, J. A. program Performance evaluation of an air vehicle utilizing A79-L48609 non-axisymmetric nozzles LOTTATI, I. [AIAA PAPER 79-18111 A79-47894 Active external store flutter suppression in the LAUTNEE, D. E. YF-17 flutter model Electric power system control techniques A79-49866 A79-48614 On single-degree-of-freedom flutter induced by LAWRENCE, J. 3., JR. activated controls Windshield technology demonstrator program-canopy A79-49867 detail design options study LOVERA, B. [AD-A070376] 879-31201 Design and development of the Agusta A 109 LEATHAN, A. L. helicopter H-X combat search and rescue avionics study results A79-49815 A79-4868L4 LOT, S. L. LEBOVITZ, B. A. Research on visual display integration for ARIA takeoff performance flight test program advanced fighter aircraft A79-50437 [AD-A069605] 879-30184 LEE, B. L. LUCAS, E. J. Experimental measurements of the rotating Engine-aircraft afterbody interactions - frequencies and mode shapes of a full scale Recommended testing techniques based on YF-17 helicopter rotor in a vacuum and correlations experience with calculated results [AIAA PAPER 79-1829] A79-147903 CARS 79-18] A79-49071 LUCKEING, J. B. LEE, J. Flow visualization studies of a general research Analysis of plume rise from let aircraft fighter model employing a strake-wing concept at [CONF-790142--1] 879-31204 subsonic speeds LEE, P. B. [NASA-TN-80057] 879-30147 A users manual for a computer program to generate LUDINGTON, D. fatigue spectrum loading sequences Real time compression of video signals [AD-A069288] 879-31198 A79-48712 LENONT, B. E. LURES, A. B. Agricultural helicopters Effect of tip shape on blade loading [AilS 79-601 A79-149064 characteristics for a two-bladed rotor in hover LENSKI, J. W.,JR. [ABS 79-1) A79-49054 Self-contained grease lubrication systems for LUNN, K. aircraft applications Realization of a helicopter-oriented real-time [ABS 79-39] A79-149091 data system for research, experimental, and LEONG, P. J. prototype flight testing Digital simulation of a three-phase generator [AHS 79-501 A79-49102 A79-L48618 LEVINE, A. B. Development of a no adjustment turboshaft engine syl control system MACALES, J. S. [ABS 79-42] A79-490914 Fuel tank survivability for hydrodynamic ram LEWIS, C. J. G. induced by high velocity fragments. Part 2: Helmet mounted display and sight development Numerical analyses [AHS 79-17] A79-49070 [AD-A070128] 879-31200 LIEBNAN, P. N. MACDONALD, B. I. A report on the Sperry Dome Radar Full scale ground and air resonance testing of the A79-49567 Army-Boeing Vertol Bearingless Main Rotor LIENBART, N. AHS 79-23] A79-49075 Aerodynamic excitation forces of blade vibrations MACK, N. D. in axial turbomachinery as a result of Aerodynamics of spoiler control devices interference from nearby cascades [AIAA PAPER 79-18731 A79-47925 A79-48572 MACMILLAN, N. L. LI000RI, F. J85-CAN-15 compressor stall and flameout A Navy plan for the development of a practical investigation computer-aided programming /CAP/ system for A79-50441 analog circuit test design NAGEE, J. P. A79-48870 XV-15 flight test results compared with design goals LITTLE, H. E. [AIAA PAPER 79-1839] A79-49336 Separation testing of large weapons from the B-i MAINE, N. E. bomber Considerations in the analysis of flight test A79-50429 maneuvers LOCKHART, L. B., JR. A79-50433 High performance composites and adhesives for NAKSUTOVA, N. K. V/STOL aircraft Gas turbines for flight vehicle engines: Theory, [AD-A069611] 879-30332 design, and calculation /Third review and LOEBERT, G. enlarged edition! Stability and control aspects of the ccV-F104c A79-501121 879-302314 NALAVASI, B. LOELIGER, N. Transatlantic flights of stratospheric balloons System configuration and algorithm design of the N79-31687 inertially aided .JTIDS Relative Navigation NALISBEVSKAIA, N. A. function On the question of selecting the characteristic A79-48716 quantity governing fuel self-ignition in a stream A79-48497

B-12

PERSONAL AUTHOR INDEX NELNIKOV, B. N.

MALOKAS, J. T., JR. MCCABE, B. J. A developmental computer model for investigations Built in test of A/D converters - Present of air traffic management problems: A case approaches and recommendations for improved BIT investigating two decision strategies effectiveness [AD-A071075] N79-31189 A79-48621 NALYSHEVA, I. V. MCCALL, N. B. Changes in the quality of 1-6 fuel upon prolonged Analysis and evaluation of current NIL-STD-1553 storage digital avionics architecture as the basis for A79-48858 advanced architectures using MIL-STD-1553R MANDELL, B. N. A79-48629 Financing the capital requirements of the US RCCLOUD, J. L., III airline industry in the 1980's The promise of multicyclic control 879-30164 [RASA-TM-78621] W79-31137 MARIE, F. MCCOLLOR, N. L. Subsonic and transonic flows on a variable sweep Techniques for fault isolation ambiguity reduction wing A79-48891 [ONERA, TP NO. 1979-102] P.79-48849 MCCOLLOUGH, J. B. MANOR, D. A design perspective on new technologies for A cheap, effective icing detector for general general aviation aviation aircraft A79-49486 [AIAA PAPER 79-1823] A79-47902 MCCOUBBET, G. A. MARCHAND, B. Design and development of a hybrid composite rotor Open/closed loop identification of stability and blade for the circulation control rotor system control characteristics of combat aircraft [AHS 79-46] A79-49098 N79-30232 RCELBEATH, K. N. MARCHM&N, J. P., III An advanced guidance and control system for rescue A cheap, effective icing detector for general helicopters aviation aircraft N79-30217 [AIAA PAPER 79-1823] A79-47902 MCGIMPSET, B. N. RARER, A. J. 385-CAR-15 compressor stall and flameout Electric power system control techniques investigation A79-48614 P.79-50441 MARGASON, B. J. MCLART!, T. T. Powered low-aspect-ratio Wing In Ground effect Helicopter performance methodology at Bell (WIG) aerodynamic characteristics Helicopter Textron [NASA-TN-78793] N79-31141 [ABS 79-2] A79-49055 MARGULIS, S. U. MCMILLAW, D. B. Determination of turning angle of a jet impinging Implementing .JTIDS in tactical aircraft on a bucket with visor N79-31491 A79-48500 NCMULDROCH, C. G. MARKETOS, J. D. VIOL controls for shipboard landing Maritime patrol airship concept study [NASA-CR-162140] N19-30193 (AD-A070131) 879-31138 RCVITIE, A. MABR, H. L. Flight experiments to evaluate the effect of Wind tunnel and flight test of the XV-15 Tilt wing-tip sails on fuel consumption and handling Rotor Research Aircraft characteristics [ABS 79-54] A79-49105 A79-49818 MARTHE, B. MEADOWS, J. An integrated analytical and experimental The development and in-flight evaluation of a investigation of helicopter hub drag triplex digital autostabilization system for a (ABS 79-5] A79-49058 helicopter MARTIN, M. S. N79-30200 E-3A sentry /AWACS/ ATPG MEBDI, I. S. A79-48873 Digital simulation of a three-phase generator MARZESKI, J. N. A79-48618 Ambient correction factors for aircraft gas MEHRA, B. K. turbine idle emissions Application of bifurcation analysis and [AD-A069240] N79-31218 catastrophe theory methodology /BACTN/ to RASCLE, J. L. aircraft stability problems at high The equipment-system interface in an antitank angles-of-attack helicopter at night P.79-47943 N79-30211 Application of singular perturbation techniques RATIAZH, A. I. /SPT/ and continuation methods for on-line Selection of geometric parameters and location of aircraft trajectory optimization nose flap on swept wing root profile from tunnel A79-47991 test data. I A study of the application of singular A79-46999 perturbation theory MAUNDER, U. P. (NASA-CR-3167] N79-30194 AFFTC parameter identification experience MELANCOR, C. [AIAA PAPER 79-1803] A79-47888 A combined air-cushion and endless belt A computer program for aircraft identification and transportation system derivative extraction P.79-49911 P.79-50306 MELENTEVA, N. I. AFFTC parameter identification experience Changes in the quality of T-6 fuel upon prolonged A79-50434 storage MAYBECK, P. S. A79-48858 Estimation of aircraft target notion using pattern RELLOB, A. M. recognition orientation measurements Correlation technique for ambient effects on P.79-47987 oxides of nitrogen P.79-49922 MAZBUL, I. I. Overall aerodynamic characteristics of caret and MELLOTT, B. B. delta wings at supersonic speeds Maintenance improvement: An analysis approach A79-47012 including inferential technical data MCALLISTER, J. D. (AD-A068382] 879-30141 Design guidance from fighter CCV flight evaluations MELNIKOV, B. N. N79-30235 Experimental investigation of helicopter flight modes on helicopter-generated noise A79-47873

B-13 MELONS, B. PERSONAL AUTHOR INDEX

Supersonic transport aircraft noise, problems of MONARHOY, N. B. noise reduction and establishment of standards Analytic formulas for wing profile aerodynamic A79-50237 NELONE, H. characteristics in incompressible flow A79-47000 Surveys of grooves in 19 bituminous runways MORGEON, B. J. (AD-A069889) N19-31233 Multifunction CO2 heterodyning laser radar for low MELUZOV, JO. V. level tactical operations Optimal thermogasdynamjc design of gas turbine engines using element prototypes. I Heterodyning CO2 laser radar for airborne A79-48685 479-46997 applications MENSBIKH, N. I. 579-30205 Most rational linearization of nonlinear unsteady MONTGOMERY, T. D. heat conduction problems Considerations in the analysis of flight test A79-48501 maneuvers BENSON, K. L. A79-50433 Recent progress in aircraft sink rate measurement MOOI.3, R. A. [AIAA PAPER 79-1798] A79-47884 A simulator investigation of handling quality NETZDOBFF, N. criteria for CCV transport aircraft Implementation of flight control in an integrated N79-30240 guidance and control system MOORE, B. D. N79-30215 Aerodynamic performance of 1.38-pressure-ratio, MICHAEL, G. J. variable-pitch fan stage Estimation for advanced technology engines [NASA-TP-1502] N79-31213 A79-47957 Aerodynamic performance of axial-flow fan stage NIKOLOWSKT, V. T. operated at nine inlet guide vane angles Identifying desirable design features for the C-XE [NASA-TP-1510] 579-31214 aircraft - A systems approach MOORE, V. H. [AIAA PAPER 79-1796] 479-47883 Design of the circulation control wing STOL MILLER, B. demonstrator aircraft Energy efficient aircraft engines [AIAA PAPER 79-1842] A79-47909 [AIAA PAPER 79-1861] A79-47918 HORDES, R. B. MILLER, C. B. An analysis of SAPPHIRE image parameters as a An evaluation of sidestick force/deflection function of processing parameters characteristics on aircraft handling qualities A79-48666 A79-50428 MORKOVIN, B. V. MILLER, F. L. Mechanics of boundary layer transition, part 2: Advanced BPV electrical systems - Instability and transition to turbulence A79-48615 [VKI-LECTUBE-SERIES-3-PT-2] N79-31530 MILLER, G. E. MORRIS, J. B. A microprocessor system for flight control research Design considerations for reliable P8W flight A79-48623 control MILLER, B. D. 579-30231 Dynamic loads analysis system (DYLOFLEX) summary. NOTYKA, P. Volume 1: Engineering formulation A deterministic investigation of strapped down [NASA-CR-2846-1] N79-31144 navigation system accuracy Dynamic loads analysis system (DYLOPLEX) summary. A79-48695 Volume 2: Supplemental system design information NOU-.JIR, L. [NASA-CR-2846-2) N79-31145 Flow patterns and aerodynamic characteristics of Equation modifying program, L219 (EQMOD) . Volume wing with strake 2: Supplemental system design and maintenance [AIAA PAPER 79-1877] A79-47928 document MODILLE, B. [NASA-CR-2856] 579-31153 Ten years of Aerospatiale experience with the A program for calculating load coefficient fenestron and conventional tail rotor matrices utilizing the force summation method, [ASS 79-58] A79-49108 L218 (LOADS). Volume 2: Supplemental system MORSE, C. E. design and maintenance document Automated tracking for aircraft surveillance radar [NASA-CR-2854] 579-31155 systems MILLS, U. S. A79-49604 Research on visual display integration for MURHIN, A. A. advanced fighter aircraft [AD-A069605] Long-life GTE operation based on technical condition N79-30184 A79-48517 NILSTEIN, L. B. NULCAT, V. Transform domain processing for digital Rotary balance data for a typical single-engine communication systems using surface acoustic general aviation design for an angle-of-attack wave devices range of 8 deg to 90 deg. 2: High-wing model A N79-31482 [NASA-CB-3101 ] N79-31149 MIRANDA, L. B. BURRO, A. M. Laminar flow stabilization by surface cooling on Recent advances in radome design hydrogen fueled aircraft A79-49574 [AIAA PAPER 79-1863] A79-47920 MYHRE, B. N. MINSKY, V. UHF coplanar-slot antenna for Critical assessment of emissions from aircraft aircraft-to-satellite data communications piston engines [NASA-TN-79239) N79-31185 [AD-A071002] N79-30190 NOCBBINO, H. J. Superplastic forming diffusion bonding of titanium helicopter airframe components NAKARO, T. [AHS 79-33] A79-49085 Investigation of air stream from combustor-liner ROCK, N. A.. air entry holes, 3 F-16 Avionics Intermediate Shop /AIS/ Interim [NASA-TN-75430] N79-31206 Contractor Support initiatives RARDI, L. U. [AIAA PAPER 79-1868] A79-47923 Ride qualities criteria validation/pilot NOMITAMA, T. S. performance study: Flight test results Project NAVTOLAND (Navy vertical takeoff and [NASA-CR-144885] landing capability development) N79-31193 N79-30212

B-i 4

PERSONAL AUTHOR INDEX PANTASON, P.

NELSON, D. P. On single-degree-of-freedom flutter induced by - Aerodynamic and acoustic investigation of inverted activated controls velocity profile coannular exhaust nozzle models A79-49867 and development of aerodynamic and acoustic NORTHAN, C. B. - prediction procedures, comprehensive data Characterization of a swept-strut hydrogen report, volume 1 fuel-injector for scranjet applications [NASA-CE-159515] N79-30185 A79-49345 Aerodynamic and acoustic investigation of inverted HORDE, V. D. velocity profile coannular exhaust nozzle models Experiments of shock associated noise of and development of aerodynamic and acoustic supersonic jets prediction procedures, comprehensive data [AIAA PAPER 79-1526] A79-47341 report, volume 2 NOVAK, L. N. (NASA-CE-159516] N79-30186 Millimeter airborne radar target detection and Aerodynamic and acoustic investigation of inverted selection techniques velocity profile coannular exhaust nozzle models A79-48665 and development of aerodynamic and acoustic NOVOSELOV, EU. N. prediction procedures Solution of the inverse aerodynamics problem by [14ASA-CR-3168] N79-31212 the random search method NELSON, J. B. A79-47002 Aircraft turbine engine monitoring experience: RUNE, B. C. Implications for the P100 engine diagnostic Helicopter high grain control system program [NASA-CR-159052] N79-31221 [AD-A069282] 879-31217 NELSON, K. D. J85-CAN-15 compressor stall and flameout L.4 investigation OBBAND, J. A79-50441 Realization of a helicopter-oriented real-time NENAT-NASSER, S. data system for research, experimental, and An approach for estimating vibration prototype flight testing characteristics of nonuniform rotor blades [AHS 79-50] 879-49102 A79-49718 OBRYAN, V. C. BENEC, C. Some results from the use of a control Verification of operational flight programs by augmentation system to study the developed spin simulation of a light plane 879-48667 [AIAA PAPER 79-1790] A79-47879 NESTERENKO, V. G. 000NNBLL, B. N. On the influence of relative pitch in the subsonic Automated tracking for aircraft surveillance radar turbine cascade systems A79-48503 A79-49604 NESTEROV, B. D. OLSON, N. N. Determination of turning angle of a jet impinging Performance modelling methods on a bucket with visor A79-50167 A79-48500 ONKBN, B. NEUNAIB, C. Failure detection in signal processing and sensing The influence of the environment on the in flight control systems elastoplastic properties of adhesives in metal A79-47971 bonded joints OBLOFF, K. I. [ESA-TT-521] N79-30391 Effect of tip shape on blade loading NEWNAN, N. characteristics, for a two-bladed rotor in hover Utilization of alternative fuels for EARS 79-1] A79-49054 transportation; Proceedings of the Symposium, ORVOS, P. S. University of Santa Clara, Santa Clara, Calif., Tapered roller bearing development for aircraft June 19-23, 1978 turbine engines A79-49376 [AD-A069440] N79-30555 NEWTON, B. C., JR. OSBORN, N. N. Power hybridization - Key to reducing avionics Aerodynamic performance of 1.38-pressure-ratio, power supply weight and volume variable-pitch fan stage A79-48652 [14ASA-TP-1502] 1179-31213 NICHOLLS, J. A. OSOBGIN, V. D. Critical assessment of emissions from aircraft On a smooth approximation method and its piston engines application to mathematical description of wing [AD-A071002] N79-30190 aerodynamic characteristics NIELSEN, J. P. A79-47001 An evaluation of asphalt-rubber mixtures for use OVCHINNIOV, V. A. in pavement systems On a smooth approximation method and its [AD-A069448] N79-30246 application to mathematical description of wing NIBNANN, J. B. aerodynamic characteristics Airworthiness and flight characteristics test, A79-47001 OV-1C takeoff performance OVEREND, N. J. [80-8069827] N79-30178 Design criteria for airline operation NIENEIER, N. H. [AIAA PAPER 79-1849] A79-49337 An evaluation of the bird aircraft strike hazard at Hill AFB, Utah (APLC) (AD-A070459] N79-31184 p WILSON, B. N. PACE, B. Engineering and manufacturing communication via Critical assessment of emissions from aircraft the computer data base piston engines [AIAA PAPER 79-1845] 879-47911 [AD-A071002] 879-30190 NILSSON, N.-A. PAEZ, C. A. Ellipsoidal modelling of aircraft targets for Design of advanced titanium structures evaluation of electronic fuzes [AIAA PAPER 79-1805] A79-47890 A79-49580 PANTASON, P. NESS, C. Rotary balance data for a single-engine trainer The Swedish approach to escape system testing design for an angle-of-attack range of 8 deg to A79-50427 90 deg NISSIN, B. [NASA-CR-3099] N79-31152 Active external store flutter suppression in the YF-17 flutter model A79-49866

B-iS

PARDINI, S. PERSONAL AUTHOR INDEX

PARDINI, S. PHILLIPS, J. W. Nultiradar tracking system using radial velocity All electric subsystems for next generation measurements transport aircraft 879-49608 [AIAA PAPER 79-1832] 879-47906 PARDON, R. J. L. PICHA D. G. The application of pulsed I G I band radio DutchI roll excitation and recovery techniques on altimeters to modern military aircraft c-141A Starlifter 879-49590 [AIAA PAPER 79-1801] 879-47886 PARENT, N. L. PINCKNET, N. L. Antennas for the Black Hawk helicopter Metal-matrix composite structures CABS 79-15] 879-49068 [ABS 79-34] A79-49086 PATE, D. P. PISKOT, N. G. Flight investigation of helicopter IFR approaches Current status of airport terminal complex to oil rigs using airborne weather and mapping development abroad radar A79-50240 [AHS 79-52] 879-49104 PITT, D. N. PATTON, J. N., JR. Advanced Scout Helicopter flying qualities The effects of configuration changes on spin and requirements - Bow realistic are they recovery characteristics of a low-wing general [ABS 79-28] 879-49080 aviation research airplane PLUNBLEE, H. E. (AIAA PAPER 79-1786] A79-47876 Duct noise radiation through a jet flow PAULSON, J. N., JR. A79-50110 Powered low-aspect-ratio Wing In Ground effect PLUNER, J. A. (WIG) aerodynamic characteristics The feasibility of inflight measurement of [NASA-TN-78793] N79-31141 lightning strike parameters PAYLECKA, V. H. [NASA-CR-158981] N79-30165 Air buoyant vehicles - Energy efficient aircraft PODVIDZ, G. L. [8188 PAPER 79-1862] 879-47919 On the influence of relative pitch in the subsonic PAVLOV, V. G. turbine cascade On a smooth approximation method and its A79-48503 application to mathematical description of wing POJETA, I. J. aerodynamic characteristics Determining the contour of helicopter rotor blades 879-47001 automatically using electro-optical techniques PEDEBSON, A. P. [Ails 79-32] 879-49084 A developmental computer model for investigations Computer-assisted high-speed balancing of T53 and of air traffic management problems: A case T55 power turbines investigating two decision strategies [AHS 79-36] 879-49088 [AD-A071075] 879-31189 POLIAKOV, A. N. PELLIAN, A. Use of the method of variable directions for Determining the contour of helicopter rotor blades numerical study of the temperature states of a automatically using electro-optical techniques turbine disk with blades [ABS 79-32] 879-49084 A79-48518 PERKINS, J. N. POLLARD, D. N. An actuator disk analysis of an isolated rotor Injuries in air transport emergency evacuations with distorted inflow A79-49995 [AD-A069884] 879-31216 PONSONBY, R. PERKINS, J. N. Critical assessment of emissions from aircraft Electric power system control techniques piston engines 879-48614 [AD-8071002] 879-30190 PESHATOY, G. D. POPE, N. L. Solution of the inverse aerodynamics problem by A novel technique for obtaining aerodynamic data the random search method using simple, free flight trajectory measurements A79-47002 A79-48051 PESTER, B. F. POPOV, K. N. Laboratory development of computer generated image Nozzles for vectored thrust jet engines displays for evaluation in terrain flight training A79-47428 [AD-A070065] N79-31236 POPOV, V. A. PETERS, D. A. Selection of geometric parameters and location of Theoretical flap-lag damping with various dynamic nose flap on swept wing root profile from tunnel inflow models test data. I [ABS 79-20] 879-49073 A79-46999 PETERSEN, K. L. PORTER, R. H. Flight control systems development of highly Automatic scanning inspection of composite maneuverable aircraft technology /H1BAT/ vehicle helicopter structure using an advanced [AIAA PAPER 79-1789] 879-47878 technology fluoroscopic system PETERSEN, I. J. [Ails 79-35] 879-49087 A computer system for identifying aircraft POSINGIES, N. N. characteristics Program for the critical components of a 879-50168 fly-by-tube backup flight control system, part 1 PETROVSKII, V. S. [80-8070387] 819-31226 Use of the method of variable directions for POST, P. N. numerical study of the temperature states of a Tactical electronic reconnaissance sensor turbine disk with blades 819-48717 A79-48518 POSTNIKOVA, N. G. PHELPS, A. Method of determining mechanical-impurity Contents An integrated analytical and experimental in jet fuels investigation of helicopter hub drag 879-48859 [ABS 79-5] 879-49058 POTONIDES, H. C. PHELPS, A. N., III Performance of a V/STOL tilt nacelle inlet with Wind-tunnel investigation of an armed mini blowing boundary layer control remotely piloted vehicle (8188 PAPER 79-1163) 879-41347 [NASA-TN-80132] 879-31151 PNANSPILL, G. 0. PHILLIPS, J. D. Role of Numerical Control Design in the computer Flight investigation of helicopter IFR approaches aided design/manufacturing interface at Sikorsky to oil rigs using airborne weather and mapping [ABS 79-30) 879-49082 radar PRASAD, N. A. (ABS 79-52] A79-49104 A simulation of amphibious hovercraft overturning A79-49904

B-i 6

PERSONAL AUTHOR INDEX RYBICKI, R. C.

PENS SLER, G. J. RESHOTKO, B. Tapered roller bearing development for aircraft Drag reduction by cooling in hydrogen-fueled turbine engines aircraft [AD-A069440] 879-30555 079-49921 PRINCE, S. V. BET, J. A. A flow field study for top mounted inlets on Computer Monitor and Control - A flexible, fighter aircraft configurations cost-effective implementation [AD-A069732) 879-30151 A19-48670 PRIOR, J. R. RICHARD, N. Performance of current radar systems in an EN A program to compute three-dimensional subsonic environment unsteady aerodynamic characteristics using the A79- 49 555 doublet lattice method, 0216 (DUBFLBX) . Volume PROKUDIN, V. N. 2: Supplemental system design and maintenance The tendency of jet fuels to form deposits on a document heated surface [NASA-CE-2850] 879-31148 A79-48856 ROBINS, A. V. PIJGLIESE, A. J. High-performance wings with significant Flight testing the circulation control wing leading-edge thrust at supersonic speeds (AIAA PAPER 79-1791] A79-47880 [AIAA PAPER 79-1871] 119-117924 PURTELL, L. P. ROBINSON, N. R. A low-velocity airflow calibration and research From HiMAT to future fighters facility (lIlA PAPER 79-1816) A79-47896 (P8-294501/2) 879-31237 ROBINSON, P. The development and in-flight evaluation of a triplex digital antostabilization system for a R helicopter RADFORD, N. F. N79-30200 A new three-dimensional surveillance radar ROBINSON, S. B. A79-49568 Performance of a pulse-decode circuit in the BANACHANDEA, S. N. presence of interference Some early experiments in the development of a A79-'48713 flying platform for aerodynamic testing ROCHE, J. N. A79-47535 Avionics design for testability - An aircraft RANAGE, contractors viewpoint Design considerations for reliable FEW flight 179-48888 control - ROGERS, S. P. 879-30231 Meeting the challenge of precise navigation during RANSOEN, J. N. nap-of-the-earth flight Lusaka accident report (ABS 79-12] A79-49065 A79-50109 RON, J. RAPSON, J. E. The calculation of non-linear aerodynamic Hovercraft skirt design requirements characteristics of wings and their wakes in A79-49907 subsonic flow RATCLIFFE, H. I. A79-47099 Flight experiments to evaluate the effect of BONERO, N. wing-tip sails on fuel consumption and handling Previsions and experimental results in open characteristics balloon controlled descent A79-49818 N79-31691 RAWLINGS, K., III ROSE, R. Dynamic test techniques - Concepts and practices Rotary balance data for a typical single-engine A79-50164 general aviation design for an angle-of-attack RAT, J. U. range of 8 deg to 90 deg. 2: High-wing model A Operation and test of composite horizontal [NASA-CR-3101] 879-311119 stabilizer for the Sikorsky Spirit helicopter ROSENDE, A., JR. (ABS 79-115] 179-49097 An improved method for load survey flight testing RATNEN, U. P. (AIAA PAPER 79-1799) A79-47885 Manned strategic system concepts 1990-2000 ROSS, A. J. (AIAA PAPER 79-1793] 179-147882 Lateral stability at high angles of attack, REBEL, J. N. particularly wing rock The T & 8 simulator - A comparison with flight N79-30226 test results ROTH, C. N. A79-50169 A computer system for identifying aircraft REDDY, D. 3. characteristics Qualification program of the composite main rotor A79-50168 blade for the Model 214E helicopter ROTNAN, I. (ABS 79-44) 179-49096 Analysis of optimal loop and split-S by energy REED, D. state modeling Evaluation of pylon focusing for reduced A79-47098 helicopter vibration ROUGERON, N. (AD-A069712) 879-30196 Previsions and experimental results in open REID, J. G. balloon controlled descent Estimation of aircraft target motion using pattern N79-31691 recognition orientation measurements RUBE!, R. J. A79-47987 The effect of standardization of avionics software REID, 0. quality assurance Aerodynamic performance of axial-flow fan stage A79-48648 operated at nine inlet guide vane angles RUBIN, J. [NASA-TP-1510] 879-31214 Distributed TUNA - An approach to JTIDS phase II REILLY, N. J. A79-49584 Development of crashworthy passenger seats for RUMBLER , U. R. general-aviation aircraft Mechanical and therrnophysical properties of (NASA-CR-159100] 879-31164 graphite/polyimide composite materials BEIQUAN, E. I. N79-30317 Electrical power system for new-technology RUSSO, U. N. transport power-by-wire airplane Recent advances in materials toxicology 179-48616 1179-31169 RYBICKI B. C. The Sikorsky elastomeric rotor [AHS 79-48] 179-49100

B-17 RYNASKI, B. G. PERSONAL AUTHOR INDEX

RTNASKI, B. G. SCHUSTER, S. H. The enhancement of aircraft parameter Fuel tank survivability for hydrodynamic ram identification using linear transformations induced by high velocity fragments. Part 2: A79-47961 Numerical analyses [AD-A070128] 979-31200 SCHWARTZNAN, L. S A report on the Sperry Dome Radar SACHS, G. A79-49567 Stall behaviour evaluation from flight test results SCR!, A. A. N79-30227 Nonlinear decoupled control synthesis for SAINT HILAXRE, A. 0. maneuvering aircraft The influence of sweep on the aerodynamic loading A79-47959 of an oscillating NACA 0012 airfoil A multiple objective optimization approach to [ASS 79-4] 879-49057 aircraft control systems design SAJAN, S. A79-47962 Application of singular perturbation techniques SEAT, J. C. /SPT/ and continuation methods for on-lime A microprocessor system for flight control research aircraft trajectory optimization A79-48623 879-47991 SEETHAEAN, H. C. A study of the application of singular Aerodynamics of spoiler control devices perturbation theory [AIAA PAPER 79-1873] A79-47925 [RASA-CR-3167] N79-30194 SEINER, 3. N. SALNIKOVA, N. V. Experiments of shock associated noise of Hethod of determining mechanical-impurity contents supersonic jets in jet fuels [AIAA PAPER 79-1526] A79-47341 A79-48859 SBLEZOV, I. T. SANANT, V. S. A method of the theory of airfoil profiles with a Low cost inertial aiding for RAVSTAR/GPS receivers jet flap in naval ship navigation A79-47119 879-48656 SENS, U. H. SAMUEL, N. A. Aircraft engine developments centre on improved ATLAS, an integrated structural analysis and performance, higher efficiency design system. Volume 5: System demonstration A79-50207 problems SEREDINSKY, V. [NASA-CR-159045] N79-31624 Design of the circulation control wing STOL SANDERS, D. C. demonstrator aircraft Electrical insulation fire characteristics. [AIAA PAPER 79-1842] A79-47909 Volume 2: Toxicity SEREGIN, B. P. [P0-294841/2] N79-30490 The tendency of jet fuels to form deposits on a SATTLER, D. H. heated surface User requirements for future combat search and A79-48856 rescue vehicles SERRANO, A. V. A79-48683 Atmospheric Electricity Hazard (AER) SATIN, L. N. [AD-A069338] N79-30169 Changes in the quality of 2-6 fuel upon prolonged SETLER, D. P. storage Investigation of inverse Vandermonde matrix A79-48858 calculation for linear system applications SATLOR, F. C. [AD-A069241) N79-31225 Complex guaternion notation in coordinate SHAH, B. N. transformations Simplified analysis spectrum for joints exposed to A79-48681 complex continuously varying stresses SCHLOTHAUER, J. [AIAA PAPER 79-1808] A79-47892 The influence of the environment on the SHAH, N. elastoplastic properties of adhesives in metal Improvement of fighter aircraft maneuverability bonded joints through employment of control configured vehicle [ESA-TT-521] N79-30391 technology SCHNIDT, D. J. N79-30225 Quaternion matching in transfer alignment for SAR SHAPIRO, B. V. motion compensation Analytic redundancy for flight control sensors on 879-48641 the Lockheed L-1011 aircraft SCHNIBT, V. A79-47960 Subsonic and transonic flows on a variable sweep SHEPPARD, C. H. wing Development and demonstration of manufacturing (ONERA, TP NO. 1979-102] 879-48849 processes for fabricating graphite/PER-is Aerodynamic interaction on a close-coupled polyimide structural elements canard-wing configuration N79-30301 [ONERA, TP NO. 1979-95] 879-49543 SHERIDAN, P. F. SCHRAGE, D. P. Interactional aerodynamics - A new challenge to Dynamics requirements for an Advanced Scout helicopter technology Helicopter /ASH/ [ASS 79-59] 879-49109 (ASS 79-19] 879-49072 SHESTERNINA, B. N. SCHROEDER, N. Harmonic oscillations of annular wing in steady Theoretical estimation of nonlinear longitudinal ideal fluid flow characteristics of wings with small and moderate A79-47009 aspect ratio by the vortex-lattice method in SHINAE, J. incompressible flow Analysis of optimal loop and split-S by energy (DLR-PR-78-26] N79-30161 state modeling SCHROERS, I. C. A79-47098 Wind tunnel and flight test of the IT-is Tilt SHISHKOV, I. N. Rotor Research Aircraft Fuels, lubricants and other fluids used in aviation [ASS 79514] A79-49105 A79-47433 SCHULZ, C. SHORT, J. J. Investigations on the design of active vibration An evaluation of the bird aircraft strike hazard isolation systems for helicopters with rigid and at Hill APR, Utah (APLC) elastic modeling of the fuselage [AD-A070459] N79-31184 [DLR-FB-78-04] N79-30183

B-la

PERSONAL AUTHOR INDEX STEVENS, A. D.

SHVARTSMAN, P. I. SOLOMON, R. U. Experimental study of the gasdynamic Flight test verification of the ASSET system characteristics of a stator cascade with cooling A79-48622 air discharge through the vane surface SPEARMAN, N. L. A79-48498 Historiáal development of worldwide supersonic SILVERMAN, S. M. aircraft From HiMAT to future fighters AIAA PAPER 79-1815] A79-47895 [AIAA PAPER 79-18163 A79-47896 SPENCER, U. J. SIMPERS, B. F. A real time video bandwidth reduction system based - Metallic coatings for graphite/epoxy composites on a CCD Nadamard transform device [AD-A069871] 879-30334 A79-48702 SINGB, S. N. SPIER, E. E. Nonlinear decoupled control synthesis for Ultra-high-modulus graphite-epoxy conical shell maneuvering aircraft development, supplement A79-47959 [AD-A069795] . 879-30335 SINHA, A. N. SPILLMAB, J. J. Runway configuration management system concepts Flight experiments to evaluate the effect of [AD-A069960] 879-31234 wing-tip sails on fuel consumption and handling SIRAZETDINOV, T. K. characteristics Analysis design of complex systems. II A79-49818 A79-48505 SPIRIDONOV, ID. A. Influence of gas turbine engine combustion chamber SKINNER, G. L. AH-1G helicopter, 19-round lightweight airborne geometric parameters on mixture formation launcher jettison envelope determination characteristics A79-48495 [AD-A069828] 879-30177 SKUPIN, N. SPRINGER, B. Investigation on information error caused by Hultipath propagation measurement by Doppler traffic loading in approach and landing systems technique 879-31480 819-31478 SLAVKIN, B. G. SRIRAMULU, V. The impact of software in automatic test equipment Factors controlling stability of swirling flames A79-48691 at diffusers in gas turbines SLIWA, S. N. A79-50209 Some flight data extraction techniques used on a STADMOBE, H. A. general aviation spin research aircraft Radar cross section fundamentals for the aircraft [AIAA PAPER 79-18023 A79-47887 designer SLUSHER, G. R. [AIBA PAPER 79-1818] A79-47898 Exhaust emission traverse investigation of a STAEBLEB, C. 3., JR. Metallic coatings for graphite/epoxy composites .iT3D-1 turbofan engine 879-303311 [AD-A072019] N79-31209 [AD-A069871] SMITH, D. STALE!, J. A. Analysis of plume rise from jet aircraft Full scale ground and air resonance testing of the [CONP-790142-1] 879-31204 Army-Boeing Vertol Bearingless Main Rotor A79-49075 SMITH, J. N. [ABS 79-23] Analysis of a lateral pilot-induced oscillation STALONT-DOBRZANSKI, J. experienced on the first flight of the YF-16 Improvement of fighter aircraft maneuverability aircraft through employment of control configured vehicle (NASA-TN-72867] N79-31220 technology W79-30225 SMITH, L. N. Actively cooled plate fin sandwich structural STAVE, I. P. panels for hypersonic aircraft Automatic test software for calibrating strapdown [NASA-CE-3159] 879-31628 systems A79-48689 SMITH, N. L. Aerodynamics for engineers STEER, U. J. A79-50375 Airborne microwave ECM A79-49554 SMITH, R. B. Airworthiness and flight characteristics test, STEIN, G. OV-1C takeoff performance Digital adaptive control laws for VTOL aircraft [AD-A069827] 879-30178 A79-48000 SMITH, H. P. STEINHAUSER, H. Interactional aerodynamics - A new challenge to An in-flight controller insensitive to parameters helicopter technology variation [ABS 79-59] A79-49109 [DLR-FB-78-07] 879-30197 SMITH, S. B. STENGEL, R. F. An evaluation of sidestick force/deflection A microprocessor system for flight control research characteristics on aircraft handling qualities A79-48623 A79-50428 NASA/Princeton digital avionics flight test facility P.79-49344 SMYTH, S. .3_ cADAN data handling from conceptual design through STENNETT, S. N. produce support Test implementation through support software - A [AIAA PAPER 79-18463 A79-47912 FIT translator A79-48687 SNELLING, K. S. Some aspects of the design and development of the STERLIN, V. A. maritime autopilot modes for the Westland Lynx Selection of geometric parameters and location of helicopter nose flap on swept wing root profile from tunnel N79-30201 test data. I P.79-46999 SODERQUIST, J. R. Certification of composites in civil aircraft STEREFELD, B., JR. [ABS 79-43] A79-49095 Study of design constraints on helicopter noise 879-32054 SOBDER, B. H. [NASA-CR-159118] Effect of steady-state temperature distortion and STEVENS, A. U. combined distortion on inlet flow to a turbofan A new three-dimensional surveillance radar P.79-49568 engine [NASA-TN-79237] 879-30187 SOKOLOV, V. U. Nozzles for vectored thrust jet engines A79-47428

B-19 STEVENS, B. S. PERSONAL AUTHOR INDEX

STEVENS, B. S. SNORTZEL, F. B. Aerodynamic and acoustic investigation of inverted Design guidance from fighter CCV flight evaluations velocity profile coannular exhaust nozzle models N79-30235 and development of . aerodynamic and acoustic. SYNONDS, N. A. prediction procedures, comprehensive data Development and demonstration of manufacturing report, volume 1 processes for fabricating graphite/PMR-15 [NASA-CR-159515) N79-30185 polyimide structural elements Aerodynamic and acoustic investigation of inverted N79-30301 velocity profile coannular exhaust nozzle models SZELAZEK, C. A. and development of aerodynamic and acoustic Upper-surface modifications for C sub 1 max prediction procedures, comprehensive data improvement of selected NASA 6-series airfoils report, volume 2 (NASA-TM-78603] N79-30143 [NASA-CB-159516] N79-30186 Aerodynamic and acoustic investigation of inverted velocity profile coannular exhaust nozzle models II and development of aerodynamic and acoustic TABAK, D. prediction procedures A multiple objective optimization approach to [NASA-CR-3168] B79-31212 aircraft control systems design STEWARD, C. N. A79-47962 A helicopter high definition rotor blade radar TALANTOV, A. V. N79-30207 Influence of gas turbine engine combustion chamber STEWART, A. A. geometric parameters on mixture formation E-4B mission electrical power characteristics A79-48617 A79-48495 STEWAET, V. B. TALYZIN, V. A. The characteristics of a lift cruise fan V/STOL Optimal thermogasdynamic design of gas turbine configuration in near proximity to a small deck engines using element prototypes. I with finite edge positions 979-46997 [AIAA PAPER 79-1854) 979-47913 TANNER, A. B. STOCKING, N. B. Development of crashworthy passenger seats for Iceater I - Air cushion ice breaker in commercial general-aviation aircraft operations (NASA-CR-159100) 579-31164 979-49912 TATE, B. P. STOCKMAN, N. 0. A users manual for a computer program to generate Recent applications of theoretical analysis to fatigue spectrum loading sequences V/STOL inlet design [AD-A069288] 579-31198 A79-49530 TAVGER, N. D. STOUGH, H. P., III On the question of selecting the characteristic The effects of configuration changes on spin and quantity governing fuel self-ignition in a stream recovery characteristics of a low-wing general 979-48497 aviation research airplane TAYLOR, B. L. [AIAA PAPER 79-17861 A79-117876 Crashworthy armored crewseat for the UH-60A Black STRIZ, A. G. Hawk Flutter analysis of two-dimensional and [985 79-10] A79-49062 two-degree-of-freedom airfoils in THEISEN, J. G. small-disturbance, unsteady transonic flow Laminar flow stabilization by surface cooling on [AD-A069223] N79-31157 hydrogen fueled aircraft STRUNKIN, V. A. [AIAA PAPER 79-1863] 979-47920 Gas turbines for flight vehicle engines: Theory, THOMAS, J. L. design, and calculation /Third review and Powered low-aspect-ratio Wing In Ground effect enlarged edition/ (WIG) aerodynamic characteristics A79-50421 [NASA-TB-78793] 579-31141 STUART, J. N. Theoretical and experimental investigation of Global enclosure fire modeling with applications ground-induced effects for a low-aspect-ratio N79-31172 highly swept arrow-wing configuration Fuselage ventilation under wind conditions (NASA-TP-1508] 579-31223 N79-31175 THOMPSON, H. K. STUCKENBERG, N. Computer Monitor and Control - A flexible, Failure detection in signal processing and sensing cost-effective implementation in flight control systems A79-48670 A79-47971 THOMPSON, S. G. STURGEON, N. R. Identifying desirable design features for the C-TX Flight investigation of helicopter IFR approaches aircraft - A systems approach to oil rigs using airborne weather and mapping [AIAA PAPER 79-1796] A79-47883 radar THOR, N. A. (AHS 79-52) A79-49104 An investigation of the rolling stability SULLIVAN, J. P. derivatives of a I-tail fighter configuration at LDV measurements on propellers high angles-of-attack A79-49052 A79-50165 SULLIVAN, N. I. THORNTON, E. A. The size and performance effects of high lift Evaluation of finite element formulations for system technology on a modern twin engine jet transient conduction forced-convection analysis transport A79-49343 [AIAA PAPER 79-1795] A79-49332 TIETZ, D. E. SUNMA, J. N. Microprocessor-based digital autopilot development A lifting-surface method for hover/climb airloads for the XBQN-106 Mini-RPV [AHS 79-3] 979-49056 A79-48608 SUPKIS, D. TIRRE, J. C. Status of candidate materials for full-scale tests Adding the challenge of nap-of-the-earth in the 737 fuselage N79-30199 N79-31170 TOCKERT, C. SVARD, L. Previsions and experimental results in open Ellipsoidal modelling of aircraft targets for balloon controlled descent evaluation of electronic fuzes 579-31691 A79-49580 TOMASI, d.-P. SWEENEY, D. A. The servoed modulation FMCW radar altimeters in Adaptive array tradeoffs for existing airborne UHF military applications radios A79-49589 A79-48598

8-20

PERSONAL AUTHOR INDEX WATTS, J. C.

TOPPING, A. D. VEPA, N. Maritime patrol airship concept study Comment on 'active flutter control using N79-31138 generalized unsteady aerodynamic theory' [AD-A070131] A79-49873 TORN ALLTAT, A. Time history solution program. L225 (1EV126). VERGEZ, P. L. Volume 2: Supplemental system design and Investigation of roll performance foi a highly maintenance document nonlinear statically unstable fighter-type (NASA-CE-2860] N79-31154 aircraft [AD-A069301] N79-31199 TRAIN, D. A combined air-cushion and endless belt VICKERT, G. L. transportation system P-16 avionics maintenance concept and A79-49911 multinational aspects A79-48894 TRENILLS. J. A. Performance predictions for open ocean air cushion VOGT, C. L. vehicles and surface effect ships The ATCBI-5 beacon interrogator A79-49905 A79-48693 TREPT, T. .3., JR. VON GLARE, U. Helicopter performance methodology at Bell Wing aerodynamic loading caused by let-induced lift associatedwith STOL-OTW configurations Helicopter Textron *79-47346 [ABS 79-21 A79-49055 [AIAA PAPER 79-1664] TREILER, C. A. VORTNEIER, P. W. Characterization of a swept-strut hydrogen Multiband antenna fuel-injector for scramjet applications A79-48596 *79-49345 VOSKRESENSKII, C, P. TROESCH, A. Numericalsolution of the problem of unsteady Predictive guidance for interceptors with time supersonic flow around the front part of the delays wings with a detached shock wave *79-47939 A79-49456 TRUBAN, A. P. VOSWINCKEL, V. Application of instrument rotation in the N73 Scan converter and raster display controller for standard inertial navigation system night vision display systems *79-48696 N79-30203 TRUSTEE. B. VOTE, P.N. Helicopter drive system N and N design guide Millimeter airborne radar target detection and N79-30181 selection techniques [AD-A069691] A79-48665 TURNER, C. B. Analysis and evaluation of current MIL-SID-1553 digital avionics architecture as the basis for advanced architectures using NIL-STD-1553B LTITA *79-48629 WAGNER, J. P., III Combined environment reliability test of the TURNER, P. Achieving consistency in the production of common strategic Doppler system critical jet engine components by means of press *79-50368 forging WALKER. G. I. *79-48945 New versus existing engines for new helicopter TWONE!, W. J. systems - A life cycle cost view The influence of engine/fuel control design on [*IAA PAPER 79-1316] A79-47348 helicopter dynamics and handling qualities WALKER, H. J. [ABS 79-37] *79-49089 Performance evaluation method for dissimilar aircraft designs [NASA-BP-1042] 1179-30139 U WALKER. .3. E. The evolution of the high-angle-of-attack features BLDG, N. N. A novel approach to the design of an all digital of the P-16 flight control system aeronautical satellite communication system A79-50938 W79-31461 WALSH, N. J. Tactical performance characterization basic UNDERWOOD, H. N. Operational experience with the AN/ARN-131 Omega methodology 1179-31235 Navigation Set [*D-A069297] A79-48676 WALTER, T. J. Computer-assisted high-speed balancing of T53 and UPADH!A!, T. N. * real-time sequential filtering algorithm for OPS T55 power turbines low-dynamics navigation system [AilS 79-36] *79-49088 A79-48657 WARD, P. S. BRIE, D. N. Recent advances in radome design L-1011 active controls, design philosophy and A79-49574 experience WASHAN, R. N. N79-30236 Correlation technique for ambient effects on oxides of nitrogen *79-99922 OTA WASHBURN, S. B. VALCKENAERE, N. Application of singular perturbation techniques Design of the circulation control wing STOL /SPT/ and continuation methods for on-line aircraft trajectory optimization demonstrator aircraft *79-47991 [AIAA PAPER 79-18421 *79-47909 VANDERVAANT, J. C. A study of the application of singular Aircraft response to windshears and downdraughts perturbation theory N79-30229 [NASA-CR-3167] N79-30194 VANGOOL, N. F. C. WATERS, D. N. P. simulator investigation of handling quality A simulation of amphibious hovercraft overturning criteria for CCV transport aircraft *79-49904 N79-30240 WATSON, .3. H. Enhanced fighter mission effectiveness by use of VAUCHERET, X. Wall corrections in transonic wind tunnel: integrated flight systems N79-30223 Equivalent porosity N79-30247 WATTS, J. C. [ESA-TT-545] Airworthiness and flight characteristics test, OV-1C takeoff performance [AD-A069827] N79-30178

8-21 VERNE, H. PERSONAL AUTHOR INDEX

WEBER, H. VOLPE, B. A. The fluorenone polyester ISO PPE of Isovolta Dynamics requirements for an Advanced Scout Company, Austria Helicopter /ASH/ U79-31183 [ABS 79-19] A79-49072 WEBER, U. B. WOLOWICZ, C. H. Testability, the key to economical and Similitude requirements and scaling relationships operationally effective avionic test software as applied to model testing A79-48890 [NASA-TP-1435) R79-30176 WEIBEEG, J. A. WOOD, N. E. Wind tunnel and flight test of the xv-15 Tilt All electric subsystems for next generation Rotor Research Aircraft transport aircraft (ABS 79-54] A79-49105 [AIAA PAPER 79-1832] A79-47906 WEIDREB, J. P. WOODWARD, A. C. Conceptual study of a turbojet/ramjet inlet Terrain-following radar - Key to low-altitude flight (NASA-TN-80141) 879-31215 A79-48686 WELT, S. WOODWARD, N. Dynamic simulator test and evaluation of a JTIDS Performance of current radar systems in an EW relative navigation system environment A79-48694 A79-49555 WERNICKE, K. G. WORMLEY, D. N. xV-15 flight test results compared with design goals Characteristics of an Air Cushion Landing System [AIAA PAPER 79-1839] A79-49336 incorporating an inelastic trunk WHEELOCK, C. U. A79-49909 Air Force modular automatic test equipment Heave-pitch-roll analysis and testing of air development program cushion landing systems A79-48878 [NASA-cR-2917] N79-30175 WHITE, F. WORSHAN, J. B. Improved method of predicting helicopter control Derivative engines for the 1980s will help limit response and gust sensitivity acquisition and maintenance costs (ABS 79-25] A79-49077 A79-50206 WHITE, V. F. WRIGHT, C. P. Flight performance of the TCV B-737 airplane at Spirit helicopter handling qualities design and Kennedy Airport using TRSB/MLS guidance development [NASA7TN-80148] 879-31186 (ABS 79-24] A79-49076 WICKENDEN, B. V. A. WUENNENBRBG, H. Recent advances in radome design Stall behaviour evaluation from flight test results A79-49574 VIEDERSUM, C. N. N79-30227 Study of design constraints on helicopter noise (NASA-CR-159118] 879-32054 WIETING, A. R. YAlE, D. Evaluation of finite element formulations for Analysis of optimal loop and split-S by energy transient conduction forced-convection analysis state modeling A79-49343 A79-47098 WILCOX, R. E. YAMAKAWA, G. N. The alpha-beta-gamma tracking filter in the Z-domain Airworthiness and flight characteristics test, A79-48680 OV-1C takeoff performance VILER, C. D. [AD-A069827) 879-30178 Manned strategic system concepts 1990-2000 TAMARTINO, R. .3. [AIAA PAPER 79-1793] A79-47882 Analysis of plume rise from jet aircraft WILKERSON, J. B. [cONF-790142-1) N79-31204 The circulation control rotor flight demonstrator YANG, V. I. test program Flutter analysis of two-dimensional and [ABS 79-51] A79-49103 two-degree-of-freedom airfoils in WILLIAMS, C. D. small-disturbance, unsteady transonic flow Verification of operational flight programs by [AD-A069223] N79-31157 simulation - YEAGER, W. T., .38. A79-48667 Analytical and experimental investigation of WILLIAMS, B. C. V-type empennage contribution to directional Performance of a V/STOL tilt nacelle inlet with control in hover and forward flight blowing boundary layer control [ABS 79-56] A79-49106 [AIAA PAPER 79-1163] A79-47347 100, J. K. WILLIS, E. A. Preprocessing for advanced image matching techniques An overview of NASA research on positive A79-48602 displacement type general aviation engines YBASEK, D. C. [NASA-TN-79254] 879-31210 Performance of two-stage fan with a first-stage WILLIS, V. S. rotor redesigned to account for the presence of QCSEE - The key to future short-haul air transport a part-span damper A79-50208 [NASA-TP-1483] 879-30191 WILSON, C. F., JR. Radio-controlled model design and testing techniques for stall/spin evaluation of general-aviation aircraft ZELASCO, C. L. [NASA-TM-80510] 879-30173 B-X combat search and rescue avionics study results WINGEOVE, B. C. A79-48684 Estimation of longitudinal aircraft ZEtJLDYBIN, E. N. characteristics using parameter identification Method of determining mechanical-impurity contents techniques in jet fuels A79-50432 A79-48859 WITHERS, C. C. ZIMINA-, I. I. Evaluation of selected class III requirements of Method of determining mechanical-impurity contents MIL-F-8785B /ASG/, Flying Qualities of Piloted in jet fuels Airplanes' A79-48859 A79-50439 ZOMICK,' D. A. WITHUAN, R. L. The DG-800 - A rugged, high performance heading An analysis of SAPPHIRE image parameters as a reference unit function of processing parameters A79-48677 A79-48666

B-22 PERSONAL AUTHOR INDEX ZURBEIDEI D.

ZOBEA, C. R. The calculation of non-linear aerodynamic characteristics of wings and their wakes in subsonic flow A79-47099 ZRELOV, V. N. Method of determining mechanical-impurity contents in jet fuels A79-48859 ZURHEIDEN, D. A self contained collision avoidance system for helicopters 1179-30206

B-23 CONTRACT NUMBER INDEX

AERONAUTICAL ENGI NEE RING/ A Continuing Bibliography (Suppl. 116) DECEMBER 1979

Typical Contract Number Index Listing F33615-78—C-0122 P62269-713—C-0003 579-47883 879-31226 F33615-78—C-1430 N62269-78—C-0176 N79-30195 NAS2-9460 7910038 A79-48657 F33615-78—C-1563 862269-78-11-6956 A79-48695 1179-31138 SF54502001 1179-30332 CONTRACT I NASA ACCESSIONI F33615-78—C-2018 NUMBER NUMBER ] A79-48614 w-31-109—ENG-38 F33616-78—C-1576 R79-31204 A79-48610 WF41400000 1179-30195 505-02-24 1179-31193 F33657-74—C-0604 Listings in this index are arranged alphanumerically by contract number, A79-48666 505-04 879-30191 Under each contract number, the accession numbers denoting documents F44620-76—C-0055 N79-31213 that have been produced as a result of research done under that contract N79-31216 1179-312114 /AA accession numbers appearing F49620-77—C-0023 505-05-41 1179-31195 are arranged in ascending order with the 505-06-34 879-30176 first. The accession number denotes the number by which the citation is N79-31217 F41421000 879-30151 505-06-53-01 879-30147 identified in either the fAA or STARsection. 11DA903-78—C-0176 505-06-53-03 879-31533 N79-30141 505-06-64 879-31220 NASW-3198 879-31206 505-10-13-07 879-301115 SF PROJ. 2104 DAAK51-78—0001 1 A79-49074 NASW-3199 879-31136 879-311119 879-30246 879-31163 1179-31152 SF PROJ. 2202 DISC 1 9-77—C-0 006 879-31236 879-31230 505-10-23-05 879-31151 879-30169 579-49909 505-11-24 1179-30139 1179-31201 DI—BM—H0133024 NAS1-12403 N79-31237 879-30175 505-11-33-01 879-31215 SF PROJ. 2307 NAS1-12911 879-31624 517-53-43-02 879-31223 879-31157 DOT—F5T0679 A79-49604 879-31137 DOT—FA72WA2801 NAs1-13382 879-31628 518-51-01 SF PROJ. 2402 791-40-19 879-30138 879-31200 A79-48692 8551-13918 879-31144 DOT—F572851242 879-31145 879-31202 H79-31147 SF PROJ. 2403 A79-49604 DO P—F 57 48 5— 1102 N79-31148 1179-31227 879-31153 SF PROJ. 2404 1179-30190 879-30 148 DOT—PA74WAI-423 879-31154 879-30149 N79-31233 879-31155 879-31203 DOT—F177W 1-3955 NAS1-14637 879-31164 N79-30959 NAS1-14742 179-49332 SF PROJ. 30118 879-31221 879-30555 879-30960 NAS1-14789 DOT—PA79W54184 14AS1-14849 879-30145 1179-31218 879-31149 SF PROJ. 7184 879-31234 N79-30184 DOT/TSC—RA7715 1179-31152 N79-304,90 NSS1-14892 879-31533 AF—APOsR-7121 45 579-118000 A79-47099 DOT/TSCRA-77-16 NAS1-1 14921 879-30301 AF—APOSR-74-2712 N79-30490 NAS1-15009 A79-47093 EY-76—0040789 8551-15113 179-47991 1179-30194 SF—A P058-352 3-78 879-30182 879-31157 FAA PROJ. 082-431-02 NAS1-15216 1179-30165 Dl PROJ. 1L1-61102—A1145 N79-31233 NAS1-15226, 879-32054 N79-31151 FAA PROJ. 201-521-100 NAS2-8700 879-31354 Dl PROJ. 1L2-62209—AH-76 879-31209 NAS2-9143 879-30138 879-30179 879-31211 IIAS2-9331 879-31195 N79-30180 F4701-77—C-0078 NAS2-93 114 879-31222 1179-30181 A79-47939 81S2-10097 179-49339 879-30196 F04701-76—C-0002 NAS3-19736 879-31207 Dl PROJ. 181-62113-5-661 A79-48603 14553-20061 879-30185 F04701-78-0181 879-30186 879-30335 1179-31212 DR PROJ. 2Q7-53143—A-772 A79-48657 N79-31236 F19628-78—C-002 14553-20646 879-30189 NAS4-2542 1179-31193 DAAB0777—C2176 A79-49604 17,9-48597 P29601-76—C-0015 14558-20630 879-31208 NGL— 05-020-243 D1AB0778A6606 N79-30246 879-31205 P33601-78-0-0042 A79-47093 NGL— 22-009-124 Dl AG 29-7 7—G — 0034 N79-30169 A79-49718 F33615-75—C-3105 N79-30193 DAAG29-77—G0205 N79-31201 808-47-003-052 879-31482 F33615-76—C2019 N79-31143 NSF GK-42133 179-47926 0A1G29-78G 0149 879-30555 579-49718 F33615-76—C-3116 t4SG-1321 579-49343 N79-31197 NSG-7072 179-49866 05AG467 5—C-0072 179-119867 879-31624 N79-31196 14SG-7373 U00014-76—C-0710 D55G4676C-0008 P33615-77—C-0115 N79-30335 A79-47882 579-47957 DSAJ 02-76—C-0047 P33615-77—C-0536 N00014-76—C-0780 879-30180 1479-30184 A79-47943 N79-30181 F33615-77C2082 N00014-77—C-0180 879-30140 OS 53 02-7 6 — C— 0069 879-31200 579-119056 1479-31202 v00014-78—C-0257 A79-48623 0113 02-77—C-0034 F33615-77—C-3062 N79-30148 N00019-77—C-0250 879-30196 N79-30334 Dl 53 02-7 7— C— 0049 N79-30149 N79-30179 F33615-77C3079 N62269-75—0O210 A79-49605 D55840-77 — 001 07 879-31227 A79-48602 F33615-773109 N62269-76—C-0105 A79-49584 D55850-7 8—C-0008 A79-47890 579-49084 F33615-78—C-0011 N62269-77—C-0138 1479-31235 A79-48596

C—i

I . Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037_(116) 4. Title and Subtitle 5. Report Date AERONAUTICAL ENGINEERING December 1979 A Continuing Bibliography (Supplement 116) 6. Performing Organization Code

7. Author(s) 8. Performing Organization Report No.

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

11. Contract or Grant No. National Aeronautics and Space Administration Washington, D. C. 205146 ______13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address

14. Sponsoring Agency Code

15. Supplementary Notes

16, Abstract

This bibliography lists 550 reports, articles, and other documents introduced into the NASA scientific and technical information system in November 1979.

17. Key Words (Suggested by Author(s)) 18. Distribution Statement Aerodynamics Aeronautical Engineering Unclassified — Unlimited Aeronautics Bibliographies

19. Security Classif. (of this report) r20. Security Classif. (of this page) 21. No. of Pages 22. Price* E02 Unclassified Unclassified $14.75 HC

For sale by the National Technical Information Service, Springfield, Virginia 22161

NASA-Langley, 1980 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC NASA distributes its technical documents and bibliographic tools to ten special libraries located in the organizations listed below. Each library is prepared to furnish the public such services as reference assistance interlibrary loans, photocopy service, and assistance in obtaining copies of NASA documents for retention. CALIFORNIA MASSACHUSETTS University of California. Berkeley Massachusetts Institute of Technology. Cambridge COLORADO MISSOURI University of Colorado. Boulder Linda Hall Library, Kansas City DISTRICT OF COLUMBIA NEW YORK Library of Congress Columbia University, New York GEORGIA PENNSYLVANIA Georgia Institute of Technology. Atlanta Carnegie Library of Pittsburgh ILLINOIS WASHINGTON The John Crerar Library. Chicago University of Washington. Seattle

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NASA CONTINUING BIBLIOGRAPHY SERIES

NUMBER TITLE FREQUENCY

NASA SP-7011 AEROSPACE MEDICINE AND BIOLOGY Monthly Aviation medicine, space medicine, and space biology NASA SP-7037 AERONAUTICAL ENGINEERING Monthly Engineering, design, and operation of aircraft and aircraft components NASA SP-7039 NASA PATENT ABSTRACTS BIBLIOGRAPHY Semiannually NASA patents and applications for patent NASA SP-7041 EARTH RESOURCES Quarterly Remote sensing of earth resources by aircraft and spacecraft NASA SP-7043 ENERGY Quarterly Energy sources, solar energy, energy conversion, transport, and storage

NASA SP-7500 MANAGEMENT Annually Program, contract, and personnel management, and management techniques

Details on the 'availability of these publications may be obtained from: SCIENTIFIC AND TECHNICAL INFORMATION OFFICE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Washington, D.C. 20546