Aeronautical NASA SP-7037(151) Engineering August 1982 A Continuing NASA Bibliography with Indexes

National Aeronautics and Space Administration

Engineering m P%Vta^ (NASA-SP-7v>37 (151) ) AERONAUTICAL N8J-10U01 j^j^^l IENGINEERIMG. A CONTINUING BIBLIOGRAPHY WITH jEABii (SUPPLEMENT 151) (National ^^^* Aeronautics and Space Administration) 118 p Unclas IJM^ mhC ib.uO CSCL 01A 00/U1 J5b92 •• i^r^i •• •%« jr-m^i^B •V«M»BW*<«I •»•« M^ Engineering Aeronautical E _ • ^^mI ^HEngineerinM • ^^ • g Aaro^ n • Aeronautical Engineering A ing Aeronautical Enginee lineerina Aeronautical F ngineering Aeronautical E ^>Jm Engineemam • ^^ i • ** eronautica_ • ^^«l EngineerinBiB^H g A ing Aeronautical Engineer! ACCESSION NUMBER RANGES

Accession numbers cited in this Supplement fall within the following ranges.

STAR (N-10000 Series) N82-22141 - N82-24160

IAA (A-10000 Series) A82-28539 - A82-31676 NASASP-7037(151)

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

(Supplement 151)

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information sys- tem and announced in July 1982 in

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

Scientific and Technical Information Branch 1982 National Aeronautics and Space Administration Washington, DC This supplement is available as NTISUB 141 093 from the National Technical Information Service (NTIS), Springfield, Virginia 22161 at the price of $5.00 domestic; S10.00 foreign. 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. This supplement to Aeronautical Engineering - A Continuing Bibliography (NASA SP- 7037) lists 362 reports, journal articles, and other documents originally announced in July 1982 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged 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 (A82-10000 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 $8.00 per document. Microfiche''' of documents announced in IAA are available at the rate of $4.00 per microfiche on demand, and at the rate of S1.35 per microfiche for standing orders for all IAA microfiche.

Minimum air-mail postage to foreign countries is $2.50 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 (N82-10000 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 preceded by the letters HC or MF in the STAR citation. Current values for the price codes are given in the tables on page vii. 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. Initially distributed microfiche under the NTIS SRIM (Selected Research in Microfiche) is available at greatly reduced unit prices. For this service and for information concerning subscription to NASA printed reports, consult the NTIS Subscription Section, Springfield, Va. 22161. NOTE ON ORDERING DOCUMENTS: When ordering NASA publications (those followed by the * symbol), use the N accession number. NASA patent applications (only the specifications are offered) should be ordered by the US-Patent-Appl-SN number. Non-NASA publications (no asterisk) should be ordered by the AD, PB, or other report number shown on the last line of the citation, not by the N accession number. It is also advisable to cite the title and other bibliographic identification.

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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. ADDRESSES OF ORGANIZATIONS

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(Effective January 1. 1982)

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A12 251-275 21.00 42.00 A13 276-300 22.50 45.00 A14 301-325 24.00 48.00 A15 326-350 25.50 51.00 A16 351-375 27.00 54.00

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A22 501-525 36.00 72.00 A23 526-550 37.50 75.00 A24 551-575 39.00 78.00 A25 576-600 40.50 81.00 601-up -21

A99-Write for quote

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E11 25.50 51.50 E12 28.50 57.50 E13 31.50 63.50 E14 34.50 69.50 E15 37.50 75.50

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E-99-Write for quote N01 30.00' 45.00 TABLE OF CONTENTS

Page IAA ENTRIES (A82-10000) 325 STAR ENTRIES (N82-10000) 343

Subject Index A-1 Personal Author Index B-1 Contract Number Index C-1

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED DOCUMENT AVAILABLE ON MICROFICHE -» N82-10021*# Kansas Univ. Center for Research. Inc.. Lawrence Flight Research Lab - NASA ACCESSION ICING TUNNEL TEST OF A GLYCOL-EXUDING POROUS NUMBER LEADING EDGE ICE PROTECTION SYSTEM ON A GENERAL LCORPORATE AVIATION AIRFOIL Final Report SOURCE • David L. Kohlman. William G. Schweikhard. and Alan E. Albright TITLE - Sep. 1981>*'37 p refs -(Gram NAG3-71) • (NASA-CR-165444; KU-FRL-464-1) Avail: NTIS" -PUBLICATION HC A03/MF A01 CSCL01C-" DATE AUTHORS- Test results show that the system is very effective in preventing ice accretion (anti-ice mode) or removing ice from an airfoil. Minimum glycol flow rates required for antiicing are a CONTRACT function of velocity, liquid water content in the air. ambient -AVAILABILITY OR GRANT- temperature, and droplet size. Large ice caps were removed in SOURCE only a few minutes using anti-ice flow rates, with the shed time being a function of the type of ice. size of the ice cap. angle of attack, and glycol flow rate. Wake surveys measurements REPORT show that no significant drag penalty is associated with the -COSATI NUMBER- installation or operation of the system tested. T.M CODE

TYPICAL CITATION AND ABSTRACT FROM IAA

-AVAILABLE ON AIAA ACCESSION MICROFICHE NUMBER A82-11317 H Development of aircraft production engineer- ing discipline at NT, Bombay^N. K. Naik (Indian Institute of Technology, Bombay, India). Aeronautical Society of India, Journal, -TITLE vol.31, Feb.-Nov. 1979^p. 119-125. The aircraft production engineering courses offered at the AUTHOR- Indian Institute of Technology, in Bombay, are discussed. To demonstrate the value of the courses, the fundamentals of aircraft — AUTHOR'S production are outlined, the discussion being confined to airframe AFFILIATION production. The loft-template method is described, and the principal loft-template scheme used in aircraft production is shown. Also TITLE OF described are the theory and laboratory courses offered at the -PUBLICATION PERIODICAL - institute. C.R. DATE AERONAUTICAL

ENGINEERING A Continuing Bibliography (Suppl. 151) AUGUST 1982

increasingly corrosion-resistant nickel-based superalloys. Attention is also given to drive shafts and bearings. O.C.

A82-28590 Composite materials. W. N. Turner, J. W. IAA ENTRIES Johnson, and C. G. Hannah (Rolls-Royce, Ltd., Derby, England). In: The development of gas turbine materials. London, Applied Science Publishers, 1981, p. 121-145. 16 refs. Since the development of the RB 162 engine, composite materials such as glass fiber/epoxy, glass fiber/polyimide, and carbon A82-28543 Occurrence of fretting fatigue failures in prac- or graphite fiber/epoxy have displaced conventional metallic compo- tice. P. J. E. Forsyth (Royal Aircraft Establishment, Materials Dept., nents in aircraft gas turbines through a combination of lower weight Farnborough, Hants., England). In: Fretting fatigue. and superior performance. Applications of such composites include London, Applied Science Publishers, Ltd., 1981, p. compressor blades and casings, fan blades, nacelle components and 99-125. thrust reversers. Emphasis is put on the development of pressure- The basic characteristics of fretting fatigue are identified and assisted resin injection and the autoclave molding resin system for practical engineering situations where fretting fatigue problems can the successful application of carbon fiber reinforced plastics. The arise are discussed. The discussion includes both commonly observed prospective development of high-temperature, metal-matrix compos- cases, such as flanges and loaded holes, and less common cases such ites able to operate above the polymer limit of 300 C is also as that of an aircraft lift strut stabilizing point where aerodynamic considered. Such composites will employ alumina, carbon and silicon vibrations are developed in the member. It is pointed out that once a carbide fibers in the reinforcement of aluminum and titanium alloy fretting fatigue failure has occurred in service, remedial measures can matrices. O.C. be found which will eliminate the problem. However, difficulties still arise in applications where the possibilities of fretting have not been A82-28594 Sheet materials - Fabrication and joining. B. identified at the design stage, and in pin-lug combinations where the Hicks (Lucas Aerospace, Ltd., Fabrication Div., Burnley, Lanes., engineering variables are difficult to control and where anti-fretting England). In: The development of gas turbine materials. compounds are difficult to maintain in situ. V.L. London, Applied Science Publishers, 1981, p. 229-258. 47 refs. A82-28565 * Finite element thermal analysis of Aircraft gas turbine engine sheet-fabricated components include convectively-cooled aircraft structures. A. R. Wieting (NASA, Lang- fan casings, combustion chambers, and bypass and exhaust ducts of ley Research Center, Hampton, VA) and E. A. Thornton (Old often complex shape which must be produced to high standards. Dominion University, Norfolk, VA). In: Numerical methods in heat Their production sequence typically entails (1) shaping sheet metal transfer. Chichester, Sussex, England and New parts by bending, drawing, stretch-forming, stamping and roll- York, Wiley-lnterscience, 1981, p. 431-443. 8 refs. forming, with inter-stage annealing and cleaning; (2) the machining The design complexity and size of convectively-cooled engine of those forgings and castings which are to become an integral part of and airframe structures for hypersonic transports necessitate the use the fabricated assembly; (3) degreasing, annealing and descaling of of large general purpose computer programs for both thermal and the parts in preparation for welding; (4) tungsten argon-arc or structural analyses. Generally .thermal analyses are based on the resistance welding; and (5) stress-relieving of the welded assembly lumped-parameter finite difference technique, and structural analyses and final heat treatment. Materials used range from high-temperature are based on the finite element technique. Differences in these superalloys employed in combustors and exhaust ducting to the alloy techniques make it difficult to achieve an efficient interface. It steels and titanium alloys of air casings and shrouds. Attention is appears, therefore, desirable to conduct an integrated analysis based given to the properties of such sheet alloys as Nimonic 75, Hastelloy on a common technique. A summary is provided of efforts by NASA X, and JetheteM 152. O.C. concerned with the development of an integrated thermal structural analysis capability using the finite element method. Particular A82-28643 Processing and uses of carbon fibre reinforced attention is given to the development of conduction/forced- plastics. (Translation of Verarbeiten und Anwenden kohlenstoffaser- convection finite element methodology and applications which verstarkter Kunststoffe, Diisseldorf, VDI-Verlag GmbH, 1981.) illustrate the capabilities of the developed concepts. G.R. Diisseldorf, VDI-Verlag GmbH, 1981. 286 p. $61.

A82-28587 The gas turbine engine. D. Driver, D. W. Hall, After an introductory paper on the processing and uses of and G. W. Meetham (Rolls-Royce, Ltd., Derby, England). In: The carbon fiber reinforced plastics (CRP), consideration is given to development of gas turbine materials. London, high-strength carbon fibers based on polyacrylonitrile, high-modulus Applied Science Publishers, 1981, p. 1-30. 28 refs. carbon fibers made from pitch, the surface treatment of carbon An historical account is given of the developments in gas turbine fibers, the nondestructive testing of CRP, and the novel high-strength engine mechanical design which, by increasing operating temperature structure materials family of hollow fiber composites. Also discussed requirements in their evolution towards greater thrust and lower fuel are CRP tension-compression struts, the CRP design and construction consumption, have strongly affected the choice of component of the Alpha-Jet elevator unit, the design and finite element method materials. The desire to reduce powerplant weight, and especially the structural analysis of the Airbus CRP rudder assembly, cardan shafts weight of rotating components, has also been a significant factor in composed of CRP and mixed laminates, an aluminum/CRP bridge, the development of materials. Compressor materials, which were chopped carbon fiber technology, and the use of carbon fiber largely aluminum alloy in the earliest gas turbine engines, were reinforced epoxy resin for human implants. O.C. supplanted by steels as temperatures rose above 200 C in the early 1950s; the development of high specific strength titanium alloys led A82-28649 Elevator unit for the Alpha-Jet, made from to their application to compressor blades and casings after 1960. carbon-fibre reinforced plastic. H. Conen and M. Kaitatzidis (Dornier Combustion chamber and turbine materials have been a succession of GmbH, Friedrichshafen, West Germany). In: Processing and uses of

325 A82-28658

carbon fibre reinforced plastics. Dusseldorf, spread lean limit of the fuels is essentially independent of the type of VDI-Verlag GmbH, 1981, p. 151-166. Translation. jet fuel and the initial jet discharge velocity. C.R. A detailed description is given of the design and construction of a carbon fiber-reinforced plastic (CRP) elevator structure for the A82-28738 The relaxation oscillation in ramjet combus- Alpha-Jet trainer aircraft. The spar box of the elevator unit consists tion. N. Huang (Beijing Institute of Aeronautics and Astronautics, of two continuous CRP shells and 11 metal ribs, and the remainder Beijing, People's Republic of China). In: Symposium/International/ of the assembly consists of CRP, or glass reinforced plastic, or a on Combustion, 18th, Waterloo, Ontario, Canada, August 17-22, combination of the two. Attention is given to comparisons of 1980, Proceedings. Pittsburgh, PA, Combustion structural complexity and production costs for the conventional Institute, 1981, p. 1891-1897. 20 refs. metallic and CRP elevator units, laminate construction details, the A mechanism of low frequency relaxation oscillation in ramjet stiffening of the spar box shells by means of a supporting sandwich, combustion is proposed. Initial pressure disturbances induce combus- and preparation of the spar box for autoclaving. A weight saving of tion instability which results in periodic heat release. Acting as 18% has been demonstrated for the CRP structure, which in fatigue feedback, the periodic heat release boosts the pressure pulsations. tests has exhibited a 20,000 flying hours capability. O.C. The complex shock wave system separating the supersonic and subsonic flows may be replaced by a virtual normal shock which A82-28658 The effect of swirl burner aerodynamics on shifts back and forth in the diffuser duct in response to the pulsating NOx formation. T. C. Clay pole and N. Syred (University College, pressure. The cold gas column expands or contracts like a buffer plug Cardiff, Wales). In: Symposium /International/ on Combustion, between the virtual normal shock and the flame front in accordance 18th, Waterloo, Ontario, Canada, August 17-22, 1980, Proceedings. with the pulsating combustion downstream. This chain of actions Pittsburgh, PA, Combustion Institute, 1981, p. and reactions results in a self-excited nonlinear relaxation oscillation 81-89. 17 refs. Research supported by the Science Research Council. with irregular frequency. The proposed mechanism explains quite When swirl is applied to the combustion air of a burner, a well the oscillograph obtained from the rig testing of a 220 mm complex, highly turbulent flow field is established which produces ramjet engine in a free jet of Mach No. 1.94 from a blowdown very stable flames. There is currently little information available tunnel. (Author) regarding the effect of the swirl on pollutant formation. The current investigation is concerned with the influence of the levels of swirl on A82-28808 Applications of structural adhesives in produc- the aerodynamics and NOx emissions at constant load. The instan- tion. W. J. Charles and S. J. Palmer (3M United Kingdom, Ltd., taneous velocities in the experiments are measured by dual beam Adhesives, Coatings and Sealants Div., Swansea, Wales). In: Adhesion laser anemometry. The flame is sampled with the aid of a quartz 5; Proceedings of the Eighteenth Annual Conference on Adhesion probe. It is found that to establish the source of pollutants in a swirl and Adhesives, London, England, March 1980. combustor, it is essential to consider the pollutant mass flow profiles. London, Applied Science Publishers, Ltd., 1981, p. 119-131. The recirculation zone, despite elevated temperatures, does not appear to play a major role in the formation of NOx. G.R. A82-28826 Instruments and installations for meteorologi- cal measurements at airports (Pribory i ustanovki dlia meteoro- A82-28660 NOx formation in flat, laminar, opposed jet logicheskikh izmerenii na aerodromakh). Edited by L. P. Afinogenov methane diffusion flames. W. A. Hahn and J. O. L. Wendt (Arizona, and E. V. Romanov. Leningrad, Gidrometeoizdat, 1981. 296 p. In University, Tucson, AZ). In: Symposium /International/on Combus- Russian. tion, 18th, Waterloo, Ontario, Canada, August 17-22, 1980, Proceed- A description is given of the systems and devices which are ings. Pittsburgh, PA, Combustion Institute, employed to provide the meteorological information which is needed 1981, p. 121-129; Comments, p. 129-131. 18 refs. U.S. Environ- for the conduction of the flight operations of civil aviation according mental Protection Agency Grant No. R-803715; Contract No. to the established standards of safety, efficiency, and reliability, 68-02-2631. taking into account the meteorological conditions at the airport and Diffusion flames can play a useful role in the study of the its environment. Problems and organizational aspects concerning the kinetic mechanisms of pollutant formation. A laminar diffusion conduction of meteorological measurements at airports are discussed, flame which has a number of useful attributes is the flat laminar giving attention also to the accuracy requirements. The various opposed jet diffusion flame. Such a flame is established between two approaches for determining visibility characteristics are examined coaxial opposed jets, one being fuel only and the other being along with the equipment employed in .the measurements. The oxidizer only, impinging on one other. This flame is strained in its determination of wind parameters, atmospheric pressure, tempera- own plane, and it can be envisioned as a prototype model for laminar ture, and humidity is also considered. A description is provided of an flamelets in turbulent diffusion flames. It is shown that the automatic system which was developed in 1971 for the utilization of considered flame, having a given stretching rate, is one dimensional in automatic procedures in connection with the acquisition, the temperature, concentration, and axial, but not radial, velocity processing, and the distribution of meteorological data. G.R. profiles, provided the correct boundary conditions are employed for the velocities of the two incoming jets. G.R. A82-28873 Tool use in cutting operations involving inte- gral structural components in aircraft construction (Werkzeugeinsatz A82-28692 The combustion of a fuel jet in a stream of bei der Zerspanung von Integralbauteilen im Flugzeugbau). H. lean gaseous fuel-air mixtures. G. A. Karim, I. Wierzba, M. Metwally, Graalmann (Messerschmitt-Bolkow-Blohm GmbH, Augsburg, West and K. Mohan (Calgary, University, Calgary, Alberta, Canada). In: Germany). In: Cutting operations for metals (Zerspanung der Symposium /International/on Combustion, 18th, Waterloo, Ontario, Metalle). Oberursel, West Germany, Deutsche Gesellschaft fur M eta II- Canada, August 17-22, 1980, Proceedings. Pitts- kunde, 1981, p. 97-104. In German. burgh, PA, Combustion Institute, 1981, p. 977-990; Comments, p. In connection with the desirability to use lighter and stiffer 990, 991. 8 refs. Research supported by the National Research structural units in aircraft designs, integral constructional approaches Council of Canada, Imperial Oil, Ltd., and University of Calgary. have been adopted in the aircraft industry during the last few years. The purpose is to establish the way in which the presence of a The change involves a replacement of a multitude of small individual fuel vapor homogeneously dispersed in the surrounding air influences sheet metal parts by a few complex integral structural components, the burning characteristics of the jet flame and the corresponding which are obtained by suitable machining operations from forgings flammability limits for both co-flowing and contra-flowing surround- or plates. The materials used for the production of integral structural ing streams in the presence of a pilot jet diffusion flame. A wide components include, in addition to aluminum, also titanium and range of jet diameters and discharge velocities is employed involving high-strength steels. However, a number of problems arise in methane or hydrogen at ambient temperature and pressure. Both connection with the required metal-cutting operations. Problems laminar and turbulent co-flowing streams are considered; the streams related, in particular, to the use of titanium are solved by making use involve a range of gaseous fuel-air mixtures and include methane, of a new cutting concept involving the use of multiple-spindle hydrogen, propane and ethylene. It is shown that the presence of machines and special tools. Attention is given to the selection of very small concentrations of fuel in the surroundings of the jet flame suitable cutting tools. G.R. tends to increase the flame thickness and height and to considerably enhance its stabilization. It is also found that the detected flame A82-28875 t Cascade converter of dc voltage to ac voltage

326 A82-28996 of higher frequency with voltage and frequency stabilization devices OH). In: Fluid/structure interactions in turbomachinery; Proceedings (Kaskadnyi preobrazoratel' postoiannogo napriazheniia v pere- of the Winter Annual Meeting, Washington, DC, November 15-20, mennoe povyshennoi chastoty s ustroistvami dlia stabilizatsii napria- 1981. New York, American Society of Mechani- zheniia i chastoty). M. M. Krasnoshapka and I. P. Terekhov (Vysshee cal Engineers, 1981, p. 9-18. 12 refs. Inzhenerno-Aviatsionnoe Voennoe Uchilishche VVS, Kiev, Ukrainian (Previously announced in STAR as N81-25080) SSR). Tekhnicheskaia Elektrodinamika, Jan.-Feb. 1982, p. 56-62. In Russian. A82-28993 # The excitation of compressor/duct systems. R. A dc-to-ac cascade converter is presented which consists of a dc E. Peacock (U.S. Naval Postgraduate School, Monterey, CA) and D. motor and an asynchronous motor with a three-phase stator winding K. Das (Cranfield Institute of Technology, Cranfield, Beds., En- gland). In: Fluid/structure interactions in turbomachinery; Proceed- and a multiphase rotor winding mounted on a common shaft within ings of the Winter Annual Meeting, Washington. DC, November the same housing. The experimental converter changes 28 V dc to 15-20, 1981. New York, American Society of 200/115 V ac. 400 Hz; it has a power of 800 VA at 6000 rpm and an Mechanical Engineers, 1981. p. 71-78. 5 refs. Research sponsored by efficiency of 0.56. The voltage stabilization circuit includes a the Ministry of Defence of England. toroidal winding on the back of the stator, an automatic voltage A series of experiments is reported in which the flow through a regulator which controls the magnetization current of the toroidal compressor/duct combination was perturbed in a cyclic way. The winding, and a capacitor bank controlled by the magnetization current through a contactor. Frequency is stabilized by an automatic unsteady flows generated were mapped through the system in the current regulator in the control field coil circuit. V.L. regime of stable compressor operations and the variation of their magnitude evaluated. It was found that in approaching the stability limit the stagnation pressure pulses tended to be magnified and that A82-28932 A multidimensional-crack-growth prediction the position of the stability limit line depended both upon the mean methodology for flaws originating at fastener holes. W. T. Fujimoto operating point of the compressor and the pulsation characteristics. and C. R. Saff (McDonnell Aircraft Co., St. Louis, MO). (Society for Further, it was possible to destabilize the system in a surge type Experimental Stress Analysis, International Congress on Experimen- manner at any superimposed frequency. (Author) tal Mechanics, 4th, Boston, MA, May 25-30, 1980.) Experimental Mechanics, vol. 22, Apr. 1982, p. 139-146. 16 refs. A general two-dimensional crack growth prediction methodolo- A82-28994 Advanced aluminum and titanium structures; gy for flawed fastener holes is developed which accounts for the Proceedings of the Winter Annual Meeting, Washington, DC, Novem- effects of residual stresses due to yielding at the hole edge as well as ber 15-20, 1981. Meeting sponsored by the American Society of the changing shape of the flaw. The methodology is based on a Mechanical Engineers. Edited by J. W. Goodman (USAF, Aeronauti- slice-synthesis model of the flawed hole which predicts the stress- cal Systems Div., Wright-Patterson AFB, OH). New York, American intensity factor distribution along the periphery of the crack after Society of Mechanical Engineers (Aerospace Symposia Series. Vol- each increment of advance. Analytic predictions of crack growth ume AD-02), 1981. 47 p. Members, $7.00; nonmembers, $14. rates are found to be in good agreement with test results. It is concluded that the assumption of a constant shape in one- Among the topics discussed are the use of the sheet metal dimensional crack growth prediction schemes can result in highly weldbonding process in A-10 aircraft production, the structural inaccurate service life estimates. V.L. integrity of an adhesively bonded aircraft fuselage, and the superplas- tic forming of 7475 aluminum alloy high-strength aircraft structures. A82-28934 Utility of a probability-density-function curve Also considered are the development of low-cost titanium alloy and F-maps in composite-material inspection. J. L. Rose, Y. H. structures using blended elemental powder metallurgy, and the Jeong, and M. J. Avioli (Drexel University, Philadelphia, PA). techniques of built-up, low-cost advanced titanium alloy aircraft Experimental Mechanics, vol. 22, Apr. 1982, p. 155-160. structure manufacture. O.C. The principles of probability-density-function analysis are brief- ly reviewed and its applications to nondestructive testing are A82-28995 ff Production weldbonding on the A-10 aircraft. discussed with emphasis on composite materials inspection. It is R. L. Rupp. A. Shames (Fairchild Republic Co., Farmingdale, NY), shown that probability-density-function curves can be used to and S. G. Lee (USAF, Wright Aeronautical Laboratories, Wright- produce feature maps (F-maps) of a composite material which are Patterson AFB, OH). In: Advanced aluminum and titanium struc- useful in both quality control and damage assessment. Sample tures; Proceedings of the Winter Annual Meeting, Washington, DC, problems involving graphite-polyimide structures and boron- November 15-20, 1981. New York, American aluminum materials are examined to illustrate the use of probability- Society of Mechanical Engineers, 1981, p. 1-10. 6 refs. Contract No. density-function curves and F-maps. The concept of inspectability F33615-78-C-5121. and its role in selecting a manufacturing technology are also The weldbonding process - an energy conservative manufac- discussed. V.L. turing process where the detail parts are fixtured by spotwelding through a structural adhesive with subsequent curing to obtain the A82-28986 Si Prediction of aerodynamically induced vibra- strength and fatigue life characteristic of adhesive bonded structure tions in turbomachinery blading. D. Hoyniak and S. Fleeter (Purdue has been production implemented on the A-10. A four-phase University, West Lafayette, IN). In: Fluid/structure interactions in program has been conducted to provide near-term service experience turbomachinery; Proceedings of the Winter Annual Meeting, and production experience on the A-10 and to define weldbond Washington, DC, November 15-20, 1981. New applicability to fatigue and fracture critical primary aircraft structure York, American Society of Mechanical Engineers, 1981, p. 1-8. 14 and secondary structure by mechanical property and environmental refs. durability testing. The production costs for the first 100 weldbond To predict the aerodynamically forced response of an airfoil, an shipsets are discussed with an analysis of the key cost drivers. energy balance between the unsteady aerodynamic work and the Planned production is in excess of 2000 weldbond assemblies. energy dissipated through the airfoil structural and aerodynamic (Author) damping is performed. Theoretical zero incidence unsteady aero- dynamic coefficients are then utilized in conjunction with this A82-28996 # Structural integrity of an adhesively bonded energy balance technique to predict the effects of reduced frequen- aircraft fuselage. D. L. Potter (Douglas Aircraft Co., Long Beach, cy, inlet Mach number, cascade geometry, and interblade phase angle CA). In: Advanced aluminum and titanium structures; Proceedings of on the torsion mode aerodynamically forced response of the cascade. the Winter Annual Meeting, Washington, DC, November 15-20, 1981. In addition, experimental unsteady aerodynamic gust data for flat New York, American Society of Mechanical plate and cambered cascaded airfoils are used together with these Engineers, 1981, p. 11-17. 11 refs. USAF-sponsored research. theoretical cascade unsteady aerodynamic damping coefficients to Procedures and test results used in the selection of a surface indicate the effects of incidence angle and airfoil camber on the treatment and adhesive system, and methods for its nondestructive forced response of the airfoil cascade. (Author) inspection, are described for the case of the Primary Adhesively Bonded Structure Technology (PABST) program. PABST is con- A82-28987 * # Measurement of aerodynamic work during fan cerned with evaluating the potential cost savings, weight reductions, flutter. A. P. Kurkov (NASA, Lewis Research Center, Cleveland, and structural integrity improvements that may result from the

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application of recently developed environment-resistant, 250 F-cure isolation, human factor design, and growth and flexibility accommo- modified epoxy adhesives and their primers. NDI-detected adhesive dation. C.D. flaws in the full-scale demonstration component structure, destruc- tively exposed after completion of the test program, showed precise A82-29005 H A Schwarz-Christoffel method for generating correlation with the Fokker Bpndtester Model. 70. It is also found internal flow grids. K. P. Sridhar (United Technologies Corp., Pratt thai metal crack propagation is contained within the stiffened and Whitney Aircraft Group, East Hartford, CT) and R. T. Davis boundaries of pressurized panels. The damage tolerance and durabil- (Cincinnati, University. Cincinnati, OH). In: Computers in flow ity of bonded primary structures are shown to be superior to those predictions and fluid dynamics experiments; Proceedings of the of mechanically-fastened structures despite the fabrication quality Winter Annual Meeting, Washington, DC, November 15-20, 1981. latitude permitted by the PABST program. O.C. New York, American Society of Mechanical Engineers, 1981, p. 35-44. 17 refs. A82-28997 # SPF of high strength aluminum structures. F. A new coordinate generation technique, developed by Davis for T. McQuilkin (Rockwell International Corp., North American Air- external flows, is extended to allow for accurate grid generation for a craft Div., Los Angeles, CA), C. H. Hamilton (Rockwell International variety of complex internal flow configurations. The approach is Science Center, Thousand Oaks, CA), and J. Waldman (U.S. Army, based on numerical integration of the Schwarz-Christoffel transfor- Research and Development Command, Dover, NJ). In: Advanced mation for polygonal surfaces. It is shown to be second-order aluminum and titanium structures; Proceedings of the Winter Annual accurate with mesh size due to analytic treatment of boundary Meeting, Washington, DC, November 15-20, 1981. singularities. The method is flexible enough to allow for treatment of New York, American Society of Mechanical Engineers, severe internal geometries, for a high degree of control of mesh 1981, p. 19-25. spacing, and for generation of either orthogonal or nonorthogonal The aluminum alloy 7475 has been shown to exhibit excellent grids. In addition, this technique directly provides the two- superplastic properties upon thermpmechanical processing, allowing dimensional incompressible potential flow solution for internal the one-step production of complex structures otherwise realizable flows, as well as a simple expression for calculating the grid metric only through the use of many parts and fasteners. After reviewing coefficients. Sample cases include symmetric and asymmetric chan- the results of tests characterizing elongation as a function of nel, diffuser, and cascade flows. (Author) temperature and strain rate, and corresponding measurements of flow stress as a function of strain rate, over the temperature range of A82-29008 * /f Application of computer generated color 371-516 C, the strain rate sensitivity exponent was determined as a graphic techniques to the processing and display of three dimensional function of temperature strain rate for the selection of optimum fluid dynamic data. B. H. Anderson, C. W. Putt, and C. C. Giamati forming parameters. The 7475 alloy was then applied to the (NASA, Lewis Research Center, Cleveland, OH). In: Computers in production of a redesigned T-39 Saberliner forward fuselage bulk- flow predictions and fluid dynamics experiments; Proceedings of the head consisting of a single, complex-formed sheet with four small Winter Annual Meeting, Washington, DC, November 15-20, 1981. clips, by contrast to 18 parts and over 100 rivets in conventional New York, American Society of Mechanical form, demonstrating a 36% cost reduction and 22% weight saving. Engineers, 1981, p. 65-72. 12 refs. O.C. (Previously announced in STAR as N81-29782)

A82-28998 # Development of low-cost titanium structures A82-29018 ff A computer-controlled oscillation mechanism using blended elemental powder metallurgy. P. C. Eloff (Imperial for unsteady aerodynamics experiments. J. P. Retelle (U.S. Air Force Clevite Technology Center, Cleveland, OH). In: Advanced aluminum Academy, Colorado Springs, CO), M. S. Francis (USAF, Office of and titanium structures; Proceedings of the Winter Annual Meeting, Scientific Research, Boiling AFB, Washington, DC), and J. E. Keese Washington, DC, November 15-20, 1981. New (USAF, Ballistic Missile Office, Norton AFB, CA). In: Computers in York, American Society of Mechanical Engineers, 1981, p. 27-31. flow predictions and fluid dynamics experiments; Proceedings of the Research supported by Gould, Inc., United Technologies Corp., and Winter Annual Meeting, Washington, DC, November 15-20, 1981. Magnavox Government and Industrial Electronics Co. New York, American Society of Mechanical By using blends of titanium sponge fine powder and elemental Engineers, 1981, p. 213-218. 5 refs. or masteralloy powders, powder metallurgy techniques have demon- Numerous wind tunnel studies of airfoil dynamic stall have been strated a halving of materials costs by comparison with conventional limited to harmonic model oscillations, but new microcomputers and wrought titanium alloy hardware production. An additional advan- hybrid servo systems have now been exploited to produce a tage of powder metallurgy in the working of the titanium alloy mechanism which provides a high degree of flexibility in achieving family in question, which is difficult to machine, is the ability to arbitrary model motions in multiple degrees of freedom over a wide produce near-net shapes requiring little subsequent machining. The range of motion alternatives. An apparatus capable of providing two structural components by which these capabilities are demon- simultaneous motions of an airfoil or wing model in both pitch and strated are a compressor-stator connecting link for the F-100 translation has been designed and fabricated. Drive motors provide turbofan engine, and a warhead body for the Army Stinger independent motion in two axes under control of servo-translator ground-to-air missile. The alloy compositions used are Ti-6AI-4V and units which respond to pulse trains generated by a microcomputer Ti-6AI-6V-2Sn, respectively. It is suggested that it may be possible to using analog position and feedback loops to smooth the pulses. formulate alloys through powder blending which would not be Programs are developed in a higher-level language using a larger obtainable by means of conventional ingot metallurgy. O.C. disk-based computer system with subsequent downline loading of the program task image through a network communications link to the A82-29000 H Advanced technology DFCS control panel for smaller computer. In addition to a description of the experimental the L-1011-500. T. E. Foster (Rockwell International Corp., Collins apparatus, the various elements of motion control, including servo- Air Transport Div., Cedar Rapids, IA). American Institute of translator dynamic characteristics, software techniques for pulse Aeronautics and Astronautics and Institute of Electrical and Elec- train generation, and required computer interface circuitry, are tronics Engineers, Digital Avionics Systems Conference, 4th, St. discussed. System performance characteristics are also discussed. Louis, MO, Nov. 17-19, 1981. AIAA Paper 81-2240. 8 p. (Author) The design features and development are described of a digital glareshield panel for the digital FCS-240 system that achieves the A82-29032 ff Fatigue behavior of adhesively bonded joints. following design objectives: (1) an efficient interface with the digital W. B. Jones, Jr. (USAF, Wright Aeronautical Laboratories, Wright- FCC's; (2) improved mean time between failures; (3) required Patterson AFB, OH) and J. Romanko (General Dynamics Corp., Fort aircraft wiring; (4) improved monitoring and fault isolation features; Worth, TX). In: 1981 advances in aerospace structures and materials; (5) accommodation of new operational features; (6) increased Proceedings of the Winter Annual Meeting, Washington, DC, Novem- flexibility for configuration changes. Besides providing traditional ber 15-20, 1981. New. York, American Society functions, the panel contains these advanced technology features: gas of Mechanical Engineers, 1981, p. 61-65. 5 refs. Contract No. discharge displays, multifunctional displays, ARINC 429 interfaces, F33615-76-C-5220. microprocessor control, dual redundant design, monitoring and fault Adhesively bonded metal aircraft structural joints are multi-

328 A82-29275 component systems, and as such, may display complex fatigue Center, Hampton, VA; Southampton, University, Southampton, behaviors over the range of loads and environments typically England) and J. G. Walker (Southampton University, Southampton, experienced in service. In order to explore the fatigue behavior of the England). Journal of Sound and Vibration, vol. 81, Mar. 8, 1982, p. adhesive layer itself, thick-adherend lap-shear joints were fabricated, 51-80. 24 refs. Research supported by the British Railways; Science stress analyzed, and tested. Stress distributions in the adhesive layer Research Council of England Grant No. B/RG/3777/3. were calculated using a finite element program. Instrumented fatigue Annoyance expressed in a railway noise survey is compared with tests were conducted at several loads, frequencies, humidities and that from two road traffic and three aircraft surveys in order to temperatures. Some of these tests were interrupted, and the metal determine whether responses to various types of environmental noise had been chem milled away. Only specimens which had experienced are source-specific. Railway noise is found to be less annoying than unduly high load amplitudes displayed damage. The damage initiated other noises at any given high noise level. Railway noise annoyance in the (calculated) high stress regions as interface cracks with scrim rises less rapidly with increasing noise level. At high levels, this gap in plane crazing. The cracks grew, with concurrent reduction in joint reactions averages about 10 dB; it ranges from 4 dB to more than 20 stiffness, until cohesive failure occured in the scrim plane. The dB. The methods used for comparing the surveys are examined. It is adhesive material tested is surprisingly tough and resistant to fatigue found that methodological uncertainties lead to imprecise compari- crack growth. (Author) sons and that different annoyance scales yield different estimates of intersurvey differences. C.R. A82-29036 ;,' Effects of moisture on the mechanical proper- ties of glass/epoxy composites. C. D. Douglas and E. R. Pattie (U.S. A82-29258 Low cost aircrew training devices. M. A. G. Army, Army Materials and Mechanics Research Center, Watertown, Knight (RAF Support Command, Brampton, Cumb., England). MA). In: 1981 advances in aerospace structures and materials; AeronauticalJournal, vol. 86, Mar. 1982, p. 98-101. 5 refs. Proceedings of the Winter Annual Meeting, Washington, DC, Novem- A description is presented of the simple aids that may be used in ber 15-20, 1981. New York, American Society the elementary stages of aircrew training, and illustrations are given of Mechanical Engineers, 1981, p. 91-97. 11 refs. of their integration with flight simulators and aircraft to constitute a Data are presented showing the effects of moisture on the systematic approach to flight training. The techniques described mechanical properties of a specific glass/epoxy composite system include books and manuals, two-dimensional trainers, cardboard that is a candidate material for fabrication of Army composite cockpits, suitcase trainers, table top trainers, cockpit procedures and helicopter rotor blades. The test specimens were immersed in instruments trainers, computer-based trainers, videogames and video- distilled water at temperatures of 25, 40, 60, and 80 C. Immersion disks. Attention is given to computer-assisted instruction, in which a times were one week, one, two, three, six, and nine months, and one microcomputer assumes many of the functions of an instructor and a year. Tension testing was then done on an Instron floor-model low-cost graphics terminal takes the role of a more complex and machine at a comant crosshead speed of 0.127 cm/min, and the detained simulator display. O.C. tangent modulus was determined. Specimen strength was found to decrease by 60 percent at 80 C immersion, less at lower tempera- A82-29259 The micro revolution comes to civil air trans- tures. The modulus dropped about 50 percent at 80 C immersion for port. M. Ryland (British Airways, Heathrow Airport, Middx., 90 deg off-axis specimens, less for those that were less off-axis. A England).AeronauticalJournal, vol. 86, Mar. 1982, p. 102-108. coupling agent with high-fiber, low-resin content was found to be A presentation is made of the range of microprocessor applica- superior to other couplers. C.D. tions currently available on civil aircraft, the hardware technology on A82-29042 # Turbulence-excited flapping motion of a rotor which these applications are based is reviewed, and the software blade in hovering flight. Y. K. Lin (Illinois, University, Urbana, IL) disciplines and certification procedures pertinent to airborne digital and C. Y. R. Hong. In: 1981 advances in aerospace structures and computers are outlined. Attention is given to the application of materials; Proceedings of the Winter Annual Meeting, Washington, microcomputer-based systems in the B 757 new-generation airliner, DC, November 15-20, 1981. New York, Ameri- which include flight control computers, flight management computer can Society of Mechanical Engineers, 1981, p. 149-153. 10 refs. systems, CRT flight instrumentation, thrust management, air data Grant No. DAAG29-78-G-0039. computation, supervisory engine control, radio navigation and Statistical properties of a randomly vibrating rotor blade under communication equipment control, and electrical generation regula- the excitation of turbulence is investigated using a simple model tion. It is shown that most problems encountered in applying which consists of a rigid blade, centrally hinged, with elastic restraint microcomputers to civil aircraft are software-related. O.C. for the flapping motion. It is shown that turbulence affects the blade motion in two ways, distinguished by two types of terms in the A82-29268 A review of U.S. Air Force research related to equation of motion. The first type appears in the coefficients, thus airframe and engine materials. A. H. Rosenstein (USAF, Office of causing the dynamic system to change randomly with time. The Scientific Research, Boiling AFB, Washington, DC). Journal of second type appears among the inhomogeneous terms. A theoretical Metals, vol. 34, Mar. 1982, p. 14-23. 16 refs. USAF-sponsored procedure is proposed in which both effects of the turbulence can be research. accounted for. Application of the methodology is illustrated by It is noted that the research addresses the fundamental physical numerical examples. (Author) nature of solids most directly relating to mechanical and thermal behavior. This involves an understanding of strengthening mecha- A82-29098 * Addition polyimide adhesives containing vari- nisms, fatigue, plasticity, creep, fracture, shock loading, the effect of ous end groups. A. K. Saint Clair and T. L. Saint Clair (NASA, stress state, the kinetics of phase transformations, lattice imperfec- Langley Research Center, Hampton, VA). Polymer Engineering and tions, and the thermal dependence of properties. An important result Science, vol. 22, no. 1, Jan. 1982, p. 9-14. 11 refs. of this research is information that will lead to improved structural Addition polyimode oligomers have been synthesized from 3,3 alloys of aluminum, titanium, and nickel and to a thorough prime, 4,4 prime-benzophenone tetracarboxylic acid dianhydride and understanding of the scientific principles governing their properties 3,3 prime-methylenedianiline using a variety of latent crosslinking and behavior. C.R. groups as end-caps. The nominal 1300 molecular weight imide prepolymers were isolated and characterized for solubility in amide, A82-29275 The investigation of aircraft accidents and chlorinated and ether solvents, melt-flow and cure properties, glass incident! • Some recent national and international developments. A. transition temperature, and thermal stability on heating in an air van Wijk (KLM Royal Dutch Airlines, Schiphol Airport, Nether- atmosphere. Adhesive strengths of the polyimides were obtained lands). Zeitschrift fur Luft- und Weltraumrecht, vol. 31, Mar. 1982, both at ambient and elevated temperatures before and after aging at p. 20-55. 75 refs. 232 C. Properties of the novel addition polyimides were compared to In June 1981, an International Civil Aviation Organization a known nadic end-capped adhesive, LARC-13. (Author) (ICAO) Panel of Experts on the General Work Programme of the ICAO Legal Committee recommended that the subject 'Legal A82-29165 • Comparing the relationships between noise Implications of Aircraft Accident and Incident Investigation' de- level and annoyance in different surveys - A railway noise vs. aircraft served consideration as a possible new item to be added to the and road traffic comparison. J. M. Fields (NASA, Langley Research General Programme of the Legal Committee and that a basic research

329 A82-29414

study should be undertaken by the ICAO Secretariat. A report is Langley low-turbulence pressure tunnel. A procedure for sailplane provided on developments both at national and international levels performance improvement has been outlined. (Author) connected with the considered subject. Major trends in recent ICAO thinking on the technical side of aircraft and incident investigation A82-29576 Fighting fire and other disasters from the air; procedures are examined, and developments in the U.S. are con- International Scientific-Technical Symposium, Hanover, West Germa- sidered. Resolutions adopted by the European Parliament in relation ny, June 11, 12, 1980, Reports (Brand- und Katastrophenbekamp- to air traffic safety issues are also discussed, and attention is given to fung aus der Luft; Internationales Wissenschaft-Technisches Sympo- developments in the-Netherlands, Switzerland, Sweden, New Zea- sium, Hanover, West Germany, June 11, 12, 1980, Vortrage). land, and Canada. G.R. Symposium sponsored by the Bundesministerium fur Forschung und Technologic. Melsungen, West Germany, A. Bernecker Verlag, 1981. 242 p. In German. $16.25. A82-29414 Soaring Society of America, National Conven- tion, Phoenix, AZ, January 14-18, 1981, Proceedings. Edited by J. Lincoln. Phoenix, AZ, Arizona Soaring Association, 1981. 120 p. Attention is given to fighting forest fires with the aid of aircraft in the U.S., the fighting of forest fires as a task for the Swiss air Features of modern sailplaning, contests, and hang gliding are force, the current state of technology concerning the fighting of forest fires from the air in Austria, the utilization of agricultural reviewed. Equipment maintenance and use in sailplanes are discussed, including the calibration of variometers, charging batteries, and types aircraft in economical operations for fighting fires in Israel, and'the of batteries. Sport hang gliding is described, as is competition tactics utilization of aircraft in fighting forest fires in France. The use of and photography. Homebuilt sailplanes are examined from the point 'water bombers' and chemical agents against forest fires is considered of view of a home sailplane builder and a manufacturer of kits, and along with the employment of two-engine and four-engine aircraft NASA research relevant to sailplane airfoils is explored. Finally, new for dropping the latest chemical fire extinguishing agents in connection with the fighting of forest fires, the adaptation and concepts in Dolphin Tactics for continuously changing airspeed to equipment of aircraft for the fighting of forest fires, and the maximize performance during a variety of sailplane maneuvers are detailed. M.S.K. employment of helicopters in Austria in connection with large-scale fires in buildings. Other topics discussed are related to the perfor- A82-29415 Checking and calibrating variometers in place mance characteristics and employment profiles of the new helicopter in the sailplane instrument panel. R. H. Ball. In: Soaring Society of BK117, and a comparative evaluation of fire extinguishing agents America, National Convention, Phoenix, AZ, January 14-18, 1981, involving the use of foam. G.R. Proceedings. Phoenix, AZ, Arizona Soaring Association, 1981, p. 29-38. A82-29577 # Fighting forest fires with the aid of aircraft in Techniques for calibrating the variometer, pitot total energy the United States of America (Waldbrandbekampfung mit Luftfahr- compensation, and netto and cruise controls while they are in a zeugen in den Vereinigten Staaten von Amerika). E. W. Keegan (U.S. glider instrument panel are described. The panel is assumed to Forest Service, Washington, DC). In: Fighting fire and other disasters feature an altimeter and clock, and further tools recommended are a from the air; International Scientific-Technical Symposium, Hanover, bottle, a needle valve, a hypodermic syringe, tubing, and fittings. West Germany, June 11, 12, 1980, Reports. Exact calibration of the variometer in conjunction with the altimeter Melsungen, West Germany, A. Bernecker Verlag, 1981, p. 17-27. In by setting the pressure equal to 3000 ft using a bottle is described, German. along with descent rate measurements to assure proper altitude change tracking. Further discussion is given of calibrating a total A82-29578 ff Fighting forest fires - A task for the Swiss air energy variometer, checking airspeed with an altimeter, the netto force (Waldbrandbekampfung - Eine Aufgabe der Schweizerischen compensation principle and calibration, and calibrating the cruise Flugwaffe). R. Salzborn (Schweiger Luftwaffe, Locarno, Switzer- control. Finally, attention is given to altitude errors with a land). In: Fighting fire and other disasters from the air; International variometer and to best flying speed at various altitudes. M.S.K. Scientific-Technical Symposium, Hanover, West Germany, June 11, 12, 1980, Reports. Melsungen, West Germany, A. Bernecker Verlag, 1981, p. 28-33. In German. A82-29416 Development of a homebuilt powered sail- Forest fires in the Swiss Alps are considered. It is found that the plane. A. Strojnik. In: Soaring Society of America, National great majority of all fires is produced by people. The development of Convention, Phoenix, AZ, January 14-18, 1981, Proceedings. a fire as a consequence of lightning is a very rare event. Long-term Phoenix, AZ, Arizona Soaring Association, 1981, p. consequences of forest fires are related to a reduction in the natural 77-89. capacity of forests to provide protection against avalanches and Design and problem solving in the fabrication of the S-2, a 15 m falling stones. Efforts to fight fires with the aid of aircraft go back to powered sailplane test flown in 1980, are discussed. Weight penalties, 1962. Fixed-wing aircraft were first utilized in firefighting opera- the use of a retractable engine to maintain aerodynamic cleanliness, tions. However, in recent years the use of such aircraft has decreased increases in drag due to the presence of an enlarged fuselage area and significantly in connection with the advantages provided by the a propeller, and the normal solution of placing the engine at the rear helicopter for the considered applications. Attention is given to the of a pod-and-boom fuselage are detailed. The S-2 features outrigger methods used in firefighting operations conducted with fixed-wing wheels on the wingtips, one under the pod, and the steering wheel aircraft and with helicopters, taking into account direct approaches under the tail. The wings are constant chord with trapezoidal outer 4 and indirect support action. G.R. ft sections to furnish an elliptical lift distribution at high lift coefficients. A middle wing section is reinforced by a carbon fiber A82-29579 # The current state of technology concerning spar, covered in 3-layer fiberglass skins, and shaped into a Wortman the fighting of forest fires from the air in Austria (Stand der Technik airfoil. Young's moduli for the materials are provided. The quality of zur Waldbrandbekampfung aus der Luft in Osterreich). T. Angermair the wing skin and the precision machining of the propeller are (Berufsfeuerwehr, Innsbruck, Austria). In: Fighting fire and other regarded as the two most crucial aspects of the S-2. M.S.K. disasters from the air; International Scientific-Technical Symposium, Hanover, West Germany, June 11, 12, 1980, Reports. A82-29417 * NASA research related to sailplane airfoils. D. Melsungen, West Germany, A. Bernecker Verlag, 1981, M. Somers (NASA, Langley Research Center, Hampton, VA). In: p. 34-39. In German. Soaring Society of America, National Convention, Phoenix, AZ, In 1973, difficulties related to the fighting of forest fires by January 14-18, 1981, Proceedings. .Phoenix, AZ. conventional means led in Austria to an investigation of more Arizona Soaring Association, 1981, p. 99-109. 8 refs. effective firefighting methods. It was first attempted to provide The theoretical methods and experimental facilities at the aircraft to ensure rapid transportation for the men and the NASA Langley Research Center have been employed to conduct equipment needed for the firefighting operations. The helicopter was investigations of sailplane airfoils. The unique and powerful capabili- found to provide significant advantages as a rapid means of ties of the Eppler Program have been used to design and analyze transportation, taking into account its capability to convey men and many airfoils and to smooth several Wortmann airfoils. Wind-tunnel material to and from locations not readily accessible by any other investigations of two sailplane airfoils have been conducted in the means. The successful solution of all problems related to the

330 A82-29586 envisaged use of the aircraft in firefighting operations was practiced A82-29583 ~ The employment of two-engine and four- in approximately 300 exercises. Attention is given to the number of engine aircraft for dropping the latest chemical fire extinguishing aircraft used in Austria for firefighting operations, the employed fire agents in connection with the fighting of forest fires (Einsatz von extinguishing agents, the attachment of the containers to the aircraft, zwei- und viermotorigen Flugzeugen fur den Abwurf der neuesten financial questions, and details concerning the firefighting opera- chemischen Lbschmittel bei der Waldbrandbekampfung). R. A. Davis tions. G.R. (Sis-Q Flying Service, Inc., Santa Rosa, CA). In: Fighting fire and other disasters from the air; International Scientific-Technical A82-29580 H The utilization of agricultural aircraft in eco- Symposium, Hanover, West Germany, June 11, 12, 1980, Reports. Melsungen, West Germany, A. Bernecker Verlag, nomical operations for fighting forest fires in Israel (Die Nutzung 1981, p. 88-96. In German. landwirtschaftlicher Flugzeugt zur okonomischen Waldbrand- bekampfung in Israel). I. Hirsch (Chimavir Services, Tel Aviv, Israel). In: Fighting fire and other disasters from the air; International A82-29584 f> Adaptation and equipment of aircraft for the Scientific-Technical Symposium, Hanover, West Germany, June 11, fighting of forest fires (Anpassung und Ausriistung von Flugzeugen 12, 1980, Reports. Melsungen, West Germany, zur Waldbrandbekampfung). R. E. Foy (Aero Union Corp., Chico, A. Bernecker Verlag, 1981, p. 40-43. In German. CA). In: Fighting fire and other disasters from the air; International The approaches used to protect the coniferous forests of Israel Scientific-Technical Symposium, Hanover, West Germany, June 11, against destruction by forest fires are discussed. The need for such a 12, 1980, Reports. ' Melsungen, West Germany, protection is illustrated by the fact that, in 1979, 2,500,000 trees A. Bernecker Verlag, 1981, p. 97-103. In German. were destroyed in connection with a total of 500 fires. It had been In connection with the selection of an aircraft for aerial found that forest fires cannot be effectively controlled on the basis firefighting operations, two alternatives have to be considered. An of an exclusive use of ground operations. However, financial aircraft expressly designed for firefighting applications can be considerations made it impossible to obtain for the protection of the purchased, or an available aircraft designed for civil or military forests special aircraft expressly designed for firefighting applica- service applications can be acquired with the aim to adapt the tions. It was, therefore, decided to utilize aircraft normally used for aircraft to the requirements which have to be met in connection with agricultural applications also for operations related to the fighting of the intended future use. Taking into account the high cost of a new forest fires. Particular attention is given to special approaches which aircraft design, it might be preferable, on the basis of economic make it possible to apply water for extinguishing fires most considerations, to decide in favor of the second alternative. All effectively from the available aircraft. G.R. private firms concerned with the operation of aircraft for the aerial application of fire retardants and fire extinguishing agents in North America use currently surplus civil aircraft or former military A82-29581 ft The utilization of aircraft in fighting forest aircraft. Attention is given to economic considerations regarding the fires - French experience (Nutzung der Luftfahrtmittel bei der Waldbrandbekampfung - Franzosische Erfahrungen). H. Bolzinger operations of such aircraft, questions of aircraft suitability for the (Ministere de I'lnterieur, Securite Civile, Marignane, Bouches-du- envisaged applications, and operational details. G.R. Rhone, France). In: Fighting fire and other disasters from the air; International Scientific-Technical Symposium, Hanover, West Germa- A82-29585 K The employment of helicopters in Austria in ny, June 11,12, 1980, Reports. Melsungen, West connection with large-scale fires in buildings (Hubschraubereinsatze Germany, A. Bernecker Verlag, 1981, p. 44-52. In German. bei Gebaudegrossbranden in Osterreich). T. Angermair (Berufsfeuer- Environmental and weather-related conditions in the case of a wehr, Innsbruck, Austria). In: Fighting fire and other disasters from substantial part of the French forests, taking into account, in the air; International Scientific-Technical Symposium, Hanover, West particular, coniferous woods, make it necessary to employ aircraft in Germany, June 11, 12, 1980, Reports. Mel- connection with the protection of these forests against destruction sungen, West Germany, A. Bernecker Verlag, 1981, p. 139-145. In by fire. In 1963, aircraft were used, for the first time in France, in German. operations related to the fighting of fires in forests. A review is Special problems concerning rescue operations in the case of provided of the aircraft available in 1980 for the protection of large fires in buildings and the fighting of these fires exist in Austria French forests against destruction by fire, giving attention to light in a very significant number of cases. About one tenth of all aircraft used in surveillance operations, helicopters, and air tankers. Austrians live in high buildings at levels above the'critical height' of The helicopter can provide a flying command post for the direction 22 m from the ground. In connection with fires, situations arise in of firefighting operations. Other functions of the helicopter are which people are isolated because all possible avenues of retreat have related to its use as a convenient means of transportation in areas been cut off. The chances. for the rescue of people in burning with accessibility problems. The air tanker carries water and other buildings can be significantly improved by supplementing the agents for an employment in direct firefighting operations from the conventional approaches of the fire department with techniques air. G.R. involving the use of helicopters. It has been found that in the case of pilots experienced in rescue operations in mountainous areas very A82-29582 # The use of 'water bombers' and chemical little additional training is required for the conduction of operations agents against forest fires, taking into account the employment of a involving the rescue of people in buildings. The conduction of such first-attack system (Einsatz von Wasserbombern und chemischen operations is discussed in detail. G.R. Mitteln gegen Waldbrande unter Verwendung eines Erstangriffs- systems). K. B. Marsden (Conair Aviation, Ltd., Abbotsford, British A82-29586 # Performance characteristics and employment Columbia, Canada). In: Fighting fire and other disasters from the air; profiles of the new helicopter BK117 (Leistungsmerkmale und International Scientific-Technical Symposium, Hanover, West Germa- Einsatzprofile des neuen Hubschraubers BK117). Mr. Schmidt- ny, June 11,12, 1980, Reports. Melsungen, West Bischoffshausen (Messerschmitt-Bblkow-Blohm GmbH, Ottobrunn, Germany, A. Bernecker Verlag, 1981, p. 66-79. In German. West Germany). In: Fighting fire and other disasters from the air; Fires in the forests, arid lands, and agricultural areas of Western International Scientific-Technical Symposium, Hanover, West Germa- Canada are efficiently controlled by making use of aircraft which ny, June 11, 12, 1980, Reports. Melsungen, West drop chemical firefighting agents that remain effective for a long Germany, A. Bernecker Verlag, 1981, p. 146-158. In German. time. The considered approach of fighting fires must be integrated Attention is given to a new helicopter developed jointly by a into a coordinated program, involving an early detection of the fire, German aerospace company and a Japanese company. The helicopter the availability of aircraft for immediate employment, and the can take off and land vertically, has the ability to hover, and can also ultimate complete extinction of the fire in connection with move slowly in any lateral direction. These flight characteristics have ground-based operations. Attention is given to the geographical provided for the helicopter a special area of application related to the features of the area of Western Canada, its meteorological character- prevention of fires, the fighting of fires, and protective operations in istics and its vegetation, the design of the employed aircraft, and the case of the occurrence of disasters. Requirements for successful details regarding the implementation of the considered program. The operations involving the fighting of fires are considered, taking into operations performed by the aircraft are illustrated with the aid of account the importance of an early detection of a fire, the need for pictures. G.R. an immediate initiation of operations, the achievement of an

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optimum of operational safety, and design and constructional details. condition of the angle of attack and sweepback angle of the leading The various types of operations for which the BK117 has been edge. The location and the strength of the shock are compared with employed are discussed, giving attention to specific data regarding those of available experimental and numerical results. They are the weight relations in each case. G.R. compatible with each other within the accuracy of the present analysis. (Author) A82-29592 F-15 fighter abilities evaluated. R. R. Ropelewski. Aviation Week and Space Technology, vol. 116, Apr. A82-29714 Sea-based remotely piloted vehicles. I - Issues 26, 1982, p. 39-43. 45, 46. and concepts. C. Henderson (Institute for Defense Analyses, Alexan- Modifications, features, and operations of the F-15 in an all dria, VA). Military Electronics/Countermeasures, vol. 8, Apr. 1982, weather air-to-ground capability configuration are described. The p. 61-64. rear cockpit has been outfitted with four multifunction CRT Remotely piloted vehicles (RPVs) in the 10,000-15,000 Ib class, displays, the mission computer memory has been expanded by 50%, equipped with radar and designed to operate from a variety of naval updates in the inertial navigation are now high velocity, and vessels, are proposed as long-range early warning platforms for carrier integration of the FLIR and laser ranging system has been accom- battle groups. Consideration is given to the inherent potential of plished. The total program took a year and a half, and successful RPVs for such missions as command, control and communications demonstration ground strikes are detailed. Specific attention is given (C3), surface surveillance, anti-air warfare, antisubmarine warfare and to lock-on and forget radar systems and digital menus for calling up electronic warfare. It is noted that the RPV payload weight plays an enlargements of displayed scenes on the CRT. Images lost during important role in determining the propulsion system thrust required, maneuvers could be restored by recycling the computer. The takeoff and landing modes, and the fuel volume needed for a mission controlled maneuverability of the aircraft is stressed, as are neces- of given duration. While C3 RPVs would be equipped with sities for calibrating the radar systems, proving the sensors, and communication gear and early warning RPVs with powerful search testing a variety of munitions. M.S.K. radars, all RPVs would carry data link hardware for command and control and sensor data transmissions. Attention is given to the use A82-29596 * Test methodology for evaluation of fireworthy of conformal radar arrays, which are shaped to the contour of the aircraft seat cushions. D. A. Kourtides and J. A. Parker (NASA, aircraft skin. O.C. Ames Research Center, Chemical Research Projects Office, Moffett A82-29773 Computational aerodynamics - Its coming of Field, CA). Journal of Fire and Flammability, vol. 13, Jan. 1982, p. age and its future. L. R. Miranda (Lockheed-California Co., Burbank, 56-76. 8 refs. FAA-sponsored research. CA). Lockheed Horizons, Spring 1982, p. 14-24. Aircraft seat materials were evaluated in terms of their thermal Current capabilities of computational aerodynamics are exam- performance. The materials were evaluated using (a) thermo- ined and an attempt is made to assess its future role in aircraft gravimetric analysis, (b) differential scanning calorimetry, (c) a design. Computational aerodynamics is the numerical solution of modified NBS smoke chamber to determine the rate of mass loss and equations of motion of fluids using digital computers and subsequent (d) the NASA T-3 apparatus to determine the thermal efficiency. In simulation of the corresponding aerodynamic flowfields. Simulations this paper, the modified NBS smoke chamber will be described in are noted to be significant for performance, design, and safety of detail since it provided the most conclusive results. The NBS smoke aircraft. Fields of numerical analysis, aerodynamic theory, and chamber was modified to measure the weight loss of materials when computer technology are combined to produce, the numerical exposed to a radiant heat source over the range of 2.5 to 7.5 W/cm simulation, with the projected flowfields being generated by solu- sq. This chamber has been utilized to evaluate the thermal tions to the IMavier-Stokes equations in the form of increasingly performance of various heat blocking layers utilized to protect the closer approximations. Panel methods, a simplified form of the full polyurethane cushioning foam used in aircraft seats. Various kinds of solution, are explored, and their ability to remain computationally heat blocking layers were evaluated by monitoring the weight loss of efficient with complex geometries is stressed. Advances in computer miniature seat cushions when exposed to the radiant heat. The technology are foreseen to enhance the option of using full effectiveness of aluminized heat blocking systems was demonstrated Navier-Stokes equations for high-speed aerodynamic simulations. when compared to conventional heat blocking layers such as M.S.K. neoprene. All heat blocking systems showed good fire protection capabilities when compared to the state-of-the-art, i.e., wool-nylon A82-29774 Fuel efficient and Mach 0.8, too. W. E. Arndt over polyurethane foam. (Author) (Lockheed-Georgia Co., Marietta, GA). Lockheed Horizons, Spring 1982, p. 26-34. A82-29597 An evaluation study of aluminide andchromo- Principles of propfan technology and problems which must be aluminide coatings on IN-100. R. Sivakumar (Defence Metallurgical solved for the introduction of propfans to production aircraft are Research Laboratory, Hyderabad, India). Oxidation of Metals, vol. discussed. The Hamilton-Standard concept, introduced in 1975, 17, Feb. 1982, p. 27-41. 21 refs. includes thin profile, swept-back multiple blades (8-10) suitable for Aluminide and chromoaluminide diffusion coatings on IN-100, a cruise speeds of Mach 0.8 with 15-20% less fuel consumption than cast Ni-base superalloy, have been investigated under laboratory currently available with turbofans. Studies in loading fatigue are conditions with reference to their structure and protective proper- necessary to determine if the cyclic loading caused by high-speed ties. The observed differences in the cyclic oxidation and hot swept back wings will adversely affect the integrity of composite- corrosion behavior of the coatings are rationalized in terms of the material propfans. Additional areas of concern are effects on the coating chemistry, and in particular, Cr and Al contents in the outer aerodynamic efficiency of aircraft induced by the presence of layers. The results obtained provide a way to predict the perfor- multibladed propfans, and the necessity of adding noise-reducing mance of NiAI-base coatings on Ni-base alloys. V.L. materials to maintain satisfactory cabin noise levels is a potential weight penalty factor. NASA trials on a converted Jetstar are A82-29659 ft Crossflow shock on the suction side of a flat described, along with possible techniques to reduce near- and farfield delta wing with supersonic leading edges. S. Kubo and T. Fujimoto noise levels. M.S.K. (Kyoto University, Kyoto, Japan). (Asian Congress of Fluid Mechan- ics, 1st, Bangalore, India, Dec. 8-13, 1980). Japan Society for A82-29789 Aerodynamics at the 1981 Le Bourget show Aeronautical and Space Sciences, Transactions, vol. 24, Feb. 1982, p. (L'aerodynamique au Salon du Bourget 1981). L. Rosenthal (Centre 211-221. 11 refs. de Documentation de l'Armement, Paris, France). L'Aeronautique et A theoretical investigation is made on the crossflow shock on I'Astronautique, no. 92, 1982, p. 37-56. 20 refs. In French. the suction side of a flat delta wing with supersonic leading edges in a Applications of the current state of the art in aircraft aero- uniform supersonic flow. An extension of the analytic characteristic dynamics and general tendencies in the development of the field as method is carried out for a three dimensional inviscid flow past a manifested at the 23rd International Air and Space Show at Le wing. Special care is taken in the treatment of the boundary Bourget in 1981 are considered. Among the new aircraft presented at conditions at the leading edge, at which there is a centered simple the show, the most original include the Transavia T 300 Sky Farmer, expansion wave. A crossflow shock is analyzed on the wing surface. the Edgley EA7 Optica three-seat observation plane and the NASA It is found that a weak crossflow shock appears under every Bell XV-15 experimental STOL craft. Configurations receiving

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significant attention at the show were those with winglets, canards For this reason it is necessary to limit the number of measurements. and strakes, especially on military aircraft, leading edge flaps, the This paper gives a mathematical formulation and examines the remotely piloted Hi MAT aircraft and aircraft with forward-swept characteristics of the optimization of the number and character of wings. Developments in propulsion aerodynamics involved air in- measurements made in the problem of state estimation using the takes, streamlined and multi-bladed propellers and the prop-fan. The least squares method in the case of an arbitrary matrix of importance of developments in composite materials, propulsion and measurements. BJ. systems to the realization of these aerodynamic configurations is emphasized. A.L.W. A82-29827 t The stability of maneuverable flight vehicles (K ustoichivosti manevrennykh letatel'nykh apparatov). A. B. A82-29792 Laser gyros - The guiding light. J. Hecht. High Aminov. Aviatsionnaia Tekhnika, no. 4, 1981, p. 7-11. 5 refs. In Technology, vol. 2, May-June 1982, p. 24, 26-28. Russian. The key advantages of laser gyros over mechanical gyroscopes A method is developed for obtaining the region of asymptotic are the absence of moving parts and lower cost. The laser gyro is a stability in the coefficient space of the nonlinear differential rotation sensor consisting of 3 rotating ring in which intense equations of the perturbed motion of a maneuverable flight vehicle. monochromatic light going in both directions is generated by the As an example, an analysis is presented of the stability of the excitation of an active medium in an optical resonator defined by longitudinal motion of a flight vehicle with large attack-angle three or more mirrors. Rotating the ring laser changes the effective deviations. B.J. resonator length so that the frequency of one beam is upshifted and the other downshifted. Turning a typical ring laser by 10 degrees per A82-29828 t Comparison of light aircraft with strutted and hour will cause a detectable frequency shift of a few hertz. A number cantilever wings (Sravnenie legkikh samoletov s podkosnym i of approaches have been taken to solve the systems's main problem, svobodnonesushchim krylom). A. A. Badiagm. Aviatsionnaia Tekhni- the tendency of the beams to lock together at the same frequency ka, no. 4, 1981, p. 11-17. 5 refs. In Russian. when the rotation rate is very small. Optical fiber gyros may find use A general formula for the analysis of the mass of strutted and in systems where cost and compactness rather than accuracy are the cantilever wings of light aircraft is proposed. Optimal aspect ratio is chief consideration. C.D. analyzed, and a formula for determining the maximum flight velocity of a strutted-wing aircraft is presented. The strutted wing is found to A82-29793 Future auto engines - Competition heats up. C. be somewhat more cost effective than the cantilever wing. B.J. Rain. High Technology, vol. 2, May-June 1982, p. 39-47. The conventional internal combustion engine will remain an A82-29829 t Design principles of a computer-aided design important factor in future automobile engines because it is perfectly system (Printsipy postroeniia sistemy mashinnogo konstruirovannia). suited to the widely varying conditions of city and highway driving, lu. V. Davydov, A. A. Zazhigin, and V. A. Osipov. Aviatsionnaia and engineers continue to eke out design advances. Diesels will Tekhnika, no. 4, 1981, p. 17-22. 11 refs. In Russian. continue to make strong gains in'the near term because of their fuel The structure and basic features of a computer system for the economy advantage, but their emissions and fuel requirement design of flight vehicles are described. Particular attention is given to problems are serious. Stratified charge engines could challenge the mathematical models for the description of wing contours, the diesel because they satisfy governmental goals and would require the determination of external loads, strength analyses, the determination lowest retooling costs. Their multifuel capability gives them long- of the geometric characteristics of the components, the graphics term viability. The gas turbine and the Stirling offer the best fuel system, and the formation of control programs. The input and economies and are clean-burning, and both run on a wide range of output parameters of each module of the system are discussed. B.J. fuels. The Stirling requires engineering to improve its power density and to cut costs, while the gas turbine needs a breakthrough in A82- 29831 t Investigation of the aerodynamic-contour durable high-temperature ceramics. C.D. method with control functions in the form of smooth constant-sign contours (Issledovanie metoda aerodinamicheskogo kontura s uprav- A82-29800 Handling air freight in the 1980s - Meeting the liaiushchimi funktsiiami v vide gladkikh obvodov postoiannogo challenge. P. L. Peoples and V. Sweetland (Boeing Commercial znaka). R. Kh. Akhatov and V. A. Osipov. Aviatsionnaia Tekhnika, Airplane Co., Renton, WA). Aircraft Engineering, vol. 54, Mar. 1982, no. 4,1981, p. 27-31. In Russian. p. 7-10. A modified aerodynamic-contour method is developed which is Flight hardware and ground system development areas which are based on the use of a control function in the form of smooth necessary to meet the expected growth in air cargo in the 1980 contours of constant sign. This makes it possible to obtain a decade are reviewed. Boeing has undertaken studies involving mathematical model for a profile curve with normalized constancy of full-scale mock-ups of the 767 and 757 and various cargo loads to sign and a wide range of variation of the input information. The attempt optimization of cargo pallets, container shapes, and handling method is convenient for controlling profile shape and produces a procedures in moving freight. The large cargo-handling capacity of considerable savings in machine time. B.J. the 747 is outlined, noting the commonality designed into the cargo configurations for the 767 and 747. Freight and baggage handling A82-29832 t Estimation of the performance of non- procedures have been observed to have divergent requirements, stationary discontinuous control systems for flight vehicles (Otsenka although the LD-4 pallet offers an opportunity for the most efficient effektivnosti nestatsionarnykh razryvnykh sistem upravleniia letatel'- loading of either. Cargo and baggage packaging within standardized nykh apparatov). E. A. Kuklev. Aviatsionnaia Tekhnika, no. 4, 1981, modules for loading on pallets is asserted to offer 95-97% space p. 37-41. In Russian. utilization. M.S.K. The paper examinesa linear dynamic system with discontinuous A82-29820 t The stressed state of a parachute canopy controls conditioned by changes in the operational modes of the during opening (Napriazhennoe sostoianie kupola parashiuta pri system at random moments of time. An analytical method is raskrytii). G. N. Gaiubov (Tashkentskii Politekhnicheskii Institut, proposed for determining the averaged values of the performance functionals of the system, with allowance for a finite number of Tashkent, Uzbek SSR). Akademiia Nauk Uzbekskoi SSR, Doklady, no. 1, 1982, p. 12-14. 5 refs. In Russian. discontinuities. B.J. A82-29834 t Analysis of a multihinged empennage with A82-29826 t Optimization of measurements in the state allowance for shear strain (Raschet mnogosharnirnogo opereniia s estimation of systems using the least squares method (Optimizatsiia uchetom deformatsii sdviga). V. A. Pavlov and V. A. Portnoi. sostava ispol'zuemykh izmerenii v zadachakh otsenivaniia sostoianiia Aviatsionnaia Tekhnika, no. 4, 1981, p. 46-51. In Russian. sistem metodom naimen'shikh kvadratov). L. G. Ambartsumov. A method for analyzing a multihinged empennage is presented, Aviatsionnaia Tekhnika, no. 4, 1981, p. 3-6. 5 refs. In Russian. wherein the shear displacements included in the resolvent compatibil- Problems of the state estimation of aircraft systems are ity equations are determined by the Timoshenko method. Analysis characterized by a large quantity of information to be processed. results are presented on the empennage of an actual aircraft, and the This results in an increase in the cost of computations, a decrease in necessity of taking into account shear strain of the control surface the reliability of the results, and an increase in data processing time. and stabilizer in their own plane is found to be confirmed. BJ.

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A82-29836 t The stability of monocoque panels under special devices, are suggested. Expressions are presented for calcula- bending (Ustoichivost' panelei kessona pri izgibe). V. I. Shalashilin, ting the downward drift angle and the effect of horizontal wind O. B. Lozhkin, and V. A. Nagaev. Aviatsionnaia Tekhnika, no. 4, currents. V.L. 1981, p. 60-65. In Russian. An analysis is presented of the elastic stability of cylindrical A82-29872 " Analysis of changes in the gas-dynamic param- monocoque panels under bending. The critical loading conditions are eters of a gas-turbine helicopter engine during acceleration (Analiza investigated, and the selection of parameter values for the discrete przebiegu parametrow gazodynamicznych i mocy turbinowego transverse reinforcement is considered. BJ. silnika smiglowcowego podczas przyspieszania). E. Jaworski. Tech- nika Lotnicza i Astronautyczna, vol. 37, Apr. 1982, p. 13-17. In A82-29837 t Application of a dimensionless criterion of Polish. transport efficiency in evaluating aircraft modifications (O primene- Changes in the gas-dynamic parameters of a gas-turbine engine nii bezrazmernogo kriteriia transportnoi effektivnosti v otsenkakh during acceleration are analyzed using the results of a mathematical modifikatsii samoletov). V. N. Sheptunov. Aviatsionnaia Tekhnika, model for the engine transients. The parameters examined include no. 4, 1981, p. 65-70. 6 refs. In Russian. compressor and rotor rpm, compression ratio and air flow rate, A dimensionless criterion of transport efficiency (defined as the margin of stability, turbine inlet temperature, excess air ratio, ratio of aircraft performance to energy consumed in cruising flight) is turbine pressure drop, and engine power. The effects of the working proposed, and its possible applications are considered. The relation- medium inertia and mass and heat accumulation on the transient ship between transport efficiency and cost efficiency is established, processes in the engine are also discussed. V.L. and a method is developed for estimating the cost efficiency of aircraft design solutions and modifications on the basis of the A82-29880 t Numerical study of vibrattonal relaxation in relationship between the dimensionless criterion and transport costs. the turbulent mixing of jets in a supersonic nozzle (Chislennoe A numerical example is discussed. B.J. issledovanie kolebatel'noi relaksatsii pri turbulentnom smeshenii strui v sverkhzvukovom sople). A. V. Lavrov and V. A. Pospelov A82-29838 t Zone loading of flight-vehicle structures (Zon- (Leningradskii Politekhnicheskii Institut, Leningrad, USSR). noe nagruzhenie konstruktsii letatel'nykh apparatov). V. S. Azarin Inzhenerno-Fizicheskii Zhurnal, vol. 42, Apr. 1982, p. 586-592. 23 and B. L. Patsenker. Aviatsionnaia Tekhnika, no. 4, 1981, p. 71-73. 5 refs. In Russian. refs. In Russian. The turbulent boundary layer equations are used to examine gasdynamic and physical processes in the nozzle and resonator of a A82-29841 t Analysis of shells of straight-wing type (K C02 gasdynamic laser with selective thermal excitation. In order to raschetu obolochek tipa priamogo kryla). S. N. Bulatov and P. N. verify the adequacy of the proposed mathematical model of the Kurochka. Aviatsionnaia Tekhnika, no. 4, 1981, p. 80-83. In laser, a comparison is made with experimental data for various values Russian. of stagnation temperature and pressure; good agreement between Obraztsov's (1966, 1973) approach is used to develop a method theoretical and experimental results is found. The effects of the for the analysis of variable-thickness shells of arbitrary cross section. composition of the secondary jet, and stagnation temperature and The resolvent system is obtained by means of the Lagrange pressure on specific energy output are investigated. It is shown that, variational principle. The solutions are obtained in the form of at high pressures and temperatures, sufficiently high specific outputs expansions whose first terms correspond to the hypothesis of plane can be obtained only in the case of optimal C02 concentration in the sections, while the other terms take into account displacements secondary jet. B.J. caused by warping. B.J. A82-29923 Air Traffic Flow Management and Air Traffic A82-29844 t Thermal stability analysis for conical shells Flow Control (Air Traffic Flow Management und Air Traffic Flow with variable parameters (Raschet termoprochnosti konicheskikh Control). R. Kuttner (Gesellschaft fur Internationalen Flugverkehr obolochek s peremennymi parametrami). V. R. Kotel'nikov. mbH, Berlin, East Germany). Technisch-okonomische Information Aviatsionnaia Tekhnika. no. 4, 1981, p. 90-93. In Russian. der zivilen Luftfahrt, vol. 17, no. 4, 1981, p. 172-177. 7 refs. In A method based on an approximate solution of an integral German. elasticity equation is proposed for analyzing, at an early design stage, The growth in the volume of air traffic and the concentration of thermoelastic stress-strain state of thin-walled conical shells with air traffic in certain areas and during certain-time periods have caused variable parameters. The proposed method is demonstrated in a case operational difficulties for a number of area control centers (ACC) involving analysis of the effect of the wall thickness profile on the and approach control offices (APP) in the German Democratic stress-strain state of a shell for specified temperature distributions. It Republic. These difficulties are related to an insufficient capacity of is shown that thinning of the shell in the direction of the larger base ACC and APP to cope with peak traffic demands, because, in results in increased stresses and shifting of the maximum stresses to connection with economic considerations, it is often not possible to the region of higher temperatures. It is therefore recommended that design installations for peak demands. Two approaches are used to the wall increase in thickness toward the larger base. V.L. reduce the considered difficulties as much as possible. The approach of Air Traffic Flow Management (ATFM) involves the assignment of A82-29845 t Determination of an optimal control program a certain flight to a specific time slot. There are generally no delays, for an aircraft power plant during climb (Opredelenie optimal'noi if the resulting requirements are met. The approach of Air Traffic programmy upravleniia silovoi ustanovkoi samoleta na uchastke Flow Control is only employed if the ATFM process is unsuitable. razgona-nabora vysoty). 0. K. lugov. Aviatsionnaia Tekhnika, no. 4, Air Traffic Flow Control specifies the number of aircraft which can 1981, p. 96-98. In Russian. enter per unit of time. G.R. The paper examines the development of an optimal control program for an aircraft power plant during climb on the basis of a A82-29924 Flight simulators (Flugsimulatoren). G. criterion of minimum fuel consumption. Theoretical results obtained Westphal (Gesellschaft fur Internationalen Flugverkehr mbH, Berlin, using this approach are presented, and attention is given to the East Germany). Technisch-okonomische Information der zivilen validity of the assumption of the constant flight weight of aircraft at Luftfahrt, vol. 17, no. 4,1981, p. 180-189. 5 refs. In German. subsonic and supersonic speeds in calculating longitudinal accelera- Simulation involves the employment of models. A 'model' is a tion loading during climb. B.J. material or a conceptual system which corresponds to the object to be simulated on the basis of certain analogies. Flight simulators are A82-29871 ff Sudden changes in wind velocity - Their effect concerned with the simulation of conditions and events occurring on aircraft and means of reducing hazard. I (Uskok wiatru - Dzialanie during the flight of an aircraft. With respect to their employment, na samolot, srodki zmniejszajace zagrozenie. I). J. M. Morawski and the simulators can be divided into devices for research and for T. Smolicz (Instytut Lotnictwa, Warsaw, Poland). Technika Lotnicza training. Research simulators make it possible to achieve an optimum i Astronautyczna, vol. 37, Apr. 1982, p. 5, 6. In Polish. design for the man-machine system in the cockpit of modern aircraft. The effect of abrupt changes in wind velocity and direction on The reasons for the employment of flight simulators in the training the trajectory and aerodynamic stability of aircraft are examined and programs for the pilots of airlines are discussed, taking into account possible counter measures, including flying techniques and the use of also the various subsystems used in the simulator. Particular

334 A82-30102 attention is given to the cockpit, the computer, and the system A82-30091 H A comparison of properties of single overlap providing a simulation of the visual scene. G.R. tension joints prepared by ultrasonic welding and other means. T. Renshaw, K. Wongwiwat, and A. Sarrantonio (Fairchild Republic A82-29925 New processes and methods of technical diag- Co., Farmingdale, NY). In: Structures, Structural Dynamics and nostics and prognostics in the case of the engine NK-8-4. II (Neue Materials Conference, 23rd, New Orleans, LA, May 10-12, 1982, Vertahren und Methoden der technischen Diagnostik und Prognostik Collection of Technical Papers. Part 1. New beim Triebwerk NK-8-4. II). S. Jung (Gesellschaft fur International York, American Institute of Aeronautics and Astronautics, 1982, p. Flugverkehr mbH, Berlin, East Germany). Technisch-okonomische 137-144. (AIAA 82-0661) Information der zivilen Luftfahrt, vol. 17, no. 4, 1981, p. 193-195. An employment of the ultrasonic welding process in aircraft In German. assembly operations might possibly lead to an achievement of very significant cost and weight reductions. A development program has A82-30004 Composite bonds improve thermal integrity. been in progress with the objective to realize the potentials of the A. Kleider (U.S. Army, Avionics Laboratory, Fort Monmouth, NJ), ultrasonic welding process for aircraft production. The present J. T. Johnson (Westinghouse Defense and Electronic Systems Center, investigation represents an extension of studies reported by Renshaw Baltimore, MD), and R. L. Kolek (Westinghouse Electric Corp., and Sarrantonio (1980). It had been found that large, single overlap Marine Div., Sunnyvale, CA). ManTech Journal, vol. 6, no. 3,1981, joints made with ultrasonic spotwelds could be loaded to sheet p. 37-41. Army-supported research. stresses above the yield strength. Tests conducted in the current Production process considerations which, once solved, permitted investigation cover series of interlayer situations which can exist in fabrication of 1000 parts/yr of stabilized line-of-sight gimbals for the assembly of aircraft. Fatigue data are also reported for the joints. aircraft electrooptical systems and sensors are discussed. A thermal Other types of joints than ultrasonically welded ones were also sample was fabricated of composites to evaluate the expansion prepared and tested in order to develop directly comparable static characteristics for mating bearings to the bore with resultant and fatigue properties. Weight and cost comparisons are included. constant friction and stiffness values over the operating temperature G.R. range. Titanium rings were chosen to interface with the outer bearing race, and a series of thermal cycles were performed in order to test A82-30096 ff Finite element analysis of through the canopy the bonds. Procedures of a design change and implementation are emergency crew escape from the T-38 aircraft. R. E. McCarty and R. outlined, noting the final design called for 121 parts, some formed A. Smith (USAF, Flight Dynamics Laboratory, Wright-Patterson with expandable internal mandrels. Curing conditions for the fiber AFB, OH). In: Structures, Structural Dynamics and Materials composite structures are detailed, including formation of the base Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection of plate stiffener ring. The gimbal produced features a 33% weight Technical Papers. Part 1. New York, American savings over previous gimbals. M.S.K. Institute of Aeronautics and Astronautics, 1982, p. 197-205. 15 refs. (AIAA 82-0705) A82-30076 Structures, Structural Dynamics and Materials The nonlinear static response to a concentrated load on the Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection of inner surface of the student pilot canopy for the T-38 aircraft has Technical Papers. Part 1 - Structures and materials. Part 2- Structural been predicted using the MAGNA (Materially and Geometrically dynamics and design engineering. Conference sponsored by AIAA, Nonlinear Analysis) finite element computer program. The analyses ASME, ASCE, and AHS. New York, American Institute of Aero- conducted were intended to simulate the impingement on the nautics and Astronautics, 1982. Pt. 1, 532 p.; pt. 2, 645 p. Price of canopy inner surface of a breaker located on the student pilot two parts, members, $100.; nonmembers, $125. ejection seat. Criteria for defining fracture of the canopy were selected and work required to fracture the canopy was then An integration scheme to determine the dynamic response of a determined from computed nonlinear load-displacement curves. The launch vehicle with several payloads is considered along with static load and work required to fracture two proposed bird-resistant aeroelastic characteristics of the Space Shuttle external tank cable designs for the T-38 student canopy were compared to those trays, the structural design of integral tankage for advanced space required to fracture the current design. It is concluded that transportation systems, and optimum damping locations for struc- transparency penetration for emergency crew escape via ejection seat tural vibration control. Attention is ^given to a damage induced breaker impingement on the T-38 student canopy is probably not aeroelastic failure mode involving combination and parametric feasible for a 0.68 in. thick monolithic stretched acrylic bird-resistant resonant instabilities of lifting surfaces, passive damping mechanisms design. The same mode of transparency penetration might prove in large space structures, an automated technique for improving feasible for a 0.40 in. thick monolithic polycarbonate bird resistant modal test/analysis correlation, pressure measurements on twin design. (Author) vertical tails in buffeting flow, and a wind-tunnel study of the aerodynamic characteristics of a slotted versus smooth-skin super- A82-30099 * ff Mechanical properties of a fiberglass prepreg critical wing. Other topics explored are related to the active control system at cryogenic and other temperatures. P. J. Klich and C. E. of aeroelastic divergence, stress constraints in optimality criteria Cockrell (NASA, Langley Research Center, Systems Engineering design, and damage tolerant design using collapse techniques. G.R. Div., Hampton, VA). In: Structures, Structural Dynamics and Materials Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection of Technical Papers. Part 1. New A82-30087 * # Effects of 50,000 hours of thermal aging on York, American Institute of Aeronautics and Astronautics, 1982, p. graphite/epoxy and graphite/polyimide composites. J. R. Kerr and J. F. Haskins (General Dynamics Corp., Convair Div., San Diego, CA). 223-230. 9 refs. (AIAA 82-0708) The compressor driving the flow in the National Transonic In: Structures, Structural Dynamics and Materials Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection of Technical Papers. Facility, which is nearing completion at the Langley Research Part 1. New York, American Institute of Center, has 25 fiberglass blades. E-glass cloth with a pre-impregnated Aeronautics and Astronautics, 1982. p. 101-108. Contract No. epoxy resin has been selected as the material for the fan blades NAS1-12308. (AIAA 82-0657) because of its low cost, high damping, and fatigue resistance. A Thermal effects on tensile strengths of advanced composite complete characterization is presented of this fan blade fiberglass systems have been determined for exposure times of 100 to 50,000 system at temperatures of 367 K, room temperature, and 89 K. The hours (5.7 years). Exposures were conducted at both ambient and characterization test results suggest that the material follows the reduced pressures at two temperatures for each composite. At the general trends of metals and other glass-reinforced plastics at completion of the various aging periods, specimens were removed cryogenic temperatures. A slight diminution in strength was observed from the specially constructed aging furnaces, visually examined, and at the elevated temperature. The tests included the following: tensile, tensile tested at elevated temperature. After tensile testing, many of compression, fatigue, inplane shear, interlaminar shear, thermal the thermal aging specimens were examined using a scanning electron expansion, creep, and thermal cycle. C.R. microscope. Results of these studies are presented, and the changes in properties and the degradation mechanisms during high- A82-30102 ft Damping and stiffness of aligned discontin- temperature aging are discussed and illustrated using metallographic uous fiber reinforced polymer composites. R. F. Gibson, C. T. Sun, techniques. (Author) and S. K. Chaturvedi (Florida, University, Gainesville, FL). In:

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Structures, Structural Dynamics and Materials Conference, 23rd, of a finite element prediction, taking into account an employment of New Orleans, LA, May 10-12, 1982, Collection of Technical Papers. the Structural Analysis of General Shells (STAGS). The obtained Part 1. New York, American Institute of results suggest that the clamped boundary condition utilized in the Aeronautics and Astronautics, 1982, p. 247-255. 24 refs. Research STAGS calculation is not exactly simulated by the employed test supported by the University of Florida. (AIAA 82-0712) setup. G.R. This paper describes recent analytical and experimental efforts to determine the effects of fiber aspect ratio, fiber spacing, and the A82-30116 # Flight qualification of composite structures at visco-elastic properties of constituent materials on the damping and AMD-BA. D. Chaumette (Avions Marcel Dassault-Breguet Aviation, stiffness of aligned discontinuous fiber reinforced polymer matrix Saint-Cloud, Hauts-de-Seine, France).' In: Structures, Structural composites. This includes the analysis of trade-offs between damping Dynamics and Materials Conference, 23rd, New Orleans, LA, May and stiffness as the above parameters are varied. Two different 10-12, 1982, Collection of Technical Papers. Part 1. analytical models show that there is an optimum fiber aspect ratio New York, American Institute of Aeronautics and for maximum damping, and that the predicted optimum aspect ratios Astronautics, 1982, p. 381-390. (AIAA 82-0755) lie in the range of actual aspect ratios for whiskers and microfibers. A brief description is provided of the different programs Experimental data for E-glass/epoxy specimens is presented for conducted in a French aerospace company, taking into account comparison with predictions. (Author) composite materials employed in the Mirage III rudder, the Mirage F1 horizontal stabilizer, the Mir F1 aileron, the Falcon 50 aileron, A82-30107 ••' Integrity analyses of surface-flawed aircraft and the fin, the rudder, and the elevens of the Mirage 2000. attachment lugs - A new, inexpensive, 3-D alternating method. T. Attention is also given to the introduction of a very new technology Nishioka and S. N. Atluri (Georgia Institute of Technology, Atlanta, in connection with the development of the Super-Mirage 4000, an GA). In: Structures, Structural Dynamics and Materials Conference, experimental Alpha Jet empennage, and the Falcon 10 wing. The 23rd, New Orleans, LA, May 10-12, 1982, Collection of Technical design of the Falcon 10 wing utilizes integrally stiffened carbon-fiber Papers. Part 1. New York, American Institute of panels. G.R. Aeronautics and Astronautics, 1982, p. 287-300. 24 refs. Grant No. AF-AFOSR-81-0057. (AIAA 82-0742) A82-30117 # On the characterization of damages in A new alternating method for the analysis of a quarter-elliptical graphite-epoxy composites. S. V. Hanagud and R. G. Clinton, Jr. corner crack is developed. The completely general analytical solution (Georgia Institute of Technology, Atlanta, GA). In: Structures, for an embedded crack, in an infinite solid, subject to arbitrary Structural Dynamics and Materials Conference, 23rd, New Orleans, crack-face tractions, is implemented in the present alternating LA, May 10-12, 1982, Collection of Technical Papers. Part 1. method. The present finite element alternating method results in an New York, American Institute of Aeronautics inexpensive procedure for routine evaluation of accurate stress and Astronautics, 1982, p. 391-404. 39 refs. (AIAA 82-0757) intensity factors for flawed structural components. The present Flaws are created in graphite-epoxy composites when they are alternating method is applied to the analyses of various shapes of exposed to an environment of high moisture and elevated tempera- quarter-elliptical corner cracks (1) in a brick subject to remote ture. The possibility of nondestructively identifying these flawed tension, (2) emanating from a hole in finite-thickness plates, subject states and quantitatively estimating the flaws have been attempted to remote tension as well as bearing pressure, and (3) emanating from by the measurement and analysis of acoustic emission events, counts a pin hole in aircraft attachment lugs subject to simulated pin per events and amplitude distribution. In particular cross ply woven loading. The results for the problem (1) and (2) are compared with composite laminates have been studied in undamaged and damaged those available in literature. For the problem (3) the stress intensity states. Techniques and methods of standardizing the test procedures factors, and their parametric variations for the corner cracks of have also been discussed. (Author) various shapes are presented. (Author) A82-30118 * ff Environmental and high strain rate effects on A82-30109 ii 737 graphite-epoxy horizontal stabilizer certi- composites for engine applications. C. C. Chamis and G. T. Smith fication. J. E. McCarty, R. W. Johnson, and D. R. Wilson (Boeing (NASA, Lewis Research Center, Cleveland, OH). In: Structures, Commercial Airplane Co., Seattle, WA). In: Structures, Structural Structural Dynamics and Materials Conference, 23rd, New Orleans, Dynamics and Materials Conference, 23rd, New Orleans, LA, May LA, May 10-12, 1982, Collection of Technical Papers. Part 1. 10-12, 1982, Collection of Technical Papers. Part 1. New York, American Institute of Aeronautics New York, American Institute of Aeronautics and and Astronautics, 1982, p. 405-419. 9 refs. (AIAA 82-0758) Astronautics, 1982, p. 307-322. 12 refs. (AIAA 82-0745) The complex environmental and loading conditions experienced The 737 graphite-epoxy horizontal stabilizer was developed as by many turbine engine components impose severe durability and part of the NASA/ACEE Advanced Composite Structures Program, damage tolerance requirements for component materials. Programs which was initiated in July 1977. Certification requirements were are being conducted to establish the structural performance of completed in February 1982. The 737 graphite-epoxy horizontal composite materials under anticipated engine operating environ- stabilizer, which represents a weight savings of 21.6 percent, will be ments. A description is presented of the results obtained in the first major component of aircraft primary structure to be connection with several of these programs. A comparison of certified for commercial airline service. The approach taken to obtain predicted and measured hygrothermal effects is considered along certification is considered. This approach complies with FAA with hygrothermal effects on defect growth, high strain rate effects regulations while maintaining the philosophy that commercial on composite mechanical properties, dynamic stress intensity factors aircraft structures are certified by structural analysis and supporting for composites, and the indentation laws for composite impact test evidence. G.R. analysis. G.R. A82-30114 * ti Experimental stress analysis of a thin-walled pressurized torus loaded by contact with a plane. D. E. Hill (Deere A82-30119 § A computerized system for the application of and Co., Moline, IL) and J. R. Baumgarten (Iowa State University of fracture tracking data to aircraft management for the C-5A military Science and Technology, Ames, IA). In: Structures, Structural airlift transport. D. V. Finkle and J. S. Wilson (Lockheed-Georgia Dynamics and Materials Conference, 23rd, New Orleans, LA, May Co., Marietta, GA). In: Structures, Structural Dynamics and Mate- 10-12, 1982, Collection of Technical Papers. Part 1. rials Conference, 23rd, New Orleans, LA, May 10-12, 1982, New York, American Institute of Aeronautics and Collection of Technical Papers. Part 1. New Astronautics, 1982, p. 369-373. 6 refs. Grant No. NsG-1605. (AIAA York, American Institute of Aeronautics and Astronautics, 1982, p. 82-0753) 429-434. USAF-supported research. (AIAA 82-0760) It is pointed out that pneumatic tires have a large effect on the The Aircraft Operational Suitability Program (AOSP) is a overall landing characteristics of an aircraft. The dynamic response computerized system which provides the United States Air Force a upon landing and steering are crucial to the safety of the vehicle and means by which to assess the impact, of day-to-day aircraft the occupants. The present investigation has the objective to operations on structural inspection schedules and structural life compare experimentally determined strains on an inner tube in reserve hours for the C-5A. The AOSP uses data generated by the contact with a flat plate with numerical values obtained on the basis C-5A individual aircraft fracture tracking system and features

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operations via remote computer terminal hookups. Specific opera- airfoils provide an economical construction method for easily varying tions of the AOSP include evaluations of the relative severity of important flutter parameters, while testing smooth-skin models is an proposed missions and the impact of proposed missions on estab- expensive and difficult way to conduct parametric studies. A lished structural inspection and modification schedules. (Author) wind-tunnel test was performed to evaluate the effects of sectional- ized model construction on aerodynamic behavior in the transonic A82-30125 fi High temperature, short term tensile strength speed range. The results indicate that sectionalized airfoils may not of C60007PMR-15 graphite potyimide. P. R. DiGiovanni and 0. significantly affect supercritical flutter aerodynamics. (Author) Paterson (Raytheon Co., Missile Systems Div., Bedford, MA). In: Structures, Structural Dynamics and Materials Conference, 23rd, A82-30140 * H Evaluation of four subcritical response New Orleans, LA, May 10-12, 1982, Collection of Technical Papers. methods for on-line prediction of flutter onset in wind-tunnel tests. Part 1. New York, American Institute of C. L. Ruhlin, J. J. Watson, R. H. Ricketts, and R. V. Doggett, Jr. Aeronautics and Astronautics, 1982, p. 487-492. 5 refs. (AIAA (NASA, Langley Research Center, Loads and Aeroelasticity Div., 82-0711) Hampton, VA). In: Structures, Structural Dynamics and Materials Tensile tests were conducted on 0 deg unidirectionally rein- Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection of forced Celion 6000 graphite fibers in PMR 15 polyimide matrix. Technical Papers. Part 2. New York, American Tensile strengths for coupons subjected to short and long term Institute of Aeronautics and Astronautics, 1982, p. 94-101. 7 refs. uniform temperatures were obtained. Thick coupons, heated on one (AIAA 82-0644) side to produce significant transient through thickness temperature Four subcritical response methods were evaluated for on-line use gradients, were tested and compared to the strength of specimens in transonic wind-tunnel tests where the flutter model is excited with uniform temperature distributions. All coupons were radiantly solely by airstream turbulence. The methods were: randomdec, heated and reached maximum test temperatures within 15 sec. power-spectral-density, peak-hold, and cross-spectrum. Subcritical Tensile loads were applied to the coupons after 15 sec of elevated response data were obtained during tests in the Langley Transonic temperature exposure. Loading rates were selected so that specimen Dynamics Tunnel of a cantilevered flutter model wing. The test failures occurred within a maximum of 45 sec after reaching the test procedure was to maintain a constant Mach number and increase the temperature. Results indicate that significant tensile strength remains dynamic pressure' (q) in incremental steps. The four methods beyond the material post cure temperature. (Author) provided damping trends by which the flutter mode could be tracked and extrapolated to a flutter-onset q. A hard flutter point was A82-30137 H An automated technique for improving modal obtained at M = 0.82. The peak-mold and cross-spectrum methods test/analysis correlation. D. T. Grossman (McDonnell Aircraft Co., gave reliable results and could be most readily used for on-line St. Louis, MO). In: Structures, Structural Dynamics and Materials testing. (Author) Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection of A82-30141 # Test demonstration of digital control of wing/ Technical Papers. Part 2. New York, American store flutter. E. H. Johnson, C. Hwang, W. S. Pi, D. F. Kesler, D. S. Institute of Aeronautics and Astronautics, 1982, p. 68-76. 7 refs. Joshi (Northrop Corp., Aircraft Div., Hawthorne, CA), and C. A. (AIAA 82-0640) Harvey (Honeywell, Inc., Minneapolis, MN). In: Structures, Struc- An automated technique for adjusting individual mass and tural Dynamics and Materials Conference, 23rd, New Orleans, LA, stiffness elements to improve the correlation of analytical frequency May 10-12, 1982, Collection of Technical Papers. Part 2. and mode shape data with ground vibration test results is described. New York, American Institute of Aeronautics and Perturbation formulae are used to calculate derivatives of a 'correla- Astronautics, 1982, p. 102-110. 8 refs. Contract No. tion coefficient' representing the overall similarity of the analytical F33615-80-C-3217. (AIAA 82-0645) and experimental results. A special iterative routine is developed to Methods of digital control have been applied to the demonstra- maximize this quantity and thus improve the overall correlation. The tion of the suppression of wing/store flutter. Digital control laws technique allows the user to take advantage of engineering judgment, were developed by applying a modified Jordan canonical transforma- produces physically realizable answers, and does not require the tion to a state variable formulation of a control law synthesized starting values of the variables to be near the final answers. Sample originally for an analog system. After performing a real time results are given. (Author) simulation of the digital control system at Northrop's Hawthorne facilities, the system was tested in the Transonic Dynamics Tunnel at A82-30138 a Pressure measurements on twin vertical tails in the NASA Langley Research Center. The results of the test showed buffeting flow. W. E. Triplett (McDonnell Aircraft Co., St. Louis, that the performance of the digital controller was comparable to that MO). In: Structures, Structural Dynamics and Materials Conference, of analog controllers. Attention during the test was focused on the 23rd, New Orleans, LA, May 10-12, 1982, Collection of Technical insertion of adequate antialiasing filters, the effects of sample time Papers. Part 2. New York, American Institute of and on the compensation for phase lags introduced by the digital Aeronautics and Astronautics, 1982, p. 77-83. USAF-sponsored control process. (Author) research. (AIAA 82-0641) Buffeting pressures were measured on the vertical tail surfaces of A82-30142 ff Flutter of forward swept wings, analyses and a 13 percent F-15 model in a low-speed wind tunnel. Test variables tests. T. A. Weisshaar, T. A. Zeiler (Purdue University, West included dynamic pressure, aircraft angle-of-attack, vertical tail Lafayette, IN), T. J. Hertz, and M. H. Shirk (USAF, Wright incidence and rudder deflection. Pressure transducers were flush Aeronautical Laboratories, Wright-Patterson AFB, OH). In: Struc- mounted on rigid and flexible tails. Steady and unsteady pressures tures, Structural Dynamics and Materials Conference, 23rd, New were obtained from the transducers at levels as low as 0.1 percent Orleans, LA, May 10-12, 1982, Collection of Technical Papers. Part full scale. The steady pressures were integrated for aerodynamic 2. New York, American Institute of Aeronautics coefficients and the unsteady pressures were reduced to spectral and Astronautics, 1982, p. 111-121. 20 refs. (AIAA 82-0646) densities. The pressures are maximum at approximately 22 deg The forward swept wing body-freedom flutter phenomenon and angle-of-attack and are significantly affected by tail flexibility. the Flight Dynamics Laboratory test program to investigate this (Author) phenomenon are discussed. Subsonic wind tunnel flutter tests of a variable sweep, forward swept wing model incorporating the rigid A82-30139 H A wind-tunnel study of the aerodynamic body fuselage pitch degree of freedom are conducted, and results characteristics of a slotted versus smooth-skin supercritical wing. W. illustrate the effects of flutter speed of static margin, wing sweep and F. Grosser (Lockheed-Georgia Co., Marietta, GA). In: Structures, composite" wing stiffness. The phenomenon occurs well below the Structural Dynamics and Materials Conference, 23rd, New Orleans, fixed root wing divergence speed, and the primary cause of LA, May 10-12, 1982, Collection of Technical Papers. Part 2. instability is found to be a coupling between the short period and the New York, American Institute of Aeronautics wing fundamental bending mode. At the onset of body freedom and Astronautics, 1982, p. 84-93. (AIAA 82-0642) flutter, significant amounts of pitch, plunge and bending motion are Wind-tunnel research test data indicate that flutter character- present in the aeroelastic and flight mechanics modes. Both istics at transonic speeds may be different for each supercritical decreasing aircraft static margin and decreasing the streamwise angle airfoil configuration. Therefore, high-speed flutter testing for limited of attack in the fundamental wing bending mode tend to increase the structural parameters may be inadequate. Models with sectionalized body-freedom flutter speed. D.L.G.

337 A82-30143

A82-30143 * * Measured and calculated effects of angle of minimize wing torsional stiffness. These variations along with the attack on the transonic flutter of a supercritical wing. E. C. Yates, sensitivity of wing torsional stiffness to the skin-to-frame attachment Jr., E. C. Wynne, and M. G. Farmer (NASA, Langley Research method complicated the structural model vibration mode predic- Center, Loads and Aeroelasticity Div., Hampton, VA). In: Struc- tions. A wing skin redesign with different fiber orientation and a tures, Structural Dynamics and Materials Conference, 23rd, New reduction in the amount of skin-to-frame bonding resulted in more Orleans, LA, May 10-12, 1982, Collection of Technical Papers. Part predictable modal characteristics without sacrificing design objec- 2. New York, American Institute of Aeronautics tives. Design and modeling considerations for future applications are and Astronautics, 1982, p. 122-144. 19 refs. (AIAA82-0647) discussed. (Author) The effects of angle of attack between 0 and 4 degrees were studied. The results indicate that increasing angle of attack from zero A82-30147 ti Durability and damage tolerance control plans can produce substantial changes in the transonic flutter characteris- for USAF aircraft. M. A. Landy and 0. L. Smithers (USAF, tics that are favorable or unfavorable depending on Mach number Aeronautical Systems Div., Wright-Patterson AFB, OH). In: Struc- and angle of attack. The bottom of the transonic flutter-boundary tures, Structural Dynamics and Materials Conference, 23rd, New 'bucket' is shown to occur at lower Mach number as angle of attack Orleans, LA, May 10-12, 1982, Collection of Technical Papers. Part increases. These flutter results correlate well with the effects of Mach 2. New York, American Institute of Aeronautics number and angle of attack on aerodynamic behavior, especially on and Astronautics, 1982, p. 166-174. 20 refs. (AIAA 82-0679) the development of transonic flow phenomena. The calculated A set of disciplined, integrated procedures involving a number of flutter characteristics are in good agreement with the experimental a contractor's functional organizations is necessary if the require- data at zero angle of attack, but at nonzero angles of attack the ments for a durable and damage tolerant structure are to be met. To experiments show sharply declining and backward-turning transonic this end, the Air Force requires that Durability and Damage flutter boundaries that are not indicated by the calculations. These Tolerance Control Plans (DADTCPs) be developed and implemented may be caused by variations in static aeroelastic deformation. C.D. during aircraft development and manufacturing. DADTCPs define all tasks necessary to ensure that the final product meets Air Force A82-30144 tf Integrated structural analysis and design durability and damage tolerance requirements. Various aspects to support for advanced launch vehicles. D. G. Wong, R. D. Bousquet, DADTCPs will be discussed in this paper. The foundation for a and C. R. Fuller (Lockheed Missiles and Space Co., Inc., Sunnyvale, generalized model outlining the tasks in a DADTCP will be CA). In: Structures, Structural Dynamics and Materials Conference, presented. Examples from existing DADTCPs will be used to 23rd, New Orleans, LA, May 10-12, 1982, Collection of Technical illustrate elements of the generalized model. (Author) Papers. Part 2. New York, American Institute of Aeronautics and Astronautics, 1982, p. 145-150. 5 refs. (AIAA A82-30150 tt Rigid body-structural mode coupling on a 82-0675) forward swept wing aircraft. G. D. Miller, J. H. Wykes,and M. J. The paper discusses a system incorporating the latest develop- Brosnan (Rockwell International Corp., El Segundo, CA). In: ments in computer hardware and software, conceived in accordance Structures, Structural Dynamics and Materials Conference, 23rd, with a five year plan initiated to support future advanced launch New Orleans, LA, May 10-12, 1982, Collection of Technical Papers. vehicle programs at the Lockheed Missiles and Space Company. Part 2. New York, American Institute of Engineering requirements for the integrated system forming the basis Aeronautics and Astronautics, 1982, p. 201-208. 10 refs. (AIAA for the department upgrades are presented. Software attributes are 82-0683) discussed, including program modularity, data management, and Physical causes of rigid/body wing bending flutter of forward programming standards. Hardware attributes are also presented, and swept wing (FSW) aircraft are discussed, and potential solutions to include system definition and design, communication network links, the phenomenon for a Rockwell design of an FSW demonstrator are and various graphical capabilities. D.L.G. considered. The use of active controls technology to design a flutter suppression system in controling the flutter on the demonstrator is A82-30145 # Bonded aluminum honeycomb - Aircraft flight discussed, including the integration of the active system with the surface primary structure application. T. R. Logan (Boeing Commer- complete aircraft design to obtain lightweight structure while cial Airplane Co., Seattle, WA) and U. Soudak (Israel Aircraft maintaining strength requirements, structural dynamic stability, and Industries, Ltd., Tel Aviv, Israel). In: Structures, Structural Dy- rigid body stability. Improvements in flying qualities, ride qualities namics and Materials Conference, 23rd, New Orleans, LA, May and reduction in the gust loads as a result of the active control 10-12, 1982, Collection of Technical Papers. Part 2. system are demonstrated. Inertial coupling in addition to wind sweep New York, American Institute of Aeronautics and is found to be a dominant variable causing the phenomenon. D.L.G. Astronautics, 1982, p. 151-156. 9 refs. (AIAA 82-0676) The first phase is discussed of a detail design and testing A82-30151 ff Active control of aeroelastic divergence. R. R. program undertaken to establish cost and weight data for a Chipman, A. M. Zislin, and C. Waters (Grumman Aerospace Corp., point-design application and to provide a basis for full-scale Bethpage, NY). In: Structures, Structural Dynamics and Materials development and certification of a bonded aluminum honeycomb Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection of empennage structural box. The baseline design is a built-up, Technical Papers. Part 2. New York, American mechanically fastened skin/stringer configuration. Structural design Institute of Aeronautics and Astronautics, 1982, p. 209-219. 15 refs. goals, inherent advantages and principal constraints of the bonded (AIAA 82-0684) design are given. Design allowables, optimum design, and substruc- On forward-swept-wing aircraft, aerodynamic destiffening of the ture arrangement are discussed in detail. A preliminary study primary wing-bending mode can cause coupling with the short-period demonstrates a significant 9.9 to 14.7 percent weight saving and a 20 mode, potentially resulting in a low-frequency dynamic instability. percent part count reduction. Potential overall manufacturing cost For a clamped wing, this coupled mechanism degenerates into reduction is estimated at 40 percent. C.D. conventional static wing divergence. Studies of a fundamental analytical model of this mechanism show that active control of the A82-30146 * If Design considerations and experiences in the clamped wing is possible only through the use of displacement use of composite material for an aeroelastic research wing. C. V. feedback. Control laws for the clamped wing are evaluated and also Eckstrom (NASA, Langley Research Center, Loads and Aero- assessed when body freedom is restored. Additionally, control laws elasticity Div., Hampton, VA) and C. V. Spain (Kentron Technical are synthesized directly for a more refined representation of the Center, Hampton, VA). In: Structures, Structural Dynamics and unrestrained vehicle. CCV configurations are not considered. Materials Conference, 23rd, New Orleans, LA, May 10-12, 1982, (Author) Collection of Technical Papers. Part 2. New York, American Institute of Aeronautics and Astronautics, 1982, p. A82-30153 * i! Static and unsteady pressure measurements on 157-165. 15 refs. (AIAA 82-0678) a 50 degree clipped delta wing at M = 0.9. R. W. Hess, E. C. Wynne, Experiences in using composite skin material on an aeroelastic and F. W. Cazier (NASA, Langley Research Center, Loads and research wing used in flight flutter testing are described. Significant Aeroelasticity Div., Hampton, VA). In: Structures, Structural Dy- variations in skin shear modulus due to stress and temperature were namics and Materials Conference, 23rd, New Orleans, LA, May encountered with the original fiberglass laminate skin designed to 10-12, 1982, Collection of Technical Papers. Part 2.

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New York, American Institute of Aeronautics and aerodynamic data were compared for a wing with an aspect ratio of 3 Astronautics, 1982, p. 234-242. 7 refs. (AIAA 82-0686) and a thickness ratio of 5% at Mach numbers of 0.7 and 0.9. Flutter Static and unsteady pressures were measured on a 50.45 degree data were compared for a wing with an aspect ratio of 5. Two clipped delta wing in the Langley Transonic Dynamics Tunnel with thickness ratios, 6% at Mach numbers of 0.715, 0.851, and 0.913, Freon as the test medium. Data taken at M = 0.9 is presented for and 4% at Mach number of 0.904, were considered. Based on the static and oscillatory deflections of the trailing edge control surface unsteady aerodynamic data obtained from LTRAN3, flutter bound- and for the wing in pitch. Comparisons of the static measured data aries were computed; they were compared with those obtained from are made with results computed using the Bailey-Ballhaus small experiments and the code NASTRAN, which uses linear aero- disturbance code. (Author) dynamics. (Author)

A82-30161 ff Analysis of aircraft dynamic behavior in a A82-30155 ff Transonic time-response analysis of three crash environment G. Wittlin (Lockheed-California Co., Burbank, D.O.F. conventional and supercritical airfoils. T. Y. Yang (Purdue CA). In: Structures, Structural Dynamics and Materials Conference, University, West Lafayette, IN) and J. T. Batina. In: Structures, 23rd, New Orleans, LA, May 10-12, 1982, Collection of Technical Structural Dynamics and Materials Conference, 23rd, New Orleans, Papers. Part 2. New York, American Institute of LA, May 10-12, 1982, Collection of Technical Papers. Part 2. Aeronautics and Astronautics, 1982, p. 316-325. 20 refs. Army- New York, American Institute of Aeronautics sponsored research. (AIAA 82-0694) and Astronautics, 1982, p. 256-266. 30 refs. (AIAA 82-0688) Differences in the crash environments and design aspects which Aeroelastic time-response analyses are performed for two influence occupant survivability in military and commercial aircraft conventional airfoils, NACA 64A006 and NACA 64A010, and one are discussed. Available analytical techniques for assessing structural supercritical airfoil MBB A-3, in small disturbance transonic flow. behavior during a crash are described. The application of a hybrid Response results for forces and displacements were obtained by technique in assessing aircraft structural behavior and trends in crash simultaneously integrating the structural equations of motion with environments is provided. Representative mathematical simulations the unsteady aerodynamic forces computed using two transonic of aircraft crash tests and correlation with light fixed-wing and codes: LTRAN2-IMLR (improved version of LTRAIM2 by Houwink rotary-wing aircraft test results are shown. The results of a recent and van der Vooren of NLR, the Netherlands) and LISTS (Unsteady FAA/NASA sponsored research program involving the review of Transonic Small Perturbation code by Isogai of NAL, Japan). Three transport accidents from 1964-79 and the formulation of potential d.o.f.'s, plunge, pitch, and aileron pitch, are considered. Flutter crash scenarios to be considered with future analysis and test analyses are first performed and the results are used as a guideline for verification are presented. Current and future analytical model time-response parameter selection. Time-response results are pre- studies to ascertain the crash dynamics of large transports are also sented showing that for each case the flight speed used to obtain discussed. (Author) neutrally stable responses is either exactly or nearly the same as the flutter speed determined in the separate flutter analysis. Effect of response amplitudes is investigated. Applicability and limitations of A82-30162* » Bird impact analysis package for turbine en- the two transonic codes are evaluated, compared, and discussed. gine fan blades. M. S. Hirschbein (NASA, Lewis Research Center, Transonic time-response behavior of these airfoils is physically Cleveland, OH). In: Structures, Structural Dynamics and Materials interpreted, discussed, and comparisons are made. (Author) Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection of Technical Papers. Part 2. New York, American A82-30156 * ff Application of a transonic potential flow code Institute of Aeronautics and Astronautics, 1982, p. 326-334. 8 refs. to the static aeroelastic analysis of three-dimensional wings. W. (AIAA 82-0696) Whitlow, Jr. and R. M. Bennett (NASA, Langley Research Center, A computer program has been developed to analyze the gross Loads and Aeroelasticity Div., Hampton, VA). In: Structures, structural response of turbine engine fan blades subjected to bird strikes. The program couples a NASTRAN finite element model and Structural Dynamics and Materials Conference, 23rd, New Orleans, modal analysis of a fan blade with a multi-mode bird impact analysis LA, May 10-12, 1982, Collection of Technical Papers. Part 2. New York, American Institute of Aeronautics computer program. The impact analysis uses the NASTRAN blade and Astronautics, 1982, p. 267-276. 12 refs. (AIAA 82-0689) model and a fluid jet model of the bird to interactively calculate A method for including elastic effects in steady, transonic wing blade loading during a bird strike event. The analysis package is analysis is presented. Since the aerodynamic theory is nonlinear, the computationaly efficient, easy to use and provides a comprehensive method requires the coupling of two iterative processes - an history of the gross structual blade response. Example cases are aerodynamic analysis and a structural analysis. A full potential presented for a representative fan blade. (Author) analysis code, FL022, is combined with a linear structural analysis to yield aerodynamic load distributions on and deflections of elastic A82-30168 * /; . Damage tolerant design using collapse tech- wings. This method was used to analyze an aeroelastically-scaled niques. R. T. Haftka (Virginia Polytechnic Institute and State wind tunnel model of a proposed executive-jet transport wing and an University, Blacksburg, VA). In: Structures, Structural Dynamics and aeroelastic research wing. The results are compared with the Materials Conference, 23rd, New Orleans, LA, May 10-12, 1982, corresponding rigid-wing analyses, and some effects of elasticity on Collection of Technical Papers. Part 2. New the aerodynamic loading are noted. (Author) York, American Institute of Aeronautics and Astronautics, 1982, p. 383-386. 13 refs. Grant No. IMAG1-168. (AIAA 82-0718) A82-30157 * If Comparison between computations and exper- A new approach to the design of structures for improved global imental data in unsteady three-dimensional transonic aerodynamics, damage tolerance is presented. In its undamaged condition the including aeroelastic applications. P. Guruswamy (Informatics, Inc., structure is designed subject to strength, displacement and buckling Palo Alto, CA) and P. M. Goorjian (NASA, Ames Research Center, constraints. In the damaged condition the only constraint is that the Moffett Field, CA). In: Structures, Structural Dynamics and Materi- structure will not collapse. The collapse load calculation is formu- als Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection lated as a maximization problem and solved by an interior extended of Technical Papers. Part 2. New York, American penalty function. The design for minimum weight subject to Institute of Aeronautics and Astronautics, 1982, p. 277-289. 20 refs. constraints on the undamaged structure and a specified level of the (AIAA 82-0690) collapse load is a minimization problem which is also solved by a Comparisons were made of computed and experimental data in penalty function formulation. Thus the overall problem is of a nested three-dimensional unsteady transonic aerodynamics, including aero- or multilevel optimization. Examples are presented to demonstrate elastic applications. The computer code LTRAN3, which is based on the difference between the present and more traditional approaches. small-disturbance aerodynamic theory, was used to obtain the (Author) aerodynamic data. A procedure based on the U-g method was developed to compute flutter boundaries by using the unsteady A82-30169 ff Shape optimization of fiber reinforced com- aerodynamic coefficients obtained from LTRAIM3. The experimental posites. S. V. Hanagud, A. Chattapadhyay, and L. Karlovitz (Georgia data were obtained from available NASA publications. All the studies Institute of Technology, Atlanta, GA). In: Structures, Structural were conducted for thin, unswept, rectangular wings with circular-arc Dynamics and Materials Conference, 23rd, New Orleans, LA, May cross sections. Numerical and experimental steady and unsteady 10-12, 1982, Collection of Technical Papers. Part 2.

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New York, American Institute of Aeronautics and control laws and previously synthesized control laws were evaluated Astronautics, 1982, p. 387-396. 5 refs. (AIAA 82-0719) analytically. In a wind tunnel entry using the flutter suppression In this paper, the problem of the shape optimization in a fiber model, one of the newly developed control laws was mechanized and reinforced composite has been considered. The shape optimization successfully demonstrated. (Author) can be interpreted as the problem of the optimum fiber distribution. In particular, the design of a long cylindrical rod that is subjected to A82-30176 ,7 Flutter analysis using nonlinear aerodynamic torsion has been discussed. The problem has been formulated as a forces. T. Udea and E. H. Dowell (Princeton University, Princeton, dual or min-max problem with appropriate constraints. The resulting NJ). In: Structures, Structural Dynamics and Materials Conference, Lagrange multipliers have been identified .with physical parameters 23rd, New Orleans, LA, May 10-12, 1982, Collection of Technical by performing the needed variations. The design procedure has been Papers. Part 2. New York, American Institute of discussed by considering the examples of the torsion of a rod of a Aeronautics and Astronautics, 1982, p. 462-481. 11 refs. Grant No. circular, a square and a rectangular cross section. (Author) AF-AFOSR-81-0123. (AIAA 82-0728) The nonlinear effects of transonic aerodynamic forces on the A82-30171 * H Transonic flutter study of a wind-tunnel flutter boundary of a typical section airfoil are studied. The flutter model of a supercritical wing with/without winglet. C. L. Ruhlin speed dependence on amplitude is obtained by utilizing a novel (NASA, Langley Research Center, Loads and Aeroelasticity Div., variation of the describing function method which takes into account Hampton, VA), F. J. Rauch, Jr., and C. Waters (Grumman Aerospace the first fundamental harmonic of the nonlinear oscillatory motion. Corp., Engineering Dept., Bethpage, NY). In: Structures, Structural By using an aerodynamic describing function, traditional flutter Dynamics and Materials Conference, 23rd, New Orleans, LA, May analysis methods may still be used while including the effects of 10-12, 1982, Collection of Technical Papers. Part 2. aerodynamic nonlinearities. The aerodynamic forces are computed New York, American Institute of Aeronautics and by the LTRAN2 aerodynamic code for NACA 64A006 and NACA Astronautics, 1982, p. 407-415. 18refs. (AIAA 82-0721) 64A010 airfoils. (Author) The scaled flutter model was a 1/6.5-size, semispan version of a supercritical wing (SCW) proposed for an executive-jet-transport A82-30177 ff Feedback control of a cantilever wing in airplane. The model was tested cantilever-mounted with a normal steady airflow. L. Meirovitch and L. Silverberg (Virginia Polytechnic wingtip, a wingtip with winglet, and a normal wingtip ballasted to Institute and State University, Blacksburg, VA). In: Structures, simulate the winglet mass properties. Flutter and aerodynamic data Structural Dynamics and Materials Conference, 23rd, New Orleans, were acquired at Mach numbers from 0.6 to 0.95. The measured LA, May 10-12, 1982, Collection of Technical Papers. Part 2. transonic flutter speed boundary for each wingtip configuration had New York, American Institute of Aeronautics roughly the same shape with a minimum flutter speed near M = 0.82. and Astronautics, 1982, p. 482-488. (AIAA 82-0729) The winglet addition and wingtip mass ballast decreased the wing A method for the active flutter suppression of a cantilever wing flutter speed by about 7 and 5%, respectively; thus, the winglet in steady airflow is presented. The wing undergoes bending and effect on flutter was more a mass effect than an aerodynamic effect. torsional vibrations. The control forces are generated by leading-edge Flutter characteristics calculated using a doublet-lattice analysis or trailing-edge flaps. Only the flutter modes are targetted for (which included interference effects) were in good agreement with control, while the remaining modes are left uncontrolled. Because of the experimental results up to M = 0.82. Comparisons of measured inherent structural damping in the wing, however, motion in these static aerodynamic data with predicted data indicated that the model modes decays exponentially with time. A numerical example is was aerodynamically representative of the airplane SCW. (Author) presented. (Author)

A82-30172 ~ Aeroelastic flutter and divergence of stiffness A82-30179 H Component coupling with time-invariant mass coupled, graphite/epoxy, cantilevered plates. S. J. Hollowell (USAF, matrix for nonisotropic rotating and nonrotating systems. S. G. Flight Dynamics Laboratory, Wright-Patterson AFB, OH) and J. Sadler, J. Corrigan, and J. G. Yen (Bell Helicopter Textron, Fort Dugundji (MIT, Cambridge, MA). In: Structures, Structural Dy- Worth, TX). In: Structures, Structural Dynamics and Materials namics and Materials Conference, 23rd, New Orleans, LA, May Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection of 10-12, 1982, Collection of Technical Papers. Part 2. Technical Papers. Part 2. New York, American New York, American Institute of Aeronautics and Institute of Aeronautics and Astronautics, 1982, p. 503-513. 13 refs. Astronautics, 1982, p. 416-426. 17 refs. Contract No. (AIAA 82-0731) F33615-77-C-5155. (AIAA 82-0722) A method has been developed which allows a nonisotropic An analytical and experimental investigation was conducted to rotating structure to be coupled with a nonisotropic nonrotating determine the aeroelastic flutter and divergence behavior of unswept, structure such that the system's coupled equations of motion have a rectangular wings simulated by graphite/epoxy, cantilevered plates time-invariant mass matrix. The modeling requirements for this with varying amounts of bending-torsion stiffness coupling. The method are defined and the analytical approach is developed using analytical approach incorporated a Rayleigh-Ritz energy formulation physical degrees of freedom to describe the motions of both the and unsteady, incompressible two-dimensional aerodynamic theory. rotating and the nonrotating components. Extensions to component Flutter and divergence velocities were obtained using the V-g method modal synthesis methods are given for a typical component modal and compared to results of low-speed wind tunnel tests. Stall flutter method, and also for a more recently developed method which behavior was also examined experimentally. There was good agree- retains only physical degrees of freedom at the component inter- ment between analytical and experimental results. Wings with faces. The method is developed for both time-domain and frequency- negative stiffness coupling exhibited divergence, while positive domain solutions. Demonstration of the method for helicopter coupling delayed the onset of stall flutter. (Author) coupled rotor/airframe dynamic analysis including a two-bladed teetering rotor are presented. (Author) A82-30173 H Application of optimal control techniques to aircraft flutter suppression and load alleviation. C. Hwang and W. S. A82-30182 * ft On the dynamic collapse of a column impact- Pi (Northrop Corp., Aircraft Div., Hawthorne, CA). In: Structures, ing a rigid surface. J. M. Housner and N. F. Knight, Jr. (NASA, Structural Dynamics and Materials Conference, 23rd, New Orleans, Langley Research Center, Structures and-Dynamics Div., Hampton, LA, May 10-12, 1982, Collection of Technical Papers. Part 2. VA). In: Structures, Structural Dynamics and Materials Conference, New York, American Institute of Aeronautics 23rd, New Orleans, LA, May 10-12, 1982, Collection of Technical and Astronautics, 1982, p. 427-438. 14 refs. Contract No. Papers. Part 2. New York, American Institute of F33615-80-C-3217. (AIAA 82-0724) Aeronautics and Astronautics, 1982, p. 530-541. 24 refs. (AIAA Optimal control techniques were applied to design the reduced 82-0735) order controllers for the purpose of aircraft flutter suppression and Results are presented of an analytical investigation on the load alleviation. Special attention was given to the multiple input, dynamic collapse of an elastic periodically supported column. The multiple output (MIMO) system, to which the classical feedback column has an attached mass at one end and impacts a rigid surface control theory cannot be conveniently applied. Using the optimal with prescribed velocity and angle of incidence at the other end. A control approach, a number of control laws were designed for the first-order approximate nonlinear analysis is developed in which it is YF-17 flutter suppression model. The relative performances of these assumed that only first-order nonlinear terms need be retained.

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Differential equations are derived and solved numerically by explicit cannot. Examples of persistent as opposed to short-period errors are time integration in order to determine specific ranges of the basic also discussed, with the two types for Mode C showing very similar nondimensional parameters for which the response characteristics are behavior. The airborne equipment was found to be at fault in all markedly different. To assess modeling sophistication relative to errors that cannot be explained as simple pulse code errors. The prediction accuracy, a comparison is made of the results from this introduction of Mode S will reduce the incidence of data errors. C.D. approximate analysis with those of a finite element computer code based on a convected coordinate formulation. C.D. A82-30313 Secondary radar for airborne collision avoid- ance. S. Ratcliffe. Journal of Navigation, vol. 35, May 1982, p. A82-30193 * If Subsonic aerodynamic and flutter character- 220-239. 14 refs. istics of several wings calculated by the SOUSSA P1.1 panel method. Cooperative collision avoidance systems, passive beacon collision E. C. Yates, Jr., H. J. Cunningham, R. N. Desmarais (NASA, Langley avoidance systems (BCAS), and active radar systems are discussed for Research Center, Hampton, VA), W. A. Silva, and B. Drobenko. civil aviation. The detection of collision risk is treated mathematical- AIAA. ASME, ASCE, and AHS, Structures, Structural Dynamics and ly. The trajectory of a possible threat as plotted in the range/range Materials Conference, 23rd, New Orleans, LA, May 10-12, 1982, rate phase plane is discussed, and the range/range-rate logic is AIAA Paper 82-0727. 20 p. 20 refs. quantitatively studied. Parameters are given for the sensitivity levels Several applications of the steady, oscillatory, and unsteady at which BCAS is operative. The use of height and height-rate data is subsonic and supersonic aerodynamics (SOUSSA) computer program described, and the operation of the collision avoidance system is to wings with steady and oscillatory motion, including flutter, are analyzed. Finally, the resolution advisory register, which ensures discussed. The program employs a generalized Green's function to compatibility between BCAS advisories, is discussed. C.D. the full, time-dependent potential-flow equation to obtain an integral equation for the velocity potential at any point in a flow, even points A82-30314 Magnetic anomalies as a reference for ground- on a body or whole bodies in a flow. Aerodynamic calculations are speed and map-matching navigation. C. Tyren. Journal of Navigation, provided for two rectangular wings, a clipped-tip delta wing, and two vol. 35, May 1982, p. 242-254. swept wings with and without a fuselage. The number and The use of the earth's magnetic field for ground referenced distribution of the finite element panels are varied in order to motion and position measurements is discussed. A magnetic terrain- demonstrate the convergence of the results. The results are shown to navigation concept is set forth, and its sensor configuration, data be close to those of lifting-surface theory, and further applications processing and data storage unit, and navigation data interface unit with bodies having deformities, arbitrary shapes, motions, and are discussed. The navigational accuracy of the system is assessed; deformations are indicated. M.S.K. one particular advantage of terrain navigation systems is that ground-speed accuracy is independent of vehicle speed until speeds A82-30294 A giant step toward composite helicopters. M. are reached at which the sensors and/or computer operations are too M. Schwartz and G. Jacaruso (United Technologies Corp., Sikorsky slow to track the vehicle path. The system is therefore excellent at Aircraft Div., Stratford, CT). American Machinist, Mar. 1982, p. low speeds and can advantageously be used for hovering operations. 133-140. The results of field tests indicate that the feasibility of both The design goals and performance achievements of the UH60A ground-speed and map-matching methods is indeed promising. C.D. Black Hawk helicopter Composite Rear Fuselage (CRF) structure's development are described, with emphasis on the use of computer- A82-30675 Aviation gear drives and reducers: Handbook assisted interactive design techniques and on the fabrication and (Aviatsionnye zubchatye peredachi i reduktory: Spravochnik). assembly methods used to produce this graphite-reinforced epoxy Edited by E. B. Vulgakov. Moscow, Izdatel'stvo Mashinostroenie, structure, which is 6 ft high, 8 ft wide, and 9 ft long. The metallic 1981. 376 p. In Russian. form of the rear fuselage is composed of 1203 parts, divided into 88 The book contains data on the geometry, kinematics, design, assemblies, with 17,000 fasteners. By contrast, the CRF comprises manufacture, and testing of aviation gear drives and reducers. In 459 detail parts, 23 assemblies and less than 6000 fasteners. Weight particular, consideration is given to the geometrical analysis of savings of 10% and manufacturing cost reductions of 30% have been involute cylindrical gear drives, gear drive strength and dynamics, demonstrated. Attention is given to the cutting and kitting of splined joints, analysis of torsional and flexural vibrations, and prepreg details, their preforming and pre-layup, frame and bulkhead computer-aided design of gear drives. Other topics discussed include fabrication, and the fabrication of the upper-center skin assembly. materials, chemical and heat treatment, tolerances, and quality O.C. assurance during the manufacture of gears, experimental testing techniques, and principal defects. Attention is also given to the A82-30311 Improvements to secondary radar for air traf- design of helicopter reduction gears, overrunning clutches, lubricants fic control. R. C. Bowes (Royal Signals and Radar Establishment, for reduction gears, and cost-effectiveness of dear manufacture. V.L. Malvern, Worcs., England). Journal of Navigation, vol. 35, May 1982, p. 193-204. Research supported by the Civil Aviation Authority. A82-30697 t Gas turbine engines used in aviation: Design The civil use of secondary surveillance radar (SSR), which is the and construction of components /5th revised and enlarged edition/ prime sensor for the control of the aircraft, is described. The use of (Aviatsionnye gazoturbinnye dvigateli: Konstruktsiia i raschet detalei SSR in air-traffic control is detailed, and comparisons with primary /5th revised and enlarged edition/). G. S. Skubachevskii. Moscow, radar are made. The prevention of sidelobe interrogations and the Izdatel'stvo Mashinostroenie, 1981. 552 p. 113 refs. In Russian. processing of SSR replies are explained. The two main types of The principles underlying the design of gas turbine engines are problems with SSR, self-interference effects and reflected signals, are expounded. The operating conditions of the various engine compart- discussed. Additional topics of discussion are monopulse direction ments, and parts thereof, are considered. Attention is also given to finding, which enables an accurate azimuth measurement to be manufacturing processes and the proper choice of materials. Exam- obtained from a single reply, and selective address SSR, which helps ples of calculations for determining the strength and vibration of the solve the SSR garble problem. C.D. principal engine components are included. C.R.

A82-30312 The reliability of height and identity data. H. A82-31048 Chem-Braze abradable seal practical. M. Levy Gent (Royal Signals and Radar Establishment, Malvern, Worcs., (U.S. Army, Army Materials and Mechanics Research Center, England). Journal of Navigation, vol. 35, May 1982, p. 204-219. Watertown, MA). ManTech Journal, vol. 6, no. 2, 1981, p. 9-12. Research sponsored by the Civil Aviation Authority. Army-supported research. The nature and extent of secondary surveillance radar (SSR) An improved Chem-Braze bonding system for attaching sintered errors are discussed with a description of the Mode A and Mode C abradable seals to titanium, steel, and nickel base compressor blade codes, and a concrete example of error is given. Investigation shows tip shrouds has been developed. The system incorporates glycerin to that short-period Mode C and Mode A errors are equally likely, each prevent premature evaporation which prolongs working life and occurring in about 1 plot in 5000, with neither airborne nor ground allows adequate time to attach abradable seals to engine hardware. equipment being wholly responsible. Pulse error counts are made for The system has demonstrated its viability with attachment involving both modes, and a comparison with garble shows that while the simple mechanical fixturing and curing and removal facilitiated by latter occurs more frequently, it can be anticipated while data errors chemical stripping, and all operations are relatively fast and

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inexpensive. Optimum inhibitor concentration was found to be 10 at a signal level of -133 dB. A total of 17 flight hours of tests with percent. Optimum drying time, cure cycle, proper chemical stripping civilian craft have been flown to test the system, with the helicopter technique, and inexpensive tooling techniques were also determined. tests covering the total system cross track error, the flight technical A preliminary cost analysis shows a 74 percent saving compared to error, and the along track error. Operational status is scheduled for attachment with gold-nickel braze. C.D. 1984. M.S.K.

A82-31057 Aircraft cabin air ozone contamination and A82-31426 H New materials fly better and cheaper. Mechan- compliance with regulations. J. F. Leach, G. R. Robinson (British ical Engineering, vol. 104, May 1982, p. 20-26. Aerospace Public Ltd.. Co., Filton, Avon, England), and F. J. The types of advanced, high-performance fibers and their Sandalls (Atomic Energy Research Establishment, Environmental advantages are described, and the process of forming composites is and Medical Sciences Div., Didcot, Oxon, England). Atmospheric outlined. The use of composites in present and future commercial Environment, vol. 16, no. 5, 1982, p. 1021-1026.9 refs. Research and military aircraft, including the Learfan 2100 and the Space supported by the Department of Transport/Department of the Shuttle Discovery, is discussed. Special attention is given to metallic Environment and Department of Industry. and ceramic materials of the future. C.D. Fifteen cabin air ozone measurements made in Concorde are ranked in order and plotted as log-normal and extreme value cumulative probability distributions. It is shown that the log-normal A82-31602 t The maximum flying range problem for an distribution gives adequate accuracy for regulatory purposes and aircraft (O zadache poleta letatel'nogo apparata na maksimal'nuiu one-sided tolerance limits may be used for statistical methods of dal'nost'). V. I. Borzov and T. R. Igonina. Akademiia Nauk SSSR, compliance with any regulatory limit. Similarly it is shown that Izvestiia, Mekhanika Tverdogo Tela, Mar.-Apr. 1982, p. 20-24. 5 refs. compliance by ozone destruction ratio may be difficult due to the In Russian. extreme stratification of ozone in the lower stratosphere. (Author) The maximum flying range problem is examined in terms of the motion of the center of mass of an aircraft in a vertical plane. By A82-31121 ,7 Optimal control and estimation for strapdown using methods based on the theory of differential equations with seeker guidance of tactical missiles. P. L. Vergez and J. R. singular perturbations, the maximum flying range problem is reduced McClendon (USAF, Armament Laboratory, Eglin AFB, FL). Journal to that of solving a boundary-value problem. The applicability of the of Guidance, Control, and Dynamics, vol. 5, May-June 1982, p. 225, proposed model is investigated, and the particular case of the 226. maximum flying range in gliding is examined. V.L. An extended Kalman filter is developed that explicitly accounts for the major error sources in a strapdown system and estimates the A82-31603 t Stability and self-oscillations of coaxial rotors state information required by an advanced guidance system. The (Ob ustoichivosti i avtokolebaniiakh soosnykh rotorov). E. L. selected guidance law is derived from linear quadratic Gaussian Pozniak. Akademiia Nauk SSSR, Izvestiia, Mikhanika Tverdogo Tela, theory, the only assumption being that the missile has instantaneous Mar.-Apr. 1982, p. 38-45. 9 refs. In Russian. response and complete control over its acceleration. The filter An analysis is presented of the stability and stable self- processes the noise from the strapdown seeker and estimates the oscillations induced by viscosity-type nonconservative forces in the information needed by the guidance law referenced to the missile's material of the shaft in a system of two coaxial rotors supported by a body-fixed coordinate system. A detailed six-degree-of-freedom rigid damped frame. The range of stability is studied as a function of simulation of a generic bank-to-turn short range air-to-air missile was the rotor velocities and directions and as a function of damping in used to evaluate the guidance and estimation algorithm developed for the bearings of the frame. A quasi-Galerkin method is used to the study. C.D. determine frequencies, amplitudes, and modes for single-frequency as well as multifrequency self-oscillations. The stability of the obtained A82-31125 * H Comment on 'Optimal control via mathemati- solutions is investigated. B.J. cal programming'. L. J. Wood (California Institute of Technology, Jet Propulsion Laboratory, Pasadena, CA). Journal of Guidance, A82-31643 t Effect of operating life on the mechanical Control, and Dynamics, vol. 5, May-June 1982, p. 318, 319; properties of the materials and load-bearirtg capacity of the rotor Authors' Reply, p. 319. 16 refs. Contract No. NAS7-100. elements of gas-turbine engines (Vliianie ekspluatatsionnoi narabotki na mekhanicheskie svoistva materialov i nesushchuiu sposobnost' A82-31179 Combat training imagery. Flight International, elementov rotorov GTD). V. L. Akhremenko (Akademiia Nauk vol. 121, Apr. 24, 1982, p. 1048-1050. UkrainskpjjSSR, Institut Problem^Prochnosti, Kiev, Ukrainian SSR). The CT-5 is a computer-generated image (CGI) using raster scan Problemy Prochnosti, Apr. 1982Tp~. 53-55. 5 refs. In Russian. that provides a daylight system design for sophisticated military Experiments have been conducted to investigate changes in the applications. The imagery includes a formation of F-16s, a CH-46 mechanical properties of turbine alloys EI698, EI961, EI437BUVD, helicopter, a KC-135, and a sea data-base. Backgrounds are realistical- and AL4 following long-term service under actual operating condi- ly depicted. The CT-5 uses a PDP-11 general-purpose minicomputer tions. It is found that ductility and impact toughness are most connected to the simulator computer and image processor, which sensitive to damage, whereas the load-bearing capacity of gas-turbine consists of the viewpoint processor and the channel processor. There rotors changes insignificantly in the course of service life and, is also a series of display processors, and scanline computation is therefore, cannot be used as a damage criterion. V.L. replaced by area computation. Extra channels and more display processors can be added. C.D. A82-31669 Distributed airborne array concepts. B. D. Steinberg (Pennsylvania, University, Philadelphia, PA) and E. Yadin A82-31290 The helicopter Navstar GPS test program. R. (Interspec, Inc., Philadelphia, PA). IEEE Transactions on Aerospace D. Till (FAA, Technical Center, Washington, DC). Vertiflite, vol. 28, and Electronic Systems, vol. AES-18, Mar. 1982, p. 219-227. 19 refs. May-June 1982, p. 22-25. Grant No. AF-AFOSR-78-3688. The use of the Navstar Global Positioning System (GPS) for The improvement in SNR and detection range due to dis- helicopter navigation is reviewed. The GPS system has a space tributing an antenna array throughout the airframe and skin of an segment with a contingent of 18-24 satellites in 12 hr circular orbits aircraft is examined. SNR formulas for three system configurations with 2 hr coverage by four satellites over selected areas, a user are presented and compared with that of a conventional, monostatic segment with a receiver/processer, and a control segment composed radar. Examples given in the paper show detection range increases as of four monitor stations. Ephemeris data on satellite location is large as a factor of 4. Three additional potential advantages of the relayed through the control segments to a Master Control station at distributed array are an increase in spatial signal processing capabil- Vandenberg AFB. The use of four satellites involves the solution of ity, an improvement in azimuthal resolution, and a potential four equations for three-dimensional requirements and for the user reduction in transmitter power for fixed radar performance so as to clock bias. Civilian use is thus far limited to a coarse/acquisition code reduce the probability of intercept. (Author)

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Avail: NTIS HC A04/MF A01: original report in FRENCH available at ONERA. Paris FF 45 A set of real time digital filters was used in a wind tunnel during testing of a transport aircraft model. The performance of the digital filters, programmed at various cutoff frequencies, was compared with that of analog filters already in use. Ten measuring channels, permitting computation of three aerodynamic STAR ENTRIES coefficients for the model, were recorded. The operating principle of the real time digital filters is described. Results confirm the interest of low pass filtering at a very low cutoff frequency for restoring static parameters while a model is performing an angle of attack sweep in continuous mode. Author (ESA) N82-22144# Royal Aircraft Establishment, Farnborough (England). THE ROYAL AIRCRAFT ESTABLISHMENT: 100 YEARS N82-22163# National Aerospace Lab.. Amsterdam (Netherlands). Div. of Structures and Materials. OF RESEARCH A. J. Smith 2 Oct. 1981 33 p refs Presented at 1981 REVIEW OF AERONAUTICAL FATIGUE INVESTIGATIONS Aviation Lighting Sem.. Williamsburg. Virginia. 9-13 Nov.. 1981: IN THE NETHERLANDS. MARCH 1979 - FEBRUARY 1981 sponsored by Illuminating Engineering Society of North America J. 8. deJonge Feb. 1981 43 p refs Presented at the 17th ICAF Conf.. Noordwijkerhout. Netherlands, 18-19 May 1981 (RAE-TM-FS-432; BR80894) Copyright. Avail: NTIS HCA03/MF (NLR-MP-81006-U) Avail: NTIS HC A03/MF A01 A01 The work of the Royal Aircraft Establishment (RAE) from its Reports on aeronautical fatigue investigations are reviewed. days as His Majesty's Balloon factory to modem times is The reports are cited in a subject index, covering: loads: flight summarized. Early setbacks to aircraft production included the simulation testing, procedures and evaluation: fatigue investiga- 1909 War Office declaration that the airplane had no military tions: prediction of crack initiation and crack propagation: damage value. The First World War changed this opinion and the interwar tolerance and residual strength: materials evaluation: inspection years saw an expansion which bore fruit in the development of methods and service failure analysis: fatigue of aircraft materials: the gyro gun sight, stabilized bomb sight and high speed aerial fatigue of laminates: fatigue of joints: and prediction of residual reconnaissance during World War 2. The tapered ladder effect strength of stiffened panels. Author (ESA) used in airfield approach lighting systems was developed after the war, along with subsonic and supersonic wind tunnels. Recent projects involving the RAE include Concorde, Earth resources N82-22154| Advisory Group for Aerospace Research and satellites, and head-up displays. Author (ESA) Development. Neuilly-Sur-Seine' (France). DYNAMIC ENVIRONMENTAL QUALIFICATION TECH- N82-22146# Office National d'Etudes et de Recherches NIQUES Aerospatiales. Paris (France). Dec. 1981 245 p refs Partly in ENGLISH: one in FRENCH LA RECHERCHE AEROSPATIALE. BI-MONTHLY BULLETIN Proceedings of the 53rd Meeting of the Structures and Mater. NUMBER 1981-6. SEPTEMBER - OCTOBER 1981 Panel. Noordwijkerhout. Netherlands. 27 Sep. - 2 Oct. 1981 Claude Sevestre. ed. ESA Feb. 1982 63 p refs Transl. into (AGARD-CP-318: ISBN-92-B35-0306-6) Avail: NTIS ENGLISH of La Rech. Aerospatiale. Bull. Bimestriel (Pan's). HC A11/MF A01 No. 1981-5. Sep. - Oct. 1981 Sponsored by ESA The state of the art of dynamic qualification techniques and (ESA-TT-725) Avail: NTIS HC A04/MF A01: original report test methods for military aircraft with external stores are reviewed, in FRENCH available at ONERA. Paris FF 45 including consideration of the rationale and interpretation of Advances in aerospace engineering are reviewed. Flow existing standards. The determination of environmental inputs theory and computation are considered. Signal processing from various sources and their application to specific aircraft algorithms are presented. Structural analysis of composite and store configurations, including helicopters, are covered. materials is discussed. Two wind tunnel investigations, helicopter Presentations were also given on the development of vibration rotor performance measurement and testing a digital filtering analysis techniques and the evaluation of possible improvements system, are also described. in prediction methods and establishment of criteria.

N82-22161# Office National d'Etudes et de Recherches N82-2215B# Air Force Wright Aeronautical Labs., Wright- Aerospatiales, Paris (France). Patterson AFB, Ohio. Combined Environments Test Group. HELICOPTER ROTOR PERFORMANCE IMPROVEMENT BY DEVELOPMENT AND USE OF DYNAMIC QUALIFICATION UTILIZATION OF SWEPT-BACK PARABOLIC BLADE TIP STANDARDS FOR AIR FORCE STORES Alan H. Burkhard and Otto F. Maurer In AGARD Dyn. Environ. J. J. Philippe and P. Lafon In its La Rech. Aerospatiale. Bi-monthly Qualification Tech. Dec. 1981 7 p refs Bull. No. 1981-5. Sep. - Oct. 1981 (ESA-TT-725) Feb. 1982 see N82-22154 13-01) p 55-56 refs Transl. into ENGLISH of La Rech. Aerospatiale, Avail: NTIS HC A11/MF A01 Bull. Bimestriel (Paris), No. 1981-5. Sep. - Oct. 1981 The cataloging and standardization act for the standardization of items, materials, and engineering practices in the defense Avail: NTIS HC A04/MF A01: original report in FRENCH industry is discussed. Formal procedures for generating, updating, available at ONERA. Paris FF 45 and utilization of these documents are presented. The advantages A sweptback parabolic tip was designed so as to improve of standardization leading to simplification of procurement, the working conditions of an advancing blade by reducing the development, and production processes by fostering uniformity, intensity of the shock waves which arise and the drag associated direct comparability, interchangeability of standardized objects with such shocks. The design is based on the computated pressure are outlined. The state of the art of test techniques and procedures distribution on a helicopter blade in the fundamental case of a are considered. E.A.K. nonlifting rotor. The results of the computations clearly show the advantages of using this geometry for a rotor blade tip. Results of tests on such tips, performed in a wind tunnel on a N82-22168# British Aerospace Aircraft Group, Preston (England). three bladed rotor, demonstrate an overall improvement in the Specialist Functions, Stress Office. performance of the rotor. Author (ESA) QUALIFICATION OF EQUIPMENT FOR GUNFIRE INDUCED VIBRATION N82-22162# Office National d'Etudes et de Recherches A. Peacock In AGARD Dyn. Environ. Qualification Tech. Dec. Aerospatiales, Paris (France). 1981 22 p refs REALTIME DIGITAL FILTERING TEST IN THE 81 CONTIN- Avail: NTIS HC A11/MF A01 UOUS WIND TUNNEL AT MODANE A method to ensure that the Tornado MK1 aircraft equipment J. Appel In its La Rech. Aerospatiale, Bi-monthly Bull. withstand gunfire induced vibrations is described. The derivation No. 1981-5. Sep. - Oct. 1981 (ESA-TT-725) Feb. 1982 p 57-61 of test spectra from rig and aircraft measurements is explained. ref Transl. into ENGLISH of La Rech. Aerospatiale, Bull. Bimestriel Test failures and in-service malfunctions are reviewed. A (Paris). No. 1981-5. Sep. - Oct. 1981 comparison with Mil specification is made. E.A.K.

343 N82-22159

N82-22169# General Dynamics/ Fort Worth. Tex. A dynamic qualification test for a subsonic and a supersonic DYNAMIC QUALIFICATION TESTING OF F-16 EQUIP- external drop tank for a European fighter is presented. The test MENT rig and the specimens are described and the measuring results H. E. Nevius and W. J. Brignac In AGARD Dyn. Environ. are discussed. It is shown that for the supersonic tank as well Qualification Tech. Dec. 1981 15 p as for the subsonic tank a certain slosh angle an eigenfrequency of the rig increases the amplitudes at the excitation position Avail: NTIS HC A11/MF A01 and the accelerations on the tank. For the subsonic tank it seems Vibration prediction methods and qualification test pro- that an eigenfrequency is excited for the nose down position of cedures are presented for F-16 equipment. Measured vibration the tank. The qualification requirements are examined. It is levels are also compared to the predictions. The most severe proposed that instead of using an arbitrary vibration amplitude vibratory environment is produced by the muzzle blast pressure and frequency for excitation, frequency ranges and amplitudes during gunfiring. Gunfiring vibration was measured during the which are averaged out of flight measurements at the tank YF-16 prototype program which indicated a correlation between attachment points on the aircraft be used and that the demand vibration levels and distance from the gun port. Vibration data for a certain input amplitude at the top of the attachment bulkheads are presented verifying this relationship. Nongunfiring random and an output amplitude at the bottom of the attachment vibration test levels are shown for F-16 airframe zones. The bulkheads be deleted. E.A.K. prediction procedures were based on a relationship between vibration and dynamic pressure using measured data from other N82-22166# Army Aviation Research and Development aircraft. Vibration levels were measured on fuselage mounted Command. St. Louis. Mo. Structures and Aeromechanics Div. stores. Other measured dynamic environments are presented which THE STRUCTURAL DYNAMIC INTERFACE REQUIRED FOR include wing tip missile response to store ejection from wing DEVELOPING HELICOPTER TARGET ACQUISITION pylons and to jet wake encounter, and buffet response at SYSTEMS high-angles-of-attack. Author Sam f. Crews In AGARD Dyn. Environ. Qualification Tech. Dec. 1981 9 p refs N82-22160# McDonnell-Douglas Corp.. St. Louis. Mo. Structural Avail: NTIS HC A11/MF A01 Dynamics Sect. A brief description of the helicopter vibration environment DEVELOPMENT OF VIBRATION QUALIFICATION TEST is given. Two development programs were used as examples to SPECTRA FOR THE F-16 AIRCRAFT show how vibration sensitive target acquisition systems can be G. R. Waymon In AGARD Dyn. Environ. Qualification Tech. interfaced to a helicopter. The systems are the Target Acquisition Dec. 1981 19 p refs Data System/Pilot Night Vision System mounted to the nose of the Army's new Advanced Attack Helicopter and the Stand-Off Avail: NTIS HC A11/MF A01 Target Acquisition System mounted underneath the Army's BLACK The vibration test spectra used for an F-15. Eagle were based HAWK helicopter. The qualification strategy and specific testing on analytical predictions combined with measured data from performed and to be performed are included. Author similar aircraft. The low frequency vibration below approximately 50 Hertz results primarily from aircraft response to gusts, buffet, landing, and taxi excitation. Vibration at higher frequencies is N82-22166| Messerschmitt-Boelkow-Blohm G.m.b.H., Munich primarily associated with acoustical excitation and gunfire. The (West Germany). airplane was divided into regions of comparable vibration levels. APPROACH IN DYNAMIC QUALIFICATION OF LIGHT The test levels were derived using the predicted spectra and HELICOPTER STORES AND EQUIPMENTS applying factors to define a performance and an endurance test. D. Braun and J. Stoppel In AGARD Dyn. Environ. Qualification The F-15 flight measured data were used to update these Tech. Dec. 1981 8p refs predictions for the present test spectra. Author Avail: NTIS HC A11/MF A01 N82-22161# British Aerospace Aircraft Group. Kingston-upon- Problems occurring in connection with the dynamic qualifica- Thames (England). tion of equipment and external stores for light military helicopters EQUIPMENT VIBRATION QUALIFICATION FOR HARRIER are evaluated. Special features of the helicopter vibratory AND HAWK AIRCRAFT environment are discussed. Some general recommendations for D. C. Thorby In AGARD Dyn. Environ. Qualification Tech. the procedure of dynamic qualification for use with helicopters Dec. 1981 7 p refs are given. The approach for dynamic qualification of relatively heavy equipment is presented using the example of combining Avail: NTIS HC A11/MF A01 the MBB BO 105 helicopter with HOT anti-tank missile launchers. Equipment for later versions of the Harrier and all versions To obtain a basic understanding of the dynamic behavior of the of the Hawk aircraft were cleared for flight vibration using test helicopter with external stores preliminary dynamic calculations procedures based on the current British Standard. The rationale were made. Shake tests were done with the separated external used in applying this Specification, and the flight vibration test stores and flight test vibration measurements were obtained. procedures are briefly outlined from a practical viewpoint.Author Test results are presented with regard to the harmonic main rotor excitation. M.D.K. N82-22162# Industrieanlagen-Betriebsgesellschaft m.b.H . Ottobrunn (West Germany). ACOUSTIC NOISE TEST AS PART OF THE DYNAMIC N82-22167# Westland Helicopters Ltd.. Yeovil (England). QUALIFICATION PROGRAM IN AEROSPACE Dynamics Dept. G. Bayerdoerfer In AGARD Dyn. Environ. Qualification Tech. THE DYNAMIC QUALIFICATION OF EQUIPMENT AND Dec. 1981 7 p EXTERNAL STORES FOR USE WITH ROTARY WINGED Avail: NTIS HC A11/MF A01 AIRCRAFT The mechanisms of noise generation for the purpose of G. M. Venn In AGARD Dyn. Environ. Qualification Tech. Dec. acoustic qualification tests are described. Special emphasis is 1981 11 p given to the modal density of acoustic noise fields in enclosures, Avail: NTIS HC A11/MF A01 such as reverberation chambers. A test program shows that for The dynamic regime imposed on helicopter-borne stores and small components a sufficient modal density can be achieved in equipment, highlighting the differences between the rotary and relatively small test chambers. Where applicable small chambers fixed-wing environments are outlined. The need for helicopter are favorable because of the lower test costs. Author requirements to be addressed in particular is discussed. The influence of a number of contributory factors to the dynamic N82-22164j? Vereinigte Flugtechnische Werke-Fokker G.m.b.H.. environment arising from varying military applications covering Bremen (West Germany). Abt. Dynamik/Aeroelastik. both land and sea operation is also discussed. The dynamic AIRCRAFT FUEL TANK SLOSH AND VIBRATION TEST criteria for design and testing are given, explaining the particular influence of discrete sinusoidal forcing on the helicopter Helmut Zimmermann In AGARD Dyn. Environ. Qualification environment. The evolution of these standards and their Tech. Dec. 1981 11 p consolidation through flight and service experience is explained. Some views on the future development of dynamic qualification Avail: NTIS HC A11/MF A01 criteria for rotary-winged aircraft are also outlined. M.D.K.

344 N82-22177

N82-22168# Deutsche Forschungs- und Versuchsanstalt fuer MAINTENANCE IN SERVICE OF HIGH TEMPERATURE Luft- und Raumfahrt. Goeningen (West Germany). Inst. of PARTS Aeroelasticity. Jan. 1982 162 p refs Meeting held at Noordwijkerhout. APPUCATION OF MODAL SYNTHESIS TECHNIQUES FOR Netherlands. 27 Sep. - 2 Oct. 1981 THE DYNAMIC QUALIFICATION OF WINGS WITH (AGARD-CP-317) Avail: NTIS HC A08/MF A01 STORES The problem areas in the inspection, repair, and life exten- E. Breitbach In AGARD Oyn. Environ. Qualification Tech. Dec. sion and prediction of gas turbine engine parts are addressed. 1981 22 p refs Avail: NTIS HC A11/MF A01 Dynamic qualification as well as flutter clearance of modem N82-22173# Ministry of Defence. London (England). combat aircraft were studied using modal coupling methods. MILITARY MAINTENANCE POLICIES AND PROCEDURES Emphasis was placed on how to deal with special phenomena FOR HIGH-TEMPERATURE PARTS. WILL THEY BE due to nonlinearities. in particular combinations of backlash and ADEQUATE? dry friction, in the connecting parts between wing, pylon and R. B. G. Hedgecock In AGARD Maintenance in Sen/, of High store which may significantly infringe on the validity of the linear Temp. Parts Jan. 1982 7 p refs mathematical models as used in ground and flight vibration testing. M.D.K. Avail: NTIS HC A08/MF A01 The problems involved in developing engine parts maintenance N82-22169jp Boeing Military Airplane Development. Seattle. policies which incorporate life estimation, inspection, repair and Wash. Structural Dynamics Dept. containment of costs are examined. Computer-based engine usage STOL AIRCRAFT STRUCTURAL VIBRATION PREDICTION monitoring systems and a low cycle atigue counter are described FROM ACOUSTIC EXCITATION along with assembled and unassembled engine inspection B. F. Dotson and J. Pearson (AFWAL) In AGARD Dyn. Environ. procedures and repair techniques. M.G. Qualification Tech. Dec. 1981 20 p refs N82-22174# Dayton Univ., Ohio. Graduate Materials Avail: NTIS HC A11/MF A01 Engineering Program. A method was developed to improve environment vibration ENGINE DEPOT MAINTENANCE REPAIR TECHNOLOGY prediction methods, particularly in the lower frequency range James A. Snide and William J. Schulz (AFWAL) In AGARD where high acoustic excitation is expected on STOL aircraft. A Maintenance in Serv. of High Temp. Parts Jan. 1982 19 p rigorous mathematical spectral analysis approach was used which refs simulated the structure with finite element models (FEM) and Avail: NTIS HC A08/MF A01 used measured and calculated acoustic input data for the forcing The scope and mission of the two USAF engine Air Logistics function. Calculated and measured vibrations levels were Centers are described. The various processes and organizational compared on a medium sized Upper Surface Blowing (USB) structure to identify repair technology requirements are discussed. STOL aircraft. The development of a method for prediction of Approaches to transition and implementation of new technology the external acoustic environment of USB flap-type STOL aircraft into a repair depot environment are described. Specific exam- was also accomplished. The method compares favorably with ples of technology developments described are: braze repair, laser actual measurements and represents a significant improvement metrology, electrophoretic, coatings, sputtered MCrAlY overlay in acoustic prediction methods for aircraft with USB type flaps. coating and inlet guide vane vibration damping. Author The method includes scaling factors for engine size, thrust, aircraft size, and other parameters. Finally, noise and vibration levels N82-2217B# Naval Aircraft Materials Lab.. Fleetlands (England). were predicted on a small STOL aircraft and later compared to measured data. Author MAINTENANCE PROBLEMS IN GAS TURBINE COMPO- NENTS AT THE ROYAL NAVAL AIRCRAFT YARD. FLEET- LANDS N82-22170# Royal Aircraft Establishment, Farnborough F. J. Plumb In AGARD Maintenance in Serv. of High Temp. (England). Aerodynamics Dept. Parts Jan. 1982 13 p refs GUNFIRE BLAST PRESSURE PREDICTIONS R. M. Munt. A. J. Perry, and S. A. Moorse In AGARD Dyn. Avail: NTIS HC A08/MF A01 Environ. Qualification Tech. Dec. 1981 20 p refs The work of the engine repair facility at Fleetlands and the major problems found in the overhaul and repair of helicopter Avail: NTIS HC A11/MF A01 and marine gas turbines are discussed. Remedies for component A scheme for predicting the blast pressures from aircraft reserviceability. developments to obtain longer service lives, and guns is presented which extends existing theory. The predictions the techniques employed are discussed. Author correlate well with some experimental measurements of gun blast pressures in free space. Blast pressures were also measured N82-22176# KLM Royal Dutch Airlines, Amsterdam (Nether- experimentally on a surface in the vicinity of the muzzle of a lands). Propulsion Systems Dept. 7.62 mm rifle but these could only be satisfactorily predicted in MAINTENANCE EXPERIENCE WITH CIVIL AERO EN- regions where the classical theory of regular reflection of shock waves could be applied. These results are discussed in relation GINES J. Ph. Stroobach In AGARD Maintenance in Serv. of High to the surface blast pressures from aircraft mounted guns. Temp. Parts Jan. 1982 3 p Author Avail: NTIS HC A08/MF A01 N82-22171# Grumman Aerospace Corp., Bethpage, N.Y. The trends in high temperature parts maintenance concept DEVELOPMENT OF A TAPED RANDOM VIBRATION developments are reviewed, indicating the constant activities to TECHNIQUE FOR ACCEPTANCE TESTING optimize the maintenance cost of the propulsion system. As a John Devitt, Richard Pokallus, Joseph Popolo, and Eugene Baird result of the escalating trends in material and fuel prices, the In AGARD Dyn. Environ. Qualification Tech. Dec. 1981 6 p presently applied maintenance concepts require a more sophisti- cated condition control in order to comply with the need to find Avail: NTJS HC A11/MF A01 the optimum operating time of each individual engine. With the The use of random vibration as a screen for latent workman- introduction of the new generation of civil aircraft (Airbus A310) ship problems normally found in avionic equipment, proved to a mutual goal between the engine manufacturer and the airline be significantly more effective than the sinusoidal form of excitation was defined to develop mathematical programs, based on normally employed. This was demonstrated and is now required actual recorded conditions, in order to control the behavior of for acceptance testing by various DoD agencies. The results of the engine, aiming at an optimum use of the propulsion a program to develop an economical technique for generating system. M.G. random vibration utilizing an audio tape deck indicate that compensating factors can be developed to account for the variations that exist in generically identical equipment. Using N8222177# Pratt and Whitney Aircraft Group. West Palm these factors, synthetic random tapes were generated. Author Beach. Fla. Government Products Div. ENGINE COMPONENT RETIREMENT FOR CAUSE N82-22172# Advisory Group for Aerospace Research and J. A. Harris. Jr.. C. G. Annis. Jr.. M. C. VanWanderham. and D. Development. Neuilly-Sur-Seine (France). L. Sims In AGARD Maintenance in Serv. of High Temp. Parts

345 N82-22178

Jan. 1982 9 p refs procedures is a guarantee of reliability and a knowledge of the stresses that occur during operation. A.R.H. Avail: NTIS HC A08/MF A01 An engine part retirement for cause (RFC) procedure is N82-22187# Advisory Group for Aerospace Research and discussed which would allow safe utilization of the full life capacity Development. Neuilly-Sur-Seine (France). of each individual component. Since gas turbine rotor components COMBAT AIRCRAFT MANOEUVRABILITY are prime candidates and are among the most costly of engine Dec. 1981 242 p refs In ENGLISH and FRENCH Proceedings components, adoption of a RFC maintenance philosophy could of the Flight Mechanics Panel Symp., Florence, 5-8 Oct. 1981 result in substantial engine systems life cycle cost savings. Two (AGARD-CP-319: ISBN-92-835-0304-X) Avail: NTIS major technical disciplines must be developed and integrated to HC A11/MF A01 realize these cost savings: fracture mechanics and nondestructive The symposium reviewed the operational requirements for evaluation. The methodology and development activity required combat aircraft maneuverability, technical prospects for maneuver- to integrate these disciplines that provide a viable RFC system ability improvements, and prediction and assessment methods for use on military gas turbine engines is discussed. The potential and their value. economic benefits of its application to a current engine system are also illustrated. M.G. N82-22188# Service Techniques des Programmes Aeronauti- ques. Paris (France). Section Etudes Generalles. N82-22178jjl Rolls-Royce Ltd., Derby (England). Dept of A REVIEW OF RECENT AGARD SYMPOSIA ON THE ANGLE Materials Engineering. OF MANEUVERABILITY OF COMBAT AIRCRAFT [RETRO- DEFECTS AND THEIR EFFECT ON THE BEHAVIOR OF GAS SPECTIVE DE REGENTS SYMPOSIUMS AGARD SOUS TURBINE DISCS L'ANGLE DE LA MANOEUVRABIUTE DES AVIONS DE Robert H. Jeal In AGARD Maintenance in Serv. of High Temp. COMBAT] Parts Jan. 1982 15 p Jean-Michel Due (Service des Recherches/Groupe 6) and Michel Vergne In AGARD Combat Aircraft Maneuverability Dec. 1981 Avail: NTIS HC A08/MF A01 50 p refs In FRENCH Unless the method used to life fatigue critical components like gas .turbine discs allows assessment of defect presence and Avail: NTIS HC A11/MF A01 behavior, the risk of serious failure is dramatically increased. A method is discussed where defect behavior can be assessed as The notion of maneuverability, in terms of flight mechanics, part of a total life approach to disc behavior prediction and is as it was treated at meetings of the Fluid Dynamics and Fluid explained together with the effects of differing defect types. Such Mechanics Panels during the past ten years is reviewed. Each an approach gives realistic manufacturing standards and controls point discussed is illustrated by graphics taken from previously and leads directly to an 'on condition life' approach. Author cited AGARD proceedings. Operational needs, hopes for improvement, methods for prediction, and methods for evalua- tion of flight qualities at high incidence are examined. A.R.H. N82-22180# Office National d'Etudes et de Recherches Aerospatiales. Paris (France). N82-22189| Royal Netherlands Air Force. Soesterberg THE INFLUENCE OF PROTECTIVE TREATMENT ON THE REVIEW OF PRACTICAL EXPERIENCE ON COMBAT MECHANICAL PROPERTIES OF SUPERALLOY PARTS AIRCRAFT MANEUVERABILITY [INFLUENCE DES TRAITEMENTS DE PROTECTION SUR A. W. Henni In AGARD Combat Aircraft Maneuverability Dec. LES PROPRIETES MECANIOUES DES PIECES EN SUPER- 1981 8 p ALLIAGE] Avail: NTIS HC A11/MF A01 J. M. Hauser, C. Duret. and R. Pichoir In AGARD Maintenance Based upon practical experience in both air to air and air in Sen/, of High Temp. Parts Jan. 1982 11 p refs In to ground operations with F-84F. F-104G. and NF-5 fighter FRENCH aircraft, an assessment is given of the importance of combat Avail: NTIS HC A08/MF A01 aircraft maneuverability. In air to ground operations the effect The high temperature environment of aircraft turbine of limited maneuverability on tactics is treated in terms of engines requires the use of protective coatings for engine parts. speed/altitude and maneuverability requirements during ingress/ These coatings are particularly necessary when the composition egress and weapon delivery, in relation to attack effectiveness of the superalloys used and associated heat treatment are chosen and survivabtlity against enemy defenses. For air to air operations in order to obtain the best mechanical properties. The durability the parameters that influence the outcome of a maneuvering of these components is determined not only by the mechanical flight are identified. The relation between maneuverability and properties of the protected heat resistance alloys, but equally by tactics is discussed. It is concluded that the impact of maneuver- the resistance of the coating to oxidation and corrosion. To restore iabilty on mission effectiveness becomes less prominent at this protection can pose diverse problems and, in certain cases, increasing total number of air to air capable aircraft, fighting in constitute an additional factor in reducing fatigue life. These a limited airspace. Dependent on the type of operation, desirable aspects are considered and illustrated by results obtained from improvements in maneuverability are discussed with emphasis aluminium coatings applied to IN 100 and IN 738LC superal- on turn performance (at low speeds), rapid speed changes and loys. Factors inherent i to t elaboration of the protection are direct force generation. In this context human tolerance limits also considered. Transl. by A.R.H. are taken into account. It is stressed that the main problems confronting a fighter pilot in the Central European environment N82-22185# Motoren- und Turbinen-Union Muenchen G.m.b.H. are not related to maneuverability but to the availability of (West Germany). military subsystems. M.G. REPAIR AND REGENERATION OF TURBINE BLADES. VANES AND DISCS N82-22190f Naval Air Systems Command. Washington. D. C. H. Huff and J. Wortmann In AGARD Maintenance in Serv. of THE MILITARY FLYING QUALITIES SPECIFICATION. A High Temp. Parts Jan. 1982 7 p refs HELP OR A HINDRANCE TO GOOD FIGHTER DESIGN

Avail. NTIS HC A08/MF A01 Ralph C. AHarrah and Robert J. Woodcock (AFWAL. Wright- The repair of incipiently cracked turbine components is Patterson AFB, Ohio) In AGARD Combat Aircraft Maneuverability essentially limited to non-rotating parts. Repairs to rotating parts Dec. 1981 13 p refs are carried out on low-stressed areas, such as seals, only. In this case, weld build-up has proved to be a suitable process. Avail: NTIS HC A11/MF A01 Stator vanes can be high-temperature brazed following reduction Based on experience with Air Force and Naval aircraft, the annealing. However, problems are encountered when it comes current qualities specification is evaluated for application to a to making sure of the complete removal of oxides. A highly future fighter design. Analog and digital fly by wire flight control promising method for increasing the reliability of turbine blades system having multiple redundancy levels and significant control that have been in service lies in their regeneration by heat law variation are discussed. Some specific observations are shared treatment or HIP-processing. Results to date are so positive on the following topics with regard to the flying qualities in that the use of regenerated blades may be a reality in the near general and the specification in particular time delays, force future. However, a prerequisite for the use of these repair commands, forward loop integration, high gains, signal blending.

346 N82-22198 equivalent systems, pilot location, high angle of attack, roll TECHNOLOGY performance, and systems integration. In addition, some general M. E. Waddoups and C. A. Anderson In AGARD Combat observations are made on the use of MIL-P-8785B. and a Navy Aircraft Maneuverability Dec. 1981 4 p conducted survey on the effectiveness of the flying qualities specification is discussed. M.G. Avail: NTIS HC A11/MF A01 Two seemingly exclusive requirements, low cost tactical N82-22191f Systems Technology, Inc.. Hawthorne. Calif. fighters and night under the weather operations, are being merged DEVELOPMENT OF A TENTATIVE FLYING QUALITIES by means of advanced technology. The key operational problem CRITERION FOR AIRCRAFT WITH INDEPENDENT CON- is forced by the extremely difficult timeline for low altitude, TROL OF SIX DEGREES OF FREEDOM: ANALYSIS AND high speed, air to surface weapon delivery. The inherent economy FLIGHT TEST of single seat operation can be developed by automation. The Roger H. Hoh, Thomas T. Myers, and Irving L Ashkenes In key technological problems are caused by the lack of volume in AGARD Combat Aircraft Maneuverability Dec. 1981 12 p a small fighter. In order to achieve automation of the required refs tasks, flight path control and sensor interfaces must be developed. (Contract F33615-78-C-3616) Based upon emerging hardware and software technology, flight Avail: NTIS HC A11/MF A01 control and avionic subsystems can be optimized and integrated A tentative flying qualities specification for aircraft having to achieve capability previously unavailable to small fighters. direct force effectors that allow independent control over the RJ.F. horizontal and vertical degrees of freedom is presented. Since the primary problem with developing flying qualities for such N82-22196# Royal Aircraft Establishment. Farnborough aircraft is their unconventional responses as reflected in a very (England). Flight Systems Dept. incomplete data base. A limited flight test of a direct force ENHANCED PILOTING CONTROL THROUGH COCKPIT control (OFC) aircraft was performed. The requirements are based FACILITIES AND A.C.T. on fundamental aspects of OFC pilot/vehicle dynamics to insure D. J. Walker (British Aerospace P.L.C.. Brough. U.K.) and P. W. universal applicability. A bandwidth hypothesis is described J. Fullam In AGARD Combat Aircraft Maneuverability Dec. which makes the fundamental assumption that the primary factor 1981 6p refs in the pilot's evaluation of a DFC mode is his ability to exert Avail: NTIS HC A11/MF A01 tight control to minimize errors and thereby achieve improved Total loop control, advanced cockpits, and other aspects of closed loop tracking performance. The bandwidth is a measure advanced flight control technology are discussed. General of the maximum frequency at which such closed loop tracking maneuvering, force sidestick, depressed roll axis, a nonlinear pitch can take place without threatening stability. It follows that controller and carefree maneuvering are discussed. RJ.F. airplanes capable of operating at a large value of bandwidth will have superior performance. M.G. N82-22196*# National Aeronautics and Space Administration. N82-22192| Dormer-Werke Gm.b.H. Friedrichshafen (West Langley Research Center. Hampton, Va. Germany). THE DEVELOPMENT OF CRYOGENIC WIND TUNNELS AND EXPERIMENTAL FLIGHT TEST PROGRAMS FOR IMPROV- THEIR APPLICATION TO MANEUVERING AIRCRAFT ING COMBAT AIRCRAFT MANEUVERABILITY BY MANEU- TECHNOLOGY VER FLAPS AND PYLON SPLIT FLAPS E. C. Polhamus and R. F. Boyden In AGARD Combat Aircraft D. Jacob. D. Welte, and H. Wonnenberg In AGARO Combat Maneuverability Dec. 1981 12 p refs Aircraft Maneuverability Dec. 1981 11 p refs Avail: NTIS HC A11/MF A01 Avail: NTIS HC A11/MF A01 The cryogenic wind tunnel and its potential for advancing Two flight test programs with the Alpha-Jet as test vehicles maneuvering aircraft technology is discussed. A brief overview are described. In the first program the standard wing of the of the cryogenic wind tunnel concept and the capabilities and aircraft was replaced by a transonic wing with maneuver flaps. status of the Langley cryogenic facilities is given, as is a review Wind tunnel and flight test results are presented which show of the considerations leading to the selection of the cryogenic the increase in performance and maneuverability based on the concept such as capital and operating costs of the tunnel, model improved drag polars and buffet limits. In the second program and balance construction implications, and test condition. pylon split flaps were to provide flat turn and side step maneuvers Typical viscous, compressibility and aeroelastic effects encountered by an alternating deflection of the four left or right split flaps. by maneuvering aircraft are illustrated and the unique ability of A drag modulation mode is ralized by symmetrical deflection of the cryogenic wind tunnels to isolate and investigate these all eight flaps. M.G. parameters while simulating full scale conditions is discussed. The status of the Langley cryogenic wind tunnel facilities is reviewed and their operating envelopes described in relation to N82-22193*# Purdue Univ., Lafayette, Ind. School of maneuvering aircraft research and development requirements. The Aeronautics and Astronautics. status of cryogenic testing technology specifically related to aircraft MULTIVARIABLE CLOSED LOOP CONTROL ANALYSIS AND maneuverability studies including force balances and buffet SYNTHESIS FOR COMPLEX FLIGHT SYSTEMS measurement techniques is discussed. Included are examples of David K. Schmidt In AGARD Combat Aircraft Maneuverability research carried out in the Langley 0.3 meter transonic cryogenic Dec. 1981 13 p refs wind tunnel to verify the various techniques. RJ.F. (Grants NAG4-1: AF-AFOSR-0042-72) Avail: NTIS HC A11/MF A01 N82-22197| Institut de Mecanique des Fluides de Lille (France). A flight control system analysis and synthesis method is STATE OF THE ART AND RECENT PERSPECTIVES ON presented that is intended to be especially suitable for application THE STUDY OF THE LOSS OF CONTROL AND SPIN [ETAT to vehicles exhibiting complex dynamic characteristics. For such DE L'ART ET PERSPECTIVES NOUVELLES RELATIVES A vehicles quantitative handling qualities specifications are not L'ETUDE DE LA PERTE DE CONTROLE ET DES VRILLES] usually available. Howver. handling qualities objectives are specifically introduced in this method via the hypothesis of M. G. Vanmansart and D. R. Tristrant In AGARD Combat correlation between pilot ratings and the objective function of Aircraft Maneuverability Dec. 1981 18 p refs In FRENCH; an optimal control model of the human pilot. Further, since ENGLISH summary augmentation and pilot operate in parallel, simultaneous determi- nation of the augmentation and pilot model gains is required. Avail: NTIS HC A11/MF A01 Desirable augmented dynamics are obtained for a variety of Some experimental and analysis methods which contribute complex systems and the method is experimentally verified in to aircraft behavior prediction at high angles and during stall-spin the case of simple pilot damper gain selection for optimum pitch are discussed. A brief review of the methods, their limitations tracking performance. M.G. and the expected results, is given, illustrated with a few examples. RJ.F. N82-22194| General Dynamics/ Fort Worth. Tex. Engineering Div. INTEGRATION OF AVIONICS AND ADVANCED CONTROL N82-22198# Office National d'Etudes et de Recherches

347 N82-22199

Aerospatiales. Paris (France). providing of adequate nose down pitch acceleration in the angle APPUCATION OF THE THEORY OF BIFURCATIONS TO of attack region near maximum lift. The aft center of gravity THE STUDY OF THE LOSS OF CONTROL IN COMBAT limits for both tailless and canard configurations without pitch AIRCRAFT [APPLICATION DE LA THEORIE OS BIFURCA- thrust vectoring were required to be forward of the optimum TIONS A L'ETUDE DES PERTES DE CONTROLE SUR AVION location for minimum subsonic maneuver trim drag. The aft tail DE COMBAT] configuration was not limited in this manner. In addition it could Phillipe Guicheteau In AGARD Combat Aircraft Maneuverability attain a higher subsonic maximum lift. It also had a greater Dec. 1981 13 p refs In FRENCH • design flexibility since the aft center of gravity limit could be influenced by the tail area. For these reasons it was the preferred Avail: NTIS HC A11/MF A01 configuration. B.W. Aircraft motion can be described in a rigorous manner by a nonlinear differential system, depending on parameters, joining N82-22202# Avions Marcel Dassault-Breguet Aviation. variables of state (incidence, side-slip, speed ...) and variable Saint-Cloud (France). control (positioning of rudders) by means of equations of flight EVALUATION OF AIRCRAFT IN SIMULATED COMBAT: mechanics and an aerodynamic model. The proposed method COMPUTER AGAINST COMPUTER OR COMPUTER consists of determining the stability limits of the system, and of AGAINST HUMAN PILOT [EVALUATION D'AVIONS EN predicting the evolution of that which becomes unstable. It is COMBAT SIMULE CALCULATEUR CONTRE CALCULATEUR based on the theory of bifurcation of nonlinear differential OU CALCULATEUR CONTRE PILOTE HUMAIN] systems. A.R.H. J. Pedotti and Y. Hignard (Centre Electronique de I'Armement) In AGARD Combat Aircraft Maneuverability Dec. 1981 14 p N82-22199j? Vought Corp.. Dallas. Tex. • Aerodynamics Div. refs In FRENCH PREDICTIONS OF AERODYNAMIC CHARACTERISTICS OF Avail: NTIS HC A11/MF A01 HIGHLY MANEUVERABLE CONFIGURATIONS A program was developed for simulating one aircraft in W. B Brooks and T. D. Beatty In AGARD Combat Aircraft combat with another. The adaptive logic of aerial maneuvers Maneuverability Dec. 1981 6 p refs (LAMA) program was validated by theoretical studies and by pilot/model tests on the CELAR simulator. The program permits Avail: NTIS HC A11/MF A01 either an entirely numerical model or a simulation of interactive The ability of a variety of currently available methods to hostility against a pilot on a simulator. Not only does the program predict the lateral/directional characteristics of arbitrary configura- provide a means for studying new weapons systems, it also tions is discussed. The programs surveyed generally had either provides a hostile performer for training pilots. A.R.H. nonlinear or arbitrary body capability, but not both. Published comparisons between the hypersonic arbitrary body program and experimental data suggested a direct extension of the commonly N82-22203# Grumman Aerospace Corp., Bethpage, N.Y. used Allen-Jorgenson cross flow analogy to arbitrary bodies. Research Dept. Though useful, this extension of the Allen-Jorgenson method THE ASSESSMENT OF AIRCRAFT COMBAT EFFECTIVE- did not include dynamic pressure losses on aft lifting surfaces. NESS USING A NEW COMPUTATIONAL METHOD An examination of a nonlinear approach which computes the Michael Falco and Gilbert Carpenter In AGARD Combat Aircraft forces on a combined body/separated region contour and corrects Maneuverability Dec. 1981 11 p refs Sponsored in part by these forces by an empirical momentum deficit in the separated Army Aviation Research and Development Command region was begun. For axisymmetric bodies the method reduces to the standard Allen-Jorgenson cross flow approach. Two Avail: NTIS HC A11/MF A01 potentially major advantages over the Allen-Jorgenson method A computational method for the assessment of aircraft are that the method does provide a model for predicting body combat effectiveness in the design concept phase is discussed. fin interaction and that the method is extendable to arbitrary The approach employs a stochastic learning method, in conjunction bodies. R.J.F. with dynamic simulation, to derive aircraft maneuver strategies in the form of a feedback control based upon a discretized set N82-22200]f British Aerospace Aircraft Group. Preston (England). of threat visual or warning system cues. The derived strategies Aerodynamics Dept. maximize either survival probability of kill probability in the one AEROELASTIC TAILORING FOR CONTROL AND PERFOR- on one setting. Computational results are presented for selected MANCE: ARE REQUIREMENTS COMPATIBLE? aircraft designs in missile and gun combat. B.W. D. Booker In AGARD Combat Aircraft Maneuverability Dec. 1981 4 p refs N82-22204# McDonnell-Douglas Corp., St. Louis. Mo. Opera- Avail: NTIS HC A11/MF A01 tions Analysis Dept. The variations of camber and twist along a wing required EVALUATION OF DIRECT FORCE MODE FIGHTERS BY for optimum performance in low 'g' (cruise) and high 'g' (combat) COMBAT SIMULATION flight are discussed. It is shown that a wing with active leading C. H. Guthrie In AGARD Combat Aircraft Maneuverability Dec. edge and trailing edge maneuverer devices scheduled with angle 1981 13 p of attack, and structurally tailored to control aeroelastic bending Avail: NTIS HC A11/MF A01 and torsion, can approach optimum performance. However the Advanced fighter concepts which have -been significantly torsional stiffness of such a wing may be too low for satisfactory influenced by air combat simulation are discussed. Both man in roll control at high airspeeds in supersonic flight. Some com- the loop and digital combat simulation are excellent tools for promise to performance is implied if torsional stiffness has to developing and screening advanced fighter concepts. One be increased to provide adequate control capability. Author important application is the evaluation of fighters with high authority aerodynamic and propulsive controls. Manned and digital N82-22201rfl Northrop Corp.. Hawthorne, Calif. Aircraft Div. air combat simulations showed that high authority controls TAIL CONFIGURATIONS FOR HIGHLY MANEUVERABLE substantially increase combat effectiveness when used both for COMBAT AIRCRAFT enhance large scale maneuverability and for automatic pointing W. E. Fellers. W. S. Bowman, and P. T. Wooler In AGARD of the fuselage. Digital simulation showed that fighters with Combat Aircraft Maneuverability Dec. 1981 18 p high authority direct force modes require lower sustained load factors than conventional designs for a constant level of Avail: NTIS HC A11/MF A01 effectiveness in close in combat. Therefore, fighters with direct The drag due to lift, maximum lift, and stability and control force modes can be lighter and less expensive than conven- characteristics of tailless, canard, and aft tail configurations of tional aircraft. In a manned simulation of close in combat, single highly maneuverable combat aircraft, using both aerodynamic fighters with several levels of aerodynamic and propulsion control surfaces and vectored thrust for pitch control are evaluated. The authority were flown against two threat fighters of equal same low aspect ratio wing planform was used on all the instantaneous sustained turn rate capability and with identical configurations. Control configured vehicle concepts were avionics and armament. For the fighter configured with the highest employed. Variable wing camber employing leading edge and authority controls, many measures of engagement control and trailing edge flaps was used to reduce profile drag. The center effectiveness were double those of the conventional (baseline) of gravity was located as far aft as allowed by the stability and fighter. B.W. control criteria, in order to reduce subsonic and supersonic trim drag. The critical pitch control criterion was found to be the N82-2220&# British Aerospace Aircraft Group. Preston (England).

348 N82-22217

THE STUDY OF COMBAT AIRCRAFT MANEUVERABILITY determine the optimum size of porosity and cavity, tunnel tests BY AIR TO AIR COMBAT SIMULATION were conducted with different airfoil porosities, cavities and flow A. G. Bames In AGARD Combat Aircraft Maneuverability Dec. Mach numbers. A higher drag reduction was obtained by the 1981 9 p 2.5 percent porosity and the 1/4-inch deep cavity. T.M. Avail. NTIS HC A11/MF A01 Air to air combat by ground based simulation and its contribution to the design, development and operational use of N82-22211*| Boeing Commercial Airplane Co., Seattle, Wash. combat aircraft is evaluated. The merits of different aircraft/missile AERODYNAMIC ANALYSIS OF VTOL INLETS AND DEFINI- combinations can be assessed under controlled conditions with TION OF A SHORT. BLOWING-UP INLET Final Report pilot involvement. Parameters which influence maneuverability, J. Syberg and A. L. Jones Apr. 1982 61 p refs such as sustained turn rate, attained turn rate, and SEP can be (Contract NAS3-22369) easily varied, and translated into combat success. The relative (NASA-CR-165617; NAS 1.26:165617; 06-51418) Avail: importance of these parameters are discussed in the light of NTIS HC A04/MF A01 CSCL 01A experimental results. B.W. The results indicated that, without boundary layer control, either a very long inlet or an inlet with a very high contraction ratio lip will be required to meet the stringent design requirements. N82-22206*jjl Old Dominion Univ.. Norfolk. Va. Dept. of It is shown that active boundary layer control is an effective Mechanical Engineering and Mechanics. means of preventing separation and that a significant reduction AERODYNAMIC PERFORMANCE OF SLENDER WINGS in inlet size can be achieved by removing only a small amount WITH SEPARATED FLOWS Technical Report, period ending of bleed in the throat region of the inlet. A short, blowing-lip 31 Dae. 1981 model was designed and fabricated. This model features an C. Subba Reddy Mar. 1982 64 p refs adjustable, blowing slot located near the hilite on the windward (Grant NsG-1561) side of the inlet. T.M. (NASA-en-168768; NAS 1.26.168768) Avail. NTIS HC A04/MF A01 CSCL 01A The aerodynamic performance of low aspect ratio sweptback N82-22212# National Aerospace Lab., Tokyo (Japan). Noise wings with vortex flows was numerically investigated using the and Emission Research Group. free vortex sheet method. The models studied included flat, AERODYNAMIC CHARACTERISTICS OF THE EXTERNAL cambered, strake. and leading edge flapped wings of different USB POWERED LIFT SYSTEM USING SIDE FENCES FOR planformS The theoretical results predicted by the method were ENHANCEMENT OF COANDA FLOW ATTACHMENT compared with the existing experimental data wherever available: Masataka Maita, Hirotoshi Fujieda. and Shigemi Shindo Oct. and the code capabilities and limitations were explored. Also 1981 20 p refs the effects of the wing thickness, fuselage, leading edge flap (NAL-TR-686T: ISSN-0389-4010) Avail: NTIS and multiple vortex modeling on the aerodynamic characteristics HC A02/MF A01 were studied. Author The fundamental aspects concerning the effect of side fences on powered lift augmentation for the external upper surface N82-22207*jjl National Aeronautics and Space Administration. blowing (USB) propulsive-lift configuration, as ascertained by wind Langley Research Center, Hampton, Va. tunnel experiment, are presented. From the comparisons of WIND-TUNNEL INVESTIGATION OF THE POWERED aerodynamic performances made of configurations using side LOW-SPEED LONGITUDINAL AERODYNAMICS OF THE fences and of those using either vortex generators or using no VECTORED-ENGINE-OVER (VEO) WING FIGHTER CONFIG- special devices, it is concluded that the USB propulsive-lift concept URATION using side fences for enhancement of engine exhaust flow John W. Paulson, Perry D. Whitten (General Dynamics Corp.. attachment has promising potential for attaining very high and Fort Worth. Tex.), and Stephen C. Stumpfl (AFWAL) Mar. 1982 efficient powered lift performances. M.G. 274 p refs (NASA-TM-83263: NAS 1.15:83263) Avail: NTIS N82-22213*# Bihrle Applied Research. Inc.. Jericho, N. Y. HC A12/MF A01 CSCL 01A ANALYSIS OF ROTARY BALANCE DATA FOR THE F-16 A wind-tunnel investigation incorporating both static and AIRPLANE INCLUDING THE EFFECT OF CONFORMAL FUEL wind-on testing was conducted in the Langley 4- by 7-Meter TANKS Tunnel to determine the effects of vectored thrust along with Billy Barnhart Washington NASA Apr. 1982 71 p refs spanwise blowing on the low-speed aerodynamics of an advanced (Contract NAS1-16205) fighter configuration. Data were obtained over a large range of (NASA-CR-3479; NAS 1.26:3479) Avail: NTIS thrust coefficients corresponding to takeoff and landing thrust HC A04/MF A01 CSCL 01A settings for many nozzle configurations. The complete set of F-15 rotary balance data was analyzed, and the influence static thrust data and the complete set of longitudinal aerodynamic of control deflections, Reynolds number and airplane components, data obtained in the investigation are presented. These data are i.e.. body, wing, horizontal and vertical tails, as well as conformal intended for reference purposes and. therefore, are presented tanks, on the aerodynamics up to 90 degrees angle of attack without analysis or comment. The analysis of the thrust-induced are discussed. Steady state spin mode predictions using these effects found in the investigation are not discussed. Author data are presented, which show excellent correlation with spin tunnel and flight test results. Generally, the data shows damped N82-22209*# Rensselaer Polytechnic Inst., Troy. N. Y. Dept. yawing moment slopes with rotation at all angles of attack, and of Mechanical Engineering. Aeronautical Engineering and good control effectiveness. Differences in the rotary aerodynamics Mechanics. due to the addition of conformal tanks are minimal. The small INVESTIGATION OF PASSIVE SHOCK WAVE-BOUNDARY differences in the region of the flat spin do, however, indicate LAYER CONTROL FOR TRANSONIC AIRFOIL DRAG that the resulting spin mode would be slightly flatter and faster REDUCTION Final Report. 1 Oct. 1979 - 30 Sep. 1981 for a conformal tank equipped airplane. The addition of conformal H. T. Nagajnatsu. W. B. Brower, Jr.. L. Bahi, and J. Ross Apr. tanks make the airplane more departure susceptible. S.L. 1982" 204 p refs (Grant NsG-1624) N82-22217*# National Aeronautics and Space Administration. (NASA-CR-168844; NAS 1.26:168844) Avail: NTIS Langley Research Center. Hampton. Va. HC A10/MF A01 CSCL 01A EFFECT OF NACELLES ON AERODYNAMIC CHARACTERIS- The passive drag control concept, consisting of a porous TICS OF AN EXECUTIVE-JET MODEL WITH SIMULATED. surface with a cavity beneath it. was investigated with a PARTIAL-CHORD. LAMINAR-FLOW-CONTROL WING 12-percent-thick circular arc and a 14-percent-thick supercritical GLOVE airfoil mounted on the test section bottom wall. The porous Richard L. Campbell Apr. 1982 104 p refs surface was positioned in the shock wave/boundary layer (NASA-TM-83271; L-14982; NAS 1.15:83271) Avail: NTIS interaction region. The flow circulating through the porous surface, HC A06/MF A01 CSCL 01A from the downstream to the upstream of the terminating shock Tests were conducted in the Langley High-Speed 7- by wave location, produced a lambda shock wave system and a 10-Foot Tunnel using a 1/10-scale model of an executive jet pressure decrease in the downstream region minimizing the flow to examine the effects of the nacelles on the wing pressures separation. The wake impact pressure data show an appreciably and model longitudinal aerodynamic characteristics. For the drag reduction with the porous surface at transonic speeds. To present investigation, each wing panel was modified with a

349 N82-22223

simulated, partial-chord, laminar-flow-control glove. Horizontal-tail and up extending over the last 20 years. This study centered effects were also briefly examined. The tests covered a range of on the effect of impact and the follow-on events on aircraft Mach numbers from 0.40 to 0.82 and lift coefficients from structures and was confined to the approach, landing and takeoff 0.20 to 0.55. Oil-flow photographs of the wing at selected segments of the flight. The significant characteristics, frequency conditions are included. Author of occurrence and the effect on the occupants of the above data base were studied and categorized with a view to establishing N82-22223# Deutsche Forschungs- und Versuchsanstalt fuer typical impact scenarios for use as a basis of verifying the Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer effectiveness of potential safety concepts. Studies were also Entwurfsaerodynamik. carried out of related subjects such as: (1) assessment of advanced DRAG REDUCTION USING PNEUMATIC TURBULATORS materials: (2) human tolerance to impact: (3) merit functions Karl-Heinz Horstmann and Armin Quast Sep. 1981 54 p refs for safety concepts: and (4) impact analysis and test methods. In GERMAN: ENGLISH summary Report will also be announced Author as translation (ESA-TT-743) 81-33) Avail: NTIS HC A04/MF A01: DFVLR. N82-22228*# Boeing Aerospace Co.. Houston. Tex. Cologne DM 11,40 A SYSTEM SAFETY MODEL FOR DEVELOPMENTAL Reduction of the additional drag, caused by laminar separa- AIRCRAFT PROGRAMS tion bubbles in airfoils and fuselages at Reynolds numbers below Emil J. Amberboy and Robert L. Stokeld Washington NASA 5 million, was investigated theoretically and experimentally. By Apr. 1982 84 p refs blowing from a row of holes located at the separation line, the (Contract NAS2-10361) laminar bubble is destroyed and drag is reduced considerably. (NASA-CR-3534: NAS 1.26:3534) Avail: NTIS Drag reduction due to blowing is naturally smaller at lower HC A05/MF A01 CSCL 01C Reynolds numbers, the bubbles being smaller. The Reynolds Basic tenets of safety as applied to developmental aircraft number range with low section drag increases if pneumatic programs are presented. The integration of safety into the project turbulators are used in the profile design. Author (ESA) management aspects of planning, organizing, directing and controlling is illustrated by examples. The basis for project N82-22224f National Aerospace Lab.. Amsterdam (Netherlands). management use of safety and the relationship of these Flight Dynamics Div. management functions to 'real-world' situations is presented. The AEROELASTIC PROPERTIES OF WINGS IN TRANSONIC rationale which led to the safety-related project decision and FLOW the lessons learned as they may apply to future projects are R. J. Zwaan 24 Feb. 1981 51 p refs Presented at Lecture presented. N.W. Ser. on Unsteady Airloads and Aeroelastic Probl. in Separated and Transonic Flow, Rhode-St.-Genese, Belgium, 9-13 Mar. N82-22229# Deutsche Forschungs- und Versuchsanstalt fuer 1981 Luft- und Raumfahrt. Cologne (West Germany). Abteilung (NLR-MP-81005-U) Avail: NTIS HC A04/MF A01 Flugverkehrswissenschaft. Literature on transonic flutter characteristics of wings, DEVELOPMENTAL POSSIBILITIES AND RESTRICTIONS IN especially the transonic dip phenomenon in the flutter boundaries, AIR TRANSPORT was reviewed. The transonic dip occurs most distinctly with Aug. 1981 91 p In GERMAN: ENGLISH summary Report sweptback wings. The dip is caused by the phase lag of the lift will also be announced as translation (ESA-TT-744) due to the fundamental wing bending mode and corresponds to (DFVLR-Mitt-81-9) Avail: NTIS HC A05/MF A01: DFVLR, a single-mode flutter mechanism. The dip can be predicted Cologne DM 16.20 qualitatively using methods for inviscid transonic unsteady air The possibilities of creating or maintaining an efficient air loads. Quasi-steady transonic methods are not wholly reliable. transport system in the present political, economical and The dip becomes relatively deeper with increasing wing-to-air technical situation were assessed. Future developments in demand mass ratio. The dip can become more pronounced for a and supply in commercial air transport and questions related to supercritical wing than for a conventional wing. The dip occurs transport policy, airport planning and supply organization of air at design conditions as well as off-design conditions. In case of carriers are discussed. flow separation, a narrow dip which depends strongly on boundary layer conditions and the spatial distribution of the separated flow can occur. Author (ESA) N82-22230# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Cologne (West Qermany). Abteilung N82-22225# Societe Nationale Industrielle Aerospatiale. Flugverkehrswissenschaft. Marignane (France.) Helicopter Div. DEVELOPMENTAL POSSIBILITIES IN CIVIL AVIATION IN AEROSPATIALE SURVEY OF WIND TUNNEL TESTING OF THE FEDERAL REPUBLIC OF GERMANY [ENTWICKLONG- SMALL AND LARGE SCALE ROTORS SMOEGLICHKEITEN IM GEWERBLICHEN LUFTVERKEHR J. P. Silvani and A. Vuillet Paris 1981 17 p refs Presented DER BUNDESREPUBLIK DEUTSCHLAND] at the 7th European Rotocraft And Powered Lift Aircraft Forum, H.-G. Nuesser In its Develop. Possibilities and Restrictions in Garmisch-Partenkirchen. West Germany 8-11 Sep. 1981: Air Transport Aug. 1981 D 11-46 In GERMAN sponsored by DFVLR. Cologne (SNIAS-821-210-107) Avail: NTIS HC A02/MF A01 Avail: NTIS HC A05/MF A01: DFVLR. Cologne DM 16.20 Wind tunnel tests on Mach scaled rotors (1/10 and 1/3) The results of a prognosis was made on the evolution of capable of a wide range of shaft angle settings are summarized. air traffic until the year 2000 in Germany. Travel motives, flight The 1/3 model hub is fitted with a swashplate. general and type, region, season and traffic paths are forecasted. Data are cyclic inputs. Continuous conversion of a tilt rotor was achieved. used to derive the required evolution in the supply of passenger Speeds > 500 km/hr were attained with conventional rotors. and cargo flights. The forecast includes a 5% annual increase in During autorotation high lift coefficients are obtained without passenger traffic, reaching in the year 2000 a total number of major drag penalties. The OA family 2-D airfoils characteristic some 765.000 starts and take offs at a seating capacity of improvements were checked. Results show good behaviour about 60%. Forecasts for individual airports are also included. throughout the entire rotor flight envelope: a 3% improvement Author (ESA) on the rotor figure of merit at nominal thrust in hover: a 9% power improvement at nominal thrust and 300 km/hr in level fight: and 12% maximum thrust improvement at stall. N82-22232jjl Flughafen G.m.b.H.. Hamburg (West Germany). Author (ESA) TRAFFIC INTRASTRUCTURE: CAN PLANNING STILL BE CARRIED THROUGH [VERKEHRSINFRASTRUKTUR: 1ST N82-22227*# Douglas Aircraft Co.. Inc.. Long Beach, Calif. PLANUNG NOCH DURCHSTEZBAR7] TRANSPORT AIRCRAFT ACCIDENT DYNAMICS Final U. Christiansen In DFVLR Develop. Possibilities and Restrictions Technical Report. 11 Feb. 1980 - Mar. 1982 in Air Transport Aug. 1981 p 61-66 In GERMAN A. Cominsky Atlantic City FAA Mar. 1982 178 p (Contract NAS1-16111) Avail: NTIS HC A05/MF A01: DFVLR. Cologne DM 16,20 (NASA-CR-165850: FAA-RD-74-12: MAS 1.26:165850) Avail: The problems facing German airport authorities in planning NTIS HC A09/MF A01 CSCL 01C either to extend existing, or to create new airports are analyzed. A study was carried out of 112 impact survivable jet transport In addition to the growing environmental awareness by the public, aircraft accidents (world wide) of 27.700 kg (60,000 Ib.) aircraft the procedures for approval at various administrative and juridical

350 N82-22243 levels are identified as the major reason for the considerable N82-22240*# California Univ., Berkeley. Inst. of Transportation delays encountered in recent projects. Several proposals are Studies. formulated for simplification and shortening these procedures. MEASURES TO INCREASE AIRFIELD CAPACITY BY Author (ESA) CHANGING AIRCRAFT RUNWAY OCCUPANCY CHARAC- TERISTICS N82-22236#* National Transportation Safety Board. Washington. Geoffrey D. Gosling, Abid Kanafani. and Stephen L M. Rockaday D. C. Dec. 1981 218 p refs SPECIAL INVESTIGATION REPORT: EVACUATION OF (Grant NAG2-19) UNITED AIRUNES OC-8-61. SKY HARBOR INTERNA- (NASA-CR-168841; NAS 1.26:168841: UCB-ITS-RR-81-7) TIONAL AIRPORT, PHOENIX. ARIZONA. DECEMBER 29. Avail: NTIS HC A10/MF A01 CSCL 17G 1980 Airfield capacity and aircraft runway occupancy characteristics 9 Sep. 1981 29 p refs were studied. Factors that caused runway congestion and airfield (PB82-115619: NTSB-SIR-81-4) Avail: NTIS crowding were identified. Several innovations designed to alleviate HC A03/MF A01 CSCL 01B the congestion are discussed. Integrated landing management, On December 29. 1980. United Airlines Charter Flight 5820. the concept that the operation of the final approach and runway a DC-8-61. with 238 passengers and a crew of 9. was evacuated should be considered in concert, was identified as underlying all at Sky Harbor International Airport. Phoenix. Arizona, when the of the innovations. R.J.F. failure of the rear landing gear bogie beam resulted in a fire in the aircraft's right main landing gear. The cockpit crew was erroneously advised of an engine fire by the airport tower and N82-22241# Aeronautical Research Labs., Melbourne (Australia). began emergency shutdown procedures. The captain initiated STRAPDOWM INERTIAL NAVIGATION SYSTEMS: AN the evacuation after all electrical power had been shut down ALGORITHM FOR ATTITUDE AND NAVIGATION COMPU- and the public address and cabin interphone systems were TATIONS without power. Therefore, the second officer had to give the R. B. Miller 1981 33 p refs evacuation orders to passengers and flight attendants by 'word (ARL/Sys-Rept-23: AR-002-265) Avail: NTIS of mouth'. As a result of its special investigation and its previous HC A03/MF A01 work on the subject of evacuations, the Safety Board has made Vehicle attitude is maintained through quaternions, which recommendations to the Federal Aviation Administration to are updated by a modified third order method. The navigation improve the availability of emergency communication equipment part of the algorithm uses a split frame technique whereby body and to promote its use. GRA related quantities are evaluated in body axis coordinates, and navigation frame related quantities are evaluated in navigation N82-22237# National Transportation Safety Board, Washington, axis coordinates. The algorithm is partitioned into three sections D. C. which are performed at different rates according to the REVIEW OF ROTORCRAFT ACCIDENTS 1977-1979 application. T.M. 11 Aug. 1981 59 p (PB82-115601: NTSB-AAS-81-1) Avail: NTIS N82-22242jjl Royal Aircraft Establishment. Farnborough HC A04/MF A01 CSCL 01B (England). Accident data on the rotorcraft. pilots and operating AIRFIELD VISUAL AIDS RESEARCH AT THE ROYAL environment which may be most useful to designers, manufactur- AIRCRAFT ESTABLISHMENT ers, operators and regulators are presented. Tables and graphs A. J. Smith 2 Oct. 1981 29 p refs Presented at the 1981 presenting accident statistics, cause/factors, rotorcraft make and Aviation Lighting Sen.. Williamsburg. Virginia. 9-13 Nov. 1981; model data, pilot experience and weather conditions are Sponsored by Illuminating Engineering Society of North Amer- included. GRA ica (RAE-TM-FS-431: BR80893) Avail: NTIS HC A03/MF :A01 N82-22238*# Ohio State Univ.. Columbus. The precision approach path indicator (PAPI) is described A TACTUAL DISPLAY AID FOR PRIMARY FLIGHT and helicopter lighting aids are discussed. The PAPI system TRAINING Final Report. 1 Jul. 1975 - 15 Dec. 1978 indicates correct glide slope at ranges > 10 km under good Richard D. Gilson Jul. 1979 76 p refs visibility conditions and provides information up to 300 m from (Contract NAS2-8954) touchdown, two color light projector units, consisting of three (NASA-CR-166242: NAS 1.26:166242) Avail: NTIS simple optical projectors side by side in a box. tell the pilot if HC A05/MF A01 CSCL 01D he is too high, too low. or on slope by the combination of red A means of flight instruction is discussed. In addition to and white lights. Trials show that it can be used by a wide verbal assistance, control feedback was continously presented range of civil and military aircraft, e.g.. the VC-10, small private via a nonvisual means utilizing touch. A kinesthetic-tactile (KT) airplanes, or helicopters. A mathematical model which predicts display was used as a readout and tracking device for a computer what pilots can see when landing in fog was used in order to generated signal of desired angle of attack during the approach optimize proposed approach lighting patterns for helicopters. If and landing. Airspeed and glide path information was presented the lighting pattern is 730 m long, initial contact is possible at via KT or visual heads up display techniques. Performance with altitudes > 100 m. Lighting trials show that red stop bar the heads up display of pitch information was shown to be lighting and green taxiway centerline need further improvement. significantly better than performance with the KT pitch display. Author (ESA) Testing without the displays showed that novice pilots who had received tactile pitch error information performed both pitch and N82-22243*# Aeronautical Research Associates of Princeton. throttle control tasks significantly better than those who had Inc.. N. J. received the same information from the visual heads up display ANALYSIS AND FLIGHT EVALUATION OF A SMALL. of pitch during the test series of approaches to landing. Author FIXED-WING AIRCRAFT EQUIPPED WITH HINGED PLATE SPOILERS N82-22239*jjl National Aeronautics and Space Administration. John W. Olcott, Edward Sackel. and David R. Ellis Sep. 1981 Langley Research Center. Hampton, Va. 161 p refs EFFECTS OF CABLE GEOMETRY AND AIRCRAFT AT- (Contract NAS2-5589) TITUDE ON THE ACCURACY OF A MAGNETIC LEADER (NASA-CR-166247; NAS 1.26:166247) Avail: NTIS CABLE SYSTEM FOR AIRCRAFT GUIDANCE DURING HC A08/MF A01 CSCL 01C ROLLOUT AND TURNOFF The results of a four phase effort to evaluate the application W. Thomas Bundick Apr. 1982 32 p refs of hinged plate spoilers/dive brakes to a small general aviation (NASA-TP-1978: L-14975: NAS 1.60:1978) Avail: NTIS aircraft are presented. The test vehicle was a single engine light HC A03/MF A01 CSCL 17G aircraft modified with an experimental set of upper surface spoilers A theoretical analysis of a single wire magnetic leader cable and lower surface dive brakes similar to the type used on system for aircraft rollout and tumoff guidance was performed sailplanes. The lift, drag, stick free stability, trim, and dynamic to determine the errors produced by the leader cable installation response characteristics of four different spoiler/dive brake geometry and aircraft attitude. It was found that errors in the configurations were determined. Tests also were conducted, under measurement of lateral displacement from the cable are smaller a wide range of flight conditions and with pilots of various than errors in the measurement of aircraft heading and that experience levels, to determine the most favorable methods of both errors are smallest at or near the cable. Author spoiler control and to evaluate how spoilers might best be used

351 N82-22244

during the approach and landing task. The effects of approach single engine TB 20 prototype aircraft are presented along with path angle, approach airspeed, and pilot technique using aircraft specifications. A.R.H. throttle/spoiler integrated control were investigated for day. night. VFR, and IFR approaches and landings. The test results indicated N82-22248*# Systems Technology, Inc.. Hawthorne, Calif. that spoilers offered significant improvements in the vehicle's FUNCTIONAL REQUIREMENTS FOR THE MAN-VEHICLE performance and flying qualities for all elements of the approach SYSTEMS RESEARCH FACILITY and landing task, provided a suitable method of control was Warren F. Clement. R. Wade Allen, Robert K. Heffley. Wayne F. available. Author Jewell. Henry R. Jex. Duane T. McRuer. Ted M. Schulman. and Robert L. Stapleford Oct. 1980 221 p refs N82-22244*# Sinacori (John B.) Associates. Hollister. Calif. (Contract NAS2-10400) CONCEPTUAL DESIGN STUDY OF A VISUAL SYSTEM FOR (NASA-CR-166315: NAS 1.26:166315: TR-1156-3) Avail: A ROTORCRAFT SIMULATOR AND SOME ADVANCES IN NTIS HC A10/MF A01 CSCL 01C PLATFORM MOTION UTILIZATION Final Report The NASA Ames Research Center proposed a man-vehicle John B. Sinacori Aug. 1980 33 p refs systems research facility to support flight simulation studies which (Contract NAS2-10278) are needed for identifying and correcting the sources of human (NASA-CR-166322: NAS 1.26:166322) Avail: NTIS error associated with current and future air carrier operations. HC A03/MF A01 CSCL 14B The organization of research facility is reviewed and functional A conceptual design of a visual system for a rotorcraft requirements and related priorities for the facility are recom- flight simulator is presented. Also, drive logic elements for a mended based on a review of potentially critical operational coupled motion base for such a simulator are given. The design scenarios. Requirements are included for the experimenter's is the result of an assessment of many potential arrangements simulation control and data acquisition functions, as well as for of electro-optical elements and is a concept considered feasible the visual field, motion, sound, computation, crew station, and for the application. The motion drive elements represent an intercommunications subsystems. The related issues of functional example logic for a coupled motion base and is essentially an fidelity and level of simulation are addressed, and specific criteria appeal to the designers of such logic to combine their washout for quantitative assessment of various aspects of fidelity are and braking functions. Author offered. Recommendations for facility integration, checkout, and staffing are included. A.R.H. N82-22246*# National Aeronautics and Space Administration. Langley Research Center, Hampton. Va. N82-22249*# Systems Technology. Inc.. Hawthorne. Calif. A LINEAR DECOMPOSITION METHOD FOR LARGE TECHNICAL APPROACHES FOR MEASUREMENT OF OPTIMIZATION PROBLEMS. BLUEPRINT FOR DEVELOP- HUMAN ERRORS Final Report MENT Warren F. Clement. Robert K. Heffley. Wayne F. Jewell, and Jaroslaw Sobieszczanski-Sobieski Feb. 1982 61 p refs Duane T. McRuer May 1980 140 p refs (NASA-TM-83248; NAS 1.15:82348) Avail: NTIS (Contract NAS2-10400) HC A04/MF A01 CSCL QIC (NASA-CR-166314: NAS 1.26:166314: STI-TR-1156-2) Avail: A method is proposed for decomposing large optimization NTIS HC A07/MF A01 CSCL01C problems encountered in the design of engineering systems such Human error is a significant contributing factor in a very as an aircraft into a number of smaller subproblems. The high proportion of civil transport, general aviation, and rotorcraft decomposition is achieved by organizing the problem and the accidents. The technical details of a variety of proven approaches subordinated subproblems in a tree hierarchy and optimizing each for the measurement of human errors in the context of the subsystem separately. Coupling of the subproblems is accounted national airspace system are presented. Unobtrusive measure- for by subsequent optimization of the entire system based on ments suitable for cockpit operations and procedures in part of sensitivities of the suboptimization problem solutions at each full mission simulation are emphasized. Procedure, system level of the tree to variables of the next higher level. A formalization performance, and human operator centered measurements are of the procedure suitable for computer implementation is discussed as they apply to the manual control, communication, developed and the state of readiness of the implementation supervisory, and monitoring tasks which are relevant to aviation building blocks is reviewed showing that the ingredients for the operations. S.L. development are on the shelf. The decomposition method is also shown to be compatible with the natural human organization N82-2225O*# Systems Technology. Inc.. Hawthorne. Calif. of the design process of engineering systems. The method is A THEORY OF HUMAN ERROR Final Report also examined with respect to the trends in computer hardware Duane T. McRuer. Warren F. Clement, and R. Wade Allen May and software progress to point out that its efficiency can be 1980 91 p refs amplified by network computing using parallel processors. B.W. (Contract NAS2-10400) (NASA-CR-166313: NAS 1.26:166313: STI-TR-1156-1) Avail: N82-22246*# National Aeronautics and Space Administration. NTIS HC A05/MF A01 CSCL 01C Washington. D. C. Human error, a significant contributing factor in a very high REVOLUTION IN AIRPLANE CONSTRUCTION? GROB proportion of civil transport, general aviation, and rotorcraft G110: THE FIRST MODERN FIBER GLASS COMPOSITION accidents is investigated. Correction of the sources of human AIRPLANE SHORTLY BEFORE ITS MAIDEN FLIGHT error requires that one attempt to reconstruct underlying and R. Dorpinghaus Mar. 1982 19 p Transl. into ENGLISH from contributing causes of error from the circumstantial causes cited Aerokuner (West Germany), no. 12, Dec. 1981 p 1550-1555 in official investigative reports. A validated analytical theory of Transl. by Scientific Translation Service. Santa Barbara, Calif. the input-output behavior of human operators involving manual (Contract NASw-3542) control, communication, supervisory, and monitoring tasks which (NASA-TM-76705; NAS 1.15:76705) Avail: NTIS are relevant to aviation operations is presented. This theory of HC A02/MF A01 CSCL 01C behavior, both appropriate and inappropriate, provides an insightful A single engine two passenger airplane, constructed com- basis for investigating, classifying, and quantifying the needed pletely from fiber reinforced plastic materials is introduced. The cause-effect relationships governing propagation of human error. cockpit, controls, wing profile, and landing gear are discussed. B.W. Development of the airframe is also presented. S.L. N82-22251*# National Aeronautics and Space Administration. N82-22247*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. Washington. D. C. PERFORMANCE TESTING OF A MAIN ROTOR SYSTEM SOCATA: TB 20 TRINIDAD GIVEN GERMAN DEBUT FOR A UTILITY HELICOPTER AT 1/4 SCALE B. Malzbender Mar. 1982 13 p Transl. into ENGLISH from John D. Berry (Army Aviation Research and Development Aerokurier (West Germany), no. 12. Dec.. 1981 p 1543. Command. Langley. Va.) Apr. 1982 49 p refs ' 1546-1547 Transl. by Scientific Translation Service. Santa (DA Proj. 1L1-61102-AH-45) Barbara. Calif. (NASA-TM-83274: L-15015: NAS 1.15:83274; (Contract NASw-3542) AVRADCOM-TR-82-B-3) Avail: NTIS HC A03/MF A01 CSCL (NASA-TM-76706: NAS 1.15:76706) Avail: NTIS 01C HC A02/MF A01 CSCL QIC Two rotor systems for the UH-1 helicopter were tested in Pilot impressions gained in a first flight in the 250 HP hover and forward flight. The baseline system was a dynamically

352 N82-22259 scaled model of the current rotor system, while the other system system, adopted from army versions, provides overall accuracy was designed for advanced performance. In hover out of ground > 3% of distance covered. The tail assembly is watertight. The effect, the advanced rotor system shows improvements up to AS 15 TT has a range > 15 km. is roll stabilized, has a 30 kg 10 percent in the figure of merit and improvements in thrust warhead, and flies a few m above the surface, descending near up to 7 percent. In forward flight, the advanced rotor system the target just before impact. Author (ESA) demonstrated reductions in required torque throughout the range of conditions tested, with reductions up to 17 percent occurring N82-22266# Societe Nationale Industrielle Aerospatiale. La at the higher advance ratios and higher lift values tested. T.M. Coumeuve (France). Helicopter Div. A LIGHT HELICOPTER FOR NIGHT FIRING N82 22252*# Hydraulic Research Textron. Valencia. Calif. J. F. Candau Paris 1981 19 p Presented at the 7th European AN ELECTRONIC CONTROL FOR AN ELECTROHYDRAUUC Rotorcraft and Powered Lift Aircraft Forum, Garmisch- ACTIVE CONTROL LANDING GEAR FOR THE F-4 AIRCRAFT Partenkirchen. West Germany. 8-11 Sep. 1981: sponsored by Final Report DFVLR. Cologne Irving Ross Washington Apr. 1982 92 p refs (SNIAS-821-210-105) Avail: NTIS HC A02/MF A01 (Contract NAS1-16420) An antitank helicopter suitable for night operation over (NASA-CR-3552: NAS 1.26:3552; HR-74600000) Avail: difficult terrain is described. A Dauphin helicopter, equipped with NTIS HC A05/MF A01 CSCL 01C HOT missiles, is treated with low IR reflectance paint and A controller for an electrohydraulic active control landing antireflective coating of glazed areas. Jet exhaust is deviated, gear was developed for the F-4 aircraft. A controller was modified engine cowlings reduce IR emission. Targets are sought by a for this application. Simulation results indicate that during landing passive system of thermal imagery. Outside surroundings are and rollout over repaired bomb craters the active gear effects a viewed via a nocturnal vision device operating on the light force reduction, relative to the passive gear, or approximately intensification principle. The navigation system is self-contained. 70%. S.L The missile is guided by a localizer coupled to. and harmonized with a thermal camera, mounted on a gyrostabilized platform. Tanks are detected up to 4 km and identified up to 2 km. N82-22253# British Aerospace Aircraft Group. Weybridge Author (ESA) (England). TAILOR-MADE STRUCTURES; TODAY. AND TOMORROW: NEW MATERIALS. AN EXPLORATORY INVESTIGATION N82-22267# Societe Nationale Industrielle Aerospatiale. INTO THEIR POTENTIAL USE Marignane (France.) Helicopter Div. W. J. Bird 16 Apr. 1980 48 p CONCEPT STUDIES OF AN ADVANCED COMPOSITE (BAe-SDW-85/A/104/005) Avail: NTIS HC A03/MF A01 HELICOPTER FIN The use of fiber/matrix combinations, e.g. in a nonmetallic A. Desmonceaux and M. Torres Paris 1981 13 p Presented airplane, is discussed. The development of fiber/matrix struc- at the 7th European Rotorcraft and Powered Lift Aircraft Forum, tures is hindered by an absence of design experience, designers Garmisch-Partenkirchen, West Germany. 8-11 Sep. 1981: whose experience is in metallics rather than textiles, the sponsored by DFVLR. Cologne conservative structures employed, and production times for fiber (SNIAS-821-210-106) Avail: NTIS HC A02/MF A01 components. A modular tooling system is proposed. The structural A composite fin and fan in fin assembly was developed for feasibility of the aircraft is established by examining the possibility the Dauphin 2. The structure is made of epoxy resin preimpreg- of constructing VC-10 components in fiber/matrix materials. nated Kevlar or graphite, single or two direction fiber cloths. A Author (ESA) single block construction is used in heavily loaded areas or areas stabilized through a sharp curvature. A sandwich construction with Nomex honeycomb filler is used where loads are less. Static N82-22254# Societe Nationale Industrielle Aerospatiale. tests and theoretical studies show that maximum thrust is Marignane (France.) Helicopter Oiv. increased by 40% compared with a similar weight metal structure. A COMPLETE METHOD FOR COMPUTATION OF BLADE Production costs are reduced by eliminating a great number of MODE CHARACTERISTICS AND RESPONSES IN FOR- parts and assemblies. Operating costs are lowered by abolishing WARD FLIGHT corrosion risks and improving maintenance through the simpler J. P. Lefrancq and B. Masure Paris 1981 10 p refs Presented design. The fail safe composites increase safety. Author (ESA) at 7th European Rotorcraft and Powered Lift Aircraft Forum. Garmisch-Partenkirchen. West Germany 8-11 Sep. 1981: N82-22268jjl Societe Nationale Industrielle Aerospatiale. sponsored by DFVLR. Cologne Marignane (France.) Helicopter Div. (SNIAS-821-210-101) Avail: NTIS HC A02/MF A01 TAIL ROTOR STUDIES FOR SATISFACTORY PERFOR- The modal approach to rotor dynamic behavior is outlined, MANCE: STRENGTH AND DYNAMIC BEHAVIOR and an azimuth method is presented. The azimuth method applies G. Blachere and F. dAmbra Paris 1981 13 p refs Presented to stabilized flights, in particular those in which rotor configuration at 7th European Rotocraft and Powered Lift Aircraft Forum. is considered repeatable after one revolution. Excitation occurs Garmisch-Partenkirchen. West Germany 8-11 Sep. 1981: at rotor frequency (R + F) or at multiples of it. Rotor behavior is sponsored by DFVLR. Cologne developed in a Fourier series of which basic frequency is R+F. (SNIAS-821-210-108) Avail: NTIS HC A02/MF A01 The series terms are considered negligible beyond the nth Flexbeam, teetered, cantilevered and semirigid two bladed harmonic. Development coefficient counts show that (2n+1) rotors were studied in flight, on whirl test stands and theoretical- successive positions (azimuths), regularly spread over the ly. The blades are compared with conventional helicopter blades. revolution, can describe rotor behavior. Accuracy depends on For 2 ton helicopters, the tested blades have fewer parts, and the number n of harmonics retained. The n number selection weigh less than conventional ones. Blade life is increased, depends on computer capacity. Author (ESA) manufacturing and maintenance costs are lowered. For 8 ton helicopters, similar improvements were achieved, but at the N82-22265^ Societe Nationale Industrielle Aerospatiale. expense of larger control forces and limited lifetime for the Marignane (France.) Helicopter Oiv. flexbeam. Author (ESA) NAVAL VERSIONS OF THE DAUPHIN AND THE AS 15 TT WEAPON SYSTEM N82-22269# Institut de Mecanique des Fluides de Lille (France). J. P. Dubreuil Paris 1981 11 p Presented at the 7th European APPLICATION OF KALMAN FILTERING TO THE KINEMAT- Rotorcraft and Powered Lift Aircraft Forum. Garmisch- IC RECONSTRUCTION OF FREE FLIGHT OF CATAPULTED Partenkirchen. West Germany, 8-11 Sep. 1981: sponsored by AIRCRAFT MODELS IN THE LABORATORY (APPLICATION DFVLR. Cologne DU FILTRAGE DE KALMAN A LA RESTITUTION DE LA (SNIAS-821-210-104) Avail: NTIS HC A02/MF A01 CINEMATIQUE DES MAQUETTES D'AVION CATAPULTEES Modifications needed to adapt the Dauphin N helicopter for EN VOL LIBRE EN LABORATOIRE] naval rescue and attack missions are outlined. The antisurface P. Colon 30 Jun. 1980 15 p In FRENCH vessel weapon system is described. Maximum continuous engine (IMFL-80-28; IMFL-8214) Avail: NTIS HC A02/MF A01 power is increased from 437 to 468 kW. takeoff power from A Kalman filtering procedure was developed in order to 492 to 552. Pressure refueling is possible in-flight or on-ground. improve results obtained with a catapult and aircraft model. Blades and fin fold. A hydraulic mooring harpoon is located Application of this procedure is criticized. It is concluded that between the two wheels of the main landing gear. A radar the procedure as it stands is unreliable. Reconfiguration of the

353 N82-22260

filtering system is recommended. A protocol of tests intended performance characteristics were obtained along with exit profiles to determine acceptable performance of the system is pre- and oil smear photographs. The sensitivity of nozzle performance sented. Author (ESA) to tailpipe length, lobe number, mixer penetration, and mixer modifications like scalloping and cutbacks were established. N82-22260# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- Residual turbine swirl was found detrimental to exhaust system brunn (West Germany). Helicopter Div. performance and the low pressure turbine system for Energy CONTROLS AND DISPLAYS FOR ALL-WEATHER OPERA- Efficient Engine was designed so that no swirl would enter the TION OF HELICOPTERS mixer. The impact of mixer/plug gap was also established, along R. D. vonReth 3 Apr. 1981 19 p refs with importance of scalloping, cutbacks, hoods, and plug angles (MBB-UD-319-81-O) Avail: NTIS HC A02/MF A01 on high penetration mixers. M O.K. Various mission requirements for all weather operations are reviewed. In particular some of the most important features for N82-22266*! Pratt and Whitney Aircraft Group. East Hartford. military applications are outlined. Some of the basic relations Conn. Commercial Products Div. between increasing display sophistication and increasing control ADVANCED LOW-EMISSIONS CATALYTIC-COMBUSTOR sophistication are discussed. Also the influence of various functions PROGRAM. PHASE 1 Final Report on the degree of control automation as it seems desirable for G. J. Sturgess Jun. 1981 158 p refs future systems under the aspect of man machine interaction are (Contract NAS3-20821) taken into consideration. The controls and displays arrangement (NASA-CR-159656; NAS 1.26:159656; PWA-5589-19; of some representative helicopters of presently operational ESL-TR-79-23) Avail: NTIS HC A08/MF A01 CSCL 21E helicopters are described. An outline of the goals and results of Six catalytic combustor concepts were defined, analyzed, and some experimental and research programs is given. The evaluated. Major design considerations included low emissions, characteristics of presently operational helicopters are compared performance, safety, durability, installations, operations and with the technologically feasible solutions taking into account development. On the basis of these considerations the two most some of the economic constraints as initial cost, operational promising concepts were selected. Refined analysis and pre- cost and reliability. In an outlook at the future some basic liminary design work was conducted on these two concepts. requirements for the controls and the displays operation are The selected concepts were required to fit within the combustor established. J MS chamber dimensions of the reference engine. This is achieved by using a dump diffuser discharging into a plenum chamber N82>22262*# National Aeronautics and Space Administration. between the compressor discharge and the turbine inlet, with Lewis Research Center. Cleveland, Ohio. the combustors overlaying the prediffuser and the rear of the THE ROLE OF MODERN CONTROL THEORY IN THE DESIGN compressor. To enhance maintainability, the outer combustor case OF CONTROLS FOR AIRCRAFT TURBINE ENGINES for each concept is designed to translate forward for accessibility J. Zeller, B. Lehtinen. and W. Merrill 1982 17 p refs Presented to the catalytic reactor, liners and high pressure turbine area. at 12th Aerospace Sci. Conf., Orlando, Fla., 11-14 Jan. 1982; The catalytic reactor is self-contained with air-cooled canning sponsored by AIAA on a resilient mounting. Both selected concepts employed (NASA-TM-82815; E-1162: MAS 1.15:82815) Avail: NTIS integrated engine-starting approaches to raise the catalytic reactor HC A02/MF A01 CSCL 21E up to operating conditions. Advanced liner schemes are used to Accomplishments in applying Modern Control Theory to the minimize required cooling air. The two selected concepts design of controls for advanced aircraft turbine engines were respectively employ fuel-rich initial thermal reaction followed by reviewed. The results of successful research programs are rapid quench and subsequent fuel-lean catalytic reaction of carbon discussed. Ongoing programs as well as planned or recommended monoxide, and, fuel-lean thermal reaction of some fuel in a future thrusts are also discussed. Author continuously operating pilot combustor with fuel-lean catalytic reaction of remaining fuel in a radially-staged main combustor. N82-22263*# Cessna Aircraft Co., Wichita, Kans. Pawnee Author Div. ADVANCED GENERAL AVIATION COMPARATIVE ENGINE/ N82-22267*# United Technologies Research Center, East AIRFRAME INTEGRATION STUDY Final Report. Jan. Hartford. Conn. 1980 - Sap. 1981 INVESTIGATION OF SOOT AND CARBON FORMATION IN George L Huggins and David R. Ellis Sep. 1981 133 p refs SMALL GAS TURBINE COMBUSTORS Final Report (Contract NAS3-22221) T. J. Rosfjord Apr. 1982 54 p refs (NASA-CR-165564; NAS 1.26:165564; Cessna-AD-217) Avail: (Contract NAS3-22524) NTIS HC A07/MF A01 CSCL 21E (NASA-CR-167853: NAS 1.26:167853: The NASA Advanced Aviation Comparative Engine/Airframe UTRC-R82-915387-16) Avail: NTIS HC A04/MF A01 CSCL Integration Study was initiated to help determine which of four 21E promising concepts for new general aviation engines for the An investigation of hardware configurations which attempt 1990's should be considered for further research funding. The to minimize carbon and soot-production without sacrificing engine concepts included rotary, diesel. spark ignition, and performance in small gas turbine combustors was conducted. turboprop powerplants; a conventional state-of-the-art piston Four fuel injectors, employing either airblast atomization, pressure engine was used as a baseline for the comparison. Computer atomization, or fuel vaporization techniques were combined with simulations of the performance of single and twin engine nozzle air swirlers and injector sheaths. Eight configurations were pressurized aircraft designs were used to determine how the screened at sea-level takeoff and idle test conditions. Selected various characteristics of each engine interacted in the design configurations were focused upon in an attempt to quantify the process. Comparisons were made of how each engine performed influence of combustor pressure, inlet temperature, primary zone relative to the others when integrated into an airframe and required operation, and combustor loading on soot and carbon formation. to fly a transportation mission. Author Cycle tests were also performed. It was found that smoke emission levels depended on the combustor fluid mechanics, the atomization quality of the injector and the fuel hydrogen content. R.J.F. N82 22264* # Pratt and Whitney Aircraft Group, East Hartford. Conn. Commercial Products Oiv. ENERGY EFFICIENT ENGINE EXHAUST MIXER MODEL N82-22268*# Beech Aircraft Corp.. Wichita. Kans. TECHNOLOGY ADVANCED GENERAL AVIATION ENGINE/AIRFRAME H. Kozlowski and M. Larkin Jun. 1981 186 p refs INTEGRATION STUDY (Contract NAS3-20646) Leon A. Zmroczek Mar. 1982 131 p refs (NASA-CR-165459; NAS 1.26:165459; PWA-5594-164) Avail: (Contract NAS3-22220) NTIS HC A09/MF A01 CSCL 21E (NASA-CR-165565: NAS 1.26:165565) Avail: NTIS An exhaust mixer test program was conducted to define HC A07/MF A01 CSCL 21E the technology required for the Energy Efficient Engine Program. A comparison of the in-airframe performance and efficiency The model configurations of 1/10 scale were tested in two of the advanced engine concepts is presented. The results indicate phases. A parametric study of mixer design options, the impact that the proposed advanced engines can significantly improve of residual low pressure turbine swirl, and integration of the the performance and economy of general aviation airplanes.* The mixer with the structural pylon of the nacelle were investigated. engine found to be most promising is the highly advanced version The improvement of the mixer itself was also studied. Nozzle of a rotary combustion (Wankel) engine. The low weight and

354 N82-22277 fuel consumption of this engine, as well as its small size, make of airframe with crew but without engines, engine weight, and it suited for aircraft use. T.M. fuel weight was defined. An 850 hp engine was made more powerful by increasing turbine inlet temperature through the N82-22269*# National Aeronautics and Space Administration. cooling of the high pressure turbine and by increasing pressure Lewis Research Center. Cleveland, Ohio. ratio. Analysis shows that a sufficient power reserve is necessary, PERFORMANCE OF SINGLE-STAGE AXIAL-FLOW TRAN- but too high a value penalizes operating cost. This confirms the SONIC COMPRESSOR WITH ROTOR AND STATOR ASPECT interest of having a super emergency rating on civil helicopter RATIOS OF 1.63 AND 1.77. RESPECTIVELY. AND WITH engines. Low fuel consumption should be the result of a DESIGN PRESSURE RATIO OF 2.05 compromise with level of complexity since high complexity Royce D. Moore and Lonnie Reid Apr. 1982 116 p refs increases the engine cost and can reduce reliability. Simultaneous (NASA-TP-2001: E-334: MAS 1.60:2001) Avail: NTIS evolution of aircraft and engine increases cost effectiveness. HC A06/MF A01 CSCL 21E Author (ESA) The overall and blade-element performance of a transonic compressor stage is presented over the stable operating range N82-22274# Rolls-Royce Ltd.. Derby (England). for speeds from 50 to 100 percent of design. The stage was ENCOUNTERS WITH SURGE: SOME EXPERIENCES OF designed for a pressure ratio of 2.05 at a flow of 20.2 kg/sec DEVELOPMENT OF AXIAL COMPRESSORS FOR AERO GAS and a tip speed of 455 m/sec. At design speed the rotor and TURBINES stage achieved peak efficiencies of 0.849 and 0.831. respectively, A. B. McKenzie Mar. 1981 35 p at the minimum flow condition. The stage stall point occurred (PNR-90071) Avail: NTIS HC A03/MF A01 at a flow higher than the design flow. Author Rolls Royce jet engine development is traced. The Avon was the first. Its design pressure ratio is 6.15, corresponding to N82-22270| Rolls-Royce Ltd.. Derby (England). a design temperature rise of 20 C per stage in each of 12 RB211 POWERPLANT DETERIORATION: REVIEW OF stages. The first stage entry diameter ratio is 0.5, lower than CURRENT SITUATION AND LESSONS LEARNED contemporary compressors. In the Avon RA14, surge, precipitated Alec G. Collins 1981 5 p when a number of stages stalled, was eliminated by progressively (PNR-90073) Avail: NTIS HC A02/MF A01 increasing the stagger of the last six rotor blade rows by 1 deg The need for high temperatures in the engine cycle of gas to 6 deg. In the Conway. a bypass provides a permanent bleed turbine aircraft engines was demonstrated: the effects of thermal from the low pressure compressor. The bleed becomes an barrier coatings (TBC) on component life, cooling air requirements, increasing proportion of total flow as speed is reduced. This and turbine entry temperature (TET) are discussed. Experience eliminates surge problems when the engine is throttled back at with the RB211, Olympus 593, and Pegasus engines illustrates high forward speed. In the Tyne. the removal of the hub section the usefulness of TBCs consisting of zirconia based ceramics permits a higher surge pressure ratio. In the RB211, a handling with nickel or cobalt bond coats. Life improvements > 50% are bleed with a variable input is placed between the compressors. directly attributable to TBCs on combustor walls, vaporizing fuel Author (ESA) injectors, and discharge nozzles. Airfoil coatings survive 150 hr RB211-524 tests at higher than normal TET. Author (ESA) N82 22275# Rolls-Royce Ltd.. Derby (England). RELIABLE POWER N82-22271# Rolls-Royce Ltd., Derby (England). J. M. S. Keen Feb. 1981 21 p Presented at Intern. Aircraft THE CONTRIBUTION OF THERMAL BARRIER COATINGS Maintenance Eng. Exhibition and Conf., Zurich, Feb. 1981 TO IMPROVEMENTS IN THE LIFE AND PERFORMANCE (PNR-90078) Avail: NTIS HC A02/MF A01 OF GAS TURBINE COMPONENTS The Rolls Royce RB211 engine design is reviewed. The S. J. Hartropp. D. A. Marsh, and G. W. Meetham 1981 lip three shaft concept increases engine thrust and cuts fuel (PNR-90076) Avail: NTIS HC A02/MF A01 consumption. The highest thrust version of the RB211 cuts fuel Ceramic coatings significantly increase the lives of components consumption of Boeing 747's by 17%. The 535E4 blends turbine in high temperature environments by insulating metal substrates and bypass flows in a buried nozzle within a longer cowl. The from a hot gas stream. The need for high temperatures in gas resultant gases are exhausted through a single final nozzle. This turbine engines, and the opportunities for and requirements from device provides an automatic rematching of the engine cycle at thermal barrier coatings are covered. Bench and service engine climb ratings, thereby saving fuel and reducing turbine entry evaluation and analysis of tested parts from which the features temperature. Reverse thrust is increased by up to 38% relative to an unmixed engine. The on-condition maintenance policy of successful coating systems were derived, are presented. reduces costs without reducing safety. The reliability management Author (ESA) program ensures the most cost effective maintainance schedule. Author (ESA) N82 22272# Rolls-Royce Ltd., Derby (England). DEVELOPMENT OF A CORRELATED FINITE ELEMENT N82 22276# Rolls-Royce Ltd.. Derby (England). DYNAMIC MODEL OF A COMPLETE AERO ENGINE FUEL EFFICIENCY ENGINES FOR LARGE TRANSPORT R. A. Bellamy. J. C. Bennett, and S. T. Elston 1981 10 p AIRCRAFT refs D. J. Parfitt 27 Mar. 1981 27 p Presented at Aeron. Soc. (PNR-90081) Copyright. Avail: NTIS HC A02/MF A01 of India Conf, Bombay, 27 Mar. 1981 The accuracy of the dynamic model of the RB211 engine (PNR-90082: MISC-555) Avail: NTIS HC A03/MF A01 and nacelle was tested. Model descriptions of load/deflection The next generation of Rolls Royce aircraft engines is behavior, natural frequencies, and mode shapes were compared discussed, especially their fuel consumption. For the RB211, with shake tests and modal analyses. Modal analysis was carried improvements on the order of 15% in fuel consumption relative out by a frequency response analyzer which used an incremental to the initial service standard are planned. Large fan engines sine technique and a minicomputer based system that input a are expected to remain technology leaders in the long-term. random signal to the shaker, operating on transducer measure- Fuel savings on the order of 10% to 15% are feasible, using ments with a software Fourier transform in order to achieve the low specific thrust designs. Noise and exhaust emission frequency response functions. Correlation between the results is improvements are predicted. Advanced wing designs and the excellent. Author (ESA) use of lightweight composite materials, linked with full authority digital control systems, enhance engine performance. Liquid N82-22273# Societe Nationale Industrielle Aerospatiale, hydrogen is suggested as a replacement for kerosene, because Marignane (France.) Helicopter Div. of its high heating value. Author (ESA) PARAMETRIC STUDY OF THE INFLUENCE OF THE ENGINE UPON THE OPERATING COST OF A CIVIL HELICOPTER Gilbert Beziac, Jean-Pierre Dedieu, and Philippe Cabrit Paris N82-22277| Rolls-Royce Ltd., Derby (England). 1981 6 p Presented at 7th European Rotorcraft and Powered COLLABORATIVE DEVELOPMENT OF AERO-ENGINES Lift Aircraft Forum. Garmisch-Partenkirchen, West Germany G. M. Lewis 1981 9 p 8-11 Sep. 1981: sponsored by DFVLR. Cologne (PNR-90083) Avail: NTIS HC A02/MF A01 (SNIAS-827-210-102) Avail: NTIS HC A02/MF A01 European cooperation in aircraft engine development is The influence of engine characteristics (weight, fuel consump- described, using the Olympus and RB199 projects as examples. tion, price, power range) upon helicopter operating cost was The management structure was based on the integration of studied. The parametric relationship between gross weight, weight existing teams in the partner companies. Author (ESA)

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N82-22278# Rolls-Royce Ltd.. Derby (England). N82-22282# National Aerospace Lab.. Tokyo (Japan). MULTI-MISSION V/STOL WITH VECTORED THRUST EXPERIMENT ON ACTIVE FLUTTER SUPPRESSION OF A ENGINES CANTILEVER WING W. J. Lewis and P. Simpkin 1981 10 p Takao Kikuchi and Hae Kyong Lee Dec. 1981 10 p refs In (PNR-90086) Avail: NTIS HC A02/MF A01 JAPANESE: ENGLISH summary The use of V / STOL aircraft in European conflicts is dis (NAL-TR-690: ISSN-0389-4010) Avail: NTIS cussed. Conventional aircraft were assumed to be inoperative within HC A02/MF A01 370 km of the main battle area because of the destruction of An experiment on active flutter suppression of a cantilever runways. Achievable bomb delivery rate of subsonic V/STOL wing with the control surface at the wing tip is described. The aircraft, and available combat air patrol time and the number of experiment was done in a low subsonic wind tunnel. The deflection aircraft required in order to maintain a standing patrol of of the wing was measured by strain gages located near the supersonic aircraft were considered. If the Harrier concept is root of the wing. The aileron was driven by a servomotor. adapted, a single vectored thrust engine with plenum chamber Comparison was made between the present and previous results. burning on two front nozzles, and a single rear nozzle, then the It is concluded that the coefficients of the control law may V/STOL aircraft is well suited to supersonic and subsonic air have a different effect on the stability of the two- and three- superiority and strike roles. Author (ESA) dimensional models. Author

N82-22279| Rolls-Royce Ltd.. Derby (England). N82-22284*# National Aeronautics and Space Administration. DIRECTIONAL SOLIDIFICATION: PROJECT 82 Final Washington, D. C. Report STUDIES ON WIND TUNNEL STRAIGHTENERS C. Lecomte-Mertens. M. Lamberigts. and D. Coutsouradis May F. Schultz-Grunow and K. Wieghardt Mar. 1982 16 p refs 1981 109 p refs Transl. into ENGLISH of Rept.no. TLT-00818A. Transl. into ENGLISH from Luftfahrtforschung (West Germany), Centre de Rech. Metal. (Belgium) Partly in ENGLISH and v. 17, no. 3. 20 Mar. 1940 p 82-86 Transl. by Kanner (Leo) FRENCH Associates, Redwood City. Calif, original doc. prep, by Kaiser- (PNR-90088: Trans-15572/TLT-00818A) Avail: NTIS Wilhelm Inst. for Flow Research, Goettingen (West Germany) HC A06/MF A01 (Contract NASw-3541) Thermal fatigue of Mar-M-002 nickel alloy blades with an (NASA-TM-76689; NAS 1.15:76689) Avail: NTIS equiaxial or columnar (directional) structure, precision cast in HC A02/MF A01 CSCL 14B the laboratory, was evaluated. Their thermal fatigue is compared Tests using small-scale straighteners are reported. The studies with that of nickel alloy blades obtained elsewhere. Creep allowed conclusions on the most favorable depth relationships, resistance of the Mar-M-002 structures was tested. The influence flow conditions behind the straightener and on the drag. The of chemical composition, grain orientation, microstructural ways an obliquely hitting airflow is deflected by a straightener fineness, the presence of carbides, and morphology was are examined. In addition the flow drag was measured and the determined by metallography. Crack length is always greater in manner in which the individual air columns emanating from the blades treated at 1100 C than in those treated at 1000 C. holes unite to form a homogeneous speed field was investi- Blade geometry is the predominant factor in thermal fatigue. gated. N.W. Crack resistance, in ascending order is: large solid blade (laboratory): small solid blade (outside supplier): small hollow N82-22286# National Inst. for Aeronautics and Systems blade (industrial). The metallographic structure is not a suitable Technology, Pretoria (South Africa). criterion for differentiating between the thermal shock behavior DESIGN OF DYNAMICALLY-SCALED. ASYMMETRICAL of equaxial blades and that of columnar blades. Author (ESA) WIND TUNNEL MODELS M. E. Beyers 6 Aug. 1981 18 p refs (NIAST-78/18) Avail: NTIS HC A02/MF A01 N82-22280*# National Aeronautics and Space Administration. Dynamically scaled models are used in aerodynamic studies, Langley Research Center, Hampton, Va. notably in aircraft/store or stage separation studies. Techniques CONTROL LAW DESIGN TO MEET CONSTRAINTS USING were developed for the design of free flight models in three SYNPAC-SYNTHESIS PACKAGE FOR ACTIVE CONTROLS general categories: dynamic stability free flight models, high William M. Adams. Jr. and Sherwood H. Tiffany Jan. 1982 maneuverability models optimized for nonoscillatory motion 16 p refs Presented at the Joint Automatic Control Conf. studies, and dynamic separation models. Dynamic scaling with Charlottesville, Va.. 17-19 Jun. 1981 fully simulated mass asymmetries play an important part in each (NASA-TM-83264; NAS 1.15:83264) Avail: NTIS of the three categories, particularly when nonplanar motions are HC A02/MF A01 CSCL 01C simulated. The method is implemented in a 'FORTRAN IV DSAM' Major features of SYNPAC (Synthesis Package for Active S.L. Controls) are described. SYNPAC employs constrained optimization techniques which allow explicit inclusion of design criteria N82-22286# Research Inst. of National Defence. Umea (Sweden). (constraints) in the control law design process. Interrelationships Huvudavdelning 4. are indicated between this constrained optimization approach, RADIAK SIMULATOR FOR AIRCRAFT INSTRUMENTS classical and linear quadratic Gaussian design techniques. Results [RADIAKSIMULATOR FOER FLYGINDIKERING] are presented that were obtained by applying SYNPAC to the Goeran Hulten. Melker Nordstrand. and Thomas Ulvsand Jun. design of a combined stability augmentation/gust load alleviation 1981 30 p ref In SWEDISH control law for the OAST ARW-2. Author (FOA-C-40136-A3) Avail: NTIS HC A03/MF A01 An intensimeter no. 23 was used to detect radiation from N82-22281*jf! National Aeronautics and Space Administration. aircraft. A simulator which could be programmed to give different Ames Research Center, Moffett Field, Calif. time controlled simulated lapses was added to the equipment. AN ANALYSIS OF A NONLINEAR INSTABILITY IN THE The missions programmed into the memory included indications IMPLEMENTATION OF A VTOL CONTROL SYSTEM along a road, over an area and spot indications. Testing was Jeanine M. Weber Mar. 1982 65 p refs performed at the Army Helicopter school in Boden under realistic (NASA-TM-84220; A-8840: NAS 1.15:84220) Avail: NTIS conditions. Results indicate that this type of simulation is useful HC A04/MF A01 CSCL QIC in training aircraft indication personnel. M.D.K. The contributions to nonlinear behavior and unstable response of the model following yaw control system of a VTOL aircraft during hover were determined. The system was designed as a N82-22314*# Boeing Commercial Airplane Co.. Seattle. Wash. state rate feedback implicit model follower that provided yaw THE 737 GRAPHITE COMPOSITE FLIGHT SPOILER FLIGHT rate command/heading hold capability and used combined full SERVICE EVALUATION Annual Report. May 1980 - Apr. authority parallel and limited authority series servo actuators to 1981 generate an input to the yaw reaction control system of the Randy L Coggeshall Feb. 1982 50 p refs aircraft. Both linear and nonlinear system models, as well as (Contract NAS1-11668) describing function linearization techniques were used to determine (NASA-CR-165826: NAS 1.26:165826: D6-37330: the influence on the control system instability of input magnitude AR-7) Avail: NTIS HC A03/MF A01 CSCL 11D and bandwidth, series servo authority, and system bandwidth. A flight service report was prepared which covers the flight Results of the analysis describe stability boundaries as a function service experience of 111 graphite epoxy spoilers on 737 transport of these system design characteristics. A.R.H. aircraft and related ground based environmental exposure of

356 N82-22398 graphite epoxy material specimens. Spoilers were installed on Panel. Noordwijkerhout. Netherlands. 27 Sep. - 2 Oct. 1981 28 aircraft representing seven major airlines operating throughout (AGARD-R-693: ISBN-92-835-1412-2) Avail: NTIS the world. Tests of removed spoilers after the seventh year, of HC A02/MF A01 service continue to indicate modest changes in composite strength Critical metals are reviewed relative to their current importance properties. Two spoilers were tested, one with 6 and one with to the aerospace industry. The roles of conservation, recycling, 7 years of service, and both had residual strengths that fall substitution, stockpiling and market place operations are analyzed. within the original static strength scatter band. Both these units Technologies are discussed relative to their effects on the critical had typical service included discrepancies when tested. Based metals, and finally, suggestions are presented for meeting material on visual, ultrasonic, and destructive inspection there continues supply problems. S.L to be no evidence of moisture migration into the honeycomb core and no core corrosion in the deployed units. M.D.K. N82-22358# Rolls-Royce Ltd.. Derby (England). POWDER METALLURGICAL INNOVATIONS FOR IM- N82-22315*# National Aeronautics and Space Administration. PROVED HOT SECTION ALLOYS IN AERO-ENGINE Langley Research Center. Hampton, Va. APPLICATIONS DEVELOPMENT AND DEMONSTRATION OF MANUFAC- P. Wildgoose. N. G. Turner. H. F. Davies. B. J. Helliwell. R. TURING PROCESSES FOR FABRICATING GRAPHITE/ Ubank, and H. Harrison 1980 27 p refs LARC 160 POLYIMIDE STRUCTURAL ELEMENTS Final (PNR-90072) Avail: NTIS HC A03/MF A01 Report The state of the art in powder material and processes, for R. K. Frost. J. S. Jones. P. J. Dynes, and D. H. Wykes Dec. aircraft engine combustor. blade, and disk alloys, was reviewed. 1981 499 p refs Processes developed in the 1970's include: gas atomization of (Contract NAS1-15371) superalloy powder for critical rotating parts: rotating electrode (NASA-CR-165809; NAS 1.26:165809) Avail: NTIS atomization for titanium powder in similar components; con- HC A21/MF A01 CSCL 11D troled thermomechanical processing of attrited powders in order The development and demonstration of manufacturing to produce superalloy sheet and airfoil parts; and plasma sprayed technologies for the structural application of Celion graphite/ gas atomized powder for hot section overlay and thermal LARC-160 polyimide composite material is discussed. Process barrier coatings. Development in titanium powder metallurgy is development and fabrication of demonstration components are hampered by difficulties in obtaining clean powder. Properties discussed. Process development included establishing quality equivalent to a conventionally processed product are obtained assurance of- the basic composite material and processing, in current alloys, with possible cost advantages. Author (ESA) nondestructive inspection of fabricated, components, developing processes for specific structural forms, and qualification of N82-22360# National Aerospace Lab.. Amsterdam (Netherlands). processes through mechanical testing. Demonstration compo- Div. of Structures and Materials. nents were fabricated. The demonstration components consisted ENGINEERING PROPERTY COMPARISONS OF 7050- of flat laminates, skin/stringer panels, honeycomb panels, chopped T73661. 7010-T7651 AND 7010-T73651 ALUMINUM ALLOY fiber compression moldings, and a technology demonstrator PLATE segment (TDS) representative of the space shuttle aft body flap. L. Schra and W. G. J. tHart Dec. 1980 33 p refs Submitted R.J.F. for publication (NLR-MP-80047-U) Avail: NTIS HC A03/MF A01 N82-22316*# Lockheed-California Co., Burbank. The strength, stress corrosion resistance, fracture toughness FLIGHT SERVICE EVALUATION OF KEVLAR-49 EPOXY and fatigue crack propagation resistance under flight simulation COMPOSITE PANELS IN WIDE-BODIED COMMERCIAL loading of aluminum alloys was tested. Standard tensile, notch, TRANSPORT AIRCRAFT Annual Flight Service Report center cracked and flight simulation tests were performed. In Robert H. Stone Jan. 1982 56 p refs order to study stress corrosion crack initiation, tuning fork type (Contract NAS1-11621) specimens were clamped to a wheel which immersed them in a (NASA-CR-165841; NAS 1.26:165841) Avail: NTIS 3.5% aqueous NaCI solution for 10 min/hr. Testing lasted for HC A04/MF A01 CSCL11D two months. Results show that both 7050 and 7010 are high Kevlar-49 fairing panels, installed as flight service compo- strength deep hardening alloys with only minor differences in nents on three 1-1011's, were inspected after 8 years service. crack tolerance properties. The fracture toughness of both alloys The fairings had accumulated a total of 62.000 hours, with one is equivalent, while 7050 possesses slightly better resistances ship set having 20,850 hours service. Kevlar-49 components to stress corrosion cracking and fatigue crack propagation under were found to be performing satisfactorily in service with no flight simulation loading. Author (ESA) major problems. The only defects noted were minor impact damage, a few minor disbonds and a minor degree of fastener hole fraying and elongation. The service history to date indicates N82-22392jjl Transportation Research Board. Washington. D.C. that Kevlar-49 epoxy composite materials have satisfactory service PAVEMENT MANAGEMENT AND REHABILITATION OF characteristics for use in aircraft secondary structures. R.J.F. PORTLAND CEMENT CONCRETE PAVEMENTS Charles V. Zegeer. Kenneth R. Agent. Rolands L. Rizenbergs, P. C. Curtayne, T. Scullion, R. Daryl Pedigo. W. Ronald Hudson. N82-22324jjl Deutsche Forschungs- und Versuchsanstalt fuer Freddy L. Roberts, M. A. Karan, Ralph Haas et al 1981 79 p Luft- und Raumfahrt. Stuttgart (West Germany). refs SERVICE LIFE INVESTIGATION OF A SAILPLANE WING (PB82-131384: TRB/TRR-814; ISBN-0-309-03255-5; OF CFRP CONSTRUCTION ISSN-0361-1981: LC-81-18882) Avail: NTIS C. Kensche 1981 33 p refs In GERMAN: ENGLISH summary HC A05/MF A01; HC also available from Transportation Presented at 17th OSTIV Congr, Paderborn-Haxterberg, West Research Board. 2102 Constitution Ave., NW. Washington. D.C. Germany, 26 May - 6 Jun. 1981 20418 CSCL 138 Avail: NTIS HC A03/MF A01 Pavement management and rehabilitation projects and A sailplane wing of CFRP design was investigated to guarantee techniques are discussed. The following topics are discussed: a higher stress level and longer service life than with glass fiber economic analyses and dynamic programming in resurfacing reinforced plastics and to define admissible design for the glider project selection; implementation of an urban pavement manage- industry. Fatigue tests were run according to a block program. ment system; pavement performance modeling for pavement The residual wing strength was also tested. Periodic measurements management; illustration of pavement management: from data are used to observe stiffness behavior during simulated service inventory to priority analysis: rehabilitation of concrete pavements life. No change in stiffness is observed during the tests. Stress by using portland cement concrete overlays; pavement manage- enhancement of 400 N/sq mm is admissible which increases ment study: Illinois tollway pavement overlays: resurfacing of service life from 3000 to 6000 hr. Author (ESA) plain jointed-concrete pavements: design procedure for premium composite pavement: model study of anchored pavement; N82-22348jjl Advisory Group for Aerospace Research and prestressed concrete overlay at O'Hare International Airport: Development. Neuilly-Sur-Seine (France). in-service evaluation: and. bonded portland cement concrete CRITICAL METALS CONSERVATION. RECYCLING AND resurfacing. GRA SUBSTITUTION E. F. Bradley (Pratt and Whitney Aircraft) Jan. 1982 23 p N82-22398*# Ohio State Univ.. Columbus. Dept. of Electrical Presented at the 53rd Meeting of the AGARD Struct, and Mater. Engineering.

357 N82-22478

GTD ANALYSIS OF AIRBORNE ANTENNAS RADIATING Felix L Pitts and Mitchel E. Thomas Mar. 1982 40 p refs IN THE PRESENCE OF LOSSY DIELECTRIC LAYERS (NASA-TM-83273: NAS 1.15:83273) Avail: NTIS Semiannual Report HC A03/MF A01 CSCL 048 R. G. Rojas-Teran and W. D. Bumside Aug. 1981 113 p Data waveforms obtained during the 1981 direct strike refs lightning tests, utilizing the NASA F-106B aircraft specially (Grant NsG-1498) instrumented for lightning electromagnetic measurements are (NASA-CR-168770; NAS 1.26:168770: ESL-710964-8) Avail: presented. The aircraft was operated in a thunderstorm environ- NTIS HC A06/MF A01 CSCL 20N ment to elicit strikes. Electromagnetic field data were recorded The patterns of monopole or aperture antennas mounted on for both attached lightning and free field excitation of the a perfectly conducting convex surface radiating in the presence aircraft. N.W. of a dielectric or metal plate are computed. The geometrical theory of diffraction is used to analyze the radiating system and extended here to include diffraction by flat dielectric slabs. Modified N82-22947*# Texas A&M Univ.. College Station. Oept. of edge diffraction coefficients valid for wedges whose walls are Mechanical Engineering. lossy or lossless thin dielectric or perfectly conducting plates THE ROLE OF COHERENT STRUCTURES IN THE GENERA- are developed. The width of the dielectric plates cannot exceed TION OF NOISE FOR SUBSONIC JETS Yearly Progress a quarter of a wavelength in free space, and the interior angle Report. 1 Nov. 1980 - 31 Oct. 1981 of the wedge is assumed to be close to 0 deg or 180 deg. Gerald L. Morrison 5 Apr. 1982 109 p refs Systematic methods for computing the individual components (Grant NAG 1-112) of the total high frequency field are discussed. The accuracy of (NASA-CR-168764: NAS 1.26:168764) Avail: NTIS the solutions is demonstrated by comparisons with measured HC A06/MF A01 CSCL 20A results, where a 2 lambda by 4 lambda prolate spheroid is The coherent structure in high Reynolds number (184.000 to used as the convex surface. A jump or kink appears in the 262.000), Mach number 0.6 to 0.8 axisymmetric cold air jets calculated pattern when higher order terms that are important exhausting at atmospheric pressure was studied. The mean flow are not included in. the final solution. The most immediate and the statistical time averaged turbulence properties were application of the results presented here is in the modelling of measured. Spectra showed a very broad frequency content which structures such as aircraft which are composed of nonmetallic shifted towards the lower frequencies as the flow progressed parts that play a significant role in the pattern. S.L downstream. Axial wave number measurements indicate that the axial wave number-frequency relationship was the same for a wide range of Mach (0.3 to 2.5) and Reynolds (3.700 to over N82-22478*# National Aeronautics and Space Administration. 200,000) numbers. Measurements of the azimuthal mode numbers Ames Research Center. Moffett Field. Calif. show that several modes from n = -3 to +3 exist simultaneously A PORTABLE. LOW-COST FLIGHT-DATA MEASUREMENT in various quantities that the different frequencies studied. Acoustic AND RECORDING SYSTEM measurements were made in the near field of the Mach number Robert J. Miller Mar. 1982 18 p refs 0.6 jet. Sound pressure level contours showed that noise appeared (NASA-TM-84229; A-8871: NAS 1.15:84229) Avail: NTIS to be radiated from a location near the end of the potential HC A02/MF A01 CSCL 14E core. Directivity plots revealed that the spectra of this noise The design of and the experience with an inexpensive, shifted towards higher frequencies as the angle from the jet hand-portable, onboard data system used to record four axis increased. It was also found that mid-band excitation parameters in the final portion of the landing approach and frequencies produced an increase in full spectrum noise. M.G. touchdown of an airplane are described. The system utilized a high-quality audio tape recorder and amateur photographic N82-22949*# Kentron International. Inc.. Hampton. Va. equipment with accessory circuitry rather than specialized PROGRAM FOR NARROW-BAND ANALYSIS OF AIRCRAFT instrumentation to given satisfactory results. Author FLYOVER NOISE USING ENSEMBLE AVERAGING TECH- NIQUES N82-22499# Applied Physics Lab.. Johns Hopkins Univ.. Laurel. Doreen Gridley Mar. 1982 70 p refs Md. (Contract NAS1-16000) PROTOTYPE FLYWHEEL SPIN TESTING PROGRAM Final (NASA-CR-165867: NAS 1.26:165867) Avail: NTIS Report. 21 Mar. 1980 - 16 Apr. 1981 HC A04/MF A01 CSCL 20A D. W. Rabenhorst and W. 0. Wilkinson Apr. 1981 59 p refs A package of computer programs was developed for analyzing Prepared for California Univ., Livermore. Lawrence Livermore acoustic data from an aircraft flyover. The package assumes the Lab. aircraft is flying at constant altitude and constant velocity in a (Contract W-7405-eng-48) fixed attitude over a linear array of ground microphones. Aircraft (UCRL-15381: SDO-5988) Avail: NTIS HC A04/MF A01 position is provided by radar and an option exists for including Flywheels were spin tested to determine for each flywheel the effects of the aircraft's rigid-body attitude relative to the (1) the rotational speed at flywheel failure and (2) within the flight path. Time synchronization between radar and acoustic capability of the facility, the initiation and mode of failure of recording stations permits ensemble averaging techniques to be the flywheel. The flywheel tested ranged in size from 12.0 to applied to the acoustic data thereby increasing the statistical 24.0 inches diameter: in weight from 5.0 to 28.5 pounds, and accuracy of the acoustic results. Measured layered meteorological in energy at failure up to 711 watt hours. M.D.K. data obtained during the flyovers are used to compute propagation effects through the atmosphere. Final results are narrow-band N82-228O8rfl National Aerospace Lab.. Amsterdam (Netherlands). spectra and directivities corrected for the flight environment to Wetenschappelijke Diensten Hoofdafdel. an equivalent static condition at a specified radius. R.J.F. CALCULATION OF THE CONTRIBUTIONS OF AIR TRAFFIC AND ROAD TRAFFIC TO AIR POLLUTION IN THE REGION N82-22962*| Bolt. Beranek. and Newman. Inc.. Canoga Park. OF SCHIPHOL AIRPORT IN 1974 Calif. J. J. Tiggelaar Oct. 1981 51 p refs In DUTCH: ENGLISH ANALYTICAL PREDICTION OF THE INTERIOR NOISE FOR summary Sponsored by Netherlands Ministerie van Volksgezond- CYLINDRICAL MODELS OF AIRCRAFT FUSELAGES FOR heid en Milieuhygiene PRESCRIBED EXTERIOR NOISE FIELDS. PHASE 2: (NLR-TR-77100-U) Avail: NTIS HC A04/MF A01 MODELS FOR SIDEWALL TRIM. STIFFENED STRUCTURES Annual and quarterly averages of CO. NOx and CxHy AND CABIN ACOUSTICS WITH FLOOR PARTITION concentrations in the Schiphol airport region are calculated using L. D. Pope and E. G. Wilby Apr. 1982 212 p refs a mathematical model. The method models traffic into a set of (Contract NAS1 -15782) line and point sources with constant emission. For CO and NOx (NASA-CR-165869: NAS 1.26:165869) Avail: NTIS the road traffic contribution to air pollution is largest, while for HC A10/MF A01 CSCL 20A CxHy the air traffic contribution is largest. The measurements An airplane interior noise prediction model is developed to suggest that other sources contribute at least as much to global determine the important parameters associated with sound air pollution as do road and air traffic. Author (ESA) transmission into the interiors of airplanes, and to identify apropriate noise control methods. Models for stiffened structures, N82-22848*# National Aeronautics and Space Administration. and cabin acoustics with floor partition are developed. Validation Langley Research Center, Hampton, Va. studies are undertaken using three test articles: a ring stringer THE 1981 DIRECT STRIKE LIGHTNING DATA stiffened cylinder, an unstiffened cylinder with floor partition.

358 N82-22990 and ring stringer stiffened cylinder with floor partition and N82-22963# Deutsche Forschungs- und Versuchsanstalt fuer sidewall trim. The noise reductions of the three test articles are Luft- und Raumfahrt. Berlin (West Germany). Abt. Tur- computed using the heoretical models and compared to measured bulenzforschung. values. A statistical analysis of the comparison data indicates PREDICTION OF FLYOVER JET NOISE SPECTRA FROM that there is no bias in the predictions although a substantial STATIC TESTS random error exists so that a discrepancy of more than five or Ulf Michel and Alfons Michalke (Technische Univ.. Berlin) In six dB can be expected for about one out of three predictions. Ecole Centrale de Lyon Euromech 142: Acoustics of Turbulent S.L. Flows 1981 4 p refs

N82-22953# National Aerospace Lab.. Tokyo (Japan). Noise Avail: NTIS HC A08/MF A01 and Emission Research Group. A scaling law for predicting the overall flyover noise of a AERODYNAMIC NOISE GENERATED BY JET-WING/FLAP single stream shock-free circular jet from static experiments is INTERACTIONS OF THE EXTERNAL USB CONFIGURATION outlined. It is valid for isothermal and hot jets. It assumes that OF STOL AIRCRAFT. PART 1: EIGHT PERCENT SCALE the jet flow and turbulence field are axially stretched in flight. COLD-FLOyV MODEL ANALYSIS Effects of the boundary layer within the nozzle and along the Masataka Malta and Shigemi Shindo Oct. 1981 29 p refs engine nacelle are neglected. The scaling laws for the power (NAL-TR 685T; ISSN-0389-4010) Avail: NTIS spectral density and spectra with constant relative bandwidth HC A03/MF A01 can be derived. In order to compare static and inflight directivities, The acoustic characteristics of the external upper surface the far field point relative to the source position must be blowing (USB) concept of a powered high lift system (PHLS) denoted by the emission angle and the wave normal distance. were studied experimentally using an 8%-scale static cold flow From the solution of the convective Lighthill equation in a model. Observations of exhaust jet flow attachment and spreading coordinate system fixed to the jet nozzle (wind tunnel case), the characteristics on wing/flap surface were also carried out using power spectral density of sound pressure at a given frequency several flow visualization techniques. Noise reduction data were is found. Predictions for Aerotrain compare well with measured obtained by optimizing basic jet nozzle wing/flap structural values. Author (ESA) geometries for the lowest noise. Among the associated parameters which define USB-PHLS configurations, (1) the location relative N82-22976# Societe Nationale Industrielle Aerospatiale. to wing/flap and the shape of the exhaust jet nozzle and (2) flow Toulouse (France). attachment devices are important parameters. Flow characteristics AIRCRAFT AERODYNAMIC NOISE DURING APPROACH dependence on these parameters and PHLS noise were also [BRUIT AERODYNAMIQUE DES AVIONS EN APPROCHE] obtained. From far field noise spectra overall sound pressure J. L. Parant In Ecole Centrale de Lyon Euromech 142: Acoustics level dependence on jet velocity and coherence across near field of Turbulent Flows .1981 3p In FRENCH surface pressure, it was concluded tht the flap trailing edge Avail: NTIS HC A08/WIF A01 noise was the most predominant noise source. Several acoustically treated flaps and serrated trailing edge design techniques were The effect of approach velocity, nose and flap inclination, and undercarriage position on aircraft noise was studied. The A applied to attenuate edge noise. Author 300 B and SN 601 aircraft made two approach passes over a N82-22965*# DyTec Engineering, Inc.. Long Beach, Calif. chain of noise recorders. The sound fields and noise spectra RECOMMENDATIONS FOR FIELD MEASUREMENTS OF show that increasing the speed and flap angle or lowering the AIRCRAFT NOISE Final Report undercarriage produces a general increase in noise level such Alan H. Marsh Washington NASA Apr. 1982 94 p refs that the directivity of the aerodynamic noise source is hardly (NASA-CR-3540; NAS 1.26:3540) Avail: NTIS changed. All noise spectra increase. Pure frequencies (400 to HC A05/MF A01 CSCL 20A 500 Hz) accompany flap deployment for the SN 601. Specific recommendations for environmental test criteria, data Anthnr IFSAI acquisition procedures, and instrument performance requirements N82-22978# Deutsche Forschungs- und Versuchsanstalt fuer for measurement of noise levels produced by aircraft in flight Luft- und Raumfahrt, Goettingen (West Germany). are provided. Recommendations are also given for measurement of associated airplane and engine parameters and atmospheric EXPERIMENTS ON PROPELLER NOISE conditions. Recommendations are based on capabilities which F. R. Grosche and H. Stiewitt In Ecole Centrale de Lyon Euromech were available commercially in 1981: they are applicable to 142: Acoustics of Turbulent Flows 1981 4 p refs field tests of aircraft flying subsonically past microphones located near the surface of the ground either directly under or to the Avail: NTIS HC A08/MF A01 side of a flight path. Aircraft types covered by the recommenda- Propeller sound generation was investigated. Tests were tions include fixed-wing airplanes powered by turbojet or performed at flow velocities up to 58 in/sec on 90 cm dia. turbofan engines or by propellers. The recommended field- four bladed propellers driven by an electric motor enclosed in a streamlined nacelle. Five models with different blade geometries measurement procedures are consistent with assumed require- were tested at helical tip Mach numbers up to 0.69. Nearfield ments for data processing and analysis. R.J.F. blade tip measurements were made at 0.14 dia. by an in-flow N82-22962# New South Wales Univ.. Sydney (Australia). School microphone. The acoustic far field was measured by four of Mechanical Engineering. microphones outside the wind tunnel flow 2.7 m from the ACOUSTIC EMISSION FROM FREE JETS propeller axis. An acoustic mirror telescope with three microphones S.-L. Hall In Ecole Centrale de Lyon Euromech 142: Acoustics was used to investigate sound generation from the upper, central of Turbulent Flows 1981 4 p and lower parts of the propeller. The spectrum in the propeller plane is dominated by the tonal components at the blade Avail: NTIS HC A08/MF A01 passing frequency and its harmonics. Tonal component amplitude Nozzle centered radiation, wider spaced waves, and low angle is greatly reduced downstream. The blades radiate high frequen- waves are seen in correctly expanded supersonic jets. In working cy noise mainly in motion direction. Author (ESA) conditions, shock jet interaction, resulting from incorrect expansion, generates additional high frequency noise. Underexpanded jets N82-22990# Deutsche Forschungs- und Versuchsanstalt fuer emit more noise than overexpanded jets, due to operating at Luft- und Raumfahrt, Brunswick (West Germany). Abteilung higher Mach numbers and oscillations of the shock cells. Technische Akustik. Shadowgraphs and Schlieren photographs show that helium jets GROUND REFLECTION EFFECTS IN MEASURING PROPEL- have larger angles and greater extent of noise radiation than air LER AIRCRAFT FLYOVER NOISE jets. Mathematical models for correctly expanded supersonic air Werner Dobrzynski Aug. 1981 85 p refs In GERMAN: jets exhausting into the quiescent atmosphere, given no extraneous ENGLISH summary Report will also be announced as (ESA-TT- shocks near the nozzle exit, calculate acoustic wave angles to 742) within 3 deg of measured values. Similar accuracy is achieved (DFVLR-FB-81-28: ESA-TT-742) Avail: NTIS HC A05/MF A01: for helium jets when the ratio of acoustic impedances is used DFVLR. Cologne DM 21 to correct the air jet values for refraction and convection effect!. In measuring flyover noise for purposes of propeller aircraft Models give reasonably good prediction of wave angles from + noise certification, microphones are positioned 1.2 m above the or - 50% of the correct expansion. For jits without extraneous ground. The influence of ground reflection on the maximum A shocks, when correctly expanded, calculated angles are within weighted aircraft noise level was investigated. Ground reflection 4 deg of measured values. Author (ESA) induces level differences of up to 3 db (A), depending on rotational

359 N82-23068

speed and number of blades. Since reflection corrections can A flutter speed is calculated for the initial fully stressed design not successfully be applied to propeller noise signatures, being 700 kt. After 5 iterations the desired flutter speed of alternative measuring arrangements, such as microphones in close 900 kt is reached with an increase < 3% total weight. Good proximity to the ground, were investigated. For different correlation with more sophisticated analyses, e.g.. NASTRAN is microphone orientations next to an acoustically hard, smooth achieved. The aeroelastic deformation of a fin and rudder are surface, or above ground plates in case of grass covered surfaces, calculated statisfactorily without iteration using the aerodynamic frequency regimes not affected by ground reflection interferences influence matrix produced by a separate program module. A 5% are determined. Author (ESA) weight saving is achieved for the delta wing. Aileron aeroelastic efficiency is above specification for a supersonic roll. N82-23068# Committee on Science and Technology (U. S. Author (ESA) House). THE 1983 NASA AUTHORIZATION, VOLUME 1 N82-23150# Advisory Group for Aerospace Research and Washington GPO 1982 114p Hearing before the Subcomm. Development, Neuilly-Sur-Seine (France). on Transportation, Aviation and Mater, of the Comm. on Sci. FLUID DYNAMICS OF JETS WITH APPLICATIONS TO and Technol., 97th Congr.. 2nd Sess.. No. 71. 17 Feb. 1982 V/STOL (GPO-91-488-Vol-1) Avail: Subcommittee on Transportation. Jan. 1982 433 p refs Proceedings of Symp. held at Lisbon, Aviation and Materials 2-5 Nov. 1981 (AGARD-CP-308: ISBN-92-835-0308-2) Avail: NTIS The status of NASA systems technology programs which provide focused technology applications principally to civil aviation HC A19/MF A01 The fluid dynamics of vertical and short take-off and landing is addressed in light of the cost effectiveness of NASA's partnership with the aircraft industry and the economic impact aircraft which employ thrust vectoring or lift augmentation were discussed. Jet interactions with neighboring surfaces, jet structure of the reduction of NASA's roll in promoting advanced aeronautical ' and development, wind tunnel simulation, injection and thrust technology. Progress made in research and technology pro- augmentation, and theoretical models were considered. grams encompassing aerodynamics, propulsion, materials and structures as well as controls and guidance, human factors, and low speed and high speed aircraft technology is reported. The six elements of the Aircraft Energy Efficiency program are N82-23161| Surrey Univ.. Guildford (England). Dept. of highlighted. These are: engine component improvement, energy Mechanical Engineering. efficient engine, advanced turboprop, energy efficient transport, SOME ASPECTS OF JET DYNAMICS AND THEIR IMPLICA- composite primary aircraft structures, and laminar flow control. TIONS FOR VTOL RESEARCH L. J. S. Bradbury In AGARD Fluid Dyn. of Jets with Appl. to The budget request for these programs is presented. N.W. V/STOL Jan. 1982 26 p refs

N82-23137# Messerschmitt-Boelkow-Blohm G.m.b.H., Otto- Avail: NTIS HC A19/MF A01 brunn (West Germany). Zentralbereich Entwicklung. Some of the problems associated with jet interference on RESEARCH AND DEVELOPMENT AT MBB. TECHNICAL VTOL aircraft are discussed. The jet interference that arises in AND SCIENTIFIC PUBLICATIONS. 1981 [FORSCHUNG hovering both in and out of ground effect is considered first UNO ETWICKLUNQ. TECHNISCH-WISSENSCHAFTLICHE and the factors that influence the entrainment that is responsible VEROEFFENTLICHUNGEN 1981] for the interference are discussed. In particular, it is shown that 1981 193 p refs Partly in ENGLISH and GERMAN the flow in the initial region of a jet is strongly affected by Avail: NTIS HC A09/MF A01 circumferential variations in the jet nozzle flow angle and that Research and development work carried out during 1981 at this might account for some of the anomolous results for the Messetschmitt-Bolkow-Blohm GmbH, Ottobrunn. FRG is decay of jets issuing from VTOL models. The possible use of presented. Aerodynamics, materials science, infrared imagery, Reichardt's method for studying the behavior of nonuniform jets aircraft and spacecraft design, and production engineering are is also discussed. The problem of jet interference in transition is discussed. Calculation methods, mathematical and scale models, next examined and the basis on which model tests are cur- and computer aided design are treated. Solar energy and high rently carried out is briefly reviewed. The dynamics of jet speed trains were investigated. interference in transition are then considered in more detail and it is suggested that unlike interference in hovering, transition N82'2314O# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- interference might well be accounted for on the basis of a potential brunn (West Germany). Military Aircraft Div. flow model of the jet in a cross flow. Some experimental evidence EXPERIENCE WITH HIGH PERFORMANCE V/STOL in support of this notion is examined and a few examples of FIGHTER PROJECTS AT MBB comparisons between predicted and experimental pressure Felix Aulehla and Gerhard K. Kissel In its Res. and Develop, at distributions around a single jet issuing from a flat plate are MBB. Tech. and Sci. Publ.. 1981 1981 16 p refs Presented given. Author at AIAA/NASA Ames V/STOL Conf.. Palo Alto. Calif. 7-9 Dec. 1981 N82-23158# Messerschmitt-Boelkow-Blohm G.m.b.H.. Munich (MB8-FE-124/S/PUB/50) Avail: NTIS HC A09/MF A01 (West Germany). Aircraft Div. Experience gained with V/STOL aircraft having the cap- AN EXPERIMENTAL AND THEORETICAL INVESTIGATION ability to reach Mach 2 and to take off at after-burning OF THE INTERACTION BETWEEN THE ENGINE JET AND temperatures is described. The German project VJ 101 C and THE SURROUNDING FLOW FIELD WITH REGARD TO THE the U-S/FRG project AVS as well as the joint U.S./FRG V/STOL PRESSURE DRAG ON AFTERBODIES Technology Program serve 'as examples. Guidance and control A. Zacharias In AGARD Fluid Dyn. of Jets with Appl. to systems are depicted, including hover and transition control. Jet V/STOL Jan. 1982 22 p refs interference aspects, e.g , hot gas ingestion during take off with reheated jets are described. Author (ESA) Avail: NTIS HC A19/MF A01 In order to clarify the interaction between rotationally N82-23141jjl Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- symmetric engine jets and afterbody configurations, the depen- brunn (West Germany). Aeroelastic Branch. dence of the jet characteristics (i.e.. the plume effect and the APPLICATION OF A STRUCTURAL OPTIMIZATION entrainment) and the afterbody pressure drag on the jet PROCEDURE FOR ADVANCED WINGS parameters, the free stream Mach number, and the afterbody Heinrich Goedel and Guenter Schneider In its Res. and Develop, geometry was analyzed. Extensive tests were carried out in the at MBB. Tech. and Sci. Publ.. 1981 1981 15 p refs Presented high subsonic Mach number range on three different afterbodies at 51st AGARD Meeting on Struct, and Mater. Panel. Aix-en- at Reynolds numbers from 500.000 to 1.300.000. The nozzle Provence,. France, 14-19 Sep. 1981 pressure ratio and the temperature ratio of the model jets were varied in the range (1.0) 1.2 to 2.4 and 1.0 to 2.86 respec- (MBB-FE-171/S/PUB/49; AGARD-691) Avail: NTIS tively. Measurements were then carried out to determine the HC A09/MF A01 static pressure and temperature distribution as well as the A finite element method optimization program was applied boundary layer profiles over the surface of the models. At the to: the sizing of a simplified metal wing for strength and flutter same time, the pressure and temperature profiles in the jet were constraints: aeroelastic efficiency calculations for fin and rudder: determined in several planes behind the jet exhaust plane. and the structural layout of a carbon fiber composite delta wing. Empirical equations are presented which show the dependence

360 N82-23170 of the plume effect, the entraimnent. and the afterbody pressure EVALUATION OF THE EFFECTS OF MODEL SCALE AND drag on the jet parameters, the free stream Mach number, and TEST TECHNIQUE ON JET-INDUCED EFFECTS the afterbody geometry. With the aid of a finite element method Stanley G. Kalemaris In AGARD Fluid Dyn. of Jets with Appl. and theoretical potential flow model for jet simulation, a numerical to V/STOL Jan. 1982 11 p procedure was developed which allows the pressure drag on rotationally symmetric afterbodies to be calculated with due Avail: NTIS HC A19/MF A01 allowance for the effects of the engine jets. Comparison of the The effects of model scale and test technique on the jet theoretical and experimental results shows satisfactory agree- induced of a twin turbofan V/STOL aircraft were evaluated. The ment. J.D. smallest mode was 2.1% as large as the full scale model. It is found that the two most important items to be modeled are N82-23163# Technische Hochschule. Aachen (West Germany). fuselage shape and the coannular nature of a typical turbofan Inst. fuer Luft- und Raumfahrt. exhaust. Lift enhancing strakes are effective in enhancing the FLOWFIELD AND NOISE SOURCES OF JET IMPINGEMENT ground cushion and eliminating a possible source of scale OF FLAPS AND GROUND SURFACE effect. E.A.K. Guenther Neuwerth In AGARD Fluid Dyn. of Jets with Appl. to V/STOL Jan. 1982 7 p refs N82-23168# Vereinigte Flugtechnische Werke G.m.b.H.. Bremen (West Germany). Avail: NTIS HC A19/MF A01 JET EFFECTS ON FORCES AND MOMENTS OF A VSTOL On the basis of experimental results it is shown that, in an FIGHTER TYPE AIRCRAFT undisturbed free jet of high subsonic speed as well as in a jet B. Haftmann In AGARD Fluid Dyn. of Jets with Appl. to deflected by externally blown flaps (EBF). there are ordered V/STOL Jan. 1982 13 p refs turbulence structures. First, a feedback mechanism which develops at small distances between nozzle and stagnation point on the Avail: NTIS HC A19/MF A01 flaps and which amplifies the turbulence structures is explained, Results of jet effects on forces and moments of the it is subsequently shown that the interaction of tne jets and VAK-191 B were compiled. The jet induced effects were EBF generates a strong noise. Even without feedback both the investigated during the Vertical/Short Take-Off and Landing undisturbed free jet and the jet deflected by EBF have the (VSTOU mode in and out of ground effect, in yawed flight, maximum levels in the noise spectrum at the Strouhal numbers during hover and transition right up to aerodynamic flight. The of the natural ordered turbulence structures. Author flight test results were compared with wind tunnel measurements performed during the VAK-191 B development phase and used N82-23165*# National Aeronautics and Space Administration. for preparation of simulation and automatic flight control system Langley Research Center. Hampton. Va. development. Trends and deviations between aircraft and model JET V/STOL WIND-TUNNEL SIMULATION AND GROUND- test results are verified. The adequacy of wind tunnel data PLANE EFFECTS preparation are questioned. The practicability of wind tunnel data Richard J. Margason In AGARD Fluid Dyn. of Jets with Appl. for the assessment of VSTOL aircraft design and determination to V/STOL Jan. 1982 21 p refs of flight characteristics and performances are discussed. Recommendations for the measurements of jet induced forces Avail: NTIS HC A19/MF A01 CSCL 01A and moments on VSTOL aircraft are outlined. E.A.K. The pretest preparation necessary to define the objectives of an appropriate investigation into the jet V/STOL wind tunnel N82-23169# Aeronautical Research Associates of Princeton. simulation and ground plane effects were examined. Low speed Inc., N. J. wind tunnel testing of V/STOL aircraft concepts to determine THRUST AUGMENTING EJECTORS: A REVIEW OF THE the aerodynamic propulsion interaction effects during the transition APPLICATION OF JET MECHANICS TO V/STOL AIRCRAFT between hover and wingbome flight is a necessary step in the PROPULSION development cycle of this type of aircraft. Powered models are Brian Quinn In AGARD Fluid Dyn. of Jets with Appl. to normally used to determine the aerodynamic performance V/STOL Jan. 1982 14 p refs characteristics. Several factors which influence the selection of the model concept and the engine simulator are discussed. Some Avail: NTIS HC A19/MF A01 of the test techniques important for this class of aircraft model The fundamental role played by the fluid dynamics of jets are examined. Wind tunnel wall effects important to this aircraft within thrust augmenting ejectors that are designed as propulsive testing with special emphasis on groundplane effects are units for V/STOL aircraft were reviewed. Energy transfer efficiency reviewed. E.A.K. and its impact on the production of thrust is discussed. It is explained why propellor like devices more effectively convert N82-23166*# McDonnell-Douglas Corp.. St. Louis. Mo. available energy to thrust and that overall ejector performance Aerodynamics Dept. is very sensitive to losses sustained by individual components. THE MODELING AND PREDICTION OF MULTIPLE JET VTOL The most important loss mechanism is incomplete mixing between AIRCRAFT FLOW FIELDS IN GROUND EFFECT the ejector's primary and entrained streams. An experimental Donald R. Kotansky In AGARD Fluid Dyn. of Jets with Appl. data base that provides insight into interactions between turbulent to V/STOL Jan. 1982 20 p refs mixing and other factors and improving mixing and ejector performance are reviewed. Free mixing and mixing in a con- (Contracts NAS2-9646: NAS2-10184: N62269-76-C-0086: fined environment are contrasted and it is concluded that the N00014-79-C-0130) development of theoretical methods that successfully predict the Avail: NTIS HC A19/MF A01 CSCL 01A performance of V/STOL ejectors must await the results of new An engineering methodology based on an empirical data experiments that measure turbulence intensities and Reynolds base and analytical fluid dynamic models was developed for the stresses in confined regions. E.A.K. prediction of propulsive lift system induced aerodynamic effects for multiple lift jet VTOL aircraft operating in the hover mode in N82-23170# Centre d'Etudes et de Recherches. Toulouse and out of ground effect. The effects of aircraft geometry, aircraft (France). Dept. of Aerothermodynamique. orientation (pitch, roll) as well as height above ground are THEORETICAL OPTIMISATION AND EXPERIMENTAL considered. Lift jet vector and splay directions fit the airframe. VERIFICATION OF AN INJECTOR lift jet exit flow conditions, and both axisymmetric and rectangular A. Mignosi In AGARD Fluid Dyn. of Jets with Appl. to V/STOL nozzle exit geometry are also accommodated. The induced Jan. 1982 12 p refs In FRENCH: ENGLISH summary suckdown flows are computed from the .potential flowfield induced by the turbulent entrapment of both the free jets and wall jets Avail: NTIS HC A19/MF A01 in ground effect and from the free jets alone out of ground A modelization of induction systems, which could be used effect. The methodology emphasized geometric considerations, for thrust augmentation or more generally constitute a fluid drive computation of stagnation lines and fountain upwash inclination, system, is proposed for the steady regime case. A simple scheme fountain upwash formation and development, and fountain in which a rapid mixing of the flows is assumed, allows to impingement on the airframe. E.A.K. solve the basic equations and express the main parameters influence. Its verification is effected, using a set of experimental N82-23167# Grumman Aerospace Corp.. Bethpage. N.Y. data obtained during the study of an induction driven wind-tunnel.

361 N82-23171

Various parameters (are ratio between injected and driven flows, optimization of the matching between angle and exhaust duct Mach number, pressure and temperature ratios) are studied. The system is developed. A theoretical approach is used by a synthesis injector configuration also appears to be very important, in program the appropriate numerical simulation of the ejector, both particular as to pressure fluctuations produced at injection and in the case of subsonic condition at the engine exhaust station the corresponding aerodynamic noise in the wind tunnel. Author and in a sonic station, with supersonic development of the flow through the ejector. To study the supersonic flow through the ejector a set of available experimental results is examinated to N82-23171# West Virginia Univ.. Morgantown. Coll. of evaluate the reliability of theoretical methods for the secondary Engineering. flow and for conditions. Hot condition experimental tests were UNSTEADY EJECTORS performed and was compared with theoretical calculations. The Herman Viets In AGARD Fluid Dyn. of Jets with Appl. to next step concerns the installation of a suitable ejector system V/STOL Jan. 1982 12 p refs on the AR 180.10 turbojet engine, which is a derived version of the AR 318 turboprop. E.A.K. (Grant AF-AFOSR-0025-81) Avail: NTIS HC A19/MF A01 N82-23179*| National Aeronautics and Space Administration. Ejectors are examined by introducing a time dependency Ames Research Center. Moffett Field. Calif. into the flow to increase the mixing rate and hence improve V/STOL AIRCRAFT AND FLUID DYNAMIC the performance of very short devices. Past studies of unsteady Leonard Roberts (Stanford Univ.) and Seth B. Anderson In flows related to ejectors are reviewed and a device is proposed AGARD Fluid Dyn. of Jets with Appl. to V/STOL Jan. 1982 which has the potential to increase the mixing by means of 5 p refs both an unsteady flow and also acoustic interaction between Avail: NTIS HC A19/MF A01 CSCL 01A the frequencies generated by the jet and the ejector shroud. The impact of military applications on rotorcraft and V/STOL Standing acoustic waves are identified in the ejector and. it is aircraft design with respect to fixed wing aircraft is discussed. found that the short unsteady ejector performance is superior to The influence of the mission needs on the configurational design that of a slot jet geometry. E.A.K. of V/STOL aircraft, the implications regarding some problems in fluid dynamics relating to propulsive flows, and their interaction N82-23172# Universite Scientifique et Medicale de Grenoble with the aircraft and the ground plane, are summarized. E.A.K. (France). Inst. de Mechanique. N82-23183I Vereinigte Flugtechnische Werke-Fokker G.m.b.H., IMPROVEMENT OF EJECTOR THRUST AUGMENTATION Bremen (West Germany). BY PULSATING OR FLAPPING JETS INTEGRATED NAVIGATION-TF/TA SYSTEM BASED ON G. Binder and H. Didelle In AGARD Fluid Dyn. of Jets with STORED TERRAIN DATA PROCESSING Appl. to V/STOL Jan. 1982 11 p refs Sponsored in part by Horst-Dieter Lerche In AGARD Guidance and Control Technol. Minstere de la Defense for Highly Integrated Systems Feb. 1982 13 p

Avail: NTIS HC A19/MF A01 Avail: NTIS HC A09/MF A01 The influence of pulsating or flapping motions forced on the A method to improve the reliability and optimization of terrain primary jet on the performance of thrust augmenting ejectors following flight is discussed. The terrain parameter comparison was investigated. The effect of the frequency and the amplitude (TERPAC) system is described in which the main source of of the forced perturbations was determined for various mixing information is a terrain data base aboard the aircraft. The duct lengths and diffusor geometries. In constant area ejectors comparison is done in the position-fix-mode by matching the the improvement in thrust augmentation ratio over the perfor- measured terrain signatures against terrain reference signatures mance obtained with a steady jet in the same geometry increases stored in the mass memory. A hardware and software design of with decreasing duct length. Thrust augmentation further improved the combined navigation and terrain following/avoidance flight by the gain in diffusor pressure recovery produced by the unsteady control system was developed and adapted to a modern avionic jets, Maximum augmentations of 1.9 and 1.65 were obtained system architecture. M.G. with pulsating and flapping jets respectively as compared to 1.35 and 1.5 in the steady case. These improvements in ejector N82-23184# Societe d'Applications Generales d'Electricite et performance are mainly due to the faster mixing produced by de Mecanique, Paris (France). these jets. E.A.K. OPTIMAL INERTIAL NAVIGATION USING TERRAIN CORRELATION: AN ATTRACTIVE SOLUTION TO THE GROUND ATTACK AIRCRAFT NAVIGATION PROBLEM N82-23173# Societe Benin et Cie. Plaisir (France). EXPERIMENTAL STUDY OF A JET DEFLECTOR [ETUDE L. Camberlein. M. deCremiers. and D. Chermette In AGARD EXPERIMENTALE D'UN DEVIATEUR DE JET] Guidance and Control Technol. for Highly Integrated Systems M. Lepretre and C. Portier In AGARD Fluid Dyn. of Jets with Feb. 1982 15 D In FRENCH: ENGLISH summary Appl. to V/STOL Jan. 1982 20 p refs In FRENCH: ENGLISH summary Sponsored in part by Delegation. Generale pour Avail: NTIS HC A09/MF A01 I'Armement The use of terrain correlation for all-weather penetration and Avail: NTIS HC A19/MF A01 ground attack aircraft is discussed. Positioning by terrain A provisional model of an aerodynamic device for orienting correlation is briefly reviewed. For the ground attack aircraft the thrust vector of a jet engine was set up by exploiting the application special algorithms allow large heading freedom over reattachment properties of a sonic or slightly supersonic jet on the updating area. The parameter sensitivity of the updating a flat or curved deflector conveniently positioned downwards accuracy is analysed. This includes the terrain characteristics, from the nozzle outlet. A parametric study shows that it would the cartography accuracy, and the altitude measurement accuracy. be possible to obtain important reverse rates without a drastic The main operational features for ground attack aircraft are loss of the resultant thrust. Such a device can be of benefit in summarized: tri-dimensional updating: high accuracy facilitated improving controllability during combat or in designing a STOL. by low altitude flight: self-contained, secure, jam-resistant, The arrangement defined is characterized by great simplicity, automated operation: a low level of heading constraint to and the jet reattachment is spontaneous over all the explored area, over the updating area: savings in weight, volume, electrical and no extra systems are required for blowing or suction. power and cost using sensors already needed on the aircraft. Transl. by A.R.H. The principle of inertial system optimal updating is also briefly discussed. Temporal carryover from position and velocity updates N82-23174| Alfa Romeo S.p.A.. Naples (Italy). can be crucial for accurate horizontal terrain following and weapon TURBOPROP AND TURBOJET EJECTOR OPTIMISATION delivery initialization and in-flight alignment of tactical missiles. The possibility of integrating correlation and optimal filtering in V. P. Riviello. A. Murolo. and G. Torella (Italian Air Force Academy) the inertial unit is shown. A typical all weather ground attack In AGARD Fluid Dyn. of Jets with Appl. to V/STOL Jan. mission scenario is described. This includes the extensive mission 1982 13 p refs preparation, the nominal flight plan and possible alternatives, Avail: NTIS HC A19/MF A01 update area selection using ground based equipment and map The off design performance of turboprop and turbojet engine data bases, and the data assembly and cassette loading. A possible with ejector exhaust ducts was investigated during the AR 318 operational systems architecture is described with the necessary turboprop engine development and certification program. The equipment. M.G.

362 N82-23196

N82-23186f McDonnell Aircraft Co.. St. Louis. Mo. A FLIGHT INVESTIGATION OF BLADE-SECTION AERODY- INTEGRATED FLIGHT AND FIRE CONTROL DEMONSTRA- NAMICS FOR A HELICOPTER MAIN ROTOR HAVING TION ON AN F-16B AIRCRAFT: SYSTEM DEVELOPMENT RC-SC2 AIRFOIL SECTIONS AND GROUND TEST RESULTS Charles E. K. Morris. Jr. Mar. 1982 163 p refs R. J. Landy. C. A. Scolatti. and J. E. Hunter (AFWAL) In AGARD (NASA-TM-83298: NAS 1.15:83298) Avail: NTIS Guidance and Control Technol. for Highly Integrated Systems HC A08/MF A01 CSCL 10A Feb. 1982 17 p refs Pressure data at 90 percent blade radius for a helicopter main rotor with RC-SC2 blade sections was obtained. Concurrent Avail: NTIS HC A09/MF A01 measurements were made of vehicle flight state, performance An integrated flight and fire control (IFFC) system is described and some rotor loads. The test envelope included hover, level which utilizes an automatic coupler and modified flight control flight from about 65 to 144 knots, climb and descent, and system to steer out tracking errors calculated by a director fire collective fixed maneuvers. Airfoil pressure distributions obtained control system using information from an ATLIS 2 electro-optical in flight agree with those theoretical calculations for two tracker. The F-15B aircraft is the test bed aircraft. .Simulation dimensional, steady flow. S.L. and analysis results indicate that the IFFC system has excellent air-to-air gunnery accuracy with decreased pilot workload. These N82-23193*# National Aeronautics and Space Administration. results also indicate that attacker survivability in air-to-ground Langley Research Center, Hampton, Va. gunnery and bombing encounters can be increased by using APPLICATION OF A TRANSONIC POTENTIAL FLOW CODE maneuvering approaches without compromising air-to-ground TO THE STATIC AEROELASTIC ANALYSIS OF THREE- weapon delivery accuracy. Extensive ground testing of IFFC DIMENSIONAL WINGS hardware and software is described. Details of the flight test Wood row Whitlow. Jr. and Robert M. Bennett Apr. 1982 12 p program plan are presented. M.G. refs Presented at the AIAA/ASME/ASCE/AHS 23rd Struct.. Structural Dyn. and Mater. Conf.. New Orleans. 10-12 May N82 23186# Singer Co.. Wayne. N. J. 1982 THE INTEGRATION OF MULTIPLE AVIONIC SENSORS AND (NASA-TM-83296: NAS 1.15:83296: AIAA-PAPER-82-0689) TECHNOLOGIES FOR FUTURE MILITARY HELICOPTERS Avail: NTIS HC A02/MF A01 CSCL 01A Since the aerodynamic theory is nonlinear, the method requires Albert J. Shapiro In AGARD Guidance and Control Technol. the coupling of two iterative processes - an aerodynamic analysis for Highly Integrated Systems Feb. 1982 21 p refs and a structural analysis. A full potential analysis code. FLO22. is combined with a linear structural analysis to yield aerodynamic Avail: NTIS HC A09/MF A01 load distributions on and deflections of elastic wings. This method Multi-sensor navigation systems already available and in use was used to analyze an aeroelastically-scaled wind tunnel model in helicopters are discussed followed by a review of the system of a proposed executive-jet transport wing and an aeroelastic trade-offs and considerations leading to new systems that use research wing. The results are compared with the corresponding more advanced digital electronic techniques to achieve the goals rigid-wing analyses, and some effects of elasticity on the of reduced pilot workload, improved performance at minimum aerodynamic loading are noted. T.M. size, weight, and cost. The beneficial impact of ongoing technological advances in improving the operating capabilities of future avionics systems is indicated. R.J.F. N82-23194*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. N82-23187# Aeronautical Systems Div , Wright-Patterson AFB. AN ACCURATE METHOD FOR EVALUATING THE KERNEL Ohio. Plans and Management Information Dept. OF THE INTEGRAL EQUATION RELATING LIFT TO PRODUCTION VERIFICATION TESTING (PVT) OF GUID- DOWNWASH IN UNSTEADY POTENTIAL FLOW ANCE AND CONTROL SYSTEMS FOR HIGH RELIABILITY Robert N. Desmarais Apr. 1982 15 p refs Presented at the AIAA/ASME/ASCE/AHS 23rd Struct.. Structural Dyn. and Mater. Paul J. Logus In AGARD Guidance and Control Technol. for Conf.. New Orleans. 10-12 May 1982 10-12 May 1982 Highly Integrated Systems Feb. 1982 11 p refs (NASA-TM-83281: NAS 1.15:83281: AIAA-PAPER-82-687) Avail: NTIS HC A02/MF A01 CSCL 01A Avail: NTIS HC A09/MF A01 The method is capable of generating approximations of The testing of equipment for highly integrated guidance and arbitrary accuracy. It is based on approximating the algebraic control systems is addressed. A departure to the usual acceptance part of the nonelementary integrals in the kernel by exponential testing is discussed by examining in some detail a technique functions and then integrating termwise. The exponent spacing called production verification testing (PVT). Some of the recent in the approximation is a geometric sequence. The coefficients literature and experience is reviewed. Computer simulation are and exponent multiplier of the exponential approximation are used to examine various facets of PVT. Particular emphasis is computed by least squares so the method is completely automated. directed toward the implementation of 100% testing of all systems Exponential approximates generated in this manner are two orders prior to delivery through the use of N sequential failure-free of magnitude more accurate than the exponential approximation cycles. Finally, conclusions drawn from computer simulations are that is currently most often used for this purpose. The method presented. The number of N sequential failure free cycles that can be used to generate approximations to attain any desired may be necessary is suggested, providing insight into interpreting trade-off between accuracy and computing cost. T.M. the results. Simulation results suggest a means for determining not only expected operational reliability but also process control N82-23195*# National Aeronautics and Space Administration. problems during manufacturing. R.J.F. Langley Research Center. Hampton. Va. STATIC AND UNSTEADY PRESSURE MEASUREMENTS ON N82-23189# Systems Control. Inc., Palo Alto, Calif. A 60 DEGREE CLIPPED DELTA WING AT M = 0.9 ANALYSIS OF COMPUTING SYSTEM CONFIGURATIONS R. W. Hess. E. C. Wynne, and F. W. Cazier Apr. 1982 10 p FOR HIGHLY INTEGRATED GUIDANCE AND CONTROL refs SYSTEMS (NASA-TM-83297: NAS 1.15:83297) Avail: NTIS J. Edwin Jones, Jay S. Karmarkar, and Randall E. Fleming In HC A02/MF A01 CSCL 01A AGARD Guidance and Control Technol. for Highly Integrated Pressures were measured with Freon as the test medium. Systems Feb. 1982 9 p refs Data taken at M = 0.9 is presented for static and oscillatory deflections of the trailing edge control surface and for the wing Avail: NTIS HC A09/MF A01 in pitch. Comparisons of the static measured data are made The importance of early and sustained validation of architec- with results computed using the Bailey-Ballhaus small disturbance tures for highly integrated systems is discussed. Two early code. T.M. validation tools are presented. A description of the two tools, (1) generalized reliability and maintainability program (GRAMP), and (2) functional emulation, is presented, along with a discussion N82-23196*jjf National Aeronautics and Space Administration. of their utility in the development of highly integrated guidance Langley Research Center. Hampton, Va. and control systems. B.W. TIME-MARCHING TRANSONIC FLUTTER SOLUTIONS INCLUDING ANGLE OF ATTACK EFFECTS N82-23192*# National Aeronautics and Space Administration. John W. Edwards. Robert M. Bennett, Woodrow Whitlow. Jr.. Langley Research Center, Hampton, Va. and David A. Seidel Apr. 1982 16 p refs Presented at the

363 N82-23197

AIAA/ASME/ASCE/AHS Struct. Structural Dyn. and Mater. LAGES WITH DIFFERENT LACINGS AND WING SETTINGS Conf. New Orleans. 10-12 May 1982 [WINDKANALUNTERSUCHUNGEN AN SEGELFLUGZEUG- (NASA-TM-83295; MAS 1.15:83295; AIAA-PAPER-82-0685) RUEMPFEN MIT VERSCHIEDENER EINSCHNUERUNG UND Avail: NTIS HC A02/MF A01 CSCL 01A FLUEGELANORDNUNG] Transonic aeroelastic solutions based upon the transonic small Rolf Radespiel 1981 14 p In GERMAN perturbation potential equation were studied. Time-marching Avail: NTIS HC A02/MF A01 transient solutions of plunging and pitching airfoils were analyzed The parameter fuselage lacing, sailplane wing setting and using a complex exponential modal identification technique, and fuselage nose radius of nine glider configurations were investigated seven alternative integration techniques for the structural in a wind tunnel. Laminar peeling off blisters were found on equations were evaluated. The HYTRAN2 code was used to strongly laced fuselages. These in the transition between fuselage determine transonic flutter boundaries versus Mach number and and wing are essential for the harmful aerodynamic resistance. angle-of-attack for NACA 64A010 and MBB A-3 airfoils. In the Resistance reduction was measured for increasing lacing and code, a monotone differencing method, which eliminates leading wing setting in the rear. These results are only valid for undisturbed edge expansion shocks, is used to solve the potential equation. flow on the fuselage front part, a condition which is not yet When the effect of static pitching moment upon the angle-of-attack fulfilled for original sailplanes. Author (ESA) is included, the MBB A-3 airfoil can have multiple flutter speeds at a given Mach number. T.M. N82-23207*# Boeing Commercial Airplane Co., Seattle, Wash. COMMERCIAL JET TRANSPORT CRASHWORTHINESS N82-23197# Aeronautical Research Labs.. Melbourne (Australia). E. Widmayer and Otto_B. Brende Apr. 1982 255 p refs A NUMERICAL INVESTIGATION OF TWO-DIMENSIONAL. (Contract NAS1-16076) SUBSONIC. LINEAR. WIND TUNNEL INTERFERENCE (NASA-CR-165849: NAS 1.26:165849: • DOT-FAA-CT-82-86) THEORY Avail: NTIS HC A12/MF A01 CSCL01C N. Pollock Jun. 1981 40 p refs The results of a study to identify areas of research and (ARL/AERO-NOTE-403: AR-002-294) Avail: NTIS approaches that may result in improved occupant survivability HC A03/MF A01 and crashworthiness of transport aircraft are given. The study An investigation of two-dimensional, subsonic, linear wind defines areas of structural crashworthiness for transport aircraft tunnel interference using the computer program TSFOIL as a which might form the basis for a research program. A 10-year numerical tunnel was carried out for solid, open, porous and research and development program to improve the structural slotted walls. The use of a computer code rather than physical impact resistance of general aviation and commercial jet transport experiment has the advantage that test parameters such as aircraft is planned. As part of this program parallel studies were wall characteristics and model chord can be varied widely at conducted to review the accident experience of commercial low cost. The aim was to determine the relative merits of the transport aircraft, assess the accident performance of structural various walls and to establish the limits of applicability of linear components and the status of impact resistance technology, interference theory. The most favorable wall type was found to and recommend areas of research and development for that be an ideal slotted wall with the slot parameter appropriate for 10-year plan. The results of that study are also given. R.J.F. zero solid blockage (F = 1.1844). For this wall type linear interference theory accurately predicted lift and pitching moment N82-23208*# National Aeronautics and Space Administration. corrections for tunnel height to chord ratios greater than 2 and Ames Research Center. Moffett Field, Calif. supersonic region height to tunnel height ratios less than 0.2. HELICOPTER HANDLING QUALITIES Author Apr. 1982 243 p refs Proceedings of the special meeting held at Moffett Field, Calif.. 14-15 Apr. 1982: sponsored by N82-23198jjl Deutsche Forschungs- und Versuchsanstalt fuer the American Helicopter Society Luft- und Raumfahrt. Oberpfaffenhofen (West Germany). Inst. (NASA-CP-2219: A-8891; NAS 1.55:2219) Avail: NTIS fuer Aeroelastik. HC A11/MF A01 CSCL01C UNSTEADY PRESSURE MEASUREMENTS AT STALL AND Helicopters are used by the military and civilian communities BUFFETING for a variety of tasks and must be capable of operating in poor Peter Bublitz Apr. 1979 52 p refs In GERMAN: ENGLISH weather conditions and at night. Accompanying extended summary Translation was announced as N81-21041 helicopter operations is a significant increase in pilot workload (DFVLR-Mitt-79-09) Avail: NTIS HC A04/MF A01 and a need for better handling qualities. An overview of the The fluid dynamic phenomena of stall and buffeting, as well status and problems in the developmept and specification of as the marked effects on elastic structures are described. By helicopter handling-qualities criteria is presented. Topics for future applying the generalized form of the equations of motion and research efforts by government and industry are highlighted. the Fourier transforms, the governing equation of the dynamic response problem is concisely derived. Quantities needed to treat the problem under consideration are determined. Then the test N82-23209*# Naval Air Development Center. Warminster, Pa. installation and the relevant test method are depicted to some VTOL AND VSTOL HANDLING QUALITIES SPECIFICA- extent, in which the direct pressure measuring method and the TIONS. AN OVERVIEW OF THE CURRENT STATUS statistical evaluation method are the main topics. A trapezoidal Kevin W. Goldstein In NASA, Ames Research Center Helicopter stalled wing with and without strake are tested. The efficiency Handling Qualities Apr. 1982 p 1-7 refs of the test procedure is shown and some insight into the dynamic behavior of the stall is provided. S.L. Avail: NTIS HC A11/MF A01 CSCL01C The highlights of a comparative analysis between the current N82-23199jjl Applied Physics Lab.. Johns Hopkins Univ.. Laurel, helicopter and VSTOL specifications and four representative rotary Md. wing aircraft are presented. Longitudinal, lateral, and directional APPROXIMATE METHOD FOR PREDICTING SUPERSONIC control power and dynamic stability characteristics were NORMAL FORCE COEFFICIENT VERY-LOW-ASPECT-RATIO analyzed for hovering conditions. Forward flight static and dynamic LIFTING SURFACES stability were analyzed for the longitudinal and lateral-directional E. F. Lucero 14 May 1981 32 p refs Sponsored in part by axes. Results of the analyses in terms of the applicability/utility NAVSEA 62 R of the MIL-H-8501A criteria are presented for each of the (AD-A111770) Avail: NTIS HC A03/MF A01 CSCL 20/4 above areas. The review of the MIL-H-8301A criteria against A simple, empirical method has been developed for predicting those in MIL-F-83300 and AGARD 577 indicate many areas in at supersonic speeds the normal force coefficient. C(N). (including which MIL-H-8501A does not give adequate design guidance. carryover) of very-low-aspect ratio lifting surfaces mounted on T.M. bodies of revolution. Predicted values of C(N) using this method are shown to be in good agreement with test data obtained on N82-23210*# Aerospatiale Helicopter Corp.. Grand Prairie. Tex. both thick and thin surfaces, at Mach numbers from about 2.5 to CIVIL (FRENCH/US) CERTIFICATION OF THE COAST 7.7 and angles of attack to 24 degrees. Author (GRA) GUARD'S HH-6SA DAUPHIN J. C. Hart. J. M. Besse (Societe Nationale Industrielle Aerospatiale. N82-23200# Akademische Fliegergruppe Braunschweig (West Marignane. France), and K. W. McElreath (Rockwell Collins Germany). Government Avionics Div , Cedar Rapids. Iowa) In NASA. Ames WIND TUNNEL INVESTIGATIONS OF SAILPLANE FUSE- Research Center Helicopter Handling Qualities Apr. 1982 p

364 N82-23218

9-13 Avail: NTIS HC A11/MF A01 CSCL 01C Avail: NTIS HC A'11/MF A01 CSCL 01C The helicopter configuration with an rpm-governed gas-turbine Certification programs with particular emphasis on handling engine was examined. A wide range of engine response time, qualities requirements are described. A dynamic simulator was vehicle damping and sensitivity, and excess power levels was designed and constructed to support and verify the dynamic studied. The data are compared with the existing handling-qualities aspects of the avionics system, particularly the Automatic Flight specifications. MIL-F-83300 and AGARD 577. and in general Control System (AFCS). The role of the Dynamic Simulator is show a need for higher minimums when performing such NOE discussed. T.M. maneuvers as a dolphin and bob-up task. T.M.

N82-23211*# Boeing Vertol Co.. Philadelphia. Pa. N82-23215*# National Aeronautics and Space Administration. BOEING 234 FLIGHT CONTROL DEVELOPMENT Ames Research Center. Moffett Field. Calif. James J. Morris In NASA. Ames Research Center Helicopter UNIFIED RESULTS OF SEVERAL ANALYTICAL AND Handling Qualities Apr. 1982 p 15-22 EXPERIMENTAL STUDIES OF HELICOPTER HANDLING QUALITIES IN VISUAL TERRAIN FLIGHT Avail: NTIS HC A11/MF A01 CSCL01C Robert T. N. Chen In its Helicopter Handling Qualities Apr. The Boeing 234 is the commercially certified derivative of 1982 p 59-74 refs the CH-47 Chinook. The automatic flight control system and flight director with coupler were designed to reduce pilot work-load Avail: NTIS HC A11/MF A01 CSCL 01C for missions of approximately six hour duration during VFR, IFR. The studies were undertaken to investigate the effects of day and night conditions. The AFCS system for the 234 is rotor design parameters, interaxis coupling, and various levels of essentially the same system as developed for the CH-47D. which stability and control augmentation on the flying qualities of has airspeed hold, attitude hold, and maneuver enhancement in helicopters performing low-level, terrain-flying tasks in visual all three axes. The system also has the capability to couple to meteorological conditions. Some unified results are presented, the Sperry Helcis flight director system which provides for and the validity and limitations of the flying-qualities data obtained enroute navigation and landing approaches. Certification testing are interpreted. Selected results, related to various design was completed, by both the FAA and CAA. to FAR Part 29 for parameters, provide guidelines for the preliminary design of rotor Transport Category Rotorcraft and BCAR Section G: Rotorcraft. systems and aircraft augmentation systems. T.M. The aircraft was certified for civil operation in June 1981. Author N82-23216*| Boeing Vertol Co.. Philadelphia. Pa. AN ASSESSMENT OF VARIOUS SIDE-STICK CONTROL- N82-23212*# Grumman Aerospace Corp.. Bethpage. N.Y. LER/STABILITY AND CONTROL AUGMENTATION SYS- INFLUENCE OF MANEUVERABILITY ON HELICOPTER TEMS FOR NIGHT NAP-OF-EARTH FLIGHT USING PILOTED COMBAT EFFECTIVENESS SIMULATION Michael Falco and Roger Smith (Army Aviation Research and Kenneth H. Landis and Edwin W. Aiken (Army Research and Development Command. St. Louis. Mo.) In NASA. Ames Research Technology Labs.. Moffett Field. Calif.) In NASA. Ames Research Center Helicopter Handling Qualities Apr. 1982 p 23-33 Center Helicopter Handling Qualities Apr. 1982 p 75-96 refs refs Avail: NTIS HCA11/MFA01 CSCL QIC Avail: NTIS HC A11/MF A01 CSCL 01C A computational procedure employing a stochastic learning Several night nap-of-the-earth mission tasks were evaluated method in conjunction with dynamic simulation of helicopter using a helmet-mounted display which provided a limited flight and weapon system operation was used to derive helicopter field-of-view image with superimposed flight control symbology. maneuvering strategies. The derived strategies maximize either A wide range of stability and control augmentation designs was survival or kill probability and are in the form of a feedback investigated. Variations in controller force-deflection characteristics control based upon threat visual or warning system cues. and the number of axes controlled through an integrated side-stick Maneuverability parameters implicit in the strategy development controller were studied. In general, a small displacement controller include maximum longitudinal acceleration and deceleration, is preferred over a stiffstick controller particularly for maneuvering maximum sustained and transient load factor turn rate at forward flight. Higher levels of stability augmentation were required for speed, and maximum pedal turn rate and lateral acceleration at IMC tasks to provide handling qualities comparable to those hover. Results are presented in terms of probability of skill for achieved for the same tasks conducted under simulated visual all combat initial conditions for two threat categories. T.M. flight conditions. T.M. N82 23217*# Martin Marietta Corp.. Orlando. Fla. N82-23213*# Deutsche Forschungs- und Versuchsanstalt fuer DEFINITION OF DISPLAY/CONTROL REQUIREMENTS FOR Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer ASSAULT TRANSPORT NIGHT/ADVERSE WEATHER Flugmechanik. CAPABILITY FLIGHT TESTS FOR THE ASSESSMENT OF TASK PERFOR- R. Joseph Milelli, Gary W. Mowery. and Carmen Pontelandolfo MANCE AND CONTROL ACTIVITY (Naval Air Development Center. Warminister, Pa.) In NASA. Heinz-Juergen Pausder and Dieter Hummes In NASA. Ames Ames Research Center Helicopter Handling Qualities Apr. 1982 Research Center Helicopter Handling Qualities Apr. 1982 p 97-107 refs p 35-46 refs Avail: NTIS HC A11/MF A01 CSCL 01C Avail: NTIS HC A11/MF A01 CSCL 01C A Helicopter Night Vision System was developed to improve The tests were performed with the helicopters BO 105 and low-altitude night and/or adverse weather assult transport UH-1D. Closely connected with tactical demands the six test capabilities. Man-in-the-loop simulation experiments were pilots' task was to minimize the time and the altitude over the performed to define the minimum display and control requirements obstacles. The data reduction yields statistical evaluation for the assult transport mission and investigate forward looking parameters describing the control activity of the pilots and the infrared sensor requirements, along with alternative displays such achieved task performance. The results are shown in form of as panel mounted displays (PMD) helmet mounted displays (HMD), evaluation diagrams. Additionally dolphin tests with varied control and integrated control display units. Also explored were navigation strategy were performed to get more insight into the influence requirements, pilot/copilot interaction, and overall cockpit of control techniques. From these test results recommendations arrangement. Pilot use of an HMD and copilot use of a PMD can be derived to emphasize the direct force control and to appear as both the preferred and most effective night navigation reduce the collective to pitch crosscoupling for the dolphin. T.M. combination. M.D.K. N82-23218*# National Research Council of Canada. Ottawa N82-23214*# Army Research and Technology Labs.. Moffett (Ontario). Airborne Simulator Facility. Field, Calif. SOME PILOTING EXPERIENCES WITH MULTIFUNCTION A HELICOPTER HANDLING-QUALITIES STUDY OF THE ISOMETRIC SIDE-ARM CONTROLLERS IN A HELICOPTER EFFECTS OF ENGINE RESPONSE CHARACTERISTICS. J. Murray Morgan In NASA. Ames Research Center Helicopter HEIGHT-CONTROL DYNAMICS. AND EXCESS POWER ON Handling Qualities Apr. 1982 p 109-119 ref NAP-OF-THE-EARTH OPERATIONS Lloyd D. Corliss In NASA. Ames Research Center Helicopter Avail: NTIS HC A11/MF A01 CSCL 01C Handling Qualities Apr. 1982 p 47-57 refs The installation of two side-arm mounted, isometric controllers

365 N82-23219 in the NAE Airborne Simulator, a modified, variable stability Avail: NTIS HCA11/MFA01 CSCL 01C Bell 205 A is described, as is the development of various control The process used in the synthesis of an integrated cockpit systems for use with them. The results of two experiments are management system was discussed. Areas covered included flight presented indicating both the feasibility and acceptability of such displays, subsystem management, checklists, and procedures (both systems for a wide variety of tasks in a conventional single normal and emergency). The process of evolving from the rotor helicopter, with a minimum of stability augmentation. Areas unimegiated conventional system to the integrated system is of future research are indicated. Author examined and a brief description of the results presented.M.D.K.

N82-23219*| National Aeronautics and Space Administration. N82-23223*# United Technologies Corp.. East Hartford. Conn. Ames Research Center. Moffett Field. Calif. Aircraft Div. RESULTS OF NASA/FAA GROUND AND FLIGHT SIMULA- THE ROLE OF VOICE TECHNOLOGY IN ADVANCED TION EXPERIMENTS CONCERNING HELICOPTER IFR HELICOPTER COCKPITS AIRWORTHINESS CRITERIA Howard P. Harper In NASA. Ames Research Center Helicopter J. Victor Lebacqz. Robert T. N. Chen. Ronald M. Gerdes. Jeanine Handling Qualities Apr. 1982 p 163-170 refs M. Weber, and Raymond D. Forrest (FAA. Moffett Field. Calif.) In its Helicopter Handling Qualities 1 Apr. 1982 p 121-138 Avail: NTIS HC A11/MF A01 CSCL 01C refs The status of voice output and voice recognition technology Avail: NTIS HCA11/MFA01 CSCL 01C in relation to helicopter cockpit applications is described. The A sequence of ground and flight simulation experiments was maturing of this technology provides many opportunities for new conducted to investigate helicopter instrument-flight-rules approaches to crew workload reduction. The helicopter operating airworthiness criteria. The first six of these experiments and major environment, potential application areas, and the impact on results are summarized. Five of the experiments were conducted advanced cockpit design are discussed. Author on large-amplitude motion base simulators. The NASA-Army V/STOLAND UH-1H variable-stability helicopter was used in the N82-23224'# Pacer Systems. Inc.. Arlington. Va. flight experiment. Artificial stability and control augmentation, COCKPIT INTEGRATION FROM A PILOT'S POINT OF longitudinal and lateral control, and in pitch and roll attitude VIEW augmentation were investigated. M.D.K. David L. Green In NASA. Ames Research Center Helicopter Handling Qualities Apr. 1982 p 171-181 N82-23220*# Rockwell International Corp.. Cedar Rapids. Iowa. Avail: NTIS HCA11/MFA01 CSCL01C Government Avionics Div. Extensive experience in both operational and engineering test STATE-OF-THE-ART COCKPIT DESIGN FOR THE HH-65A flight was used to suggest straightforward changes to helicopter HELICOPTERS cockpit and control system design that would improve pilot Daniel E. Castleberry and Marsha Y. McElreath In NASA. Ames performance in marginal and instrument flight conditions. Needed Research Center Helicopter Handling Qualities Apr._ 1982 control system improvements considered include: (1) separation p 139-143 refs of yaw from cyclic force trim: (2) pedal force proportional to Avail: NTIS HC A11/MF A01 CSCL 01C displacement rate: and (3) integration of engine controls in In the design of a HH-65A helicopter cockpit, advanced collective stick. Display improvements needed include: (1) natural integrated electronics systems technology was employed to cuing of yaw rate in attitude indicator: (2) collective position achieve several important goals for this multimission aircraft. indication and radar altimeter placed within primary scan: and They were: (1) integrated systems operation with consistent and (3) omnidirectional display of full range airspeed data. M.D.K. simplified cockpit procedures: (2) mission-task-related cockpit displays and controls, and (3) reduced pilot instrument scan effort with excellent outside visibility. The integrated avionics system N82-23225*| Costruzioni Aeronautiche Giovanni Agusta S.p.A.. was implemented to depend heavily upon distributed but Samarate (Italy). Helicopter Systems Engineering Div. complementary processing, multiplex digital bus technology, and INTEGRATED COCKPIT FOR A-129 multifunction CRT controls and displays. This avionics system Filippo Reina, James J. Gracia (Harris Government Information was completely flight tested and will soon enter operational service Systems Div.). and Bryce W. Koth (Harris Government Information with the Coast Guard. M.D.K. Systems Div.) In NASA. Ames Research Center Helicopter Handling Qualities Apr. 1982 p 183-192

N82 23221 *# Ohio State Univ., Columbus. Avail: NTIS HC A11/MF A01 PERFORMANCE EVALUATION OF A KINESTHETIC- Weight, size, and mission requirements for the A-129 TACTUAL DISPLAY mandated an integrated system approach for the crew/cockpit Richard J. Jagacinski. John M. Flach, Richard D. Gilson, and interface design. Instead of the usual multitude of cockpit controls, Richard S. Dunn (Army Research and Technology Lab.. Moffett indicators, gauges, and lights, the primary crew interface is a Field. Calif.) In NASA. Ames Research Center Helicopter single multifunction keyboard and one or more multifunction CRT Handling Qualities Apr. 1982 p 145-150 refs display units. This cockpit design approach imposed unusual constraints upon the system architecture to overcome the (Grant NsG-2179) inherent information access limitations of a data input/output Avail: NTIS HCA11/MFA01 CSCL QIC window that was restricted by the available space. The conceptual Simulator studies demonstrated the feasibility of using approach and resulting design of the A-129 cockpit with the kinesthetic-tactual (KT) displays for providing collective and cyclic intent to enhance the development of cockpit standardization command information, and suggested that KT displays may are described. Author increase pilot workload capability. A dual-axis laboratory tracking task suggested that beyond reduction in visual scanning, there N82-23226*# Systems Technology. Inc.. Hawthorne. Calif. may be additional sensory or cognitive benefits to the use of NEW DEVELOPMENT IN FLYING QUALITIES WITH multiple sensory modalities. Single-axis laboratory tracking tasks APPLICATION TO ROTARY WING AIRCRAFT revealed performance with a quickened KT display to be equivalent Roger H. Hoh In NASA. Ames Research Center Helicopter to performance with a quickened visual display for a low frequency Handling Qualities 9 Apr. 1982 p 193-198 refs sum-of-sinewaves input. In contrast, an unquickened KT display was inferior to an unquickened visual display. Full scale simulator Avail: NTIS HC A11/MF A01 CSCL QIC studies and/or inflight testing are recommended to determine Some recent considerations and developments in handling the generality of these results. Author quality criteria are reviewed with emphasis on using fixed wing experience gained in developing MIL-F-8785C and the more N82-23222*# Army Avionics Research and Development recent MIL Standard and Handbook. Particular emphasis is placed Activity, Fort Monmouth, N. J. Avionics Lab. on the tasks and environmental conditions used to develop the SYNTHESIS OF AN INTEGRATED COCKPIT MANAGEMENT criterion boundaries. SAS failures, and potential fixed wing criteria SYSTEM that are applicable to rotary wing aircraft. Author Joseph A. Dasaro and Charles T. Elliott In NASA. Ames Research Center Helicopter Handling Qualities Apr. 1982 p 151-162 N82-23227*| National Aeronautics and Space Administration. refs Ames Research Center. Moffett Field. Calif.

366 N82-23235

HELICOPTER SIMULATION TECHNOLOGY: AN AMES A sun sensing guidance system for high altitude aircraft is RESEARCH CENTER PERSPECTIVE described. The system is characterized by a disk shaped body Richard S. Bray In its Helicopter Handling Qualities Apr. 1982 mounted for rotation aboard the aircraft in exposed relation to p 199-208 refs solar radiation. The system also has a plurality of mutually isolated Avail: NTIS HC A11/MF A01 CSCL 01C chambers: each chamber being characterized by an opening having The total experience for evidence regarding the levels of a photosensor disposed therein and arranged in facing relation motion and visual cueing fidelity required for handling-qualities with the opening for receiving incident solar radiation and research in ground-based simulators is reviewed. Positive responsively providing a voltage output. Photosensors are contributions of cockpit motion were identified, but much connected in paired relation through a bridge circuit for providing remains to be learned regarding the sensitivities of individual heading error signals in response to detected imbalances in control modes to cueing attenuation. A firmer understanding of intensities of solar radiation. the pilot's utilization of visual and motion cues is the key to Official Gazette of the U.S. Patent and Trademark Office more efficient use of simulation in helicopter control-systems research. Author N82-23233*# National Aeronautics and Space Administration. Langley Research Center. Hampton. Va. N82-23228*| Stanford Univ.. Calif. Joint Inst. of Aeronautics ANALYSIS AND MONTE CARLO SIMULATION OF NEAR- and Acoustics. TERMINAL AIRCRAFT FLIGHT PATHS PAST APPLICATIONS AND FUTURE POTENTIAL OF James R. Schiess and Christine G. Matthews (Computer Sciences VARIABLE STABILITY RESEARCH HELICOPTERS Corp.) Apr. 1982 39 p refs William S. Hindson In NASA. Ames Research Center Helicopter (NASA-TP-1997; L-15062: NAS 1.60:1997) Avail: NTIS Handling Qualities Apr. 1982 p 209-219 refs HC A03/MF A01 CSCL 17G The flight paths of arriving and departing aircraft at an airport Avail: NTIS HC A11/MF A01 CSCL01C are stochastically represented. Radar data of the aircraft The historical development of variable-stability research movements are used to decompose the flight paths into linear helicopters and some of their previous applications are presented and curvilinear segments. Variables which describe the segments as a guide for assessing their future potential. The features of are derived, and the best fitting probability distributions of the three general-purpose rotary-wing flight research aircraft that variables, based on a sample of flight paths, are found. Conversely, provide complementary capabilities are described briefly, and a given information on the probability distribution of the variables, number of future applications are proposed. Author generation of a random sample of flight paths in a Monte Carlo simulation is discussed. Actual flight paths at Dulles International N82-23229*# Systems Technology. Inc., Mountain View, Calif. Airport are analyzed and simulated. S.L. A PILOT IN THE LOOP ANALYSIS OF HELICOPTER ACCELERATION/DECELERATION MANEUVERS N82-23234*# Lockheed-Georgia Co.. Marietta. Robert K. Heffley In NASA. Ames Research Center Helicopter DETERMINATION OF WIND TUNNEL CONSTRAINT Handling Qualities Apr. 1982 p 221-232 refs EFFECTS BY A UNIFIED PRESSURE SIGNATURE METHOD. PART 1: APPLICATIONS TO WINGED CONFIGURATIONS Avail: NTIS HC A11/MF A01 CSCL01C Final Report. Oct. 1980 - Nov. 1981 Helicopter flight acceleration/deceleration maneuvers are J. E. Hackett. S. Sampath. and C. G. Phillips Jun. 1981 185 p quantified and put to use in the fields of handling qualities, refs 2 Vol. flight training and evaluation of simulator fidelity. The three specific (Contract NAS2-9883) cases include the normal speed change maneuver, the nap-of-the- (NASA-CR-166186, NAS 1.26.166186, LG81ER0166-PM) Earth dash/quickstop. and the decelerating approach to hover. Avail: NTIS HC A09/MF A01 CSCL 01C All of these maneuvers share common generic features in terms A new, fast, non-iterative version of the 'Wall Pressure of pilot adaptation and mathematical description: yet each differs Signature Method' is described and used to determine blockage in terms of the essential feedback loop structure, implications and angle-of-attack wind tunnel corrections for highly-powered for handling qualities requirements, and simulator fidelity jet-flap models. The correction method is complemented by the criteria. Author application of tangential blowing at the tunnel floor to suppress flow breakdown there, using feedback from measured floor N82-23230*# National Aeronautics and Space Administration. pressures. This tangential blowing technique was substantiated Ames Research Center. Moffett Field. Calif. by subsequent flow investigations using an LV. The basic tests APPLICATIONS OF SYSTEM IDENTIFICATION METHODS on an unswept. knee-blown, jet flapped wing were supplemented TO THE PREDICTION OF HELICOPTER STABILITY. to include the effects of slat-removal, sweep and the addition CONTROL AND HANDLING CHARACTERISTICS of unflapped tips. C sub mu values were varied from 0 to 10 G. D. Padfield (RAE. Bedford. England) and R. K. OuVal In its free-air C sub I's in excess of 18 were measured in some cases. Helicopter Handling Qualities Apr. 1982 p 233-247 refs Application of the new methods yielded corrected data which agreed with corresponding large tunnel 'free air' resuls to within Avail: NTIS HCA11/MFA01 CSCL 01C the limits of experimental accuracy in almost all cases. A program A set of results on rotorcraft system identification is described. listing is provided, with sample cases. Author Flight measurements collected on an experimental Puma helicopter are reviewed and some notable characteristics highlighted. N82-23235*# Lockheed-Georgia Co.. Marietta. Following a brief review of previous work in rotorcraft system DETERMINATION OF WIND TUNNEL CONSTRAINT identification, the results of state estimation and model structure EFFECTS BY A UNIFIED PRESSURE SIGNATURE METHOD. estimation processes applied to the Puma data are presented. PART 2: APPLICATION TO JET IN-CROSSFLOW Final The results, which were obtained using NASA developed software, Report. Oct. 1980 - Nov. 1981 are compared with theoretical predictions of roll, yaw and pitching J. E. Hackett, S. Sampath, and C. G. Phillips Jun. 1981 186 p moment derivatives for a 6 degree of freedom model structure. refs 2 Vol. Anomalies are reported. The theoretical methods used are (Contract NAS2-9883) described. A framework for reduced order modelling is outlined. (NASA-CR-166187: NAS 1.26:166187: LG81ER0167-Pt-2) Author Avail: NTIS HC A09/MF A01 CSCL 01C The development of an improved jet-in-crossflow model for N82-23231* National Aeronautics and Space Administration. estimating wind tunnel blockage and angle-of-attack interference Hugh L. Dryden Flight Research Center. Edwards. Calif. is described. Experiments showed that the simpler existing models SUN SENSING GUIDANCE SYSTEM FOR HIGH ALTITUDE fall seriously short of representing far-field flows properly. A AIRCRAFT Patent new, vortex-source-doublet (VSD) model was therefore developed Robert D. Reed. Principal Investigator Issued 27 Apr. 1982 which employs curved trajectories and experimentally-based 7 p Filed 12 Mar. 1980 Supersedes N80-20249 (18 - 11. p singularity strengths. The new model is consistent with existing 1375) and new experimental data and it predicts tunnel wall (i.e. far-field) (NASA-Case-FRC-11052-1; US-Patent-4.326.685. pressures properly. It is implemented as a preprocessor to the US-Patent-Appl-SN-129783; US-Patent-Class-244-175; wall-pressure-signature-based tunnel interference predictor. The US-Patent-Class-244-168: US-Patent-Class-244-190:- supporting experiments and theoretical studies revealed some US-Patent-Class-318-580) Avail: US Patent and Trademark new results. Comparative flow field measurements with 1-inch Office CSCL 17G 'free-air' and 3-inch impinging jets showed that vortex penetra-

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tion into the flow, in diameters, was almost unaltered until 'hard' (M) from 0.6 to 0.95. The measured transonic flutter speed impingement occurred. In modeling impinging cases, a 'plume boundary for each wingtip configuration had roughly the same redirection' term was introduced which is apparently absent in shape with a minimum flutter speed near M = 0.82. The winglet previous models. The effects of this term were found to be very addition and wingtip mass ballast decreased the wing flutter significant. Author speed by about 7 and 5 percent, respectively: thus. the.winglet effect on flutter was more a mass effect than an aerodynamic N82-23236*# National Aeronautics and Space Administration. effect. T.M. Langley Research Center, Hampton. Va. COMPARISON OF ANALYTICAL PREDICTIONS OF N82-23240*# National Aeronautics and Space Administration. LONGITUDINAL SHORT PERIOD PILOT-INDUCED OSCIL- Langley Research Center. Hampton. Va. LATIONS WITH RESULTS FROM A SIMULATION STUDY EVALUATION OF FOUR SUBCRITICAL RESPONSE OF THE SPACE SHUTTLE ORBITER METHODS FOR ON-UNE PREDICTION FLUTTER ONSET Donald R. Riley and G. Kimball Miller. Jr. Apr. 1982 43 p IN WIND-TUNNEL TESTS refs Charles L. Ruhlin. Judith J. Watson, Rodney H. Ricketts. and (NASA-TM-83267: L-14847: NAS 1.15:83267) Avail: NTIS Robert V. Doggett. Jr. Mar. 1982 10 p refs Presented at HC A03/MF A01 CSCL 01C the AIAA/ASME/ASCE/AHS 23rd Struct.. Structural Dyn. and An analytical analysis of conditions producing pilot induced Mater. Conf.. New Orleans. 10-12 May 1982 oscillations (PIO's) was made for the space shuttle orbiter in a (NASA-TM-83278: NAS 1.15:83278: landing approach configuration for the task of milling the elevation AIAA-PAPER-82-0644CP) Avail: NTIS HC A02/MF A01 CSCL angle of the line of sight to a target vehicle. The analysis yielded 01C a value of PIO frequency and a value for the amount of total The methods were evaluated for use in tests where the system time delay (pilot + control system) that can be tolerated flutter model is excited solely by airstream turbulence. The methods before instability results. Calculations were performed showing were: randomdec. power-spectral-density, peak-hold, and the effect of varying the range to the target and of varying the cross-spectrum. The test procedure was to maintain a constant handling qualities of the orbiter vehicle. Analytical predictions Mach number (M) and increase the dynamic pressure (g) in were compared with simulation results obtained using a visual incremental steps. The test Mach numbers were 0.65. 0.75. motion simulator. Author 0.82. 0.90. and 1.15. The four methods provided damping trends by which the flutter mode could be tracked and extrapolated to N82-23237*# National Aeronautics and Space Administration. a flutter-onset q. A hard flutter point was obtained at M - Ames Research Center, Moffett Field, Calif. 0.82. The peak-hold and cross-spectrum methods gave reliable VALIDATION OF ZERO-ORDER FEEDBACK STRATEGIES results and could be most readily used for on-line testing. At M FOR MEDIUM RANGE AIR-TO-AIR INTERCEPTION IN A = 0.82, a p-k analysis predicted the same flutter mode as the HORIZONTAL PLANE experiment but a 6-percent lower flutter q. At the subcritical Josef Shinar Apr. 1982 48 p refs dynamic pressures, calculated damping values were appreciably (NASA-TM-84237: NAS 1.15:84237; A-8895) Avail: NTIS lower than measured data. T.M. HC A03/MF A01 CSCL 01 C A zero order feedback solution of a variable speed interception N82-23241*# National Aeronautics and Space Administration. game between two aircraft in the horizontal plane, obtained by Lewis Research Center. Cleveland. Ohio. using the method of forced singular perturbation (FSP), is NASA/HAA ADVANCED ROTORCRAFT TECHNOLOGY compared with the exact open loop solution. The comparison AND TILT ROTOR WORKSHOP. VOLUME 5: PROPULSION indicates that for initial distances of separation larger than eight SESSION turning radii of the evader, the accuracy of the feedback 1980 211 p Workshop held at Palo Alto. Calif.. 3-5 Dec. approximation is better than one percent. The result validates 1980 the zero order FSP approximation for medium range air combat (NASA-TM-84207: NAS 1.15:84207) Avail: NTIS analysis. S.L HC A10/MF A01 CSCL01C The expressed needs and priorities of the civil helicopter N82 23238*# North Carolina State Univ., Raleigh. Oept. of users, the existing research efforts, and technology requirements Mechanical and Aerospace Engineering. as perceived by leading airframe and engine manufacturers were AUTOMATED DESIGN OF MINIMUM DRAG LIGHT addressed, compared, and evaluated. Specifically, the observations AIRCRAFT FUSELAGES AND NACELLES Final Report and conclusions of these areas as they relate to the helicopter Frederick O. Smetana. Star R. Fox, and Baruch E. Karlin 14 May propulsion system are reported. Author 1982 25 p refs (Grant NsG-1584) N82-23242*# National Aeronautics and Space Administration. (NASA-CR-168913: NAS 1.26:168913) Avail: NTIS Ames Research Center. Moffett Field, Calif. HC A02/MF A01 CSCL QIC NASA/HAA ADVANCED ROTORCRAFT TECHNOLOGY The constrained minimization algorithm of Vanderplaats is AND TILT ROTOR WORKSHOP. VOLUME 6: VEHICLE applied to the problem of designing minimum drag faired bodies CONFIGURATION SESSION such as fuselages and nacelles. Body drag is computed by a 1980 256 p Workshop held at Palo Alto. Calif.. 2-5 Dec. variation of the Hess-Smith code. This variation includes a 1980 boundary layer computation. The encased payload provides (NASA-TM-84180: NAS 1.15:84180) Avail: NTIS arbitrary geometric constraints, specified a priori by the designer, HC A12/MF A01 CSCL QIC below which the fairing cannot shrink. The optimization may Five high speed rotorcraft configurations are considered: the include engine cooling air flows entering and exhausting high speed helicopter, compound helicopter, ABC. tilt rotor and through specific port locations on the body. M.O.K. the X wing. The technology requirements and the recommended actions are discussed. S.L. N82-23239*# National Aeronautics and Space Administration. Langley Research Center. Hampton. Va. N82-23243*^ National Aeronautics and Space Administration. TRANSONIC FLUTTER STUDY OF A WIND-TUNNEL MODEL Ames Research Center. Moffett Field. Calif. OF A SUPERCRITICAL WING WITH/WITHOUT WINGLET NASA/HAA ADVANCED ROTORCRAFT TECHNOLOGY Charles L. Ruhlin. Frank J. Rauch. Jr.. and Catherine Waters AND TILT ROTOR WORKSHOP. VOLUME 7: TILT ROTOR Mar. 1982 11 p refs Presented at the 23rd AIAA/ASME/ASCE/ SESSION AHS Struct.. Structural Dyn. and Mater. Conf.. New Orlean. 1980 37 p Workshop held at Palo Alto. Calif.. 2-5 Dec. 10-12 May 1982 Prepared in cooperation with Grumman 1980 Aerospace Corp.. Bethpage. N.Y. (NASA-TM-84705: NAS 1.15:84705) Avail: NTIS (NASA-TM-83279; NAS 1.15:83279) Avail: NTIS HC A03/MF-A01 CSCL 01C HC A02/MF A01 CSCL QIC The technical characteristics of the XV-15 aircraft were The model was a 1/6.5-size. semipan version of a wing discussed. Program objectives, concept evaluation, tilt rotor proposed for an executive-jet-transport airplane. The model was experiments and civil market applications are presented. The tested with a normal wingtip. a wingtip with winglet, and a XV-15 status and test schedule are also included. S.L. normal wingtip ballasted to simulate the winglet mass proper- ties. Flutter and aerodynamic data were acquired at Mach numbers N82-23244*# National Aeronautics and Space Administration.

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Langley Research Center. Hampton, Va. (NASA-CR-165503: NAS 1.26:165503; PWA-5779-10) Avail: PLANAR EQUATIONS OF ROLLOUT MOTION FOR AN NTIS HC A05/MF A01 CSCL 21E AIRCRAFT WITH FREE OR STEERABLE LANDING GEARS High load damping requirements for modern jet engines are Robert K. Sleeper and Eunice G. Smith May 1982 54 p refs discussed. The design of damping systems which could satisfy (NASA-TP-1984; L-11689: NAS 1.60:1984) Avail: NTIS these requirements is also discusseed. In order to evaluate high HC A04/MF A01 CSCL QIC load damping requirements, engines in three major classes were Equations were derived for an aircraft in a three-point attitude. studied: large transport engines, small general aviation engines, Transient .tire forces were simulated by delaying the application and military engines. Four damper concepts applicable to these of forces derived from steady-state considerations. Predicted engines were evaluated: multi-ring, cartridge, curved beam, and rollout trajectories were similar to those measured in tests of a viscous/friction. The most promising damper concept was selected small-scale landing-gear model equipped with pneumatic tires for each engine and performance was assessed relative to (where a laterally sloping runway was used to simulate a conventional dampers and in light of projected damping require- crosswind). both with and without nose-wheel steering. T.M. ments for advanced jet engines. B.W.

N82-23245*# Kansas Univ. Center for Research. Inc.. Lawrence. N82-23249*# Pratt and Whitney Aircraft Group. West Palm DEVELOPMENT OF A SIMPLE. SELF-CONTAINED FLIGHT Beach. Fla. Government Products Div. TEST DATA ACQUISITION SYSTEM Progress Report ADVANCED TURBINE STUDY Final Report. Aug. 1980 - Robert Clarke. Douglas Shane. Jan Roskam. and Dale I. Rummer Dec. 1981 Apr. 1982 250 p refs 12 Apr. 1982 94 p (Grant NsG-4019) (Contract NAS8-33821) (NASA-CR-168912: NAS 1.26:168912: KU-FRL-407-7) Avail: (NASA-CR-162003: NAS 1.26:162003: FR-15978) Avail: NTIS HC A11/MF A01 CSCL 14B NTIS HC A05/MF A01 CSCL 21E The flight test system described combines state-of-the-art Experiments to determine the available increase in turbine microprocessor technology and high accuracy instrumentation with horsepower achieved by increasing turbine inlet temperature over parameter identification technology which minimize data and flight a range of 1800 to 2600 R, while applying current gas turbine time requirements. The system was designed to avoid permanent airfoil cling technology are discussed. Four cases of rocket turbine modifications of the test airplane and allow quick installation. It operating conditions were investigated. Two of the cases used is capable of longitudinal and lateral-directional stability and 02/H2 propellant. one with a fuel flowrate of 160 pps, the control derivative estimation. Details of this system, calibration other 80 pps. Two cases used 02/CH4 propellant, each having and flight test procedures, and the results of the Cessna 172 flight different fuel flowrates, pressure ratios, and inlet pressures. Film test program are presented. The system proved easy to install, cooling was found to be the required scheme for these rocket simple to operate, and capable of accurate estimation of stability turbine applications because of the high heat flux environments. and control parameters in the Cessna 172 flight tests. Author Conventional convective or impingement cooling, used in jet engines, is inadequate in a rocket turbine environment because of the resulting high temperature gradients in the airfoil wall, N82-23246*J Pratt and Whitney Aircraft Group. West Palm causing high strains and low cyclic life. The hydrogen-rich turbine Beach. Fla. Government Products Div. environment experienced a loss, or no gain, in delivered COMPUTER MODELING OF FAN-EXIT-SPUTTER SPACING horsepower as turbine inlet temperature was increased at constant EFFECTS ON F100 RESPONSE TO DISTORTION Final airfoil life. The effects of film cooling with regard to reduced Report flow available for turbine work, dilution of mainstream gas M. Shaw and R. W. Murdoch Mar. 1982 115 p refs temperature and cooling reentry losses, offset the relatively low (Contract NAS3-22739) specific work capability of hydrogen when increasing turbine inlet (NASA-CR-167879: NAS 1.26:167879: FR-15596) Avail: temperature over the 1800 to 2600 R range. However, the NTIS HC A06/MF A01 CSCL 21E methane-rich environment experienced an increase in delivered The distortion response of the F 100(3) engine was effected horsepower as turbine inlet temperature was increased at by the fan exit splitter configuration. The sensitivity for a proximate constant airfoil life. The results of a materials survey and heat splitter fan is calculated to be slightly greater than a remote transfer and durability analysis are discussed. M.G. splitter configuration with identical airfoils. Predicted response was based upon a multiple segment parallel compressor Model modified to include a bypass ratio representation that effects N82-23250# Shaker Research Corp.. Ballston Lake. N. Y. the performance characteristics of the last rotor and intermediate BASIC TECHNOLOGY OF SQUEEZE-FILM DAMPERS FOR case struts. The predicted distortion response required an ROTOR DYNAMICS CONTROL Final Report, Jul. 1978 - accurate definition of row pre- and post-stall undistorted Jul. 1981 operation. Author C. H. T. Pan Nov. 1981 47 p refs (Contract DAAG29-78-C-0027) N82-23247*| Notre Dame Univ.. Ind. Dept. of Electrical (AD-A110842; SRC-81-TR-74; ARO-15657.4-E) Avail: NTIS Engineering. HC A03/MF A01 CSCL 21/5 ALTERNATIVES FOR JET ENGINE CONTROL Technical Research was performed to develop a rigorous treatment Progress Report. 1 Oct. 1980 - 30 Sep. 1981 for the film rupture process in the squeeze-film damper. The Michael K. Sain 1981 140 p refs short bearing analysis was generalized to accommodate a (Grant NsG-3048) consistent treatment of the rupture domain for a squeeze-film (NASA-CR-168894; NAS 1.26:168894: TPR-12) Avail: NTIS damper, which is undergoing a circular orbit motion either in a HC A07/MF A01 CSCL 21E submerged condition or with one end subjected to a pressurized Research centered on basic topics in the modeling and feed condition. GRA feedback control of nonlinear dynamical systems is reported. Of special interest were the following topics: (1) the role of series N82-23252# Messerschmitt-Boelkow-Blonm G.m.b.H.. Otto- descriptions, especially insofar as -they relate to questions of brunn (West Germany). Kurzuebersicht fuer Information und scheduling, in the control of gas turbine engines: (2) the use of Dokumentation. algebraic tensor theory as a technique for parameterizing such ACTTA: INVESTIGATION OF NEW PILOTING AND FLIGHT descriptions: (3) the relationship between tensor methodology CONTROL TECHNOLOGIES. VOLUME 1: REVIEW; ACTIVE and other parts of the nonlinear literature: (4) the improvement WING Milestone Report on Phase 1. 1979 - 1980 [ACTTA: of interactive methods for parameter selection within a tensor UNTERSUCHUNG NEUARTIGER STEUERUNGS- UND viewpoint; and (5) study of feedback gain representation as a FLUGFUEHRUNGSTECHNOLOGIEN. MEILENSTEINBERIC- counterpart to these modeling and parameterization ideas. HT ZUR PHASE 1: 1979/1980. BAND 1: UEBERSICHT; Author AKTIVER FLUEGEL] Weise Kolander and U. A. Fischer 23 Mar. 1981 192 p refs N82-23248*| Pratt and Whitney Aircraft Group, East Hartford. In GERMAN 2 Vol. Conn. (Contract BMFT-LFK-7960-9) ANALYSIS OF HIGH LOAD DAMPERS Final Report (MBB-UH-05-81-Vol-1) Avail: NTIS HC A09/MF A01 S. T. Bhat, D. F. Buono, and D. H. Hibner 21 Aug. 1981 Flight control technologies were investigated as to their 79 p refs realizability and economy. The conceptual phase of project Active (Contract NAS3-22518) Wing is presented. Investigation methodology, calculation

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methods, tests, and results, concerning system interpretation, multilayer insulation blanket placed between a hot and a cold system dynamics and achievable cost reduction, are described. boundary. The blanket consists of parallel identical perforated The problems with an integrated digital flight control system shields with left and right side emissivity. Shield thickness is so are treated. Gust load alleviation can be realized with available small that shield temperature is assumed to be even. The gas components. Operating cost reductions from 1% to 1.5% can be is assumed to flow from the hot towards the cold boundary, as obtained. The choice of control surfaces represents a risk, since in the case of insulation of a hot black box from cold space their unsteady highly subsonic aerodynamics during fast control environment. The model also applies for cryogenic vessel insulation is not sufficiently known. Author (ESA) (the cryogen at the cold side, the low pressure environment at the hot boundary) by interchanging suffixes in the governing N82-23253# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- equations. Results from guarded hot plate calorimeter tests confirm brunn (West Germany). Kurzueberischt fuer Information und model predictions. Author (ESA) Doku mentation. ACTTA: INVESTIGATION OF NEW PILOTING AND FLIGHT N82 23281# Utah Univ.. Salt Lake City. CONTROL TECHNOLOGIES. VOLUME 2: AIRCRAFT WITH THE EFFECT OF AN ACIDIC CATALYST ON SIMULTA- REDUCED LATERAL STABILITY Milestone Report on Phase NEOUS HYDRODENITROGENATION AND HYDRODESUL- 1, 1979 - 1980 [ACTTA: UNTERSUCHUNG NEUARTIGER FURIZATION OF MODEL COMPOUNDS Ph.D. Thesis STEUERUNGS- UND FLUGFUEHRUNGSTECHNOLOGIEN. Holly Jean Moore 1981 171 p MEILENSTEINBERICHT ZUR PHASE 1: 1979/1980. BAND Avail: Univ. Microfilms Order No. 8125903 2: FLUGZEUG REDUZIERTER LAENGSSTABILITAET] The hydrodesulfurization of thiophene and the hydrodenitro- Weise Kolander and U. A. Fischer 23 Mar. 1981 194 p refs genation of pyridine over acidic catalysts was studied. Four In GERMAN 2 Vol. catalysts were considered: CoMo-Si02/AI2O3. CoMo-AI203, (Contract BMFT-LFK-7960-9) NiW-Si02/AI203, and NiW-AI203. These catalysts were chosen (MBB-UH-05-81-Vol-2) Avail: NTIS HC A09/MF A01 so that the effect of the metallic complex and the effect of the The stretched version of the A-300 aircraft was used to acidic support could be isolated. Reaction conditions of 200 to assess the feasibility and economy of various digital flight 400 C and 40 to 200 psia were used. A two site reaction technologies for aircraft with reduced lateral stability. Investigation mechanism (sites 1 and 2) based on the Langmuir adsorption methodology, calculation methods, tests, and results, concerning isotherm was used to model the reaction of thiophene. A single system interpretation, system dynamics and achievable cost site (site 1) analysis described the reaction of pyridine. Values reduction, are described. Operating cost reduction of 1% to 3% of the reaction rate constants (k), and the adsorption equilib- is expected with reduced stability, using a trim tank as the first rium constants (K) were calculated from the data collected for step in a stepped design where sufficient emergency flight safety pure thiophene, pure pyridine, and for a 50/50 solution of each. is maintained in case the stabilizing system fails. Author (ESA) The results showed that both thiophene and pyridine adsorb significantly on the type 1 sites, but not on the type 2 sites. N82-23254* National Aeronautics and Space Administration. No consistent metal effect (NiW or CoMo) was observed. However, Langley Research Center, Hampton. Va. alumina was the more effective catalyst substrate for the reaction METRIC HALF-SPAN MODEL SUPPORT SYSTEM Patent of both thiophene and pyridine for 50/50 feeds. Alumina was Charlie M. Jackson, Jr.. Samuel M. Dollyhigh, and David S. also more effective for pure thiophene reaction, but silica alumina Shaw, inventors (to NASA) Issued 4 May 1982 5 p Filed was more effective for pyridine reaction from a pure feed. Supersedes N80-24334 (18 - 15. p 1943) Dissert. Abstr. (NASA-Case-LAR-12441-1. US-Patent-4.327.581. US-Patent-Appl-SN-145210: US-Patent-Class-73-147) Avail: US Patent and Trademark Office CSCL 148 N82-234O9# Research Inst. of National Defence. Linkoeping A model support system used to support a model in a wind (Sweden).. tunnel test section is described. The model comprises a metric, TRANSIENT MEASUREMENTS UNDER ELECTRIC PULSE or measured, half-span supported by a nonmetric. or nonmeasured EXCITATION IN 37 VIGGEN AIRCRAFT [TRANSIENTMAET- half-span which is connected to a sting support. Moments and NINGAR VID STROEMPULSEXCITERING AV FPL 37 forces acting on the metric half-span are measured without VIGGEN] interference from the support system during a wind tunnel test. Sven Garmland Oct. 1981 54 p In SWEDISH Official Gazette of the U.S. Patent and Trademark Office (FOA-C-30243-A3) Avail: NTIS HC A04/MF A01 Determinations of the magnetic field at different locations N82-23255# British Aerospace Aircraft Group, Preston (England). in aircraft and of the induced electromotive force in two typical Engine Simulation Section. communication cables of a transmission system, during full DEVELOPMENT OF A CONVOLUTED INTAKE SEAL FOR scale electric pulse tests, are reported. These measurements were MODEL R66 carried out in relation with lightning tests, for trying out a A. P. Winstanley Mar. 1981 33 p refs computerized measurement system, including transient digitizers, (BAE-ARG-163) Copyright. Avail: NTIS HC A03/MF A01 microwave link and magnetic field cells. The pulse generator A low constraint convoluted seal is described which connects was equipped with capacitors charged up to 75 kV. developing the live intake to the earthed ejector duct in a 1/7.5 scale low a sine wave 30 kHz pulse current with a 100 kA max amplitude. speed model with full engine simulation. A 6 component model Results enabled a computer program to be modified so as to with two earthed ejectors is required. Several seals were tested, account for actual conditions. Author (ESA) achieving a progressively lower constraint by modifying either the geometry, material or manufacturing process. Subjecting the N82-23471*# National Aeronautics and Space Administration. final seal to a representative pressure difference and end offset Langley Research Center. Hampton, Va. causes a lateral load of 6N. but incorporating the modifications BLOCKAGE AND FLOW STUDIES OF A GENERALIZED TEST recommended for future seals reduces this. Because the seals APPARATUS INCLUDING VARIOUS WING CONFIGURA- are on a moment arm from the balance when they are installed TIONS IN THE LANGLEY 7-INCH MACH 7 PILOT TUNNEL in the model, calibrations may have to account for pressure and Cindy W. Albertson Mar. 1982 50 p end misalignment. A facility for measuring pressure differences (NASA-TM-83301: NAS 1.15:83301) Avail: NTIS at the seal is incorporated in the design. Author (ESA) HC A03/MF A01 CSCL 20D A 1/12th scale model of the Curved Surface Test Apparatus N82-23263# National Aerospace Lab.. Amsterdam (Netherlands). (CSTA). which will be used to study aerothermal loads and evaluate Spaceflight Oiv. Thermal Protection Systems (TPS) on a fuselage-type configuration MULTILAYER INSULATION BLANKETS FOR SPACECRAFT in the Langley 8-Foot High Temperature Structures Tunnel (8 APPLICATIONS. THERMAL MODEL ACCOUNTING FOR ft HTST). was tested in the Langley 7-Inch Mach 7 Pilot Tunnel. OUTGASSING AND DIFFERENT WAYS OF GAS MIGRA- The purpose of the tests was to study the overall flow TION characteristics and define an envelope for testing the CSTA in A. A. M. Delil and J. F. Heemskerk 2 Sep. 1981 10 p refs the 8 ft HTST. Wings were tested on the scaled CSTA model Presented at 7th Intern. Heat Transfer Conf.. Munich, 6-10 Sep. to select a wing configuration with the most favorable characteris- 1982 tics for conducting TPS evaluations for curved and intersecting (NLR-MP-81051-U) Avail: NTIS HC A02/MF A01 surfaces. The results indicate that the CSTA and selected wing A model of hybrid pumping (broadside and edge) in space- configuration can be tested at angles of attack up to 15.5 and craft insulation blankets was developed for an evacuated circular 10.5 degrees, respectively. The base pressure for both models

370 N82-24137

was at the expected low level for most test conditions. Results ENGLISH summary generally indicate that the CSTA and wing configuration will (DFVLR-Mitt-82-01) Avail: NTIS HC A04/MF A01; DFVLR. provide a useful test bed for aerothermal pads and thermal Cologne DM 21.50 structural concept evaluation over a broad range of flow conditions Damage to buildings caused by the impact of trailing wake in the 8 ft HTST. Author vortices shed from widebodied aircraft in the final approach area of Dusseldorf Airport was studied. Forty-two occurrences N82-23494*# National Aeronautics and Space Administration. of roof damage were analyzed, using a simplified model for the Langley Research Center, Hampton, Va. strength, transport, and decay of wake vortices. The model is HISTORICAL PERSPECTIVES ON THERMOSTRUCTURAL interpreted with reference to the results of a vortex allevation RESEARCH AT THE NACA LANGLEY AERONAUTICAL program carried out in the U.S. Wake vortex characteristics, LABORATORY FROM 1948 TO 1958 maximum tangential velocity and vortex decay are discussed. Richard R. Heldenfels In its Computational Aspects of Heat Measurement of vortex far field reduction is considered. Other Transfer in Struct. 1982 p 363-392 refs investigations of roof damage in the approach areas of Hamburg, Berlin (Tempelhof). and London (Heathrow) airports are sum- Avail: NTIS HC A24/MF A01 CSCL 20D marized. The value of potential aircraft modifications and Some of the early research on structural problems produced precautions on the ground are assessed, suggesting supplementary by aerodynamic heating, conducted at the Langley Aeronautical measurements on board aircraft and in buildings. Author (ESA) Laboratory of the National Advisory Committee for Aeronautics from 1948 to 1958 is described. That was the last decade of N82-23561# National Aerospace Lab., Amsterdam (Netherlands). the NACA: in 1958 NACA became the nucleus of NASA. The Structures and Materials Div. . NACA initially contracted for research but was aware that a SOME CASE STUDIES AND THE SIGNIFICANCE OF well-equipped and suitably staffed laboratory was required to FATIGUE THRESHOLDS fulfill its obligations. Langley was established in 1920: the other R. J. H. Wanhill Apr. 1981 15 p refs Presented at Intern. listed were added during the NACA expansion in the World Symp. on Fatigue Thresholds, Stockholm, Jun. 1981 War II years. Some specific research activities are described, (NLR-.MP-81015-U) Avail: NTIS HC A02/MF A01 starting with calculation of the temperature of the structure. Examples of service failures, involving low-cycle and/or B.W. high-cycle fatigue, are described and discussed with respect to the significance of thresholds for high-cycle fatigue crack N82-23542# National Aerospace Lab.. Amsterdam (Netherlands). propagation. The examples are: aircraft undercarriage cylinders Structures and Materials Div. made of high strength 4340 steel: aircraft gas turbine compressor COMPARISON OF RELIABILITY. SENSITIVITY AND drive shafts made of A286 steel: and aircraft gas turbine blades ACCURACY OF SOME NDI TECHNIQUES made of Rene 80 nickel-base superalloy. The examples show E. A. B. deGraaf and P. deRijk Oct. 1980 32 p refs In that the importance of Delta K sub th is unlikely to be important DUTCH: ENGLISH summary Presented at Dutch Soc. for for a particular service fatigue problem. Delta K sub th as a Non-Destructive Testing Lecture Series, 4 Nov. 1980 design criterion is restricted to safe crack growth components (NLR-MP-80039-U) Avail: NTIS HC A03/MF A01 and structures whose anticipated service loads consist mainly or Reliability, sensitivity and accuracy of some nondestructive entirely of large numbers of low amplitude cycles and which inspection (NDI) methods were investigated and compared. are difficult or impossible to inspect in service. Author (ESA) Reliability, sensitivity and accuracy of nondestructive inspection are defined. The restrictions on reusing NDI reliability specimens are described. Inspection results obtained with fluorescent and N82-24O60*# Boeing Vertol Co., Philadelphia, Pa. red penetrants are compared. Reliability, sensitivity and accuracy AN INVESTIGATION OF ROTOR HARMONIC NOISE BY of a number of the most popular NDI methods, as applied to THE USE OF SMALL SCALE WIND TUNNEL MODELS Final aluminum specimens and rejected steel aircraft landing gear Report components are treated. Three investigations are briefly depicted. Harry Sternfeld, Jr. and Edward G. Schaffer Apr. 1982 100 p Spreading in NDI results is substantial. Corrosion deteriorates refs reliability, sensitivity and accuracy. Red penetrant is much worse (Contract NAS2-10767) than fluorescent penetrant. Fluorescent penetrant inspection (NASA-CR-166337: NAS 1.26:166337) Avail: NTIS results strongly depend on the specimen configuration and vary HC A05/MF A01 CSCL 20A from very good to moderate. Eddy current method gives good Noise measurements of small scale helicopter rotor models results. Magnetic inspection is advisable wherever it can be were compared with noise measurements of full scale helicopters applied. Author (ESA) to determine what information about the full scale helicopters could be derived from noise measurements of small scale helicopter models. Comparisons were made of the discrete N82-23549*# National Aeronautics and Space Administration. frequency (rotational) noise for 4 pairs of tests! Areas covered Langley Research Center, Hampton, Va. were tip speed effects, isolated rotor, tandem rotor, and main A TWO DEGREE OF FREEDOM FLUTTER MOUNT SYSTEM rotor/tail rotor interaction. Results show good comparison of WITH LOW DAMPING FOR TESTING RIGID WINGS AT noise trends with configuration and test condition changes, and DIFFERENT ANGLES OF ATTACK good comparison of absolute noise measurements with the Moses G. Farmer Apr. 1982 20 p refs Presented at Va. corrections used except for the isolated rotor case. Noise Academy of Sci. Meeting, Blacksburg, Va., 20-23 Apr. 1982 measurements of the isolated rotor show a great deal of scatter (NASA-TM-83302: NAS 1.15:83302) Avail: NTIS reflecting the fact that the rotor in hover is basically unstable. HC A02/MF A01 CSCL 14B Author A wind tunnel model mount system for conducting flutter research using a rigid wing was developed. The wing is attached to a splitter plate so that the two move as one rigid body. The N82-24137*# National Aeronautics and Space Administration. splitter plate is supported away from the tunnel wall by a system Lyndon B. Johnson Space Center, Houston. Tex. of rods with fixed fixed and conditions. The rods flex in such a RESEARCH AND TECHNOLOGY ANNUAL REPORT way that only pitch and plunge oscillations are permitted. At FY 1981 the tunnel wall the rods are attached to a remotely controlled Nov. 1981 100 p turntable so that angle of attack can be varied. Wind tunnel (NASA-TM-84199: NAS 1.15:84199) Avail: NTIS data obtained by using the mount system are presented for a HC A05/MF A01 CSCL 05A supercritical and a conventional airfoil. Both classical flutter and Space transportation systems are summarized: space shuttle stall flutter data are presented. S.L. enhancement, a space operations center, the space platform, and geostationary activites are discussed. Aeronautics and space N82-23560# Deutsche Forschungs- und Versuchsanstalt fuer technology are summarized: experiments, energy systems, Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer propulsion technology, synthetic aperture radar, large space Flugmechanik. systems, and shuttle-launched vehicles are discussed. Space A THEORETICAL STUDY OF THE IMPACT OF AIRCRAFT sciences are summarized: lunar, planetary, and life sciences are WAKE VORTICES ON ROOFS IN THE FINAL APPROACH discussed. Space and terrestrial applications are summarized. The AREA OF DUSSELDORF AIRPORT AgRISTARS program, forest and wildland resource, and Texas Otto Weber and Rolf Ulken Dec. 1981 63 p refs In GERMAN: LAND SAT applications are discussed. N.W.

371 SUBJECT INDEX AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 151) AUGUST 1982

Typical Subject Index Listing

SUBJECT HEADING) ACTTA: Investigation of nev piloting and flight control technologies. Volume 2: Aircraft with AITIICIIG ADDITIVES reduced lateral stability -Icing tunnel tests of a composite porous leading CHBB-OH-05-81-VOL-2] H82-23253 edge foe use vith a liquid anti-ice system ADBESIOH TESTS -Leuis icing research tunnel Structural integrity of an adhesively bonded [HASA-CH-164966] N82-11052 aircraft fuselage A82-28996 ADHESIVE BOIDIBS Applications of structural adhesives in production A82-28808 Production veldbonding on the A-10 aircraft A82-28995 The title is used to provide a description of the subject matter. When the Fatigue behavior of adhesively bonded joints title is insufficiently descriptive of the document content, a title extension A82-29032 is added, separated from the title by hyphens. The NASA or AIAA accession Bonded aluminum honeycomb - Aircraft flight number is included in each entry to assist the user in locating the abstract surface primary structure application in the abstract section of this supplement. If 9pplicable, a report number [AIAA 82-0676] A82-30145 is also included as an aid in identifying the document. ADHESIVBS Addition polyioide adhesives containing various end groups A82-29098 AEBIAL BECOBBAISSABCE The utilization of aircraft in fighting forest A-10 AIBCHAF1 fires - French experience Production veldbonding on the A-10 aircraft A82-29581 A82-28995 AEBODIHAHIC BBAEES A-300 AIBCBAPI Analysis and flight evaluation of a small, &CITA: Investigation of nev piloting and flight fized-ving aircraft equipped vith hinged plate control technologies. Volume 1: Beview; active spoilers wing [HASA-CB-166247] S82-22243 [HBB-OB-05-81-VOL-1] H82-23252 ABBODIHA8IC CHABACTEEISTICS ACTTA: Investigation of nev piloting and flight A computer-controlled oscillation mechanism for control technologies. Volume 2: Aircraft vith unsteady aerodynamics experiments reduced lateral stability A82-29018 [HBB-UH-05-81-VOI.-2] H82-23253 Development of a homebnilt povered sailplane ACCBiBBATIOH (PBISICS) A82-29416 Analysis of changes in the gas-dynamic parameters Computational aerodynamics - Its coming of age and of a gas-turbine helicopter engine during its future acceleration A82-29773 A82-29872 A wind-tunnel study of the aerodynamic A pilot in the loop analysis of helicopter characteristics of a slotted versus smooth-skin acceleration/deceleration maneuvers supercritical ving H82-23229 [AIAA 82-0642] A82-30139 ACCIDEH I1VESTIGATIOS Subsonic aerodynamic and flutter characteristics Transport aircraft accident dynamics of several wings calculated by the SOOSSA P1.1 [NASA-CB-165650] B82-22227 panel method Special investigation report: Evacuation of [AIAA PAPEB 82-0727] A82-30193 United Airlines DC-8-61, Sky Barbor Predictions of aerodynamic characteristics of International Airport, Phoenix, Arizona, highly maneuverable configurations December 29, 1980 II82-22199 (PB82-115619] H82-22236 Evaluation of direct force node fighters by combat ACODSTIC EHISSIOH simulation Acoustic emission from free jets supersonic jets N82-22204 H82-22962 Aerodynamic performance of slender vings vith ACODSTIC BICITAIIOi separated flows Acoustic noise test as part of the dynamic [HASA-CB-168768] 882-22206 qualification program in aerospace Aerodynanic characteristics of the external USB H82-22162 povered lift system using side fences for STOL aircraft structural vibration prediction from enhancement of Coanda flov attachment acoustic excitation [HA1-TB-686T] H82-22212 N82-22169 Application of Hainan filtering to the kinematic ACTIVE COKBOt reconstruction of free flight of catapulted Active control of aeroelastic divergence aircraft models in the laboratory £A±AA 82-0684] A82-30151 [IHFL-80-28] H82-22259 An electronic control for an electrohydraulic A flight investigation of blade-section active control landing gear for the F-4 aircraft aerodynamics for a helicopter main rotor having [SASA-CB-3552] H82-22252 BC-SC2 airfoil sections Control lav design to meet constraints using [SASA-TH-83298] H82-23192 SIHPAC-synthesis package for active controls AEBODXHMIC COEFFICIEHTS [HASA-TH-83264] H82-22280 Prediction of aerodynamically induced vibrations ACTTA: Investigation of nev piloting and flight in turbomacbinery blading control technologies. Volume 1: Eeviev; active A82-28986 ving [HBB-OH-05-81-V01-1] S82-23252

A-1 ABBODIiABIC COBFIGUB4TI08S SUBJECT IHDEI

Beal tine digital filtering test in the SI Application of a transonic potential flow code to continuous Hind tunnel at nodane the static aeroelastic analysis of B82-22152 three-dimensional wings Effect of nacelles on aerodynamic characteristics [HASA-TB-83296] H82-23193 of an executive-jet aodel vith simulated, Transonic flutter study of a wind-tunnel model of partial-chord, laainar-floii-control wing glove a supercritical wing with/without winglet [NASA-TB-83271] H82-22217 conducted in Langley Transonic Dynamics Tunnel Approximate method for predicting supersonic [HASA-Tfl-83279] H82-23239 nor»al force coefficient very-low-aspect-ratio AESODIliflIC STALLIIG lifting surfaces A computer-controlled oscillation mechanism for [AD~A111770] H82-23199 unsteady aerodynamics experiments ABBODIHABIC COBFIGOBATIOHS A82-29018 Aerodynamics at the 1981 Le Bourget show State of the art and recent perspectives on the A82-29789 study of the loss of control and spin Investigation of the aerodynamic-contour method H82-22197 with control functions in the form of smooth Performance pf single-stage axial-flow transonic constant-sign contours compressor with rotor and stator aspect ratios A82-29831 of 1.63 and 1.77, respectively, and with design Predictions of aerodynamic characteristics of pressure ratio of 2.05 highly maneuverable configurations [HASA-TP-2001] H82-22269 H82-22199 Unsteady pressure measurements at stall and Tail configurations for highly maneuverable combat buffeting aircraft [DFVLB-BITT-79-09] H82-23198 H82-22201 ABBODIBABICS Analysis of rotary balance data for the F-15 The effect of swirl burner aerodynamics on HOx airplane including the effect of ccnformal fuel formation tanKs A82-28658 [NASA-CB-3479] H82-22213 Measurement of aerodynamic work during fan flutter An experimental and theoretical investigation of A82-28987 the interaction between the engine jet and the Aerodynamic analysis of VTOL inlets and definition surrounding flow field with regard to the of a short, blowing-lip inlet pressure drag on afterbodies [HASA-CB-165617] H82-22211 H82-23158 The 1983 HASA Authorization, Volume 1 Experimental study of a jet deflector [GPO-91-488-VOL-1] H82-23068 B82-23173 An accurate method for evaluating the kernel of ABBODIBASIC DEA6 the integral equation relating lift to downvash Studies on wind tunnel straighteners in unsteady potential flow [BASA-TB-76689] B82-22284 [BASA-TB-83281] H82-23194 Automated design of minimum drag light aircraft AEBOBLASTICITI fuselages and nacelles Flutter of forward swept wings, analyses and tests [HASA-CB-168913] B82-23238 [AIAA 82-0646] A82-30142 AEBODIHAMC FOBCES Design considerations and experiences in the use Flutter analysis using nonlinear aerodynamic forces of composite material for an aeroelastic [AIAA 82-0728] A82-30176 research wing 4EBODIIABIC BEAIIH6 [AIAA 82-0678] A82-30146 Historical perspectives on thermostructural Active control of aeroelastic divergence research at the NACA Langley Aeronautical [AIAA 82-0684] A82-30151 Laboratory from 1948 to 1958 Transonic time-response analysis of three D.O.F. B82-23494 conventional and supercritical airfoils AEBODI1ABIC I1IEBFEBEHCE [AIAA 82-0688] A82-30155 A numerical investigation of two-dimensional, Application of a transonic potential flow code to subsonic, linear, vind tunnel interference theory the static aeroelastic analysis of [ABL/AEBO-HOTE-403] B82-23197 three-dimensional wings AEBODIBABIC LOADS [AIAA 82-0689] A82-30156 The stressed state of a parachute canopy during Comparison between computations and experimental opening data in unsteady three-dimensional transonic A82-29820 aerodynamics, including aeroelastic applications Application of a transonic potential flow code to [AIAA 82-0690] A82-30157 the static aeroelastic analysis of Aeroelastic flutter and divergence of stiffness three-dimensional vings coupled, graphite/epoxy, cantilevered plates [AIAA 82-0689] A82-30156 [AIAA 82-0722] A82-30172 Application cf optimal control techniques to Flutter analysis using nonlinear aerodynamic forces aircraft flutter suppression and load alleviation [AIAA 82-0728] A82-30176 [ilAA 82-0124] A82-30173 Feedback control of a cantilever wing in steady Development cf a correlated finite element dynamic airflow model of a complete aero engine [AIAA 82-0729] A82-30177 [PHB-90081] B82-22272 Aeroelastic tailoring for control and performance: ABBODIBABIC BOISE Are requirements compatible? The role of coherent structures in the generation B82-22200 of noise for subsonic jets Aeroelastic properties of wings in transonic flow [HASA-CB-168764] B82-22947 [BLB-BP-81005-0] H82-22224 Aerodynamic noise generated by jet-wing/flap Application of a transonic potential flow code to interactions of the external DSB configuration the static aeroelastic analysis of of STOL aircraft. Fart 1: Eight percent scale three-dimensional wings cold-flow model analysis [BASA-TB-83296] B82-23193 [HAL-TB-685T] H82-22953 Tine-marching transonic flutter solutions Aircraft aerodynamic noise during approach including angle-of-attack effects B82-22976 [BASA-TB-83295] B82-23196 AEBODYBABIC SIABILITI Transonic flutter study of a wind-tunnel model of Experiment on active flutter suppression of a a supercritical wing with/without winglet cantilever wing conducted in Langley Transonic Dynamics Tunnel [BAL-TB-690] B82-22282 [BASA-TH-83279] B82-23239 Jet V/STOL wind-tunnel simulation and gronndplane AEBOHADTICiL BHGIHEBBIIG effects Beview of aeronautical fatigue investigations in B82-23165 the Netherlands, March 1979 - February 1981 The modeling and prediction of multiple jet VTOL [SLB-BP-81006-0] B82-22153 aircraft flow fields in ground effect The 1983 NASA Authorization, Volume 1 B82-23166 [GEO-91-488-VOL-1] H82-23068 SUBJECT IHDBZ AIBCBAFT ACCIDBBTS

Research and Technology annual report FT-1981 AIB IBAFFIC COHTEOL [HASA-TM-84199] B82-24137 The investigation of aircraft accidents and ABBOSPACB BBGIIEEBIIG incidents - Sone recent national and The Boyal Aircraft Establishment: 100 years of international developments research A82-29275 [BAB-TM-FS-432] H82-22144 Air Traffic Flow Management and Air Traffic Flow Besearch and Technology annual report FY-1981 Control [HASA-TM-84199] H82-24137 A82-29923 ABBOSPACB IHDDSIBI Improvements to secondary radar for air traffic Critical netals conservation, recycling and control substitution A82-30311 [AGABD-B-693] H82-22348 Measures to increase airfield capacity by changing Besearch and development at MBB. Technical and aircraft runway occupancy characteristics scientific publications, 1981 [NASA-CB-168841] H82-22240 H82-23137 Analysis and Monte Carlo simulation of AEBOSPACB SCIBBCBS near-terminal aircraft flight paths Besearch and Technology annual report FY-1981 [HASA-TP-1997] H82-23233 [HASA-TM-84199] H82-24137 Extravehicular Activity/Air Traffic Control AFTEBBODIES (EVA/ATC) test report communication links to An experimental and theoretical investigation of the astronaut the interaction between the engine jet and the [HASA-CB-167600] H82-23381 surrounding flow field with regard to the AIB TBAISPOBTATIOH pressure drag on afterbodies The micro revolution cones to civil air transport 882-23158 A82-29259 ASI16 (BATEBIALS) Developmental possibilities and restrictions in Effects of 50,000 hours of thermal aging on air transport graphite/epozy and graphite/polyinide composites [DFVLB-MITT-81-9] H82-22229 [AIAA 82-0657] A82-3008V AIBBOBBE EQOIFBBBI AGBICOLIOBU AIBCBAFT Fighting fire and other disasters from the air; The utilization of agricultural aircraft in International Scientific-Technical Symposium, economical operations for fighting forest fires Hanover, iest Germany, Jane 11, 12, 1980, Beports in Israel A82-29576 A82-29580 Fighting forest fires with the aid of aircraft in AIB CAB60 the United States of America Handling air freight in the 1980s - Meeting the A82-29577 challenge Fighting forest fires - A task for the Swiss air 482-29800 force AIB DEPEBSE A82-29578 Multi-mission V/STOL with vectored thrust engines The current state of technology concerning the bombing, air superiority fighting of forest fires from the air in Austria £EHB-90086] B82-22278 A82-29579 AIB DOCIS The utilization of agricultural aircraft in The excitation of coopressor/duct systems economical operations for fighting forest fires 482-28993 in Israel AIB FLOi 182-29580 Pressure measurements on twin vertical tails in The utilization of aircraft in fighting forest buffeting flo« fires - French experience [AIAA 82-06141] A82-30138 A82-29581 Feedback control of a cantilever ving in steady The use of 'water bombers' and chemical agents airflow against forest fires, taking into account the [AIAA 82-0729] A82-30177 employment of a first-attack system Studies on wind tunnel straighteners A82-29582 [BASA-TM-76689] H82-22284 The employment of two-engine and four-engine AIB IRAKES aircraft for dropping the latest chemical fire Aerodynamic analysis of VIOL inlets and definition extinguishing agents in connection with the of a short, blowing-lip inlet fighting of forest fires [HASA-CB-165617] B82-22211 A82-29583 AIB BAVIGATIOI The employment of helicopters in Austria in Integrated navigation-TF/TA-system tased on stored connection with large-scale fires in buildings terrain data processing A82-29585 H82-23183 Performance characteristics and employment The integration of multiple avionic sensors and profiles of the new helicopter BK117 technologies for future ailitary helicopters A82-29586 H82-23186 BADIAK simulator for aircraft instruments AIB POLLDIIOH [FOA-C-40136-A3] H82-22286 Calculation of the contributions of air traffic The 1981 direct strike lightning data and road traffic to air pollution in the region utilizing the F-106 aircraft of Schiphol airport in 1S74 [HASA-TH-83273] N82-22848 [HLB-TB-77100-0] H82-22808 AIBBOBHE SOBVBILLAHCE BAD1B AIB 10 AIB HISSI1BS Secondary radar for airborne collision avoidance Optimal control and estimation for strapdown A82-30313 seeker guidance of tactical missiles AIBBOBIB/SPACEBOBBB COHPUIEBS A82-31121 The micro revolution comes to civil air transport AIB TO SDBFACE HISSILBS A82-29259 Naval versions of the Dauphin and the AS 15 XT Analysis of computing system configurations for weapon system helicopters highly integrated guidance and control systems [SHIAS-821-210-104] H82-22255 N82-23189 A light helicopter for night firing Development of a simple, self-contained flight [SHIAS-821-210-105] B82-22256 test data acquisition system AIB TBAFFIC [NASA-CB-168912] H82-23245 Developmental possibilities and restrictions in AIHCBAFT ACCIDEiT IBVBSTI6ATIOI air transport The investigation of aircraft accidents and [DF VLB-MITT-81-9] B82-22229 incidents.- Some recent national and Developmental possibilities in civil aviation in international developments the Federal Republic of Germany 482-29275 H82-22230 AIBCBAFT ACCIDEBTS Analysis of aircraft dynamic behavior in a crash environment [AIAA 82-0694] A82-30161

A-3 AIBCBAFI 1HTEHH1S SOBJECT IBDBX

Transport aircraft accident dynamics Some case studies and the significance of fatigue [BASA-CB-165850] B82-22227 thresholds aircraft components Beviev of rotorcraft accidents 1977-1979 [NLB-HP-81015-0] N82-23561 [PB82-115601] H82-22237 AIBCBAFI COBIBOl Technical approaches for measurement of human errors Estimation of the performance of nonstationary [BASA-CB-166314] 882-22219 discontinuous control systems for flight vehicles A theory of human error A82-29832 [HASA-CB-166313] B82-22250 Test demonstration of digital control of Comercial jet transport crashworthiness wing/store flutter (BASA-CB-165849] B82-23207 [AIAA 82-0645] A82-30141 AIBCBAFI AITEHIAS Improvements to secondary radar for air traffic Distributed airborne array concepts control 482-31669 A82-30311 GTO analysis of airborne antennas radiating in the Development of a tentative flying qualities presence of lossy dielectric layers criterion for aircraft with independent control £HASA-CB-168770] H82-22398 of six degrees of freedom: Analysis and flight AIBCBAFI COHPABMBHIS test Aircraft cabin air ozone contamination and 882-22191 compliance with regulations Hultivariahle closed loop control analysis and A82-31057 synthesis for complex flight systems Analytical prediction of the interior noise for 882-22193 cylindrical models of aircraft fuselages for Integration of avionics and advanced control prescribed exterior noise fields. Phase 2: technology Models for sidewall trim, stiffened structures B82-22194 and cabin acoustics vith floor partition Enhanced piloting control through cockpit [BASA-CB-165869] 882-22952 facilities and A.C.T. AIBCBAFI COBFIGUBATIOHS 882-22195 F-15 fighter abilities evaluated State of the art and recent perspectives on the A82-29592 study of the loss of control and spin Aerodynamics at the 1981 Le Bourget show 882-22197 A82-29789 Aeroelastic tailoring for control and performance: An automated technique for improving modal Are requirements compatible? test/analysis correlation B82-22200 [AIAA 82-0640] A82-30137 Tail configurations for highly maneuverable combat Control law design to meet constraints using aircraft SYNEiC-synthesis package for active controls 882-22201 [BASA-TH-83264] 882-22280 Analysis of rotary balance data for the F-15 HASA/HAA Advanced Botorcraft Technology and Tilt airplane including the effect of conformal fuel Botor iorkshop. Volume 6: Vehicle tanks Configuration Session [HASA-CB-3479] 882-22213 '[BASA-Tfl-84180] B82-23242 Effects of cable geometry and aircraft attitude on AIRCRAFT COBSXBOCIIOB HATBBIAIS the accuracy of a magnetic leader cable system Processing and uses of carbon fibre reinforced for aircraft guidance during rollout and turnoff plastics Book [BASA-TP-1978] B82-22239 A82-28643 An electronic control for an electrohydranlic Elevator unit for the Alpha-Jet, made from active control landing gear for the F-4 aircraft carbon-fibre reinforced plastic [NASA-CB-3552] 882-22252 482-28649 Control law design to Beet constraints using Tool use in cutting operations involving integral SINEAC-synthesis package for active controls structural components in aircraft construction [NASA-TH-83264] H82-22280 A82-28873 An analysis of a nonlinear instability in the Advanced aluminum and titanium structures; implementation of a VIOL control system Proceedings of the Binter Annual Meeting, [BASA-TH-84220] 882-22281 Washington, DC, November 15-20, 1981 Production Verification Testing (PVT) of guidance A82-28994 and control systems for high reliability A review of D.S. Air Force research related to B82-23187 airframe and engine materials State-of-the-art cockpit design for the HH-65A A82-29268 helicopters Flight qualification of composite structures at B82-23220 AHD-BA Performance evaluation of a kinesthetic-tactual IAIAA 82-0755] A82-30116 display A giant step tovard composite helicopters B82-23221 A82-30294 Synthesis of an integrated cockpit management system New materials fly better and cheaper B82-23222 A82-31426 Cockpit integration from a pilot's point of view Bevolution in airplane construction? Grob G110: B82-23224 The first modern fiber glass composition BASA/HAA Advanced Botorcraft Technology and Tilt airplane shortly before its maiden flight Botor Borkshop. Volume 7: Tilt Botor Session [NASA-IH-76705] H82-22246 tSASA-T«-84705] 882-23243 Tailor-made structures; today, and tomorrow: Hew ACTTA: Investigation of new piloting and flight materials, an exploratory investigation into control technologies. Volume 1: Beview; active their potential use in aircraft wing [BAE-SDB-85/A/104/005] B82-22253 [HBB-OH-05-81-VOL-1] 882-23252 Flight service evaluation of Kevlar-49 epoxy ACTTA: Investigation of new piloting and flight composite panels in wide-bodied commercial control technologies. Volume 2: Aircraft with transport aircraft reduced lateral stability [BASA-CB-165841] N82-22316 [MBB-OH-05-81-VOL-2] 882-23253 Critical metals conservation, recycling and AIBCBAFI DESIGB substitution Development of a homebnilt powered sailplane [AGABD-B-693] 882-22348 A82-29416 Powder metallurgical innovations for improved hot 8ASA research related to sailplane airfoils section alloys in aero-engine applications A82-29417 [PBB-90072] B82-22358 The utilization of agricultural aircraft in Engineering property comparisons of 7050-T73651, economical operations for fighting forest fires 7010-T7651 and 7010-l73t£1 aluminum alloy plate in Israel for aircraft construction A82-29580 £HLB-HP-80047-U] N82-22360

A-4 SUBJECT IIDIX AIBCBAFT BQUIPBBIT

The use of 'water bombers' and chemical agents V/STOL aircraft and fluid dynamic against forest fires, taking into account the H82-23179 employment of a first-attack system State-of-the-art cockpit design for the HH-65A A82-29582 helicopters The employment of two-engine and four-engine N82-23220 aircraft for dropping the latest chemical fire Synthesis of an integrated cockpit nanagement system extinguishing agents in connection with the N82-23222 fighting of forest fires Automated design of minimum drag light aircraft 482-29583 fuselages and nacelles Adaptation and equipment of aircraft for the [NASA-CB-168913] H82-23238 fighting of forest fires NASA/HAA Advanced Botorcraft Technology and Tilt &82-2958U Botor Workshop. Volume 7: Tilt Botor Session Computational aerodynamics - Its cooing of age and [NASA-TH-84705] 882-23243 its future AIBCBAFT EHGIHES 482-29773 The gas turbine engine Aerodynamics at the 1981 le Bourget show 482-28587 482-29789 Composite materials with emphasis for aircraft Comparison of light aircraft with strutted and gas turbine parts cantilever wings 482-28590 482-29828 4 review of O.S. Air Force research related to Design principles of a computer-aided design system airframe and engine materials 482-29829 482-29268 Investigation of the aerodynamic-contour method Development of a homebuilt powered sailplane with control functions in the form of smooth 482-29416 constant-sign contours Determination of an optimal control program for an 482-29831 aircraft power plant during climb Flight simulators 482-29845 482-29924 New processes and methods of technical diagnostics Pinite element analysis of through the canopy and prognostics in the case of the engine emergency crew escape fiom the T-38 aircraft NK-8-4. II [4144 82-0705] 482-30096 A82-29925 737 graphite-epoxy horizontal stabilizer Gas turbine engines used in aviation: Design and certification construction of components /5th revised and [AIA4 82-0745] 482-30109 enlarged edition/ Bnssian book Flight qualification of composite structures at A82-30697 AHD-BA chem-Braze abradable seal practical [4144 82-0755] 482-30116 A82-31048 Bonded aluminum honeycomb - Aircraft flight Maintenance in Service of High Temperature Parts surface primary structure application [AGABD-CP-317] N82-22172 [4IA4 82-0676] 482-30145 Engine depot maintenance repair technology Analysis of aircraft dynamic behavior in a crash N82-22174 environment Haintenance problems in gas turbine components at [AIAA 82-0694] A82-30161 the Boyal Naval Aircraft lard, Fleetlands Hew materials fly better and cheaper helicopter and marine gas turbines 482-31426 N82-22175 Combat 4ircraft Manoeuvrability Haintenance experience with civil aero engines [AGABD-CP-319] 1182-22187 1182-22176 The military flying gualities specification, a Engine component retirement for cause help or a hindrance to good fighter design N82-22177 flight control systems The influence of protective treatment on the 1182-22190 mechanical properties of superalloy parts The development of crycgenic wind tunnels and N82-22180 their application to maneuvering aircraft The role of modern control theory in the design of technology controls for aircraft turbine engines H82-22196 [NASA-TH-82815] H82-22262 State of the art and recent perspectives on the Advanced general aviation comparative study of the loss of control and spin engine/airfrane integration study H82-22197 [N4S4-CB-165564] N82-22263 Predictions of aerodynamic characteristics of Advanced Low-Emissions Catalytic-Combustor highly oaneuverable configurations Program, phase 1 aircraft gas turbine engines S82-22199 [H4S4-CB-159656] N82-22265 Aeroelastic tailoring for control and performance: Advanced general aviation engine/airframe Are requireaents compatible? integration study N82-22200 [HASA-CB-165565] N82-22268 The assessment of aircraft combat effectiveness BB211 powerplant deterioration: Review of current using a new computational method situation and lessons learned H 82-22 2 03 [PHB-90073] N82-22270 4 system safety model for developmental aircraft Development of a correlated finite element dynamic programs model of a complete aero engine [HAS4-CB-3534] H82-22228 [PNB-90081] N82-22272 Conceptual design study of a visual system for a Encounters with surge: Some experiences of rotorcraft simulator and some advances in development of axial compressors for aero gas platform motion utilization turbines [NASA-CB-166322] N82-22244 [PNB-90071] N82-22274 A linear decomposition method for large Beliable power BB211 aircraft engines optimization problems. Blueprint for development [PNB-90078] N82-22275 [NASA-TH-83248] H82-22245 Collaborative development of aero-engines Bevolution in airplane construction? Grob G110: [PNB-90083] H82-22277 The first modern fiber glass composition Powder metallurgical innovations for improved hot airplane shortly before its maiden flight section alloys in aero-engine applications [N4SA-Tfl-76705] 1182-22246 [PNB-90072] N82-22358 The 1983 NASA Authorization, Volume 1 AIBCB4FI EQDIPBEH1 [GPO-91-488-VOL-1] H82-23068 Cascade converter of dc voltage to ac voltage of Research and development at HBB. Technical and higher frequency with voltage and freguency scientific publications, 1981 stabilization devices — aircraft electric H82-23137 equipment Application of a structural optimization procedure 482-28875 for advanced wings [JIBB-FE-171/S/POB/49] H82-23141

4-5 AIBCBiFT GUIDABCB SUBJECT IBDBI

Adaptation and equipment of aircraft for the A review of recent AGABD Symposia on the Angle of fighting of forest fires Baneuverability of Combat Aircraft A82-29584 B82-22188 F-15 fighter abilities evaluated Beview of practical experience on combat aircraft 482-29592 uaneuverability Dynamic Environmental Qualification Techniques H82-22189 conference Experimental flight test programs for improving [AGABD-CP-318] B82-22154 combat aircraft maneuverability by maneuver Qualification of eguipnent for gunfire induced flaps and pylon split flaps vibration H82-22192 H82-22158 Integration of avionics and advanced control Dynamic qualification testing of F-16 equipment technology H82-22159 082-22191 Equipment vibration qualification for Harrier and Enhanced piloting control through cockpit Hawk aircraft facilities and A.C.T. H82-22161 882-22195 Gunfire blast pressure predictions The development of cryogenic wind tunnels and H82-22170 their application to maneuvering aircraft Development cf a taped random vibration technique technology for acceptance testing B82-22196 H82-22171 State of the art and recent perspectives on the Production Verification Testing (PVT) of guidance study of the loss of control and spin and control systems for high reliability H82-22197 H82-23187 Application of the theory of bifurcations to the AIBCBAFT GOIDAHCE study of the loss of control in combat aircraft Effects of cable geometry and aircraft attitude on H82-22198 the accuracy of a magnetic leader cable system Predictions of aerodynamic characteristics of for aircraft guidance during rollout and turnoff highly maneuverable configurations [BASA-TP-1S78] H32-22239 B82-22199 Integrated navigation-Tf/TA-system based on stored Evaluation of aircraft in simulated combat: terrain data piocessing Computer against computer or computer against B82-23183 human pilot Optimal inertial navigation using terrain B82-22202 correlation: An attractive solution to the The assessment of aircraft combat effectiveness ground attack aircraft navigation problem using a new computational method B82-2318U B82-22203 The integration of multiple avionic sensors and Evaluation of direct force mode fighters by coabat technologies for future nilitary helicopters simulation B82-23186 882-22204 Production Verification Testing (PVT) of guidance Flight tests for the assessment of task and control systems for high reliability performance and control activity H82-23187 H82-23213 San sensing guidance systeo for high altitude A helicopter handling-qualities study of the aircraft effects of engine response characteristics, [BASA-CASE-FBC-11052-1] B82-23231 height-control dynamics, and excess power on AIBCBAFT HAZABDS nap-of-the-Earth operations Sudden changes in wind velocity.- Their effect on B82-23214 aircraft and means of reducing hazard. I Dnified results of several analytical and A82-29871 experimental studies of helicopter handling AIBCHAPT I1STBOHEBTS qualities in visual terrain flight Checking and calibrating variometers in place in B82-23215 the sailplane instrument panel Validation of zero-order feedback strategies for A82-29U15 medium range air-to-air interception in a F-15 fighter abilities evaluated horizontal plane A82-29592 [BASA-Tfl-84237] B82-23237 BADIAK simulator for aircraft instruments AIBCBAFI MODELS [FOA-C-40136-A3] 1182-22286 Design of dynamically-scaled, asymmetrical wind AIBCBAPI LAID1BG tunnel models A portable, low-cost flight-data measurement and CBIAST-78/18] B82-22285 recording system Alternatives for jet engine control [HASA-TM-84229] B82-22478 [HASA-CB-168894] B82-23247 Analysis and Monte Carlo simulation of AIBCBAFT BOISE near-terminal aircraft flight paths Comparing the relationships between noise level [BASA-TP-1997] N82-23233 and annoyance in different surveys - A railway Planar equations of rollout motion for an aircraft noise vs. aircraft and road traffic comparison with free or steerable landing gears A82-29165 [BASA-TP-1984] B82-23214 Fuel efficient and Hach 0.8, too AIBCBAFI HAIiTEBABCE A82-29774 A computerized system for the application of STOL aircraft structural vibration prediction from fracture tracking data to aircraft management acoustic excitation for the C-5A military airlift transport 882-22169 [ilAA 82-0760] A82-30119 Becommendations for field measurements of aircraft Military maintenance policies and procedures for noise high-temperature parts, till they be adequate? [HASA-CB-3540] B82-22955 H82-22173 Aircraft aerodynamic noise during approach Engine depot maintenance repair technology B82-22976 B82-22174 Ground reflection effects in measuring propeller Maintenance experience with civil aero engines aircraft flyover noise H82-22176 [DFVLB-FB-81-28] B82-22990 Concept studies of an advanced composite An investigation of rotor harmonic noise by the helicopter fin use of small scale wind tunnel models £SBIAS-821-210-106] B82-22257 [BASA-CB-166337] - B82-24050 AIBCBAFX HAHEDVEBS AIBCBAFI PAB1S The stability of maneuverable flight vehicles Aviation gear drives and reducers: Handbook in A82-29827 Bussian Combat Aircraft Manoeuvrability A82-30675 [AGABD-CP-319] H82-22187 AIBCBAFI PEBFOBfliBCB BAS1 research related to sailplane airfoils A82-29417

A-6 SUBJECT IHDBX AIBCB4FT SIBOCTORES

The current state of technology concerning the Beview of rotorcraft accidents 1977-1979 fighting of forest fires from the air in Austria [PB82-115601] H82-22237 482-29579 NASA/HAA Advanced Botorcraft Technology and Tilt The use of 'water bombers' and chemical agents Botor Borkshop. Volume 6: Vehicle against forest fires, taking into account the Configuration Session employment of a first-attack system [BASA-TM-84180] 882-23242 482-29582 AIECBAFT SPECIFICATION F-15 fighter abilities evaluated The military flying qualities specification, a A82-29592 help or a hindrance to good fighter design Fuel efficient and Bach 0.8, too flight control systems A82-29774 N82-22190 Optimization of measurements in the state Development of a tentative flying gualities estimation of systems using the least sguares criterion for aircraft with independent control method of six degrees of freedom: Analysis and flight 182-29826 test Application of a dimensionless criterion of N82-22191 transport efficiency in evaluating aircraft Socata: TB 20 Trinidad given German debut modification s [HASA-TH-76706] N82-22247 A82-29837 Helicopter Handling Qualities The maximum flying range problem for an aircraft [NASA-CP-2219] H82-23208 A82-31602 VIOL and VSTOL handling qualities specifications, Combat Aircraft Hanoeuvrability an overview of the current status [AGAED-CP-319] N82-22187 H82-23209 The military flying qualities specification, a IlBCBAFT SPIH help or a hindrance to good fighter design Analysis of rotary balance data for the F-15 flight control systems airplane including the effect of conformal fuel H82-22190 tanks Development of a tentative flying qualities [NASA-CB-3479] S82-22213 criterion for aircraft with independent control AIBCBAFT STABILITY of six degrees of freedom: Analysis and flight Analysis of a multihinged empennage with allowance test for shear strain N82-22191 A82-29834 Experimental flight test programs for improving Application of optimal control techniques to combat aircraft maneuverability by maneuver aircraft flutter suppression and load alleviation flaps and pylon split flaps [AIAA 82-0724] A82-30173 N82-22192 AIBCBAFT STBOCTDBES Bultivariable closed loop control analysis and Occurrence of fretting fatigue failures in practice synthesis for complex flight systems A82-28543 H82-22193 Finite element thermal analysis of Aeroelastic tailoring for control and performance: convectively-cooled aircraft structures Are requirements compatible? A82-28565 N82-22200 Tool use in cutting operations involving integral Experience with high performance V/S10L fighter structural components in aircraft construction projects at BBB A82-28873 [MBB-FE-124/S/POB/50] H82-23140 Advanced aluminum and titanium structures; A flight investigation of blade-section Proceedings of the Winter Annual Meeting, aerodynamics for a helicopter main rotor having Washington, DC, November 15-20, 1981 BC-SC2 airfoil sections A82-28994 [NASA-Tfl-83298] N82-23192 Production weldbonding on the A-10 aircraft NASA/HAA Advanced Botorcraft Technology and Tilt A82-28995 Botor Borkshop. Volume 7: Tilt Botor Session Structural integrity of an adhesively bonded [NASA-TH-84705] H82-23243 aircraft fuselage ilBCBAFT PBODOCIIOH A82-28996 Tool use in cutting operations involving integral SPF of high strength aluminum structures structural components in aircraft construction superplastic forming for complex aircraft A82-28873 structures A comparison of properties of single overlap A82-28997 tension joints prepared by ultrasonic welding Development of low-cost titanium structures using and other means blended elemental powder metallurgy [AIAA 82-0661] A82-30091 A82-28998 A giant step toward composite helicopters Fatigue behavior of adhesively bonded joints A82-30294 A82-29032 AIBCBAFT BBLIABIUTT Development of a homebnilt powered sailplane Durability and damage tolerance control plans for A82-29416 OSAF aircraft Analysis of a multihinged empennage with allowance [AIAA 82-0679] A82-30147 for shear strain Civil (French/OS) certification of the Coast A82-29834 Guard's HH-654 Dauphin Zone loading of flight-vehicle structures N82-23210 A82-29838 Besults of NASA/FAA ground and flight simulation Structures, Structural Dynamics and Materials experiments concerning helicopter IFB Conference, 23rd, Hew Orleans, LA, Hay 10-12, airworthiness criteria 1982, Collection of Technical Papers. Part 1 - H82-23219 Structures and materials. Part 2 - structural AIBCBAFT SAFETI dynamics and design engineering Sudden changes in wind velocity - Their effect on A82-30076 aircraft and means of reducing hazard. I Integrity analyses of surface-flawed aircraft A82-29871 attachment lugs - A new, inexpensive, 3-D Secondary radar for airborne collision avoidance alternating method A82-30313 [AIAA 82-0742] A82-30107 Transport aircraft accident dynamics 737 graphite-epoxy horizontal stabilizer [NASA-CB-165850] N82-22227 certification A system safety model for developmental aircraft [AIAA 82-0745] A82-30109 programs Flight qualification of composite structures at [HASA-CB-3534] H82-22228 ABD-BA Special investigation report: Evacuation of [AIAA 82-0755] A82-30116 United Airlines DC-8-61, Sky Harbor Acoustic noise test as part of the dynamic International Airport, Phoenix, Arizona, qualification program in aerospace December 29, 1980 N82-22162 [PB82-115619] H82-22236

A-7 AIBCBAFI SDBVI74BH.III SOBJECT IHDBI

Aeroelastic tailoring for control and performance: Calculation of the contributions of air traffic Are reguirements compatible? and road traffic to air pollution in the region H82-22200 of Schiphol airport in 1974 Bevolntion in airplane construction? Grob G110: [HLB-TB-77100-0] H82-22808 The first nodern fiber glass composition Analysis and Honte Carlo simulation of airplane shortly before its maiden flight near-terminal aircraft flight paths [SASA-TH-76705] H82-22246 [HASA-IP-1997] H82-23233 Historical perspectives on thermostructural ALL-BBATHBB AIB S4?IS4TIOH research at the HACA Langley Aeronautical Controls and displays for all-weather operation of Laboratory froa 1948 to 1958 helicopters H82-23494 [HBB-OD-319-81-0] 1182-22260 AIBCBAFX SDBVI?ABILIII ALLOTS Analysis of aircraft dynamic behavior in a crash Hew materials fly better and cheaper environment A82-31426 [AIAA 82-0694] A82-30161 ALUHIIOB ALLOTS The assessment of aircraft com tat effectiveness Advanced aluminum and titanium structures; using a new computational method Proceedings of the Sinter Annual fleeting, H82-22203 Washington, DC, November 15-20, 1981 Commercial jet transport crashworthiness A82-28994 [HASA-CB-165849] N82-23207 SPF of high strength aluminum structures AIBCBAFT IIBES superplastic forming for complex aircraft Experimental stress analysis of a thin-walled structures pressurized torus loaded by contact with a plane A82-28997 dynamic response of aircraft tires Bonded aluminum honeycomb - Aircraft flight [AIAA 82-0753] A82-30114 surface primary structure application AIBCBAFI BAKES [AIAA 82-0676] A82-30145 A theoretical study of the impact of aircraft wake Beview of aeronautical fatigue investigations in vortices on roofs in the final approach area of the Netherlands, March 1979 - February 1981 Ousseldorf airport [HLB-HP-81006-0] H82-22153 [DFVLB-HITT-82-01] H82-23560 Engineering property comparisons of 7050-T73651, AIBFIBLD SUBFACB BOVBHEBTS 7010-T7651 and 7010-T73651 aluminum alloy plate Measures to increase airfield capacity by changing for aircraft construction aircraft runway occupancy characteristics [HLB-HP-80047-U] N82-22360 [BAS4-CB-168841] M82-22240 ALDHIBOB COATIBGS AIBFOIL FBBCBS An evaluation study of aluminide and Aerodynamic characteristics of the external OSB chromoaluoinide coatings on IB-100 powered lift system using side fences for A82-29597 enhancement of Coanda flow attachment ABGLB OF ATTACK [HAL-TB-686T] H82-22212 Measured and calculated effects of angle of attack AIBFOIL PBOFILBS on the transonic flutter of a supercritical wing A computer-controlled oscillation mechanism for [AIAA 82-0647] A82-30143 unsteady aerodynamics experiments State of the art and recent perspectives on the 482-29018 study of the loss of control and spin Transonic time-response analysis of tJiree O.O.F. N82-22197 conventional and supercritical airfoils A tactual display aid for primary flight training [AIAA 82-0688] A82-30155 [HASA-CB-166242] B82-22238 AIRFOILS Time-marching transonic flutter solutions Prediction of aerodynamically induced vibrations including angle-of-attack effects in turbomachinery blading [HASA-TH-83295] B82-23196 482-28986 A two-degree-of-freedom flutter mount system with HASA research related to sailplane airfoils low damping for testing rigid wings at different A82-29417 angles of attack Time-marching transonic flutter solutions [HASA-IH-83302] H82-23549 including angle-of-attack effects AHISOTBOPIC HBDIA [HASA-TH-83295] H82-23196 Component coupling with time-invariant mass matrix AIBFBAHE HATEBIALS for nonisotropic rotating and nonrotating systems High temperature, short term tensile strength of [AIAA 82-0731] A82-30179 C6000/PHB-15 graphite polyimide ABOHALXBS [4144 82-0711] 482-30125 Elastic suspension of a wind tunnel test section A giant step toward composite helicopters N82-23363 482-30294 ABTEHHA ABB4IS Beview of aeronautical fatigue investigations in Distributed airborne array concepts the Netherlands, Harch 1979 - February 1981 A82-31669 [NLB-HP-81006-IJ] H82-22153 AHTBHSA BADIAIIOI PATTEBIS AIBFB4BES GTD analysis of airborne antennas radiating in the A review of D.S. Air Force research related to presence of lossy dielectric layers airframe and engine materials [H4S4-CB-168770) B82-22398 A82-29268 AHTITABK BISSI1ES Component coupling with time-invariant mass matrix Approach in dynamic gualification of light for nonisotropic rotating and nonrotating systems helicopter stores and equipments [4I4A 82-0731] A82-30179 H82-22166 AIBPOBT PLA1BIBG APPBOACB Traffic intrastructure: Can planning still be Aircraft aerodynamic noise during approach carried through 882-22976 H82-22232 A theoretical study of the impact of aircraft wake AIBPOBTS vortices on roofs in the final approach area of Instruments aud installations for meteorological Dusseldorf airport measurements at airports finssian book [DF?LB-BITT-82-01] H82-23560 482-28826 ABCHIIBCTOBE (COHPDTEBS) Traffic intrastructure: Can planning still be Analysis of computing system configurations for carried through highly integrated guidance and control systems B82-22232 B82-23189 Measures to increase airfield capacity by changing ASYMPTOTIC HETHODS aircraft runway occupancy characteristics The stability of manenverable flight vehicles [HASA-CB-168841] H82-22240 A82-29827 Airfield visual aids research at the Boyal Aircraft Establishment [BAB-Tfl-FS-431] H82-22242

A-8 SOBJBCT IIDBX BDBIBBS

ASIBCHBOIOOS HOSOBS Cascade converter of dc vcltage to ac voltage of higher frequency with vcltage and frequency B stabilization devices aircraft electric BACKHABD iAVBS equipment Heasurement of aerodynamic work during fan flatter 482-28875 A82-28987 ATTACK AIBCBAFt BBBDIBG THBOBY Development of a tentative flying qualities The stability of monocoque panels under bending criterion for aircraft with independent control A82-29836 of six degrees of freedoa: Analysis and flight BIBD-AIBCBAFT COLLISIOBS test Bird impact analysis package for turbine engine 1182-22191 fan blades Experimental flight test programs for improving [AIAA 82-0696] A82-30162 combat aircraft maneuverability by maneuver BLADE TIPS flaps and pylon split flaps Helicopter rotor performance improvement by 1182-22192 utilization of swept-back parabolic blade tip Hultivariable closed loop control analysis and wind tunnel tests synthesis for complex flight systems H82-22151 H82-22193 BLAST LOADS Optimal inertia! navigation using terrain Gunfire blast pressure predictions correlation: An attractive solution to the 882-22170 ground attack aircraft navigation problem BLOCKING H82-23184 Blockage and flow studies of a generalized test ATTIfODB COBIBOL apparatus including various wing configurations Boeing 234 flight control development in the Langley 7-inch Hach 7 Pilot Tunnel B82-23211 [HASA-TH-83301] H82-23471 ATTIIUDB STABILITY BLOBIBG Development of a simple, self-contained flight Aerodynamic analysis of VIOL inlets and definition test data acquisition system of a short, blowing-lip inlet [HASA-CB-168912] 1182-23245 [HASA-CB-165617] H82-22211 AUTOMATIC COHTBOL BO-105 HELICOPTBB Design principles of a computer-aided design system Flight tests for the assessment of task A82-29829 performance and control activity Estimation of the performance of uonstationary N82-23213 discontinuous control systems for flight vehicles BODI-ilHG COBFI60BAIIOBS A82-29832 Flutter of forward swept wings, analyses and tests AUTOMATIC FLIGHT COHIBOL [AIAA 82-0646] A82-30142 Advanced technology DFCS control panel for the Bigid body-structural mode coupling on a forward L-1011-500 swept wing aircraft [AIAA PAPEB 81-2240] A82-29000 [AIAA 82-0683] A82-30150 Enhanced piloting control through cockpit Approximate method for predicting supersonic facilities and A.C.T. normal force coefficient very-low-aspect-ratio H82-22195 lifting surfaces Integrated navigation-lF/IA-system based on stored [AD-A111770] 882-23199 terrain data processing BOEING AIBCBAFT M82-23183 Handling air freight in the 1980s - Meeting the Boeing 234 flight control development challenge H82-23211 A82-29800 Some piloting experiences Kith multifunction Boeing 234 flight control development isometric side-arm controllers in a helicopter 882-23211 Jl 82-23218 BOBIBG 737 AIBCBAFT iOIOBOBILB EHGIHBS 737 graphite-epoxy horizontal stabilizer Future auto engines - Competition heats up certificat ion A82-29793 [AIAA 82-0745] A82-30109 ATBBAGB BOBBBB AIBCBAFT Program for narrow-band analysis of aircraft Bulti-mission V/STOL with vectored thrust engines flyover noise using ensemble averaging techniques bombing, air superiority [HASA-CB-165867] B82-22949 [P8B-90086] 1182-22278 A7IOIICS BONDIBG The structural dynamic interface required for Composite bonds improve thermal integrity developing helicopter target acguisition systems A82-30004 1182-22165 BOOBDABI LAIEB COHTBOL Integration of avionics and advanced control Investigation of passive shock wave-boundary layer technology control for transonic airfoil drag reduction H82-22194 [HASA-CB-168844] 882-22209 The integration of multiple avionic sensors and Aerodynamic analysis of VTOL inlets and definition technologies for future military helicopters of a short, blowing-lip inlet H 82-23186 [NASA-CB-165617] 882-22211 Analysis of computing system configurations for BBAZIHG highly integrated guidance and control systems Chem-Braze abradable'seal practical B82-23189 A82-31048 Helicopter Handling Qualities BOFFBTIBG [NASA-CP-2219] N82-23208 Pressure measurements on twin vertical tails in Civil (French/OS) certification of the Coast buffeting flow Guard's HH-65A Dauphin [AIAA 82-0641] A82-30138 882-23210 Unsteady pressure measurements at stall and Integrated cockpit for A-129 buffeting 882-23225 [DFVLB-HITT-79-09] H82-23198 AXIAL FLOB BDILDIBGS Performance of single-stage axial-flow transonic The employment of helicopters in Austria in compressor with rotor and stator aspect ratios connection with large-scale fires in buildings of 1.63 and 1.77, respectively, and with design A82-29585 pressure ratio of 2.05 BOB SEES [BASA-TP-2001] H82-22269 The effect of swirl burner aerodynamics on SOx AZIHDTH formation A complete method for computation of blade mode A82-28658 characteristics and responses in forward flight [SBIAS-821-210-101] H82-22254

A-9 C-5 AIBCBiFT SOBJECI IHDBI

CEIIEB OF BASS The maximum flying range problem for an aircraft A82-31602 C-5 AIBCBAFT CEBAHIC COATIiSS A computerized system for the application of The contribution of thermal barrier coatings to fracture tracking data to aircraft management improvements in the life and performance of gas for the C-5A military airlift transport turbine components [AIAA 82-0760] 182-30119 [PBB-90076] B82-22271 CABIH ATHOSPHBBBS CBBABICS Aircraft cabin air ozone contamination and Bew materials fly better and cheaper compliance with regulations A82-31426 A82-31057 CBBTIFICATIOB CALIBBAIIIG 737 graphite-epoxy horizontal stabilizer Checking and calibrating variometers in place in certification the sailplane instrnnent panel [AIAA 82-0745] A82-30109 A82-29415 Civil (French/OS) certification of the Coast CAHBEBED iI»6S Guard's HH-65A Dauphin Aerodynamic performance of slender wings with S82-23210 separated flows CESSHA 172 AIBCBAFT £HASA-CB-168768] H82-22206 Development of a simple, self-contained flight CABOPIBS test data acguisition system The stressed state of a parachute canopy daring [BASA-CB-168912] B82-23245 opening CHBOBIOH COHEOOBDS A82-29820 An evaluation study of aluminide and Finite element analysis of through the canopy chromoaluminide coatings on IH-100 emergency crew escape from the 1-38 aircraft A82-29597 [AIAA 82-0705] A82-30096 CIVIL AVIATI01 CABTXLBVEB UEBBEBS The micro revolution comes to civil air transport Experiment on active flutter suppression of a A82-29259 cantilever King Developmental possibilities in civil aviation in [HAL-TB-690] H82-22282 the Federal Republic of Germany CA1TI1EVEB FLAXES B82-22230 Aeroelastic flutter and divergence of stiffness Socata: IB 20 Trinidad given German debut coupled, graphite/epoxy, cantilevered plates [BASA-TB-76706] 882-22247 [AIAA 82-0722] A82-30172 The 1983 BASA Authorization, Volume 1 CAHBOH [GPO-91-488-VOL-1] B82-23068 Investigation of soot and carbon formation in Civil (French/OS) certification of the Coast small gas turbine combostors Guard's HH-65A Dauphin [BASA-CB-167853] H82-22267 B82-23210 CABBOI DIOXIDE LASEBS CLIBBIBG FLIGHT Humerical study of vibrational relaxation in the Determination of an optimal control program for an turbulent nixing of jets in a supersonic nozzle aircraft power plant during climb A82-29880 A82-29845 CABBOI FIBEB BEISFOBCED PLASTICS COABDA EFFECT Composite materials with emphasis for aircraft Aerodynamic characteristics of the external USB gas turbine parts powered lift system using side fences for A82-28590 enhancement of Coanda flow attachment Processing and uses of carbon fibre reinforced [HAL-TB-686T] B82-22212 plastics Book COCKPITS A82-28643 Flight simulators Elevator unit for the Alpha-Jet, made from A82-29924 carbon-fibre reinforced plastic Enhanced piloting control through cockpit A82-28649 facilities and A.C.T. High temperature, short term tensile strength of H82-22195 C6000/PBB-15 graphite pclyimide Helicopter Handling Qualities [AIAA 82-0711] A82-30125 [BASA-CP-2219] B82-23208 Service life investigation of a sailplane wing of State-of-the-art cockpit design for the HH-65A CFBP construction helicopters 882-22324 *~ B82-23220 CASCADE COBTBOL Synthesis of an integrated cockpit management system Cascade converter of dc voltage to ac voltage of 1 B82-23222 higher frequency with voltage and frequency The role of voice technology in advanced stabilization devices aircraft electric helicopter cockpits equipment 882-23223 A82-28875 Cockpit integration from a pilot's point of view CASCADE FLOB B82-23224 Prediction of aerodynamically induced vibrations Integrated cockpit for A-129 in tnrbouachinery blading 882-23225 A82-28986 Helicopter simulation technology: An Ames CATALYTIC ACTIVITY Besearch Center perspective Advanced Low-Emissions Catalytic-Combustor B82-23227 Program, phase 1 —- aircraft gas turbine engines COLLAPSE [BASA-CB-159656] H82-22265 Damage tolerant design using collapse techniques CATASTBOPHE THEOBY [AIAA 82-0718] A82-30168 Application of the theory of bifurcations to the On the dynamic collapse of a column impacting a study of the loss of control in combat aircraft rigid surface H82-22198 [AIAi 82-0735] A82-30182 CATHODE BAY TUBES COLLISION AVOIDABCE Integrated cockpit for A-129 Improvements to secondary radar for air traffic B82-23225 control CAVITIES A82-30311 A multidimensional-crack-growth prediction Secondary radar for airborne collision avoidance methodology for flaws originating at fastener A82-30313 holes COLOB CODIHG A82-28932 Application of computer generated color graphic CEHEBTS techniques to the processing and display of Pavement management and rehabilitation of Portland three dimensional fluid dynamic data for cement concrete pavements torbofan mixer nozzle mixing process analysis [PB82-131384] B82-22392 A82-29008

A-10 SUBJECT IBDBI COMPOTES PBOSBiHS

COLDHIS (SOPPOBIS) Design considerations and experiences in the use On the dynamic collapse of a column impacting a of composite material for an aeroelastic rigid surface research wing [AIAA 82-0735] A82-30182 [AIAA 82-0678] A82-30146 COBBAI New materials fly better and cheaper Combat training imagery A82-31426 A82-31179 COMPOSITE STBOCTOBES Coobat Aircraft Manoeuvrability Composite bonds improve thermal integrity [AGABD-CP-319] H82-22187 A82-30004 Beview of practical experience on conbat aircraft A giant step toward composite helicopters maneuverability A82-30294 N82-22189 La Becherche Aerospatiale, bi-monthly Bulletin The assessment of aircraft combat effectiveness number 1981-5, September - October 1981 using a neu computational method aerospace B and D methodology and instrumentation H82-22203 [ESA-TT-725] H82-22145 Evaluation of direct force mode fighters by combat Flight service evaluation of Kevlar-49 epoxy simulation composite panels in wide-bodied commercial H82-22204 transport aircraft The study of combat aircraft maneuverability by [BASA-CB-165841] S82-22316 air to air combat simulation COHPBBSSOB EFFICIEiCI H82-22205 Encounters with surge: Some experiences of Influence of maneuverability on helicopter combat development of axial compressors for aero gas effectiven ess turbines H82-23212 [PHB-90071] N82-22274 Validation of zero-order feedback strategies for COHPBESSOB BOTOES medium range air-to-air interception in a Performance of single-stage axial-flow transonic horizontal plane compressor with rotor and stator aspect ratios [HASA-TM-84237] H82-23237 of 1.63 and 1.77, respectively, and with design COHBOSTIOI CH AH BEES pressure ratio of 2.05 Advanced Low-Emissions Catalytic-Combustor [BASA-TP-2001] H82-22269 Program, phase 1 aircraft gas turbine engines COBPOTATIOHAL FLOID DIHAHICS [NASA-CB-159656] H82-22265 The relaxation oscillation in ramjet combustion Investigation of soot and carbon formation in A82-28738 small gas turbine combnstors A Schwarz-Christoffel method for generating [HASA-CB-167853] S82-22267 internal flow grids COHBOSTIOI PHISICS A82-29005 The combustion of a fuel jet in a stream of lean Computational aerodynamics - Its coming of age and gaseous fuel-air mixtures its future A82-28692 A82-29773 COHBOSTIOI PBODOCTS COMPOTES AIDED DBSIGH HOx formation in flat, laminar, opposed jet Computational aerodynamics - Its coming of age and methane diffusion flames its future A82-28660 A82-29773 Investigation of soot and carbon formation in Design principles of a computer-aided design system small gas turbine combnstors A82-29829 [HASA-CB-167853] H82-22267 Integrated structural analysis and design support COHBOSTIOI STABILITY for advanced launch vehicles The relaxation oscillation in ramjet combustion [AIAA 82-0675] A82-30144 A82-28738 A giant step toward composite helicopters COHHABD AID COMTEOL A82-30294 Sea-based remotely piloted vehicles. I - Issues COMPOTEE 6BAPHICS and concepts Application of computer generated color graphic A82-29714 techniques to the processing and display of COHHBBCIAL AIBCBAFT three dimensional fluid dynamic data for Test methodology for evaluation of fireworthy turbofan mixer nozzle mixing process analysis aircraft seat cushions A82-29008 A82-29596 Combat training imagery Calculation of the contributions of air traffic A82-31179 and road traffic to air pollution in the region COMPOTES PB06BABBIHG of Schiphol airport in 1574 Transient measurements under electric pulse [HLB-TB-77100-0] H82-22808 excitation in 37 Tiggen aircraft COHHOIICATIOI EQOIPBEHI [FOA-C-30243-A3] H82-23409 Sea-based remotely piloted vehicles. I - Issues COMPOTEB PEOGB1HS and concepts The micro revolution comes to civil air transport A82-29T14 A82-29259 Special investigation report: Evacuation of A computerized system for the application of Onited Airlines EC-8-61, Sky Harbor fracture tracking data to aircraft management International Airport, Phoenix, Arizona, for the C-5A military airlift transport December 29, 1980 [AIAA 82-0760] A82-30119 [PB82-115619] H82-22236 Comparison between computations and experimental COBPOSITE HATEBIALS data in unsteady three-dimensional transonic Processing and uses of carbon fibre reinforced aerodynamics, including aeroelastic applications plastics Book [AIAA 82-0690] A82-30157 A82-28643 Bird impact analysis package for turbine engine Otility of a probability-density-function curve fan blades and F-maps in composite-material inspection [AIAA 82-0696] A82-30162 A82-28934 Subsonic aerodynamic and flutter characteristics Structures, Structural Dynamics and Materials of several wings calculated by the SOOSSA P1.1 Conference, 23rd, Hew Orleans, LA, flay 10-12, panel method 1982, Collection of Technical Papers. Part 1 - [AIAA PAPEB 82-0727] A82-30193 Structures and materials. Part 2 - Structural Program for narrow-band analysis of aircraft dynamics and design engineering flyover noise using ensemble averaging techniques A82-30076 [HASA-CB-165867] H82-22949 Flight qualification of composite structures at Analysis of computing system configurations for AHD-BA highly integrated guidance and control systems [AIAA 82-0755] A82-30116 N82-23189 Environmental and high strain rate effects on A numerical investigation of two-dimensional, composites for engine applications subsonic, linear, wind tunnel interference theory [AIAA 82-0758] A82-30118 [ABL/AEBO-HOTE-403] H82-23197

1-11 COBPOIEB SIS1EBS DESI6H SO EJECT IBDBX

COHPOIEB SISIBBS DBSIGH Application of optimal control techniques to Integrated structural analysis and design support aircraft flutter suppression and load alleviation foe advanced launch vehicles [AIAA 82-0724] A82-30173 [AIAA 82-0675] A82-30144 Control law design to meet constraints using COHPOTBBIZED SIBOLATION SINPAC-synthesis package for active controls & Schwarz-Christoffel aethod for generating [HiSA-TH-83264] H82-22280 internal flow grids COBIBOL SOBFACBS A82-29005 Analysis of a anltibinged empennage with allowance A computer-controlled oscillation Mechanism for for shear strain unsteady aerodynamics experiments A82-29834 A82-29018 COBIBOL IBEOBI Lou cost aircrev training devices The role of modern control theory in the design of A82-29258 controls for aircraft turbine engines Cooputational aerodynamics - Its cooing of age and [HASA-TH-82815] H82-22262 its future COHIBOLLABILITI A82-29773 A review of recent AGABD Symposia on the Angle of Flight simulators flanenverability of Combat Aircraft A82-29924 1182-22188 Combat training imagery Helicopter Handling Qualities A82-31179 [NASA-CP-2219] N82-23208 Evaluation of aircraft in simulated combat: VIOL and VSTOL handling qualities specifications, Computer against computer or coaputer against an overview of the current status human pilot N82-23209 H82-22202 A helicopter handling-qualities study of the The study of combat aircraft maneuverability by effects of engine response characteristics, air to air combat simulation height-control dynamics, and excess power on H82-22205 nap-of-the-Earth operations COBCBEIES N82-2321U Pavement management and rehabilitation of pprtland Unified results of several analytical and cement concrete pavements experimental studies of helicopter handling [PB82-131384] H82-22392 gualities in visual terrain flight COBFEBBBCBS N82-23215 Advanced aluminum and titanium structures; An assessment of various side-stick Proceedings of the iinter Annual Meeting, controller/stability and control augmentation lashington. DC, Hovember 15-20, 1981 systems for night nap-of-Earth flight using A 82-28994 piloted simulation Soaring Society of America, Rational Convention, N82-23216 Phoenix, AZ, January 14-18, 1981, Eroceedings COBIBOLLEBS A82-29414 An assessment of various side-stick Fighting fire and other disasters froa the air; controller/stability and control augmentation International Scientific-Technical Synposiun, systens for night nap-of-Earth flight using Hanover, West Germany, June 11, 12, 1980, Beports piloted simulation A82-29576 N82-23216 Structures, Structural Dynamics and Baterials Some piloting experiences with multifunction Conference, 23rd, New Orleans, LA, flay 10-12, isometric side-arm controllers in a helicopter 1982, Collection of Technical Capers. Part 1 - N82-23218 Structures and materials. Part 2 - Structural CONNECTIVE BEAI fBAISFBE dynamics and design engineering Finite element thermal analysis of A82-30076 convectively-cooled aircraft structures Dynamic Environmental Qualification Techniques A82-28565 conference Advanced turbine study airfoil coling in [AGABD-CP-318] 1182-22154 rocket turbines Haintenance in Service of High Temperature Carts [HASA-CB-162003] 882-23249 [AGABB-CP-317] H82-22172 COOLIBG Fluid dynamics of jets with applications to V/STOL Finite element thermal analysis of [AGABD-CC-308] H82-23150 convectively-cooled aircraft structures Helicopter Handling Qualities A82-28565 [HASA-CP-2219] N82-23208 COOLIBG SISTEHS COHGBESSIO1AL BBPOBSS Advanced turbine study airfoil coling in The 1983 NASA Authorization, Volume 1 rocket turbines [GPO-91-488-VOL-1] N82-23068 [BASA-CB-162003] N82-23249 C01IC1L SHELLS COBBELAIIOB COEFFICIENTS Thermal stability analysis for conical shells with An automated technique for improving modal variable parameters test/analysis correlation A82-29844 [AIAA 82-0640] A82-30137 COBTABXBAHTS COSX EFFECTIVENESS Aircraft cabin air ozone contamination and Application of a dimensionless criterion of compliance with regulations transport efficiency in evaluating aircraft A82-31057 modifications COHTBACT BABAGEBEB1 A82-29837 Durability and damage tolerance control plans for COSX BEDOCTIOI DSAF aircraft Development of low-cost titaniua structures using [AIAA 82-0679] A82-30147 blended elemental powder metallurgy COBIBOL BOABDS A82-28998 Advanced technology DFCS control panel for the ACTTA: Investigation of new piloting and flight L-1011-500 control technologies, volume 1: Review; active [AIAA PAPEB 81-2240] 482-29000 wing Controls and displays for all-weather operation of [HBB-UH-05-81-VOL-1] H82-23252 helicopters ACTTA: Investigation of new piloting and flight [flBB-DD-319-81-0] N82-22260 control technologies. Volume 2: Aircraft with COHBOL COBFI60BBD VEHICLES reduced lateral stability Investigation of the aerodynamic-contour method [BBB-DH-05-81-VOL-2] N82-23253 with control functions in the form of smooth CBACE IHIII1TION constant-sign contours Integrity analyses of surface-flawed aircraft A82-29831 attachment lugs - A new, inexpensive, 3-D Bigid body-structural mode coupling on a forward alternating method swept wing aircraft. [AIAA 82-0742] A82-30107 [AIAA 32-0683] A82-30150

1-12 SUBJECT IIDU DELTA BUGS

CBACK PBOPAGATIOi & multidimensional-crack-growth prediction methodology for flans originating at fastener boles DAHAGB A82-28932 Damage tolerant design using collapse technignes Beview of aeronautical fatigue investigations in [AIAA 82-0718] A82-30168 the Motherlands, March 1S79 - February 1981 DAHAGB ASSESSHEII [BLB-HP-81006-D] H82-22153 Utility of a probability-density-function curve Engineering property comparisons of 7050-173651, and F-aaps in composite-material inspection 7010-17651 and 7010-173451 aluminum alloy plate A82-2893U --- for aircraft construction A computerized system for the application of [BLB-HP-80047-0] H82-22360 fracture tracking data to aircraft management CBlSflBS for the C-5A military airlift transport Transport aircraft accident dynaiics [AIAA 82-0760] A82-30119 [SASA-CB-165850J B82-22227 A theoretical study of the impact of aircraft wake Commercial jet transport crashvorthiness vortices on roofs in the final approach area of [BASA-CB-165849] S82-23207 Dusseldorf airport CBASBIOBTHIiESS [DFVLB-HITT-82-01] 1182-23560 Analysis of aircraft dynamic behavior in a crash DATA ACQUISIIIOI environnent Beview of rotorcraft accidents 1977-1979 [AIAA 82-0654] A82-30161 [PB82-115601] H82-22237 Commercial jet transport crashvorthiness Development of a simple, self-contained flight [HASA-CB-165819] 1182-23207 test data acgnisition system CRITICAL LOADIHG [HASA-CB-168912] H82-232H5 The stability of monocogue panels under bending DATA PBOCBSSIHG A82-29836 Application of Kalman filtering to the kinematic CBOSS FLOi reconstruction of free flight of catapulted Crossflow shock on the suction side of a flat aircraft models in the laboratory delta ving uith supersonic leading edges [IHFL-80-28] B82-22259 A82-29659 DAZA BEDOCTIOI Fluid dynamics of jets uith applications to V/STOL Application p£ Kalman filtering to the kinematic [AGABD-CP-308] H82-23150 reconstruction of free flight of catapulted Some aspects of jet dynamics and their aircraft models in the laboratory implications for VIOL research [IHFL-80-28] H82-22259 H82-23151 DATA STOBAGB An experimental and theoretical investigation of Integrated navigation-TF/TA-systen based on stored the interaction between the engine jet and the terrain data processing surrounding flow field with regard to the N82-23183 pressure drag on afterbodies DATA IBASSBISSIOB H82-23158 The micro revolution comes to civil air transport Determination of wind tunnel constraint effects by A82-29259 a unified pressure signature method. Part 2: Design principles of a computer-aided design system Application to jet-in-crossflow A82-29829 [BASA-CB-166187] N82-23235 DC 8 AIBCBAFT CBOISIBG FLIGHT Special investigation report: Evacuation of Checking and calibrating variometers in place in Onited Airlines DC-8-61, Sky Barbor the sailplane instrument panel International Airport, Phoenix, Arizona, A82-29U15 December 29, 1980 CBIOGEilC HID TOBBBLS [PB82-115619] B82-22236 Mechanical properties of a fiberglass prepreg DBCOHPOSITIOB system at cryogenic and other temperatures A linear decomposition method for large [AIAA 82-0708] A82-30099 optimization problems. Blueprint for development The development of cryogenic wind tunnels and [HASA-TH-83248] N82-22245 their application to maneuvering aircraft DEFECTS technology Defects and their effect on the behavior of gas H82-22196 turbine discs COBS N82-22178 Helicopter simulation technology: An Ames DEFLECT.OBS Research Center perspective Experimental study of a jet deflector H82-23227 1182-23173 CDHDLAIIfB DAHAGB DEGBEBS OF FBBEDOH On the characterization of damages in Flutter of forward swept wings, analyses and tests graphite-epoxy composites [AIAA 82-06"6] A82-30112 [AIAA 82-0757] A82-30117 Development of a tentative flying gnalities C OBI 16 criterion for aircraft with independent control Tailor-made structures; today, and tomorrow: Mew of six degrees of freedom: Analysis and flight materials, an exploratory investigation into test their potential use in aircraft B82-22191 [BAE-SDB-85/A/101/005] H82-22253 Elastic suspension of a wind tunnel test section COBVEO PABBLS H82-23363 The stability of monocogue panels under bending A two-degree-of-freedom flutter mount system with A82-29836 low damping for testing rigid wings at different CDSBIOIS angles of attack Test methodology for evaluation of fireworthy [HASA-TH-83302] B82-235H9 aircraft seat cushions DELTA ilBGS A82-29596 Crossflow shock on the suction side of a flat CYLIHDBICAL BODIES delta wing with supersonic leading edges Shape optimization of fiber reinforced composites A82-29659 [AIAA 82-0719] A82-30169 Static and unsteady pressure measurements on a 50 Analytical prediction of the interior noise for degree clipped delta wing at H = 0.9 cylindrical models of aircraft fuselages for [AIAA 82-0686] A82-30153 prescribed exterior noise fields. Phase 2: Application of a structural optimization procedure Models for sidewall trim, stiffened structures for advanced wings and cabin acoustics with floor partition [HBB-FB-171/S/POB/"»9] H82-231«1 [HASA-CB-165869] H82-22952 Static and unsteady pressure measurements on a 50 degree clipped delta wing at H = 0.9 conducted in the Langley Transonic Dynamics Tunnel [HASA-TH-83297] B82-23195

A-13 DBSIGI AIALISIS SUBJECT IIDBI

DBSIGI 4I41ISIS DOIHIASH SASA research related to sailplane airfoils An accurate method for evaluating the kernel of 182-29417 the integral equation relating lift to dovavash Design principles of a computer-aided design system in unsteady potential flow 482-29829 [H4SA-IB-83281] H82-23194 Design considerations and experiences in the use DBAG BE4SOBBBBIT of coaposite material for an aeroelastic iind tunnel investigations of sailplane fuselages research wing with different lacings and wing settings [1144 82-0678] 182-30146 aerodynamic drag measurement Damage tolerant design using collapse techniques BS2-23200 [4144 82-0718] 482-30168 DBAG BEDOCTIOI 4 linear decomposition method for large Investigation of passive shock wave-boundary layer optimization problems. Blueprint for development control for transonic airfoil drag redaction [H1S1-TH-83248 ] B82-22245 [BAS4-CB-168844] H82-22209 Advanced Low-Emissions Catalytic-Combustor Drag redaction using pneamatic turbulators Progran, phase 1 aircraft gas turbine engines laminar airfoils [B4S1-CB-159656] H82-22265 [DFVLB-FB-81-33] B82-22223 Synthesis of an integrated cockpit management system Automated design of minimum drag light aircraft H82-23222 fuselages and nacelles DIELECTRICS [HASA-CB-168913] H82-23238 G1D analysis of airborne antennas radiating in the DUCTS presence of lossy dielectric layers Turboprop and turbojet ejector optimisation [BAS4-CB-168770] 882-22398 H82-23174 DIESEL EIGIHES DOBABILITI Advanced general aviation comparative Durability and damage tolerance control plans for engine/airframe integration study OSAF aircraft [H4SA-CB-165564] B82-22263 [AIAA 82-0679] 482-30147 DIFFOSIOB FLiBES DIBAHIC CHARACTERISTICS BOx formation in flat, laminar, opposed jet Tail rotor studies for satisfactory performance: methane diffusion flames Strength and dynamic behavior 482-28660 [SBIAS-821-210-108] B82-22258 DIGITAL FILTBBS DIBAflIC COBTBOL La Becherche Aerospatiale, bi-nonthly Bulletin Estimation of the performance of nonstatiouary number 1981-5, September - October 1981 -:— discontinuous control systems for flight vehicles aerospace E and D methodology and instrumentation A82-29832 [ESA-TT-725] H82-22145 DIBABIC LOADS Heal time digital filtering test in the SI Aircraft fuel tank slosh and vibration test continuous vind tunnel at Hodane B82-22164 B82-22152 DIBABIC BODELS DIGITAL SIBOiATIOB Analysis of aircraft dynamic behavior in a crash The assessment of aircraft combat effectiveness environment using a new computational method [1111 82-0694] A82-30161 B82-22203 The maximum flying range problem for an aircraft Evaluation of direct force mode fighters by combat A82-31602 sinulation DIBABIC PBESSDBE M82-22204 Gunfire blast pressure predictions DIGITAL SYSTEMS B82-22170 Advanced technology DFCS control panel for the static and unsteady pressure measurements on a 50 L-1011-500 degree clipped delta wing at B = 0.9 [4144 PiPEB 81-2240] 482-29000 conducted in the Laugley Transonic Dynamics Tunnel DIGITAL TECHBIQDES [NASA-TB-83297] H82-23195 Analysis of computing system configurations for DIBAflIC BBSIOBSB highly integrated guidance and control systems Experimental stress analysis of a thin-walled H82-23189 pressurized torus loaded by contact with a plane DIHEISIOBLBSS HUB BEES dynamic response of aircraft tires Application of a dimensicnless criterion of [4IAA 82-0753] 482-30114 transport efficiency in evaluating aircraft Evaluation of four subcritical response methods modifications for on-line prediction of flutter onset in 482-29837 wind-tunnel tests DXBECTIOI1L COBIBOL £4144 82-0644] 482-30140 Besults of S4SA/FAA ground and flight simulation Dynamic Environmental Qualification Techniques experiments concerning helicopter IFB conference airworthiness criteria [AGABD-CP-318] B82-22154 N82-23219 Development and use of dynamic qualification DIBECTIOBA1 SOLIDIFICATIOB (CBISTAIS) standards for Air Force stores Directional solidification: project B2 of gas H82-22155 turbine rotor blade alloys Qualification of equipment for gunfire induced [PHB-90088] H82-22279 vibration DISPLAY DEVICES K82-22158 Controls and displays for all-weather operation of Development of vibration qualification test helicopters spectra for the F-15 aircraft [HBB-OD-319-81-O] H82-22260 B82-22160 State-of-the-art ccckpit design for the Hfl-654 Application of modal synthesis techniques for the helicopters dynamic qualification of wings with stores H82-23220 B82-22168 Performance evaluation of a kinestietic-tactual A complete method for computation of blade mode display characteristics and responses in forward flight H82-23221 [SBIAS-821-210-101] B82-22254 Cockpit integration from a pilot's point of view 4 helicopter handling-qualities study of the H82-23224 effects of engine response characteristics, Integrated cockpit for 4-129 height-control dynanics, and excess power on H82-23225 nap-of-the-Earth operations DISTOBTIOB B82-23214 Cooputer modeling of fan-exit-splitter spacing DIBABIC STABILITY effects on F100 response to distortion Design of dynamically-scaled, asymmetrical wind [NASA-CB-167879] H82-23246 tunnel models [HIAST-78/18] B82-22285

A-14 SUBJECT IHDEI EBGIBB FAILOBB

OIBAHIC SIBOCTURAL ABUISIS ELASTIC BEBDIHG Structures, Structural Dynamics and Materials The stability of monocoqne panels under bending Conference, 23rd, Hen Orleans, Li, day 10-12, A82-29836 1982, Collection of Technical Papers. Part 1 - ELASTIC HEDIi Structures and materials. Part 2 - Structural Elastic suspension of a wind tunnel test section dynamics and design engineering H82-23363 482-30076 ELASTIC PBOPBBTIES Experimental stress analysis of a thin-nailed Unsteady pressure measurements at stall and pressurized torus loaded by contact with a plane buffeting -— dynamic response of aircraft tires [DFVLB-HITT-79-09] H82-23198 [AIAA 82-0753] 482-30114 ELECTBIC PULSES Rigid body-structural mode coupling on a forward Transient measurements under electric pulse swept wing aircraft excitation in 37 Viggen aircraft [4144 82-0683] 482-30150 [F04-C-30243-43] 882-23409 Active control of aeroelastic divergence BLECTBOHIC BECOBDIBG SI SIMS [AIAA 82-0684] A82-30151 Development of a taped random vibration technique Application of a transonic potential flow code to for acceptance testing the static aeroelastic analysis of H82-22171 three-dimensional wings ELECTBOHIC BABFABE [Alii 82-0689] 482-30156 Sea-based remotely piloted vehicles. I - Issues Analysis of aircraft dynamic behavior in a crash and concepts environment A82-29714 [AIAA 82-0694] A82-30161 ELETATOBS (COBTBOL StJBFACES) Flatter analysis using nonlinear aerodynamic forces. Elevator unit for the Alpha-Jet, made from [4144 82-0728] 482-30176 carbon-fibre reinforced plastic Component coupling with time-invariant mass matrix A82-28649 for nonisotropic rotating and nonrotating systems EBEB6I COHVBBSIOB BFFICIEHCI [AIAA 82-0731] A82-30179 Energy efficient engine exhaust mixer model On the dynamic collapse of a column impacting a technoloqy rigid surface [HASA-CB-165459] H82-22264 [AIA4 82-0735] 482-30182 EHBBGI POLICI Application of a transonic potential flow code to Fuel efficiency enqines for large transport aircraft the static aexoelastic analysis of fPHB-90082] H82-22276 three-dimensional wings EHGIHE AIBFBABE IBTEGSATIOB [HASA-TM-83296] N82-23193 Advanced general aviation engine/airframe Historical perspectives on thermostructural integration study research at the H4CA Langley Aeronautical [H4S4-CB-165565] H82-22268 Laboratory from 1948 to 1S58 BBGIHB COBTBOL H82-23494 Determination of an optimal control program for an DIBAOIC TESTS aircraft power plant during climb Dynamic qualification testing of F-16 equipment 482-29845 N82-22159 A helicopter handling-qualities study of the The dynamic qualification of equipment and effects of engine response characteristics, external stores for use vith rotary winged height-control dynamics, and excess power on aircraft nap-of-the-Earth operations H82-22167 H82-23214 EBGIHB DESIGN The gas turbine engine A82-28587 BABLI BABBIB6 SIS1EHS Sheet materials - Fabrication and joining for Sea-based remotely piloted vehicles. I - Issues gas turbine engine components and concepts A82-28594 482-29714 Future auto engines - Competition heats up BCOBOHIC FACTORS A82-29793 Adaptation and equipment of aircraft for the Gas turbine engines used in aviation: Design and fighting of forest fires construction of components /5th revised and 432-29584 enlarged edition/ Russian book Air Traffic flow Management and Air Traffic flow A82-30697 Control The role of modern control theory in the design of A82-29923 controls for aircraft turbine engines EFFECTIVE EEBCEITED BOISE LEVELS [HASA-TH-82815] B82-22262 Comparing the relationships between noise level Energy efficient engine exhaust mixer model and annoyance in different surveys - A railway technology noise vs. aircraft and road traffic comparison [HASA-CB-165459] " H82-22264 A82-29165 BB211 powerplant deterioration: Review of current EPFECTITBHESS situation and lessons learned The assessment of aircraft combat effectiveness [PNB-90073] H82-22270 using a new computational method Development of a correlated finite element dynamic H82-22203 model of a complete aero engine Influence of maneuverability on helicopter combat [PNR-90081] N82-22272 effectiveness Parametric study of the influence of the engine H82-23212 upon the operating cost of a civil helicopter BJECTOBS [SNIAS-827-210-102] H82-22273 Fluid dynamics of jets with applications to V/STOL Reliable power -— RB211 aircraft engines [4GABD-CP-308] H82-23150 [PHB-90078] H82-22275 Thrust augmenting ejectors: A review of the Fuel efficiency engines for large transport aircraft application of jet nechanics to V/STOL aircraft [PHB-90082] H82-22276 propulsion Alternatives for jet engine control H82-23169 [H4S4-CB-168894] H82-23247 Theoretical optimisation and experimental Advanced turbine study airfoil coling in verification of an injector rocket turbines H82-23170 INAS4-CB-162003] H82-23249 Unsteady ejectors EBGIBE FAILOHE N82-23171 Computer modeling of fan-exit-splitter spacing Improvement of ejector thrust augmentation by effects on F100 response to distortion pulsating or flapping jets [HASA-CB-167879] H82-23246 H82-23172 Turboprop and turbojet ejector optinisation 882-23174

A-15 EB6IIE II1EIS SUBJECT IHDEI

EHGIIE IH1BTS EXHAOST EBlSSIOi Effect of nacelles on aerodynamic characteristics The effect of svirl burner aerodynamics on 8Ox of an executive-jet nodel Mitt simulated, formation partial-chord, laninar-flow-contiol King glove A82-28658 [HASA-TH-83271] N82-22217 BXBAOSZ GASES Development of a convoluted intake seal for model Calculation of the contributions of air traffic B66 v/stol wind tunnel and road traffic to air pollution in the region IBAE-ABG-163 ] H82-23255 of Schiphol airport in 1974 BBGIBB PABIS [H1B-TB-77100-U] H82-22808 The gas turbine engine EXHAUST SOZZLBS A82-28587 Energy efficient engine exhaust mixer model Gas turbine engines used in aviation: Design and technology construction of components /5th revised and [HASA-CB-165459] 1182-22264 enlarged edition/ -•— Bussian book EIHAOST SISTEHS £82-30697 Energy efficient engine exhaust mixer model Chen-Braze abradable seal practical technology S82-310i»8 [HASA-CB-165459] H82-22264 Effect of operating life on the mechanical Turboprop and turbojet ejector optimisation properties of the aaterials and load-bearing H82-23174 capacity of the rotor elements of gas-turbine Computer modeling of fan-exit-splitter spacing engines effects on F100 response to distortion 482-31643 [HASA-CB-167879] H82-23246 Maintenance in Service of High Temperature Farts EXHAUST VELOCITY [AGABD-CP-317] H82-22172 Evaluation of the effects of model scale and test Military maintenance policies and procedures for technique on jet-induced effects high-temperature pacts. Bill the; be adequate? H82-23167 H82-22173 BXTEBSAI SIOBB SBPABATIOI Engine depot maintenance repair technology Design of dynamically-scaled, asymmetrical wind N82-22174 tunnel models Maintenance problems in gas turbine components at [HIAST-78/18] H82-22285 the Boyal naval Aircraft lard, Fleetlands BZIBBBAL SIOBBS helicopter and marine gas turbines Dynamic Environmental Qualification Techniques — H82-22175 conference Maintenance experience with civil aero engines IAGABD-CP-318] 1182-22154 H82-22176 Development and use of dynamic gualification Engine component retirement for cause standards for Air Force stores N82-22177 H82-22155 Defects and their effect on the behavior of gas Qualification of equipment for gunfire induced turbine discs vibration H82-22178 882-22158 Bepair and regeneration of turbine blades, vanes Aircraft fuel tank slosh and vibration test and discs H82-22164 H82-22185 Approach in dynamic qualification of light The contribution of thermal barrier coatings to helicopter stores and equipments improvements in the life and performance of gas H82-22166 turbine components The dynamic qualification of equipment and [PHB-90076] H82-22271 external stores for use with rotary Hinged Advanced turbine study airfoil coling in aircraft rocket turbines H82-22167 CHASA-CB-162003] H82-23249 Application of modal synthesis techniques for the BBGIBB TESTS dynamic qualification of wings with stores New processes and methods of technical diagnostics - H82-22168 and prognostics in the case of the engine EXTBAVEHICOLAB ACTIVITY HK-8-4. II Extravehicular Activity/Air Traffic Control A82-29925 (EVA/ATC) test report communication links to BPOXX BATBIX. COHEOSITBS the astronaut Effects of moisture on the mechanical properties [HASA-CB-167600] H82-23381 of glass/epoxy composites A82-29036 EQUAIIOHS OF BO MOB Computational aerodynamics - Its coming of age and F-4 AIECBAFT its future An electronic control for an electrohydraulic A82-29773 active control landing gear for the F-4 aircraft Planar equations of rollout motion for an aircraft [HASA-CB-3552] H82-22252 vith free or steerable landing gears P-15 AIBCBAFT [HASA-TP-1984] H82-23244 F-15 fighter abilities evaluated EBBOB ABALISIS 482-29592 The reliability of height and identity data Pressure measurements on twin vertical tails in secondary surveillance radar error analysis buffeting flow A82-30312 £4144 82-0641] 482-30138 Technical approaches for measurement of human errors Development of vibration qualification test [HASA-CB-166314] H82-22249 spectra for the F-15 aircraft ESCAPE SISTEHS H82-22160 Finite element analysis of through the canopy Analysis of rotary balance data for the F-15 emergency crew escape from the T-38 aircraft airplane including the effect of conformal fuel [AIAA 82-0705] A82-30096 tanks EVACOATIB6 (TBAISPOBTATIOH) [N4SA-CB-3479] H82-22213 Special investigation report: Evacuation of Integrated flight and fire control demonstration United Airlines EC-8-61, Sky Harbor on an F-15B aircraft: System development and International 4irport, Phoenix, Arizona, ground test results December 29, 1980 H82-23185 [PB82-115619] H82-22236 F-16 AIBCBAFT BfUOATIOB Dynamic qualification testing of F-16 equipment Experience Kith high performance V/STOL fighter H82-22159 projects at HBB Integration of avionics and advanced control [HBB-FE-124/S/POB/50] H82-23140 technology H82-22194

A-16 SUBJECT ISDBI FUME BLEBBBT HBIBOD

F-106 AIBCBAFT FIBBB OBIEBIATION The 1981 direct strike lightning data • Damping and stiffness of aligned discontinuous utilizing the F-106 aircraft fiber reinforced polymer composites [NASA-TB-83273] H82-22848 [AIAA 82-0712] A82-30102 FABBICATIOI Shape optimization of fiber reinforced composites Development of a hoaebuilt powered sailplane [AIAA 82-0719] A82-30169 A82-29416 FIBBB BBIiFORCBD COBPOSITBS Developnent and demonstration of nanufacturing Damping and stiffness of aligned discontinuous processes for fabricating graphite/LABC 160 fiber reinforced polymer composites polyimide structural elements [AIAA 82-0712] A82-30102 [BiSA-CB-165809] H82-22315 Shape optimization of fiber reinforced composites FAIL-SAFE SISTEBS [AIAA 82-0719] A82-30169 Damage tolerant design using collapse technigues FISHTBB AIBCBAFT [AIAA 82-0718] A82-30168 Flight qualification of composite structures at FAILUBB ABALISIS AHD-BA Production Verification Testing (PVI) of guidance [AIAA 82-0755] A82-30116 and control systems for high reliability Aircraft fuel tank slosh and vibration test N82-23187 B82-22164 FAILDEE BODES Combat Aircraft Manoeuvrability Defects and their effect on the behavior of gas [AGABD-CP-319] H82-22187 turbine discs A review of recent AGABD Symposia on the Angle of H82-22178 Maneuverability of Combat Aircraft FAIBIBGS N82-22188 Flight service evaluation of Kevlar-49 epozy Beview of practical experience on combat aircraft conposite panels in Hide-bodied commercial maneuverability transport aircraft N82-22189 [BASA-CB-165841] H82-22316 The military flying gualities specification, a FAB BLADES help or a hindrance to good fighter design Mechanical properties of a fiberglass prepreg flight control systems system at cryogenic and other temperatures N82-22190 [AIAA 82-0708] A82-30099 Enhanced piloting control through cockpit Bird impact analysis package for turbine engine facilities and A.C.T. fan blades $8Z- 22195 [AIAA 82-0696] A82-30162 The development of cryogenic wind tunnels and FASTEBBBS their application to maneuvering aircraft A multidimensional-crack-growth prediction technology methodology for flaws originating at fastener N82-22196 holes State of the art and recent perspectives on the 182-28932 study of the loss of control and spin FAII6OB (BATEBIALS) N82-22197 Beviev of aeronautical fatigue investigations in Application of the theory of bifurcations to the the Netherlands, Batch 1979 - February 1981 study of the loss of control in combat aircraft [HLB-HP-81006-U] 882-22153 N82-22198 FATIGUE LIFE Tail configurations for highly maneuverable combat On the characterization of damages in aircraft graphite-epoxy composites H82-22201 [AIAA 82-0757] A82-30117 Evaluation of aircraft in simulated combat; Engine component retirement for cause Computer against computer or computer against S82-22177 human pilot Defects and their effect on the behavior of gas N82-22202 turbine discs The assessment of aircraft combat effectiveness H82-22178 using a new computational method Engineering property comparisons of 7050-T73651, H82-22203 7010-T7651 and 7010-T73651 aluminum alloy plate Evaluation of direct force mode fighters by combat for aircraft construction simulation [HLB-HP-80047-0] N82-22360 N82-22204 FATIGOB IESXS The study of combat aircraft maneuverability by Production veldbonding on the A-10 aircraft air to air combat simulation A82-28995 N82-22205 Fatigue behavior of adhesively bonded joints wind-tunnel investigation of the powered low-speed A82-29032 longitudinal aerodynamics of the A comparison of properties of single overlap Vectored-Engine-Over (VEO) wing fighter tension joints prepared by ultrasonic welding configuration and other means [NASA-TH-83263] N82-22207 [AIAA 82-0661] A82-30091 Hulti-mission V/STOL with vectored thrust engines FAULT TOLBBAiCE bombing, air superiority Analysis of computing system configurations for [CBB-90086] B82-22278 highly integrated guidance and control systems Experience with high performance V/STOL fighter N82-23189 projects at MSB FEEDBACK COITBOL [BBB-FB-124/S/POB/50] H82-23140 Active control- of aeroelastic divergence Validation of zero-order feedback strategies for [AIAA 82-0684] A82-30151 medium range air-to-air interception in a Feedback control of a cantilever wing in steady horizontal plane airflow [HASA-TH-84237] N82-23237 [AIAA 82-0729] A82-30177 FILLETS Hultivariable closed loop control analysis and Flight service evaluation of Kevlar-49 epoxy n- synthesis for complex flight systems composite panels in wide-bodied commercial /*• N82-22193 transport aircraft ,,' FIBEfl COHPOSITES [HASA-CB-165841] N82-22316 Processing and uses of carbon fibre reinforced FILB COOLING plastics Book Advanced turbine study airfoil coling in ,- A82-28643 rocket turbines '' Tailor-made structures; today, and tomorrow: New [NASA-CB-162003] N82-23249 materials, an exploratory investigation into FINITE BLEBEHT HBTHOD their potential use in aircraft Finite element thermal analysis of [BAE-SDH-85/A/104/005] B82-22253 convectively-cooled aircraft structures A82-28565

A-17 FIIS SOBJBCT IIDBX

Finite element analysis of through the canopy Performance characteristics and employment emergency crew escape from the 1-38 aircraft profiles of the new helicopter BK117 [AI4A 82-0705] A82-30096 A82-29586 Integrity analyses of surface-flawed aircraft FIBEPBOOFIBG attachment lags - A new, inexpensive, 3-0 Test methodology for evaluation of fireworthy alternating aethod aircraft seat cushions [AIA4 82-07*12] A82-30107 A82-29596 Experimental stress analysis of a thin-walled FIXED ilIGS pressurized torus loaded by contact with a plane Analysis and flight evaluation of a small, dynaaic response of aircraft tires fixed-wing aircraft equipped with hinged plate [Alii 82-0753] A82-30114 spoilers FIIS [HASA-CB-166247J B82-22243 Concept studies of an advanced composite V/STCL aircraft and fluid dynamic helicopter fin H82-23179 [SHIAS-821-210-106] S82-22257 Hew development in flying qualities with FIBS COBIBOL application to rotary wing aircraft Integrated flight and fire control denonstration 882-23226 on an F-15B aircraft: System development and FLAHE PBOPAGATIOi ground test results The relaxation oscillation in ramjet combustion 882-23185 A82-28738 FIBE EXTIIGOISHBHS FLAFCIIG Fighting fire and other disasters froo the air; Improvement of ejector thrust augmentation bj International Scientific-Technical Symposium, pulsating .or flapping jets Hanover, West Germany, June 11, 12, 1980, Beports B82-23172 A82-29576 FLAPPIB6 BIIGES Fighting forest fires with the aid of aircraft in Turbulence-excited flapping motion of a rotor the United States of America blade in hovering flight A82-29577 ' A82-29042 Fighting forest fires - A task, for the Swiss air FLEXIBLE IIBGS force Application f>f a transonic potential flow code to A82-29578 the static aeroelastic analysis of The current state of technology concerning the three-dimensional wings fighting of forest fires from the air in Austria [AIAA 82-0689] A82-30156 A82-29579 FLIGH1 ALTITUDE The utilization of agricultural aircraft in Checking and calibrating variometers in place in economical operations for fighting forest fires the sailplane instrument panel in Israel A82-29415 A82-29580 FLIGHT CBABACTEBISTICS The utilization of aircraft in fighting forest Performance characteristics and employment fires - French experience profiles of the new helicopter BK117 A82-29581 A82-29586 The use of 'water bombers' and chemical agents Belicopter rotor performance improvement by against forest fires, taking into account the utilization of swept-back parabolic blade tip employment of a first-attack system wind tunnel tests A82-29582 H82-22151 The employment of two-engine and four-engine Combat Aircraft Hanoeuvrability aircraft for dropping the latest chemical fire [AGABD-CP-319] H82-22187 extinguishing agents in connection with the The military flying qualities specification, a fighting of forest fires help or a hindrance to good fighter design A82-29583 flight control systems Adaptation and equipment of aircraft for the N82-22190 fighting of forest fires Development of a tentative flying qualities A82-29584 criterion for aircraft with independent control FIBE FI6HIIH6 of six degrees of freedom: Analysis and flight Fighting fire and other disasters from the air; test International Scientific-Technical Symposium, H82-22191 Hanover, Best Germany, June 11, 12, 1980, Beports Experimental flight test programs for improving 682-29576 combat aircraft maneuverability by maneuver Fighting forest fires with the aid of aircraft in flaps and pylon split flaps the United States of America N82-22192 A82-29577 Bultivariable closed loop control analysis and Fighting forest fires - A task for the Swiss air synthesis for complex flight systems force 882-22193 A82-29578 The development of cryogenic wind tunnels and The current state of technology concerning the their application to maneuvering aircraft fighting of forest fires from the air in Austria technology A82-29579 B82-22196 The utilization of agricultural aircraft in Socata: IB 20 Trinidad given German debut economical operations for fighting forest fires [HASA-TM-76706] H82-22247 in Israel Applications of system identification methods to 482-29580 the prediction of helicopter stability, control The utilization of aircraft in fighting forest and handling characteristics fires - French experience B82-23230 A82-29581 FLIGHT COSIBOl The use of "water bcmbers1 and chemical agents Combat Aircraft Hanoenvrability against forest fires, taking into account the £AGABD-CP-319] H82-22187 employment of a first-attack system The military flying qualities specification, a A82-29582 help or a hindrance to good fighter design The employment of two-engine and four-engine flight control systems aircraft for dropping the latest chemical fire H82-22190 extinguishing agents in connection with the flultivariable closed loop control analysis and fighting of forest fires synthesis for complex flight systems A82-29583 H82-22193 Adaptation and equipment of aircraft for the Integration pf avionics and advanced control fighting of forest fires technology 482-29584 H82-22194 The employment of helicopters in Austria in connection with large-scale fires in buildings A82-29585

A-18 SUBJECT IHDBI FLIGHT VEHICLES

Tie development of cryogenic wind tunnels and FLIGHT SAFETY their application to maneuvering aircraft The investigation of aircraft accidents and technology incidents - Some recent national and H82-22196 international developments Application of the theory of bifurcations to the 482-29275 study of the loss of control in combat aircraft Air Traffic Flow Management and Air Traffic Flow H82-22198 Control Strapdowm inertial navigation systems: &n A82-29923 algorithm for attitude and navigation computations FLIGHT SIBOLATIOB [AHL/Srs-BEPT-23] H82-22241 fieview of aeronautical fatigue investigations in Optimal inertial navigation using terrain the Netherlands, March 1979 - February 1981 correlation: in attractive solution to the [HLB-HP-81006-0] H82-22153 ground attack aircraft navigation problem Evaluation of aircraft in simulated combat: 1182-23184 Computer against computer or computer' against Integrated flight and fire control demonstration human pilot on an F-15B aircraft: System development and H82-22202 ground test results Functional reguirenents for the nan-vehicle H82-23185 systems research facility identifying and The integration of multiple avionic sensors and correcting human errors during flight simulation technologies for future military helicopters [NASA-CB-166315] 882-22248 1182-23186 Application pf Kalman filtering to the kinematic Production Verification Testing (PVT) of guidance reconstruction of free flight of catapulted and control systems for high reliability aircraft models in the laboratory H82-23187 [IHFL-80-28] H82-22259 Analysis of computing system configurations for Results of HASA/FAA ground and flight simulation highly integrated guidance and control systems experiments concerning helicopter IFB H82-23189 airworthiness criteria Flight tests for the assessment of task N82-23219 performance and control activity Helicopter simulation technology: An Ames H82-23213 Sesearch Center perspective An assessment of various side-stick H82-23227 controller/stability and control augmentation A pilot in the loop analysis of helicopter systems for night uap-of-Earth flight using acceleration/deceleration maneuvers piloted simulation H82-23229 H82-23216 Comparison ><& analytical predictions of Some piloting experiences with multifunction longitudinal short period pilot-induced isometric side-arm controllers in a helicopter oscillations with results from a simulation H82-23218 study of the space shuttle orbiter Results of HASA/FAA ground and flight simulation [HASA-TM-83267] H82-23236 experiments concerning helicopter IFB FLIGHT SIHOLATOHS airworthiness criteria Low cost aircrew training devices H82-23219 A82-29258 State-of-the-art cockpit design for the HH-65A Flight simulators helicopters A82-29924 H82-23220 Conceptual design study of a visual system for a The role of voice technology in advanced rotorcraft simulator and some advances in helicopter cockpits platform motion utilization H82-23223 [NASA-Cfi-166322] 1182-22244 Comparison of analytical predictions of FLIGHT STABILITY. TESTS longitudinal short period pilot-induced The stability of maneaverable flight vehicles oscillations with results from a simulation A82-29827 study of the space shuttle orbiter FLIGHT TESTS [HASA-TH-83267] H82-23236 F-15 fighter abilities evaluated ACTTA: Investigation of nev piloting and flight A82-29592 control technologies. Volume 1: Review; active Fuel efficient and Hach 0.8, too wing A82-29774 [HBB-UH-05-81-VOL-1] H82-23252 Flight qualification of composite structures at ACTTA: Investigation of new piloting and flight AUD-BA control technologies. Volume 2: Aircraft with [AIAA 82-0755] A82-30116 reduced lateral stability The helicopter Havstar GPS test program £HBB-OH-05-81-VOL-2] H82-23253 A82-31290 FLIGHT CBEiS Development .of a tentative flying qualities Low cost aircrew training devices criterion for aircraft with independent control A82-29258 of six degrees of freedom: Analysis and flight FLIGHT HBCHiHICS test A review of recent AGABD Symposia on the Angle of II82-22191 Haneuverability of Combat Aircraft Experimental flight test programs for improving 1182-22188 combat aircraft maneuverability by maneuver FLIGHT OCTIHIZATIOH flaps and pylon split flaps Comparison of light aircraft with strutted and N82-22192 cantilever wings Civil (French/OS) certification of the Coast A82-29828 Guard's HB-65A Dauphin Application of a dimensiciless criterion of N82-23210 transport efficiency in evaluating aircraft Flight tests for the assessment of task modifications performance and control activity A82-29837 H82-23213 The maximum flying range problem for an aircraft FLIGHT TBAIBIHG A82-31602 Low cost aircrew training devices FLIGHT PATHS A82-29258 Analysis and Honte Carlo simulation of A tactual display aid for primary flight training near-terminal aircraft flight paths (UASA-CB-166242] H82-22238 fHASA-TP-1997] H82-23233 A pilot in the loop analysis of helicopter FLIGHT SBCOEDEBS acceleration/deceleration maneuvers A portable, low-cost flight-data measurement and H82-23229 recording system FLIGHT VEHICLES [HASA-TH-84229] H82-22478 The stability of maneuverable flight vehicles A82-29827

A-19 F1IB DETECIOBS SUBJECT IHDEI

FLIB DBIBCIOBS Evaluation of four subcritical response methods Definition of display/control requirements for for on-line prediction flutter onset in assault transport night/adverse Heather capability wind-tunnel tests conducted in the Langley H82-23217 Transonic Dynamics Tunnel FLOB CHABACTEBIS3ICS [BASA-Tfl-83278] 1182-23240 The role of coherent structures in tie generation FLOTIBB AHALISIS of noise for subsonic jets A wind-tunnel study of the aerodynamic [HASA-CB-168764] H82-22947 characteristics of a slotted versus smooth-skin Determination of wind tunnel constraint effects by supercritical wing a unified pressure signature method. Fart 1: [AIAA 82-0642] A82-30139 Applications to winged configurations Evaluation of four subcritical response methods [MASA-Cfi-166186] H82-23234 for on-line prediction of flatter onset in Blockage and flow studies of a generalized test wind-tunnel tests apparatus including various wing configurations [AIAA 82-0644] A82-30140 in the Langley 7-inch Hach 7 Pilot Tunnel Test demonstration of digital control of [HASA-TH-83301] H82-23471 wing/store flutter FLO! DJSTBIBUTIOS [AIAA 82-0645] A82-30141 The modeling and prediction of multiple jet VTOL Flatter of forward swept wings, analyses and tests aircraft flow fields in ground effect [AIAA 82-0646] A82-30142 H82-23166 Heasnred and calculated effects of angle of attack Determination of wind tunnel constraint effects by on the transonic flutter of a supercritical wing a unified pressure signature method. Fart 2: [AIAA 82-0647] A82-30143 Application to jet-in-crossflow Design considerations and experiences in the use [MASA-CB-166187] 1182-23235 of composite material for an aeroelastic Automated design of minimum drag light aircraft research wing fuselages and nacelles [AIAA 82-0678] A82-30146 [HASA-CB-168913] H82-23238 Bigid body-structural node coupling on a forward FLO! BQDATIOHS swept wing aircraft Fluid dynamics of jets with applications to V/STOL [AIAA 82-0683] A82-30150 [AGABD-CP-308] H82-23150 Transonic flutter study of a wind-tunnel model of An experimental and theoretical investigation of a supercritical wing with/without winglet the interaction between the engine jet and the [AIAA 82-0721] A82-30171 surrounding flov field with regard to the Flutter analysis using nonlinear aerodynamic forces pressure drag on afterbodies [AIAA 82-0728] A82-30176 H82-23158 Subsonic aerodynamic and flutter characteristics FLOB GBOHE1BI of several wings calculated by the SOOSSA E1.1 A Schwarz-Christoffel method for generating panel method internal flow grids [AIAA PAPEB 82-0727] A82-30193 A82-29005 A two-degree-of-freedom flatter mount system with Fluid dynamics of jets with applications to V/SIOL low damping for testing rigid wings at different [AGABD-CP-308] H82-23150 angles of attack Flowfield and noise sources of jet impingement of [SASA-Tn-83302] 1182-23549 flaps and ground surface FLI BI 1IBE COHTBOL 1182-23163 Some piloting experiences with multifunction The modeling and prediction of multiple jet VTOL isometric side-arm controllers in a helicopter aircraft flow fields in ground effect H82-23218 H82-23166 FLIBBBEIS Jet effects on forces and moments of a VSTOL Prototype flywheel spin testing program fighter type aircraft [UCBL-15381] H82-22499 N82-23168 FOBCED yiBBAXIOH FLO! ttEASOBEHEHS Prediction of aerodynamically induced vibrations Determination of wind tunnel constraint effects by in turbomachinery blading a unified pressure signature method. Part 1: A82-28986 Applications to winged configurations FOBBST FIBES [NASA-CB-166186] H82-23234 Fighting fire and other disasters from the air; Determination of wind tunnel constraint effects by International Scientific-Technical Symposium, a unified pressure signature method. Part 2: Hanover, Best Germany, Jane 11, 12, 1980, Beports Application to jet-in-crossflow A82-29576 [NASA-CB-166187] H82-23235 Fighting forest fires with the aid of aircraft in FLO! SIABILIII the United States of America The excitation of compressor/duct systems A82-29577 A 82-28993 Fighting forest fires - A task for the Swiss air FLUID DIBAHICS force Thrust augmenting ejectors: A review of the A82-29578 application of jet mechanics to V/SIOL aircraft The current state of technology concerning the propulsion fighting of forest fires from the air in Austria H82-23169 A82-29579 V/STOL aircraft and fluid dynamic The utilization of agricultural aircraft in 1182-23179 economical operations for fighting forest fires Unsteady pressure measurements at stall and in Israel buffeting A82-29580 [DfVLB-HITT-79-09] H82-23198 The utilization of aircraft in fighting forest FLUID I8JBCII01 fires - French experience Theoretical optimisation and experimental A82-29581 verification of an injector The use of 'water bombers' and chemical agents H82-23170 against forest fires, taking into account the FLOTIEB employment of a first-attack system Measurement of aerodynamic work during fan flutter A82-29582 A82-28987 The employment of two-engine and four-engine Aeroelastic flutter and divergence of stiffness aircraft for dropping the latest chemical fire coupled, graphite/epoxy, cantilevered plates extinguishing agents in connection with the [AIAA 82-0722] A82-30172 fighting of forest fires Application of optimal control techniques to A82-29583 aircraft flutter suppression and load alleviation Adaptation and equipment of aircraft for the [AIAA 82-0721] A82-30173 fighting of forest fires A 82-2 9584

A-20 SUBJECT IBDEZ 61S TDHBIHB EIGIHES

FOHBIIG TECHHIQOBS FULL SCALE TESTS Sheet materials - Fabrication and joining for Transient measurements under electric pulse gas turbine engine components excitation in 37 Vigqen aircraft A82-28594 IFOA-C-30243-A3] H82-23409 SEP of high strength aluminum structures FOBCTIOHS (HATHBBATICS) superplastic forming for complex aircraft Investigation of the aerodynamic-contour method struct ores uith control functions in the form of smooth A82-28997 constant-sign contours FH1CTOHB BECHAIICS A82-29831 A multidimensional-crack-grovth prediction FDSB1AGBS aethodologj for flavs originating at fastener Structural integrity of an adhesively bonded holes aircraft fuselage 482-28932 A82-28996 Engine component retirement for cause Analytical prediction of the interior noise for H82-22177 cylindrical models of aircraft fuselages for FBACTOBB STBEHGIfl prescribed exterior noise fields. Phase 2: Engineering property comparisons of 7050-173651, Models for sideuall trim, stiffened structures 7010-17651 and 7010-173651 aluminum alloy plate and cabin acoustics with floor partition for aircraft construction [NASA-CB-165869] H82-22952 [HLB-HP-80047-U] 1182-22360 Hind tunnel investigations of sailplane fuselages FBACTOBBS (BA1BBIALS) uith different lacings and King settings A computerized system for the application of aerodynamic drag measurement fracture tracking data to aircraft management H82-23200 for the C-5A military airlift transport Automated design of minimum drag light aircraft £AIA4 82-0760] A82-30119 fuselages and nacelles FBEE FLIGHT TEST APPiBAIOS CHASA-CB-168913] S82-23238 Design of dynamically-scaled, asymmetrical Hind tunnel models [HIAST-78/18] H82-22285 FBEE JEIS GAS DIHAHICS Acoustic emission from free jets — supersonic jets Analysis of changes in the gas-dynamic parameters N82-22962 of a gas-turbine helicopter engine during Fluid dynamics of jets vith applications to V/STOL acceleration [AGABD-CP-308] B82-23150 A82-29872 Flovfield and noise sources of jet impingement of GAS STBEAHS flaps and ground surface The combustion of a fuel jet in a stream of lean H82-23163 gaseous fuel-air mixtures FBEQOBHCI STABILITY A82-28692 Cascade converter of dc voltage to ac voltage of GAS TDHBIHE EHGIIBS higher fregnency Hith voltage and frequency The gas turbine engine stabilization devices aircraft electric A82-28587 eguipment Composite materials -— uith emphasis for aircraft A82-28875 gas turbine parts FRETTIMG A82-28590 Occurrence of fretting fatigue failures in practice Sheet materials - Fabrication and joining --- for A82-28513 gas turbine engine components FUEL COBBOSTIOH A82-28594 The effect of SHirl burner aerodynamics on BOx Analysis of changes in the gas-dynamic parameters formation of a gas-turbine helicopter engine during A82-28658 acceleration The combustion of a fuel jet in a stream of lean A82-29872 gaseous fuel-air mixtures Gas turbine engines used in aviation: Design and A82-28692 construction of components /5th revised and Advanced Lov-Emissions Catalytic-Combnstor enlarged edition/ Bussian book Program, phase 1 aircraft gas turbine engines A82-30697 [BASA-CB-159656] B82-22265 Effect of operating life on the mechanical FOE! COiSOHPTIOB properties - of the materials and load-bearing Fuel efficient and Bach 0.8, too capacity of the rotor elements of gas-turbine A82-29774 • engines Application of a dimensionless criterion of A82-31643 transport efficiency in evaluating aircraft Maintenance in Service of High Temperature Parts modifications [AGABD-CP-317] H82-22172 482-29837 Military maintenance policies and procedures for Determination of an optimal control program for an high-temperature parts, iill they be adeguate? aircraft power plant during climb 1182-22173 A82-29845 Engine depot maintenance repair technology Advanced general aviation comparative H82-22174 engine/air frame integration study Maintenance problems in gas turbine components at [HASA-CB-165564] H82-22263 the Boyal Naval Aircraft lard, Fleetlands Energy efficient engine exhaust mixer model helicopter and marine gas turbines technology H82-22175 [HASA-CB-165459] N82-22264 Maintenance experience vith civil aero engines Parametric study of the influence of the engine H82-22176 upon the operating cost of a civil helicopter Engine component retirement for cause £SHIAS-827-210-102] N82-22273 N82-22177 Encounters uith surge: Some experiences of Defects and their effect on the behavior of gas development of axial compressors for aero gas turbine discs turbines H82-22178 £ PHB-90071] B82-22274 The influence of protective treatment on the Fuel efficiency engines for large transport aircraft mechanical properties of superalloy parts tPBB-90082] H82-22276 N82-22180 FDBL TASKS Bepair and regeneration of turbine blades, vanes Aircraft fuel tank slosh and vibration test and discs B82-22164 H82-22185 Analysis of rotary balance data for the F-15 Investigation of soot and carbon formation in airplane including the effect of conformal fuel small gas turbine combustors tanks (NASA-CB-167853] H82-22267 [HASA-CB-3479] 1182-22213

A-21 GAS IOBBIIES SUBJECT IIDEX

EB211 poverplant deterioration: Beviev of current Service life investigation of a sailplane wing of situation and lessens learned CFBP construction [PBB-90073] H82-22270 882-22324 The contribution of thermal barrier coatings to iind tunnel investigations of sailplane fuselages improvements in the life and performance of gas with different lacings and wing settings turbine components aerodynamic drag measurement [PHB-90076] H82-22271 B82-23200 Reliable power BB211 aircraft engines GLOBAL POSIIIOIIHG SISTBH [PHB-90078] H82-22275 The helicopter Bavstar GPS test program Directional solidification: Project B2 --- of gas A82-31290 turbine rotor blade alloys GOVEBBflBH PBOCOBBBBiT £PBB-90088] H82-22279 Durability and damage tolerance control plans for A helicopter handling-qualities stud; of the OSA* aircraft effects of engine response characteristics, [AIAA 82-0679] A82-30147 height-control dynamics, and excess power on GBAPHITE-EPOXI COHPOSITES nap-of-the-Earth operations Composite bonds improve thermal integrity H82-2321U A82-30004 Analysis of high load dampers Effects of 50,000 hours of thermal aging on [HAS1-CB-165503] 882-23248 graphite/epoxy and graphite/polyimide composites GAS TDBBISES [AIAA 82-0657] A82-30087 Basic technology of squeeze-film dampers for rotor 737 graphite-epoxy horizontal stabilizer dynamics control certification [AD-A110842] H82-23250 [AIAA 82-0745] A82-30109 GASDIBABIC 1ASEBS On the characterization of damages in numerical study of vibrational relaxation in the graphite-epoxy composites turbulent mixing of jets in a supersonic nozzle [AIAA 82-0757] A82-30117 A82-29880 Aeroelastic flutter and divergence of stiffness GASEOUS FUELS coupled, graphite/epoxy, cantilevered plates The combustion of a fuel jet in a stream of lean [AIAA 82-0722] A82-30172 gaseous fuel-air mixtures A giant step toward composite helicopters A82-28692 A82-30294 GEABS Concept studies of an advanced composite Aviation gear drives and reducers: Handbook in helicopter fin Bussian [SBIAS-821-210-106] B82-22257 A82-30675 The 737 graphite composite flight spoiler flight GBBEBAL AVIATION AIBCBAW service evaluation Maintenance experience with civil aero engines [HASA-CB-165826] B82-22314 S82-22176 GBAPHITB-POLIIBIDE COHPOSITES Effect of nacelles on aerodynamic characteristics Effects of 50,000 hours of thermal aging on of an executive-jet model with simulated, graphite/epoxy and graphite/polyimide composites partial-chord, laminar-flow-contrcl ving glove [AIAA 82-0657] A82-30087 [BASA-TB-83271] H82-22217 High temperature, short term tensile strength of Analysis and flight evaluation of a small, C6000/PBB-15 graphite polyimide fixed-wing aircraft equipped with hinged plate [AIAA 82-0711] A82-30125 spoilers Development and demonstration of manufacturing [BASA-CB-166247] H82-22243 processes for fabricating graphite/LABC 160 Revolution in airplane construction? Gcob G110: polyimide structural elements The first modern fiber glass composition [HASA-CB-165809] B82-22315 airplane shortly before its maiden flight GBIDS [BASA-TM-76705] H82-222U6 A Schwarz-Christoffel method for generating GEOHETBICAL THEOBI OF DIFJBACTIOB internal flow grids GTD analysis of airborne antennas radiating in the A82-29005 presence of lossy dielectric layers GBOOBD BASED COBTBOL [BASA-CB-168770] B82-22398 Helicopter simulation technology: An Ames 6BBHABI Besearch Center perspective Developmental possibilities in civil aviation in B82-23227 the Federal Republic of Germany GBOOBD EFFECT B82-22230 Ground reflection effects in measuring propeller Traffic intrastructure; Can planning still be aircraft flyover noise carried through [DFV1B-FB-81-28] B82-22990 B82-22232 GBODHD EFFECT (ABBODISABICS) GIBBALS Performance testing of a main rotor system for a Composite bonds improve thermal integrity utility helicopter at 1/4 scale A82-30004 [HASA-TB-83274] H82-22251 GLASS PIBBB BEKFOBCBD PLASTICS The modeling and prediction of multiple jet VTOL Composite materials with emphasis for aircraft aircraft flow fields in ground effect gas turbine pacts B82-23166 A82-28590 Evaluation of the effects of model scale and test Effects of moisture on the mechanical properties technique on jet-induced effects of glass/epoxy composites 882-23167 A82-29036 Jet effects on forces and moments of a VSTOL Mechanical properties of a fiberglass prepreq fighter type aircraft system at cryogenic and other temperatures 882-23168 [AIAA 82-0708] A82-30099 V/STOL aircraft and fluid dynamic Bevolution in airplane construction? Grob G110: 882-23179 The first modern fiber glass composition GBOOBD SPEED airplane shortly before its maiden flight Hagnetic anomalies as a reference for ground-speed [BASA-TH-76705] B82-22246 and map-matching navigation GtlDEBS A82-30314 Soaring Society of America, Bational Convention, GBODBD TESTS Phoenix, AZ. January 14-18, 1981, Proceedings Integrated flight and fire control demonstration A82-29414 on an F-15B aircraft: System development and Checking and calibrating variometers in place in ground test results the sailplane instrument panel B82-23185 A82-29415 6DIDABCB SEBSOBS Development of a homebuilt powered sailplane The integration of multiple avionic sensors and A82-29416 technologies for future military helicopters BASA research related to sailplane airfoils 882-23186 A82-29417

A-22 SUBJECT JHDBI HBLICOPTBB PBBFOBBANCB

Sun sensing guidance system for high altitude A helicopter handling-qualities study of the aircraft effects of engine response characteristics, [HASA-CASE-FBC-11052-1] H82-23231 height-control dynamics, and excess power on 6UBPIBE nap-of-the-Barth operations Qualification of equipment for gunfire induced N82-23214 vibration An assessment of various side-stick N82-22158 controller/stability and control augmentation GDIS (OBDBABCB) systems for night nap-of-Earth flight using Gunfire blast pressure predictions piloted simulation H82-22170 H82-23216 COST ALLEYIATOBS Helicopter simulation technology: An Ames Control lav design to meet constraints using Besearch Center perspective SIHPAC-synthesis package for active controls B82-23227 [NASA-TH-83264] H82-22280 Applications of system identification methods to 6DSX LOADS the prediction of helicopter stability, control Sudden changes in wind velocity - Iheir effect on and handling characteristics aircraft and means of reducing hazard. X N82-23230 A82-29871 HBLICOPTEB DESJG1 fieviev of aeronautical fatigue investigations in Performance characteristics and employment the Netherlands, Barch 1979 - February 1981 profiles of the neu helicopter BK117 [SLB-flP-81006-U] H82-22153 A82-29586 HASA/HAA Advanced Botorcraft Technology and lilt A giant step toward composite helicopters Botor Horkshop. Volume 7: Tilt Botor Session A82-30294 [NASA-TB-84705] N82-23243 Approach in dynamic qualification of light helicopter stores and equipments N82-22166 H The dynamic qualification of equipment and HI16 GLIDEBS external stores for use with rotary winqed Soaring Society of America, National Convention, aircraft Phoenix, AZ, January 14-18, 1981, Proceedings N82-22167 A82-29414 Naval versions of the Dauphin and the AS 15 TT HAHHOHIC OSCILLAIIOI weapon system helicopters A computer-controlled oscillation mechanism for [SNIAS-821-210-104] N82-22255 unsteady aerodynamics experiments A light helicopter for night firing A82-29018 [SNIAS-821-210-105] N82-22256 HABHOBTCS Concept studies of an advanced composite An investigation of rotor harmonic noise by the helicopter fin use of small scale vind tunnel models [SNIAS-821-210-106] H82-22257 [BASA-CB-166337] 1182-24050 Parametric study of the influence of the engine HABBIBB AIBCBAFT upon th'e operating cost of a civil helicopter Equipment vibration qualification for Barrier and (SNIAS-827-210-102] H82-22273 Hawk aircraft Cockpit integration from a pilot's point of view N82-22161 N82-23224 HEAD-OP DISPLAYS Integrated cockpit for A-129 Definition of display/control reguirements for N82-23225 assault transport night/adverse weather capability Past applications and future potential of variable N82-23217 stability research helicopters HEAT BBSISTA1I 1LLQIS N82-23228 The gas turbine engine NASA/HAA Advanced Botorcraft Technology and Tilt 182-28587 Botor Workshop. Volume 5: Propulsion Session Sheet materials - Fabrication and joining for IHASA-TB-84207] N82-23241 gas turbine engine components NASA/HAA Advanced Botorcraft Technology and Tilt A82-28594 Botor workshop. Volume 6: Vehicle An evaluation study of aluainide and Configuration Session chromoaluminide coatings on IN-100 [NASA-TB-84180] N82-23242 A82-29597 HELICOPTBB EBGIBBS Effect of operating life on the mechanical Analysis of changes in the gas-dynamic parameters properties of the materials and load-bearing of a gas-turbine helicopter engine during capacity of the rotor elements of gas-turbine acceleration engines A82-29872 A82-31643 New processes and methods of technical diagnostics The influence of protective treatment on the and prognostics in the case of the engine mechanical properties of superalloy parts NK-8-4. II 882-22180 A 82-29925 Directional solidification: Project B2 --- of gas Parametric study of the influence of the engine turbine rotor blade alloys upon the operating cost of a civil helicopter [PNB-90088] N82-22279 [SSIAS-827-210-102] N82-22273 Powder metallurgical innovations for improved hot A helicopter handling-qualities study of the section alloys in aero-engine applications effects of engine response characteristics, [PNB-90072] N82-22358" height-control dynamics, and excess power on HEAT TBAISFEB nap-of-the-Earth operations Historical perspectives en thermostructnral N82-23214 research at the NACA Langley Aeronautical HASA/HAA Advanced Botorcraft Technology and Tilt laboratory from 1948 to 1958 Botor Borkshop. Volume 5: Propulsion Session N82-23494 £NASA-Tfl-84207] N82-23241 HELICOPTBB COITBOL HBLICOPTEB PEBPOBHAICE The helicopter Kavstar GPS test program Fighting forest fires - A task for the Swiss air A82-31290 force Helicopter Handling Qualities A82-29578 [NASA-CP-2219] N82-23208 Performance characteristics and employment VIOL and VSTOL handling qualities specifications, . profiles of the new helicopter BK117 an overview of the current status A82-29586 N82-23209 Approach in dynamic qualification of light Boeing 234 flight control development helicopter stores and equipments N82-23211 N82-22166 Flight tests foe the assessment of task Concept studies of an advanced composite performance and control activity helicopter fin N82-23213 [SNIAS-821-210-106] S82-22257

1-23 HBLICOPIEB Till. EOIOBS SUBJECT IIDBI

Influence of maneuverability on helicopter combat HOHBXCOHB SIBOCTOBES effectiveness Bonded aluminum honeycomb - Aircraft flight H82-23212 surface primary structure application Unified results of several analytical and [AIAi 82-0676] A82-30145 experimental studies of helicopter handling Concept studies of an advanced composite qualities in visual terrain flight helicopter fin H82-23215 £SBIAS-821-210-106] H82-22257 New development in flying qualities with HOBIZOBTAL PLIGBT application to rotarj wing aircraft A complete method for computation of blade node H82-23226 characteristics and responses in forward flight A pilot in the loop analysis of helicopter [SBIAS-821-210-101] H82-22254 acceleration/deceleration maneuvers Validation of zero-order feedback strategies for H82-23229 medium range air-to-air interception in a HELJCOPIBB TAIL BOIOBS horizontal plane A complete method for computation of blade node [HASA-TM-84237] H82-23237 characteristics and responses in forward flight HOHIZOHTA1 TAIL SOBPACES [SBIAS-821-210-101] H82-22254 737 graphite-epozy horizontal stabilizer Concept studies of an advanced composite certification helicopter fin (AIAA 82-0745] A82-30109 [SBI4S-821-210-106] 882-22257 HOB! AHTBBHAS Tail rotor studies for satisfactory performance: Besearch and development at HBB. Technical and Strength and dynamic behavior scientific publications, 1981 [SHI4S-821-210~108] 882-22258 B82-23137 BBLICOPTEBS HOT PBESSIBG Turbulence-excited flapping motion of a rotor Bepair and regeneration of turbine blades, vanes blade in hovering flight and discs 182-29042 B82-22185 The employment of helicopters in Austria in HOT SDBPACES connection with large-scale fires in buildings Powder metallurgical innovations for improved hot 482-29585 section alloys in aero-engine applications Dynamic Environmental Qualification Techniques [EHB-90072] B82-22358 conference HOVBBIHG [4GABD-CP-318] U82-22154 Performance testing of a main rotor system for a Maintenance problems in gas turbine components at utility helicopter at 1/4 scale the Boyal Saval Aircraft Yard, Fleetlands --- [HASi-TB-83274] B82-22251 helicopter and marine gas turbines Some aspects of jet dynamics and their B82-22175 implications for VIOL research Conceptual design study of a visual system for a B82-23151 rotorcraft simulator and some advances in Jet effects on forces and moments of a V5TOL platform motion utilization fighter type aircraft £HASA-CB-166322] H82-22244 H82-23168 BADIAK simulator for aircraft instruments HOVEBIB6 STABILITY £FOA-C-40136-A3] H82-22286 Xurbulence-ezcited flapping motion of a rotor HELIMBTS blade in hovering flight Airfield visual aids research at the Boyal A82-29042 Aircraft Establishment An analysis of a nonlinear instability in the [BAE-TH-FS-431] B82-22242 implementation of a VTOL control system HElflET H001IED DISPIAIS [HASA-TH-84220] B82-22281 Definition of display/control requirements for HOHAB BBBA7IOB assault transport night/adverse Heather capability A theory of human error H82-23217 [BASA-CB-166313] 882-22250 HI6B ALTITUDE HOflAH PACfOBS EBGIBEEBIIG Sun sensing guidance system for high altitude Technical approaches for measurement of human errors aircraft [NASA-CB-166314] B82-22249 C SASA-CASB-FBC-11052-1] H82-23231 A theory of human error HIGH SPEED [HASA-CB-166313] B82-22250 NASA/BAA Advanced Botorcraft Technology and Tilt Controls and displays for all-weather operation of Botor Horkshop. Volume 6: Vehicle helicopters Configuration Session [BBB-OD-319-81-0] 882-22260 £SASA-TB-84180] H82-23242 HOflAH PEBPOBHABCB BIGH STBEIGIB ALLOYS Functional requirements for the man-vehicle SPP of high strength aluminum structures systems research facility identifying and superplastic forming for complex aircraft correcting human errors during flight simulation structures [BASA-CB-166315] H82-22248 A82-28997 BOHAB UOLBBABCBS BIGH STBBlGTfl STBBLS Comparing the relationships between noise level comparison of reliability, sensitivity and and annoyance in different surveys - A railway accuracy of some MDI-Techniques noise vs. aircraft and road traffic comparison [HLB-HP-80039-D] H82-23542 A82-29165 HIGH TEBPEBATUBB TESTS BIDBAOL1C COBTBOL High temperature, short term tensile strength of An electronic control for an electrohydranlic C6000/PBB-15 graphite cclyimide active control landing gear for the F-4 aircraft IAIAA 82-0711] A82-30125 [HASA-CB-3552] 882-22252 HXGHBAIS HIDBOC4BBOH COHBOSTIOI Pavement management and rehabilitation of portland HOz foroation in flat, laminar, opposed Jet cement concrete pavements methane diffusion flames [PB82-131384] B82-22392 A82-28660 HIIGES Analysis of a multihinged empennage with allowance for shear strain A82-29834 IMAGE PBOCBSSIBG HISIOHIES Combat training imagery The Boyal Aircraft Establishment: 100 years of A82-31179 research IHPACT D4HA6B [BAE-TB-FS-432] B82-22144 Bird impact analysis package for turbine engine Bistorical perspectives on thermostructural fan blades research at the HACA Langley Aeronautical [AIAA 82-0696] A82-30162 Laboratory from 1948 to 1958 H82-23494

1-24 SUBJECT IHDEI JET TBBOST

IHPACT LOADS Prediction of flyover jet noise spectra from On the dynamic ccllapse of a column impacting a static tests rigid surface H 82-22 963 [AIA4 82-0735] A82-30182 JET EBGIHE FUELS IBPACT BBSISTAICE The combustion of a fuel jet in a stream of lean Commercial jet transport crashvorthiness gaseous fuel-air mixtures [BASA-CB-165849] H82-23207 482-28692 IBBBTIAL 1AVI6AIIOB JET EB6IBES Strapdovm inertial navigation systems: An Encounters vith surge: Some experiences of algorithm for attitude and navigation co»putations development of axial compressors for aero gas [ABL/SIS-BEPT-23] 882-22241 turbines Optimal inertial navigation using terrain [EBB-90071] 882-22274 correlation: An attractive solution to the Alternatives for jet engine control ground attack aircraft navigation problem [BASA-CB-168891] 1182-23247 1182-23184 JET BIHAOST IBFBABBD PBOIOSBAPfll An experimental and theoretical investigation of Fighting forest fires vith the aid of aircraft in the interaction between the engine jet and the the United States of Aaerica surrounding flov field vith regard to the A82-29577 pressure drag on afterbodies IHFBABED BADIATIOH K82-23158 A light helicopter for night firing JET FLAPS [SBIAS-821-210-105] 1182-22256 Aerodynamic noise generated by jet-ving/flap IBJECTOBS * interactions of the external USB configuration Theoretical optimisation and experimental of STOL aircraft. Part 1: Eight percent scale verification of an injector cold-flow model analysis B82-23170 [BAL-TB-685T] H82-22953 ISLET FLOi JEX FLOi The excitation of compressor/duct systems The role of coherent structures in the generation AS 2-28993 of noise for subsonic jets IBLEI BOZZLBS [HASA-CB-166764] B82-22947 Aerodynamic analysis of VTOL inlets and definition Aerodynamic noise generated by jet-ving/flap of a short, bloving-lip inlet interactions of the external USB configuration [HASA-CB-165617] N82-22211 of SIOL aircraft. Part 1: Eight percent scale IHLET PHESSOHB cold-floH model analysis Computer modeling of fan-exit-splitter spacing [B4L-TB-685T] H82-22953 effects on FIDO response to distortion Fluid dynamics of jets vith applications to V/STOL [BASA-CB-167879] 882-23246 [4G4BD-CP-308] H82-23150 IHLET TEHPEBATUBE Some aspects of jet dynamics and their Computer modeling of fan-exit-splitter spacing implications for VTOL research effects on F100 response to distortion B82-23151 [HASA-Cfl-167879] H82-23246 An experimental and theoretical investigation of IBSPBCTIOI the interaction betveen the engine jet and the Utility of a probability-density-function curve surrounding flov field vith regard to the and F-naps In composite-material inspection pressure drag on afterbodies A82-28934 882-23158 A computerized system for the application of Flovfield and noise sources of jet impingement of fracture tracking data to aircraft management flaps and ground surface for the C-5A military airlift transport B82-23163 [AIAA 82-0760] A82-30119 Jet effects on forces and moments of a VSTOL Comparison of reliability, sensitivity and fighter type aircraft accuracy of some BDI-Technigues 1182-23168 [SLB-HP-80C39-UJ 882-23542 Theoretical optimisation and experimental IHSTBOHBH BBBOBS verification of an injector The reliability of height and identity data 882-23170 secondary surveillance radar error analysis Determination of vind tunnel constraint effects by A82-30312 a unified pressure signature method. Part 2: Hagnetic anomalies as a reference for ground-speed Application to jet-in-crossflov and map-matching navigation (HASA-CB-166187] 882-23235 A82-3031U JEI IflPIIGEBBII IBTBBIAIIOIAL COOEEBAIIOB Fluid dynamics of jets vith applications to V/STOL The investigation of aircraft accidents and [46ABD-CP-308] 882-23150 incidents - Some recent national and Flovfield and noise sources of jet impingement of international developments flaps and ground surface 482-29275 882-23163 Collaborative development of aero-engines JEX LIFT [PSB-90083] 882-22277 Evaluation of the effects of model scale and test IHTEBIATIOHAL LAB technique on jet-induced effects The investigation of aircraft accidents and 882-23167 incidents - Some recent national and JET fllXIBG FLOI international developments Numerical study of vibrational relaxation in the . 482-29275 turbulent mixing of jets in a supersonic nozzle IBVEBTED COHVEBIEBS (DC 10 AC) A82-29880 Cascade converter of dc voltage to ac voltage of Fluid dynamics of jets vith applications to V/ST01 higher frequency vith vcltage and frequency [A6ABD-CP-308] 882-23150 stabilization devices aircraft electric Some aspects of jet dynamics and their equipment implications for VTOL research 482-28875 H82-23151 Unsteady ejectors 882-23171 JEI PBOEULSIOI JET AIBCBAFT Thrust augmenting ejectors: A reviev of the Commercial jet transport crashvorthiness application of jet mechanics to V/STOL aircraft [BASA-CB-165849] H82-23207 propulsion JET AIBCBAFT BOISE 882-23169 Program for narrov-band analysis of aircraft JEI XHBDSI flyover noise using ensemble averaging techniques Reliable pover BB211 aircraft engines [H4S4-CB-165867] B82-22949 [PBB-90078] 882-22275 Acoustic emission from free jets supersonic jets Experimental study of a jet deflector B82-22962 882-23173

A-25 JOIH1S (JOBCTIOBS) SUBJECT IHDEI

JOIBTS (JOIC1IOBS) LEAST SQOABES BEIHOD Fatigue behavior of adhesively bonded joints Optimization of measurements in the state A82-29032 estimation of systems using the least squares method A82-29826 K LEGAL LIABILITI KALBAB FILTBBS The investigation of aircraft accidents and Optimal control and estimation foe strapdown incidents - Some recent national and seeker guidance of tactical missiles international developments A82-31121 482-29275 Application of Hainan filtering to the kinematic LIFT reconstruction of free flight of catapulted An accurate method for evaluating the kernel of aircraft models in the laboratory the integral equation relating lift to downwash [IBFL-80-28] H82-22259 in unsteady potential flow KEBBEL FOICTIOBS [BASA-TB-83281] B82-23194 in accurate method for evaluating the kernel of LIFT ADGBBBTATIOB the integral equation relating lift to downwash Aerodynamic characteristics of the external OSB in unsteady potential flow powered lift system using side fences for [NASA-TH-83281 ] B82-23194 enhancement of Coanda flow attachment KEVLAB (TBADEHABK) [BAL-TB-686T] B82-22212 Concept studies of an advanced composite LIFT DEVICES helicopter fin Aerodynamic characteristics of the ezternal OSB [SBIAS-821-210-106] 1182-22257 powered lift system using side fences for Flight service evaluation of Kevlar-19 epozy enhancement of Coanda flow attachment composite panels in wide-bodied commercial [BAL-TH-686T] B82-22212 transport aircraft Aerodynamic noise generated by jet-wing/flap [BASA-CB-165841] H82-22316 interactions of the ezternal DSB configuration of S10L aircraft. Part 1: Eight percent scale cold-flow model analysis [BAL-TB-685T] B82-22953 L-1011 AIBCBAFT LIFT FAHS Advanced technology OFCS control panel for the Evaluation of the effects of model scale and test 1-1011-500 technigue on jet-induced effects [AIAA PAPEB 81-2240] A82-29000 B82-23167 Flight service evaluation of Kevlar-49 epozy LIFTIBG BOTOBS composite panels in Hide-bodied commercial Aerospatiale survey of wind tunnel testing of transport aircraft small and large scale rotors [HASA-CB-165£41] H82-22316 [SBIAS-821-210-107] H82-22225 LABIBAB FLO! LIGHT AIBCBAFI BOz formation in flat, laninar, opposed jet Comparison of light aircraft with strutted and methane diffusion flanes cantilever wings A82-28660 A82-29828 IAHI1AB FLOI AIBFOILS Socata: IB 20 Trinidad given German debut Drag reduction using pneumatic tnrbnlators [BASA-IH-76706] B82-22247 laminar airfoils LIGHT BEAB.S [DFVLB-FB-81-33] H82-22223 Laser gyros - The guiding light LASDIBG AIDS A82-29792 Airfield visual aids research at the Boyal LIGHTBIBG Aircraft Establishment The 1981 direct strike lightning data [BAE-TB-FS-431] B82-22242 utilizing the F-106 aircraft LABDIBG GBAB [BASA-TB-83273] H82-22848 An electronic control for an electrohydraulic LIBB OF SIGHT active control landing gear for the F-4 aircraft Comparison of analytical predictions of [BASA-CB-3552] B82-22252 longitudinal short period pilot-induced Planar equations of rollout motion for an aircraft oscillations with results from a simulation with free or steerable landing gears study of the space shuttle orbiter [BASA-TP-1S84] B82-23244 [SASA-TH-83267] B82-23236 Comparison of reliability, sensitivity and LIBBAB SISTBHS accuracy of some BDI-Techniques Estimation of the performance of noustationary [HLB-BP-80039-U] B82-23542 discontinuous control systems for'flight vehicles LABDIBG IBSIBOBESIS A82-29832 Airfield visual aids research at the Boyal LIQUID SLOSHIBG Aircraft Establishment Aircraft fuel tank slosh and vibration test [BAE-IB-FS-431] B82-22242 B82-22164 LABDIBG LOADS LOAD DISIBIBOTIOI (FOBCES) An electronic control for an electrohydraulic Zone loading of flight-vehicle structures active control landing gear for the F-4 aircraft A82-29838 [HASA-CB-3552] B82-22252 LOADIBG BITE LAP JOIIIS Zone loading of flight-vehicle structures A comparison of properties of single overlap A82-29838 tension joints prepared by ultrasonic welding LOBGITODIBAL STABILITY and other means Comparison of analytical predictions of [AIAA 82-0661] A82-30091 longitudinal short period pilot-induced LASEB GIBOSCOPES oscillations with results from a simulation Laser gyros - The guiding light study of the space shuttle orbiter A82-29792 [BASA-TH-83267] B82-23236 IAIBBAL STABILITY LOSSI HEDIA ACTTA: Investigation of new piloting and flight GTD analysis of airborne antennas radiating in the control technologies. Volume 2: Aircraft with presence of lossy dielectric layers reduced lateral stability [BASA-CB-168770] B82-22398 [HBB-OH-05-81-VOL-2] B82-23253 LOi ASPECT BAUD BUGS LAOBCH fEHICLBS Aerodynamic performance of slender wings with integrated structural analysis and design support separated flows for advanced launch vehicles [BASA-CB-168768] B82-22206 [AIAA 82-0675] A82-30144 Approzimate method for predicting supersonic LEADIBG EDGES normal force coefficient very-low-aspect-ratio Crossflow shock on the suction side of a flat lifting surfaces delta wing with supersonic leading edges [AD-A111770] B82-23199 A82-29659

A-26 SOBJECT IBDEX HBCHABICAL DBITES

LOI COSZ The development of cryogenic wind tunnels and Lou cost aircrew training devices their application to maneuvering aircraft A82-29258 technology LOB PASS FILIEBS H82-22196 Eeal tine digital filtering test in the S1 State of the art and recent perspectives on the continuous wind tunnel at Bodane study of the loss of control and spin H82-22152 H82-22197 LOI SPEED ilBD 10HHBLS Aeroelastic tailoring for control and performance: Jet V/STOL wind-tunnel simulation and groundplane Are requirements compatible? effects S82-22200 H82-23165 Tail configurations for highly manenverable combat LOB TBBUSX aircraft Comment on 'Optimal control via mathematical 882-22201 programming1 The study of combat aircraft maneuverability by 482-31125 air to air combat simulation LUBBICAHIG OILS H82-22205 Basic technology of sgueeze-film dampers for rotor Belicopter Handling Qualities • dynamics control [HASA-CP-2219] B82-23208 [AD-A110842] H82-23250 Influence of maneuverability on helicopter combat LOGS effectiveness Integrity analyses of surface-flawed aircraft B82-23212 attachment lugs - A new, inexpensive, 3-D HABOFACTOBIBG alternating net hod Applications of structural adhesives in production [AIAA 82-0742] A82-301C7 A 82-28808 Development and demonstration of manufacturing processes for fabricating graphite/LABC 160 M polyimide structural elements OACHIBE TOOLS [NASA-CB-165809] N82-22315 Tool use in cutting operations involving integral BAP HATCHIHG GOIDiBCB structural components in aircraft construction Magnetic anomalies as a reference for ground-speed A82-28873 and map-matching navigation MAG1EIIC AHOMALIES A82-30314 Magnetic anomalies as a reference for ground-speed MABIBB CBOPOLSIOI and map-matching navigation Maintenance problems in gas turbine components at A82-30314 the Boyal Haval Aircraft Yard, Fleetlands HAGHE1IC COBTBOL helicopter and marine gas turbines Effects of cable geometry and aircraft attitude on N82-22175 the accuracy of a magnetic leader cable system MASS DISIBIBOTIOB for aircraft guidance during rollout and turnoff An automated technique for improving modal [NASA-TP-1978] H82-22239 test/analysis correlation BAGIBXIC FIELDS [AIAA 82-0640] A82-30137 Transient measurements under electric pulse MATBBIALS BBCOVBBX excitation in 37 Viggen aircraft Critical metals conservation, recycling and [FOjJ-C-30243-43] M82-23409 substitution MAIB1EBABCB [AGABD-B-693] B82-22348 Maintenance in Service of High Temperature Farts MATEBIALS SCIEBCB IAG4BD-CP-317] N82-22172 Bew materials fly better and cheaper Maintenance problems in gas turbine components at A82-31426 the Boyal Naval Aircraft Yard, Fleetlands MATEBIALS TESTS helicopter and marine gas turbines Test methodology for evaluation of fireworthy N82-22175 aircraft seat cushions Eepair and regeneration of turbine blades, vanes A82-29596 and discs MATHEMATICAL MODELS N82-22185 Investigation of the aerodynamic-contour method Pavement management and rehabilitation of Portland with control functions in the form of smooth cement concrete pavements constant-sign contours [PB82-131384] U82-22392 A82-29831 HAI HACHlBB SISTEHS Theoretical optimisation and experimental Flight simulators verification of an injector A82-29924 B82-23170 Functional requirements for the man-vehicle A theoretical study of the impact of aircraft wake systems research facility identifying and vortices on roofs in the final approach area of correcting human errors during flight simulation Dusseldorf airport [BASA-CB-166315] B82-22248 [DFVLB-MITT-82-01] N82-23560 Technical approaches for measurement of human errors MATHEMATICAL PROGBAMMISG [BASA-CB-166314] H82-22249 Comment on 'Optimal control via mathematical HABAGEBESX HBTHODS programming* A system safety model for developmental aircraft A82-31125 programs MATBIX HEIHODS [NASA-CB-3534] B82-22228 Component coupling with time-invariant mass matrix HAHAGEflEST SISTEHS for nonisotropic rotating and nonrotating systems Air Traffic Flow Management and Air Traffic Flow [AI44 82-0731] A82-30179 Control HEASOBB ABD IBTEGBATIOS A82-29923 Optimization of measurements in the state HAIEOVBBABILITI estimation of systems using the least sguares Combat Aircraft Manoeuvrability method [AGABD-CP-319] B82-22187 A82-29826 A review of recent AGABD Symposia on the Angle of BEASDBIBG IBSTBOHEBIS Maneuverability of Combat Aircraft A portable, low-cost flight-data measurement and H82-22188 recording system Beview of practical experience on combat aircraft [BASA-TM-84229] B82-22478 maneuverability MBCHABICAL DBITES H82-22189 Aviation gear drives and reducers: Handbook in Experimental flight test programs for improving Bussian combat aircraft maneuverability by maneuver A82-30675 flaps and pylon split flaps Advanced general aviation comparative H82-22192 engine/air frame integration study [BASA-CB-165564] B82-22263

A-27 HBCHAHICAL PBOPBBTIBS SUBJECT ISDEX

BBCHABICAL PBOPBBTIBS Controls and displays for all-weather operation of Composite materials -— with emphasis for aircraft helicopters gas turbine farts [BBB-OD-319-81-0] H82-22260 182-28590 The integration of multiple avionic sensors and processing and ases of carbon fibre reinforced technologies for future military helicopters plastics Book H82-23186 A82-28643 VIOL and VSTOL handling gualities specifications, Effects of noisture on the mechanical properties an overview of the current status of glass/epoxy composites H82-23209 A82-29036 Civil (French/DS) certification of the Coast A review of D.S. Air Force research related to Guard's HH-65A Dauphin airframe and engine aaterials H82-23210 A82-29268 Influence of maneuverability on helicopter combat Mechanical properties of a fiberglass prepreg effectiveness system at crjogenic and other temperatures H82-23212 [AIAA 82-0708] A82-30099 Definition of display/control requirements for Environmental and high strain rate effects on assault transport night/adverse weather capability composites for engine applications H82-23217 [AIAA 82-0758] A82-30118 Some piloting experiences with multifunction Effect of operating life on the mechanical isometric side-arm controllers in a helicopter properties of the materials and load-bearing S82-23218 capacity of the rotor elements of gas-turbine Besults of HASA/FAA ground and flight simulation engines experiments concerning helicopter IFB A82-31643 airworthiness criteria The influence of protective treatment on the H82-23219 mechanical properties of superalloy parts. State-of-the-art cockpit design for the HH-r65A N82-22180 helicopters HEZAL COTUHG N82-23220 Tool use in cutting operations involving integral Performance evaluation of a kinesthetic-tactnal structural components in aircraft construction display A82-28873 H82-23221 HBTAL tATIGOE Synthesis of an integrated cockpit management system Occurrence of fretting fatigue failures in practice H82-23222 A82-28543 The role of voice technology in advanced Some case studies and the significance of fatigue helicopter cockpits thresholds aircraft components H82-23223 [HLB-HP-81015-D] H82-23561 Cockpit integration from a pilot's point of view HETAL JOIBIS N82-23224 Sheet materials - Fabrication and joining -— for HILITABI fSCHHOlOGI gas turbine engine components V/STOL aircraft and fluid dynamic A82-28594 H82-23179 HETAL PLATES HISSILB BODIES GTD analysis of airborne antennas radiating in the Besearch and development at HBB. Technical and presence of lossy dielectric layers scientific publications, 1981 [HASA-CB-168770] 882-22398 H82-23137 HETAL SHEETS HISSILB C08TBOL Sheet materials - Fabrication and joining for Optimal control and estimation for strapdown gas turbine engine components seeker guidance of tactical missiles A 82-28 591 A82-31121 HETA1 BOBKIBG HISSILE DESIGH SPF of high strength aluminum structures Approximate method for predicting supersonic snperplastic forming for complex aircraft normal force coefficient very-lov-aspect-ratio structures lifting surfaces A82-28997 [AD-A111770] H82-23199 HETAL-METAL BOHDISC HISSILE SISIEHS Structural integrity of an adhesively bonded Naval versions of the Dauphin and the AS 15 TT aircraft fuselage weapon system helicopters A82-28996 [SHIAS-821-210-104] H82-22255 HETAIS HZIIHG LEHGTH FLOS TBEOBZ Critical metals conservation, recycling and Thrust augmenting ejectors: A review of the substitution application of jet mechanics to V/STOL aircraft [AGABD-B-693] B82-22348 propulsion HETEGEOLOGICAL IHSIBOflBRS H82-23169 Instruments and installations for meteorological Unsteady ejectors measurements at airports Russian book H82-23171 A82-28826 Improvement of ejector thrust augmentation by HETBABB pulsating or flapping jets HOz formation in flat, laminar, opposed jet H82-23172 methane diffusion flames HODAL BESCOISE A82-28660 A complete method for computation of blade mode BICBOPBOCESSOBS characteristics and responses in forward flight The micro revelation comes to civil air transport [SSIAS-821-210-101] H82-22254 A82-29259 HOISIOBE COSIEST BILITABI AIBCBAFI Effects of moisture on the mechanical properties A computerized system for the application of of glass/epoxy composites fracture tracking data to aircraft management A82-29036 for the C-5A military airlift transport HOLECOLAB BELAX1TIOI [AIAA 82-0760] A82-30119 Huaerical study of vibrational relaxation in the Durability and damage tolerance control plans for turbulent mixing of jets in a supersonic nozzle USAF aircraft A82-29880 [AIAA 82-0679] A82-30147 HOZOB VEHICLES HillTAB! HELICOPIEBS Calculation of the contributions of air traffic The structural dynamic interface required for and road traffic to air pollution in the region developing helicopter target acquisition systems of Schiphol airport in 1974 H82-22165 [HL8-TB-77100-0] H82-22808 Naval versions of the Dauphin and the AS 15 TT HBCA AIBCBAFT weapon system helicopters Qualification of eguipment for gunfire induced [SMIAS-821-210-104] H82-22255 vibration H82-22158

A-28 SUBJECT IHDBI BOHBBICAL COBTBOL

BOISE BBASDBBBBBX The role of coherent structures in the generation N of noise for subsonic jets HACBLLES [HASA-CB-168764] H82-22947 Effect of nacelles on aerodynamic characteristics Program for narrow-band analysis of aircraft of an executive-jet model with simulated, flyover noise using ensemble averaging techniques partial-chord, laoinar-flow-control wing glove [HASA-CB-165867] 882-22949 [HASA-TB-83271] H82-22217 Recommendations for field measurements of aircraft BB211 powerplant deterioration: Beview of current noise situation and lessons learned [HASA-CB-3540] H82-22955 tPHB-90073] H82-22270 An investigation of rotor harmonic noise by the Development of a correlated finite elenent dynamic use of small scale wind tunnel models nodel of a complete aeic engine [HASA-CB-166337] H82-24050 [PHfl-90081] H82-22272 BOISE PBEDICTIOB (AIBCBAFT) Automated design of minimum drag light aircraft STOL aircraft structural vibration prediction from fuselages and nacelles acoustic excitation £HASA-CB-168913] H82-23238 H82-22169 Development of a convoluted intake seal for nodel Analytical prediction of the interior noise for B66 v/stol nind tunnel cylindrical models of aircraft fuselages for £BAE-ABG-163] S82-23255 prescribed exterior noise fields. Phase 2: •AP-OF-THB-EABTH BAVIGAIIOB Bodels for sidewall trim, stiffened structures Helicopter Handling Qualities and cabin acoustics with floor partition [HASA-CP-2219] 882-23208 [HASA-CB-165869] H82-22952 Flight tests for the assessment of task Prediction of flyover jet noise spectra from performance and contrcl activity static tests H82-23213 H82-22963 A helicopter handling-qualities study of the BOISE EBOPAGAIIOH effects of engine response characteristics, Experiments on propeller noise height-control dynamics, and excess pover on H82-22978 nap-of-the-£arth operations BOISB SPECTBA H82-23214 The role of coherent structures in the generation Deified results of several analytical and of noise for subsonic jets experimental studies of helicopter handling £ HASA-CB-16876*] H82-22947 gualities in visual terrain flight Program for narrow-band analysis of aircraft H82-23215 flyover noise using ensemble averaging techniques An assessment of various side-stick [NASA-CB-165867] H82-22949 controller/stability and control augmentation Prediction of flyover jet noise spectra from systems for night nap-of-Earth flight using static tests piloted simulation H82-22963 H82-23216 HOISB TOLEBABCE HASA PBOGBABS Comparing the relationships between noise level The 1983 HASA Authorization, Volume 1 and annoyance in different surveys - A railway [GPO-91-488-VCL-1] H82-23068 noise vs. aircraft and road traffic comparison HAVIGAIIOI A82-29165 Analysis of computing system configurations for BOHDESTBOCTIVE TESTS highly integrated guidance and control systems Utility of a probability-density-function curve N82-23189 and F-maps in composite-material inspection BAVIGATIOB IHSTBOflBHTS A82-28934 Magnetic anomalies as a reference for ground-speed On the characterization of damages in and map-matching navigation graphite-epoxy composites A82-30314 [AIAA 82-0757] A82-30117 HAVSXAB SATELLITES Comparison of reliability, sensitivity and The helicopter Navstar GPS test program accuracy of some HDI-Techniques A82-31290 INLB-HP-80039-0] H82-23542 •ATI HOBLIBEAB SISTEHS Sea-based remotely piloted vehicles. I - Issues Flutter analysis using nonlinear aerodynamic forces and concepts £AIAA 82-0728] A82-30176 A82-29714 Application of the theory of bifurcations to the HICKE1 ALLOTS study of the loss of control in combat aircraft The gas turbine engine H82-22198 A82-28587 An analysis of a nonlinear instability in the An evaluation study of aluninide and implementation of a VTOL control system chromoalnminide coatings on IN-100 [NASA-TH-84220] H82-22281 A82-29597 BOZZLB FlOi Directional solidification: Project B2 of gas Application of computer generated color graphic turbine rotor blade alloys techniques to the processing and display of [PHB-90088] N82-22279 three dimensional fluid dynamic data for. HIGH! PLIGHTS (AIBCBAFT) turbofan mixer nozzle mixing process analysis A light helicopter for night firing A82-29008 [SHIAS-821-210-105] H82-22256 Some aspects of jet dynamics and their Helicopter Handling Qualities implications for VTOL research [HASA-CP-2219] H82-23208 H82-23151 An assessment of various side-stick HOZZLE GEOBBIBI controller/stability and control augmentation Aerodynamic analysis of VTOL inlets and definition systems for night nap-of-Earth flight using of a short, blowing-lip inlet piloted simulation [NASA-CB-165617] H82-22211 N82-23216 Experimental study of a jet deflector BIGHT VISIOH H82-23173 Definition of display/control requirements for HOZZLB TBBOST COBFFICIEBIS assault transport night/adverse Heather capability iind-tnnnel investigation of the powered low-speed H82-23217 longitudinal aerodynamics of the HITBOGB1 OXIDES Vectored-Engine-Over (VEO) wing fighter The effect of swirl burner aerodynamics on HOx configurat ion formation IHASA-TH-83263] H82-22207 A82-28658 BOBEBICAL COBIBOL HOx formation in flat, laminar, opposed jet A computer-controlled oscillation mechanism for methane diffusion flames unsteady aerodynamics experiments A82-28660 A82-29018

A-29 HOSBBICAL FLO! ?ISUALIZ1TIOB SUBJECT IIDEZ

Test demonstration of digital control of PABACBDTB DESCEHT •ing/store flatter The stressed state of a parachute canopy during [AIAA 82-0645] £82-30141 opening •DHBBICAL FLOB VISOALIZATIOB A82-29820 Application of computer generated color graphic PABABBTEB IDBBTIFICATIOI techniques to the processing and display of Analytical prediction of the interior noise for three dimensional fluid dynamic data for cylindrical models of aircraft fuselages for turbofan mixer nozzle ailing process analysis prescribed exterior noise fields. Phase 2: A82-29008 Bodels for sidewall trim, stiffened structures HUHBBICAL IHTEGEAIJOB and cabin acoustics with floor partition A Schwarz-Christoffel method for generating [HASA-CB-165869] B82-22952 internal flow grids Analysis and Bonte Carlo simulation of A82-29005 near-terminal aircraft flight paths [HASA-TP-1997] H82-23233 PA?EBEHTS Pavement management and rehabilitation of Portland OBSTACLE A¥OIDAHCB cement concrete pavements Integrated navigation-TJ/TA-system rased on stored [PB82-131384] H82-22392 terrain data processing PEBFOBHABCE PBEDICTIOB H82-23183 Prediction of aerodynamically induced vibrations OB-LI BE SISTBBS in turboaachinery blading Evaluation of four subcritical response methods A82-28986 for on-line prediction flutter onset in Estimation of the performance of nonstationary wind-tunnel tests conducted in the Langley discontinuous control systems for flight vehicles Transonic Dynamics Tunnel A82-29832 [BASA-Tfl-83278] H82-23240 PEBFOBHABCB TESTS OPEBATOBS (PEBSCBBBL) Tail rotor studies for satisfactory performance: A theory of human error Strength and dynamic behavior [HASA-CB-166313] H82-22250 [SMIAS-821-210-108] B82-22258 OPTICAL GIBOSCOPES Production Verification Testing (PVT) of guidance Laser gyros - The guiding light . and control systems for high reliability A82-29792 H82-23187 OPTIBAL COSTBOL PILOT EBBOB Determination of an optimal control program for an Functional reguirements for the man-vehicle aircraft power plant during cliob systems research facility identifying and A82-29845 correcting human errors during flight simulation Application of optimal control techniques to [HASA-CB-166315] H82-22248 aircraft flutter suppression and load alleviation A theory of human error [AIAA 82-0724] A82-30173 [BASA-CB-166313] H82-22250 Optimal control and estimation for strapdovn PILOT PEBFOBflABCE seeker guidance of tactical missiles Enhanced piloting control through cockpit A82-31121 facilities and A.C.T. Multivariable closed loop control analysis and H82-22195 synthesis for complex flight systems Technical approaches for measurement of human errors H82-22193 [HASA-CB-166314] H82-22249 OFTIHIZATIOB Flight tests for the assessment of task Optimization of. measurements in the state performance and control activity estimation of systems using the least sguares H82-23213. method PILOT IBAIHIBG A82-29826 Evaluation of aircraft in simulated combat: Design principles of a computer-aided design system Computer against computer or computer against A82-29829 human pilot Shape optimization of fiber reinforced composites B82-22202 [AIAA 82-0719] A82-30169 PISTOH BBS!BBS A linear decomposition method for large Advanced general aviation comparative optimization problems. Blueprint for development engine/airframe integration study [HASA-TH-83248] H82-22245 [HASA-CB-165564] B82-22263 OSCILLATIBG FLO! FITCHIBG HOHBBTS The relaxation oscillation in ramjet combustion A two-degree-of-freedom flatter mount system with A82-28738 low damping for testing rigid wings at different OSCILLAIIOHS angles of attack Comparison of analytical predictions of [HASA-TH-83302] B82-23549 longitudinal short period pilot-induced PLASTIC AIBCBAFT STBOCTDBES oscillations with results from a simulation Addition polyimide adhesives containing various study of the space shuttle orbiter end groups [HASA-TH-83267] 1182-23236 A82-29098 OZOIOHETBI On the characterization of damages in Aircraft cabin air ozone contamination and graphite-epoxy composites compliance with regulations [AIAA 82-0757] A82-30117 A82-31057 A giant step toward composite helicopters A82-30294 FBBOBATIC BQOIPHBBT Drag reduction using pneumatic turbnlators PABEL HBTBOD (FLUID DIBAHICS) laminar airfoils Subsonic aerodynamic and flutter characteristics [DFVLB-IB-81-33] H82-22223 of several wings calculated by the SOOSSA P1.1 POLICIES panel method Developnental possibilities and restrictions in [AIAA PAPEB 82-0727] A82-30193 air transpprt PABELS [DFVLB-HITT-81-9] N82-22229 Flight service evaluation of Kevlar-49 epoxy POLLOTIOB HOBITOBIHG composite panels in vide-bodied commercial Aircraft cabin air ozone contamination and transport aircraft compliance with regulations [HASA-CB-165841] H82-22316 A82-31057 PABABOLIC BODIES POLIIHIDE BESIBS Helicopter rotor performance improvement by Addition polyiaide adhesives containing various utilization of swept-back parabolic blade tip end groups -:— nind tunnel tests A82-29098 B82-22151

i-30 SUBJECT IHDBI QOALIPICATIOBS

POLTBBB BATBIX COMPOSITES PBBSSOBB POISES Damping and stiffness of aligned discontinuous The excitation of compressor/duct systems fiber reinforced polymer composites A82-28993 EAIAA 82-0712] A82-30102 PBBSSOBB BATIO POSIIIOB BBBOBS performance of single-stage axial-floH transonic The reliability of height and identity data compressor Kith rotor and stator aspect ratios secondary surveillance radar error analysis of 1.63 and 1.77, respectively, and Kith design A82-30312 pressure ratio of 2.05 POTBHTIil FLOi [HASA-TP-2001] N82-22269 Application of a transonic potential flow code to PBOBABILITI DEBSIXI FOICTIOIS the static aeroelastic analysis of Utility of a probability-density-function curve three-dimensional Kings and F-maps in composite-material inspection £AIAA 82-0689] A82-30156 A82-28934 Subsonic aerodynaaic and flatter characteristics PBOBLBfl SOIVIBG of several Kings calculated by the SOOSSA P'1.1 A complete method for computation of blade mode panel method characteristics and responses in forward flight [AIAA PAPEE 82-0727] A82-30193 [SBIAS-821-210-101] 882-2225* Application of a transonic potential floK code to PBODOCI DBVBLOCHBI! the static aeroelastic analysis of Collaborative development of aero-engines three-dimensional Kings [PNB-90083] H82-22277 [HASA-TB-83296] H82-23193 PHODOCTIOH EHGIHEEBIIG An accurate method for evaluating the kernel of Applications of structural adhesives in production the integral equation relating lift to downwash A82-28808 in unsteady potential flow Directional solidification: Project B2 of gas EHASA-Tfl-83281] N82-23194 turbine rotor blade alloys POiDEB BBTALIUB6T [PNB-90088] H82-22279 Development of low-cost titanium structures using PBOGMOSIS blended elemental powder metallurgy Developmental possibilities and restrictions in A82-28998 air transport, Ponder metallurgical innovations for improved hot [DFV1B-BI1T-81-9] »82-22229 section alloys in aero-engine applications Developmental possibilities in civil aviation in CPHE-90072] H82-22358 the Federal Bepublic of Germany POiBB EFPICIEICI H82-22230 Analysis of changes in the gas-dynamic parameters PROJECT BAIAGBBEiT of a gas-turbine helicopter engine during A system safety model for developmental aircraft acceleration programs A82-29872 £NASA-CB-3534] 1182-22228 POBBHBD BODBLS PBOPEI1AHT EXPLOSIOIS Development of a convoluted intake seal for model Gunfire blast pressure predictions B66 v/stol Kind tunnel H82-22170 £BAE-AB6-163] U82-23255 PBOPB11BB BLADES PBEDICTIGI A1ALISIS XECHIIQDBS A flight investigation of blade-section Sen processes and methods of technical diagnostics aerodynamics for a helicopter main rotor having and prognostics in the case of tie engine BC-SC2 airfoil sections HK-8-it. II [NASA-TB-83298] H82-23192 A82-29925 PBOPEILBB DEI7E Gunfire blast pressure predictions Ground reflection effects in measuring propeller H82-22170 aircraft flyover noise Predictions of aerodynamic characteristics of [DFVLB-FB-81-28] H82-22990 highly maneuverable configurations PBOPELLBB PAHS H82-22199 Fuel efficient and Bach 0.8, too PBEDICTIOHS A82-29774 Evaluation of four subcritical response methods New processes and methods of technical diagnostics for on-line prediction flutter onset in and prognostics in the case of the engine Kind-tunnel tests conducted in the Langley HK-8-4. II Transonic Dynamics Tunnel A82-29925 £HASA-Tfl-83278] H82-23240 PBOPBLLEBS PBEPBEGS Experiments on propeller noise Bechanical properties of a fiberglass prepreg H82-22978 system at cryogenic and other temperatures PBOPHIOCBPTIOH £AIAA 82-0708] A82-30099 A tactual display aid for primary flight training PBESSDBE DISTBIBOIIOB £HASA-CB-166242] 1182-22238 Subsonic aerodynamic and flutter characteristics PBOPD1SIOH of several Kings calculated by the SODSSA P1.1 Jet V/STOL Wind-tunnel simulation and groundplane panel method effects [AIAA PAPEB 82-0727] A82-30193 1182-23165 A flight investigation of blade-section PBOPOLSIOH SISTBB COIFIGOBATIOHS aerodynamics for a helicopter main rotor having The role of modern control theory in the design of BC-SC2 airfoil sections controls for aircraft turbine engines £HASA-Tfl-83298] H82-23192 EHASA-TB-82815] H82-22262 PBBSSOBB DBAS PBOPOLSIOB SISTBB PBBFOBBAHCE An experimental and theoretical investigation of NASA/HAA Advanced Botorcraft Technology and Tilt the interaction between the engine jet and the Botor Borkshop. Volume 5: Propulsion Session surrounding floK field Kith regard to the [HASA-TB-84207] H82-23241 pressure drag on afterbodies PBOTECTIVE COATIBGS H82-23158 An evaluation study of aluminide and PBBSSOBB GBADIEHTS chromoaluminide coatings on IN-100 Static and unsteady pressure measurements on a 50 A82-29597 degree clipped delta King at B = 0.9 The influence of protective treatment on the conducted in the Langley Transonic Dynamics Tunnel mechanical properties of snperalloy parts £HASA-Tfl-83297] N82-23195 H82-22180 PBBSSOBE HBASDBEBBB5 Pressure measurements on twin vertical tails in buffeting flow Q [AIAA 82-0641] A82-30138 QDALIFICATIOBS Static and unsteady pressore measurements on a 50 Development and use of dynamic qualification degree clipped delta King at H = 0.9 standards for Air Force stores [AIAA 82-0686] A82-30153 B82-22155

A-31 QOUIZI COBTBOL SOBJECT IBDEX

QUALITY. COBTBOL Performance characteristics and employment Development of a taped random vibration technique profiles of the new helicopter BK117 for acceptance testing 482-29586 H82-22171 Naval versions of the Dauphin and the AS 15 TT weapon system — helicopters [SHIAS-821-210-104] B82-22255 BESBABCB ABO DBVBLOPBBBT BADAA ABTBHHAS A review of U.S. Air Force research related to Distributed airborne array concepts airframe and engine materials 482-31669 A82-29268 BADAB BE1COIS The Boyal Aircraft Establishment: 100 years of Secondary radar for airborne collision avoidance research 482-30313 [BAE-TB-FS-432] H82-22144 BADAB DETBCTIOB Besearch and development at MBB. Technical and Distributed airborne array concepts scientific publications, 1981 482-31669 B82-23137 B4DI4TIOB DBTBCTOBS BESBABCH FACILITIES BADIAK siDulator f.or aircraft instruaents Functional requirements for the man-vehicle [F04-C-40136-43] B82-22286 systems research facility identifying and B4DIO HAVIGA3IOB correcting human errors daring flight simulation The helicopter Havstar GPS test program [BASA-CB-166315] H82-22248 482-31290 BESIDOAL STBBSS BAIL TBABSPOBI4IIOH A multidimensional-crack-growth prediction Comparing the relationships between noise level methodology for flaws originating at fastener and annoyance in different surveys - A railway holes noise vs. aircraft and road traffic comparison A82-28932 A82-29165 BESIB BOIDIBG BABJBT EBGIBBS Addition polyimide adhesives containing various The relaxation oscillation in ramjet combustion end groups 482-28738 A82-29098 BBAL TIHE OPEB41IOH BBSIB BAIBII COHJOSITES Beal time digital filtering test in the 51 Tailor-made structures; today, and tomorrow: Hew continuous wind tunnel at Bodane materials, an exploratory investigation into H82-22152 their potential use in aircraft BEATTACBED FLOB [BAE-SDH-85/A/104/005] H82-22253 Experimental study of a jet deflector BETIBBBEBI FOB C4DSB H82-23173 Engine component retirement for cause RECOBDIBG IBSIBUBBBIS H82-22177 A portable, low-cost flight-data measurement and BEVBBBEBAIIOB recording system Acoustic noise test as part of the dynamic [HASA-TH-84229] H82-22478 qualification program in aerospace BBCTABSOLAB BIBGS 1182-22162 Analysis of shells of straight-wing type BIGID SIBOCTOBBS 482-29841 An automated technique for improving modal BECICLIBG test/analysis correlation Critical metals conservation, recycling and CAIAA 82-0640] A82-30137 substitution Bigid body-structural mode coupling on a forward [AGABD-B-693] H82-22348 swept wing aircraft BEFLBCTED BATES [AIAA 82-0683] A82-30150 Ground reflection effects in measuring propeller On the dynamic collapse of a column impacting a aircraft flyover noise rigid surface [DFVLB-PB-81-28] H82-22990 [AIAA 82-0735] A82-30182 BEFBACTOBI BAXBBIALS BIGID iIHGS Maintenance in Service of High Temperature Parts A two-degree-of-freedom flutter mount system with [AGABD-CP-317] H82-22172 low damping for testing rigid wings at different Military maintenance policies and procedures for angles of attack high-temperature parts. Bill they be adequate? [BASA-TB-83302] H82-23549 H82-22173 BODS BBGEHEBATIOi (EH6IBEBBIBG) Shape optimization of fiber reinforced composites Repair and regeneration of turbine blades, vanes (AIAA 82-0719] A82-30169 and discs BOLL H82-22165 Planar equations of rollout motion for an aircraft BES01ATIOBS vith free or steerable landing gears Traffic intrastrncture: Can planning still be [BASA-TP-1984] H82-23244 carried through BOOFS H82-22232 A theoretical study of the impact of aircraft wake BBLIABILIIX AIA1ISIS vortices on roofs in the final approach area of The reliability of height and identity data Dusseldorf airport secondary surveillance radar error analysis [DFV1B-BITT-82-01] B82-23560 A82-30312 BOTABI STABILITY Production Verification Testing (PVT) of guidance Stability and self-oscillations of coaxial rotors and control systems for high reliability A82-31603 H82-23187 BOSABI BIBS AIBCBAFI BBBOTB SEBSOBS Beview of rotorcraft accidents 1977-1979 Improvements to secondary radar for air traffic [PB82-115601] H82-22237 control Hew development in flying qualities with A82-30311 application to rotary wing aircraft Magnetic anomalies as a reference for ground-speed B82-23226 and map-matching navigation Past applications and future potential of variable A82-30314 stability research helicopters BBBOTBLI PILOTED VEHICLES H82-23228 Sea-based remotely piloted vehicles. I - Issues Applications of system identification methods to and concepts the prediction of helicopter stability, control A82-29714 and handling characteristics BESC OB OPEBATIOiS H82-23230 The eaployoent of helicopters in Austria in HASA/HAA Advanced Botorcraft Technology and Tilt connection with large-scale fires in buildings Botor Borkshop. volume 6: Vehicle 482-29585 Configuration Session IHASA-TB-84180] H82-23242

A-32 SUBJECT IHDEX SHOBT TAKEOFF AIBCBAPT

BOTABI BUGS SATELLITE HAVIG1IIOI SXSIEBS Turbulence-excited flapping notion of a rotor The helicopter Havstar GPS test program blade in hovering flight A82-31290 A82-29042 SCALE HODBLS Component coupling vith tine-invariant mass matrix Aerospatiale survey of wind tunnel testing of for nonisotropic rotating and nonrotating systems small and large scale rotors [AIAA 82-0731] A82-30179 [SHIAS-821-210-107] H82-22225 La fiecherche Aerospatiale, bi-nonthly Bulletin Design of dynamically-scaled, asymmetrical wind nanber 1981-5, Septeaber - October 1981 tunnel models aerospace B and D methodology and instrumentation [HIAST-78/18] H82-22285 [ESA-TT-725] H82-22145 SCALIHG LABS Helicopter rotor perfprnance improvement by Prediction of flyover jet noise spectra from utilization of svept-back parabolic blade tip static tests . —- vind tunnel tests H 82-22 963 H82-22151 SCHBABZ-CBBISTOFFBL TBABSFOEBATIOB Performance testing of a main rotor system for a A Schwarz-Christoffel sethod for generating utility helicopter at 1/4 scale internal flow grids [HASA-TH-83274] H82-22251 A82-29005 A flight investigation of blade-section SEALS (STOPPBBS) aerodynamics for a helicopter main rotor having Chem-Braze abradable seal practical BC-SC2 airfoil sections A82-31048 [HASA-TM-83298] H82-23192 Development of a convoluted intake seal for model Unified results of several analytical and B66 v/stol wind tunnel experimental studies of helicopter handling IBAB-ABG-163] B82-23255 qualities in visual terrain flight SEATS 1182-23215 Test methodology for evaluation of fireworthy NASA/HAA Advanced Botorcraft Technology and lilt aircraft seat cushions Botor lorkshop. Volume 6: Vehicle 182-29596 Configuration Session SECOBDABI BADAB [HASA-TH-84180] H82-23242 Improvements to secondary radar for air traffic An investigation of rotor harmonic noise by the control use of small scale Hind tunnel models A82-30311 [HASA-CB-166337] H82-24050 The reliability of height and identity data — BOTATIBG DISKS secondary surveillance radar error analysis Defects and their effect on the behavior of gas A82-30312 turbine discs Secondary radar for airborne collision avoidance M82-22178 A82-30313 BOIOB AEBODYHAHICS SELF OSCILLAIIOH Analysis of rotary balance data for tie F-15 Stability and self-oscillations of coaxial rotors airplane including the effect of conformal fuel A82-31603 tanks SEBVICE LIFE CHASA-CB-3479] H82-22213 The contribution of thermal barrier coatings to Performance testing of a main rotor system for a improvements in the life and performance of gas utility helicopter at 1/4 scale turbine components [HASA-TH-83274] H82-22251 [PBB-90076] B82-22271 Prototype flywheel spin testing program Service life investigation of a sailplane wing of [OCBL-15381] H82-22499 CFBP constrnction BOIOB BLADES (TOBBOHACBIHEBI) H82-22324 Performance of single-stage axial-flow transonic SBBVOCOBTBOL compressor vith rotor and stator aspect ratios An electronic control for an electrohydraulic of 1.63 and 1.77, respectively, and with design active control landing gear for the F-4 aircraft pressure ratio of 2.05 [HASA-CB-3552] H82-22252 [NASA-TP-2001] H82-22269 An analysis of a nonlinear instability in the BOXOBS implementation of a VTOL control system Measurement of aerodynamic work during fan flutter CNASA-TH-84220] H82-22281 A82-28987 SHAPE COBTBOL Stability and self-oscillations of coaxial rotors Investigation of the aerodynamic-contour method A82-31603 with control functions in the form of smooth Effect of operating life on the mechanical constant-sign contours properties of the materials and load-bearing A82-29831 capacity of the rotor elements of gas-turbine SHEAS SIBAIB engines Analysis of a multibinged empennage with allowance A82-31643 for shear strain Basic technology of squeeze-film dampers for rotor A82-29834 dynamics control SHELL STABILITY [AD-A110842] B82-23250 Thermal stability analysis for conical shells with BOBBAXS variable parameters Measures to increase airfield capacity by changing A82-29844 aircraft runway occupancy characteristics SHELLS (STBOCTDBAL FOBBS) [HASA-CB-168841] H82-22240 Analysis of shells of straight-wing type Pavement management and rehabilitation of portland A82-29841 cement concrete paveaents SHOCK BAVE PBOPAGATIOi [PB82-131384] H82-22392 Crossflow shock on the suction side of a flat delta wing with supersonic leading edges A82-29659 SHOCK BAVES SAAB 37 AIBCBAFI The relaxation oscillation in ramjet combustion Transient measurements under electric pulse 182-28738 excitation in 37 Viggen aircraft Investigation of passive shock wave-boundary layer [FOA-C-30243-A3] H82-23409 control for transonic airfoil drag reduction SAFETY DEVICES [HASA-CB-168844] N82-22209 Sudden changes in wind velocity - Their effect on SHOBT TAKEOFF AIBCBAFT aircraft and means of reducing hazard. I STOL aircraft structural vibration prediction from A82-29871 acoustic excitation SAILIII6S H82-22169 Service life investigation of a sailplane wing of CFBP construction H82-22324

A-33 SIG1AL PBOCBSSIHG SUBJECT IIDBI

Aerodynamic noise generated by jet-wing/flap SPECIBAL BABDS interactions of the external USB configuration Program for narrow-band analysis of aircraft of STOL aircraft. Part 1: Eight percent scale flyover noise using ensemble averaging techniques cold-flow aodel analysis [HASA-CB-165867] H82-22949 [HAL-TB-685T] H82-229S3 SPIB TESTS SIGBAL PiOCESSIHG Prototype flywheel spin testing program Distributed airborne array concepts [DCBL-15381] H82-22U99 £82-31669 SPLIT FLIPS La fiecherche Aerospatiale, -bi-monthly Bulletin Experimental flight test programs for improving number 1981-5, Septenber - October 1981 — combat aircraft maneuverability by maneuver aerospace B and t methodology and instrumentation flaps and pylon split flaps [ESA-TT-725] H82-22145 H82-22192 SI6H4L TO IOISB BATIOS SP01LBBS Distributed airborne array concepts Analysis and flight evaluation of a small, A82-31669 fixed-wing aircraft equipped with hinged plate SKIH (STBOCTUBAL BBHBIB) spoilers Design considerations and experiences in the use [HASA-CB-166247] H82-22243 of composite material for an aeroelastic The 737 graphite composite flight spoiler flight research King service evaluation [AIAA 82-0678] A82-30146 [HASA-CB-165826] B82-22314 SOABJIG SPOT 1ELDS Soaring Society of America, Hational Convention, Production weldbonding on the A-10 aircraft Phoenix, AZ, January 14-18, 1981, Proceedings A82-28995 A82-29414 A comparison of properties of single overlap SOLAB SE1SOBS tension joints prepared by ultrasonic welding Sun sensing guidance system for high altitude and other means aircraft [AIAA 82-0661] A82-30091 [HASA-CASE-FBC-11052-1] H82-23231 SQUEEZE FILBS SOOT Basic technology of sgueeze-film dampers for rotor Investigation of soot and carbon formation In dynamics control small gas turbine corniestors [AD-A110842] H82-23250 [HASA-CB-167853] H82-22267 STABILITY AOGHEHTATIOi SOOBD SESEBATOBS 'Control law design to meet constraints using Experiments on propeller noise SXBPAC-synthesis package for active controls H82-22978 [HASA-TB-83264] H82-22280 SOOBD TBABSBISSIOH Unified results of several analytical and Analytical prediction of the interior noise for experimental studies of helicopter handling cylindrical models of aircraft fuselages for qualities in visual terrain flight prescribed exterior noise fields. Phase 2: H82-23215 Ho dels for sideirall trim, stiffened structures An assessment of various side-stick and cabin acoustics with floor partition controller/stability and control augmentation [HASA-CB-165869] 882-22952 systems for night nap-of-Earth flight using SOOBD iA»BS piloted simulation Unsteady ejectors H82-23216 H82- 23171 STABILIZEBS (FLUID DYHABICS) SPACE COBBOBICATIOB Pressure measurements on twin vertical tails in Extravehicular Activity/Air Traffic Control buffeting flow (E?A/AIC) test report communication links to [AIAA 82-0641] A82-30138 the astronaut Bonded aluminum honeycomb - Aircraft flight £HASA-CB-167600] H82-23381 surface primary structure application SPACE SHUTTLE OBBITEBS [AIAA 82-0676] A82-30145 Comparison of analytical predictions of STABLE OSCIL1ATIOBS longitudinal short period pilot-induced Stability and self-oscillations of coaxial rotors oscillations with results from a sionlation A82-31603 study of the space shuttle orbiter SIAGBAIIOB PBESSOBE [HASA-TB-83267] H82-23236 The excitation of compressor/duct systems SPACE SHUTTLE PAILOADS A82-28993 Research and development at BBB. Technical and SIAHDABDIZAflOH scientific publications, 1981 Development and use of dynamic gnalification H82-23137 standards for Air Force stores SPACE SHUTTLES H82-22155 Development and demonstration of manufacturing STATE VECTOBS processes for fabricating graphite/LABC 160 Optimization of measurements in the state polyinide structural elements estimation of systems using the least squares [HASA-CB-165809] H82-22315 method SPACE TBABSPOBTAIIOH SISTBH A82-29826 Beseacch and Technology annual report FY-1981 STATIC 8BESSUBB [HASA-TB-84199] H82-24137 Static and unsteady pressure measurements on a 50 SPACECBAIT COlSJBOCIlOi HAIIBIALS degree clipped delta wing at B = 0.9 Development and demonstration of manufacturing [AIAA 82-0686] A82-30153 processes for fabricating graphite/LABC 160 Static and unsteady pressure measurements on a 50 polyimide structural elenents degree clipped delta wing at B = 0.9 [HASA-CB-165809] H82-22315 conducted in the Langley Transonic Dynamics Tunnel SPACECBAFI COITEOL [HASA-TB-83297] H82-23195 Comparison of analytical predictions of STATIC TESTS longitudinal short period pilot-induced Prediction of flyover jet noise spectra from oscillations with results from a simulation static tests study of the space shuttle orbiter 082-22963 [HASA-Tfl-83267] 1182-23236 STATISTICAL AHALISIS SPACBCBUI DESI6H Beview of rotorcraft accidents 1977-1979 Besearch and development at BBB. Technical and [PB82-115601] H82-22237 scientific publications, 1981 Program for narrow-band analysis of aircraft H82-23137 flyover noise using ensemble averaging techniques SPACECBAFT STBOCTOBBS [HASA-CB-165867] H82-22949 Development and demonstration of manufacturing STEADY FLOi processes for fabricating graphite/LABC 160 Feedback control of a cantilever wing in steady polyinide structural elements airflow [HASA-CB-165809] H82-22315 [AIAA 82-0729] A82-30177

A-34 SUBJECT HDBX SOBSOHIC PLOW

SIIFFIESS Damage tolerant design using collapse techniques Damping and stiffness of aligned discontinuous [4144 82-0718] 482-30168 fiber reinforced polyaer composites 4 linear decomposition method for large [4144 82-0712] 482-30102 optimization problems. Blueprint for development Aeroelastic flatter and divergence of stiffness [H4S4-TH-83248] 882-22245 coupled, graphite/epoxy, cantilevered plates Application of a structural optimization procedure £4144 82-0722] 482-30172 for advanced wings STE4I1 B4IE [HBB-PB-171/S/PUB/49] H82-23141 Environmental and high strain rate effects on STBOCIOB41 DBSIG1 CBITBHIA conposites for engine applications Tool use in cutting operations involving integral [&I44 82-0758] 482-30118 structural components in aircraft construction SIHAKBS 482-28873 Dnsteady pressure measurements at stall and Durability and damage tolerance control plans for buffeting OS4F aircraft [DFVLB-MITT-79-09] H82-23198 [4144 82-0679] 482-30147 SIH4PDOBB IBBBTIA1 GOIDAICB Application of a structural optimization procedure Optimal control and estimation for strapdovn for advanced wings seeker guidance of tactical missiles [BBB-FB-171/S/POB/49] H82-23141 482-31121 Some case studies and the significance of fatigue Strapdovm inertial navigation systems: An thresholds —•- aircraft components algoritha for attitude and navigation computations [B1B-HP-81015-0] N82-23561 [4B1/SY.S-BEPT-23] H82-22211 STBOCTOB4L BHGIHBBBIBG STBBSS 414LISIS Occurrence of fretting fatigue failures in practice The stressed state of a parachute canopy during 482-28543 opening SIBDCTOB4L P4ILDBE 482-29820 Occurrence of fretting fatigue failures in practice Analysis of shells of straight-Ming type 482-28543 482-298U1 Damage tolerant design using collapse technignes 4 comparison of properties of single overlap [4144 82-0718] 482-30168 tension joints prepared by ultrasonic welding On the dynamic collapse of a column impacting a and other neans rigid surface [4144 82-0661] 482-30091 [4144 82-0735] 482-30182 Experimental stress analysis of a thin-walled STBOCTOBAL BEIIABILITI pressurized torus loaded by contact with a plane Structural integrity of an adhesively bonded —- dynamic response of aircraft tires aircraft fuselage [4144 82-0753] 482-30114 482-28996 STBESS COICEIIBATIOH Durability and damage tolerance control plans for Occurrence of fretting fatigue failures in practice OS4P aircraft 482-28543 [4144 82-0679] 482-30147 S TEE S3 COBBOSIOH CB4CKH6 Flight service evaluation of Kevlar-49 epoxy Engineering property comparisons of 7050-T73651, composite panels in wide-bodied commercial 7010-17651 and 7010-173651 aluminum alloy plate transport aircraft for aircraft construction [N4S4-CB-165841] N82-22316 [HL8-HP-80047-0] 882-22360 SIBOCTOB4L STABILITY. SXBBSS ISTEBSIXI FACTOBS Analysis of a multihinged empennage with allowance Integrity analyses of surface-flawed aircraft for shear strain attachment lugs - 4 new, inexpensive, 3-D 482-29834 alternating method The stability of monocogne panels under bending [4144 82-0742] 482-30107 482-29836 Environmental and high strain rate effects on Effect of operating life on the mechanical composites for engine applications properties of the naterials and load-bearing [4144 82-0758] 482-30118 capacity of the rotor elements of gas-turbine STBESS-STB4II BELATIOHSHIPS engines Thermal stability analysis for conical shells with 482-31643 variable parameters STBOCTOB4L VIBBAXI01 482-29844 An automated technique for improving modal STBDCTOBAt AH1LXSIS test/analysis correlation 4 review of U.S. Air force research related to [4144 82-0640] 482-30137 airframe and engine materials Pressure measurements on twin vertical tails in 482-29268 buffeting flow 737 gtaphite-epoxy horizontal stabilizer [4144 82-0641] 482-30138 certification Transonic time-response analysis of three D.O.P. [4144 82-0745] 482-30109 conventional-and supercritical airfoils Environmental and high strain rate effects on [4144 82-0688] 482-30155 composites for engine applications Development of vibration qualification test [4144 82-0758] 482-30118 spectra for the F-15 aircraft Integrated structural analysis and design support H82-22160 for advanced launch vehicles Approach in dynamic qualification of light [4144 82-0675] 482-30144 helicopter stores and eguipments Bird impact analysis package for turtine engine N82-22166 fan blades The dynamic qualification of equipment and [4144 82-0696] 482-30162 external stores for use with rotary winged 4 linear decomposition method for large aircraft optimization problems. Blueprint for development N82-22167 [flASA-TH-83248] H82-22245 STOL aircraft structural vibration prediction from STBOCTOBAL DESI6B acoustic excitation Structures, Structural Dynamics and Materials N82-22169 Conference, 23rd, New Orleans, LA, Hay 10-12, . STBOCTOBAL 1EIGHT 1982, Collection of Technical Papers. Part 1 - Comparison of light aircraft with strutted and Structures and materials. Part 2 - structural cantilever wings dynamics and design engineering 482-29828 482-30076 SOBSOIIC FLO! Finite element analysis of through the canopy Subsonic aerodynamic and flutter characteristics emergency crew escape from the 1-38 aircraft of several wings calculated by the SOOSS4 P1.1 [4144 82-0705] 482-30096 panel method Integrated structural analysis and design support [4144 P4PEB 82-0727] 482-30193 for advanced launch vehicles The role of coherent structures in the generation [4144 82-0675] 482-30144 of noise for subsonic jets [H4S4-CB-168764] H82-22947

4-35 SOBSOIIC FLOTTEB SUBJECT IMDBI

SOBSOBIC JLOHBB SOSPEHDIHG (HAH6IHG) Experiment on active flutter sappression of a Elastic suspension of a Hind tunnel test section cantilever wing H82-23363 [BAL-TB-690] H82-22282 SiBPI FOBBABD BIH6S SOBSOBIC SEBED Flutter of forward swept wings, analyses and tests Fuel efficient and Hach 0.8, too [AIAA 82-0646] A82-30142 A82-29774 Bigid body-structural mode coupling on a forward SOBSOBIC II»D TOSHELS swept wing aircraft A nuaerical investigation of two-dimensional, [AIAA 82-0683] A82-30150 subsonic, linear, wind tunnel interference theory Active control of aeroelastic divergence [ABL/AEBO-BOIE-403] H82-23197 [AIAA 82-0684] A82-30151 SOCTIOI S1BPTBACK 1IBGS Crossflow shock on the suction side of a flat Helicopter rotor performance improvement by delta King with supersonic leading edges utilization of suept-back parabolic blade tip A82-29659 ~.— wind tunnel tests SOFEBCBIXICAL BIBGS B82-22151 A Hind-tunnel stud; of the aerodynamic Aerodynamic performance of slender wings with characteristics of a slotted versus smooth-skin separated flows supercritical King [HASA-CB-168768] S82-22206 [AIAA 82-0642] A82-30139 Aeroelastic properties of wings in transonic flow Heasnred and calculated effects of angle of attack [HLB-HP-81005-0] B82-22224 on the transonic flutter of a supercritical wing SBIBLIH6 [AIAA 82-0647] A82-30143 The effect of swirl burner aerodynamics on BOX Transonic flutter study of a Hind-tunnel oodel of formation a supercritical Hing Kith/without Kinglet A82-28658 [AIAA 82-0721] A82-30171 SISI8H EFFEdTIVBHBSS Investigation of passive shock wave-boundary layer Estimation of the performance of nonstationary control for transonic airfoil drag reduction discontinuous control systems for flight vehicles [BASA-CB-168844] B82-22209 A82-29832 Aeroelastic properties of wings in transonic flow SISTBHS BSGIBEEBIBG [NLB-HP-81005-0] H82-22224 Applications of system identification methods to Transonic flutter study of a wind-tunnel model of the prediction of helicopter stability, control a supercritical Hing with/without Hinglet and handling characteristics conducted in Langley Transonic Dynamics Tunnel B82-23230 [BASA-TB-83279] H82-23239 SYSTEflS IHTEGBATIOB SOPEBPLASTICITI The integration of multiple avionic sensors and SPF of high strength aluoinun structures technologies for future military helicopters superplastic forming for complex aircraft B82-23186 structures A82-28997 SDPEBSOBIC F10B CrossfloH shock on the suction side of a flat T-38 AIBCEAFI delta Hing with supersonic leading edges Finite element analysis of through the canopy A82-29659 eaergency crew escape from the T-38 aircraft Turboprop and turbojet ejector optimisation [AIAA 82-0705] A82-30096 B82-23174 TACTICS SDPEBSOBIC JET FLOB Beview of practical experience on combat aircraft Acoustic emission fron free jets supersonic jets maneuverability 882-22962 B82-22189 Experimental study of a jet deflector TACTILE DISCBlaiBAlIOB B 82- 23173 A tactual display aid for primary flight training SOPEBSOBIC BOZZLES [NASA-CB-166242] N82-22238 numerical study of vibrational relaxation in the TAIL ASSEflBLIES turbulent ailing of jets in a supersonic nozzle Tail configurations for highly maneuverable combat A82-29880 aircraft SOPEBSOBIC SPEEDS H82-22201 Approximate method for predicting supersonic Concept studies of an advanced composite normal force coefficient very-loH-aspect-ratio helicopter fin lifting surfaces [SBIAS-821-210-106] H82-22257 [AD-A111770J B82-23199 TAILLESS AIBCBAFT SOPPOBT SISIBHS Tail configurations for highly maneuverable combat Metric half-span model support system aircraft tBASA-CASE-LAB-12441-1] H82-23254 B82-22201 SOB?ACE DEFECTS TAKEOFF Integrity analyses of surface-flawed aircraft Analysis and flonte Carlo simulation of attachment lugs - A new, inexpensive, 3-0 near-terminal aircraft flight paths alternating method [BASA-TP-1997] H82-23233 [AIAA 82-0742] A82-30107 TAHES (COHBAT VEHICLES) SURFACE FIBISHIBG A light helicopter for night firing Structural integrity of an adhesively bonded [SBIAS-821-210-105] - H82-22256 aircraft fuselage TAPE BECOBDBBS A82-28996 A portable, low-cost flight-data measurement and SDBGES recording system Encounters with surge: Seme experiences of [BASA-TH-84229] H82-22478 development of axial compressors for aero gas TABGEI ACflOISITIOB turbines The structural dynamic interface required for [PBB-90071] H82-22274 developing helicopter target acguisition systems SOBVEILLiBCE BADAB B82-22165 Improvements to secondary radar for air traffic TABGET BBC06BITIOB control A light helicopter for night firing A82-30311 [SBIAS-821-210-105] B82-22256 The reliability of height and identity data TAXIIHG secondary surveillance radar error analysis Effects of cable geometry and aircraft attitude on A82-30312 the accuracy of a magnetic leader cable system SDBVITU for aircraft guidance during rollout and turnoff Commercial jet transport crashuorthiness [BASA-TP-1978] B82-22239 [HASA-CB-165849] B82-23207

A-36 SOBJECT IIDEX TOBOSBS

TBCH10LOGICAL FOBBCASTI1G THICKBESS B4TIO Developmental possibilities in civil aviation in Analysis of shells of straight-wing type the federal Bepublic of German; 482-29841 B82-22230 IHIH BALLED SHELLS IBCHiOLOGI ASSBSSBBiT Thermal stability analysis for conical shells with Fuel efficient and Bach 0.8, too variable parameters 482-29774 482-29844 Effects of cable geometry and aircraft attitude on THIH BAILS the accuracy of a magnetic leader cable systea Experimental stress analysis of a thin-vailed for aircraft guidance during rollout and turnoff pressurized torus loaded by contact with a plane [BASA-TP-1978] S82-22239 dynamic response of aircraft tires Conceptual design stud; of a visual system for a [AIA4 82-0753] 482-30114 rotorcraft simulator and some advances in THESE DIHBBSIOBAL FLOB platform motion utilization Application of computer generated color graphic [BASA-CB-166322] H82- 22244 techniques to the processing and display of TBBPBBAIOBE DISIBIBOIIOI three dimensional fluid dynamic data • for Thermal stability analysis for conical shells Hith turbofan mixer nozzle mixing process analysis variable parameters 482-29008 A82-29844 Comparison between computations and experimental TEiSXLE SIBBIGTH data in unsteady three-dimensional transonic Effects of 50,000 hours of thermal aging on aerodynamics, including aeroelastic applications graphite/eroxy and graphite/pclyimide composites [4144 82-0690] 482-30157 [4144 82-0657] 482-30087 IHBUSX A06HEII4TI08 High temperature, short term tensile strength of Thrust augmenting ejectors: 4 review of the C6000/PBB-15 graphite folyimide application of jet mechanics to V/STOL aircraft [4144 82-0711] 482-30125 propulsion TEISILE TESTS N82-23169 Effects of moisture on the mechanical properties Improvement of ejector thrust augmentation by of glass/epoxy composites pulsating or flapping jets 482-29036 H82-23172 TEBSOB AB4LISIS THBOSI VECTOB COSTBOL Alternatives for jet engine control Wind-tunnel investigation of the powered low-speed £H4S4-CB-168894] 882-23247 longitudinal aerodynamics of the 1BBBIH4L FACILITIES Vectored-Engine-Over (VEO) wing fighter Instruments and installations for meteorological configuration measurements at airports Russian book [B4S4-TH-83263] H82-22207 482-28826 THDHDEBSTOBHS IBBB4IB AB4LTSIS The 1981 direct strike lightning data Integrated navigation-TF/14-system based on stored utilizing the F-106 aircraft terrain data processing [HAS4-TB-83273] N82-22848 H82-23183 TILT BOTOB BESE4BCH AIHCHAFT PBOGB4B TBBB4IH FOU.OBIBG AIBCBAFI H4S4/H44 Advanced Botorcraft Technology and Tilt Integrated navigation-TF/TA-system based on stored Botor Borkshop. Volume 7: Tilt Botor Session terrain data processing [B4S4-TB-84705] B82-23243 H82-23183 1ILTIIG BOTOBS Optimal inertial navigation using terrain Aerospatiale survey of wind tunnel testing of correlation: An attractive solution to the small and large scale rotors ground attack aircraft navigation problem [SHI4S-821-210-107] H82-22225 B82-23184 TIDE BABCHIIG TEST CHABBBBS Time-marching transonic flutter solutions Acoustic noise test as part of the dynamic including angle-of-attack effects qualification program in aerospace [HASA-TB-83295] H82-23196 B82-22162 TIHE OPTIMAL COBTBOL IBS! EQOIPBE1T Comment on 'Optimal control via mathematical Blockage and flow studies of a generalized test programming1 apparatus including various Ming configurations 482-31125 in the Langley 7-inch Bach 7 Pilot Tunnel TIBB BESPOBSE [H4S4-IH-83301] H82-23471 Transonic time-response analysis of three 0.0.F. THEBBAL COITBOL C04TIH6S conventional and supercritical airfoils The contribution of thermal barrier coatings to [4144 82-0688] 482-30155 improvements in the life and performance of gas TITAHIOfl ALLOIS turbine components Advanced aluminum and titanium structures; [PBB-90076] N82-22271 Proceedings of the Winter Annual Beeting, THEBBAL OBGB4D4XZOH Washington, DC, November 15-20, 1981 Effects of 50,000 hours of thermal aging on 482-28994 graphite/epoxy and graphite/polyimide composites Development of low-cost titanium structures using [4144 82-0657] 482-30087 blended elemental powder metallurgy On the characterization of damages in 482-28998 graphite-epoxy composites Beview of aeronautical fatigue investigations in [4144 82-0757] 482-30117 the Setherlands, March 1979 - February 1981 THBBBAL BBISSIOS [ BLB-UP-81006-0] B82-22153 4 light helicopter for night firing Powder metallurgical innovations for improved hot [SMI4S-821-210-105] H82-22256 section alloys in aero-engine applications THEBB4L BBSISTAHCB [IBB-90072] B82-22358 Test methodology for evaluation of firevorthy TOOLIBG aircraft seat cushions Tailor-made structures; today, and tomorrow: Bew 482-29596 materials, an exploratory investigation into THEBBAL SIABILIII their potential use in aircraft Thermal stability analysis for conical shells with [B4E-SDB-85/4/104/005] B82-22253 variable parameters TOBSIOHAL SIBBSS 482-29844 Shape optimization of fiber reinforced composites Composite bonds improve thermal integrity [4144 82-0719] 482-30169 482-30004 TOBOSBS THBBBOBECHAilCAI TBBATBBBI Experimental stress analysis of a thin-walled SPF of high strength aluminum structures pressurized torus loaded by contact with a plane superplastic forming for complex aircraft dynamic response of aircraft tires structures [4144 82-0753] 482-30114 482-28997

A-37 TBAFPIC SUBJECT IIDBX

TBAFFIC The development of cryogenic wind tunnels and Coaparing the relationships between noise level their application to maneuvering aircraft and annoyance in different surveys - & railway technology noise vs. aircraft and road traffic comparison B82-22196 A82-29165 TBAHSPOBT AIBCBAFT TBAILIBG-BDGE F1APS Application of a dimensionless criterion of Aerodynamic noise generated by jet-wing/flap transport efficiency in evaluating aircraft interactions of the external DSB configuration modifications of STOL aircraft. Part 1: Eight percent scale A82-29837 cold-flow aodel analysis Transport aircraft accident dynamics [HAI-TB-685T] B82-22953 [BASA-CB-165850] B82-22227 TBAIBIHG SIH01AIOBS Fuel efficiency engines for large transport aircraft Combat training imagery [CHB-90082] H82-22276 A82-31179 The 737 graphite composite flight spoiler flight TBAJECTOBI OPHBIZAIIOH service evaluation Determination of an optimal control program for an [HASA-CB-165826] B82-22314 aircraft power plant daring climb Commercial jet transport crashworthiness A82-29845 [HASA-CB-165849] H82-23207 Comment on 'Optimal control via oathenatical Definition of display/control requirements for programming1 assault transport night/adverse weather capability A82-31125 H82-23217 IBABSFEH CEBITS TBAPEZOIDAL 1IHGS Comment on 'Optimal contrcl via mathematical Unsteady pressure measurements at stall and programming* buffeting A82-31125 [DFVLB-HITT-79-09] B82-23198 TBABSBISSI01S (HACHIBB B1EHBBTS) TOBBIBE BLADES Aviation gear drives and reducers: Handbook in Engine depot maintenance repair technology Bussian H82-22174 A82-30675 Bepair and regeneration of turbine blades, vanes TBABSHJTIBB BECEIVBBS and discs Extravehicular Activity/Air Traffic Control S82-22185 (EV&/ATC) test report communication links to TDBBIBE EHGIBES the astronaut Bird impact analysis package for turbine engine [HASA-CB-167600] H82-23381 fan blades TBABSOBIC FLOi [AIAA 82-0696] A82-30162 Application of a transonic potential flow code to The role of modern control theory in the design of the static aeroelastic analysis cf controls for aircraft turbine engines three-dimensional wings [BASA-TH-82815] S82-22262 [AIAA 82-0689] A82-30156 Advanced general aviation engine/airframe Investigation of passive shock wave-boundary layer integration study control for transonic airfoil drag reduction [BASA-CB-165565] B82-22268 [HASA-CB-168844] B82-22209 Advanced turbine study airfoil coling in Aeroelastic properties of wings in transonic flow rocket turbines [BLB-SP-81005-U] H82-22224 [HASA-CB-162003] H82-23249 Application of a transonic potential flow code to TDBBOCOHSBESSOBS the static aeroelastic analysis of The excitation of compressor/duct systems three-dimensional wings 482-28993 [HASA-Ta-83296] H82-23193 Encounters with surge: 'Some experiences of TBABSOBIC FLOTTEB development of axial compressors for aero gas A wind-tunnel study of the aerodynamic turbines characteristics of a slotted versus smooth-skin [PHB-90071] B82-22274 supercritical wing Computer modeling of fan-exit-splitter spacing [AIAA 82-0642] A82-30139 effects on F100 response to distortion Evaluation of four subcritical response methods [BASA-CB-167879] B82-23246 for on-line prediction of flutter onset in TUBBOFAB EHGIBES wind-tunnel tests Heasnrement of aerodynamic work during fan flutter [AIAA 82-0644] A82-30140 A82-28987 Measured and calculated effects of angle of attack Energy efficient engine exhaust mixer model on the transonic flutter of a supercritical wing technology [AIAA 82-0647] A82-30143 [HASA-CB-165459] H82-22264 Transonic tine-response analysis of three D.O.F. Computer modeling of fan-exit-splitter spacing conventional and supercritical airfoils effects on F100 response to distortion [AIAA 82-0688] A82-30155 [SASA-CB-167879] B82-23246 Comparison between computations and experimental Alternatives for jet engine control data in unsteady three-dimensional transonic [BASA-CB-168894] B82-23247 aerodynamics, including aeroelastic applications TOBBOFABS [AIAA 82-0690] A82-30157 Evaluation of the effects of model scale and test Transonic flutter study of a wind-tunnel model of technique on jet-induced effects a supercritical wing with/without winglet B82-23167 [AIAA 82-0721] A82-30171 TDBBOJBT EHGIBES Flutter analysis using nonlinear aerodynamic forces Environmental and high strain rate effects on [AIAA 82-0728] A82-30176 composites for engine applications Aeroelastic properties of wings in transonic flow [AIAA 82-0758] A82-30118 [HLB-HP-81005-D] H82-22224 Turboprop and turbojet ejector optimisation Time-marching transonic flutter solutions H82-23174 including angle-of-attack effects Basic technology of squeeze-film dampers for rotor [HASA-TH-83295] H82-23196 dynamics control Transonic flutter study of a wind-tunnel model of [AD-A110842] H82-23250 a supercritical wing with/without winglet lOBBOHACBIBE BLADES conducted in Langley Transonic Dynamics Tunnel Prediction of aerodynamically induced vibrations [HASA-M-03279] H82-23239 in turbomachinery blading TBABSOIIC iHD lOBBElS A82-28986 Evaluation of four subcritical response methods Directional solidification: Project B2 of gas for on-line prediction cf flutter onset in turbine rotor blade alloys wind-tunnel tests [fHB-90088] H82-22279 [AIAA 82-0644] A82-30140 IOBBOPBOP EHGIBES Static and unsteady pressure measurements on a 50 Advanced general aviation comparative degree clipped delta wing at H = 0.9 engine/airframe integration study [AIAA 82-0686] A82-30153 [SASA-CB-165564] H82-22263

A-38 SUBJECT IBDBX VIBBATIOB TESTS

Turboprop and turbojet ejector optimisation Experience with high performance V/STOL fighter 882-23174 projects at BBB TOBBOBOCKBT BB6IBES [HBB-FB-124/S/PUB/50] H82-23140 Advanced turbine study airfoil coling in Jet effects on forces and moments of a VSTOL rocket turbines fighter type aircraft [BASA-CB-162003] 882-23249 882-23168 TOBBOLBICB EFFECTS Thrust augmenting ejectors: A review of the Turbulence-excited flapping notion of a rotor application of jet mechanics to V/STOL aircraft blade in hovering flight propulsion A82-29042 1182-23169 TOBBDLBIT BODBOABI LIIEH V/STOL aircraft and fluid dynamic La Becherche Aerospatiale, bi-monthly Bulletin H82-23179 number 1981-5, Septenber - October 1981 VTOL and VSTOL handling gualities specifications, aerospace B and D methodology and instrumentation an overview of the current status [ESA-II-725] H82-22145 N82-23209 Drag reduction using pneumatic turbulators VABIABLB PITCH PBOPBLLEBS laminar airfoils Past applications and future potential of variable [DFVLB-FB-81-33] H82-22223 stability research helicopters TOBBOLE1T FLO! H82-23228 Flowfield and noise sources of jet impingement of VABIATIOHAL PHIBCIPLBS flaps and ground surface Analysis of shells of straight-wing type H82-23163 A82-29841 TORBDIBIT JETS VAHIOHBTEES Fluid dynamics of jets with applications to V/STOL Checking and calibrating variometers in place in [AGABD-CP-308] H82-23150 the sailplane instrument panel IOBBDLEST BIXIBG 482-29415 Humerical study of vibrational relaxation in the VEBTICAL TAKEOFF AIBCHAFT turbulent mixing of jets in a supersonic nozzle Aerodynamic analysis of VTOL inlets and definition A82-29880 of a short, bloving-lip inlet TOBSIIG FLIGHT [SASA-CB-165617] H82-22211 Validation of zero-order feedback strategies for An analysis of a nonlinear instability in the medium range air-to-air interception in a implementation of a VTOL control system horizontal plane [BASA-TM-84220] 882-22281 [8ASA-TS-84237] H82-23237 Jet V/STOL wind-tunnel simulation and groundplane effects 882-23165 u The modeling and prediction of multiple jet VTOL OH-1 HELICOPTBB aircraft flow fields in ground effect Performance testing of a main rotor system for a 882-23166 utility helicopter at 1/4 scale Evaluation of the effects of model scale and test [HASA-Tfl-83274] 1182-22251 technique on jet-induced effects Flight tests for the assessment of task H82-23167 performance and control activity VIBBATIOH DAHPIBG S82-23213 Damping and stiffness of aligned discontinuous OLTBASOBIC 1BLDIBG fiber reinforced polymer composites A comparison of properties of single overlap [AIAA 82-0712] A82-30102 tension joints prepared by ultrasonic welding Test demonstration of digital control of and other means wing/store flutter [AIAA 82-0661] A82-30091 [AIAA 82-0645] A82-30141 DISTBADX FLOi Bigid body-structural mode coupling on a forward The excitation of compressor/duct systems swept wing aircraft A82-28993 [AIAA 82-0683] A82-30150 Comparison between computations and experimental Active control of aeroelastic divergence data in unsteady three-dimensional transonic [AIAA 82-0684] A82-30151 aerodynamics, including aeroelastic applications Feedback control of a cantilever wing in steady £AIAA 82-0690] A82-30157 airflow Unsteady ejectors [AIAA 82-0729] A82-30177 B82-23171 Experiment on active flutter suppression of a Improvement of ejector thrust augmentation by cantilever wing pulsating cr flapping jets [BAL-TB-690] N82-22282 H82-23172 Analysis of high load dampers An accurate method for evaluating the kernel of [BASA-CB-165503] B82-23248 the integral eguation relating lift to dovnwash Basic technology of squeeze-film dampers for rotor in unsteady potential flov dynamics control [BASA-TH-83281] H82-23194 [AD-A110842] B82-23250 OBSTEADI STATE VIBBATIOB ISOLATOBS Static and unsteady pressure measurements on a 50 Analysis of high load dampers degree clipped delta King at a = 0.9 [HASA-CB-165503] N82-23248 CAIAA 82-0686] A82-30153 VIBBATIOB HBASOBBHEHT OBSBBCT BIBGS The structural dynamic interface required for Aeroelastic properties of wings in transonic flow developing helicopter target acquisition systems [HLB-HP-81005-0] H82-22224 882-22165 DPPBfl SOBFACB BLOilHG STOL aircraft structural vibration prediction from Aerodynamic characteristics of the external DSB acoustic excitation powered lift system using side fences for 882-22169 enhancement of Coanda flow attachment VIBBATIOB BODE [BAL-TB-686T] H82-22212 Evaluation of four subcritical response methods Aerodynamic noise generated by jet-wing/flap for on-line prediction of flutter onset in interactions of the external USB configuration wind-tunnel tests of SIOL aircraft. Part 1: Eight percent scale [AIAA 82-0644] A82-301UO cold-flow model analysis Active control of aeroelastic divergence [BAL-TB-685T] 882-22953 [AIAA 82-0684] A82-30151 VIBBATIOB TESTS An automated technique for improving modal test/analysis correlation V/STOL AIBCBAFI [AIAA 82-0640] A82-30137 Haiti-mission V/SIOL with vectored thrust engines Dynamic Environmental Qualification Techniques --- —.— bombing, air superiority conference [PHfl-90086] H82-22278 [AGABD-CP-318] 882-22154

A-39 7IBBAIOBI LOADS SUBJECT IHDEX

Development and use of dynamic qualification Determination of wind tunnel constraint effects by standards for Air Force stores a unified pressure signature method. Part 1: H82-22155 Applications to winged configurations Qualification of equipment for gunfire induced [HASA-CB-166186] H82-23234 vibration Determination of wind tunnel constraint effects by H82-22158 a unified pressure signature method. Part 2: Dynamic qualification testing of F-16 equipment Application to jet-in-crossflow H82-22159 [HASA-CB-166187] B82-23235 Development of vibration qualification test BABEEL EB6IHES spectra for the F-15 aircraft Advanced general aviation engine/airframe H82-22160 integration study Equipment vibration qualification for Harrier and [HASA-CB-165565] B82-22268 Hank aircraft BAB GAMES H82-22161 Evaluation of aircraft in simulated combat: Aircraft fuel tank slosh and vibration test CoBpnter against computer or computer against 882-22164 huoan pilot Approach in dynamic qualification of light 882-22202 helicopter stores and equipments •ABBIBG SISIEHS H82-22166 The assessment of aircraft combat effectiveness Application of modal synthesis techniques for the using a new computational method dynamic qualification of Mings with stores B82-22203 H82-22168 iATBE TEHPEBAIUBB Development of a taped random vibration technique Effects of moisture on the mechanical properties for acceptance testing of glass/epoxy composites H82-22171 A82-29036 VIBBAIOB! LOADS BAVEFOBBS The structural dynamic interface required for The 1981 direct strike lightning data developing helicopter tarqet acquisition systems utilizing the F-106 aircraft H82-22165 [HASA-Tfl-83273] H82-22848 Approach in dynamic qualification of light BEAPOB SYSTEMS helicopter stores and equipments Military maintenance policies and procedures for H82-22166 high-temperature parts. Hill they be adequate? The dynamic qualification of equipment and B82-22173 external stores for use with rotary winged HBiPOHS DELIVERS aircraft Integrated flight and fire control demonstration H82-22167 on an F-15B aircraft: System development and VISCOELASXIC DAHPIBG ground test results Damping and stiffness of aligned discontinuous H82-23185 fiber reinforced polymer composites HBAIBEB STAIIOHS [AIAA 82-0712] A82-30102 Instruments and installations for meteorological VISUAL AIDS measurements at airports —- Bnssian book Flight simulators 482-28826 A82-29924 HEIGHT ABALISIS VISUAL C01TE01 Zone loading of flight-vehicle structures Conceptual design study of a visual system for a A82-29838 rotorcraft simulator and some advances in HELDED STBUCTUBBS platform motion utilization Production weldbonding on the A-10 aircraft [HASA-CB-166322] B82-22244 A82-28995 Performance evaluation of a Jcinesthetic-tactual BIBD EFFECTS display Sudden changes in wind velocity - Their effect on H82-23221 aircraft and means of reducing hazard. I VISUAL FLIGHT A82-29871 Unified results of several analytical and BIBD IOIBEL APPIBAIOS experimental studies of helicopter handling Studies on wind tunnel straighteners qualities in visual terrain flight [MASA-TH-76689] H82-22284 H82-23215 Metric half-span model support system VOICE COBIBOL . [HASA-CASE-LAB-12441-1] B82-23254 The role of voice technology in advanced Elastic suspension of a wind tunnel test section helicopter cockpits B82-23363 B82-23223 BIBD IOBBEL DBIVBS VOLTAGE BEGDLATOBS Mechanical properties of a fiberglass prepreq Cascade converter of dc voltage to ac voltage of system at cryogenic and other temperatures higher frequency with vcltage and frequency [AIAA 82-0708] 482-30099 stabilization devices aircraft electric Theoretical optimisation and experimental equipment verification of an injector A82-28875 H82-23170 VOBTE1 BBEAKDOIB BIBD IOBBBL MODELS La Recherche Aerospatiale, bi-monthly Bulletin Transonic flutter study of a wind-tunnel model of number 1981-5, September - October 1981 -— a supercritical wing with/without winglet aerospace B and D methodology and instrumentation [AIAA 82-0721] A82-30171 [ESA-TT-725] B82-22145 Design of dynamically-scaled, asymmetrical wind VORTICES tunnel models A flight investigation of blade-section [HIAST-78/18] H82-22285 aerodynamics for a helicopter main rotor having Determination of wind tunnel constraint effects by BC-SC2 airfcil sections a unified pressure signature method. Part 1: £HASA-TB-832S8] H82-23192 Applications to winged configurations [HASA-CB-166186] B82-23234 Determination of wind tunnel constraint effects by w a unified pressure signature method. Part 2: BALL FLOB Application to jet-in-crossflow Fluid dynamics of jets with applications to V/STOL [HASA-CB-166187] H82-23235 [AGABD-CP-308] 1182-23150 Metric half-span model support system BALL JETS [HASA-CASE-LAB-12441-1] B82-23254 Fluid dynamics of jets with applications to V/STOL Development of a convoluted intake seal for model [AGABD-CP-308] B82-23150 B66 v/stol Bind tunnel HALL PBBSSUBE [BAE-ABG-163] H82-23255 Jet V/STOL wind-tunnel sinnlation and qroundplane BIBD TOBHEL TESTS effects BASA research related to sailplane airfoils H82-23165 A82-29417

A-40 SUBJECT IHDBI IIBID POJHT

flechanical properties of a fiberglass prepreg Static and unsteady pressure measurements on a 50 system at cryogenic and other temperatures degree clipped delta wing at H = 0.9 -— [Alii 82-0708] A82-30099 conducted in the Langley Transonic Dynamics Tunnel A wind-tunnel study of the aerodynamic [SASA-Tfl-83297] H82-23195 characteristics of a slotted versus smooth-skin BZBG iBOFILBS supercritical wing Comparison of light aircraft with strutted and [AIAA 82-0642] A82-30139 cantilever wings Evaluation of four subcritical response methods A82-29828 for on-line prediction cf flutter onset in Subsonic aerodynamic and flutter characteristics wind-tunnel tests of several wings calculated by the SOOSSA P1.1 [41AS 82-0644] A82-30140 panel method Flutter of forward swept wings, analyses and tests [AIAA CAPEB 82-0727] A82-30193 [AIAA 82-0646] A82-30142 iind tunnel investigations of sailplane fuselages Aerospatiale survey of wind tunnel testing of with different lacings and wing settings snail and large scale rotors aerodynamic drag measurement [SBIAS-821-210-107] H82-22225 B82-23200 Ezperinent on active flutter suppression of a IIHG SLOTS cantilever wing A wind-tunnel study of the aerodynamic £ BAL-TB-69 0 ] N82-22282 characteristics of a slotted versus smooth-skin Experiments on propeller noise supercritical wing H82-22978 [AIAA 82-0642] A82-30139 Fluid dynamics of jets with applications to V/S1OL BIBG TIP VOBTICES [AGABD-CP-308] B82-23150 A theoretical study of the impact of aircraft wake Jet V/STOL wind-tunnel sinulation and groundplane vortices on roofs in the final approach area of effects Dusseldorf airport 082-23165 [DFVLB-BITT-82-01] H82-23560 Hind tunnel investigations of sailplane fuselages II16-FOSELA6B STOBES with different lacings and wing settings Test demonstration of digital control of aerodynamic drag measurement wing/store flutter H82-23200 [AIAA 82-0645] A82-30141 Evaluation of four subcritical response methods BIBGLB1S for on-line prediction flutter onset in Transonic flutter study of a wind-tunnel model of wind-tunnel tests conducted in the Langley a supercritical wing with/without winglet Transonic Dynamics Tunnel [AIAA 82-0721] A82-30171 [BASA-TB-83278] H82-23240 Transonic flutter study of a wind-tunnel model of Hetrie half-span model support system a supercritical wing with/vithout Kinglet [HASA-CASE-LAB-12441-1] H82-23254 conducted in Langley Transonic Dynamics Tunnel HIBO TOHHE1 BALIS [HASA-TB-83279] H82-23239 A numerical investigation of two-dimensional, BIBGS subsonic, linear, wind tunnel interference theory Design considerations and experiences in the use [ABL/AEBO-HOTE-403] H82-23197 of composite material for an aeroelastic Determination of wind tunnel constraint effects by research wing a unified tressure signature method. Part 1: [AIAA 82-0678] A82-30146 Applications to winged configurations Investigation of passive shock wave-boundary layer [HASA-CB-166186] N82-23234 control for transonic airfoil drag reduction Determination of wind tunnel constraint effects by [BASA-CB-168844] H82-22209 a unified pressure signature method. Part 2: Experiment on active flutter suppression of a Application to jet-in-ciossflow cantilever wing [HASA-CB-166187] 1182-23235 [NAL-TB-690] H82-22282 BUD VELOCITY Application of a transonic potential flow code to Sudden changes in wind velocity - Their effect on the static aeroelastic analysis of aircraft and means of reducing hazard. I three-dimensional wings A82-29871 [BASA-TB-83296] H82-23193 BIB6 CABBEB Aeroelastic tailoring for control and performance: Are requirements compatible? 1182-22200 XT-15 AIBCBATT ilBG FLAfS NASA/BAA Advanced Botorcraft Technology and Tilt Experimental flight test programs for improving Botor workshop. Volume 7: Tilt Botor Session combat aircraft maneuverability by maneuver [HASA-TM-84705] H82-23243 flaps and pylon split flaps H82-22192 BIBG 10 A DUG Application of a structural optimization procedure YAi for advanced wings An analysis of a nonlinear instability in the [HBB-FE-171/S/POB/49] H82-23141 implementation of a VTOL control system HUG OSCILLATIOHS [HASA-TB-84220] H82-22281 Test demonstration of digital control of IABIBG BOBEBXS wing/store flutter Jet effects on forces and moments of a VSTOL [1IAA 82-0645] A82-30141 fighter type aircraft Static and unsteady pressure measurements on a 50 N82-23168 degree clipped delta wing at B = 0.9 HELD POIBT [AIAA 82-0686] A82-30153 A multidimensional-crack-growth prediction Comparison between computations and experimental methodology for flaws originating at fastener data in unsteady three-dimensional transonic holes aerodynamics, including aeroelastic applications A82-28932 [1IAA 82-0690] A82-30157 Transonic flutter study of a wind-tunnel model of a supercritical wing with/without winglet [AIAA 82-0721] A82-30171 Feedback control of a cantilever wing in steady airflow [AIAA 82-0729] A82-30177 Application cf modal synthesis techniques for the dynamic qualification of wings with stores H82-22168

A-41 PERSONAL AUTHOR INDEX AERONAUTICAL ENGINEERING//* Continuing Bibliography (Suppl. 151) I AUGUST 1982

Typical Personal Author Index Listing

[PERSONAL AUTHOR| ABBEBBOI, B. J. A system safety model for developmental aircraft programs ADAHS, B. B. i. INASA-CB-3534] N82-22228 I—Badar mapping, archaeology, and ancient land use AHIBO?. A. B. in the Haya lowlands The stability of maueuverable flight vehicles [BASA-CB-164931] 1182-11514 A82-29827 ABDBBSOB. B. B. Application ,of computer generated color graphic REPORT TITLE techniques to the processing and display of NUMBER three dimensional fluid dynamic data A 82-29 00 8 AHDEBSOS, C. A. Listings in this index are arranged alphabetically by personal author. The title of the document provides the user with a brief description of the subject Integration of avionics and advanced control matter. The report number helps to indicate the type of document cited (e.g., technology NASA report, translation, NASA contractor report). The accession number N82-22194 is located beneath and to the right of the title, e.g., N82-11514. Under any AHDEBSOB, S. B. ' one author's name the accession numbers are arranged in sequence with V/SIOL aircraft and fluid dynamic the IAA accession numbers appearing first. 1182-23179 AHGEBHAIB, I, The current state of technology concerning the fighting of forest fires from the air in Austria A82-29579 The employment of helicopters in Austria in ADAHS, I. B., Jfi. connection with large-scale fires in buildings Control law design to neet constraints using A82-29585 SIHPAC-synthesis package for active controls ABHIS, C. G., Jfi. [BASA-IH-83264 J B82-22280 Engine component retirement for cause AFIBOGEBOV, L. P. H82-22177 Instruments and installations for meteorological APPBL, J. measurements at airports Beal time digital filtering test in the S1 A82-28826 continuous wind tunnel at Hodane AGEBI, K. B. H82-22152 Pavement management and rehabilitation of Portland ABBOT, B. E. cement concrete pavements Fuel efficient and Hach 0.8, too [PB82-131384] N82-22392 A82-29774 AHABBAH. B. C. ASHKBIES, I. L. The military flying qualities specification, a Development of a tentative flying qualities help or a hindrance to good fighter design criterion for aircraft with independent control H82-22190 of six degrees of freedom: Analysis and flight AIKE8, X. B. test An assessment of various side-stick H82-22191 controller/stability and control augmentation AILOBI, S. H. systems for night nap-of-Earth flight using Integrity analyses of surface-flawed aircraft piloted simulation attachment lugs - A new, inexpensive, 3-D B82-23216 alternating method AKHAIOV, B- KH. [AIAA 82-0742] A82-30107 Investigation of the aerodynamic-contour method AOLEHLA, F. with control functions in the form of soooth Experience with high performance V/SIOL fighter constant-sign contours projects at HBB A82-29831 [MBB-FE-124/S/PUB/50] H82-23140 AKHBEHBHKO, V. L. AflOLI, H. J. Effect of operating life on the mechanical Utility of a probability-density-function curve properties of the materials and load-bearing and F-maps in composite-material inspection capacity of the rotor elements of gas-turbine A82-28934 engines AZABIB, V. S. A82-31643 Zone loading of flight-vehicle structures ALBEBTSOB, C. B. A82-29838 Blockage and flow studies of a generalized test apparatus including various ving configurations in the Langley 7-inch Bach 7 Pilot Tunnel B [NASA-TH-83301 ] S82-23471 BADIAGIB, A. A. ALLEB, B. B. Comparison of light aircraft with strutted and Functional requirements for the man-vehicle cantilever wings systems research facility A82-29828 [HASA-CB-166315] B82-22248 BAHI, L. A theory of human error Investigation of passive shock wave-boundary layer [BASA-CB-166313] H82-22250 control for transonic airfoil drag reduction ABBABTSOHOT, L. 6. [SASA-CB-168844] B82-22209 Optimization of measurements in the state BAIBD, B. estimation of systems using the least sgnares Development of a taped random vibration technique method for acceptance testing A82-29826 B82-22171

B-1 BALL, PBBSOSAL AOIHOB IBDBI

BALL, B, H. BOBZOT, V. I. Checking and calibrating variometers in place in The maximum flying range problem for an aircraft the sailplane instrument panel A82-31602 182-29415 BOOSQDET, B. D. BABIES, A. G. Integrated structural analysis and design support The study of combat aircraft maneuverability by for advanced launch vehicles air to air conbat sinulation [AIAA 82-0675] A82-30144 H82-22205 BOBES, B. C. BAB»BABT, B. Improvements to secondary radar for air traffic Analysis of rotary balance data for the F-15 control airplane including the effect of conformal fuel A82-30311 tanks BOBHAB, B. S. [BASA-CB-3479] H82-22213 Tail configurations for highly manenverable combat BAXIBA. J. I. aircraft Transonic time-response analysis of three D.O.P. H82-22201 conventional and supercritical airfoils BOIOEH, B. F, [AIAA 82-0688] A82-30155 The development of cryogenic wind tunnels and BiOHSJBTEi. J. I. their application to maneuvering aircraft Experimental stress analysis of a thin-vailed technology pressurized torus loaded by contact with a plane H82-22196 £AIAA 82-0753] A82-30114 BBADBOBI, L. J. S. BAIEBDOBBFBB, G. Some aspects of jet dynamics and their Acoustic noise test as part of the dynamic implications for VIOL research qualification program in aerospace B82-23151 S82-22162 BBADLEI, B. F. BEAttI, I. 0. Critical metals conservation, recycling and Predictions of aerodynamic characteristics of substitution highly maneuverable configurations [AGABD-B-693] H82-22348 B82-22199 BEADS, D. BEU.AHI. B. A. Approach in dynamic qualification of light Development of a correlated finite element dynamic helicopter stores and equipments model of a complete aero engine H82-22166 [PBB-90081] B82-22272 BBAI, B. S. BBBBBCT, J. C. Helicopter simulation technology: An Ames Development of a correlated finite element dynamic Besearch Center perspective model of a complete aero engine B82-23227 [PHB-90081] H82-22272 BBEITBACB. E. BBBBBf?. B. H. Application of modal synthesis techniques for the Application of a transonic potential flou code to dynamic qualification of wings with stores the static aeroelastic analysis of B82-22168 three-dimensional wings BBEBOE, 0. B. [AIAA 82-0689] A82-30156 Commercial jet transport crashworthiness Application of a transonic potential flow code to [HASA-CB-165849J B82-23207 the static aeroelastic analysis of BBIGBAC, B. J. three-dimensional wings Dynamic qualification testing of F-16 equipment [HASA-1B-83296] H82-23193 B82-22159 Time-marching transonic flutter solutions BBOOKS, 8. B. including angle-of-attack effects Predictions of aerodynamic characteristics of [HASA-TH-83295] B82-23196 highly maneuverable configurations BEBBI, J. D, B82-22199 Performance testing of a main rotor system for a BBOSBiB, B. J. utility helicopter at 1/4 scale Bigid body-structural mode coupling on a forward [BASA-TH-83274] H82-22251 swept wing aircraft BESSE, J. B. [AIAA 82-0683] A82-30150 Civil (French/OS) certification of the Coast BBOBEB, B. B., JB. Guard's HH-65A Dauphin Investigation of passive shock wave-boundary layer H82-23210 control for transonic airfoil drag reduction BBTBBS, H. B. [BASA-CB-168844] B82-22209 Design of dynamically-scaled, asymmetrical wind BOBLITZ, F. tunnel models Unsteady pressure measurements at stall and £HIAST-78/18] H82-22285 buffeting BBZIAC. G. [DFVLB-BITT-79-09] B82-23198 Parametric study of the influence of the engine BDLAXOV. S. B. upon the operating cost of a civil helicopter Analysis of shells of straight-wing type [SHIAS-827-210-102] H82-22273 A82-29841 BBAZ, S. I. BOBDICK, I. I. Analysis of high load dampers Effects of cable geometry and aircraft attitude on [8ASA-CB-165503] 882-23248 the accuracy of a magnetic leader cable system BIBDBB, G. for aircraft guidance during rollout and turnoff Improvement of ejector thrust augmentation by [BASA-TP-1978] B82-22239 pulsating or flapping jets BOOBO, D. F. H82-23172 Analysis of high load dampers BIBD, B. J. [BASA-CB-165503] H82-23248 Tailor-made structures; today, and tomorrow: Hev BOBKHABD, A. B. materials, an exploratory investigation into Development and use of dynamic gualification their potential use standards for Air Force stores [BAE-SDI-85/A/104/005] H82-22253 882-22155 BLACHEBE, G. BDBSSIDE, B. D. Tail rotor studies for satisfactory performance: GTD analysis of airborne antennas radiating in the Strength and dynamic behavior presence of lossy dielectric layers [SHIAS-821-210-108] S82-22258 [BASA-CB-168770] H82-22398 BOLZIB6EB, B. The utilization of aircraft in fighting forest fires - French experience A82-29581 CABBIT, P, BOOKBB, 0. Parametric study of the influence of the engine Aeroelastic tailoring for control and performance: upon the operating cost of a civil helicopter Are requirements compatible? [SBIAS-827-210-102] B82-22273 1182-22200

B-2 PEBSOHAL A01HOB IHDBZ DECBEBIBBS, H.

CABBEBLBII. L. COCKBBXL, C. E. Optimal inertial navigation using terrain Hechanical properties of a fiberglass prepreg correlation: An attractive solution to the system at cryogenic and other temperatures ground attack aircraft navigation problem [AIAA 82-0708] A82-30099 B82-23181 COSGESHA11, B. L. CAHPBBiL, B. i. The 737 graphite composite flight spoiler flight Effect of nacelles on aerodynamic characteristics service evaluation of an executive-jet model with simulated, [UASA-CB-165826] B82-22314 partial-chord, laminar-flow-control wing glove COLLIBS. A. G. [HASA-TB-83271] 882-22217 BB211 powerplant deterioration: Beview of current CAIDJO. J. P. situation and lessons learned A light helicopter for night firing [PHB-90073] H82-22270 [SBIAS-821-210-105] B82-22256 COaiHSKT, A. CABPB1TBB, G. Transport aircraft accident dynamics The assessment of aircraft combat effectiveness [BASA-CB-165850] H82-22227 using a new computational method COBEH, H. B82-22203 Elevator unit for the Alpha-Jet, made from CASZ1BBBBBI, D. B. carbon-fibre reinforced plastic State-of-the-art cockpit design for the HH-65A A82-28649 helicopters COBLISS, L. D. 882-23220 A helicopter handling-qualities study of the CAZIEB, F. H. effects of engine response characteristics, Static and unsteady pressure measurements on a 50 height-control dynamics, and excess power on degree clipped delta wing at H = 0.9 nap-of-the-Earth operations [AIAA 82-0686] A82-30153 B82-23214 Static and unsteady pressure measurements on a 50 COBBIGAB, J. degree clipped delta ving at H = 0.9 Component coupling with time-invariant mass matrix [SASA-Tfi-83297] B82-23195 for nonisotropic rotating and nonrotating systems CHABIS. C. C. [AIAA 82-0731] A82-30179 Environmental and high strain rate effects on COTOH, F. composites for engine applications Application of Raiman filtering to the kinematic [AIAA 82-0758] A82-30118 reconstruction of free flight of catapulted CHAB1BS, 8. J. aircraft models in the laboratory Applications of structural adhesives in production [IHFL-80-28] B82-22259 A82-28808 COUTSOOBADIS, D. CHATIAPADHYAY, A. Directional solidification: Project B2 Shape optimization of fiber reinforced composites [PBB-90088] N82-22279 [AIAA 82-0719] A82-30169 CBEiS, S. I. CHATOBVBDI, S. K. The structural dynamic interface required for Damping and stiffness of aligned discontinuous developing helicopter target acquisition systems fiber reinforced polymer composites B82-22165 [AIAA 82-0712] A82-30102 CDBBIBGHAB, H. J. CHAOBETTB, D. Subsonic aerodynamic and flutter characteristics Flight qualification of composite structures at of several wings calculated by the SOUSSA P1.1 AHD-BA panel method [AIAA 82-0755] A82-30116 [AIAA PAPEB 82-0727] A82-30193 CHEi, B. T. I. COBTAINE, P. C. Unified results of several analytical and Pavement management and rehabilitation of Portland experimental studies of helicopter handling cement concrete pavements qualities in visual terrain flight [PB82-131384] B82-22392 B82-23215 Besults of BASA/FAA ground and flight simulation experiments concerning helicopter IFB airuorthiness criteria DAMBBA, F. H82-23219 Tail rotor studies for satisfactory performance: CHEBBETTE, D. Strength and dynamic behavior Optimal inertial navigation using terrain [SHIAS-821-210-108] H82-22258 correlation: An attractive solution to the DAS, D. K. ground attack aircraft navigation problem The excitation of compressor/duct systems 1182-23184 A82-28993 CHIPBAB, B. B. DASABO, J. A. Active control of aeroelastic divergence Synthesis of an integrated cockpit management system [AIAA 82-0684] A82-30151 B82-23222 CHBISTIAISEH, 0. DAflBS, H. F. Traffic infrastructure: Can planning still be Powder metallurgical innovations for improved hot carried through section alloys in aero-engine applications H82-22232 [PBB-90072] B82-22358 CLABKE, B. DAVIS, B. A. Development of a simple, self-contained flight The employment of two-engine and four-engine test data acguisition system aircraft for dropping the latest chemical fire [HASA-CB-168912] B82-23245 extinguishing agents in connection with the CUIPOLE, T. C. fighting of forest fires The effect of swirl burner aerodynamics on HOx A82-29583 formation DAFIS, B. T. A82-28658 A Schwarz-Christoffel method for generating CLBHEIT, I. F. internal flow grids Functional requirements for the man-vehicle A82-29005 systems research facility DAVIDOV. ID. T. [HASA-CB-166315] N82-22248 Design principles of a computer-aided design system Technical approaches for measurement of human errors A82-29829 [BASA-CB-166311] 1182-22249 DEBBA. D. B. A theory of human error Elastic suspension of a wind tunnel test section [NASA-CB-166313] H82-22250 B82-23363 CLIMTOI, B. G.. JB. DECBEBIEBS, B. On the characterization of damages in Optimal inertial navigation using terrain graphite-epoxy composites correlation: An attractive solution to the [AIAA 82-0757] A82-30117 ground attack aircraft navigation problem B82-23184

B-3 DBDIEO, J. P. PEBSOSAL i01HOB IHDEX

DBDIEO, J. P. DOGOBDJI. J. Parametric stud; of the influence of the engine Aeroelastic flutter and divergence of stiffness upon the operating cost of a civil helicopter coupled, graphite/epoxy, cantilevered plates [SBIAS-827-210-102] H82-22273 [AIAA 82-0722] A82-30172 DEGBAAP. E. A. B. DOHH. B. S. Coaparison of reliability, sensitivity and Performance evaluation of a kinesthetic-tactual accuracy of some sol-Techniques display [BLB-HP-80039-0] B82-23542 B82-23221 DBJOIGB. J. B. DOBET, C. Beview of aeronautical fatigue investigations in The influence of protective treatment on the the Netherlands, Harch 1979 - February 1981 mechanical properties of superalloy parts [HLB-MP-81 006-0] 1182-22153 B82-22180 DEBZJK, P. DOVAL, B. K. Comparison of reliability, sensitivity and Applications of system identification methods to accuracy of some HDI-Techniques the prediction of helicopter stability, control [HLB-flP-80039-0] B82-23542 and handling characteristics DESBABAIS. B. H. B82-23230 Subsonic aerodynamic and flutter characteristics DUES, P. J. of several Kings calculated by the SOOSSA P1.1 Development and demonstration of manufacturing panel method processes for fabricating graphite/LABC 160 [AIAA PAPEE 82-0727] A82-30193 polyimide structural elements An accurate nethod for evaluating the kernel of [HASA-CB-165809] B82-22315 the integral eguation relating lift to dovnwash in unsteady potential flow [BASA-TM-83281] B82-23194 DBSHOICEAOX. A. BCKSTBOH. Co ?. Concept studies of an advanced composite Design considerations and experiences in the use helicopter fin of composite material for an aeroelastic [SHIAS-821-210-106] 1182-22257 research wing DBTIXT, J. [AIAA 82-0678] A82-30146 Development of a taped random vibration technique BDIABDS, J. B. for acceptance testing Time-marching transonic flutter solutions B82-22171 including angle-of-attack effects DIDE1LE, B. [BASA-TH-83295] B82-23196 Improvement of ejector thrust augmentation by BLLIOIT, C. I. pulsating or flapping jets Synthesis of an integrated cockpit management system H82-23172 H82-23222 DIGIOVABU, P. B. ELLIS, D. B. High temperature, short term tensile strength of Analysis and flight evaluation of a small, C6000/PHB-15 graphite polyimide fixed-wing aircraft equipped with hinged plate [AIAA 82-0711] A82-30125 spoilers OOBBZIHSKI, B. [BASA-CB-166247] B82-22243 Ground reflection effects in measuring propeller Advanced general aviation comparative aircraft flyover noise engine/airframe integration study [DFVLB-FB-81-28] B82-22990 [ BASA-CB-165564] B82-22263 DOGGBXT, B. ?., JB. BLOFF. P. C. Evaluation of four subcritical response methods Development of low-cost titanium structures using for on-line prediction cf flutter onset in blended elemental powder metallurgy vind-tunnel tests A82-28998 [AIAA 82-0644] A82-30140 ELSTOB, S. T. Evaluation of four sobcritical response methods Development of a correlated finite element dynamic for on-line prediction flutter onset in model of a complete aero engine wind-tunnel tests [PBB-90081] B82-22272 [SASA-TH-83278] B82-23240 DOLLIBIGB, S. H. Hetric half-span model support system [BASA-CASE-I.AB-12441-1] H82-23254 FALCO, H. DOBPIBGBAOS, B. The assessment of aircraft combat effectiveness Eevolution in airplane construction? Srob G110: using a new computational method The first modern fiber glass composition B82-22203 airplane shortly before its maiden flight Influence of maneuverability on helicopter combat [BASA-Tn-76705] 882-22216 effectiveness OOTSOB, B. t. H82-23212 STOL aircraft structural vibration prediction from PABBEB, H. G. acoustic excitation Beasnred and calculated effects of angle of attack B82-22169 on the transonic flutter of a supercritical wing DOOGLAS, C. D. [AIAA 82-0647] A82-30143 Effects of moisture on the mechanical properties A two-degree-of-freedom flutter mount system with of glass/ecoxy composites low damping for testing rigid wings at different A82-29036 angles of attack DOBELL, E. B. [BASA-TH-83302] B82-23549 Flutter analysis using nonlinear aerodynamic forces FELLBBS, i. B. [AIAA 82-0728] A82-30176 Tail configurations for highly maneuver/able combat DBIVBB, 0. aircraft The gas turbine engine 1182-22201 A82-28587 FIELDS, J. B. DBOBEHKO, B. Comparing the relationships between noise level Subsonic aerodynamic and flutter characteristics and annoyance in different surveys - A railway of several Kings calculated by the SOOSSA P1.1 noise vs. aircraft and road traffic comparison panel method A82-29165 [AIAA PAPEB 82-0727] A82-30193 FIIKLE, 0. V. DOBBBOU, J. . P. A computerized system for the application of Haval versions of the Dauphin and the AS 15 TT fracture tracking data to aircraft management ireapon system for the C-5A military airlift transport [SHIAS-821-210-104] B82-22255 [AIAA 82-0760] A82-30119 DOC, J. H. A review of recent AGABD Symposia on the Angle of Haneuverability of Combat Aircraft B82-22188

B-4 PBISOHAL AOTflOB IHDBI BAAS, B.

FISCHEB, 0. A. GEBDES, B. a. AC1TA: Investigation of new piloting and flight Besults of HASA/FAA ground and flight simulation control technologies. Volume 1: Beview; active experiments concerning helicopter IFB ving airworthiness criteria [MBB-DH-05-81-VOI,-1] H82-23252 H82-23219 ACT1A: Investigation of nev piloting and flight GIAHATI, C. C. control technologies. Volume 2: Aircraft vith Application of computer generated color graphic reduced lateral stability techniques to the processing and display of [BBB-DH-05-81-VOL-2] H82-23253 three dimensional fluid dynamic data FL&CH, J. a. A 82-29008 Performance evaluation of a kinesthetic-tactual GIBSOB, B. F. display Damping and stiffness of aligned discontinuous H82-23221 fiber reinforced polymer composites FLEEIBB. S. [AIAA 82-0712] A82-30102 Prediction of aerodynamically induced vibrations 6ILSOH, B. D. in turbomacbinery blading A tactual display aid for primary flight training A82-28986 [NASA-CB-1662U2] U82-22238 FLEBIBG. B. B. Performance evaluation of a kinesthetic-tactual Analysis of computing system configurations for display highly integrated guidance and control systems H82-23221 H82-23189 GOEDEL, fl. FOBBEST, B. D. Application of a structural optimization procedure Besults of NASA/FAA ground and flight simulation for advanced vings experiments concerning helicopter IFB [BBB-FE-171/S/POB/49] H82-23141 airworthiness criteria 60LDSIEI1. K. I. N82-23219 VIOL and VSTOL handling qualities specifications, FOBSTIH. P. J. E. an overview of the current status Occurrence of fretting fatigue failures in practice H82-23209 A82-28543 GOODSAB, J. B, FOSTEB, 1. E. Advanced aluminum and titanium structures; Advanced technology DFCS control panel for the Proceedings of the Sinter Annual Meeting, L-1011-500 Washington, DC, November 15-20, 1981 [4IAA PAPEE 81-2210] A82-29000 A82-28994 FOX. S. B. GOOBJIAB, P. B. Automated design of minimum drag light aircraft Comparison betveen computations and experimental fuselages and nacelles data in unsteady three-dimensional transonic [HASA-CB-168913] 1182-23238 aerodynamics, including aeroelastic applications FOI, B. B. [AIAA 82-0690] A82-30157 Adaptation and equipment of aircraft for the 60SLIIS, G. 0. fighting of forest fires Measures to increase airfield capacity by changing A82-29584 aircraft runway occupancy characteristics FBABCIS, fl. S. [ HASA-CB-168841] H82-22240 A computer-controlled oscillation mechanism for GBAALHABB, B. unsteady aerodynamics experiments Tool use in cutting operations involving integral A82-29018 structural components in aircraft construction FBOST, B. K. A82-28873 Development and demonstration of manufacturing GBACIA, J. J. processes for fabricating graphite/LABC 160 Integrated cockpit for A-129 polyimide structural elements H82-23225 [HASA-CB-165809] N82-22315 GBEEH, D. L. FOJIEDA, H. Cockpit integration from a pilot's point of view Aerodynamic characteristics of the external USB N82-23224 powered lift system using side fences for GBIDLEI, D. enhancement of Coanda flow attachment Program for narrow-band analysis of aircraft [-HAL-TB-6861] 882-22212 flyover noise using ensemble averaging techniques FOJIHOXO, T. [NASA-CB-165867] H82-22949 Crossflov shock on the suction side of a flat 6BOSCHE, F. B, delta ving vith supersonic leading edges Experiments on propeller noise A82-29659 H82-22978 FOJIBOTO, B. I. GBOSSEB, B. F. A mnltidimensional-crack-grovth prediction A wind-tunnel study of the aerodynamic methodology for flavs originating at fastener characteristics of a slotted versus smooth-skin holes supercritical wing A82-28932 [AIAA 82-0642] A82-30139 FOLLAB, P. B. J. 6BOSSHAH, D. I. Enhanced piloting control through cockpit An automated technique for improving modal facilities and A.C.T. test/analysis correlation S82-22195 [AIAA 82-0640] A82-30137 FOLLEB, C. B. GDICHETEAO, P. Integrated structural analysis and design support Application of the theory of bifurcations to the for advanced launch vehicles study of the loss of control in combat aircraft [AIAA 82-0675] A82-30144 H82-22198 GOBOSBABI, P. Comparison between computations and experimental data in unsteady three-dimensional transonic GAIOB07, G. 1. aerodynamics, including aeroelastic applications The stressed state of a parachute canopy during [AIAA 82-0.690] A82-30157 opening 60TBBIE, C. fl. A82-29820 Evaluation of direct force mode fighters by combat GABBLABD, S. simulation Transient measurements under electric pulse N82-22204 excitation in 37 Viggen aircraft [FOA-C-30243-A3] H82-23409 GEHt, B. H The reliability of height and identity data BAAS, B. A82-30312 Pavement management and rehabilitation of portland cement concrete pavements [PB82-131384] H82-22392

B-5 HACKEE, B. PEBSOHiL 10TBOE IBDEI

HACKBB, B. HELDBHFBLS, E. E. Elastic suspension of a wind tunnel test section Historical perspectives on thermostrnctnral H82-23363 research at the HACA Langley Aeronautical BACKBIT, J. B. Laboratory from 1948 to 1958 Determination of wind tunnel constraint effects by B82-23494 a unified pressure signature method. Pact 1: HBLLIBELL, B. J. Applications to winged configurations Ponder metallurgical innovations for improved hot [HASA-CB-166186] H82-23234 section alloys in aero-engine applications Determination of wind tunnel constraint effects by [JBB-90072] B82-22358 a unified pressure signature method. Part 2: HBBDBBSOB, C. Application to jet-in-crossflow Sea-based remotely piloted vehicles. I - Issues [BASA-CB-166187] H82-23235 and concepts HAPIKA, B. 1. A82-29714 Damage tolerant design using collapse techniques HEBHI, A. B. [AIAA 82-0718] A82-30168 Beview of practical experience on combat aircraft HAPiaAHB. B. maneuverability Jet effects on forces and moments of a 7STOL B82-22189 fighter tjpe aircraft HBBTZ, T. J. H82-23168 Flatter of forward swept wings, analyses and tests HAH*, i- A. [AIAA 82-0646] A82-30142 HOx formation in flat, laiinar, opposed jet BBSS, B. H. methane diffusion flames Static and unsteady pressure measurements on a 50 A82-28660 degree clipped delta wing at a = 0.9 BALI., 0. B. [AIAA 82-0686] A82-30153 I he gas turbine engine Static and unsteady pressure measurements on a 50 A82-28587 degree clipped delta wing at H = 0.9 HALL, S. L. [BASA-TH-83297] B82-23195 Acoustic emission from free jets HIBIEB, D. B. H82-22962 Analysis of high load dampers HABJLTOH, C. H. [BASA-CB-165503] B82-23248 SPF of high strength aluminum structures HICKS, B. A82-28997 Sheet materials - Fabrication and joining HABASOD, S. V. A82-28594 On the characterization of damages in HIGHABD, I. graphite-epoxy composites Evaluation of aircraft in simulated combat: [AIAA 82-0757] A82-30117 Computer against computer or computer against Shape optimization of fiber reinforced composites human pilot [AIAA 82-0719] A82-30169 B82-22202 HAHSAH, C. G. BILL, D. B. Composite materials Experimental stress analysis of a thin-walled A82-28590 pressurized torus loaded by contact with a plane HABPEB, fl. P. [AIAA 82-0753] A82-30114 The role of voice technolcgj in advanced HIHDSOB, I. S. helicopter cockpits Past applications and future potential of variable B82-23223 stability research helicopters HABBIS, J. A., JB. B82-23228 Engine component retirement for cause HIBSCH, I. N82-22177 The utilization of agricultural aircraft in HABBISOI, B. economical operations for fighting forest fires powder metallurgical innovations for improved hot in Israel section alloys in aero-engine applications A82-29580 [PBB-90072] B82-22358 HIBSCHBEIH, H. S. HABI, J. C. Bird impact analysis package for turbine engine Civil (French/OS) certification of the Coast fan blades Guard's HH-65A Dauphin [AIAA 82-0696] A82-30162 B82-23210 BOB, B. B. HABTBOPP, S. J. Development of a tentative flying qualities The contribution of thermal barrier coatings to criterion for aircraft with independent control improvements in the life and performance of gas of six degrees of freedom: Analysis and flight turbine components test [PBB-90076] H82-22271 B82-22191 HABfEI, C. A. New development in flying qualities with Test demonstration of digital control of application to rotary wing aircraft wing/store flutter B82-23226 [AIAA 82-0645] A82-30141 BOLLOBBLL, S. J. HASKIHS, J. F. Aeroelastic flutter and divergence of stiffness Effects of 50,000 hours of thermal aging on coupled, graphite/epoxy, cantilevered plates graphite/epoxy and graphite/poljimide composites [AIAA 82-0722] A82-30172 [AIAA 82-0657] A82-30087 HOBG, C. I. B. HAOSBB. J. B. Turbulence-excited flapping notion of a rotor The influence of protective treatment on the blade in hovering flight mechanical properties of superalloy parts A82-29042 B82-22180 HOBSTHABB, K. B. HECHI, J. Drag reduction using pneumatic turbnlators Laser gyros - the guiding light [DFVLB-FB-81-33] B82-22223 A82-29792 HOOSBBB, J. H. HEDGECOCK, B. B. 6. On the dynamic collapse of a column impacting a Hilitary maintenance policies and procedures for rigid surface high-temperature parts. Hill they be adequate? [AIAA 82-0735] A82-30182 882-22173 BOIHIAK, 0. HEFFLEI, B. K. Prediction of aerodynamically induced vibrations Functional requirements for the man-vehicle in turbomachinery blading systems research facility A82-28986 [BASA-CS-166315] H82-22248 HOABS, B. Technical approaches for measurement of human errors The relaxation oscillation in ramjet combustion [BASA-CB-166314] H82-22249 A82-28738 A pilot in the loop analysis of helicopter acceleration/deceleration maneuvers B82-23229

B-6 BBBSOBA1 AQIBOB IHDEX KBSLBB. D. F.

HDD SOI. B. B. JOBBSOB, J. B. Pavement management and rehabilitation of Portland Composite materials cement concrete paveaents A 82-28 590 [PB82-131384] H82-22392 JOHHSOS, B. •. BOfF, B. 737 graphite-epoxy horizontal stabilizer Repair and regeneration of turbine blades, vanes certification and discs [AIAA 82-0745] A82-30109 N82-22185 JOBBS, A. L. HDGGIIS, 6. L. Aerodynamic analysis of VIOL inlets and definition Advanced general aviation comparative of a short, bloving-lip inlet engine/airframe integration stud; [HASA-CB-165617] H82-22211 [HASA-Cfi-165564] H82-22263 JOBBS. J. B. HOLTBB, G. Analysis of computing system configurations for BAOIAK simulator for aircraft instruments highly integrated guidance and control systems [FOA-C-40136-A3] H82-22286 H82-23189 BOHBES, 0. JOBBS, J. S. Flight tests for the assessment of task Development and demonstration of manufacturing performance and control activity processes for fabricating graphite/LABC 160 H82-23213 polyimide structural elements HOBTBB, J. B. [HASA-CB-165809] N82-22315 Integrated flight and fire control demonstration JOBBS, B. B., JB. on an F-15B aircraft; System development and Fatigue behavior of adhesively bonded joints ground test results A82-29032 H82-23185 JOSEI, D. S. HiAHG. C. Test demonstration of digital control of Test demonstration of digital control of ving/store flutter ^ing/store flatter [AIAA 82-0645] A82-30141 [AIAA 82-0645] A82-30141 JOSS. S. Application of optimal control technigues to New processes and methods of technical diagnostics aircraft flatter suppression and load alleviation and prognostics in the case of the engine [AIAA 82-0724] A82-30173 HK-8-4. II A82-29925

IGOHIBA, T. E. K The maximum flying range problem for an aircraft KA1TATZIDIS, B. A82-31602 Elevator unit for the Alpha-Jet, made from IBGOf, 0. K. carbon-fibre reinforced plastic Determination of an optimal control program for an A82-28649 aircraft poiier plant during climb KALEBABIS, S. G. A82-29845 Evaluation of the effects of model scale and test technique on jet-induced effects B82-23167 KAHAFABI, A. JACABOSO, G. Measures to increase airfield capacity by changing A giant step toward composite helicopters aircraft runway occupancy characteristics A82-30294 [HASA-CB-168841] H82-22240 JACESOB, C. fl., JB. KABAH, B. A, Metric half-span model support system pavement management and rehabilitation of portland [ HASA-CASE-LAB-12441-1 ] H82-23254 cement concrete pavements JACOB, D. [PB82-131384] H82-22392 Experimental flight test programs for improving KABIB, G. A. combat aircraft maneuverability by maneuver The combustion of a fuel jet in a stream of lean flaps and pylon split flaps gaseous fuel-air mixtures H82-22192 482-28692 JAGACIBSSI. B. J. KABLIB, B. B. Performance evaluation of a kinesthetic-tactual Automated design of mininum drag light aircraft display fuselages and nacelles H82-23221 [HASA-CB-168913] H82-23238 JAHOBSKI, B. KABLOVIIZ, L. Analysis of changes in the gas-dynamic parameters Shape optimization of fiber reinforced composites of a gas-turbine helicopter engine during [AIAA 82-0719] A82-30169 acceleration KABBABKAB, J. S. A82-29872 Analysis of computing system configurations for JEAL. R. B. highly integrated guidance and control systems Defects and their effect on the behavior of gas B82-23189 turbine discs KBBGAH, B. B. H82-22178 Fighting forest fires with the aid of aircraft in JEOBG, I. B. the United States of America Utility of a probability-density-function curve A82-29577 and F-maps in composite-material inspection KBBB, J. B. S. A82-28934 Reliable power JEWELL, B. F. [PBH-90078] H82-22275 Functional requirements for the man-vehicle REESE, J. B. systems research facility A computer-controlled oscillation mechanism for [HASA-CB-166315] H82-222U8 unsteady aerodynamics experiments Technical approaches for leasurement of human errors A82-29018 [HASA-CB-166314] 882-22249 KEHSCBE, C. JBZ, B. B. Service life investigation of a sailplane wing of Functional reguirements for the man-vehicle CFEP construction systems research facility B82-22324 [HASA-CB-166315] H82-22248 KBBB, J. B. JOBBSOI, E. B. Effects of 50,000 hours of thermal aging on Test demonstration of digital control of graphite/epoxy and graphite/polyimide composites wing/store flutter [AIAA 82-0657] A82-30087 [AIAA 82-0645] A82-30141 KBS1EB, 0. F. JOBBSOB, J. 1. Test demonstration of digital control of Composite bonds improve thermal integrity wing/store flutter A82-30004 [AIAA 82-0645] A82-30141

B-7 1 KIEOCHI, X. PBBSOHAL ADTHOB IHDEI

CXKOCHI, I. 1AHDIS, K. H. Experiment on active flottei suppression of a An assessment of various side-stick cantilever wing controller/stability and control augmentation [BAL-TB-690] V 82-22282 systems for night nap-of-Earth flight using KISSBL, 6. K. piloted simulation Experience with high performance V/S1OL fighter H82-23216 projects at HBB IAHDI, B, A, [HBB-FB-124/S/POB/50] H82-23140 Durability and damage tolerance control plans for KLBIDEB, A. DSAF aircraft Composite bonds improve thermal integrity [AIAA 82-0679] A82-30147 A82-30004 LiiDT, B. J. KUCH, P. J. Integrated flight and fire control demonstration Mechanical properties of a fiberglass prepreg on an F-15B aircraft: System development and system at cryogenic and other temperatures ground test results [AIAA 82-0708] 482-30099 H82-23185 MIGHT, H. 1. G. LABKIB, M. Low cost aircrew training devices Energy efficient engine exhaust mixer model 482-29258 technology MIGHT, H. P., JB. tHASA-CB-165459] H82-22264 On the dynamic collapse of a column impacting a LATBOT, A. V. rigid surface Numerical study of vibrational relaxation in the [AIAA 82-0735] A82-30182 turbulent mixing of jets in a supersonic nozzle COLAIDEB, i. A82-29880 ACTTA: Investigation of neu piloting and flight LEACB, J. F. control technologies. Volume 1: fievie«; active Aircraft cabin air ozone contamination and wing compliance with regulations [HBB-OH-05-81-VOL-1] H82-23252 A82-31057 ACTTA: Investigation of new piloting and flight LBBACfiZ, J. V. control technologies. Volume 2: Aircraft with Besults of NASA/FAA ground and flight simulation reduced lateral stability experiments concerning helicopter IFB [MBB-UH-05-81-VOL-2] H82-23253 airworthiness criteria KOLEK, B. 1. H82-23219 Composite bonds improve thermal integrity LBCOHTE-HBBTBHS. C. A82-30004 Directional solidification: Project B2 KO1ABSKI, D. B. [PSB-90088] S82-22279 The modeling and prediction of multiple jet VT01 IBB. H. K. aircraft flow fields in ground effect Experiment on active flutter suppression of a H82-23166 cantilever wing KOTELBIKOV, ?. B. [HA1-TB-690] H82-22282 Thermal stability analysis for conical shells with IBB, S. G. variable parameters Production weldbonding on the A-10 aircraft 482-29814 A82-28995 KOTH, B. I. LBFBAHCQ. J. P. Integrated cockpit for A-129 A complete method for computation of blade mode 1182-23225 characteristics and responses in forward flight KOOBIIDBS, D. A. [SBIAS-821-210-101] B82-22254 Test methodology for evaluation of fireworthy LEHTIBBH, B, aircraft seat cushions The role of modern control theory in the design of A82-29596 controls for aircraft turbine engines KO2LOBSKI, H. [HASA-TM-82815] B82-22262 Energy efficient engine exhaust mixer model LEPBBIBB, H. technology Experimental study of a jet deflector [BASA-CB-165459] N82-22264 B82-23173 KBASIOSBAPKA, H. H. LEBCBB, B. 0. Cascade converter of dc voltage to ac voltage of Integrated navigation-TF/TA-system based on stored higher freguency with voltage and frequency terrain data processing stabilization devices H82-23183 A82-28875 LETT, H. KUBO, S. Chem-Braze abradable seal practical Crossflow shock on the suction side of a flat A82-31048 delta wing with supersonic leading edges LBilS, 6. H. A82-29659 Collaborative development of aero-engines KUBTIHBB, B. [PHB-90083] 882-22277 Air Traffic Flow Management and Air Traffic Flow LEWIS, B. J. Control Multi-mission V/STOL with vectored thrust engines A82-29923 [PHB-90086] 882-22278 KUUEV, B. A. LIB, I. K. Estimation of the performance of nonstationary Turbulence-excited flapping motion of a rotor discontinuous control systems for flight vehicles blade in hovering flight A82-29832 A82-29042 KORKOV, A. P. LIHCOLH, J. Measurement of aerodynamic work during fan flutter Soaring Society of America, National Convention, A82-28987 Phoenix, AZ, January 14-18, 1981, Proceedings KOBOCBKA, F. B. A82-29414 Analysis of shells of straight-wing type L06AB, X. B. A82-29841 Bonded aluminum honeycomb - Aircraft flight surface primary structure application [AIAA 82-0676] A82-30145 LOGOS, P. J, LAFOB, P. Production Verification Testing (PVT) of guidance Helicopter rotor performance improvement by and control systems for high reliability utilization of swept-back parabolic blade tip H82-23187 H82-22151 LOZHKIB, 0. B. LAMBBBIGTS, M. The stability of monocogue panels under bending Directional solidification: project B2 A82-29836 [EHB-90088] B82-22279

B-8 PEBSOHA1 AOIBOB ISDEI HOHBIS, J. J.

LOCBBO, B. F. HBETBAM, 6. H. Approximate method for predicting supersonic The gas turbine engine normal force coefficient very-low-aspect-ratio A82-28587 lifting surfaces The contribution of thermal barrier coatings to [AD-A111770] H82-23199 improvements in the life and performance of gas turbine components tPSB-90076] B82-22271 M BBIBOVUCH, L. RAITA, e. Feedback control of a cantilever wing in steady Aerodynamic characteristics of the external USB airflow powered lift system using side fences for [AIAA 82-0729] A82-30177 enhancement of Coanda flow attachment HEBBILI, B. [NAL-TB-686T] . H82-22212 The role of modern control theory in the design of Aerodynamic noise generated by jet-wing/flap controls for aircraft turbine engines interactions of the external USB configuration tHASA-Tfl-82815] H82-22262 of STOL aircraft. Part 1: Eight percent scale BBIBALLI, a. cold-flow model analysis The combustion of a fuel jet in a stream of lean [BAL-1B-685T] H82-22953 gaseous fuel-air mixtures BALZBEIDBB, B. A82-28692 Socata: IB 20 Trinidad given German debut BICHALKB, A. [HASA-TB-76706] N82-22247 Prediction of flyover jet noise spectra from BABGAS01, B. J. static tests Jet V/STOL wind-tunnel simulation and gronndplane H82-22963 effects HICHBL, D. B 82-23165 Prediction of flyover jet noise spectra from HABSDBH, K. B. static tests The use of 'water bombers' and chemical agents 1)82-22963 against forest fires, taking into account the HIGHOSI, A. employment of a first-attack system Theoretical optimisation and experimental A82-29582 verification of an injector HARSH, A. B. N82-23170 Becommeudations for field measurements of aircraft BILE1LI, B. J. noise Definition of display/control reguirements for [BASA-CB-3540] H82-22955 assault transport night/adverse weather capability HABSH, D. A. N82-23217 The contribution of thermal barrier coatings to HILLBB, G. 0. improvements in the life and performance of gas Bigid body-structural mode coupling on a forward turbine components swept wing aircraft £PHB-90076] N82-22271 [AIAA 82-0683] A82-30150 HASOBE, B. BILLBB. 6. K., JB. A complete method for computation of blade mode Comparison of analytical predictions of characteristics and responses in forward flight longitudinal short period pilot-induced [SBIAS-821-210-101] B82-22254 oscillations with results from a simulation BATSHBiS. C. G. study of the space shuttle orbiter Analysis and Bonte Carlo simulation of [NASA-TB-83267] B82-23236 near-terminal aircraft flight paths HILLEB, B. B. [NiSA-TP-1997] H82-23233 Strapdowm inertial navigation systems: An BAOBEB, 0. F. algorithm for attitude and navigation computations Development and use of dynamic qualification [ABl/SIS-BEPT-23] N82-22241 standards for Air force stores BILLBB, B. J. H82-22155 A portable, low-cost flight-data measurement and HCCABII, J. E. recording system 737 graphite-epoxy horizontal stabilizer [NASA-TH-84229] B82-22478 certification HIBABDA, L. B. £AIAA 82-0715] A82-30109 Computational aerodynamics - Its coming of age and BCCABTX, B. E. its future Finite element analysis of through the canopy A82-29773 emergency crew escape from the T-36 aircraft BOHAH, K. [AIAA 82-0705] A82-30096 The combustion of a fuel jet in a stream of lean BCCLEHDOS, J. B. gaseous fuel-air mixtures Optimal control and estimation for strapdovn A82-28692 seeker guidance of tactical missiles BOOBB, B. 0. A82-31121 Performance of single-stage axial-flow transonic HCELBEATH, K. B, compressor with rotor and stator aspect ratios Civil (French/OS) certification of the Coast of 1.63 and 1.77, respectively, and with design Guard's BB-65A Dauphin pressure ratio of 2.05 H82-23210 [HASA-TP-2001 ] B82-22269 HCBLBEATB, H. I. BOOBSB, S. A. State-of-the-art cockpit design for the HB-65A Gunfire blast pressure predictions helicopters B82-22170 H82-23220 BOBAiSKI, J. B. HCKESZIE, A. B. Sudden changes in wind velocity - Their effect on Encounters with surge: Some experiences of aircraft and means of reducing hazard. I development of axial compressors for aero gas A82-29871 turbines BOBGAH, J, B. [PHB-90071] B82-22274 Some piloting experiences with multifunction HCQOILKII, F. I. isometric side-arm controllers in a helicopter SPF of high strength aluminum structures H82-23218 A82-28997 BOBBIS, C. E. K., JR. HCBDEB, D. I. A flight investigation of blade-section Functional requirements for the man-vehicle aerodynamics for a helicopter main rotor having systems research facility BC-SC2 airfoil sections [HASA-CB-166315] N82-22248 [HASA-TH-83298] N82-23192 Technical approaches for measurement of human errors BOBBIS, J. J. [BASA-CB-166314] H82-22249 Boeing 234 flight control development A theory of human error H82-23211 [KASA-CB-166313] M82-22250

B-9 BOBBISOB. 6. L. PBBSOBAL ADTHOB IBDEX

BOBBISOI. G. L. PABKBB. J. A. The role of coherent structures in the generation Test methodology for evaluation of fireworthy of noise for subsonic jets aircraft seat cushions [BASA-CB-168764] S82-22947 A82-29596 BOBBBI, G. i. PAIBBSOB, D. Definition of display/control requirements for High temperature, short term tensile strength of assault transport night/adverse weather capability C6000/PHB-15 graphite polyimide H 82- 23217 [AIAA 82-0711] A82-30125 HO»T, B. H. PAISBHKEB, B. L. Gunfire blast pressure predictions Zone loading of flight-vehicle structures H82-22170 A82-29838 BOBDOCH, B. I. PAZTIB, E. B. Computer modeling of fan-exit-splitter spacing Effects of moisture on the mechanical properties effects on F100 response to distortion of glass/epoxy composites [BASA-CB-167879] B82-23246 A82-29036 BOBOLO, A. PAOLSOH, J. •«, Turboprop and turbojet ejector optimisation iind-tnnnel investigation of the powered low-speed B82-23174 longitudinal aerodynaaics of the HIEBS, I. 1. Vectored-Engine-Over (VEO) wing fighter Development of a tentative flying qualities configuration criterion for aircraft with independent control [BASA-TB-83263] B82-22207 of six degrees of freedom: Analysis and flight PAUSDEB, H. J, test Flight tests for the assessaent of task H82-22191 performance and control activity B82-23213 PAVLOV, V. A. N Analysis of a multihinged enpennage with allowance •AGAEV, V. A. for shear strain The stability of monocogue panels under bending A82-29834 A82-29836 PEACOCK, A. HAGAHATSO, B. 3. Qualification of equipment for gunfire induced Investigation of passive shock wave-boundary layer vibration control for transonic airfoil drag reduction B82-22158 [HASA-CB-168844] B82-22209 PEACOCK, B. B. BBOBBBTB, G. The excitation of compressor/duct systems Flovfield and noise sources of jet iapingenent of A82-28993 flaps and ground surface PBABSOH, J. H82-23163 STOL aircraft structural vibration prediction from HEVIOS, B. B. acoustic excitation Dynamic qualification testing of F-16 equipment H82-22169 882-22159 CBDIGO, B. D. BISHIOKA, I. Pavement management and rehabilitation of Portland Integrity analyses of surface-flawed aircraft cement concrete pavements attachment lugs - A new, inexpensive, 3-D [PB82-131384] B82-22392 alternating method PEDOTII, J. [AIAA 82-0742] A82-30107 Evaluation of aircraft in simulated combat: BOBDS1BABD, B. Computer against computer or computer against BADIAK simulator for aircraft instruments human pilot [FOA-C-40136-A3] H82-22286 B82-22202 BUBSSEH. H. G. PEOPLES, P. L. Developmental possibilities in civil aviation in Handling air freight in the 1980s - Meeting the the Federal Bepnblic of Germany challenge N82-22230 A82-29800 PEBBI, A. J. Gunfire blast pressure predictions H82-22170 OLCOTT. J. B. PHILIPPE, J. J. Analysis and flight evaluation of a small, Helicopter rotor performance improvement by fixed-wing aircraft eguipped with hinged plate utilization of swept-back parabolic blade tip spoilers H82-22151 [HASA-Cfi-166247] B82-22243 PHILLIPS, C. G. OSIPOV. V. A. Determination of wind tunnel constraint effects by Design principles of a computer-aided design system a unified pressure signature method. Part 1: A82-29829 Applications to winged configurations Investigation of the aerodynamic-contour method [HASA-CB-166186] H82-23234 with control functions in the form of smooth Determination of wind tunnel constraint effects by constant-sign contours a unified pressure signature method. Part 2: A82-29831 Application to jet-in-crossflow [HASA-CB-166187] S82-23235 PI, B. S. Test demonstration of digital control of PADFIELD, G. 0. wing/store flutter Applications of system identification methods to CAIAA 82-0645] A82-30141 the prediction of helicopter stability, control Application .of optimal control techniques to and handling characteristics aircraft flutter suppression and load alleviation B82-23230 [AIAA 82-0724] A82-30173 PAiHBB, S. J. PICHOIfl, B. Applications of structural adhesives in production The influence of protective treatment on the 482-28808 mechanical properties of superalloy parts PAB, C. B. I. B82-22180 Basic technology of squeeze-film dampers for rotor PITTS, S. L. dynamics control The 1981 direct strike lightning data [AD-4110842] B82-23250 [HASA-TB-83273] H82-22848 PABAB1, J. L. PLDHB, t. J. Aircraft aerodynamic noise during approach Maintenance problems in gas turbine components at B82-22976 the Boyal Naval Aircraft Yard, Fleetlands PABFITt, D. J. B82-22175 Fuel efficiency engines for large transport aircraft [PBB-90082] 1182-22276

B-10 PBBSOBAL AOIBOB I8DEI BOSBHTBAL, L.

POKAUDS, B. HEED, B. D. Development of a taped random vibration technique Sun sensing guidance system for high altitude for acceptance testing aircraft M82-22171 £ HASA-CASE-FBC-11052-1] H82-23231 POLBAHOS, E. C. BEID, L. The development of cryogenic Mind tunnels and Performance of single-stage axial-flow transonic their application to maneuvering aircraft compressor with rotor and stator aspect ratios technology of 1.63 and 1.77, respectively, and with design H82-22196 pressure ratio of 2.05 POLLOCK, 1. tHASA-TP-2001] H82-22269 A numerical investigation of two-dimensional, BBIBA, F. subsonic, linear, wind tunnel interference theory Integrated cockpit for A-129 [ABL/AEBO-NOTE-403] N82-23197 H82-23225 POITBIAIDCLFO, C. BEHSHA1, I. Definition of display/control requirements for A comparison of properties of single overlap assault transport night/adverse Heather capability tension joints prepared by ultrasonic welding 1182-23217 and other means POPE, L. 0. [AIAA 82-0661] A82-30091 Analytical prediction of the interior noise for BBTBLLB, J. P. cylindrical models of aircraft fuselages for A computer-controlled oscillation mechanism for prescribed exterior noise fields. Phase 2: unsteady aerodynamics experiments Models for sidevall trim, stiffened structures A82-29018 and cabin acoustics with floor partition BICKETTS, B. H. [HASA-CB-165869] H82-22952 Evaluation of four subcritical response methods POP010, J, for on-line prediction of flutter onset in Development of a taped random vibration technique wind-tunnel tests for acceptance testing [AIAA 82-0644] A82-30140 H82-22171 Evaluation of four subcritical response methods POBTIBB, C. for on-line prediction flutter onset in Experimental study of a jet deflector wind-tunnel tests N82-23173 [HASA-TH-83278] H82-23240 POBTBOI, ?. A. BILBZ, D. B. Analysis of a multihinged empennage with allowance Comparison of analytical predictions of for shear strain longitudinal short period pilot-induced A82-29834 oscillations with results from a simulation POSPELOt, V. A. study of the space shuttle orbiter Numerical study of vibrational relaxation in the [HASA-TH-83267] H82-23236 turbulent mixing of jets in a supersonic nozzle BIVIELLO. V. P. A82-29880 Turboprop and turbojet ejector optimisation POIIEB, 0. L. H82-23174 Structural integrity of an adhesively bonded BIZBHBEBGS, B. L. aircraft fuselage Pavement management and rehabilitation of Portland A82-28996 cement concrete pavements POZBIAK, E. L. [PB82-131384] H82-22392 Stability and self-oscillations of coaxial rotors BOBBBTS, F. L. A82-31603 Pavement management and rehabilitation of Portland POTT, C. I. cement concrete pavements Application of computer generated color graphic [PB82-131384] N82-22392 techniques to the processing and display of BOBEBTS, L. three dimensional fluid dynamic data V/STOL aircraft and fluid dynamic A82-29008 N82-23179 BOBIHSOB, 6. B. Aircraft cabin air ozone contamination and compliance with regulations QOiST, A. A82-31057 Drag reduction using pneumatic turbnlators BOCE, S.. [DFVLH-FB-81-33] H82-22223 Elastic suspension of a wind tunnel test section QDIHI, B. H82-23363 Thrust augmenting ejectors: A re vie if of the BOCKADAX, S. L. tt. application of jet mechanics to V/STOL aircraft Measures to increase airfield capacity by changing propulsion aircraft runway occupancy characteristics H82-23169 [NASA-CB-168841] H82-22240 BOJAS-TEBAH, B. 6. GTD analysis of airborne antennas radiating in the R presence of lossy dielectric layers BABBBHOBST, D. I, [NASA-CB-168770] H82-22398 Prototype flywheel spin testing program BOHAHKO, J. [UCBL-15381] H82-22499 Fatigue behavior of adhesively bonded joints BADESPIEL, B. A82-29032 Hind tunnel investigations of sailplane fuselages BOHABOV, B. V. with different lacings and wing settings Instruments and installations for meteorological H82-23200 measurements at airports BAH, C. A82-28826 Future auto engines - Competition heats up BOPELEiSKI, B. B. A82-29793 F-15 fighter abilities evaluated BATCLIPPE. S. A82-29592 Secondary radar for airborne collision avoidance BOSE. J. L. A82-30313 Utility of a probability-density-function curve BAUCH, F. J., JB. and F-oaps in composite-material inspection Transonic flutter study of a wind-tunnel model of A82-28934 a supercritical wing with/without winglet BOSEHSTEI1, A. B. [AliA 82-0721] A82-30171 A review of D.S. Air Force research related to Transonic flutter study of a wind-tunnel model of airframe and engine materials a supercritical wing with/without winglet A82-29268 [NASA-TH-83279] H82-23239 BOSEHTHAL, L. BBDDI, C. S. Aerodynamics at the 1981 Le Bonrget show Aerodynamic performance of slender wings with A82-29789 separated flows [NASA-CB-168768] S82-22206

B-11 BOSFJOBD, I. J. PBBSOBAL AOTHOB IBDEI

BOSFJOBD. 5. J. SABBABXOBIO, A. Investigation of soot and carbon formation in A comparison of properties of single overlap snail gas turbine combustors tension joints prepared by ultrasonic welding [BiSA-Cfi-167853] B82-22267 and other means BOSKAB, J. [AIAA 62-0661] A82-30091 Development of a simple, self-contained flight SCHAFFEB. E. 6. test data acquisition system An investigation of rotor harmonic noise by the [BASA-CB-168912] B82-23245 use of small scale wind tunnel models BOSS, I.: [HASA-CB-166337] B82-24050 An electronic control for an electrohydraulic SCHIESS, J. B. active control landing gear for the F-4 aircraft Analysis and Honte Carlo simulation of [HASA-CB-3552] H82-22252 near-terminal aircraft flight paths BOSS, J. [HASA-TP-1997] 1182-23233 Investigation of passive shock wave-boundary layer SCHttlDI-BISCHOPPSflAOSEB, HE. control for transonic airfoil drag redaction Performance characteristics and employment [BASA-CB-168844] H82-22209 profiles of the new helicopter BK117 BOBLIB, C. I. A82-29586 Evaluation of four subcritical response methods SCHHIDT. D. K. for on-line prediction of flutter onset in Bultivariable closed loop control analysis and wind-tunnel tests synthesis for complex flight systems [AIAA 82-0644] A82-30140 B82-22193 Transonic flutter stud; of a wind-tunnel model of SCBBBIDBB, G, a supercritical wing with/without winglet Application of a structural optimization procedure [AIAA 82-0721] A82-30171 for advanced wings Transonic flutter stud; of a wind-tunnel oodel of [HBB-FE-171/S/POB/49] B82-23141 a supercritical wing with/without vinglet SCBBA. I. [HASA-TH-83279] U82-23239 Engineering property comparisons of 7050-T73651, Evaluation of four subcritical response methods 7010-T7651 and 7010-T73651 aluminum alloy plate for on-line prediction flutter onset in [HLB-HP-80 047-0] B82-22360 wind-tunnel tests SCBOZBAB, I. B. [BASA-TH-83278] B82-23240 Functional reguirements for the man-vehicle BOBflBB, 0. I. systems research facility Development of a simple, self-contained flight [HASA-CB-166315] 1182-22248 test data acguisition systea SCHOLTZ-CBOHOi, F. [BASA-CB-168912] 1182-23245 Studies on wind tunnel straighteners BDPP, B. 1. [BASA-TH-76689] H82-22284 Production weldbonding on the A-10 aircraft SCBOLZ. B. J. A82-28995 Engine depot maintenance repair technology BILABD, B. H82-22174 The micro revolution cones to civil air transport SCBBABTZ, B. B. A82-29259 A giant step toward composite helicopters A82-30294 SC01AITI, C. A. Integrated flight and fire control demonstration SACKBL, B. on an F-15B aircraft: System development and Analysis and flight evaluation of a snail, ground test results fixed-wing aircraft equipped with hinged plate H82-23185 spoilers SCOU.IOI, I. [HASA-CB-166247] B82-22243 Pavement management and rehabilitation of Portland SAOLBB, S. 6. cement concrete pavements Component coupling with tine-invariant mass matrix [PB82-131384] B82-22392 for nonisotropic rotating and nonrotating systems SEIDBL, D. A. [AIAA 82-0731] A82-30179 Time-marching transonic flutter solutions SAFF, C. B. including angle-of-attack effects A multidimensional-crack-growth prediction £HASA-TB-83295] B82-23196 methodology for flaws originating at fastener SB7BSIBB, C. holes La Becherche Aerospatiale, bi-monthly Bulletin A82-28932 number 1981-5, September.- October 1981 SAIB, B. K. [ESA-TT-725] B82-22145 Alternatives for jet engine control SBAUSBILIB, f. I. [BASA-CB-168894] N82-23247 The stability of aonocogue panels under bending SAIiT CLAIB, A. K. A82-29836 Addition polvimide adhesives containing various SBABES, A. end groups Production weldbonding on the A-10 aircraft A82-29098 A82-28995 SAIBT CLAIB, 1. L. SBAHE, 0. Addition polyiaide adhesives containing various Development of a simple, self-contained flight end groups test data acquisition system A82-29098 [HASA-CB-168912] B82-23245 SALZBOBB, B. SHIPIBO, A. J. Fighting forest fires - A task for the Swiss air The integration of multiple avionic sensors and force technologies for future military helicopters 482-29578 B82-23186 SABPAIH, S. SBA8, 0. S. Determination of wind tunnel constraint effects by He trie half-span model support system a unified pressure signature method. Part 1: [BASA-CASE-LAB-12441-1] B82-23254 Applications to winged configurations SBAB, B. [HASA-CB-166186] H82-23234 Computer modeling of fan-exit-splitter spacing Determination of wind tnnnel constraint effects by effects on F100 response to distortion a unified pressure signature method. Part 2: [BASA-CB-167879] 882-23246 Application to jet-in-ciossflow SHBPTOBO?, V. B. [BASA-CB-166187] B82-23235 Application of a dimensiouless criterion of SAICALLS, F, J. transport efficiency in evaluating aircraft Aircraft cabin air ozone contamination and nodifications compliance with regulations A82-29837 A82-31057

B-12 PBBSOHA1 A01BOB IHDBI SXBED, H.

SBIBAB, J. SBOLICZ, I. Validation of zero-order feedback strategies for Sudden changes in wind velocity - Their effect on medium range air-to-air interception in a aircraft and Beans of reducing hazard. I horizontal plane A82-29871 [HASA-TU-84237] H82-23237 S8IDE, J. A. SBI1DO, S. Engine depot maintenance repair technology Aerodynamic characteristics of the external USB H82-22174 powered lift system using side fences for SOBIBSZCZABSKI-SOBIBSKI, J. enhancement of Coanda flov attachment A linear decomposition method for large [NAL-TB-686T] H82-22212 optimization problems. Blueprint for development Aerodynamic ncise generated by jet-wing/flap [B&SA-TH-83248] H82-22245 interactions of the external USE configuration SOHBBS, 0. a. of SIOL aircraft. Fart T: Eight percent scale NASA research related to sailplane airfoils cold-flow model analysis A82-29417 [HAL-TB-685T] N82-22953 SOODAK, D. SHIBK, B. H. Bonded aluminum honeycomb - Aircraft flight Flatter of forward swept wings, analyses and tests surface primary structure application [AIAA 82-0646] A82-30142 [AIAA 82-0676] A82-30145 SILVA, i. 1. SPAIH, C. V. Subsonic aerodynamic and flatter characteristics Design considerations and experiences in the use of several wings calculated by the SOOSSA P1.1 of composite material for an aeroelastic panel method research wing [AI4A P4PEB 82-0727] A82-30193 [AIAA 82-0678] A82-30146 SI17AII, J. t. SBIDBAB, K.. P. Aerospatiale survey of wind tunnel testing of A Schwarz-Christoffel method for generating small and large scale rotors internal flow grids [SHIAS-821-210-107] H82-22225 482-29005 SILVEBBEBG. t. STAPIBFOBD, B. I. Feedback control of a cantilever wing in steady Functional reguirements for the man-vehicle airflow systems research facility £AIAA 82-0729] A82-30177 [HASA-CB-166315] B82-22248 SXHEKIB, P. STEIHBBHG. B. D. Bulti-mission V/STOL with vectored thrust engines Distributed airborne array concepts [PHB-90086] H82-22278 A82-31669 SIHS, D. L. STEBBFB1D, fl., Jfl, Engine component retirement for cause An investigation of rotor harmonic noise by the H82-22177 use of small scale wind tunnel models SIHACOBI. J. B. [HASA-CB-166337] H82-24050 Conceptual design study of a visual system for a SIIEBITT, H. rotorcraft simulator and some advances in Experiments on propeller noise platfortf motion utilization H82-22978 [HASA-CB-166322] 882-22244 STOKELD. B. L. SIVAKOMB, B. A system safety model for developmental aircraft An evaluation study of aluninide and programs chromoaluminide coatings on IH-100 [NASA-CB-3534] B82-22228 A82-29597 STOBE, B. B. SKOBACHBtSKIJ. 6. S. Flight service evaluation of Kevlar-49 epoxy Gas turbine engines used in aviation: Design and composite panels in wide-bodied commercial construction of components /5th revised and transport aircraft enlarged edition/ [HASA-CB-165841] H82-22316 A82-30697 SIOPPBI, J. SLEEPBB. B. K. Approach in dynamic gnalification of light Planar equations of rollout motion for an aircraft helicopter stores and equipments with free or steerable landing gears N82-22166 [HASA-TP-1S84] N82-23244 SIBOJHIK, A. SHETAIA, F. 0. Development of a homebuilt powered sailplane Automated design of minimum drag light aircraft A82-29416 fuselages and nacelles S1BOOBACB, J. P. [HASA-CB-168913] 1182-23238 Haintenance experience with civil aero engines saiia, A. j. H82-22176 The Boyal Aircraft Establishment: 100 years of STOHPFL, S. C. research Rind-tunnel investigation of the powered low-speed [BAE-TH-FS-432] . N82-22144 longitudinal aerodynamics of the Airfield visual aids research at the Boyal ?ectored-Engine-Over (¥EO) wing fighter Aircraft Establishment configuration [BAE-TB-FS-431] H82-22242 [BASA-TB-83263] N82-22207 SBITH, E. G. STOB6ESS. 6. J. Planar equations of rollout motion for an aircraft Advanced Low-Emissions Catalytic-Combustor with free or steerable landing gears Program, phase 1 [HASA-TP-1984] 1182-23244 [BASA-CB-159656] H82-22265 SBITH, 6. 1. SOB, C. X. Environmental and high strain rate effects on Damping and stiffness of aligned discontinuous composites for engine applications fiber reinforced polymer composites [AIAA 82-0758] A82-30118 [AIAA 82-0712] A82-30102 SHITH, B. SIEBTIAHD, ?. Influence of maneuverability on helicopter combat Handling air freight in the 1980s - Beeting the effectiveness challenge H82-23212 482-29800 SHITH, B. A. SIBEBG, J. Finite element analysis of through the canopy Aerodynamic analysis of VIOL inlets and definition emergency crew escape from the 1-38 aircraft of a short, blowing-lip inlet [AIAA 82-0705] A82-30096 [HASA-CB-165617] H82-22211 SBITBBBS, 0. L. SIBED, B. Durability and damage tolerance control plans for The effect of swirl burner aerodynamics on HOx USAF aircraft formation [AIAA 82-0679] A82-30147 A82-28658

B-13 IEBEKHOV, I. P. PEBSOHA1 AOIHOB IHDEI

IEBEKHO?, I. P. TAB IIJK, A, Cascade converter of dc voltage to ac voltage of The investigation of aircraft accidents and higher frequency vith vcltage and frequency incidents - Sone recent national and stabilization devices international developments A82-28875 A82-29275 TH1BI. I. G. J. TA1BABSABT, B. G. Engineering property comparisons of 7050-T73651, State of the art and recent perspectives on the 7010-17651 and 7010-T73C51 alaninan alloy plate study of the loss of control and spin [BLB-HP-80047-U] B82-22360 B82-22197 THOBAS, B. E. •AB1AHDBBUB, B. C, The 1981 direct strike lightning data Engine component retirement for cause [HASA-IH-83273] H82-22848 882-22177 SHOBBX, 0. C. TBBH, G. B. Equipment vibration qualification for Harrier and The dynamic qualification of equipment and Hank aircraft external stores for use with rotary winged 882-22161 aircraft TBOBMIOB, B. A. 882-22167 Finite element thermal analysis of TBBGBZ, P. L. convectively-cooled aircraft structures Optimal control and estimation for strapdown A82-28565 seeker guidance of tactical missiles XIFFABI, S. fl. A82-31121 Control lav design to Beet constraints using 7BB6SB. B. SIHPAC-synthesis package for active controls A review of recent AGABD Symposia on the Angle of [HASA-TH-83264] 1182-22280 Baneuverability of Combat Aircraft TIGSE1AAB. J. J. 882-22188 Calculation of the contributions of air traffic flEIS, H. and toad traffic to air pollution in the region Unsteady ejectors of Schiphol airport in 1974 882-23171 [BLB-TB-77100-0] H82-22808 TOBBETH, B. D, TILL, B. D. Controls and displays for all-weather operation of The helicopter Havstar GPS test program helicopters 482-31290 IBBB-OD-319-81-0] B82-22260 TOHABO, 0. J. TOILLBI, A. Extravehicular Activity/Air Traffic Control Aerospatiale survey of wind tunnel testing of (EVA/ATC) test report small and large scale rotors [HASA-CB-167600] H82-23381 [SBIAS-821-210-107] H82-22225 TOBBLLA. 6. rOIGAEOT, E. B. Turboprop and turbojet ejector optimisation Aviation gear drives and reducers: Bandbook 882-23174 A82-30675 TOBBBS. B. Concept studies of an advanced composite helicopter fin w [SBI4S-821-210-106] H82-22257 IADDOOPS., Bo B. TBIPLBTT. g. B. Integration of avionics and advanced control Pressure measurements on twin vertical tails in technology buffeting flow H82-22194 [AIA4 82-0641) A82-30138 1A1DHA8, 0. TBISTBABT. 0. B. SPF of high strength aluminum structures State of the art and recent perspectives on the A82-28997 study of the loss of control and spin iALKBB, D. J. H82-22197 Enhanced piloting control through cockpit IOBBBB, H. G. facilities and i.C.T. Powder metallurgical innovations for iaproved hot B82-22195 section alloys in aero-engine applications IALKBB, J. G. [PHB-90072] H82-22358 Comparing the relationships between noise level TDBBBB, 8. I. and annoyance in different surveys - A railway Composite materials noise vs. aircraft and road traffic comparison A82-28590 A82-29165 TIBEB, C. BABBILL, B. J. B. Hague tic anomalies as a reference for ground-speed Some case studies and the significance of fatigue and nap-matching navigation thresholds A82-30314 [HIB-BP-81015-0] H82-23561 •AIBBS. C. Active control of aeroelastic divergence u [AIAA 82-0684] A82-30151 OBAIK. B. Transonic flutter study of a wind-tunnel model of Powder metallurgical innovations for iaproved hot a supercritical wing with/without winglet section alloys in aero-engine applications IAIAA 82-0721] A82-30171 tPHB-90072] H82-22358 Transonic flutter study of a wind-tunnel model of ODEA, I. a supercritical wing with/without winglet Flutter analysis using nonlinear aerodynamic forces IHASA-TB-83279] H82-23239 [AIAA 82-0728] A82-30176 1AISOH, J. J. OU2B, B. Evaluation of four subcritical response methods A theoretical study of the impact of aircraft wake for on-line prediction of flutter onset in vortices on roofs in the final approach area of wind-tunnel tests Dusseldorf airport tAIAA 82-0644] A82-30140 £DF?lB-HITT-82-01] H82-23560 Evaluation of four subcritical response methods OLVSABD, I. for on-line prediction flutter onset in BADIAK simulator for aircraft instrunents wind-tunnel tests [FOA-C-40136-A3] H82-22286 CHASA-TH-83278] H82-23240 IAIHOB, G. B. Development of vibration qualification test spectra for the F-15 aircraft H82-22160

B-14 FEBSOBU. 4D1HOB IBDBX ZAZHIGIB, 4. A. iEBEB, J. B. BIITLIH, G. An analysis of a nonlinear instability in the Analysis of aircraft dynamic behavior in a crash implementation of a VIOL control system environment [HASA-TB-8II220] H82-22281 [AIAA 82-0.694] A82-30161 Results of NASA/FAA ground and flight simulation BOHG, 0. G. experiments concerning helicopter IFE Integrated structural analysis and design support airworthiness criteria for advanced launch vehicles H82-23219 [AIAA 82-0675] 482-30144 BBBBB, 0. BOH6HIHAI, K. A theoretical stud; of the impact of aircraft wake A comparison of properties of single overlap vortices on roofs in the final approach area of tension joints prepared by ultrasonic welding Ousseldorf airport and other means [DFVLB-HIl'T-82-01] H82-23560 [AIAA 82-0661] A82-30091 BBISSHAAB, I. A. BOBBBBBEBG, H. Flutter of forward swept wings, analyses and tests Experimental flight test programs for improving [AIAA 82-0646] A82-30142 combat aircraft maneuverability by maneuver BELIE, 0. flaps and pylon split flaps Experimental flight test programs for improving B82-22192 combat aircraft maneuverability by maneuver BOOD, L. J. flaps and pylon split flaps Comment on 'Optimal control via mathematical H82-22192 programming' •£•01, J. 0. L. A82-31125 NOx formation in flat, laminar, opposed jet BOODCOCK. B. J. methane diffusion flames The military flying qualities specification, a A82-28660 help or a hindrance to good fighter design HESTBHAl, 6. H82-22190 Flight simulators HOOLBB, f. I. A82-29924 Tail configurations for highly maneuverable combat BHITIOH, B., JB. aircraft Application of a transonic potential flow code to N82-22201 the static aeroelastic analysis of HOBTMAHH, J. three-dimensional Kings Bepair and regeneration of turbine blades, vanes [AIAA 82-0689] A32-30156 and discs Application of a transonic potential flow code to N82-22185 the static aeroelastic analysis of BIKES. D. B. three-dimensional vings Development and demonstration of manufacturing [HASA-TH-83296] H82-23193 processes for fabricating graphite/LABC 160 Time-marching transonic flutter solutions polyimide structural elements including angle-of-attack effects [HASA-CB-165809] B82-22315 [HAS4-TM-83295] N82-23196 HIKES. J. B. BHIITBH, P. D. Bigid body-structural mode coupling on a forward Hind-tunnel investigation of the powered low-speed swept ving aircraft longitudinal aerodynamics of the [AI4A 82-0683] A82-30150 Vectored-Engiue-Over (VEO) wing fighter BIHBB, B. C. configuration Measured and calculated effects of angle of attack [HASA-Tfl-83263] H82-22207 on the transonic flutter of a supercritical wing BIDHAXBB, E. [AIAA 82-0647] A82-30143 Commercial jet transport crashworthiness Static and unsteady pressure measurements on a 50 [HASA-CH-165849] N82-23207 degree clipped delta wing at M = 0.9 BIEGHABDT, K. [AIAA 82-0686] A82-30153 Studies on wind tunnel straighteners Static and unsteady pressure measurements on a 50 [HASA-TH-76689] B82-22284 degree clipped delta wing at H = 0.9 ilBBZBA, I. [HASA-TM-83297] H82-23195 The combustion of a fuel jet in a stream of lean gaseous fuel-air mixtures A82-28692 SIETIHG, A. B. IADIH, B. Finite element thermal analysis of Distributed airborne array concepts convectively-cooled aircraft structures A82-31669 A82-28565 XABG, 1. I. BILBI, B. G. Transonic time-response analysis of three D.O.F. Analytical prediction of the interior noise for conventional and supercritical airfoils cylindrical models of aircraft fuselages for [AIAA 82-0688] A82-30155 prescribed exterior noise fields. Phase 2: IATBS, E. C., JB. Models for sidewall trim, stiffened structures Measured and calculated effects of angle of attack and cabin acoustics with floor partition on the transonic flutter of a supercritical wing [HASA-CB-165869] B82-22952 [AIAA 82-0647] A82-30143 BILDGOOSE, P. Subsonic aerodynamic and flutter characteristics Powder metallurgical innovations for improved hot of several wings calculated by the SOUSSi P1.1 section alloys in aero-engine applications panel method [PHB-90072] H82-22358 [AIAA PAPEB 82-0727] 482-30193 HILKIBSOB, H. 0. IEH, J. G. Prototype flywheel spin testing program Component coupling with time-invariant mass matrix [UCEL-15381] B82-22499 for nonisotropic rotating and nonrotating systems 1IIS01, 0. B. [AIAA 82-0731] A82-30179 737 graphite-epoxy horizontal stabilizer certification [AIAA 82-0745] A82-30109 BILSOI, J. S. ZACHABIAS, A. A computerized system for the application of An experimental and theoretical investigation of fracture tracking data to aircraft management the interaction between the engine jet and the for the C-5A military airlift transport surrounding flow field with regard to the [AIAA 82-0760] A82-30119 pressure drag on afterbodies BIBSXABLBI, A. I. M82-23158 Development cf a convoluted intake seal for model ZAZHIGIH, A. A. B66 Design principles of a computer-aided design system [BAE-ABG-163] N82-23255 A82-29829

B-15 ZB6EBB. C. V. PEBSOI1L AOIHOB IHDEX

ZESEEB, C. f. Paveaent nanagenent and rehabilitation of Portland cement concrete paveoents [PB82-131384] H82-22392 ZEZLBB, X. A. Flatter of forward stiept wings, analyses and tests [Alii 82-0646] £82-30142 ZBLLBB, J. The role of nodern control theory in the design of controls for aircraft turbine engines [HASA-TH-82815] H82-22262 ZIUBBBAH, B. Aircraft fuel tank slosh and vibration test H82-22164 ZIS1I1, i. H. Active contrcl of aeroelastic divergence [AIAA 82-0684] A82-30151 ZHBOCZBK, 1. A. Advanced general aviation engine/airfraae integration study [HASA-CB-165565] H82-22268 ZiAAl, B. J. Aeroelastic properties of vings in transonic flov [HLB-aP-81005-0] N82-22224

B-16 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 151) AUGUST 1982

Typical Contract Number Index Listing

CONTRACT NUMBER

HAS1-14693 B82-10028

Listings in this index are arranged alphanumerically by contract number. Under each contract number, the accession numbers denoting documents that have been produced as a result of research done under that contract are arranged in ascending order with the IAA accession numbers appearing first. The accession number denotes the number by which the citation is identified in either the IAA or STAR section.

AF-AFOSB-78-3688 HAS2-10278 H82-22244 AS 2-31669 NAS2-10361 H8 2-22228 AF-APOSB-81-0057 NAS2-10400 M82-22248 A82-30107 H8 2-22249 AF-AFOSB-81-0123 B82-22250 A82-30176 MAS2-10767 082-24050 AF-AFOSB-0025-81 NAS3-20646 H82-22264 N8 2-23171 NAS3-20821 H82-22265 AF-AFOSB-0042-72 HAS3-22220 N82-22268 H8 2-22193 NAS3-22221 N8 2-22263 BBFT-LFK-7960-9 8AS3-22369 H82-22211 H82-23252 HAS3-22518 N82-23248 H82-23253 HAS3-22524 H82-22267 DA PSOJ. 1L1-61102-AH-45 BAS3-22739 N82-23246 H82-22251 NAS7-100 A82-31125 DAAG29-78-C-0027 NAS8-33821 B82-23249 H82-23250 NAS9-15800 H82-23381 DAAG29-78-G-0039 HSG-1498 N82-22398 A82-29042 HSG-1561 H82-22206 EPA-8-803715 A82-28660 HSG-1584 B82- 23238 EPA-68-02-2631 HSG-1605 A82-30114 AS 2-28660 HSG-1624 882-22209 F33615-76-C-5220 HSG-2179 B82-23221 A82-29032 NSG-3048 N82-23247 F33615-77-C-5155 NSG-4019 H82-23245 A82-30172 H00014-79-C-0130 F33615-78-C-3616 M82-23166 N82-22191 B62269-76-C-0086 F33615-78-C-5121 B82-23166 A82-28995 SBC-B/BG/3777/3 F33615-80-C-3217 482-29165 A8 2-30111 B-7405-EHG-48 A82-30173 H82-22499 BAG1-112 882-22947 505-03-22 B82-22265 NAG1-168 A82-30168 505-31-43-03 B82-22217 NAG2-19 K82-22240 505-31-83-02 N82-23233 NAG4-1 1182-22193 505-32-2A S82-22269 SASI-3541 B82-22284 505-32-03-01 H82-22955 HASH-3542 H82-22246 505-33-52-01 B82-23239 SB 2-22247 505-33-53-07 H82-23193 HAS1-11621 N82-22316 B82-23194 HAS1-11668 H82-22314 N82-23196 .HAS1-12308 A82-30087 505-33-63-02 S82-22245 HAS1-15371 H82-22315 505-34-33-05 B82-22280 HAS1-15782 N82-22952 505-35-31 B82-22478 BAS1-16000 H82-22949 505-42-23-01 H82-22251 NAS1-16076 1182-23207 505-42-71 882-22281 SAS1-J6111 S3 2-22227 882-23234 HAS 1-16205 H82- 22213 B82-23235 BAS1-16420 H82-22252 505-43-13-01 H82-22213 HAS2-5589 H82-22243 505-43-23-04 H82-22207 HAS2-8954 H82-22238 505-43-33-01 B82-23240 NAS2-9646 N82- 23166 505-44-13-02 H82-22848 NAS2-9883 H82-23234 505-44-33-01 H82-23244 H82-23235 506-53-63-05 B82-23471 UAS2-10184 M82-23166 532-03-11 882-22228 534-04-13-54 B82-22239

C-1 y 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037 (151) 4. Title and Subtitle 5. Report Date August 1982 Aeronautical Engineering 6. Performing Organization Code A Continuing Bibliography (Supplement 151)

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, DC 20546 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address

14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract

This bibliography lists 362 reports, articles and other documents introduced into the NASA Scientific and Technical Information System in July 1982.

17. Key Words (Suggested by Author(s)) 18. Distribution Statement Aerodynamics Aeronautical Engineering Unclassified - Unlimited Aeronaut ics Bibliographies

19. Security dassif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price*

Unclassified Unclassified 118 $5.00 HC

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