Aeronautical NASA SP-7037(123) Engineering June 1980 A Continuing N/\SA Bibliography with Indexes
National Aeronautics and Space Administration CASE FILE (;OPY Aeronautical Engineering Ae ering Aeronautical E igineering Aeronautical Engir mi Engineering Aeronautical I nautical Engineering AeruFai Aeronautical Engineering Aeu ?ring Aeronautical Engineerin gineering Aerorautical Engin aronautil Engineering,. cal E i Engineering Aeronai mtautical Engineering Aen ring Aeronautical Engineerim ACCESSION NUMBER RANGES
Accession numbers cited in this Supplement fall within the following ranges.
STAR (N-10000 Series) N80-17981 - N80-20022
!AA (A-I0000 Series) A80-24721 A80-28952
This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by PRC Data Services Corn pa ny NASA SP-7031(123)
AERONAUTICAL ENGINEERING
A Continuing Bibliography
Supplement 123
A selection of annotated references to unclas- sified reports and journal articles that were introduced into the NASA scientific and tech- nical information system and announced in May 1980 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (/AA).
Scientific and Technical Information Branch 1980 NfGA National Aeronautics and Space Administration Washington, DC INTRODUCTION
Under the terms of an interagency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering. The first issue of this bibliography was published in September 1970 and the first supplement in January 1971. Since that time, monthly supplements have been issued. This supplement to A eronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 529 reports, journal articles, and other documents originally announced in May 1980 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 (A80-10000 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 $7.00 per document up to a maximum of 40 pages. The charge for each additional page is $0.25. Microfiche ' of documents announced in IAA are available at the rate of $3.00 per microfiche on demand, and at the rate of $1.25 per microfiche for standing orders for all IAA microfiche. The price for the /AA microfiche by category is available at the rate of $1.50 per microfiche plus a $1.00 service charge per category per issue. Microfiche of all the current AIAA Meeting Papers are available on a standing order basis at the rate of $1.50 per microfiche.
Minimum air-mail postage to foreign countries is $1.00 and all foreign orders are shipped on payment of pro-forma invoices.
All inquiries and requests should be addressed to AIAA Technical Information Service. Please refer to the accession number when requesting publications.
STAR ENTRIES (N80-10000 Series)
One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviations are listed below. If the publication is available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line.
Avail: NTIS. Sold by the National Technical Information Service. Prices for hard copy (HC) and microfiche (MF) are indicated by a price code followed by the letters HC or MF in the STAR citation. Current values for the price codes are given in the tables on page viii.
Documents on microfiche are designated by a pound sign (#) following the accession number. The pound sign is used without regard to the source or quality of the microfiche.
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.
Avail: SOD (or GPO). Sold by the Superintendent of Documents, U.S. Government Printing Office, in hard copy. The current price and order- number are given following the availability line. (NTIS will fill microfiche requests, at the standard $3.50 price, for those documents identified by a symbol.)
(1) A microfiche is a transparent sheet of film. 105 by 148 mm in size, containing as many as 60 to 98 pages of information reduced to micro images (not to exceed 26:1 reduction). iv Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration, Public Documents Room (Room 126). 600 Independence Ave., SW., Washington. D.C. 20546, or public document rooms located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Office at the Jet Propulsion Laboratory.
Avail: DOE Depository Libraries. Organizations in U.S. cities and abroad that maintain collections of Department of Energy reports. usually in microfiche form, are listed in Energy Research Abstracts. Services available from the DOE and its depositories are described in a booklet. DOE Technical Information Center - Its Functions and Services (TID-4660). which may be obtained without charge from the DOE Technical Information Center.
Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Dissertation Abstracts and are sold by University Microfilms as xerographic copy (HC) and microfilm. All requests should cite the author and the Order Number as they appear in the citation.
Avail: USGS. Originals of many reports from the U.S. Geological Survey, which may contain color illustrations, or otherwise may not have the quality of illustrations preserved in the microfiche or facsimile reproduction, may be examined by the public at the libraries of the USGS field offices whose addresses are listed in this introduction. The libraries may be queried concerning the availability of specific documents and the possible utilization of local copying services, such as color reproduction.
Avail: HMSO. Publications of Her Majesty's Stationery Office are sold in the U.S. by Pendragon House. Inc. (PHI). Redwood City, California. The U.S. price (including a service and mailing charge) is given, or a conversion table may be obtained from PHI.
Avail: BLL (formerly NLL): British Library Lending Division, Boston Spa, Wetherby, Yorkshire, England. Photocopies available from this organization at the price shown. (If none is given, inquiry should be addressed to the BLL.)
Avail: Fachinformationszentrum, Karlsruhe. Sold by the Fachinformationszentrum Energie.Physik, Mathematik GMBH, Eggenstein Leopoldshafen, Federal Republic of Germany. at the price shown in deutschmarks (DM).
Avail: Issuing Activity, or Corporate Author, or no indication of availability. Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document.
Avail: U.S. Patent and Trademark Office. Sold by Commissioner of Patents and Trademarks. U.S. Patent and Trademark Office, at the standard price of 50 cents each, postage free.
Other availabilities: If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line.
v GENERAL AVAILABILITY
All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and /AA Entries sections. It is suggested that the bibliography user contact his own library or other local libraries prior to ordering any publication inasmuch as many of the documents have been widely distributed by the issuing agencies, especially NASA. A listing of public collections of NASA documents is included on the inside back cover.
SUBSCRIPTION AVAILABILITY
This publication is available on subscription from the National Technical Information Service (NTIS). The annual subscription rate for the monthly supplementsis$50.00 domestic; $10000 foreign. All questions relating to the subscriptions should be referred to NTIS. Attn: Subscrip- tions, 5285 Port Royal Road, Springfield Virginia 22161.
vi ADDRESSES OF ORGANIZATIONS
American Institute of Aeronautics Pendragon House. Inc. and Astronautics 899 Broadway Avenue Technical Information Service Redwood City, California 94063 555 West 57th Street, 12th Floor New York, New York 10019 Superintendent of Documents U.S. Government Printing Office British Library Lending Division, Washington, D.C. 20402 Boston Spa, Wetherby. Yorkshire, England University Microfilms Commissioner of Patents and A Xerox Company Trademarks 300 North Zeeb Road U.S. Patent and Trademark Office Ann Arbor, Michigan 48106 Washington, D.C. 20231
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Her Majesty's Stationery Office U.S. Geological Survey P.O. Box 569, S.E. 1 601 E. Cedar Avenue London, England Flagstaff, Arizona 86002
NASA Scientific and Technical Information U.S. Geological Survey Facility 345 Middlefield Road P.O. Box 8757 Menlo Park, California 94025 B. W. I. Airport, Maryland 21240
National Aeronautics and Space U.S. Geological Survey Administration Bldg. 25, Denver Federal Center Scientific and Technical Information Denver, Colorado 80225 Branch (NST-41) Washington, D.C. 20546 Fachinformationszentrum Energie, Physik, National Technical Information Service Mathematik GMBH 5285 Port Royal Road 7514 Eggenstein Leopoldshafen Springfield, Virginia 22161 Federal Republic of Germany
vii NTIS PRICE SCHEDULES
Schedule A STANDARD PAPER COPY PRICE SCHEDULE
(Effect.ne January 1. 1980)
Price Page N s Iaeth A.nsdcsn Foeon Cads Price Price AOl Microfiche S 350 $ 5.25 A02 001.025 5.00 10,00 A03 026050 6.00 1200 A04 051075 1.00 14.00 A05 016-100 800 16.00 A06 101-125 9.00 1800
AOl 126-150 10.00 20.00 A08 151-115 1100 2200 A09 116-200 12.00 2400 Al)) 201-225 1100 26.00 All 226-250 1400 28,00
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All 376-400 20.00 4000 A18 401-425 21.00 42.00 A19 426-450 2200 44.00 A20 451-475 2300 4600 A21 476-500 24.00 4800
A22 501-525 2500 5000 A23 526-550 2600 52.00 A24 551-575 21.00 54.00 A25 576-600 26.00 56.00 A99 601-op -- 1/ -- 2/
1/ Add $1.00 for each additional 25 page increment or portion thereof for 601 pages op.
2/ Add $2.00 for each additional 25 page increment or portion thereof for 601 pages and more
Schedule E EXCEPTION PRICE SCHEDULE Paper Copy & Microfiche
Pyle. North American Fansig., Cad. Pile. Pile. (01 S 5.50 $ 1150 (02 6.50 13.50 (03 8.50 1750 (04 10,50 21,50 (05 12.50 2550
(06 14.50 29.50 (01 1650 33.50 (08 18.50 3150 E09 20.50 41.50 610 22.50 45.50
(11 24.50 4950 E12 27.50 5550 (13 3050 61.50 (14 33.50 61.50 E15 38.50 1350
(16 39.50 - 19.50 (11 4250 6550 (18 45.50 91,50 (19 50.50 100,50 EZO 6050 12150
(99 - Write for goose NOl 28.00 40,00
viii
TABLE OF CONTENTS
IAAEntries ...... 189 STAREntries ...... 219
SubjectIndex ...... A-i Personal Author Index ...... B-i Contract Number Index ...... c-i
TYPICAL CITATION AND ABSTRACT FROM STAR
NASA SPONSORED DOCUMENT AVAILABLE ON MICROFICHE NASA ACCESSION N80-1014.8# Northwestern Univ.. Evanston. Ill. Transportation NUMBER______Center, FACTORS AFFECTING THE RETIREMENT OF COM- CORPORATE MERCIAL TRANSPORT JET AIRCRAFT SOURCE Frank A. Spencer Aug. 1979, 296 refs IV TITLE(Grant N5G-2149( Avail. NTIS HC A13/MF AOl -- PUBLICATION CSCLO1C The historical background of the technology and economics DATE AUTHOR of aircraft replacement and retirement in the prejet era is reviewed 1 in order to determine whether useful insights can be obtained applicable to the Jet era. Significant differences between the AVAILABILITY CONTRACT two periods are noted New factors are identified and examined SOURCE OR GRANT J Topics discussed include concern Over current policies regarding deregulation, regulatory reform, and retroactive noise regulations; financing and compliance legislation; aging; economic environment REPORT and inflation; technological progress; fuel efficiency and cost; COSATI NUMBER and a financial perspective of replacement decisions A.R.H. CODE
TYPICAL CITATION AND ABSTRACT FROM fAA
AVAILABLE ON V MICROFICHE AIAA ACCESSION A80-10196 /' Effect of flow swirling on heat transfer in the NUMBER i-... cylindrical part of the prenozzle volume of a model chamber (Vliianie zakrutki potoka na teplootdachu v tsilindricheskoi chasti predsoplovogo ob'ema model'noi kamery). F. I. Sharafutdinov, A. I. TITLE ______- AUTHORS Mironov, and V. K. Shchukin (Kazanskii Aviatsionnyl Institut, ...... ______Kazan, USS.R Inzhenerno. Fizicheskii Zhurna/, vol. 37, Oct. 1979, AUTHOR'S TITLE OF p. 595. 601,8 refs, In Russian. AFFILIATION PERIODICAL Experimental results are presented on the hydrodynamics and heat transfer in swirling flow in a short orificed tube with PUBLICATION straight-blade turbilizers. Data are correlated by the local simulation DATE method, employing the maximum axial component of wall gas velocity and the torque momentum/axial momentum ratio at the turbilizer outlet. B.J.
ix
AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 123)
JUNE 1980
An investigation has been conducted into the effects of emulsion characteristics on the flame structure of pure Jet A fuel, Jet A fuel and surfactant blend, and Jet A fuel . waser-surfactant emulsion IAA ENTRIES sprays burning over an air-blast atomizer in quiescent and swirling surroundings. The effects of surfactant concentration and water concentration on the characteristics of emulsions, flame stability, axial and radial temperature profiles, the total radiation emitted, and A80-24739 NAVAIR pushes SPF/DB for structures. W. T. the soot concentration are documented. It is concluded that the Highberger (U.S. Naval Air Systems Command, Engineering Support addition of surfactant alone to fuel changes the flame characteristics very slightly, whereas changes in both surfactant and water concen- Management Div., Washington, D.C.). ManTech Journal, vol. 4, no. 1, 1979. p. 36-39. trations in emulsions affect the flame structure considerably. Superplastic forming/diffusion bonding (SPF/DB) of titanium (Author) alloys is discussed with regard to NAVAIR applications, including missile technology. Fine grain size is easily obtained using titanium A80-24819 Local laminarization in turbulent diffusion alloys, which have the capacity for self diffusion bonding at SPF flames. T. Takafi, H.-D. Shin, and A. lshio (Osaka University, Suita, temperatures; the diffusion bonds are self inspecting. Project plans at Japan). Combustion and Flame, vol. 37, Feb. 1980, p. 163-170. 11 NAVAIR for SPF/DB include demonstrating an ultrahigh strength refs. SPF/DB titanium sandwich construction, making a glove vane for the The turbulence in round fuel jets with and without flame is F. 14, and constructing bubble core sandwich panels of graduated examined experimentally considering the characteristic difference of weights and corresponding mechanical strengths. J.P.B. turbulence due to the existence and nonexistence of flame. Measure- ments of flow velocity, turbulence intensity, gas temperature and species concentration are carried Out and quantitative verification is A80-24740 Fiberglass rotor produced, P. S. Baumgardner presented for the effects of flame on turbulence. Visual study by (Bell Helicopter Textron, Fort Worth, Tex.). ManTech Journal, vol. schlieren photography shows the local laminarizasion phenomena 4, no. 1, 1979, p. 45.48. due to the existence of flame at lower nozzle flow Reynolds number The design and manufacture of fiberglass helicopter rotor blades and the apparent taminarization which exists pertinaciously even at are discussed. Fiberglass blades (FBs) offer higher fatigue strength higher Reynolds number in the outer layer just near the nozzle exit. than conventional metal blades, as well as insensitivity to small (Author) defects, gradual failure modes, freedom from corrosion, and damage tolerance. Blades were not damaged structurally by lightning strikes of 200,000 amperes, and passed a ballistics test by swallowing a 23 A80-24899 Increasing aircraft efficiency through laminar mm high explosive impact round rather than permitting it to exit. In flow control. R. Cotta. Aviation Engineering and Maintenance, vol. 4, Jan. 1980, p. 12-15. the manufacture of FBs, upper and lower spar caps are wound on an orbital pin winding machine, and a filament winding machine is used The article discusses recent work in improving laminar flow in order to reduce drag and thereby overall fuel consumption. Atten- for the trailing edges and the inner and outer torque tubes, J.P.B. tion is given to NASA's laminar flow control project )LFC), the object of which is to demonstrate that the technology required to incorporate LFC into long-range commercial jet transports of the A80-24746 Optical design of airport control tower cabs. P. 1990's is available. Discussion covers LFC aircraft configurations D. Carman and H. W. Budde (National Research Council, Div. of proposed by Boeing, Lockheed, and Douglas. Also covered are Physics, Ottawa, Canada). Applied Optics, vol. 19, Feb. 15, 1980, p. computer aided design, possible materials, and compromises for 490-498. maintenance access. Finally attention is given to losses in aero- A study has been made of optical aspects of airport control dynamic efficiency which stem from insect accumulation of wind towers as part of a planned general optimization of control towers by leading edges, dents, mismatched surface panels, and leaking pressuri- Transport Canada. Problems found were reflections, glare, visual zation of aerodynamic seals. M.E.P. obstructions, identification of distant objects, and excessive solar heat. The study makes recommendations on cab shape, tower height, A80-25059 Rain erosion of lightning protection coatings glazing, shades, sunglasses, binoculars, and internal lighting. Proper for carbon fibre composites. H. W. Schrbder )Dornier System GmbH, choice of cab shape (e.g., 30 deg window inclination and 12-28 sides) Friedrichshafen, West Germany). In: International Conference on provided effective control of reflections. Some plastic shades were Erosion by Liquid and Solid Impact, 5th, Cambridge, England, found to increase the risk of eye damage. Two tower cabs September 3-6, 1979, Proceedings. Cambridge, incorporating the recommendations have been built and were found Cambridge University, 1979, p. 74-1 to 74-8. 7 refs. to be satisfactory. (Author) In the future large parts of the outer skin of aircraft will be made of carbon fibre composites. In areas where the probability of lightning strikes is high, carbon fibre materials have to be protected A80-24817 Characteristics of burning Jet A fuel and Jet A by lightning protection systems. The erosion resistance of different fuel-water emulsion sprays. H. Jahani and S. R. Gollahalli (Okla- lightning protection systems consisting of aluminum foils, flame- homa, University, Norman, Okla.). Combustion and Flame, vol. 37, sprayed aluminum, aluminum-mesh and metal powder loaded paints Feb. 1980, p. 145-154. 18 refs. was investigated, using a rotating arm apparatus. In the same way,
189 A80-25093
the use of polyurethane coatings for enhancing the rain erosion An error model for precise time transfer using GPS is presented in resistance was investigated. (Astrocoat 7100 and 7200, Chemglaze terms of satellite clock and ephemeris prediction errors, user position M213 and M313 and ICI F407-636). Special attention was paid to and clock errors, atmospheric errors, and random noise. Expected the influence of the drop diameter and to the different modes of time transfer errors for the operational GPS user are less than 100 ns B.J. failure which were observed. (Author) relative to UTC and less than 30 ns relative to GPS time. A80-25149 Applications of the spread-spectrum signals A80.25093 A rotary inverter system for a multiple. A' II from the NOVA satellites. E. F. Prozeller (Johns Hopkins University, electrode MHD generator. C. S. J. Lamb, S. Ramakrishnan, and H. K. Laurel, Md.). In: Navigation satellite users; Proceedings of the Messerle (Sydney, University, Sydney, Australia). In: Symposium on National Aerospace Symposium, Springfield, Va., March 6-8, 1979. the Engineering Aspects of Magnetohydrodynamics, 18th, Butte, Washington, D.C., Institute of Navigation, 1979, Mont., June 18. 20, 1979, Preprints. Bozeman, p. 93-100. 9 refs. Mont., Montana State University, 1979, p. F.2.1-F.2.3. High-precision timing signals from the NOVA satellites will offer Coupling of magnetohydrodynamic generators to existing power several new options to a Transit system user. Experiments using grids requires dc to ac conversion. Most of the present day research spread-spectrum signals from TIP satellites (prototypes of the teams are considering the use of solid-state inverters for this task. In production NOVA satellites) have demonstrated the use of these this paper, a rotary inverter system is proposed which makes use of a signals for real-time ionospheric correction, worldwide time dissemi- parallel-connected rotary motor driving a conventional alternator. nation fron a single satellite, and the elimination of interference The advantages are direct connection to a multiple-electrode MHD between covisible satellites. This paper discusses the characteristics of generator, simple construction, and easy operation. (Author) the NOVA spread-spectrum signals and describes typical ground equipment modifications that allow simple recovery of the new A80-25141 Navigation satellite users; Proceedings of the precision ranging/timing signals. B.J. National Aerospace Symposium, Springfield, Va., March 6-8, 1979. Symposium sponsored by the Institute of Navigation. Washington, A80-25157 A' A collision avoidance system using Navstar/ D.C., Institute of Navigation, 1979. 218 p. GPS and ATCRBS. P. S. Noe (Texas A & M University, College Station, Tex.) and A. W. Yendrey (U.S. Navy, Naval Training Center, Topics addressed include shipboard antenna tests for GPS; the Orlando, Fla.(. In: Navigation satellite users; Proceedings of the use of Transit for time dissemination; geodetic uses of the NNSS by National Aerospace Symposium, Springfield, Va., March 6-8, 1979. European agencies; the role of navigation satellites in oil exploration; Washington, D.C., Institute of Navigation, 1979, the outlook for she GPS in civil aircraft operations; and GPS satellite p. 157-160.26 refs. selection for sequential receivers. Also discussed are NNSS applica- The proposed airborne collision avoidance system, based on the tion research in Japan, a collision avoidance system using GPS and use of the Navstar/GPS navigation satellite system, can determine the ATCR BS, and ionospheric measurements from Navstar satellites. aircraft position with an accuracy of 10 to 100 meters. Position data B.J. will be transmitted on an unassigned civil mode (mode 0), using the ATC Radar Beacon System. The design can be economically A80-25143 # Navstar field test results. D. W. Henderson and implemented for aircraft equipped with a GPS receiver and a beacon J. A. Strada (USAF, Space and Missile Systems Organization, El transponder, with collision avoidance warning provided by ground Segundo, Calif.). In: Navigation satellite users; Proceedings of the control. A beacon receiver could also be designed, based on National Aerospace Symposium, Springfield, Va., March 6-8, 1979. avoidance algorithms, which would automatically provide the pilot Washington, D.C., Institute of Navigation, 1979, warning. It is shown that the proposed system is more economical p. 8-44. than other collision avoidance concepts. V. L. After a brief description of the Navstar Global Positioning System the paper presents some of the significant field test results. Attention is given to Navstar accuracy, the landing approach, A80.25158 A' Outlook for Global Positioning System /GPS/ rendezvous, shipboard operations, foliage attenuation, and time in civil aircraft operations. D. J. Sheftel (FAA, Washington, D.C.). transfer. The results are summarized in a series of figures. B.J. In: Navigation satellite users; Proceedings of the National Aerospace Symposium, Springfield, Va., March 6-8, 1979. A80-25144 A' Shipboard antenna tests for GPS. R. W. Major Washington, D.C., Institute of Navigation, 1979, p. 161, 162. and R. M. Akita (U.S. Naval Ocean Systems Center, San Diego, The evaluation of the GPS for use in domestic and international Calif.). In: Navigation satIlite users; Proceedings of the National civil aviation by the Federal Aviation Administration (FAA) is Aerospace Symposium, Springfield, Va., March 6-8, 1979. discussed. Operational and economic reasons for the replacement of Washington, D.C., Institute of Navigation, 1979, p. present systems (primarily VORTAC) with the GPS are considered, 45-56. 5 refs. and the performance, cost, compatibility, operational suitability and Shipboard antenna tests for the Global Positioning System institutional requirements for a replacement system are indicated. (GPS( were performed to determine the multipath effects on a The FAA program currently under way to investigate these factors is prototype antenna for submarine use and to compare the perfor- outlined, and it is predicted that, with a basic finding on the mance of prototype surface ship GPS antennas. This paper describes suitability of the GPS for civil aviation arrived at by 1983 and a final the details of planning, installation, testing, and analysis of test selection for a VORTAC replacement made by 1985, an official results; in-plant, dockside, and at-sea tests are discussed. B. J. system change on national and international basis can be accom- plished by 1995. A.L.W.
A80.25146 II The Navstar Global Positioning System and A80-25162 II On-board precision approach system using time. D. J. Henson, J. T. Dolloff, and D. D. Thornburg (General NAVSTAR GPS. R. E. Harper (OAO Corp., Atlantic City, N.J.). In: Dynamics Corp., Electronics Die., San Diego, Calif.). In: Navigation Navigation satellite users; Proceedings of the National Aerospace satellite users; Proceedings of the National Aerospace Symposium, Symposium, Springfield, Va., March 6-8, 1979. Springfield, Va., March 6-8, 1979. Washington, Washington, D.C.. Institute of Navigation, 1979, p. 183-188. 5 refs.
D.C., Institute of Navigation, 1979, p. 65-73. The paper describes a model used to verify the feasibility of a The GPS uses a network of highly stable spaceborne and method of providing an IFR precision approach system, using the ground-based atomic clocks. This paper describes the precise time Global Positioning System, to replace or supplement the existing ILS and time interval characteristics of GPS; a method of using GPS system. Similarly the method described could be used to replace or precise time transfer both for users with accurately known locations supplement the MLS system (under development at this time). The and for users requiring GPS for both position and time is considered. technique described uses an on-board computer and a GPS receiver
190
A80-25448
to establish a flight path and glide s ' ope for a landing aircraft. The aerodynamicznej). D. Konopska and I. Osipiak-Chmielewska. Insty- computer uses GPS receiver input data and information which could tut Lotnictwa, Prace, no. 77-78. 1979, p. 139-153. 5 refs. In Polish. be entered via keyboard or magnetic strip, as well as resident data The system described will measure simultaneously the pitching, base within the on-board computer that contains dynamic vehicle rolling, and yawing moments, the three force components, the parameters. (Author) ambient temperature, and the chamber temperature. The data are printed and recorded on perforated tape. V. P. A80-25164 # On the NNSS application research in Japan. K. Kimura, S. Nishi, and H. Nasu (Ministry of Transport, Electronic Navigation Research Institute, Tokyo, Japan). In: Navigation satellite A80.25245 # The re-organization of airport administration users; Proceedings of the National Aerospace Symposium, Spring- in Canada. D. Varty. In: Annals of air and space law. Volume 4. field, Va., March 6-8, 1979. Washington, D.C., Montreal, McGill University; Toronto, Carswell Institute of Navigation. 1979, p. 191-197. 5 refs. Co., Ltd.; Paris, Editions A. Pedone, 1979, p. 359-365. ii refs. The paper presents several studies carried out by the Electronic The centrally controlled administrative organization of Canada's Navigation Research Institute, Japan, concerning the Navy Navi- airports is discussed, as well as the changes recommended by a Task gation Satellite System (NNSS). Evaluation of the actual receiving Force on Airport Management )TFAM). The objectives of the TFAM system installed at an automated tanker is outlined along with the included finding a management structure that emphasized local study of the NNSS position-fixing accuracy of different parameters. autonomy, financial viability, managerial efficiency, effectiveness The results of a three-dimensional positioning experiment are and accountability, with the constraint that land ownership at discussed and application of the Kalman filter technique to the principal airports remain federal. To provide more local direction of NNSS-Omega Hybrid Navigation System is also investigated. V. T. operations at each major airport, the Airport Commission concept was proposed. This commission would consist of members of the A80-25165 # The impact of GPS on CV mission effective- local community and would not be subject to federal public service ness. J. H. Fagan, M. D. Gaphardt, and P. E. Connolly (Analytic acts or directions from an Ottawa headquarters, but would be Sciences Corp., Reading, Mass.). In: Navigation satellite users; accountable to the Minister of Transportation. J.P.B. Proceedings of the National Aerospace Symposium, Springfield, Va., March 6-8, 1979. Washington, D.C., Institute of Navigation, 1979, p. 198-207. 7 refs. Contract No. A80-25445 # Problems of older jet aeroplanes - A regulatory N62269-77-D-01 18. authority view, J. C. Chaplin (Civil Aviation Authority, London, The impact of NAVSTAR Global Positioning System (GPS) on England). Aircraft Engineering, vol. 52, Feb. 1980, p. 2-5. the general purpose aircraft carrier (CV) is assessed on three Some problems of older jet airplanes are reviewed, with performance levels: navigation equipment, tactical operations and particular reference to matters concerning airworthiness and opera- mission effectiveness. Several uses of GPS-derived position and tion. Particular attention is given to the problem of airplane structure velocity information to augment both the current and the projected and to the design standard and physical standard of the airplane. The mid-1980 CV navigation system are compared to current capabilities. role of the operator is discussed for a particular airplane. V. P. The potential impacts of the addition of GPS to the CV on existing navigation equipment and shipboard systems which use navigation A80-25446 # A scientific approach to defeating helicopter data are summarized. Four general areas of CV tactical operations vibration. N. E. Trigg )Helitune, Ltd., Fleet, Hants., England). that could benefit from GPS are alignment of aircraft inertial Aircraft Engineering, vol. 52, Feb. 1980, p. 6-.9. navigation systems, post-mission recovery of aircraft, command and The essence of combatting helicopter vibration is to remove control, and over-the-horizon targeting. Within these areas, the out-of-balance mechanical and aerodynamic forces which cause performance of GPS-augmented tactical operations are compared to vibration, using trim tabs and balance weights. Past methods of pre-GPS tactical capabilities. Relative measures of effectiveness are applying these correctives were essentially experimental. In the presented for three typical mission scenarios, each of which exercises present paper, it is shown how scientific tuning methods developed a number of tactical operations. The three scenarios deal with local over the past decade can provide remedy to the vibration problem in warfare, task force transit and aircraft rendezvous and recovery. a precise and rapid way. Some illustrative examples are presented. (Author) V. P.
A80. 25214 # An induction gyrocompass (Busola giroinduk- A80-25447 # Transparent engines at Rolls-Royce - The cyjna). A. Radon. Instytut Lofnictwa, Prace, no. 77-78, 1979, p. application of high energy X-ray technology to gas turbine develop- 53-59. In Polish. ment. P. A. E. Stewart (Rolls-Royce, Ltd., Advanced Projects Dept., The paper deals with the design and principle of an induction Bristol, England). Aircraft Engineering, vol. 52, Feb. 1980, p. 10.13. gyrocompass intended for light aircraft. A distinctive feature of the Experience with work directed to provide direct viewing of the device is the use of a dc torque motor as the azimuthal corrector. growths, flexures, or movements in a gas-turbine engine operated in a The torque characteristic varies as a function of the angular test facility is reviewed. Prior to the advent of high-energy displacement. V. P. radiography, the standard practice was to infer information by modifying an engine specially and inserting retractable wearaway A80-25220 # A mass flowmeter with compensation for probes to measure gap clearances. Alternatively, induction probes thermal density variations of the fluid )Przeplywomierz masowy z were used, but the need to specially prepare an engine still remained. korekcja temperaturowych zmian gestosci cieczy). Z. Szymanski. In the mid-1960s, exploratory work with X-rays was conducted, but Instytut Lotnictwa, Prace, no. 77-78, 1979, p. 127-137. 6 refs. In the X-ray energy level attainable was insufficient. Better results were Polish. obtained in 1969 with a flash pulsed high energy X-ray source of The mass flowmeter discussed in the present paper was designed about 2.3 million electron volts. The discussion is focused on a for measuring the flow rate of aircraft fuels by multiplying the successful experiment carried out on the M-45 engine, using iridium volume flow rate by the actual fuel density. The fuel density is 192 and cobalt 60 radioactive isotopes with energy levels ranging monitored by fixing an initial fuel density at a temperature of 293 K from 1 t 2 MeV. V. P. and automatically compensating for the thermal density variations on the basis of its mean linear dependence on the measured fuel temperature. V. P. A80.25448 # Pratt and Whitney innovations. Aircraft Engi- neering, vol. 52, Feb. 1980, p. 21-23. A80.25221 # A system for measuring and recording wind- The paper deals with a completely automated casting facility tunnel balance data (Zestaw do pomiaru i rejestracji danych z wagi capable of producing strong, efficient turbine blades of advanced
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metallurgical structure and exceptional uniformity. The blades, in real time, and can routinely produce ocean directional wave produced in two parts, require less cooling air, resulting in more spectra with off-line data processing. J.P.B. efficient aircraft engine operation. The casting facility provides casting process control and individual part accountability never possible with conventional casting methods. The details of the A80-26193 3 Evaluation of the effectiveness of case- production process are outlined. V. P. hardening gas-turbine-engine components on the basis of fatigue' failure similarity equations (Otsenka effektivnosti poverkhnostnogo uprochneniia detalei GTD s pomoshch'iu uravneniia podobiia A80. 25449 3 Improved MPG for the BAe 146 feeder-jet. G. ustalostnogo razrusheniia). V. K. latsenko (Zaporozhskii Mashino- Giles. Aircraft Engineering, vol. 52, Feb. 1980, p.28,29. stroitel'nyi Institut, Zaporozhe, Ukrainian SSR). Problemy Proch- For the BAe 146, a short-haul pressurized civil transport, the air nosti, Jan. 1980, p. 56-58. In Russian. conditioning system must be compatible with high by-pass turbofan The paper deals with an experimental investigation of the engines and with an onboard auxiliary power unit. The considera- fatigue strength of E1961 steel specimens, carried out to obtain data tions underlying the design of the air system are outlined, and the for evaluating the effectiveness of case-hardening components made operating costs of a baseline system are identified as a requirement of this steel on the basis of a fatigue-failure similarity equation for evaluating the net gains. The reduced cost of operation provided proposed by Serensen, Kogaev, and Shneiderovich (1975). The by a reduced engine bleed system is an attractive feature of the air results of the fatigue tests are tabulated. V. P. system under consideration. V. P.
A80.26195 3 Crack development in panels of a pressurized A80-25498 Measurement of Stress distribution in sandwich fuselage under the combined effect of pressurization-induced cyclic beams under four-point bending. K. Kemmochi (Agency of Industrial loads and high-frequency vibrations (Razvitie treshchin v paneliakh Science and Technology, lbaraki, Japan) and M. Uemura (Tokyo, germ ofiuzeliazha pri sovmestnom deistvii tsiklicheskikh nagruzok ot University, Tokyo, Japan). Experimental Mechanics, vol. 20, Mar. nadduva I vysokochastotnykh vibratsii). N. A. Mozzherova )Tsentral' 1980, p. 80-86. 8 refs. nyi Aerogidrodinamicheskii Institut, Zhukovskiy, USSR). Problemy The bending-stress distributions through thickness in sandwich- Prochnosti, Jan. 1980, p.63.66. 8 refs. In Russian. composite beams are different from those obtained by conventional In the experiments described, 86 x 100 cm thin-walled composite-beam theory because of the shear effect of the core. The cylindrical panels with a radius of curvature of 17.5 cm, prepared of stress distributions in sandwich beams of composite materials with D16AT aluminum alloy, were used to study the influence of various combinations of face and core materials subjected to high-frequency vibrations induced by a turboprop engine on the rate four-point bending are analyzed by introducing the multilayer- of crack growth in the panels. Vibrations superposed on builtup theory. Photoelastic measurements were carried out on pressurization-induced cyclic loads are shown to result in a drastic model specimens having four different k-values and the applicable (two to three orders of magnitude) increase in crack propagation ranges of the two theories are discussed on the basis of the rate. V. P. experimental results. It is shown that the experimental-stress distributions in sandwich-composite beams having k-values larger than 120 can be explained by the multi layer-builtup theory. (Author) A80-26206 Local ground noise generated by supersonic transport planes. E. M. Zhmulin, A. G. Munin, A. A. Tupolev, and G. A. Cheremukhin. (Akusticheskii Zhurnal, vol. 25, July-Aug. 1979, p. A80-25945 Error rate performance of M-ary IDPSK sys- 521-527.) Soviet Physics - Acoustics, vol. 25, July-Aug. 1979. p. tems in satellite/aircraft communications. V. Miyagaki )Okayama 297-301. Translation. University of Science, Okayama, Japan), N. Morinaga, and T. In the present paper, the noise characteristics of the Tu-144 and Namekawa (Osaka University, Suita, Japan). In: ICC '79; Interna- the Concorde are analyzed, and noise abatement methods are tional Conference on Communications, Boston, Mass., June 10-14, examined. The noise characteristics of supersonic and subsonic 1979, Conference Record. Volume 2. Piscata- aircraft are compared. The expected noise levels of second-generation way, N.J., Institute of Electrical and Electronics Engineers, Inc., SSTs are assessed, and some suggestions concerning SST noise 1979, p. 34.6.1-34.6.6. 16 refs. regulations are proposed. V. P. This paper treats the performance of the M-ary DPSK systems at low band rate in the L-band satellite/aircraft channel. The symbol error rate, the double symbol error rate, and the error rate in dual A80-26221 # Present-day problems of air traffic control in diversity reception are theoretically evaluated. The comparison with ground-to-air communications (Problemi odierni nelle comunicazioni the M-ary CPSK systems is made under a certain condition. terra-aria nel controllo del traffico aereo). G. B. Stracca )Milano, (Author) Politecnico, Milan, Italy). Alta Frequenza, vol. 48, Dec. 1979, p. 706-713. 5 refs. In Italian. The problems of the present-day system which utilizes radio A80-26085 * # The Surface Contour Radar, a unique remote channels allocated in the VHF and UHF bands for civilian ground- sensing instrument. J. E. Kenney, E. A. Uliana )U.S. Navy, Naval aircraft communication purposes over metropolitan areas are dis- Research Laboratory, Washington, D.C.). and E. J. Walsh (NASA, cussed. Radio channel overload, interference, gaps in coverage, and Wallops Flight Center, Wallops Island, Va.). (Institute of Electrical breakdowns in two-way radio transmission are considered. Attention and Electronics Engineers, International Microwave Symposium, is given to the possible future advantages of a ground-air data link in Orlando, Fla., Apr. 30-May 2 1979.) IEEE Transactions on addition to voice channels. J.P.B. Microwave Theory and Techniques, vol. MTT-27, Dec. 1979, p. 1080-1092. 6 refs. A 36 GHz computer controlled airborne Surface Contour Radar A80-26268 Yawed slender wings at small angles of attack )SCR) is described, which was developed by the Naval Research (Schiebende schlanke Flugel mit kleinem Anstellwinkel). B. Wagner Laboratory and NASA. The system uses pulse-compression tech- )Dornier GmbI-1, Friedrichshafen, West Germany). Zeitschrift für niques and dual frequency carriers spaced far enough apart to be Flugwissenschaften und Weltraumforschung, vol. 4, Jan-Feb. 1980, decorrelated on the sea surface. The continuous wave transmitter is p. 16-27. 21 refs. In German. Research supported by the Deutsche biphase modulated, the return signal is autocorrelated, and the code F or sch u ngsg eme in schaf t. length and clock rate are variable, providing selectable range Jones' slender wing theory is extended to include a free vortex resolutions of 0.15, 0.30, 0.61 and 1.52 m. The SCR generates a sheet leaving a lateral edge because of a sideslip. The integral false-color coded elevation map of the sea surface below the aircraft equation of the vortex strength in the wake is solved by iterative
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processes. Formulas for vortex strengths, pressure distributions, and The article reviews major improvements in structural efficiency, aerodynamic coefficients are developed for such wings; theoretical durability, and cost effectiveness which have been realized during the results are compared with those from experiments. C.F.W. past fifty years through a series of continuing advances in SDM technology. It is concluded that the emergence of advanced A80-26269 Unsteady pressure measurements on wing- composites and advanced metallic Structures offers significant addi- store combinations in incompressible flow. H. Triebstein (Deutsche tional improvements, provided opportunities are made available for Forschungs. und Versuchsanstalt für Luft. und Raumfahrt, Institus using them. M.E,P, für Aeroelastik, Gdttingen, West Germany). Zeitschrift für Flug- wissenschaften und Weltraumforschung, vol. 4, Jan.. Feb. 1980, p. A80-26344 # New approaches to sailing. B. Smith. Astro- 28-38. 10 refs. nauticsandAeronautics, vol. 18, Mar. 1980, p . 36-47. The present paper deals with the fneasurements of unsteady It is noted that sailing involves no thermodynamic cycle and pressures on harmonically oscillating wing-store combinations in generates little heat, and that sailboats react mechanically to the incompressible flow. The experiments were made in the 3 by 3 m force of the wind without any train of energy-losing conversions in subsonic wind tunnel of she DFVLR in Gbttingen. The pressure was the path of the action. The paper investigates some possible measured for yaw-, pitch- and heave-oscillations of the store at configurations for sail powered vessels, such as a blimp sail boat, different locations of the store. The pitching and yawing oscillations hybrid motor-sailer, and a tanker sailed with the gases derived from were performed about two different axes. Further unsteady pressure the well yielding the oil. Attention is also given to some model distributions were measured on the wing-store combination at aerohydrofoils which have been experimented with. M.E.P. harmonically pitching oscillations of the wing and on the store at pitching and heaving oscillations of the store without the wing. (Author) A8026345 # CADD on the F-18 program. J. H Zadar. nowski (McDonnell Aircraft Co., St. Louis, Mo.). Astronautics and A80-26305 // One-dimensional aerodynamic control calcula- Aeronautics, vol. 18, Mar. 1980, p. 48-51. 61. tions for cooled gas turbines (Odnomernyi proverochnyi aerodina- The paper examines the application of computer-aided design micheskii ratchet okhlazhdaemykh gazovykh turbin). Ia. A. Sirotkin. drafting to the development of the F-18, noting that much Akademiia Nauk SSSR, Izvestiia, Energetika i Transport, Jan-Feb. traditional boardwork was made obsolete. It is shown that CADD 1980, p. 137-149. 15 refs. In Russian. was principally used in the design and fabrication of advanced The paper deals with a one-dimensional control method devel- composites, sheet metal parts, and aircraft tubing. To a lesser degree, oped for air-cooled gas-turbine stages. Detailed attention is given to the system was applied to honeycomb structure and machined parts. such features as air injection, flow, and mixing. The method is Attention is given to manufacturing benefits, and cost analysis. developed on the basis of irreversible thermodynamics, with separate Finally, it is reported that cost effectiveness of CADD is confirmed consideration of aerodynamic and thermodynamic losses in the for small aircraft components, noting however, that cost effective- analysis. Instead of the conventional conservation laws, use is made ness will always depend on schedule coordination and can be of the balance, entropy and moment of momentum (with respect to affected by a number of design criterions. M.E.P. the axis of rotation) equations. This provides a better treatment of the complex physical flow pattern in a stage than the theory of viscous, thermal, and mass interaction. V. P. A80-26349 II Theory of by-pass ducted-fan engines )Teoriia dvukhkonturnykh turboreaktivnykh dvigatelei). V. P. Demenchenok, L. N. Druzhinin, A. L. Parkhomov, V. A. Sosunov, M. M. A80-26325 # On the equations of motion about the mass Tskhovrebov, S. M. Shliakhtenko, and A. S. El'perina. Moscow, centre of the jet aircraft considered as variable mass system. M. M. Izdatel'stvo Mash inostroenie, 1979. 432 p. 76 refs. In Russian, Nita (Bucuresti, Institutul Politehnic, Bucharest, Rumania). Revue The book deals with the general aspects of ducted-fan-engine Roumaine des Sciences Techniques, Série de Mécanique Appliquee, theory and with methods of optimizing the operational parameters vol. 24, July-Aug. 1979, p. 527-536. of subsonic and supersonic ducted-fan engines. The operational, Equations of motion of a jet aircraft about its center of mass are control, and noise characteristics of low and high bypass ratio presented. The aircraft is considered a mass system that is variable engines are examined. Attention is given to the correlation of owing to continuous air capture and gas ejection. There is an gas-turbine and compressor weights and dimensions. V. P. additional term in the equation of motion which may have an effect of positive or negative damping on the spinning motion of the aircraft, depending on the position of the jet engines and fuel tanks. A80-26350 # Aircraft instruments and automatic systems Under certain conditions this effect is so significant that it may /3rd revised and enlarged edition/ (Aviatsionnye pribory i avtomaty influence aircraft flight performance. B. J. /3rd revised and enlarged edition/). D. A. Braslavskii, S. S. Logunov, and D. S. PeI'por, Moscow, lzdatel'stvo Mash inostroenie, 1978, 428 p. 35 refs. In Russian. A80-26342 # Breaking V/STOL free of Catch 22. D. C, The book deals with the fundamentals of the theory of aircraft Hazen (Princeton University, Princeton, N.J.). Astronautics and instruments and the principles of designing manometric, electric, and Aeronautics, vol. 18, Mar. 1980, p. 24-30. gyroscopic instruments for measuring the position and motion of The article examines the problem that no mission role has been aircraft (altitude, heading, airspeed, angles of pitch, roll, and yaw, determined that clearly makes V/STOL aircraft worth the additional and angular velocities). Autopilots, navigation systems, and control cost, noting that no overwhelming demand for V/STOL has yet systems are discussed, along with instruments for monitoring engine emerged from the civilian world. Attention is given to the use of the operation. V. P. Harrier AV-8A by the Marine Corps. It is shown that unconventional mission profiles can allow the V/STOL to be used to its best advantage, noting that short distance missions allow some fuel to be A80-26471 Design of an electronic model of a microwave replaced by ordinance. Comparisons are also made between mission aircraft landing system. A. I, Nikitin. (Radiotekhnika, vol. 34, June 1979, p. 39-41.) Telecommunications and Radio Engineering, Part 2 requirements of the Navy, and Air Force. M.E.P, Radio Engineering, vol. 34, June 1979, p. 83-85. 5 refs. Translation. A algorithm is presented for the electronic simulation of A80-26343 # The cautious course to introducing new SOM microwave landing systems. The method involves simulation of MLS technology into production systems. R. N. Hadcock (Grumman signals on the second intermediate frequency of the onboard Aerospace Corp,, Bethpage, N.Y.). Astronautics and Aeronautics, receiver. The proposed model makes it possible to evaluate the vol. 18, Mar, 1980. p. 31-33. curacy and noise immunity of microwave landing systems. B.J.
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A80-26630 Constant speed 400 Hz aircraft electric genera- and real-time reconnaissance in the post 1983 time period at a tion system. R. C. McClung (Sundstrand Corp., Sundstrand Aviation fraction of the cost to develo p a new aircraft. (Author) Electric Power Group, Rockford, Ill.). Society of Automotive Engineers, Aerospace Meeting, Los Angeles, Calif., Dec. 3-6, 1979, A80.26636 The practical aircraft hydraulic test stand. R. Paper 791067. 11 p. A. Morley (Teledyne Sprague Engrg., Gardena, Calif.). The purpose of this paper is to examine recent innovations in Society of Automotive Engineers, Aerospace Meeting, Los Angeles, Calif., Dec. the state-of-the-art of aircraft constant speed drive alternating 3-6, 1979, Paper 791079. 9 p. current electric power generation systems. An engineering problem was posed by the concepts used in designing the latest generation of An approach to the design of the portable hydraulic test stand is commercial aircraft. The approach to solving the problem and the presented, with the basic test-stand circuit expected to perform solutions chosen have offered the opportunity to further increase the satisfactorily on 90% of the commercial and military aircraft now in reliability of the aircraft secondary power system. The maintenance use. The subsystems are discussed with respect to the cost reduction, required has been decreased by simplifying the system, and much of power requirements, fluid cleanliness, instrumentation, and the the error potential involved in fault isolation has been eliminated by simplified and noisefree operations. Consideration is given to the a reliable Built-In Test (BITE) system. (Author) selection and location of the filters and pumps, as well as the heat exchanger and valves. The system has been used successfully in the manufacture and care of utility, transport and military aircraft up to A80-26631 Air supply system approach for the Boeing the Mach 2 class. A schematic diagram of the test stand is provided Model 767 Airplane. J. P. Patrick (United Technologies Corp., along with diagrams of the subsystems. L.M. Hamilton Standard Div., Windsor Locks, Conn.) and A. K. Trikha (Boeing Commercial Airplane Co., Seattle, Wash.). Society of Automotive Engineers, Aerospace Meeting, Los Angeles, Calif., Dec. A80-26637 MCAIR design philosophy for fighter aircraft 3-6, 1979, Paper 791068. 13 p. departure and spin resistance. J. Mello and J. Agnew (McDonnell The purpose of the paper is to describe the salient features of Aircraft Co., St. Louis, Mo.). Society of Automotive Engineers, the Boeing 767 air supply system and to present data that illustrate Aerospace Meeting, Los Angeles, Calif., Dec. 3-6, 1979, Paper its steady state and dynamic performance characteristics. The air 791081. 11 p. supply system consists of two engine bleed air systems and a The McDonnell Aircraft Company (MCAIR) design philosophy remotely built-in-test equipment module. Attention is given to the pertaining to the departure and spin resistance and out-of-control electrical systems and to the digital module that indicate failures to recovery characteristics of fighter aircraft is presented. The more the line replaceable unit level. C.F.W. important military specification requirements are reviewed and their influence on this philosophy is discussed. Aerodynamic stability and A80-26632 Development and flight test of a two-place control criteria and control system design guidelines are presented night/adverse weather A-10 for the close-air support and battlefield which are used to assure that a fighter aircraft will exhibit a high attack mission. J. M. Williamson and W. Shawler (Fairchild Republic level of departure and spin resistance and rapid recovery from Co., Farmingdale, N.Y.). Society of Automotive Engineers, Aero- out-of-control situations. (Author) space Meeting, Los Angeles, Calif, Dec. 3-6, 1979, Paper 791069. 9 p. 6 refs. The paper discusses the development, building and critical A80-26638 Effects of forebody, wing and wing-body-LEX evaluation of a cost-effective solution to a critical void in battlefield flowfields on high angle of attack aerodynamics. W. A. Moore, G. E. support tactical air capacity in night and adverse weather. The Erickson, D. J. Lorincz, and A. M. Skow (Northrop Corp., Aircraft objective is to incorporate an effective integration of proven avionics Group, Hawthorne, Calif.). Society of Automotive Engineers, Aero- with appropriate displays and presentations into a modified A-iD space Meeting, Los Angeles, Calif., Dec. 3-6, 1979, Paper 791082. 27 system, and to demonstrate night/adverse weather tactical effective- p. ii refs. ness using this system to exploit the A-10's tactics and munitions. The effects of forebody, wing, and wing-body-LEX flowfields C.F.W. on high angle of attack aerodynamics are examined. Vortex flows emanating from the forebody and hybrid wings can affect the high A80-26633 AV-88 - A second generation V/STOL. J. angle-of-attack handling qualities and the departure and spin resis- Warakomski (McDonnell Aircraft Co., St. Louis, Mo.). Society of tance of fighter aircraft. Depending on the strengths, orientation, and Automotive Engineers, Aerospace Meeting, Los Angeles, Calif., Dec. breakdown characteristics of these vortices, an aircraft may be 3-6, 1979, Paper 791070. 20 p. departure-prone or departure-resistant. Studies were conducted to State-of-the-art technology developments have enabled the determine the effect of shed vortices, and guidelines were developed enhancement of an operationally proven, superior weapon system to for the design of forebody and hybrid-wing shapes so that aircraft provide next generation capability. Significant advances applicable to stability will be enhanced. A. T. vertical and short take-off and landing (V/STOL) aircraft have been made in aerodynamic, propulsion, composite structure and avionics technologies. These have been incorporated into the AV-813 Weapon System, whose performance has been demonstrated through the A80.26639 • Control system techniques for improved YAV-813 prototype flight program. (Author) departure/spin resistance for fighter aircraft. L. T. Nguyen (NASA, Langley Research Center, Hampton, Va.). Society of Automotive A80-26634 Production Eagle and its potential. R. W. Engineers, Aerospace Meeting, Los Angeles, Calif., Dec. 3-6, 1979, White (McDonnell Aircraft Co., St. Louis, Mo.). Society of Auto- Paper 791083. 25 p. 6 refs, motive Engineers, Aerospace Meeting, Los Angeles, Calif., Dec. 3-6, Some fundamental information on control system effects on 1979, Paper 791071. 9 p. 7 refs. controllability of highly-maneuverable aircraft at high angles of The USAF F-iSA/B air superiority fighter, built by the attack and techniques for enhancing fighter aircraft departure/spin McDonnell Aircraft Company and introduced into active service in resistance using control system design is summarized. The discussion 1974, has demonstrated exceptional performance and combat includes: )a) a brief review of pertinent high angle-of-attack readiness. Recent introduction of the F-i 5C/D with increased phenomena including aerodynamics, inertia coupling, and kinematic internal fuel, provisions for conformal fuel tanks, increased takeoff coupling; )b( effects of conventional stability augmentation systems gross weight plus incorporation of a Radar Programmable Signal at high-alpha; (c) high-alpha control system concepts designed to Processor provides improvement in range and mission flexibility. enhance departure/spin resistance; and (d) the outlook for applica- These improvements will enhance already demonstrated capabilities tions of these concepts to future fighters, particularly those designs for performing other roles, i.e., in-weather strike, defense suppression which incorporate relaxed static stability. (Author)
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A80.26640 High-angle-of-attack flying qualities - An over- studies and conduct scale model tests of aerodynamic interference, view of current design considerations. H. K. Heffley and D. E. aeroelastic effects, and dynamic load distributions. A. T. Johnston (Systems Technology, Inc.. Hawthorne, Calif.). Society of Automotive Engineers, Aerospace Meeting, Los Angeles, Calif., Dec. 3-6, 1979, Paper 791085. 8 p. 15 refs. Contract No. A80-26644 The KC-135 - A successful multirole transport F33615-78-C-3604. aircraft. S. Starch (Boeing Military Airplane Co., Seattle, Wash.). An overview is presented on the design for high-angle-of-attack Society of Automotive Engineers, Aerospace Meeting, Los Angeles, flying qualities by examining the groups of airframe manufacturers, Calif., Dec. 3-6, 1979, Paper 791093. 13 p. the research community, and the aircraft users. The aircraft The paper examines the origin of the requirements for the manufacturers are restricted by cost and time constraints in their KC-135 aircraft, its growth in missions, present status, and future ability to use new design tools, and the user-pilots present factors prospects. Various photographs showing the development stages are which the manufacturers and researchers find difficult to address, presented together with graphs examining airlift statistics. It is such as provision of sensory cues or the pilots' discomfort with flight concluded that the aircraft will use appreciably less fuel and meet control computers. It is concluded that taken together, the three civil standards for noise and atmospheric pollution because of its points of perspective suggest methods of using design practices and modern engine. C.F.W. standards to enhance the high-angle-of-attack flying qualities. A. T.
A80-26641 HLH and beyond. G. H. Fries and J. J. A80.26645 * Multirole cargo aircraft options and configura- Schneider (Boeing Vertol Co., Philadelphia, Pa.). Society of Automo- tions. D. W. Conner and J. C. Vaughan, Ill (NASA, Langley Research tive Engineers, Aerospace Meeting, Los Angeles, Calif, Dec. 3-6, Center, Hampton, Va.). Society of Automotive Engineers, Aerospace 1979, Paper 791086. 15 p. 26 refs. Meeting, Los Angeles, Calif., Dec. 3. 6, 1979, Paper 791096. 16 p. 9 Design, fabrication, and test of large high powered helicopter refs. components in the U.S. Army Heavy Lift Helicopter Advanced The paper discusses multirole cargo aircraft options and configu- Technology Component development program demonstrated the rations. It was shown that derivatives of current wide-body aircraft feasibility of efficient, large helicopter components and reduced the would be economically attractive through 2008, but new dedicated risk and cost of future heavy lift helicopter development. The airfreighters incorporating 1990 technology would offer little or no components included a 92-foot diameter rotor system, an 18,000 economic incentive. Option studies indicate that Mach 0.7 propfaris horsepower drive system, a fly-by-wire flight control system, a 35 would be economically attractive in trip cost, aircraft price, and ton cargo handling system, and 8,000 horsepower turbo-shaft airline ROI; spanloaders would be lower priced with higher Aol, but engines. Bench testing of the large, high power transmissions was not would have a relatively higher trip cost because of aerodynamic completed and is required to verify the adequacy of the design inefficiencies. Finally, air cushion landing gear configurations are modifications resulting from the ATC technology development identified as an option for avoiding runway constraints on airport program. Moreover, current design methods were found to be accommodation of very large airfreighters. A. T. inadequate for large flight weight gears, and new analytical design methods employing finite element techniques will be required for future large aircraft gear design applications. Extrapolation of the A80-26646 Future multi-mission transport aircraft - design and manufacturing technologies developed in the ATC Requirements and design possibilities. R. H. Lange and W. T. program to larger but similar tandem rotor heavy lift configurations Mikolowsky (Lockheed-Georgia Co., Marietta, Ga.). Society of indicates that there are no formidable reasons why shaft driven Automotive Engineers, Aerospace Meeting, Los Angeles, Calif, Dec. helicopters cannot continue to grow in size. A study comparing shaft 3-6, 1979, Paper 791097. 14 p. 19 refs. driven tandem helicopter configurations with hybrid airship con- An assessment of future requirements for possible civil and/or figurations shows the helicopter to be competitive in the logging and military multimission aircraft is presented. A multirole strategic containership off-loading applications for which the hybrid airship is aircraft (the LX-MRSA) configuration with flexibility for a variety of being proposed. (Author) missions such as a strategic missile carrier, ICBM carrier/launcher, and aerial tanker is discussed; a 1995 IOC advanced technology large aircraft is presented along with an assessment of desirable design A80-26642 Single rotor options for heavy lift and poten- features for a common military/commercial transport. Finally, a new tial of multi lift. E. S. Carter, D. E. Cooper, and L. G. Knapp (United aircraft concept known as Flatbed, configured for multirole opera- Technologies Corp., Sikorsky Aircraft Div., Stratford, Conn.(. tions with a novel backbone fuselage capable of carrying a passenger Society of Automotive Engineers, Aerospace Meeting, Los Angeles, module or intermodal containers, is described. A. T. Calif., Dec. 3.6, 1979, Paper 791087. 16 p. The paper reviews the current state-of-the-art rotorcraft payload capacity growth, to show that the root of the problem is not any A80-26647 Opportunistic maintenance policies for unsurmountable technical barrier, and briefly discusses the single economic replacement of internal life-limited components in rotor options for heavier lift. The economic factors which appear to modular aircraft engines. J. L. Madden (USAF, Directorate of have militated, up to this point, against development of larger Management Sciences, Wright-Patterson AFB, Ohio). Society of helicopters for civil or military requirements are examined. C.F.W. Automotive Engineers, Aerospace Meeting, Los Angeles, Calif., Dec. 3-6, 1979, Paper 791101. 13 p. 7 raft. New USAF aircraft engines have modules, each with internal life-limited components. Engines are repaired by replacing modules. A80-26643 Multi rotor options for heavy lift. J. DeTore Modules are repaired at either base or depot. An opportunistic and S. Martin, Jr. (Bell Helicopter Textron, Fort Worth, Tex.). maintenance policy specifies how early life-limited components may Society of Automotive Engineers, Aerospace Meeting, Los Angeles, be replaced provided that the engine (or module) is already in repair. Calif., Dec. 3-6, 1979, Paper 791089. 17 p. 23 refs. A repair level policy specifies when to repair a whole engine at depot The paper reviews the three and four rotor, tilt rotor V/STOL instead of at base. Expected long term costs are calculated using aircraft with an advanced tandem helicopter. The multirotor dynam- computer simulation. Costs are maintenance manhours, pipeline ic systems are projected to weight less than twin rotor systems and requirements, shipping, and component replacement. Costs are should avoid rapid design disk loading increases; design considera- graphed and the least cost policy choices are identified. (Author) tions are discussed, including safety, aeroelastic stability, external noise, and downwash effects. It is shown that the multirotor option can service four times the revenue-producing territory per day than A80-26648 On-condition maintenance - Review of mili- an advanced tandem helicopter. It is recommended to pursue design tary engines. D. H. Story (USAF, Propulsion Management Div., Kelly
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AFB, Tex.). Society of Automotive Engineers, Aerospace Meeting, Wright-Patterson AFB, Ohio). In: Fatigue and microstructure; Los Angeles, Calif., Dec. 3-6, 1979, Paper 791102. 6 p. Proceedings of the Materials Science Seminar, St. Louis, Mo., The Air Force has adopted the commercial airline's concept of October 14, 15, 1978. Metals Park, Ohio, on-condition maintenance. Application to transport aircraft type American Society for Metals, 1979, p. 29-56. 6 refs. engines parallels the airline's experience. New generation, modular The paper examines fatigue in aircraft machines and structures. design, fighter engines have different manpower, facilities and Analyses of aircraft failures shows that the engine failures are the equipment requirements. Engine diagnostics and automated trending single most important cause of aircraft accidents; premature fatigue and analysis have the potential to enhance maintenance under the cracking has resulted from improper part design or choice of on-condition concept. Long term impact of the concept will require materials, illustrated by failures in airframes and airframe/wing spar continued monitoring and evaluation. (Author) attachments. The former Air Force approach emphasizing the initial static strength of the structure and the 'safe-life' concept to achieve the desired fatigue life was replaced by the new Aircraft Structural A80-26649 An approach to the runway denial problem. H. Integrity Program which is based on the 'fail-safe' and the 'safe-crack- H. Ostroff )McDonnell Aircraft Co., St. Louis, Mo.). Society of growth' design approaches. It is concluded that the new method will Automotive Engineers, Aerospace Meeting, Los Angeles, Calif., Dec. provide a better understanding of the metallurgical factors that 36, 1979, Paper 791107. 5 p. control fatigue behavior and a better ability to achieve desired Short runway operational aircraft are proposed as a more timely equipment life. solution to the concern over runway denial weapons for the Air A. T. Force. Means for obtaining the required aircraft characteristics in the near and long term are discussed, as well as a possible role for Air A80-26791 A time-shared monopulse approach to air/ Force VTOL aircraft. A tool for airbase vulnerability analysis is surface radar ranging. R. E. Wilcox (Emerson Electric Co., Electron- described. C.F.W. ics and Space Div., St. Louis, Mo.). In: EASCON '79; Electronics and Aerospace Systems Conference, Arlington, Va., October 9-11, 1979, Conference Record. Volume 2. New York, A80-26650 Fighter options for tactical air defense, G. R. Institute of Electrical and Electronics Engineers, Inc., 1979, p. Kutz (Grumman Aerospace Corp., Bethpage, N.Y.). Society of 249-255. Automotive Engineers, Aerospace Meeting, Los Angeles, Calif. Dec. The paper discusses the relative merits and deficiencies of 7-6, 1979, Paper 791108. 16 p. con-scan and COSRO systems for A/S ranging, after which a A recent Grumman/ Raytheon study sponsored by the AFFDL time-shared monopulse system TSMP is defined which is an examined technology needs for future defensive counterair aircraft. autonomous and adaptive processing method to obtain ranging The arena for that examination was theater air defense of NATO in information over a large class of surface cross sections and the 1990's. This paper presents results of that effort with emphasis topologies. The TSMP processor would time-share all three M.P. on the characteristics and technology complements of alternative channels and perform the following sequence of operations. First, an concepts examined during the study. Five distinctly different angular section of the main beam is located, followed by finding that weapon system designs emerged as competitive alternatives. These point in this main beam section at which the product of the azimuth ranged from a small, low cost, transonic fighter armed with short and elevation difference channels achieve a minimum with respect to range, IR guided missiles and deployed in quantity, to a large, the attendant sum channel. This final range gate corresponds to the sophisticated, and relatively expensive supersonic fighter/interceptor reflection delay along the desired ranging vector. (Author) employing long range radar directed missiles. (Author) A80-26797 Application of Nd:YAG optical communica- A80.26651 Reliability and maintainability design stan- tions technology for aircraft to satellite links. J. D. Wolf, J. N. dards from read iness. related goals. L. Rogin and J. Gold (Informa- Windham, and J. A. Pautler (McDonnell Douglas Astronautics Co., tion Spectrum, Inc., Warminster, Pa.). Society of Automotive St. Louis, Mo.). In: EASCON '79; Electronics and Aerospace Engineers, Aerospace Meeting, Los Angeles, Calif., Dec. 3-6, 1979, Systems Conference, Arlington, Va., October 9-11, 1979, Conference Paper 791109. lop. Record. Volume 2. New York, Institute of The paper considers the reliability and maintainability design Electrical and Electronics Engineers, Inc., 1979, p. 286-294. Con- standards for a Naval aircraft weapon system in terms of readiness. tract No. F33615-76-C-1002. related goals. Generalized relationships and specific logic tracks are A functional description is given for a general purpose satellite identified for the principal readiness- related parameters; the pro- laser receiver. Low data rate multiple access, as well as single-user cedures assume that the systems will be consistent with the Naval high data rate communications, are applied to airborne-satellite operational methods. The anticipated ranges of variation for the linking. Presented are advancements in solid state GaAs diode laser principal parameters are established by evaluating the Fleet-wide pump technology, which can provide a very long life. Nd:YAG is averages over a wide range of current Naval aircraft systems. A. T. used for a low power laser beacon for precision pointing and tracking and for 20 Kbps communication. Geographic coverage advantages of small optical antennas in flush-mounted aircraft installations are A80-26730 Fatigue and microstructure; Proceedings of the shown for typical satellite orbits. )Author) Materials Science Seminar, St. Louis, Mo., October 14, 15, 1978. Seminar sponsored by the American Society for Metals. Metals Park, Ohio, American Society for Metals, 1979. 543 p. $60. A80. 26802 # Radiometric measurements of targets and clut- The Seminar focused on fatigue in machines and structures, in ter. J. P. Hollinger, B. E. Troy, and B. S. Yaplee (U.S. Navy, Naval power generation, aircraft, and ground vehicles, new techniques for Research Laboratory, Washington, D.C.). In: EASCON '79; Electron- detection and monitoring of machine damage, mechanisms and ics and Aerospace Systems Conference, Arlington, Va., October 9-11, iheories of fatigue, cyclic plastic deformation and microstructure, 1979, Conference Record. Volume 2. New York, fatigue-crack initiation and crack growth theories, high temperature Institute of Electrical and Electronics Engineers, Inc., 1979, p. fatigue, environmental effects of fatigue, fatigue crack propagation 348-352. theories, and control of fatigue resistance through microstructure of Optimum passive detection of an object in a clutter background ferrous alloys and high strength aluminum. A. T. requires a knowledge of the detailed properties of the object and of the background. Airborne measurements at 90 GHz of the millimeter A80-26731 Fatigue in machines and structures - Aircraft. wavelength characteristics of selected targets and backgrounds are T. D. Cooper and C. A. Kelto (USAF, Materials Laboratory, described and target detection enhancement is discussed. (Author)
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A80-26810 # Advanced computer program. N. A. Blake Calif., Technology Conferences, 1979. 403 p. $48. (FAA, Washington, D.C.). In: EASCON '79; Electronics and Aero- space Systems Conference, Arlington, Va., October 9-11, 1979, The conference focused on materials development, environ- Conference Record. Volume 3. New York, mental effects, dimensional stability, defects and their effects, repair Institute of Electrical and Electronics Engineers, Inc., 1979, p. technology, and nondestructive evaluation of composite structures. 502.506. Papers were presented on the development of a new dimensionally The paper examines the FAA's advanced engineering and and thermally stable composite, failure mechanisms for advanced development program, consisting of the development activities composite sandwich construction in hostile environments, the effects needed to define the automation and computer system improve- of high humidity environments on the behavior of aerospace grade ments for the late 1980 and 1990 time period. The introduction of graphite/epoxy composites, ultrasonic monitoring of flaw growth in electronic tabular displays of flight data and computer assistance in graphite/epoxy laminates under fatigue loading, and influence of the the planning function is discussed. Attention is given to an outlined interface on composite failure. V. L. program that is both feasible and offers benefits in improved safety, C.F.W. productivity, and system performance. A80-26884 Failure mechanisms for advanced composite sandwich construction in hostile environments. G. Waring, K. E. A80-26811 Theoretical limitations on collision avoidance Hofer, Jr. (lIT Research Institute, Chicago, III.), E. Vadala, and R. systems. I. W. Kay (Institute for Defense Analyses, Arlington, Va.). Trabocco (U.S. Naval Material Command, Naval Air Development In: EASCON '79; Electronics and Aerospace Systems Conference, Center, Warminster, Pa.). In: Advanced composites - Special topics; Arlington, Va., October 9-11, 1979, Conference Record. Volume 3. Proceedings of the Conference. El Segundo, Calif., December 4-6, New York, Institute of Electrical and Electronics 1979. El Segundo, Calif., Technology Confer- Engineers, Inc.. 1979, p. 507-512. 7 refs. FAA-supported research. ences, 1979, p. 83-122. 25 refs. Navy-supported research. General limitations on the performance of collision avoidance The effect of environmental degradation was studied with systems in dense air traffic result from the trade-off between the reference to composite sandwich components of naval aircraft. The amount of protection afforded by a system and the frequency of the investigated environmental conditions included high humidity, ele- warnings that it will generate. In this context the protection referred vated temperature, stress cycling, and stack gases and sea water. The to is meant to allow for unforeseen turns by encountering aircraft 672-hour test program consisted of 336 hours of Constant tempera- and some minimum aircraft separation requirement. The effective- ture (165 F)/constant humidity (95% RH) together with stress ness and efficiency of a collision avoidance system's threat criterion cycling representative of 1000 flight hours followed by 336-hour can be illustrated qualitatively, for purposes of comparison, by exposure to synthetic sea water and stack gases at ambient means of a geometrical Construct due to Holt et al. This kind of temperature. Strength loss and failure modes are detailed for various analysis indicates that at altitudes below 10,000 ft the use of bearing samples. Failure modes include compressive rupture of the composite data will not greatly enhance the efficiency of a threat criterion that skin and failure due to disbond of the adhesive. V. L. otherwise depends upon the use of separation data alone. A quantitative analysis of alarm rates shows that for the traffic A80'26888 Repair of advanced composite structure. J. D. distribution that has been projected for the Los Angeles Basin in Labor (Northrop Corp., Hawthorne, Calif.). In: Advanced Com- 1982 it is likely that alarm rates will be a problem. Conceivably, by posites - Special topics; Proceedings of the Conference. El Segundo, the use of adaptive collision avoidance techniques or through the Calif., December 4-6, 1979. El Segundo, Calif., agency of air traffic control procedures it may be possible to alleviate Technology Conferences, 1979, p. 161-170. 5 refs. Contract No. the problem. (Author) F33615-79-C-3217. Developments in the repair technology of advanced composite aerospace structures are reviewed. Several programs over the last A80-26819 fl The Federal Aviation Administration naviga- decade have yielded a number of repair procedures, e.g., flush and tion program. N. A. Blake (FAA, Washington, D.C.). In: EASCON tapered external patches, injection of delaminations, and flush repair '79; Electronics and Aerospace Systems Conference, Arlington, Va., using a scarf joint. A new program is underway which will result in October 9. 11, 1979, Conference Record. Volume 3. the publication of the Repair Guide scheduled for March 1982. V.L. New York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. 666-672. The Federal Aviation Administration's navigation program for A80-26890 Advanced composites serviceability program the next two decades is outlined, which includes the following areas: Status review. J. M. Altman (Rockwell International Corp.,. Los those associated with certification of navigation systems to meet Angeles, Calif.). In: Advanced composites - Special topics; Proceed- current requirements and those associated with building a data base ings of the Conference, El Segundo, Calif., December 4'6, 1979. to define future system improvements. Attention is given to Loran-C, El Segundo, Calif., Technology Conferences, Omega, and the Helicopter IFR Program, as well as to the cost 1979. p. 183-204. 5 raft. USAF-sponsored research. factors involved in the Global Positioning System. C. F. W. A three-phase serviceability program sponsored by the Air Force will determine the effect of defects on the performance and serviceability of advanced composite primary structures and develop A80-26867 Hybrid optical/digital processing for target acceptance/rejection criteria for various zones of the structures. identification. R. Wood (USAF, Rome Air Development Center, Phase I includes characterization of structural defects, development Griffiss AFB, .Y.). In: Optical signal processing for CCCI; Proceed- of empirical /analytical design tools, and coupon testing. Under ings of the Seminar, Boston, Mass., October 29, 30, 1979. phases II and Ill the damage mechanism models and acceptance/re- Bellingham, Wash., Society of Photo-Optical Instru- jection criteria generated in phase I are to be validated by testing mentation Engineers, 1980, p. 74. 80. 6 refs. element-size specimens of primary composite structures and correla- Real-time processing techniques for aircraft identification of ting these data with the coupon test results. Summaries of test results friend, foe, or neutral (I FFN) in a noncooperative target recognition are presented. V. L. (NCTR) environment are reviewed. Attention is given to motion compensation, image generation-scaling, and translation identifica- tion. V. T. A80.26891 Nondestructive evaluation of graphite com- A80-26878 Advanced composites - Special topics; Pro- posite aircraft structures. W. H. Sheldon (Northrop Corp., Aircraft ceedings of the Conference, El Segundo, Calif., December 4-6, 1979. Div., Hawthorne, Calif.). In: Advanced composites - Special topics; Conference sponsored by Technology Conferences. El Segundo, Proceedings of the Conference, El Segundo, Calif., December 4-6,
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1979. El Segundo, Calif., Technology Confer- Research Center, Hampton, Va.) and S. Balakrishna (NASA, Langley ences, 1979, P. 205-227. Research Center, Hampton; Old Dominion University, Norfolk, Va.). Various nondestructive evaluation techniques were tested for In: Aerodynamic Testing Conference, 11th, Colorado Springs, Cob., detection of flaws in graphite composite aircraft structures. These March 18-20, 1980, Technical Papers. New York, techniques included ultrasonic inspection, laser holography, radio- American Institute of Aeronautics and Astronautics, Inc., 1980, p. graphy, and inspection by Fokker Bond Tester and a Sondicator. 10-15. (AIAA8O-0416) Visibility of defects was optimized using B-scan (section views) and Experience during the past 6 years of operation of the 0.3-meter 3-D imaging techniques. It was found that B-scans/3-D scans enhance transonic cryogenic tunnel at the NASA Langley Research Center has flaw geometry and depth, and provide information on the distri- shown that there are problems associated with efficient operation bution of impact damage through the laminate thickness. Laser and control of cryogenic tunnels using manual control schemes. This holography was successful in detecting skin/core defects; radiography is due to the high degree of process crosscoupling between the was useful for detecting core damage and core tolerances; and the independent control variables (temperature, pressure, and fan drive Fokker Bond Tester was more successful than the Sondicator for speed) and the desired test condition (Mach number and Reynolds detecting flaws. V. L. number). One problem has been the inability to maintain long-term accurate control of the test parameters. Additionally, the time A80-26895 • Influence of interface on composite failure. G. required to change from one test condition to another has proven to C. Sih and E. T. Moyer, Jr. (Lehigh University, Bethlehem, Pa.). In: be excessively long and much less efficient than desirable in terms of Advanced composites . Special topics; Proceedings of the Confer- liquid nitrogen and electrical power usage. For these reasons, studies ence, El Segundo, Calif., December 4-6, 1979. El have been undertaken to: (1) develop and validate a mathematical Segundo, Calif., Technology Conferences, 1979, p. 283-312. 6 refs. model of the 0.3-meter cryogenic tunnel process, (2( utilize this Grant No. NsG-3179. model in a hybrid computer simulation to design temperature and The influence of the interface on the composite system behavior pressure feedback control laws, and (3) evaluate the adequacy of is investigated by analytical modeling. The stress analysis is based on these control schemes by analysis of closed-loop experimental data. the two-dimensional finite element procedure in which twelve-node This paper will present the results of these studies. (Author) isoparametric elements with cubic shape functions are used. The location of possible failure sites is predicted by the strain energy density (SED) failure theory which assumes failure to coincide with A80-26932 • # A study of nonadiabatic boundary-layer stabi- locations of minimum SED while the locations of maximum SED lization time in a cryogenic tunnel for typical wing and fuselage correspond to regions of excessive distortion or yielding. The results models. C. B. Johnson (NASA, Langley Research Center, Subsonic- of the analysis show that the way in which the modulus of elasticity Transonic Aerodynamics Div., Hampton, Va.). In: Aerodynamic varies within the interface is as important in modeling as the average Testing Conference, 11th, Colorado Springs, Cob., March 18-20, interface modulus. V. L. 1980, Technical Papers. New York, American Institute of Aeronautics and Astronautics, Inc., 1980, p. 16-23. 10 refs. (AIAA8O-0417( A80.26929 Aerodynamic Testing Conference, 11th, Colo- A theoretical study has been made of the time varying effect of rado Springs, Cob., March 18-20, 1980, Technical Papers. Confer- nonadiabatic wall conditions on boundary layer properties for a ence sponsored by the American Institute of Aeronautics and two-dimensional wing section and an axisymmetric body of revolu- Astronautics. New York, American Institute of Aeronautics and tion typical of a fiselage. The wing section and body of revolution Astronautics, Inc., 1980. 386 p . $40. are representative of the root chord and fuselage of what is considered to be a typical size transport model for the National Topics discussed include the automatic control of Langley's Transonic Facility. The transient analysis was made at a Mach 0.3-meter cryogenic test facility, the Ascent Air Data System for the number of 0.85, for stagnation pressures of 2, 6, and 9 atmospheres Space Shuttle, the measurement of local skin friction and static at several cryogenic values of total temperature for a solid wing and pressure on a swept wing in flight, the simulation of jet plumes in for three different fuselage skin thickness configurations. The wind tunnels, supersonic flow development in slotted wind tunnels, analysis considered wing and fuselage sections made from stainless and the high-fidelity flight simulation of commercial transports. Also steel, beryllium copper, and aluminum. Examples are presented that considered are ground and flight test studies of reentry vehicle may be used to determine the time required to reach an adiabatic heatshield roll torque, aircraft Store separation motion prediction via condition after a change in total tfmperature. (Author) grid data trajectories, and high-resolution LDA measurements of Reynolds stress in boundary layers. B.J.
A80-26930 # The National Transonic Facility - Status and A80-26933 # Numerical simulation of the wind tunnel operational planning. R. R. Howell (NASA, Langley Research environment by a panel method. K. D. Lee (Boeing Commercial Center, Hampton, Va.). In: Aerodynamic Testing Conference, 11th, Airplane Co., Seattle, Wash.). In: Aerodynamic Testing Conference, Colorado Springs, Cob., March 18-20, 1980, Technical Papers. 11th, Colorado Springs, Cob., March 18-20, 1980, Technical Papers. New York, American Institute of Aeronautics New York, American Institute of Aeronautics and Astronautics, Inc., 1980, p . 1-9. (AIAA 80-0415) and Astronautics, Inc., 1980, p. 24-30. 13 refs. (AIAA 80-0419) The National Transonic Facility is scheduled to be completed in A simulation technique has been developed to analyze the 1982. Several technical concerns remain, including thermal stress testing environment of practical three-dimensional subsonic wind constraints which may limit the rate at which temperatures can be tunnels. A higher-order panel method was used to model complex changed, seal performance in the cryogenic environment, and the wind tunnel environments including the effects of slot openness, tunnel process controls which could affect data acquisition rate. The finite test section length, and model mounting system. The homoge- current design affords the capability of dealing with all these neous wall boundary condition represented the slotted test section. concerns if they become problems. The outstanding instrument need Results on a subsonic lifting wing are presented to demonstrate the is a real-time model surface deformation measurement system. interference effects due to various features in a rectangular tunnel. Finally, an examination of the occupancy cost and the cost of liquid The present technique provides a diagnostic tool for the interpreta- nitrogen for high Reynolds number tests indicates that operating tion of experimental data and an effective means for designing a test costs should not be an inhibiting factor in the use of the facility. environment with minimum interference. (Author) B.J. A80-26934 # On the historical development of apparatus A80-26931 # Automatic control of NASA Langley's 0.3- and techniques for smoke visualization of subsonic and supersonic meter cryogenic test facility. J. J. Thibodeaux (NASA, Langley flows. T. J. Mueller (Notre Dame, University, Notre Dame,Ind.). In:
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Aerodyn amic Testing Conference, 11th, Colorado Springs, Cob., A80.26941 # The simulation and modeling of jet plumes in March 18-20, 1980, Technical Papers. New York, wind tunnel facilities. H. H. Korst, R. A. White (Illinois, University, American Institute of Aeronautics and Astronautics, Inc., 1980, p. Urbana, Ill.), S.-E. Nyberg, and J. Agrell (Flygsekniska Forsoksanstal. 31-44. 60 refs. Research sponsored by the University of Notre Dame; ten, Bromma, Sweden). In: Aerodynamic Testing Conference, 11th, Grant No. AF-AFOSR-77-3412. (AIAA 80-0420) Colorado Springs, Cob., March 18-20, 1980, Technical Papers. The history of smoke visualization in wind tunnels is traced New York, American Institute of Aeronautics from 1893 to the present. The requirements necessary to produce a and Astronautics, Inc., 1980, p. 104. 116. 20 refs. Research sup- wind tunnel capable of being used for smoke visualization are ported by the European Research Office, FbygtekniskaForsoks- discussed along with the development of smoke generating equip- anstabten and U.S. Army; Grants No. DA-ERO-78-G-028; No. ment. The apparatus and techniques used for the visualization of DAAG29. 76-G.0209. (AIAA 80-0430) subsonic and supersonic flows are described, and some results on A high pressure hot gas supply system has been developed for practical aerodynamic problems are presented. B.J. the FFA 0.5 x 0.5 m supersonic wind tunnel to allow the study of aerodynamic interference effects caused by plume induced flow A80-26935 • # Visualization of the laminar-turbulent transi- separation from propulsive afterbodies. Experimental programs tion in the flow over an airfoil using the smoke-wire technique. S. M. carried out with air and Freon-22 confirmed the correctness of the Batill and T. J. Mueller (Notre Dame, University, Notre Dame, Ind.). plume simulation method with the accuracy of modeling extending In: Aerodynamic Testing Conference, 11th, Colorado Springs, Cob., over wide ranges of jet-to-ambient pressure ratios straddling the March 18-20, 1980, Technical Papers. New York, design points. (Author) American Institute of Aeronautics and Astronautics, Inc., 1980, p. 45-53. 16 refs. Grant No. NsG-1419. (AIAA 80-0421) A flow visualization technique, referred to as the smoke-wire, A80-26942 # Evaluation of a new concept for reducing was used for visualization of the transition of the free shear layer free-stream turbulence in wind tunnels. R. A. Wigeland, J. associated with the laminar separation bubble of a NACA 66 sub Tan-atichat, and H. M. Nagib (Illinois Institute of Technology, 3-018 airfoil section at low Reynolds number (50,000-130,000). The Chicago, Ill.). In: Aerodynamic Testing Conference, 11th, Colorado smoke-wire technique allows the introduction of fine smoke streak- Springs, Cob., March 18-20, 1980, Technical Papers. lines into the flow field through the electrical resistive heating of a New York, American Institute of Aeronautics and very fine wire which has been coated with oil and which is located Astronautics, Inc., 1980, p. 117-128. 7 refs. Grant No. NsG-1451. upstream from the leading edge of the airfoil section. Streakline data (AIAA 80-0432) were collected using both high speed still and motion picture A 45 deg-honeycomb flow manipulator, mounted parallel to the photography. (Author) corner turning vanes, was investigated for improving the flow quality in win d tunnels with little or no settling chamber length. This manipulator permits increased turbulence decay distance in compari- A80-26937 // Local skin friction and static pressure on a son to a conventional honeycomb arrangement. The resulting swept wing in flight. A. Bertelrud )Flygtekniska Forsoksanstalten, turbulence levels in a wind tunnel using the 45 deg-honeycomb are Bromma, Sweden). In: Aerodynamic Testing Conference, 11th, comparable to those obtained using a conventional honeycomb, but Colorado Springs, Cob., March 18-20, 1980, Technical Papers. only when a 45 deg-screen is mounted immediately downstream of New York, American Institute of Aeronautics the honeycomb and when some separation distance between the and Astronautics, Inc., 1980, 61-73. 14 refs. Air Materiel p. turning vanes and the 45 deg-honeycomb is provided for adequate Department of Sweden Contracts No. INK-82223-76-001-21-001; decay of the turning vane wakes (at least twice the spacing between No. INK-82223-77-001-21-001; No. INK-82223-77-116-21-001; No. the turning vanes). (Author) INK-82223-78-003-21-001. (AIAA 80-0423) A series of flight tests were performed to explore the possibility of using multiple total head/static probes (modified Preston tubes) A80-26943 • # A comparison of experimental and theoretical for the measurement of local skin friction and static pressure turbulence reduction from screens, honeycomb and honeycomb- distributions on a swept wing with moderate crossflow. The accuracy screen combinations. J. Scheiman and J. D. Brooks (NASA, Langley and repeatibility of the experiments were found to be acceptable. Research Center, Hampton, Va.). In: Aerodynamic Testing Confer- Calculations were performed (assuming infinite swept wing flow) ence, 11th, Colorado Springs, Cob., March 18-20, 1980, Technical with a three-dimensional Navier-Stokes code. The pressure coeffi- Papers. New York, American Institute of Aero- cient prediction was good, but the level of skin friction was nautics and Astronautics, Inc., 1980, p. 129-137. 11 refs. (AIAA overpredicted for the case of moderate viscous effects. B.J. 80-0433) A 1/2-scale model of a portion of the NASA Langley 8-foot transonic pressure tunnel was used to conduct some turbulence A80-26939 # Development of test methods for scale model reduction research. The experimental results are correlated with simulation of aerial applications in the NASA Langley Vortex various theories. Screens alone reduce axial turbulence more than the Facility. F. L. Jordan, Jr. (NASA, Langley Research Center, lateral turbulence; whereas, honeycomb alone reduce lateral turbu- Hampton, Va.). In: Aerodynamic Testing Conference, 11th, Colo- lence more than axial turbulence. Because of this difference, the rado Springs, Cob., March 18-20, 1980, Technical Papers. physical mechanism for decreasing turbulence for screens and New York, American Institute of Aeronautics and honeycomb must be completely different. Honeycomb with a Astronautics, Inc., 1980, p.79-93. 12 refs. )AIAA8O-0427) downstream screen is an excellent combination for reducing Methods have been developed at the Langley Vortex Research turbulence. (Author) Facility to simulate and measure the deposition patterns of aerially applied sprays and granular materials by means of tests with A80.26944 • # Additional flow quality measurements in the small-scale models of agricultural and dynamically scaled test Langley Research Center 8-Foot Transonic Pressure Tunnel. J. D. particles. Interactions between the aircraft wake and the dispersed Brooks, P. C. Stainback, and C. W. Brooks, Jr. )NASA, Langley particles are studied with the aim of modifying wake characteristics Research Center, Hampton, Va.). In: Aerodynamic Testing Confer- and dispersal techniques in order to increase swath width, improve ence, 11th, Colorado Springs, Cob., March 18-20, 1980, Technical deposition pattern uniformity, and minimize drift. This paper Papers. New York, American Institute of Aero- examines the particle sizing analysis, test methods for particle nautics and Astronautics, Inc., 1980, p. 138-145. 6 refs. )AIAA dispersal from the model aircraft, and measurement and computer 80-0434) analysis of test deposition patterns. Results that indicate improved Additional tests were conducted to further define the distur- control of chemical drift by winglets are presented to demonstrate bance characteristics of the Langley 8-Foot Transonic Pressure test methods. B.J. Tunnel. Measurements were made in the settling chamber with hot
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wire probes and in the test section with pressure transducers when detail. Test results indicate advantages over use of ground-based various methods were used to choke the flow. In addition to facilities, and indicate potential expanded use of these test aircraft. presenting rms values measured at various locations and tunnel (Author) condition, autocorrelations and cross correlation data are also presented. (Author) A80-26952 # Description of a new high-alpha, high-load, pitch-yaw dynamic stability test mechanism at AEDC. S. M. Coulter A80-26948 # Experimental investigation of the interference- and T. D. Buchanan (ARO, Inc., Arnold Engineering Development free flow field around a lifting wing-body model to establish cross Center, Arnold Air Force Station, Tenn.). In: Aerodynamic Testing flow characteristics for ventilated wind tunnel walls at low super- Conference, 11th, Colorado Springs, Cob., March 18-20, 1980, sonic Mach numbers. S.-E. Nyberg and H. Sorensen (Flygtekniska Technical Papers. New York, American Institute Forsoksanstalten, Bromma, Sweden). In: Aerodynamic Testing Con- of Aeronautics and Astronautics, Inc., 1980, p. 211-220. 8 refs. ference, 11th, Colorado Springs, Cob., March 18-20, 1980, Techni- (AIAA 80-0451) cal Papers. New York, American Institute of A description of a forced-oscillation test mechanism and associated instrumentation for measuring pitch- and yaw-damping Aeronautics and Astronautics Inc., 1980, p. 172. 182. 9 refs. (AIAA 80-0444) derivatives on aircraft configurations is presented. The mechanism is The interference-free flow field around a lifting delta-wing-body designed for 10-percent-scale models and can support 4000 lb normal configuration has been measured with a probe in wind tunnel tests. force and 1000 lb axial force. Results of laboratory tests and a wind Pressure and flow deflection were determined at Mach numbers 1.15, tunnel verification test of a typical fighter configuration indicate that 1.20 and 1.30, at nominal incidences of 0, 5, 15 and 25 deg and at the system can accurately measure dynamic moments; preliminary radial locations in relation to the model, where in wind tunnel tests results from cross and cross-coupling measurements are discussed. the walls are normally situated. Some comparisons with theoretical (Author) calculations are made. The results indicate that the required relationship between pressure drop and cross flow for a minimum interference wind tunnel wall is quite different from hitherto widely A80-26955 * # The influence of wing, fuselage and tail design used Criteria based on the flow field around a cone-cylinder at zero on rotational flow aerodynamics data obtained beyond maximum lift angle of attack. (Author) with general aviation configurations. W. Bihrle, Jr. )Bihrle Applied Research, Inc., Jericho, N.Y.) and J. S. Bowman, Jr. (NASA, Langley Research Center, Hampton, Va.). In: Aerodynamic Testing Confer- ence, 11th, Colorado Springs, Cob., March 18-20, 1980, Technical A80-26949 # New requirements, test techniques, and devel- Papers. New York, American Institute of Aero- opment methods for high fidelity flight simulation of commercial nautics and Astronautics, Inc., 1980, p. 237-246. 18 refs. )AIAA transports. E. F. Carlson, T. J. Galbraith; and P. C. Rumsey (Boeing 80-0455) Commercial Airplane Co.. Seattle, Wash.). In: Aerodynamic Testing The NASA Langley Research Center has initiated a broad Conference, 11th, Colorado Springs, Cob., March 18-20, 1980, general aviation stall/spin research program. A rotary balance system Technical Papers. New York, American Institute was developed to support this effort. Located in the Langley spin of Aeronautics and Astronautics, Inc., 1980, P. 183-189. )AIAA tunnel, this system makes it possible to identify an airplane's 80-0445) aerodynamic characteristics in a rotational flow environment, and In order to improve the fidelity of flight simulation, a number thereby permits prediction of spins. This paper presents a brief of departures from past practices have been implemented in the description of the experimental set-up, testing technique, five model modeling techniques at Boeing. A fully nonlinear aerodynamic model programs conducted to date, and an overview of the rotary balance is used to avoid the approximations associated with linear derivatives. results and their correlation with spin tunnel free-spinning model More comprehensive corrections are made to the aerodynamic data results. It is shown, for example, that there is a large, nonlinear base for scale effects due to the Reynolds number. Significant dependency of the aerodynamic moments on rotational rate and that changes have been made in the methods used to adjust the these moments are pronouncedly configuration-dependent. Fuselage aerodynamic data for the effects of aeroelasticity. In the present shape, horizontal tail and, in some instances, wing location are shown paper the use of modern wind tunnel test techniques and flight test to appreciably influence the yawing moment characteristics above an methods to generate and validate an improved aerodynamic data base angle of attack of 45 deg. (Author) for the simulator is described, and specific illustrations of wind tunnel testing on the Boeing 767 are given. The importance of a computerized data handling system to organize the increased size and A80-26956 # Measurements of the dynamic performance of complexity of the aerodynamic data base is stressed, and examples of the main drive fan of the RAE 5 metre pressurised low speed wind the use of modern minicomputers in an interactive graphics mode to tunnel. R. W. Jeffery (Royal Aircraft Establishment, Aerodynamics accomplish this task are presented. B.J. Dept., Farnborough, Hants., England). In: Aerodynamic Testing Conference, 11th, Colorado Springs, Cob., March 18-20, 1980, Technical Papers. New York, American Institute of Aeronautics and Astronautics, Inc., 1980, p. 247-255. 9 refs. A80.26950 # Control and data acquisition aircraft for (A IAA 80-0456) ALCM flight tests. J. D. Lang and R. A. Pitzer )USAF, Directorate of Tests were carried out to monitor and evaluate the performance Flight Test Engineering, Wright-Patterson AFB, Ohio). In: Aero- of the blades in the main drive fan of the 5 meter pressurized low dynamic Testing Conference, 11th, Colorado Springs, Cob., March speed wind tunnel. A technique was developed for in situ mainte- 18-20, 1980, Technical Papers. New York, nance checking to detect the onset of internal cracking or debaminari- American Institute of Aeronautics and Astronautics, Inc., 1980, p. zation in the glass reinforced plastic blades. Three of the ten fan 190-197. 6 refs. )AIAA 80-0446) blades were instrumented with Strain gauges to monitor the dynamic Ten aircraft were modified for control of the Air Launched performance of the fan under different loadings resulting from Cruise Missile (ALCM) and for data acquisition during flight testing. combinations of fan speed and tunnel pressurization. The effect of a Instrumentation systems were designed and installed b y the 4950th model was also investigated, with the model both stalled and Test Wing on two of the Wing's EC-135N Advanced Range unstabled. (Author) Instrumentation Aircraft (ARIA) and on eight Air Force Flight Test Center F-4E 'chase' aircraft. These airborne facilities, which are used A80-26957 * # Measurements of control stability characteris- for reception, recording and relay of all flight test data as well as for tics of a wind-tunnel model using a transfer function method. I. fail-safe control of the unmanned test vehicles, are described in Chopra (NASA, Ames Research Center, Moffett Field; NASA!
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Stanford, Joint Institute for Aeronautics and Acoustics, Stanford, A80-26960 • # Exploratory investigation of the effects of Calif.) and J. D. Ballard (NASA, Ames Research Center, Moffett vortex bursting on the high angle-of-attack lateral-directional stabili- Field, Calif.). In: Aerodynamic Testing Conference, 11th, Colorado ty characteristics of highly-swept wings. J. L. Johnson, Jr., S. B. Springs, Cob., March 18-20, 1980, Technical Papers. Grafton, and L. P. Yip (NASA, Langley Research Center, Hampton, New York, American Institute of Aeronautics and Va.). In: Aerodynamic Testing Conference, 11th, Colorado Springs, Astronautics, Inc., 1980. p. 256-261. (AIAA 80-0457) Cob., March 18-20, 1980, Technical Papers. Recent state-of-the-art techniques in rotor systems include the New York, American Institute of Aeronautics and Astronautics, Inc., use of active feedback to augment the dynamic control characteris- 1980, p. 282-297. 6 refs. (AIAA 80-0463) tics of an aircraft system. A recent test of a stoppable rotor with A recent low-speed wind-tunnel investigation of highly-swept blade circulation blowing was conducted in the Ames Research wings has shown that vortex breakdown at high angles of attack can cause large destabilizing effects on static lateral-directional stability Center's 40- by 80-ft wind tunnel. A major part of the test schedule was dedicated to the acquisition of data to determine the stability of characteristics, and that the destabilizing effects of vortex break- a closed-loop hub-moment feedback control system. Therefore, the down can be greatly aggravated by model support strut interference open-loop control response was measured at several flight conditions effects. The present paper discusses these effects based on the results to ascertain the stability of the system prior to the final closed-loop of static force tests of several highly-swept wing configurations for feedback control test. Measurements were made during both the different wind-tunnel strut setup arrangements. Also included in the stopped and rotating rotor modes, and open-loop Bode plots were paper are photographs obtained during tuft-, smoke-, and helium- obtained for the control loops associated with the moments about bubble flow visualization studies to indicate wing flow behavior the longitudinal and lateral axis. . (Author) patterns. (Author)
A80-26961 A new rig for flight mechanics studies in the ONERA Aerothermodynamic Test Center of Modane. J. Christophe A80-26958 # Selected wind tunnel testing developments at (ONERA, Châtillon-sous-Bagneux, Hauts-de-Seine, France). In: Aero- the Boeing Aerodynamics Laboratory. J. P. Crowder, E. G. Hill, and dynamic Testing Conference, 11th, Colorado Springs, Cob., March C. R. Pond (Boeing Co., Seattle, Wash.). In: Aerodynamic Testing 18-20, 1980, Technical Papers. New York, Conference, 11th, Colorado Springs, Cob., March 18-20, 1980, American Institute of Aeronautics and Astronautics, Inc., 1980, p. Technical Papers. New York, American Institute 298-305. (AIAA 80-0464) of Aeronautics and Astronautics, Inc., 1980, p. 262-272. (AIAA The new rig of the large Si Modane wind tunnel is designed for 80-0458) the study of the low-speed handling qualities of large models. These Three unique testing techniques that recently have been models, powered or not, will be studied under various environmental introduced at the Boeing Aerodynamic Laboratory are described; the effects: ground effect, side wind on runways, atmospheric gusts, and laser angle meter, fluorescent mini-tufts for surface flow visualiza- large angle of attack excursion. The system has four degrees of tion, and the photo-graphical flow field survey technique. The laser freedom: pitch, yaw, and roll inside the model for steady position angle meter, installed in the Boeing Transonic Wind Tunnel, is a and oscillation; and steady position and oscillation of the supporting highly precise and responsive fringe counting interferometer that strut. Device requirements are summarized, and preliminary tunnel directly measures model angle of attack at working distances of 4 to acceptance testing is discussed. B.J. Sm. Use of the sophisticated angle meter is warranted when accurate drag data levels are required for internal balance mounted models or when rapid acquisition of model angular attitude data is essential. Fluorescent mini-tufts, extremely small nylon monofilaments, are A80-26962 # A system for the measurement of the attitude sufficiently nonintrusive to be used concurrently with conventional of wind tunnel models. R. W. Jeffery, A. N. Tuck, and R. D. Law data acquisition on subsonic and transonic models. This capability is (Royal Aircraft Establishment, Aerodynamics Dept., Farnborough, particularly useful for wind tunnels where model access is limited. Hants., England(. In: Aerodynamic Testing Conference, 11th, Colo- The photo-graphical flow field survey technique permits acquisition rado Springs, Cob., March 18-20, 1980, Technical Papers. and online presentation of complete graphical records of total New York, American Institute of Aeronautics and pressure isobars, or other isoparameter Contour plots, with a greatly Astronautics. Inc., 1980, p. 306-315.6 refs. (AIAA 80-0465( simplified traversing mechanism and without any computer analysis. Due to very large aerodynamic loads, deflections in the support Information obtained with this technique provides valuable insight systems of models tested in the RAE 5 meter pressurized low speed into the structure of model flow fields. (Author) wind tunnel can be significant. For the continual measurement of the achieved model attitude a system, which includes a laser yaw-meter for the measurement of attitude in the horizontal plane, has been developed. From simple geometry the yaw angle can be calculated A80-26959 II Aircraft s're separation motion prediction via and, for a model mounted on the mechanical balance, the equipment grid data trajectories. J. P. Billingsley (ARO, Inc., Arnold Engineer- can also measure displacements from the balance calibration center. ing Development Center, Arnold Air Force Station, Tenn.; TRW Attitude in pitch and roll is measured by an orthogonal set of Defense and Space Systems Group, Redondo Beach, Calif.), J. T. accelerometers. (Author) Best, and R. H. Burt (ARO, Inc., Arnold Engineering Development Center, Arnold Air Force Station, Tenn.). In: Aerodynamic Testing A80-26963 # The experimental modeling of unstalled super- Conference, 11th, Colorado Springs, Cob., March 18-20, 1980, sonic turbofan flutter. R. E. Riffel (General Motors Corp., Detroit Technical Papers. New York, American Institute Diesel Allison Div., Indianapolis, Ind.) and S. Fleeter (Purdue of Aeronautics and Astronautics, Inc., 1980, p . 273-281. 16 refs. University, West Lafayette, Ind.(. In: Aerodynamic Testing Confer- (A IAA 80-0462) ence, 11th, Colorado Springs, Cob., March 18-20, 1980, Technical The grid data trajectory (GDT) technique of computing store Papers. New York, American Institute of Aero- separation trajectories is established as an accurate method by nautics and Astronautics, Inc., 1980, p. 316-324. 8 refs. (AIAA comparisons with the captive trajectory technique. This was done by 80-0454) obtaining an extensive and systematic grid of static aerodynamic The paper examines experimental techniques necessary to forces and moments on a store model in the flow field beneath an extend current experimental unsteady rectilinear cascade modeling aircraft model. The data were employed to predict trajectories using capability to include the relatively low supersonic inlet Mach the GOT technique; the GOT predictions were compared directly number, high pressure ratios, and high reduced frequency values with captive trajectories generated by the AEDC-VKF Captive characteristic of the unstalbed supersonic flutter of fan stages. Trajectory System. (Author) Particular consideration is given to the cascade modeling concepts,
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the steady and time-invariant experimental techniques, fabrication facilitate measurement of internal drag and adjustment to free-flight and instrumentation considerations, data acquisition and reduction values. Excellent agreement is obtained between the adjusted wind procedures, and the correlation of steady, high-frequency time- tunnel results and the ballistic range data. Limited pressure measure- invariant translation mode oscillating cascade data with correspond- ments within the control section indicate that the flow field is ing state-of-the-art predictions. B.J. complex, with the internal dreg resulting from combined effects of wake and stagnation pressures. Qualitative agreement is obtained A80-26964 • # The development of a self-streamlining flexible between internal force and pressure data. (Author) walled transonic test section. M. J. Goodyer and S. W. D. Wolf (Southampton University, Southampton, England). In: Aerodynamic Testing Conference, 11th, Colorado Springs, Cob., March 18-20, A80.27021 Lightning protection for aircraft. P. Little 1980, Technical Papers. New York, American (Atomic Energy Research Establishment, Culham Laboratory, Institute of Aeronautics and Astronautics, Inc., 1980, p. 325-335. 9 Abingdon, Oxon, England). Atom, vol. 281, Mar. 1980, p.63-67. refs. Research supported by the Science Research Council of The problems of protecting aircraft against lightning are England; Grant No. NsG-7172. (AIAA 80-0440) discussed. The structure of electric fields existing due to electric This design eliminates the Uncertainties in data from conven- charge in a cloud base is analyzed. Relative motions of a lightning tional transonic test sections. Sidewalls are rigid, and the flexible channel with respect to an aircraft are described along with typical floor and ceiling are positioned by motorized jacks controlled by zones on an aircraft. Laboratory simulation and testing are also on-line computer to minimize run times. The tunnel-computer outlined. V. T. combination is self-streamlining without reference to the model. Data is taken from the model only when the walls are good streamlines, and is corrected for the small, known but inevitable A80-27127 # Analysis of the nonuniqueness of solutions to residual interferences. Two-dimensional validation testing in the the problem of flow separation for small-aspect delta wings (Issledo- Mach range up to about 0.85 where the walls are just supercritical vanie need instvennostj resheniia zadachi ob otryvnom obtekanii shows good agreement with reference data using a height:chord ratio sistemy krylo-fiuzeliazh malogo udlineniia). A. V. Voevodin. TsAGI, of 1.5. Techniques are under development to extend Mach number Uchenve Zapiski, vol. 10, no. 1, 1979, p. 10-18. 10 refs. In Russian. above 1. This work has demonstrated the feasibility of almost A method is proposed for analyzing the nonuniqueness of eliminating wall interferences, improving flow quality, and reducing solutions for leading-edge separation from slender delta wings. The power requirements or increasing Reynolds number. Extensions to method is essentially a modification of Pullin's (1973( iterative three-dimensional testing are outlined. (Author) method for calculating inviscid separation from conical slender bodies, which, however, does not require the use of a fairly exact solution to the problem with a fully developed vortex sheet as the A80-26967 • # High-resolution LDA measurements of initial approximation, and makes it possible to obtain solutions based Reynolds stress in boundary layers and wakes. K. L. Orloff and L. E. on such simple flow schemes as Brown and Michael's (1954) model. Olson (NASA, Ames Research Center, Moffett Field, Calif.). In: Flow patterns, lift coefficients, and pressure distributions are Aerodynamic Testing Conference, 11th, Colorado Springs, Cob., obtained for a range of angles of attack and aspect ratios. The March 18-20, 1980, Technical Papers. New York, calculations confirm the nonuniqueness of solutions for wing-body American Institute of Aeronautics and Astronautics, Inc., 1980, p. configurations. 363-374. 11 refs. (A IAA 80-0436) V.P. The turbulent character of she boundary layer and wake associated with an airfoil has been studied at a Reynolds number of A80-27132 # Analytical determination of the influence of 1,000.000 and a Mach number of 0.1. To accomplish these elasticity and mass distribution on the aerodynamic characteristics of measurements, a unique laser Doppler anemometer (LDA( has been an aircraft in quasi-steady motion (Teoreticheskoe opedelenie developed that is capable of sensing two velocity components from a vliianiia uprugosti i raspredeleniia mass konstruktsii na nekotorye remote distance of 2.13 m. Using special simultaneity logic and aerodinamicheskie kharakteristi ki samoleta v kvaziustanovivshemsia counter-type signal processors, the geometrical features of the LDA dvizhenii). G. A. Amir'iants. TsAG/, Uchenye Zapiski, vol. 10, no. 1, have been exploited to provide variable spatial resolution as low as 1979, p. 55-63. 6 refs. In Russian. 0.2 mm. By combining the LDA with an on-line computerized data A procedure, based on the method of polynomials, is proposed acquisition and display system, it has been possible to measure mean for calculating the characteristics of static aeroelasticity. The velocity and Reynolds stress tensor distribution at several locations calculations show that the mass distribution in elastic design has a along the upper surface of a 0.9-m-chord, flapped airfoil installed in substantial influence on the major aerodynamic characteristics of an the Ames 7-by 10-Foot Wind Tunnel. (Author) aircraft in quasi-steady flight. Some possible means of achieving mass redistributions to improve the aerodynamic behavior of an aircraft are examined. A80-26968 # Wind tunnel and flight test drag comparisons V.P. for a guided projectile with cruciform tails. W. H. Appich, Jr. (Martin Marietta Aerospace, Orlando, Fla.), R. L. McCoy (U.S. Army, Ballistics Research Laboratories, Aberdeen Proving Ground, Md.(, A80-27134 # Singularities of the numerical solution of the and W. D. Washington (U.S. Army, Missile Command, Redstone algebraic Riccati equation in matrix form by a modification of the Arsenal, Ala.(. In: Aerodynamic Testing Conference, 11th, Colorado Lax-Wendroff method (Osobennosti chislennogo resheniia matrich. Springs, Cob., March 18-20, 1980, Technical Papers. nogo algebraicheskogo uravneniia Rikkati metodom ustanovleniia). .New York, American Institute of Aeronautics and V. M. Kuvshinov. TsAGI, Uchenye Zap/ski, vol. 10, no. 1, 1979, p. 69-76. 6 refs. In Russian. Astronautics, Inc., 1980, p. 375-382. 11 refs. Grant No. DAAA09- 76-2001. (AIAA 80-0426) The conditions and rate of convergence of an iterative process Drag measurements from full-scale wind tunnel tests and for solving the algebraic Riccati equation by a modification of the ballistic range firings of a cannon-launched guided projectile are Lax-Wendroff method are examined, and the singularities of the compared at Mach numbers between 0.8 and 1.5. The projectile has numerical solution, caused by poor convergence are analyzed. The internally-housed cruciform wings and sails which deploy through effectivenness of applying the Euler method and the Runge-Kutta longitudinal body slots. Within the control section, air can flow method to the numerical integration of first-order differential Ricatti longitudinally and transversely between slots during flight; however, equations is compared. V.P. no flow passes through the projectile base, which is sealed to prevent damage during the gun launch. These internal flow characteristics A80.27135 # A single-step method of optimizing statically were preserved in the wind tunnel model which was designed to indeterminate minimum-volume systems (Odnoshaaos',i
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optimizatsii staticheski neopredelimykh sistem minimal'nogo A80-27143 # Distribution of forces and stresses along rows ob'ema). E. K. Lipin. TsAG/, Uchenye Zapiski, vol. 10, no. 1, 1979, of bolted connections (Raspredelenie usilii i napriazheni, P0 riadam 77.89. In Russian. p. boltovykh soedinenii). V. F. Kozhevnikov. TsAG/, Uchenye Zapiski, A single-step method is proposed for calculating the design vol. 10, nu. I, 1979, p. 134-139. In Russian. parameters for statically indeterminate minimum-volume systems. The paper presents a method of determining forces transmitted The method is based on determining 'parasitic' constraints, the by multiple row bolted connections operating in shear by plane presence of which in the system does not permit simultaneous models of optically sensitive material. Distribution of forces and realization of optimality conditions and strain compatibility. It is stresses is investigated in three-, four-, and five-row models of a shown that in a system that is free of parasitic constraints, the double shear bolt connection; it is shown that increasing the number stresses are independent of the mass distribution in the system of bolt rows above three does not produce appreciable reduction of elements, so that the optimal parameters can be determined in a forces and maximum stresses in the outer, highly loaded rows of tingle step. The idea of the method is illustrated by examples connections. A. T. involving trusses. Three theorems for the optimal design of elastic systems are formulated and are used to construct a single-step optimization process. V.P. A80-27147 # Numerical modeling of supersonic flow near a thin delta wing with discontinuous edge (Chislennoe modelirovanie sverkhzvukovogo techeniia okolo tonkogo treugol'nogo kryla s A80-27136 # Minimum-weight wing in the presence of lift constraints (Krylo minimal'nogo vesa pri ogranichenii po nesushchei izlomom kromki). A. N. Minailos. TsAGI, Uchenye Zapiski, vol. 10, sposobnosti). N. V. Banichuk, V. I. Biriuk, I. I. Koande, A. A. no. 2, 1979, p. 22-29. 9 refs. In Russian, Mironov, and A. P. Seiranian. TsAGI, Uchenye Zapiski, vol. 10, no. The method of Kosykh and Minailos (1977) is used to study the 1, 1979, p. 90-98. 7 refs. In Russian. supersonic flow (at freestream Mach of 2-8) past a delta wing with The necessary conditions for minimizing the weight functional discontinuous edges at angles of attack of 12, 15, 18, 23, and 27 deg. of the wing are identified and are used as a basis to calculate Two different conditions of flow near the upper surface of the wing numerically the optimal rigidity distribution over the wing by a are examined: with and without developed vortex bundles. It is gradient method. Results obtained for various values of the prob- found that these vortices are formed by tangential discontinuities at lem's parameters are examined, along with the influence of 'the angle the leading edges of the wing. B. J. of sweep and the ratio of torsional to flexural rigidity on the optimal solution. The dependence of the solution on the permissible lift A80-27148 # Numerical method for calculating supersonic losses due to aeroelastic strains is analyzed. V. P. flow past a plane air intake with detached shock wave (Chislennyi metod rascheta obtekaniia ploskogo vozdukhozabornika sverkhzvu- kovym potokom na rezhimakh s vybitoi udarnoi volnoi). N. I. A80-27137 # Application of geometrical programming to Tilliaeva, TsAGI, lJchenye Zapiski, vol. 10, no. 2, 1979, p. 30-40. 11 problems of optimal design (Primenenie geometricheskogo program- refs. In Russian. mirovaniia k zadacham optimal'nogo proektirovaniia konstruktsii). An ideal gas model is used to develop an algorithm for V. A. Pavlov and V. A. Shiriniants. TsAGI, Uchenye Zapiski, vol. 10, calculating supersonic flow past an intake with detached shock wave. no. 1, 1979, p. 99-105. In Russian. A difference scheme for calculating the flow is described, and some The analysis deals with the problem of optimizing an axially numerical results for different freestream Mach numbers are present- compressed reinforced panel. The strength conditions and the design ed. Finally, approximate methods for determining the integral and technological constraints are written in the form of inequalities, characteristics of the intake are discussed, using the panel weight as the objective function. The effectiveness of B.J. applying geometrical programming methods to the solution of the optimization problem is demonstrated. V.P. A80-27152 , The use of the spectral summation of fatigue damages in order to examine the combined stress state of structures (Primenenie spektral'nogo summirovantia ustalostnykh povrezhdenii A80-27138 # Influence of the angle of attack on the thermal pri slozhno-napriazhennom sostoianii konatrujktsii). V. D. II 'ichev. flux at the stagnation point at supersonic speeds (Vliianie ugla ataki TsAGI, Uchenye Zapiski, vol. 10, no. 2, 1979, p. 65-75. 8 refs. In na teplovoi potok v kriticheskoi tochke pri sverkhzvukovykh Russian. skorostiakh), G. I. Maikapar, TsAGI, UchenyeZapiski, vol. 10, no. 1, The spitrai summation method is used to obtain estimates of 1979, p. 106-111. In Russian. the fatigue damage of aircraft structures in the case of a random In the present paper, the variation of heat flux at the stagnation dynamic combined stress state, The finite element method and the point of a blunt-nosed body of continuously varying curvature with obtained estimates are used to develop an algorithm for calculating the angle of attack is analyzed under the assumption that the heat the fatigue zones of the structure. A method for calculating the static flux is proportional to the square root of the mean curvature. It is component of the combined stress state is described. B.J. shown that for large angles of attack, the optimal configuration is not an oblate ellipsoid or elliptical cylinder, as is the case at zero angle of attack, but rather configurations close to a circular cylinder A80-27157 # Pressure distribution in rectangular wing or a sphere. V. P. /blade/ sections during curvilinear motion in an incompressible medium (Raspredelenie davleniia v secheniiakh priamougol'nogo kryla /lopasti/ pri krivolineinom dvizhenii v neszhimaemoi srede). L. A80-27139 # Influence of the empennage on the effective S. Pavlov. TsAGI, UchenyeZapiski, vol. 10, no. 2. 1979, p. 104-108. thrust of jet engine exhaust nozzles (Vliianie opereniia na effek- In Russian. tivnuiu tiagu reaktivnykh sopi VRD). B. N. Mikhailov and E. V. Results of an experimental investigation of the effects of a Pavliukov. TsAG/, UchenyeZapiski, vol. 10, no. 1, 1979, p. 116-121. time-varying velocity vector on the pressure distribution on a section 7 refs. In Russian. of a rectangular wing moving along a trajectory corresponding to the The paper deals with an experimental study of the interference plane projection of the rotational trajectory of a moving propeller of tail surfaces with a jet nozzle at freestrearn Mach numbers blade section are discussed. A flat, rectangular wing with a between 0.6 and 1.14. A parameter used by Glasgow and Santman NACA-0012 profile was attached at its end to a rotating shaft in the (1972) to generalize experimental data on the drag of isolated engine open section of a wind tunnel, and changes of pressure were nacelles is modified for tail units. The critical value of this parameter, measured around ten wing sections at various air speeds with a which separates the region where interference increases the effective constant zero angle of attack. It is found that for a wing moving drag from the region where the effective drag is reduced by against the direction of air flow, for which total speed and slip angle interference is determined. V. P. vary slowly, wing pressure distribution does not differ significantly
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from that of a wing moving in a straight line, while on the return subsonic leading edges at supersonic speeds. The effectiveness of section, the direction and magnitude of the velocity change abruptly suction for wings with rounded leading edges is demonstrated. V. P. and the elementary air mass experiences a greater increase in pressure, leading to flow reversal. The direct interaction between the A80-27183 # Improvement of the convergence of the wing and its vortex bundle, which occurs only in curvilinear motion, A.L.W. method of polynomials in designing small-aspect-ratio wings is also discussed. (Uluchshenie skhodimosti metoda mnogochlenov v raschetakh kryl'ev malogo udlinenlia). E. I. Kriuchkov. TsAGI, Uchenye Zapiski, A80-27165 # Calculation of minimum-weight and vol. 10, no. 3, 1979, p. 130-135. In Russian. maximum-rigidity structures in the presence of design constraints In the practical application of the method of polynomials there (Raschet silovykh konstruktsii minimal'nogo vesa i maksimal'noi arises an error in she calculation of the stiffness matrix, which is zhestkosti pri nalichii konstruktivnykh ogranichenii). T. G. Zuraev. magnified when determining the inverse stiffness matrix. The error TsAGI, Uchenve Zapiski, vol. 10, no. 2, 1979, p. 149-155.8 refs. In involved in the solution then depends on the accuracy of the Russian. calculations. To reduce the effect of the poor formulation of the The analysis dealt with the problem of designing for minimum stiffness matrix, it is proposed to minimize the total energy weight or maximum rigidity in the presence of constraints placed, in functional under certain additional static equilibrium conditions.S.D. the form of equalities or inequalities, on the parameters of the load-carrying members. A procedure for solving the problem is A80-27202 Value analysis and the optimum Cost concept proposed and is applied to a mass-minimization problem in the applied to aerospace (L'analyse de la valeur et le Principe conception presence of design and strength constraints. V. P. pour un coat optimum /C.C.0./ appliqué a I'aérospatiale), R. Tassinari )Société Nationale I ndustrielle Aérospatiale; Association L'Aéronautique A80-27167 II Hysteresis of aerodynamic characteristics (0 Francaise pour l'Analyse de la Valeur, Paris, France). gisterezise aerodinamicheskikh kharakteristik). A. I. Kur'ianov, G. I. etl'Astronautique, no. 80, 1980, p.29-37. In French. Stoliarov, and R. I. Shteinberg. TsAG/, Uchenye Zap/ski, vol. 10, no. The concept of optimum cost considered as part of the design 3, 1979, p. 12-15. In Russian. stage for new aircraft is discussed. Attention is given to the The paper dealt with an experimental investigation of the economics concerning costs of production and maintenance, known integral aerodynamic characteristics and the pressure distribution as life-cycle-cost, as well as to economics and performance criteria. In over wing models and segmented conical bodies of revolution at addition, the design-to-cost method of program administration is subsonic and supersonic speeds. The results reveal a hysteresis nature considered, taking U.S. Defense Department experience into ac- of the behavior of the aerodynamic characteristics of forces and count. J.P.B. moments and of the pressure distribution with decreasing or increasing angle of attack. A distinct dependence of the hysteresis on A80-27203 Laminar separation bubble with transition the Reynolds number is noted. V.P. /theory and experiment/ (Bulbe de décollement laminaire avec A80-27168 # Similarity of the aerodynamic characteristics transition /théorie et expérience/), C. Gleyzes, J. Cousteix, and J.-L. of delta wings at supersonic speeds (Podobie aerodinamicheskikh Bonnet (ONERA, Centre d'Etudes et de Recherches de Toulouse, (Co/loque d'Aérodynamique Appliquée, 16th, kharakteristik treugol'nykh kryl'ev pri sverkhzvukovykh skoro- Toulouse, France). Lille, France, Nov. 12-16, 1979.) L'Aéronautiqueetl'Astronautique, stiakh). A. N. Minailos. TsAG/, Uchenye Zapiski, vol. 10, no. 3, no. 80, 1980, p. 41-57. 14 refs. In French. 1979. p. 16-26. 13 refs. In Russian. In the present paper, the errors in the aerodynamic characteris- The leading edge bubble on a Peaky airfoil was studied experimentally using a 200 mm chord profile. Boundary layer tics calculated within the framework of shock layer theory, or Brown and Michael's (1955) formula in slender body theory, are determined measurements regarding mean velocity and longitudinal intensity of turbulence were carried out at Reynolds numbers for R sub c (c is on the basis of the supersonic flow past infinitely thin triangular plates. It is shown that the similarity parameters of linear theory, as the chord length) between 100,000 and 1,000,000. A study of the well as Messiter's (1963) parameters of hypersonic theory, are valid transition process is also presented by means of flow visualizations J.P.B. over a wide range of variation of the determining quantities. V.P. and a spectral analysis of the velocity.
A80-27173 # Method of determining steady-state aero- A80-27221 Simulation defines alternatives for Copen- dynamic characteristics for an elastic aircraft in free longitudinal hagen terminal expansion. E. Bastiansen, J. Hviid. and P. Matthiesen motion (Metodika opredelenhia statsionarnykh aerodinamicheskikh )Peter Matthiesen A/S, Herlev, Denmark). Airport Forum, vol. 10, kharakteristik prodol'nogo dvizhenia uprugogo svobodnogo Feb. 1980, p. 21-24. samoleta), D. D. Evseev and lu. F. laremchuk. TsAGI, Uchenve The paper deals with an analysis of alternate designs of an Zap/ski, vol. 10, no. 3, 1979, p. 71-77. In Russian. apron/terminal system within a planning horizon of 1980 to 2000. The paper deals with the problem of determining experimentally The study takes into account forecasts for such factors as: air traffic the steady-state aerodynamic characteristics of an elastic aircraft in and passenger volumes, transfer passenger patterns, aircraft mix, free directional flight. An approximate procedure is proposed for operations, and the number and size of aircraft stands. V.T. determining the influence on the aerodynamic characteristics of the aircraft's elastic deformations produced by inertial mass forces. The A80-27222 Aeropuerto de Caracas - An unusual new procedure is based on comparing wind-tunnel deformation data for general aviation facility near the city, A. Calzadilla. Airport Forum, rigid and elastic models. The potentialities of the procedure are vol. 10, Feb. 1980, p. 35-40. Design problems of the Aeropuerto de Caracas are described. demonstrated by examples. V.P. Consideration is given to the airport planning, engineering and architectural features, hangar design studies, and environmental A80-27175 # Induced drag and lift-drag ratio of swept wings aspects. Emphasis is placed on the large amount of earth moving at supersonic speeds (Induktivnoe soprotivlenie i aerodinamicheskOe required to obtain graded surfaces for the airport complex. V.T. kachestvo strelovidnykh kryl'ev pri sverkhzvukovykh skorostiakh). R. A. Breusova, N. P. Vedeneeva, and A. I. Shteinberg. TsAG/, Uchenye Zap/ski, vol. 10, no. 3, 1979, p. 87-90. In Russian. A80-27223 The use of computer systems in air traffic The paper deals with a theoretical and experimental study of the control. H. Ebert )Telefunken AG, Ulm, West Germany). Airport induced drag and lift-drag ratio of wings of various sweep with Forum, vol. 10, Feb. 1980, p . 47, 48, 50-52, 54.
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The use of computer systems for air traffic control (ATC) is airborne system is totally compatible with existing full-scale ground reviewed. Consideration is given to the main areas that can be taken preflight-maintenance and data processing display facilities over by computers: processing flight plan data, processing radar data, A. T. display of the air traffic situation on screens, communication of data from and to other control centers, and furnishing of decision aids. A80.27231 A low cost airborne data acquisition system. Electronic computers, display units, data transmission systems, and H. N. Webb (USAF. Airborne Instrumentation Div., Eglin AFB, other peripheral systems used in ATC are outlined. V. T. Fla.). In: Society of Flight Test Engineers, Annual Symposium, 10th, Las Vegas, Nev., September 4-6, 1979, Proceedings. Lancaster, Calif., Society of Flight Test Engineers, A80-27227 Achieving effective Radar Cross Section flight 1979. 6 p. profiles on the B-i aircraft. J. W. Walkington and L. W. Huster The paper presents a Pulse Code Modulation (PCM) data (USAF. Flight Test Center, Edwards AFB, Calif.). In: Society of acquisition system which is accurate and easy to calibrate and Flight Test Engineers, Annual Symposium, 10th, Las Vegas, Nev., maintain. This airborne system is modular and software program- September 4-6, 1979, Proceedings. Lancaster, mable, and would be interfaced with the aircraft central computer Calif., Society of Flight Test Engineers, 1979. 16 p. data bus to gather general airframe and avionics data, and utilize This paper analyzes the flight profiles of the B-i Radar Cross remote signal conditioning units for other unique parameters. An Section (RCS) missions to ascertain whether they produce sufficient off-the-shelf system capable of growth to over 1000 channels was data to correlate with previously acquired data from a quarter-scale chosen; PCM data is recorded on board and telemetered for real time model. Analysis of the time-expended versus benefits-derived is also assessment, and a cockpit video system composed of multiple presented. Finally, alternate flight profiles are investigated to cameras and a cassette video tape recorder provides HUD, radar, and determine whether they will provide part of the required data with E-O weapons recording capability. A. T. less time expended. (Author)
A80-27228 First experience with telemetry and real time A80-27232 Airborne video instrumentation/data reduc- data reduction at Gates Learjet. J. P. Dwyer and E. Tooley (Gates tion. J. E. Seller (McDonnell Aircraft Co., St. Louis, Mo.). In: Learjet Corp., Wichita, Kan.). In: Society of Flight Test Engineers, Society of Flight Test Engineers, Annual Symposium, 10th, Las Annual Symposium, 10th, Las Vegas, Nev., September 4-6, 1979, Vegas, Nev., September 4-6, 1979, Proceedings. Proceedings. Lancaster, Calif., Society of Flight Lancaster, Calif., Society of Flight Test Engineers, 1979. 14 p. Test Engineers, 1979. 17 p. The paper examines the development of airborne video instru- The paper considers a telemetry and real time data reduction mentation systems and ground-based video reduction stations. The system. The choice of a ground based system including cost, the airborne system consisting of a HUD video camera system, video front end, computer, and special peripherals are discussed, noting its interface unit, and long range electro-optical TV sensor tracker limitations which reduce the number of parameters that can be system is described; the video data reduction station which will processed simultaneously. Applications of the telemetry system to generate a copy of the HUD camera video tape, provide for the Model 28/29 Longhorn aircraft with NASA designed winglets simultaneous playback of the tapes for rapid examination, and will and store separation tests in a 'Special Missions' aircraft are produce digitized coordinate data of a target relative to some point described. It is concluded that the telemetry system reduced flight in the field-of-view is discussed. It is concluded that airborne video and data turnaround time, increased safety, and decreased data instrumentation is cost-effective in evaluating aircraft performance, errors. A. T. its avionics equipment, and its pilot. AT.
A80-27229 Are we spending too much on flight tes instrumentation. C. M. Miller (USAF, Flight Test Center, Edwards A80-27233 Investigation of engine performance degrada- AFB, Calif.). In: Society of Flight Test Engineers, Annual tion of TF33-P-7 engines. R. E. Hart (USAF, Flight Test Center, Symposium, 10th, Las Vegas, Nev., September 4-6, 1979, Proceed- Edwards AFB, Calif.). In: Society of Flight Test Engineers, Annual Symposium, 10th, Las Vegas, Nev., September 4-6, 1979. ings, Lancaster, Calif., Society of Flight Test Engineers, 1979. 7 p. Lancaster, Calif., Society of Flight Test Engineers, 1979. 13 p. The paper considers the problem of expenditures on flight test instrumentation. The reasons for these expenditures including As a result of the actual C-141A cruise performance being less instrumentation users' inadequate time for participation in she design than that in the Flight Manual, the Air Force initiated a test program process, ignorance of instrumentation and of data reduction costs, to attempt to correlate engine performance degradation with time and a lack of shelf hardware to provide a cheaper method are since overhaul. Analysis of test cell data from more than 40 discussed; alternatives to digital data instrumentation systems TF33-P-7 engines showed no apparent correlation. In addition, there including photo panel, gun camera, tape recorder, and analog strip was no noticeable correlation between performance degradation and recorder are considered. Finally, involvement in cost analysis by the engine cycles. These results were unexpected. Test cell calibrations flight test engineer is examined, concluding that the solution of the conducted on engines used on the stretch YC-1418 flight test problem of overspending on flight test instrumentation lies in the program showed no fuel flow or thrust deterioration; however, an involvement of the instrumentation engineer at the start of the increase in turbine exhaust temperature was noted. With the current instrumentation process. A. T. emphasis on fuel economy, further investigation in the area of fuel flow and engine operation time is warranted. (Author)
A80-27230 MIDS -The right tool for small test jobs. W. G. Densford and D. L. Jones (McDonnell Aircraft Co., St. Louis, Mo.). A80-27234 VSTOL test techniques utilizing laser tracking. In: Society of Flight Test Engineers, Annual Symposium, 10th, Las M. B. Deitchman (U.S. Naval Air Systems Command, Naval Air Test Vegas, Nev., September 4-6, 1979, Proceedings. Center, Patuxent River, Md.). In: Society of Flight Test Engineers, Lancaster, Calif., Society of Flight Test Engineers, 1979. 7 p. Annual Symposium, 10th, Las Vegas, Nev., September 4-6, 1979, The paper considers Minature Integrated Data Systems (MIDS). Proceedings. Lancaster, Calif., Society of Flight This system features onboard recording and telemetry, and consists Test Engineers, 1979. 9 p. of a set of palletized units which replace production hardware The paper presents various test methods used in the evaluation without structural changes and use production wiring to gain access of VSTOL aircraft utilizing automatic laser tracking. The extensive to basic aircraft and avionic systems information. Installation time is manual labor and long turnaround time required by photo-theodolite required only for program-peculiar, hard-wired measurands. The tracking has been virtually eliminated by the near real-time capability
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of the Automatic Laser Tracking System (ALTS) which does not rely 4.6, 1979, Proceedings. Lancaster, Calif., Society on a surveyed runway centerline for the test aircraft to track, but of Flight Test Engineers, 1979. 9 p. determines three-dimensional aircraft space positioning with a range The paper describes the testing of F . 18 aircraft at the U.S. Naval well in excess of airfield operations. The laser tracking system, the Air Test Center. The F/A . 18 replaces the F-4 and A-i models, and it YAV-813 flight demonstration program, and the girder bridge ski is a fighter/attack common, single-seat, twin-engine, high perfor- jump evaluation programs are discussed, concluding that the ALTS mance strike fighter with high reliability and low maintenance. The system provides improved safety and efficiency in VSTOL aircraft Naval Air Test Center was used as the test site to optimize testing. A.T. cross-utilization of test aircraft, minimize personnel and hardware support cost, and establish a common data base. Five of the first A80.27235 Experience from testing the Viggen electronic flight test aircraft have completed 155 flights for a total of 220 flight systems utilizing existing computer capacity. J. G. Uhlin (Saab- hours; simulators were used extensively to predict the F/A.18 Scania AB, Linkoping, Sweden). In: Society of Flight Test Engineers, characteristics, and Navy preliminary assessments were made of the Annual Symposium, 10th, Las Vegas, Nev., September 4.6, 1979, APG-65 radar system, initial arrested landings, and catapult shots. Proceedings. Lancaster, Calif., Society of Flight A. T. Test Engineers, 1979. 11 p. The paper examines the testing of the Viggen electronic systems A80-27240 Helicopter crash position indicator flight trials. utilizing existing computer capacity. In the testing of JA37 Viggen K. D. Nelson (Aerospace Engineering Test Establishment, CFB Cold studies were made of decreasing the pilot workload by presenting Lake, Alberta, Canada). In: Society of Flight Test Engineers, Annual errors from the required test flight condition on the HUD to enable Symposium, 10th, Las Vegas, Nev., September 4-6, 1979, Proceed- the pilot to maintain the correct condition during landing tests and ings. Lancaster, Calif., Society of Flight Test of methods to optimize test runs by using syncpulses for start of Engineers, 1979. 12 p. target maneuvers. The sync is originated by a computer and The paper examines the Canadian Forces (CF) helicopter crash transmitted to the target, signalling to start the maneuvers. To position indicator flight trials. These tests were conducted to clear implement these objectives, available core-memory areas in the the selected Crash Position Indicator (CPI) systems on fixed and Central Data Computer of the aircraft were used to optimize the rotary -'ing aircraft; for the rotary wing systems, a test method was usage of currently available hardware without additional expendi- developed using a combination of surface and stand-off tufting to tures. A. T. define the flow-field characteristics in the vicinity of the CPI. Results were used to predict the separation characteristics and the trajectory A80-27236 Firebrand anti-ship missile target - Flight test of the CPI airfoil, concluding that this tufting prediction method in program objectives and vehicle instrumentation requirements. L. 0. conjunction with a computer model will reduce the large test matrix Lehman (U.S. Naval Material Command, Naval Air Development on the CH-135 Twin Huey CPI installation to manageable size. A.T. Center, Warminster, Pa.). In: Society of Flight Test Engineers, Annual Symposium, 10th, Las Vegas, Nev., September 4 .6, 1979, Proceedings. Lancaster, Calif., Society of Flight A80-27241 Aircraft motion analysis using limited flight Test Engineers, 1979. 19 p. and radar data. A. C. Wingrove, R. E. Bach, Jr. (NASA. Ames The paper examines the Firebrand supersonic anti-ship missile Research Center, Aircraft Guidance and Navigation Branch, Moffett target system which will provide realistic threat simulation for test Field, Calif.), and E. K. Parks (Arizona, University, Tucson, Ariz.(. and evaluation of ship defense weapons systems. The flight test plans In: Society of Flight Test Engineers, Annual Symposium, 10th, Las'' including the vehicle configuration requirements and objectives for Vegas, Nev.. September 4-6, 1979, Proceedings. the evaluation phase of the Contractor Test and Evaluation and Navy Lancaster, Calif., Society of Flight Test Engineers, 1979. 18 p. 11 Technical Evaluation are discussed; demonstration flights which will refs. collect mission profile data and reliability data are described. The development and application of methods for reconstructing, Instrumentation requirements for each vehicle configuration are from a limited set of recorded data, a comprehensive scenario of defined, and a summary of the planned flight test schedules is aircraft motions before and during an accident are described. The presented. A.T. accuracy of these analytical methods is investigated using data recorded onboard the Ames CV-990 research aircraft. In these experiments, the expanded set of data, derived from either foil or A80. 27237 Tactical navigation system testing. D. M. ATC records, is compared with corresponding values measured by Carlson and J. C. Dunn (USAF, Armament Development and Test the research instrumentation system onboard the aircraft. The results Center, Eglin AFB, Fla.(. In: Society of Flight Test Engineers, indicate that many of the derived quantities are in good agreement Annual Symposium, 10th, Las Vegas, Nev., September 4-6, 1979, with the corresponding onboard measurements. A recent application Proceedings. Lancaster, Calif., Society of Flight of this procedure using actual accident records is presented and Test Engineers, 1979. 17 p. potential applications are briefly reviewed. (Author) The paper examines tactical navigation system testing. The major avionics systems including the AN/ARN-101 Digital Modular Avionics System of F-4 aircraft with its software and the Pave Tack A80•27242 Factorial design of experiments in the test and electro .optical target acquisition, laser designation, and weapon delivery system are discussed. The 'hardware-in-the-loop' ground evaluation of a complex control system. B. L. Hildret (U.S. Naval Air simulation facility is described noting that new and existing systems Systems Command, Naval Air Test Center, Patuxent River, Md.). In: should be integrated; the integration of the Pave Tack System on the Society of Flight Test Engineers, Annual Symposium, 10th, Las F-4 and F-1 11aircraft exemplified the advantages and disadvantages Vegas, Nev., September 4-6, 1979, Proceedings. of testing described here. It is concluded that simulation, integration, Lancaster, Calif., Society of Flight Test Engineers, 1979. 20 p. and test environment must be considered in a complete simulation Factorial design is applied to the testing and optimization of the facility which can test navigation systems, perform target U.S. Navy's Automatic Carrier Landing System (ACLS(. Two, three, acquisition/identification, and test delivery of guided and unguided and four factorial design test matrices are developed to examine the effect of proportional, derivative, integral, and acceleration feed- missiles. A. T. backs on ACLS control. The vertical glideslope deviation is found to decrease with increasing proportional and derivative feedbacks, while A80. 27239 Testing the F-18 at the U.S. Naval Air Test an increase in the integral gain results in increased deviation. The Center. J. L. Dunn (U.S. Naval Air Systems Command, Naval Air changing of the acceleration feedback has little effect on the vertical Test Center, Patuxent River, Md.). In: Society of Flight Test glideslope deviation. Factorial design is shown to be an effective Engineers, Annual Symposium, 10th, Las Vegas, Nev., September technique in the design and analysis of complex structures. V. L.
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A80-27243 From tape measure to computer tape. K. J. SNR enhancement and pulse recognition. The matched filter Bicker )Pilatus Aircraft, Ltd., Stans, Switzerland). In: Society of structure takes into account photon noise, modulation noise, Flight Test Engineers, Annual Symposium, 10th, Las Vegas, Nev., generation-recombination (GR) noise, Contact noise, and various September 4 .6, 1979, Proceedings. Lancaster, thermal noise sources. A multicolor radiant-intensity structure for Calif., Society of Flight Test Engineers, 1979. 15 p. target discrimination is developed by analyzing the uncertainties in The data acquisition system of a PC-7 Turbo Trainer, utilizing such target irradiance parameters as range, temperature, projected PCM is described. The system includes a desktop computer with a area, and emissivity. Bias terms, variances, and other statistical printer, plotter, and flexible disk driver. Consideration is given to descriptors are derived. Certain statistical discrimination techniques flight tests, sy stem specifications, and software. V.T. are discussed that exploit the radiant-intensity format. Helstrom's method for processing radar signals is adapted to a four-channel pulse-recognition system for which degradation due to arrival time A80-27257 Applying pressure . . . Relieving stress. H. K. delays and mismatched filters is discussed. (Author) Lew. Aviation Engineering and Maintenance, vol. 4, Feb. 1980. p. 27-29. The article describes the process of stress coining which it is believed can reduce fatigue failure, and extend the useful life of A80-27377 F/A-18 status report. J. E. Krings (McDonnell equipment subject to high cyclic loading. It is shown that Stress Douglas Corp., St. Louis, Mo.). (Society of Experimental Test Pilots, coining is a cold work technique in which pressure is exerted to Symposium, 23rd, Beverly Hills, Calif., Sept. 26-29, 1979.1 Society compress metal in or around a hole or slot beyond its elastic limit of Experimental Test Pilots, Technical Review, vol. 14, no. 4, 1979, into a plastic state. After the material recovers, residual compressive P. 1-9. stresses remain. It is concluded that since these stresses are located F/A-18 aircraft performance during flight tests is discussed in around the hole, they subsequently reduce service induced fatigue. terms of flying qualities, propulsion, carrier suitability, structural type stresses. M.E.P. tests, avionics development, and high angle-of-attack studies. Atten- tion is given to range-while-scan, track-while-scan, and velocity search radar modes, as well as to problems with regard to lateral sensitivity, a leaky environmental control system, and nose wheel liftoff. J.P.B. A80-27269 Future large cargo aircraft technology, R. H. Lange )Lockheed-Georgia Co., Advanced Concepts Dept., Marietta, A80-27378 Night/adverse weather A-10 evaluator program Ga.). Lockheed Horizons, Spring 1980, p. 16-24. /A-10BI. W. H. Shawler )Fairchild Republic Co., Farmingdale, N.Y.). Some innovative design concepts are surveyed which show (Society of Experimental Test Pilots, Symposium, 23rd, Beverly potential for significant improvements in aerodynamic efficiency, Hills, Calif., Sept. 26-29, 1979.) Society of Experimental Test Pilots, operating economics, and operational efficiency. Topics examined Technical Review, vol. 14, no. 4, 1979, p. 10-21. include military/civil commonality issues, and cargo capacity. Atten- The A-10B fighter aircraft, which is designed for low-level flying tion is given to the environmental impact of future cargo aircraft and night/adverse weather MAW) conditions, is described. Atten- covering advanced composite materials, advanced aircraft propulsion, tion is given to avionics, including the head-up display which is the aircraft drag reduction, alternate fuels, and innovative design key display for the complete system, the forward-looking infrared concepts. M.E.P. receiver, radar, the inertial navigation system, radar altimeter, laser ranger, and low light level TV. It is concluded that two crewmembers A80.27270 The changing horizons for technical progress. are required to significantly increase the probability of mission II. R. H. Hopps )Lockheed-California Co., Burbank, Calif.). Lock- success, and N/AW mission capability has been demonstrated for the heed Horizons, Spring 1980, 32-39. p. A-10. J.P.B. Some new technologies are surveyed that offer the possibility of obsoleting the present concept of a jet transport. Attention is given A80. to such areas as laminar flow control, all-wing concepts, superlarge 27379 The Tornado all-weather high-speed low-level aircraft, advanced turboprops, air cargo, avionics, hydrogen, VTOL system. L. Obermeier )Messerschmitt-Bblkow-Blohm GmbH, Munich, and V/STOL. Also covered are a nuclear-powered airplane and a West Germany). (Society of Experimental Test Pilots, Symposium, supersonic transport. It is concluded that new developments will be 23rd, Beverly Hills, Calif., Sept. 26-29, 1979.) Society of Experi- of an evolutionary manner rather than a sudden jump to a new mental Test Pilots, Technical Review, vol. 14, no. 4, 1979, p. 22-36. The Interdictor/Strike version of the Tornado, an all-weather, generation of aircraft, as in the past. M.E.P. low-level aircraft useful in high-threat environments, is described. Particular attention is given to the terrain-following )TF) system, A80-27306 Experimental measurement of fields excited including radar, computer, and inertial navigator, as well as to TF inside the fuselage of an aircraft. J. Perini )Syracuse University, cockpit displays and controls, and safety and warning logics. Also Syracuse, N.Y.). IEEE Transactions on Electromagnetic Compatibil- considered are ride comfort, weapon aiming system, and the (two ity, vol. EMC-22, Feb. 1980, p. 72-75. 5 refs. man) crew workload. J.P.B. The results of Piatkowski et al., 1975 and A. T. Adams et al., 1975 have been used in computing the fields excited inside the fuselage of an aircraft when subjected to external electromagnetic A80-27380 F.16 European test and evaluation. T. P. radiation. In addition, the fields were assumed to propagate in free McAtee and L. Timm (USAF, Flight Test Center, Edwards AFB, space instead of inside a cavity. The present measurement program Calif.). (Society of Experimental Test Pilots, Symposium, 23rd, shows that it is improper to make this assumption, since the presence Beverly Hills, Calif., Sept 26-29, 1979.) Society of Experimental of metallic structures and the cavity resonances may account for Test Pilots, Technical Review, vol. 14, no. 4, 1979, 37-51. deviations over 20 dB in relation to the free space field. p. M.E.P. Four F-16's were tested in Europe in order to qualify for operations in adverse weather and to complete operational test and evaluation. Areas surveyed included routine operations, air-to-air and air-to-surface effectiveness, and operational suitability, and overall, A80-27347 Methodology for target discrimination. F. the performance of the F-16 was highly satisfactory. It was found McNolty (Lockheed Research Laboratories, Palo Alto, Calif.) and R. that the reclined seat significantly improves the pilot's ability to Clow. Applied O p tics, vol. 19, Mar. 15, 1980. p. 984'999. 21 refs. perform under high g loads. In addition, 64 deficiencies were noted, The objective is to distinguish the true target from point-target mostly of a minor nature, but some significant problems with the imitators and from extended-target clutter in the exoatmospheric radar and the air-to-air refueling system were reported for the first regime. Matched filters are carefully studied from the viewpoint of time. J.P.B.
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A80-27381 VAV-8B status report. C. A. Plummer, Jr. Dassault-Brequet Aviation, Vaucresson, Hauts-de-Seine, France). (McDonnell Douglas Corp., St. Louis, Mo.). (Society of Experimental (Society of Experimental Test Pilots, Symposium, 23rd, Beverly Test Pilots, Symposium, 23rd, Beverly Hills, Calif., Sept. 26-29, Hills, Calif., Sept. 26-29, 1979.) Society of Experimental Test Pilots, 1979.) Society of Experimental Test Pilots, Technical Review, vol. Technical Review, vol. 14, no. 4, 1979, p. 123-137. 14. no. 4, 1979, p. 52-58. The development and performance of the Mystere Falcon 50 The YAV-8B aircraft was modified from the AV-8A, containing (F-SO) triengine business jet is discussed. The F-SO is basically these major changes: wing with a supercritical airfoil constructed composed of F-10 engines on the F-20 fuselage, but having a wing almost entirely of graphite epoxy materials, a second row of optimized for supercritical flow with less curvature on its upper side, auxiliary inlet air doors and a changed inlet lip shape, positive thus providing a wide zone of moderate supersonic flow terminated circulation generated by large flaps interconnected with the nozzles by a mild shock wave. The F-SO can climb directly to 41.000 ft and such that full flap (62 degrees) is obtained with approximately 50 fly 3500 nautical miles in still air; maximum cruise is Mach 0.81 to degrees of nozzle angle, and lift improvement devices including 0.84, depending on weight. J.P.B. strakes fitted to the 30-mm gun pods under the aircraft and a retractable door which connects them at the forward end. Flight test A80-27387 CL-600 Challenger. F. D. Adkins (Canadair, performance is discussed, where the goal was to demonstrate a Ltd., Montreal, Canada). (Society of Experimental Test Pilots, tropical-day vertical takeoff and transition to wing-borne flight at a Symposium, 23rd, Beverly Hills, Calif., Sept. 26-29, 1979.) Society takeoff weight/hover weight ratio of 0.99. J.P.B. of Experimental Test Pilots, Technical Review, vol. 14, no. 4, 1979, p. 138-144. The CL-600 Challenger flight test program is described, in which A80-27382 Have Bounce. R. A. Borowski (USAF, Flight the aircraft is averaging 25 to 30 hours per month; nearly 400 stalls Test Center, Edwards AFB, Calif.). (Society of Experimental Test have been done. The flight flutter program, which utilizes a flutter Pilots, Symposium, 23rd, Beverly Hills, Calif., Sept. 26-29, 1979.) vane system powered from the aircraft hydraulic system with the Society of Experimental Test Pilots, Technical Review, vol. 14, no. vanes mounted on the wingtips, the aft fuselage, and the top of the 4, 1979, p. 61-67. vertical stabilizer, is discussed; Mach 0.94 and 460 KCAS have been The validation of computer simulations of F-4 dynamic response achieved. J.P.B. to multiple runway repairs was carried out utilizing the AM-2 mat, made up of extruded aluminum sections 2 ft wide which interlock to A80.27388 Review of five years of flight testing the B-i. form a mat 54 ft wide and of any desired length. Testing to date has J. S. Smith, Ill and F. A. Fiedler )USAF, Flight Test Center, shown that for a 55,000 pound F-4E, reinforcement occurs at about Edwards AFB, Calif.). (Society of Experimental Test Pilots, Sympo- 32, 55, and 155 knots, where the 55-knot point leads to the highest sium, 23rd, Beverly Hills, Calif., Sept. 26-29, 1979.) Socigjy of loads. In addition, the rigid body response of the F-4, characterized Experimental Test Pilots, Technical Review, vol. 14, no. 4, 1979, p. by bouncing up and down on the main gear struts, seems to be 209-231. consistent at a frequency of about 2 hertz. J.P.B. Five years of B-i testing are reviewed, considering flutter, flying qualities, airloads, and performance testing. In addition, tests of the weapons delivery system are discussed, as well as a hinge moment A80.27383 General aviation icing flight test. W. H. problem, and capsule versus ejection seats. Furthermore, terrain Lawson (Piper Aircraft Corp., Lock Haven, Pa.). (Society of following )TF) testing was made, and the most successful aspect of Experimental Test Pilots, Symposium, 23rd, Beverly Hills, Calif., the B-i TF flight tests was the response of the airplane to the TF Sept. 26-29, 1979.) Society of Experimental Test Pilots, Technical commands; the most serious anomalies in the flight test program Review, vol. 14, no. 4, 1979, p. 68-76. were electrical system malfunctions. J.P.B. FAA certification of the Navajo, a light, twin reciprocating engined commuter aircraft, for flight into known icing is discussed. Attention is given to the simulated fiberglass ice shapes installed on parts of the wing, on horizontal and vertical tail surfaces that were A80-27389 Crossing the Channel in the Gossamer Alba- not deiced by the pneumatic boots, and on the unheated radome/ tross. P. MacCready (Aerovironment, Inc., Pasadena, Calif.), (Society nose cone, in order to confirm the handling qualities, stability, and of Experimental Test Pilots, Symposium, 23rd, Beverly Hills, Calif, stall characteristics of the aircraft during or following an icing Sept. 26-29, 1979.) Society of Experimental Test Pilots, Technical encounter. The development and flight tests of the icing tanker are Review, vol. 14, no. 4, 1979, p. 232-243. also considered. J.P.B. The design and performance history of the Gossamer Albatross (GA), the first human-powered aircraft to cross the English Channel, A80-27384 • The Quiet Short-Haul Research Aircraft and its predecessor the Gossamer Condor, the first human-powered /QSRA/. J. L. Martin (NASA, Ames Research Center, Moffett Field, aircraft to sustain controlled flight, are discussed. Emphasis was Calif.). (Society of Experimental Test Pilots, Symposium, 23rd, placed on having a simple, large, light, slow flying, wire-braced craft; Beverly Hills, Calif., Sep t. 26-29, 1979.) Society of Experimental therefore, carbon filament tubing was used, along with ribs con- Test Pilots, Technical Review, vol. 14, no. 4, 1979, p. 77-93. 10 refs. structed from expanded polystyrene foam and a mylar covering. Also The Quiet Short-Haul Research Aircraft )QSRA), designed to discussed are the apparent mass effect, and the relevance of the GA expand the technology base of the upper-surface blowing propulsive- flight for possible applications of low power. J.P.B. lift principle in order to establish criteria for the U.S. aircraft industry and for advanced STOL aircraft, is considered. The aircraft, which includes a three-axis, single channel, limited authority series A80-27415 Computational aerodynamics on large compu- type stability augmentation system, and a high-speed data system is ters. W. F. Ballhaus and F. R. Bailey (NASA, Ames Research Center, described. Also discussed are STOL and acoustic performance, and Moffett Field, Calif.). (Symposium on Computers in Aerodynamics, handling qualities, particularly thrust effects. The QSRA has demon- Farmingdale, N. V., June 4, 5, 1979.) Computers and Fluids, vol. 8, strated its ability, even with the critical engine inoperative, to Mar. 1980, p. 133-144. 22 refs. approach at 66 knots (wing loading of 83 lb/sq ft) and on a 9 degree Three examples of advances in computational aerodynamics; (1) glidepath; to maneuver in a 700-ft radius turn, and to land in an FAA three-dimensional inviscid transonic analysis, (2) design calculations field length of 1450 ft (over a 35-ft obstacle). J.P.B. for wings, and (3) the computation of viscous-induced aileron buzz, are reviewed. Attention is given to wing surface pressures, design optimization, computer memory, speed and advanced solution A80.27386 The development of the world's first triengine methods on parallel computer architecture. It is determined that business jet, the Mystere Falcon 50. J. A. Resal )Avions Marcel many implicit approximate-factorization schemes, that have been
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developed for Navier-Stokes equations, can be coded to run loaded test specimens. The effects of compression load intensity efficiently on microprocessors. C.F.W. were such that lightly loaded graphite structures (such as aircraft secondary structure) were insensitive to impact damage. In more heavily loaded structures, (such as wing panels), however, appreciable A80-27479 Acceleration of multicycle fatigue testing on aluminum structural alloys. M. N. Stepnov and S. P. Evstratova reductions in compressive strength occurred. The implications of the (Moskovskii Aviatsionnyi Tekhnologicheskii I nstitut, Moscow, tests for structural design are discussed by comparing panel masses for designs where ultimate strains have been reduced due to impact USSR). (Zavodskaia Laboratoriia, vol. 45, July 1979, p. 649-653.) Industrial Laboratory, vol. 45, no. 7, Jan. 1980, p. 805-809. 8 refs. considerations with the masses of designs with higher ultimate Translation. strains. Finally, preliminary test data is presented to show the A forced testing method for specimens and parts of aluminum possibility of improvements in damage tolerance achievable by using alloys is presented which makes it possible to evaluate fatigue an alternate matrix material. (Author) properties and their scattering for a large life range. Tests were performed on smooth and notched specimens 8 to 10 mm in diameter. In order to plot fatigue curves with an equal probability of A80-27599 # Operational implications of some NACA/ failure, the invariance of the variability coefficient was utilized for NASA rosary wing induced velocity studies. H. H. Heyson (NASA, the endurance limit to the life base. It is shown that by using the Langley Research Center, Hampton, Va.). Illinois Department of proposed forced testing technique to determine the endurance limit Transportation, Annual Midwest Helicopter Safety Seminar, 3rd, of specimens and structural elements of deformable aluminum alloys Joliet, III., Feb. 26, 27, 1980, Paper. 53 p. 60 refs. for bases of 100 to 1000 million cycles the testing times can be The purpose of the paper is to present some highlights of the shortened by a factor of 20 to 200 respectively, with satisfactory broad NACA/NASA efforts throughout the years, with particular accuracy. V.L. emphasis given to those results having special importance to aircraft users. Subjects covered include the rotor wake and vortex hazards, partial power descent and minimum speed for autorotation. Several A80-27596 # The potential for damage from the accidental aspects of ground effect are covered, including nonuniform wakes, release of conductive carbon fibers from aircraft composites. V. L. nonlinear power and control effects in forward flight, and yaw Bell (NASA, Langley Research Center, Hampton, Va.). NATO, control at near-hovering speeds. C.F.W. AGARD, Specialists Meeting on the Effect of Service Environment on Composite Materials, Athens, Greece, Apr. 16, 1980, Paper. 22 p. 37 refs. A80-27612 Reliability growth testing of avionic equip- The paper considers the potential for damage from the ment. E. B. Gamble (RCA, Avionics Systems Div., Van Nuys, Calif.). accidental release of conductive carbon fibers from aircraft compos- RCA Engineer, vol. 25, Dec. 1979-Jan. 1980, ites. The electrical conductivity of carbon and graphite fibers has led p. 52-56. 5 refs. The article examines the features of a reliability growth program to electrical equipment damage from the inadvertent release of virgin used to achieve cost effective reliability for new systems produced fibers into the atmosphere; an accidental release of carbon fibers for the aviation market. The origin of reliability growth is reviewed from filamentary composites from the burning of crashed commer- and illustrative data are presented from results obtained with the cial airliners could damage electrical and electronic equipment. The PriMUS. 20/30 X-oand digital weather radar. experimental and analytical results by NASA of the methods of M.E.P. assessing the extent of potential damage in terms of costs is presented; the NASA materials research program to provide alternate or modified composites to overcome electrical hazards of carbon A80-27622 Source book on materials for elevated- composites in aircraft Structures is described. A. T. temperature applications: A comprehensive collection of outstanding articles from the periodical and reference literature. Edited b y E. F. Bradley. Metals Park, Ohio, American Society for Metals, 1979. 408 p. $35. A80-27597 • # Composite components on commercial air- The book focuses on industrial turbine applications, super 12% craft. H. B. Dexter (NASA, Langley Research Center, Hampton, Cr steels, stainless steels, heat-resistant alloy castings, iron-base and Va.). NATO, AGARD, Specialists Meeting on the Effect of Service iron-containing superalloys, nickel-base superalloys, cobalt-base Environment on Composite Materials, Athens, Greece, Apr. 13-18, superalloys, directional solidification, protective coatings, and weld- 1980, Paper. 23 p . 16 refs. ing. Papers were presented on high-temperature oxidation and The paper considers the use of composite components in corrosion of superalloys in the gas turbine, environment-dependence commercial aircraft. NASA has been active in sponsoring flight of the mechanical properties of metals at high temperature, the super service programs with advanced composites for the last 10 years, 12% Cr steels, strength of stainless steels at elevated temperatures, with 2.5 million total composite component hours accumulated since and welding of the nickel alloys and dissimilar metals for high- 1970 on commercial transports and helicopters with no significant temperature service. A. T. degradation in residual strength of composite components. Design, inspection, and maintenance procedures have been developed; a A80-27716 # Airport radio navigation systems (Radio- major NASA/US industry technology program has been developed to navigatsionnye sistemy aeroportov). K. V. Makarov, V. V. Cherve- reduce fuel consumption of commercial transport aircraft through tsov, I. F. Sheshin, and V. A. Volynets. Moscow, lzdatel'stvo the use of advanced composites. A.T. Transport, 1978. 336 p. 60 refs. In Russian. The book deals with radio navigation systems used at airports for landing aircraft and for navigation. Principles of organizing air A80-27598 * # Graphite-epoxy panel compression strength traffic are discussed, along with the interaction between navigation reduction due to local impact. M. P. Card and M. D. Rhodes (NASA, and landing aids during all stages of flight. The principle of operation Langley Research Center, Hampton, Va.). NATO, AGARD,Special- and the block diagrams of homing stations, radio marker beacons, ists Meeting on the Effect of Service Environment on Composite radio direction finders, glide-path beacons, and radio-range beacons Materials, Athens, Greece, Apr. 13-18, 1980, Paper. 14 p. 10 refs. are examined. V. P. A review of results from on-going research to investigate the effects of low-velocity impact on the compressive strength of A80-27723 # Stationary movement of wings in the transonic graphite-epoxy structures is presented. Extensive tests have been regime (Movimiento estacionario de alas en regimen transónico). F. J. conducted on sandwich beams, laminated plates and stiffened panels. S. Calero. Madrid, Universidad Politécnica, Doctor lngeniero Aero- Conditions for failures were investigated by impact tests on statically náutico Thesis, 1978. 155 p. 245 refs. In Spanish.
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The exact transonic small perturbation equation of order delta Computational techniques are covered including a calculation pro- (squared) is derived; avoidance of the explicit determination of the cedure for three-dimensional, viscous, compressible duct flow, far field singularities of a wing is accomplished by using appropriate numerical prediction of three-dimensional subsonic diffuser flows, transformations. The three-dimensional boundary value problem is and analysis of the three-dimensional flow in a turbine scroll. Finally, split into a series of simplified problems corresponding to its two the characteristics of ducts and diffusers are examined. M.E.P. limits: in the outer flow the wing shrinks to a line of singularities; in the inner region the problem becomes a local investigation of two-dimensional airfoil sections. The local non-uniform region at A80-27733 II Effect of non-rotating passages on perfor- wing tips of large curvature is also investigated. J.P.B. mance of centrifugal pumps and subsonic compressors. A. Kovats. In: Flow in primary, non-rotating passages in turbomachines; Proceedings of the Winter Annual Meeting, New York, N.Y., A80-27725 Fundamentals of design. V . Fin design for December 2-7, 1979. New York, American combat aircraft. B. R. A. Burns. Air International, vol. 18, Jan. 1980, Society of Mechanical Engineers, 1979, p. 1-14. 31 refs. p. 21-25. It is noted that in the past studies of flow conditions in pumps The basic principles of fin design are discussed and the pros and and compressors, as well as design recommendation, were Concentrat- cons of various alternative layouts are presented. Attention is given ed on the impeller. It is only in the last decades that researchers have to rudder designs, twin-fins, all-moving fins and ventral fins, as well directed more attention to the importance of inlet conditions and as to dihedral and anhedral tailplanes, dorsal fins, and wing-tip fins. diffusers or volutes. The paper evaluates and surveys test results and C.F.W. calculations which can be of use to designers. Attention is given to the problem of turbulence, noting that at this time the appropriate A80-27726 767 . A Boeing for the 'eighties. Air Interna- physical laws can not be expressed in exact mathematical formulas. tional, vol. 18, Feb. 1980, p. 59-66, 99. M.E.P. The article surveys the development of the 767 into its present twin engine, low tail configuration. Attention is given to the 7X7 wide body studies and the 7N7 narrow body using the 727/737 A80-27734 # Rotating stall in a vaneless diffuser of a fuselage cross section. Discussion also covers the various twin and centrifugal fan. K. Imaichi and H. Tsurusaki (Osaka University, three engines proposals, low and T-tails, and upper surface blowing Toyonaka, Japan). In: Flow in primary, non-rotating passages in configurations which have the engines forward of and above the wing turbomachines; Proceedings of the Winter Annual Meeting, New leading edge. Finally, complete specifications for 767-200 are given. York, N.Y., December 2-7, 1979. New York, M.E.P. American Society of Mechanical Engineers. 1979, p. 23-31. In a centrifugal fan which had an axisymmetric vaneless diffuser, A80-27727 The light fighter market - . - and a European circumferentially uniform discharge at the exit of the diffuser proposal. Air International, vol. 18, Feb. 1980, p. 77-81. suddenly changed into a periodic circumferentially fluctuating flow It is noted that the market for light fighters is of a similar size to state. Detailed measurements were carried Out on this fluctuating that for heavier fighters, and that the export market is considerably flow state, and it was proved to be a rotating stall in the diffuser. larger than that for heavier models. Attention is given to the Piranha Properties of the rotating stall in the diffuser are made clear, and it is concept, designed by a Swiss-based organization, which is shown to pointed out that a measured rotating stall is different from the be comparable with the F-5E in terms of weight and capability. previously studied rotating stall in a diffuser proper. Moreover, a Discussion covers armament such as Oerlikon KCA or Mauser Bk-27 causal relation between back flow in the diffuser and the rotating cannon, and avionics. Also covered are various engine options, stall is actually proved, and numerical values on a radial extent of the including twin engines, as well as performance, political and back flow are presented. These data can be used to predict the economic considerations. M.E.P. initiation of the rotating stall. (Author)
A80.27735 # Aerodynamic performance of a centrifugal A80-27728 Fundamentals of design. VI Tailplanes, tail- compressor with caned diffusers. Y. Yoshinaga, H. Mishina, F. less and canard design. B. R. A. Burns (British Aerospace, Warton Koseki, N. Nishida (Hitachi, Ltd., Tokyo, Japan), and I. Gyobu Div., Preston, Lancs., England). Air International, vol. 18, Mar. 1980, (Hitachi, Ltd., Tsuchiura, Japan). In: Flow in primary, non-rotating p. 126-129. passages in turbomachines; Proceedings of the Winter Annual It is noted that in contrast to fins the design of tailplanes has Meeting, New York, N.Y., December 2-7, 1979. evolved progressively with the extending speed range of combat New York, American Society of Mechanical Engineers, 1979, p. aircraft. The article discusses the design of longitudinal stabilizing 33-40. 9 refs. and control surfaces, and examines the pros and cons of alternative An experimental investigation to improve the stage efficiency configurations. Topics covered include control power, tailless air- through the use of vaned diffusers is presented. Sixteen different craft, canard configurations, and artificial stability. M.E.P. vaned diffusers were tested on a model compressor rig. The results showed that the pressure recovery of the vaned diffuser increased up to the critical diffusion ratio, which was shown to be approximately A80-27732 Flow in primary, non-rotating passages in 0.5. The measured pressure distribution around vanes of the turbomachines; Proceedings of the Winter Annual Meeting, New well-designed diffusers which had the fair diffusion ratios, were York, N.Y., December 2-7, 1979. Meeting sponsored by the found to agree well with the potential flow solutions. Finally, the American Society of Mechanical Engineers. Edited by H. J. Herring importance of the diffuser inlet configuration to the improvement of (Dynalysis, Princeton, N.J.), A. Soler (Pennsylvania, University. the stage efficiency is discussed. (Author) Philadelphia, Pa.), and W. G. Steltz (Westinghouse Electric Corp., Lester, Pa.). New York, American Society of Mechanical Engineers, 1979. 193 p. Members, $15.; nonmembers, $30. A80-27737 • # Laser anemometer measurements at the exit of The symposium discusses turbomachine performance including a T63 combustor. D. A. Zimmerman (General Motors Corp., Detroit the effects of inlet guide vane on performance characteristics of a Diesel Allison Div., Indianapolis, Ind.). In: Flow in primary, high specific speed propeller pump, and rotating stall in a vaneless non-rotating passages in turbomachines; Proceedings of the Winter diffuser of a centrifugal fan. Attention is also given to experimental Annual Meeting, New York, N.Y., December 2-7, 1979. techniques including loss coefficient determination by water tank New York, American Society of Mechanical Engineers, test and application to turbomachine development, and laser 1979, p. 57-62. 9 refs. Research supported by the General Motors anemometer measurements at the exit of a T63 combustor. Corp.; Contract No. NAS3-21267.
'S A80-27747
In the first practical application of laser anemometry to an York, N.Y., December 2-7, 1979. New York, actual gas turbine engine combustor, the mean velocity and turbulent American Society of Mechanical Engineers, 1979, p. 125-132. 19 intensity profiles were measured in a steady-flow combustion rig refs. Research supported by the McDonnell Douglas Independent across an annulus simulating a turbine inlet; to establish a basis for Research and Development Program. comparison with similar measurements to be made in an operating Finite difference solutions for transonic flowfields about engine engine and to confirm current turbine aerodynamics and heat inlet nacelles are obtained by combining a general grid-generation transfer design assumptions. It was necessary to develop a new scheme with a previously developed general solver for transonic experimental technique for traversing the annulus due to differential potential flowfields. An extrapolated relaxation procedure is used to thermal expansion of the cantilevered combustion rig and a new obtain improved convergence of the transonic solution to small computer-graphics analysis technique for analyzing the velocity residuals. Results obtained for flowfields with embedded supersonic histograms due to the high background light intensity. The axial regions both outside and inside the inlets compare well with mean velocity and turbulent intensity were uniform across the experimental results. (Author) annulus under all operating conditions and the flow had little or no swirl component. The isothermal mean velocity was doubled by the A80-27745 f/ Three-dimensional inviscid compressible rota- burning of fuel, however, the isothermal turbulent intensity was tional flows - Numerical results and comparison with analytical relatively unaffected. (Author) solutions. M. Pandolfi and G. Colasurdo (Torino, Politecnico, Turin, Italy). In: Flow in primary, non-rotating passages in turbomachunes; Proceedings of the Winter Annual Meeting, New York, N.Y., A80-27738 # Flow measurements in a turbine scroll. W. December 2-7, 1979. New York, American Tabakoff, V. Sheeran, and K. Kroll (Cincinnati, University, Cincin- Society of Mechanical Engineers, 1979, p. 141-149.9 refs. Consiglio nati, Ohio). In: Flow in primary, non-rotating passages in turbo' Nazionale delle Ricerche Contract No. 78,02427,07. machines; Proceedings of the Winter Annual Meeting, New York, The paper presents a numerical method for predicting 3D N.Y., December 2-7, 1979. New York, American inviscid compressible rotational flows. The approach is shown to be Society of Mechanical Engineers, 1979, p. 63-73. 9 refs. Grant No. based on a time dependent technique, and the equations, boundary NsG-3066. conditions, and features of the algorithm are discussed. The accuracy The paper presents a study conducted to determine experi- of the results is checked by means of computations which have been mentally the flow behavior in the combined scroll nozzle asembly of performed on four flow fields where analytical solutions are a radial inflow turbine. It is shown that hot film anemometry was available. Finally, numerical results are compared with analytical used to measure the flow velocity in the scroll. M.E.P. results. M.E.P.
A80-27746 # Straight-walled, two-dimensional diffusers - A80-27742 # Evaluation of an analysis for axisymmetric Transitory stall and peak pressure recovery. J. Ashjaee and J. P. internal flows in turbomachinery ducts. T. J. Barber, P. Raghuraman Johnston )Stanford University, Stanford, Calif.). In: Flow in )United Technologies Corp., Commercial Products Div., East Hart- primary, non-rotating passages in turbomachines; Proceedings of the ford, Conn.), and 0. L. Anderson (United Technologies Research Winter Annual Meeting, New York, N.Y., December 2-7, 1979, Center, East Hartford, Conn.). In: Flow in primary, non-rotating New York, American Society of Mechanical passages in turbomachines; Proceedings of the Winter Annual Engineers, 1979, p. 151-158. 15 refs. Project SQUID. Meeting, New York, N.Y., December 2-7, 1979. An investigation of straight-walled, two-dimensional diffusers of New York, American Society of Mechanical Engineers, 1979, p. large aspect ratio for the purpose of studying the regime of incipient 107-114. 26 refs. transitory stall, is presented. Twelve symmetric diffusers of constant The paper demonstrates that the Anderson analysis is sufficient- nondimensional length with total included angles ranging from 4 to ly versatile and reliable to be used as a design tool. The analytical 24 deg, covering attached, intermittently detaching, and unsteady basis of the method is examined in order to review the necessary detached flows were examined. It is reported that pressure recovery assumptions and the solution algorithm. Attention is given to a series and flow direction intermittency were obtained along the diffuser of comparisons which demonstrate the applicability of the method walls. Finally, conclusions are drawn concerning the nature of the to practical duct problems having either moderate flow skew, flow in the vicinity of peak pressure recovery. M.E.P. moderate cross-sectional area variations or stator cascades. M.E.P.
A80-27743 # Numerical prediction of compressible poten- tial flow for arbitrary geometries. C. K. Forester (Boeing Aerospace A80-27747 # Effect of wake-type nonuniform inlet velocity Co., Seattle, Wash.). In: Flow in primary, non-rotating passages in profiles on first appreciable stall in plane-wall diffusers. K. F. Kaiser turbomachines; Proceedings of the Winter Annual Meeting, New (Wallace Murray Corp., Indianapolis,Ind.) and A. T. McDonald York, N.Y., December 2-7, 1979. New York, )Purdue University, West Lafayette, Ind.). In: Flow in primary, American Society of Mechanical Engineers, 1979, p. 115-124. 36 non-rotating passages in turbomachines; Proceedings of the Winter refs. Annual Meeting, New York, N.Y., December 2-7, 1979. A method for calculating compressible potential flow through New York, American Society of Mechanical Engineers, and about arbitrary geometries is being developed for applications in 1979, p. 159-168. 16 refs. the subsonic, transonic, and supersonic flow speed range. Discussion The combustor diffuser in a gas turbine engine must accept a of the technique focuses on the mathematical and Computer coding high-speed, unsteady, distorted flow from the engine compressor. It considerations which impact the algorithm efficiency, accuracy and must deliver flow to the combustor with minimum loss in total applicability to generally shaped physical domains. An example of pressure and minimum velocity profile distortion. Both pressure flow computed and compared with experimental data for an S-duct recovery and outlet flow distortion characteristics of diffusers must like that of a Boeing 727 center engine is highlighted. Highly be considered in design tradeoffs. The purpose of this investigation compressible flow in an S-duct is also shown. (Author) was to study the effects of nonuniform inlet velocity profiles on the inception of stall in two-dimensional plane-wall diffusers. Centrally- located 'wake-type' inlet velocity profiles were chosen to simulate the flow conditions at the inlet of a combustor diffuser. The inlet A80-27744 # Transonic inlet flow calculations using a distortion was characterized by dimensionless wake strength and general grid-generation scheme. L. T. Chen (McDonnell Douglas wake width parameters. The experiments were performed on an open Research Laboratories, St. Louis, Mo.) and D. A. Caughey (Cornell surface water table to make flow visualization possible. A centerline University, Ithaca, N.Y.). In: Flow in primary, non-rotating passages or pocket-type stall, such as previously reported in swirling flows, in turbomachines; Proceedings of the Winter Annual Meeting, New was observed for sufficiently. severe inlet profile distortion. A new
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definition of first appreciable stall, based on a fraction of the exit A80.27777 Computational techniques for EMP inter- area stalled, was introduced to characterize stalls which did not occur action. F. M. Tesche (Lulech, Inc., Berkeley, Calif.) and J. P. on a solid surface. (Author) Castillo (USAF, Weapons Laboratory, Kirtland AFB, N. Mex.). In: Electromagnetic compatibility 1979; Proceedings of the Third Symposium and Technical Exhibition, Rotterdam, Netherlands, May Flight recording in the UK. I - Evolution. T. E. A80-27751 # 1-3, 1979. Zurich, Eidgenössische Technische Ford. 52, Mar. 1980, p. 6-8. Aircraft Engineering, vol. Hochschule Zurich, 1979, p. 287-292. 19 refs. The evolution of flight recording in the UK from the 1960's to Various computational techniques for EMP interaction are the present is reviewed. Relevant flight parameters, and crash reviewed, including the eigenvalue method, integral equation protection requirements for both the flight data and cockpit voice approaches, and the finite difference method. It is shown that the recorders are outlined, as are the various recording requirements for most accurate solution to a particular interaction problem is not subsonic aircraft, depending on size. Areas of present study are always the best, because of errors inherent in the process of considered, including flight operations, structures, systems, and decomposing a system into its topological pieces. The methods are engine condition monitoring. J.P.B. illustrated by examples and comparisons between the computations and the experimental data. V. L. A80-27752 # The energy problem: Its effect on aircraft design. I . Supply and demand. W. Tye. Aircraft Engineering, vol. 52, Mar. 1980, p. 9.11. A80-27778 Modelling of aircraft responses to EMP. T. W. Energy demands for aircraft by the year 2000 are discussed, Armour (Atomic Weapons Research Establishment, Aldermaston, considering fuel supply shortages that are expected to result in a 7% Berks., England). In: Electromagnetic compatibility 1979; Proceed- Cut in the availability of aviation fuel. Attention is given to the use of ings of the Third Symposium and Technical Exhibition, Rotterdam, kerosine with higher aromatic content and an expected trend toward Netherlands, May 1-3, 1979. Zurich, Eidge- fuels more like diesel oil, as well as consequent engine and aircraft nössische Technische Hochschule Zurich, 1979, p. 293-295. modifications. J.P.B. The Fl 11 fighter-bomber is studied using a wire-grid model, in which the length of the fuselage is 22.4 m and the wing-span 19.2 m. The time-domain response of surface current is obtained by A80-27760 Experimental procedure to determine limits of computing Current over the range of frequencies from 1 to 40 MHz ISM interference affecting navigational ILS equipment. P. Corona in 1 MHz steps. Predictions made by a modelling code CHAOS-3 are and E. Paolini (Istituto Universitario Navale, Naples, Italy). In: compared with the finite-difference calculations and experimental Electromagnetic compatibility 1979; Proceedings of the Third published data. It is concluded that the wire-grid model predictions Symposium and Technical Exhibition, Rotterdam, Netherlands, May are in good agreement with the experimental data. The wire-grid and 1-3, 1979. Zurich, Eidgenössische Technische finite difference calculations are also very similar; however, it is Hochschule Zurich, 1979, p. 141.146. stressed that comparisons are only possible for points on the aircraft A method for determining acceptable ISM (industrial, scientific, fuselage. L. M. medical) interference field limits for instrument landing systems is described. The method involves the definition of the useful field of the ILS local izer and the measurement of the receiving patterns of A80-27783 Induced effects of lightning on an all com- the localizer antennas. A laboratory evaluation of the limits for posite aircraft R. A. Perala, R. Cook )Electro Magnetic Applications, interference voltage is presented. B.J. Inc., Golden, Cob.), and K. Lee (Mission Research Corp., Albu- querque, N. Mex.). In: Electromagnetic compatibility 1979; Proceed- ings of the Third Symposium and Technical Exhibition, Rotterdam, A80-27766 Swedish EMP research. G. Dahlen, L. Hoglund, Netherlands, May 1-3, 1979. Zurich, Eid- T. Karlsson, H. Persson )Forsvarets Forskningsanstalt, Linköping, genossische Technische Hochschule ZUrich, 1979, p. 421-424.8 refs. Sweden), and B. Sjoholm (Forsvarets Forskningsanstalt, Stockholm, Contract No. F33615-77-C-5169. Sweden). In: Electromagnetic compatibility 1979; Proceedings of the The paper presents results for lightning induced cable currents Third Symposium and Technical Exhibition, Rotterdam, Nether- and voltages on typical cable runs inside an all composite aircraft. lands, May 1-3, 1979. Zurich, Eidgenossische Consideration is given to both a direct stroke and a nearby stroke. Attention is also given to results for the case in which the aircraft is Technische Hochschule Zurich, 1979, p. 197-201. 5 refs. The electromagnetic pulse from nuclear explosions )EMP or coated with 6-mil aluminum flame spray. Finally, it is shown that, as NEMP) has been studied since 1965 at the Swedish National Defense expected, the direct stroke induces the largest voltages, but that the Research Institute )the FDA). This paper reviews recent research at effects of the nearby strike are not negligible. M.E.P. the FDA on EMP environments, coupling, simulators, measurements, and shielded cables. B.J. A80-27784 System EMC - Tendencies of a worldwide standardization and cooperation. R. Rode )Messerschmitt-Bölkow- Blohm GmbH, Munich, West Germany). In: Electromagnetic compat- ibility 1979; Proceedings of the Third Symposium and Technical Exhibition, Rotterdam, Netherlands, May 1-3, 1979. A80.27773 EMC in lightweight helicopters . Special Zurich, Eidgenossische Technische Hochschule Zurich, 1979, p. problems and experience in design and control. K. H. Rippl 485-490. )Messerschmitt-Bölkow. BIohnl GmbH, Munich, West Germany). In: The paper deals with the tendencies in worldwide EMC Electromagnetic compatibility 1979; Proceedings of the Third standardization and cooperation. Emphasis is placed on standardiza- Symposium and Technical Exhibition, Rotterdam, Netherlands, May tion of test methods including system analyses, system integration, 1 . 3, 1979. Zurich, Eidgenbssische Technische prototype and production systems. EMC problems in an interna- Hochschule Zurich, 1979, 247.250. p. tional airport and military aircraft are outlined. The study deals with EMC problems of lightweight helicopter V.T. design. In order to ensure she compatible operation of various units of electronic and electrical equipment, all technical and economical possibilities must be exploited in the course of planning and A80-27789 The fatigue performance of service aircraft and development with the aim of verifying the appropriate EMC the relevance of laboratory data. P. J. E. Forsyth (Royal Aircraft principles. Consideration is given to the EMC problems due to the Establishment, Farnborough, Hants., England). (Society of Environ- existing design and operation. V.1. mental Engineers, Symposium on Environmental Engineering Today,
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London, England, May 9-11, 1979.) Society of Environmental is the forward fuselage bulkhead of the Boeing YC-14 aircraft. This Engineers, Journal, vol. 19. 1, Mar. 1980, p. 3-10. 14 refs. structure meets all the requirements for a successful demonstration Corrosion factors reducing the fatigue life of aircraft parts are of the technology. The discussion covers material data on fatigue and discussed along with other factors similarly reducing fatigue life and fracture behavior, effects of defects, equivalent initial flaw approach causing differences between laboratory data and service experience. and fatigue rating approach to effects of defects, structural analysis, The aircraft structural environment is reviewed, and consideration is and full-scale testing. The CAST program has demonstrated that given to the possible breakdown of corrosion-protective coatings in castings can be used in primary aircraft structure. S. D. fatigue-sensitive areas, leading to the development of a corrosion pit, the initiation of fatigue cracks in corrosion pits, and the effects of corrosion on fatigue crack propagation. The effects of anodize pits A80.27898 # Structural design of transport airplanes for on fatigue crack initiation, and of pits in general on fatigue life are transient environments. J. E. Wignot (Lockheed-California Co., considered, and the reliability of simple coupon, simplified joint and Burbank, Calif.). In: Survival of mechanical systems in transient major structural fatigue life are considered, and the reliability of environments; Proceedings of the Winter Annual Meeting, New York, simple coupon, simplified joint and major structural fatigue tests is N.Y., December 2-7, 1979. Meeting sponsored by the American discussed in relation to the environmental factors considered. It is Society of Mechanical Engineers. New York, American Society of concluded that the damage tolerance approach in structural design Mechanical Engineers (Applied Mechanics Symposia Series. AMD should eliminate most of the uncertainty in fatigue life prediction. Volume 36), 1979, p. 33-59. 10 refs. A.L.W. A survey of some of the analytical techniques used at Lockheed to design transport airplanes to survive the transient environments- A80-27790 Simulating the shock protection performance experienced during their service life it presented. Transient loads in of large transit packs by means of small scale laboratory models. I. P. flight are due to gusts, steady maneuvers and abrupt maneuvers. On Layne (Rolls-Royce, Ltd., Aero Div., Bristol, England). (Society of the ground transient loads result from landing, taxiing, braking and Environmental Engineers. Symposium on Environmental Engineering turning. Transient impulses will be experienced under such emer- Today, London, England, May 9-11, 1979.) Society of Environ- gency conditions as gear deranged landings, rapid decompression and mental Engineers, Journal, vol. 19-1, Mar. 1980, p. 13-16. hail or bird impact while high frequency transients are associated The simulation of the performance of the shock protection of with sonic fatigue and equipment vibration requirements. The use of large packages for the transport of such items as aircraft engine multidiscipline inputs together with a matrix algebra approach is power plants using small-scale laboratory models is discussed. The highlighted by summarizing the analytical methods used. References development of transit pack model testing techniques in the aircraft are given to sources for use in further study. (Author) industry is reviewed, and the scaling and construction of models is considered. The testing and interpretation methods used with model tests are indicated, and the practical applications and benefits of the A80-27902 The duration of false alarms in surveillance procedure are presented. Advantages of the testing of the shock radar. J. M. Smith and G. Duckworth (Marconi Radar Systems, Ltd., Protection performance of models of transit packs include the ability Leicester, England). Marconi Review, vol. 42, 4th Quarter, 1979, p. to represent a large variety of test parameters at a considerable 219-234. 7 refs. reduction in time and cost compared to full-scale testing, the ability The generation of false alarms by noise in a scanning pulsed to select the optimum shock protection system, and accurate radar is examined with emphasis placed on the size of corresponding performance prediction at an early stage in development. A.L.W. plots in range and bearing coordinates. Results are derived for noncoherently detected video signals with ideal analog integration of 'M out of N' binary processing. V. T. A80-27797 Optimal twisting of blades in axial turbo- machines. Y. A. Lesokhin (Technion - Israel Institute of Technology, Haifa, Israel). Journal of Mechanical Engineering Science, vol. 21, A80-27992 # Minimum-mass designs of stiffened graphite/ polyimide compression panels. G. G. Weaver, II (Hercules, Inc., Oct. 1979, p. 367-369. 11 refs. One possible way to improve the aerodynamic performance of Wilmington, Del.) and J. R. Vinson (Delaware, University, Newark, turbomachines is to analyse and generalize existing results obtained Del.). In: Modern developments in composite materials and struc- from design and testing. These can be applied to develop a tures; Proceedings of the Winter Annual Meeting, New York, N.Y., quantitative relationship between the geometry of various regions of December 2-7, 1979. New York, American the flow path and turbomachine performance. An optimal correla- Society of Mechanical Engineers, 1979, p. 215-233. 16 refs. tion between various geometric parameters can be established in this NSF-supported research; Grant No. NsG-1488. manner. By studying blade geometry of various kinds of axial This study presents results from an analytic investigation to turbomachine (compressors, gas turbines, hydraulic turbines and determine minimum-mass designs of stiffened Gr/Pi compression pumps), the author has found some regularities in their geometry panels for a wide range of uniaxial compression loads. Four panel which enable the design of highly efficient blades. Regularities in the configurations are considered: (1) hat stiffened-laminated skin, (2) twisting of impeller blades of axial compressors working over a wide hat stiffened-honeycomb core sandwich skin, (3) blade stiffened- range of Mach numbers are represented in this work. Information is laminated skin and (4) blade stiffened-honeycomb core sandwich presented showing that analogous regularities exist also for axial skin panels. Designs are generated by an automatic optimization computer code entitled PASCO (Panel Analysis and Sizing COde). hydraulic turbine and pump blades. (Author) The analysis portion of PASCO contains a generalized buckling analysis which calculates all critical modes without assuming any of A80-27875 # Cast aluminum primary aircraft structure. C. them a priori. Mass-strength curves are presented for the four K. Gunther (Boeing Aerospace Co., Seattle, Wash.). In: Cast metals configurations along with specific designs generated for low, moder- for structural and pressure containment applications; Proceedings of ate and high values of compression load. A mass-strength curve for a the Winter Annual Meeting, New York, N.Y., December 2-7, 1979. titanium hat stiffened panel is provided for comparison. A 30% to Meeting sponsored by the American Society of Mechanical Engi- 50% mass savings over titanium panels is shown for moderately and neers. New York, N.Y., American Society of Mechanical Engineers heavily loaded Gr/Pi panels. (Author) (MPC Publications, No. 11), 1979, p.315-329. 6 refs. The paper describes the efforts required to demonstrate the structural integrity of cast primary structure by using the demonstra- tion component of the Cast Aluminum Structures Technology A80-28010 • Wear of seal materials used in aircraft propul- (CAST) program as an example. The component selected for the sion systems. R. C. Bill (U.S. Army, Army Aviation Research and demonstration of the technology emerging from the CAST program Development Center, Cleveland, Ohio) and L. P. Ludwig (NASA,
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Lewis Research Center, Cleveland, Ohio). (U.S. Navy, Workshop on Tests have been conducted on numerous modifications of Thermal Deformation, Annapolis, Md., June 19, 20, 1979.) Wear, dynamically tuned gyros designed especially for experimental use. vol. 59, Mar. 1, 1980, p. 165. 189. 23 refs. Following a brief review of the characteristics of experimental gyros A review of various types of seal locations in a gas turbine of particular importance to the test program, the paper discusses engine and the significance of wear for each type are presented. some of the results of and experience gained from the tests, along Material selection guidelines and the PV (contact pressure times with their consequences for the design of dry tuned gyros. The sliding velocity) criteria for teal materials are discussed, and examples discussion focuses primarily on shaft bearing assembly, spin motor, of wear mechanisms in positive contact seals are given. It is suggested pickoff, suspension, rotor balancing, and gas torques. S. D. that improved wear, erosion, and oxidation resistant materials will be required for improved seal durability; finally, a correlation is proposed between wear characteristics and a factor that includes material strength, ductility, specific heat and hot-working tempera- A80-28218 /1 The experimental strapdown system of ture to attain low porosity metallic gas path seal materials. A. T. DFVLR. D. Rahlfs (Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt, Institut für FlugfUhrunge, Braunschweig, West Germany). In: Symposium on Gyro Technology, Stuttgart, West A80-28018 # Flight control design based on nonlinear Germany, September 25, 26, 1979, Proceedings. model with uncertain parameters. I. Horowitz )Weizmann Institute Düsseldorf, .Deutsche Gesellschaft für Ortung und Navigation, 1979, of Science, Rehovot, Israel), B. Golubev, and T. Kopelman. Journal p. 8.0.8.40. 9 refs. vol.3, Mar-Apr. 1980, 113-118.9 refs. of Guidance and Control, p. Strapdown inertial systems presently play an increasingly Grant No. AF-AFOSR-77-3355. important role in guidance and navigational applications. The paper A nonlinear model used for a short-period longitudinal flight shows that the experimental modular strapdown system constructed problem is described. An approach discussed is based on a synthesis by DFVLR offers many possibilities for future research in the area of technique for feedback around a nonlinear uncertain plant. The inertial strapdown techniques. The system is based on a nearly nonlinear plant set is replaced by a linear time-invariant plant set. self-contained sensor unit with a digital BPWM rebalance readout of Design execution then involves frequency response concepts. V.T. high accuracy and a high-quality temperature control of sensor and electronics. The strapdown computer consists of multiple microcom- A80.28019' # Implicit model following and parameter iden- puters interconnected by dual memories. The sensor and the tification of unstable aircraft. J. V. Lebacqz (NASA, Ames Research computer are controlled by intelligent units for flexible control of Center, Moffett Field, Calif.; Calspan Advanced Technology Center, system operation. Sensor module test is discussed relative to test Buffalo, N.Y.) and K. S. Govindaraj )Calspan Advanced Technology procedures and first results. A low drift rate of the digital output Center, Buffalo, N.Y.). Journal of Guidance and Control, vol. 3, signal is identified. S. D. Mar.-Apr. 1980, p. 119-123. 11 refs. A transformation in the s-plane is described which has utility in implicit model-following optimal control design application and in estimation or parameter identification problems. The objective of the A80-28221 The laser gyro and its application to an transformation is, for the control problem, to achiev an unstable helicopter navigation system. B. de Salaberry (Société Francaise closed-loop system, and, for the estimation problem, to alleviate d'Equipements pour la Navigation Aérienne, Boulogne-Billancourt, algorithm convergence problems that may arise in identifying Hauts.de-Seine, France). In: Symposium on Gyro Technology, unstable systems. For the control problem, the transformation is a Stuttgart, West Germany, September 25, 26, 1979, Proceedings. shift along the real (sigma) axis of the plant and model poles and Düsseldorf, Deutsche Gesellschaft für Ortung zeros. This transformation is shown to be equivalent to a modified und Navigation, 1979, p. 11.0.11.25. performance index but offers the advantage of compatibility with The challenge for the avionics industry is to propose high- existing optimal control solution algorithms. For the estimation performance yet cost-effective systems consistent with the economy problem, the data are multiplied by an exponential function and the of European military helicopter projects. The SEXTAN system is assumed measurement and process noise covariances are appropri- proposed which offers an attractive new solution to the difficult ately modified. Examples of both control and estimation applica- problem of helicopter navigation. This system, presently under tions are presented. (Author) development, continuously combines redundant and complementary data provided by a suitable strapdown laser gyro inertial unit, a A80.28050 The role of research applied to the air traffic doppler radar and a magnetometer. The discussion covers the control system (II ruolo della ricerca applicata nel sistema di SEXTAN system architecture; merits and performance of such a controllo del traffico aereo). F. Valdoni )Fondazione Ugo Bordoni; system; heading, attitude and velocity unit (CA y ); laser rate gyro; CNR, Rome, Italy). lsrituto Italiano di Navigazione, Atti, July-Dec. pendulous force balancing accelerometer; CAV computer and algo- rithm; NADIR Mkll computer; mechanization algorithm; and self. 1979, p. 25-35. In Italian. This paper reviews the role of research in the air traffic control compensated magnetometer. S. D. system from various points of view, including the economic, social, administrative, and operative. The role of industry and universities in research programs is discussed, as is the airport system and territorial A80-28254 Buoyant module VHF antenna design for concerns. In addition, research is considered in terms of short term submerged systems/aircraft communications. R. J. Decesari (Hydro experimentation, medium term innovation, and long term acquisition Products, Inc., San Diego, Calif.). In: OCEANS '79; Proceedings of of knowlege. The scope of the Finalized Project for air traffic the Fifth Annual Combined Conference, San Diego, Calif., Sep- navigation and control is also reviewed, considering its subprojects in tember 17-19, 1979. New York, Institute of administrative improvement, primary and secondary radar, and Electrical and Electronics Engineers, Inc., 1979, p. 366. 372. Navy- takeoff and landing safety. J.P.B. supported research. The paper presents a description of a prototype communications system designed to provide VHF communications from a stationary A80-28212 # Experience based upon experimental dry or moving body or submarine at depth. The design approach revolves tuned gyros. H. Karnick )AnschUtz und Co., GmbH, Kiel, West around the existing submarine buoyant cable antenna and the Germany). In: Symposium on Gyro Technology, Stuttgart, West utilization of existing low frequency buoyant coaxial cable. Atten- Germany, September 25, 26, 1979, Proceedings. tion is given to the three distinct subsystems of the electrical design: Düsseldorf, Deutsche Gesellschaft für Ortung und Navigation, 1979, the submarine control station, the existing buoyant cable, and the p. 2.0-2.28. buoyant module antenna and electronics. C.F.W.
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A80-28269 # Airships - Basis for a new oceanic capability. J. to fade out of the system and only secondary radar be used for G. Vaeth (NOAA. National Environmental Satellite Service, Suitland, enroute aircraft tracking. The industry viewpoint is discussed, which Md.). In: OCEANS '79; Proceedings of the Fifth Annual Combined holds that primary radar should be directed toward the detection of Conference, San Diego, Calif., September 17-19, 1979. hazardous weather rather than aircraft tracking. B. J. New York, Institute of Electrical and Electronics Engineers, Inc., 1979, p. 700-703. A80-28382 ft Electronic flight rules /EFR/ - A concept for Blimps, modernized versions of the U.S. Navy's antisubmarine enhanced freedom of airspace. P. R. Drouilhet, Jr. (MIT, Lexington. and early warning airships of the 1940's and 50's, offer an untapped Mass.), In: Radio Technical Commission for Aeronautics, Technical potential for ocean science and engineering. As buoyant aircraft, Symposium and Annual Assembly Meeting, Washington, D.C., they are not only energy-conserving but could engage uniquely in November 15, 16, 1979, Proceedings. Washing- protracted airborne operations for remote and in-situ sensing. Their ton, D.C., Radio Technical Commission for Aeronautics, 1979, p. range, endurance, and ability to use sound equipment could be useful 49-56. in detecting, following, observing, and protecting marine life. By This paper reviews the EFR concept, ground rules, control combining a 'view from above' with an ability to 'work from above', procedures, and mechanizations. It is concluded that EFR offers an airships could add a valuable new dimension to scientific and interesting approach to reducing both the direct and indirect cost of engineering activities in the sea. (Author) aviation by extending the efficiency and flexibility of VFR to operation in instrument meteorological conditions. There appear to A80-28284 • # Evaluation of finite element formulations for be ground-based (centralized( and aircraft-based (distributed) transient conduction forced-convection analysis. E. A. Thornton approaches which can adequately provide EFR service. B. J. (Old Dominion University, Norfolk, Va.) and A. R. Wieting (NASA, Langley Research Center, Hampton, Va.). In: National Conference A80-28383 ft The introduction of new systems in interna- on Numerical Methods in Heat Transfer, 1st, College Park, Md., tional civil aviation. 0. Carel (Direction Générale de I'Aviation Civile, September 24-26, 1979, Proceedings. College Service Technique de la Navigation Aérienne, Paris, France). In: Park, Md., University of Maryland, 1979, p. 250-267. 13 refs. Grant Radio Technical Commission for Aeronautics, Technical Symposium No. NsG-1321. and Annual Assembly Meeting, Washington, D.C., November 15, 16, Conventional versus upwind convective finite elements, and 1979, Proceedings. Washington, D.C., Radio lumped versus consistent formulations for practical conduction/ Technical Commission for Aeronautics, 1979, p. 71-77. forced convection analysis are evaluated on the basis of numerical The international coordination of civil aviation is discussed with studies, with finite element and finite difference lumped-parameter particular reference to the European situation. Particular attention is temperatures compared to closed-form analytical solutions for given to the standardization of new navigation systems; such systems convection problems. Attention is given to two practical combined as VOR/Decca and MLS are discussed. B. J. conduction and forced convection applications, stressing that the finite element method, showing superior accuracy, is competitive with the finite difference lumped-parameter method. Also considered A80-28384 ft Adding more automation to the air traffic are the computational time savings offered by the zero capacitance control system. B. M. Horowitz (Mitre Corp., Bedford, Mass.). In: nodes procedure and comparative finite element and finite difference Radio Technical Commission for Aeronautics, Technical Symposium lumped-parameter computer times. The present study has reference and Annual Assembly Meeting, Washington, D.C., November 15, 16, to the design of actively cooled engine and airframe structures for 1979, Proceedings. Washington, D.C., Radio hypersonic flight. L. M. Technical Commission for Aeronautics, 1979, p. 97-106. The paper summarizes the recommendations of an FAA- sponsored automation/productivity group that dealt with problems A80-28380 ft Capacity payoffs at large hub airports from of air traffic control. The group's recommendations are discussed ATC initiatives. J. C. Ormar. and S. L. M. Hockaday (Peat, Marwick, with respect to required resources, ATC concept development, field Mitchell and Co., San Francisco, Calif.). In: Radio Technical tests, NAFEC tests, computer hardware, display hardware tests, Commission for Aeronautics, Technical Symposium and Annual software costs, costs to achieve needed levels of confidence, and Assembly Meeting, Washington, D.C., November 15, 16, 1979, overall costs. B. J. Proceedings. Washington, D.C., Radio Technical Commission for Aeronautics, 1979, p. 21-38. The paper reviews the current status of system capacity and delay analysis with particular reference to ongoing FAA efforts in A80-28418 • # Strouhal number influence on flight effects on the E&D field. The main emphasis of the capacity element of jet noise radiated from convecting quadrupoles. R. Dash (NASA, existing E&D programs is on increasing system capacity through Ames Research Center, Moffett Field; Stanford University, Stanford, reductions in minimum IFR radar longitudinal separations between Calif.). AIAA Journal, vol. 18, Mar. 1980, p. 337-339. arrival aircraft. The biggest problem associated with achieving The paper reports a complementary extension of previous work reduced longitudinal separation of any type is the ability to deal to include the high-frequency features reflected in the discussion of effectively with wake turbulence. Analysis at high-activity airports the higher Strouhal number influence on flight effects. It is found indicates that gains in system capacity and reductions in aircraft that, in addition to the usual features of flight effects on noise from travel time may be achieved by methods other than reduction in ordinary flows, the high Strouhal number flows exhibit some more minimum longitudinal separations. A summary of 14 of the more interesting features which are uniquely characteristic to them. The promising methods is presented, including examples of potential additional features are as follows: (1) Flight effects are more site-specific applications and benefits. B.J. favorable to hot jets than to cold jets; (2) the higher the Strouhal number of the jet flow, the lesser the forward arc amplification due A80-28381 ft Primary radar in ATC. D. D. Thomas. In: to flight; (3) as the Strouhal number increases, the peak amplifica- Radio Technical Commission for Aeronautics, Technical Symposium tion angle in the forward quadrant and the peak suppression angle in and Annual Assembly Meeting, Washington, D.C., November 15, 16, the aft quadrant move toward 90 deg and get closer, thus reducing 1979, Proceedings. Washington, D.C., Radio the amplification exposure to a constricted angular region; (4) the silence zone is disturbed and displaced from its normal position Technical Commission for Aeronautics, 1979, p. 43-48. A basic question concerning air traffic control in the United parallel to the jet flow to give rise to multiple crossings of flight States is addressed: whether all existing primary long-range enroute curves with the static line; and 151 the occurrence of multiple radars should be replaced with more modern equipment for tracking crossings is a strange phenomenon solely characteristic of high of nonbeacon-equipped aircraft or whether they should be permitted Strouhal number with high subcritical jet flows in flight. S. D.
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A80-28419 • # Effect of temperature on surface noise. W. techniques can be used to solve the control and flight mechanics Olsen and C. Wasserbauer (NASA, Lewis Research Center, Cleveland, problems associated with the large mass and moments of inertia. B.J. Ohio). AIA,4 Journal, vol. 18, Mar. 1980, p. 339, 340. 8 refs. An experimental work is discussed whose objective was to obtain data that show the effect of temperature and temperature A80-28491 # Major areas of research in aeronautics and air fluctuations on surface noise. This was accomplished experimentally traffic at the German Aerospace Research Establishment /DFVLR/. by immersing a small chord airfoil in the turbulent airstream of a hot F. Thomas (Deutsche Forschungs- und Versuchsanstalt für Luft- und jet. The theory and experiment reported by Olsen (1976) provided a Rfal Braunschweig, West Germany). In: International S y mpo- guide for designing and validating the hot let experiment and for sium on Traffic and Transportation Technologies, Hamburg, West interpreting the data. It is shown that increased temperature causes a Germany, June 18-20, 1979, Proceedings. Volume E. small decrease in the sound levels; at the same time it causes a shift in Bonn, Bundesministerium für Forschung und Techno- the spectra that is smaller but similar to the shift observed with logie, 1979, p. 108-136. subsonic hot let noise. S. D. The paper examines the large experimental facilities and some significant research achievements of the DFVLR; medium-term and long-term planning of DFVLR research activities is also described. It A80-28487 # The future development of air traffic as seen is shown that requirements of high cost efficiency, good energy by airline companies. M. Wernet (Deutsche Lufthansa AG, Cologne, West Germany). In: International Symposium on Traffic and conversion, improved ATC, and far-reaching integration of air traffic into the overall transport system will significantly determine the Transportation Technologies, Hamburg, West Germany, June 18-20, technological development of aviation for decades to come. Atten- 1979, Proceedings. Volume E. Bonn, Bundes- tion is given to the utilization of such new technologies as cryogenics ministerium für Forschung und Technologie, 1979, 1-24. p. in wind tunnel design, digital control concepts, automated ATC The development of traffic volume handled by scheduled air procedures, and advanced composites and ceramics. services is examined. Particular consideration is given to regulation B.J. and market organization constraints; the shortcomings of the 'old' system based on the 1944 Chicago Convention are emphasized. Some recommendations on improving the old system are made, and A80-28492 # Avionics - The leading technology in flight predictions on the development of air traffic in the 1980s are given. guidance and air traffic control. J. FiIz (Deutsche Lufthansa AG, B.J. Hamburg, West Germany). In: International S ym posium on Traffic and Transportation Technologies, Hamburg, West Germany, June 18-20, 1979, Proceedings. Volume E. Bonn, A80-28488 # Influence of air traffic on the concept of air Bundesministerium für Forschung und Technologie, 1979, p. traffic control. K. Platz (Bundesanstalt für Flugsicherung, Frankfurt 137-159. 1 0 refs. am Main, West Germany(. In: International Symposium on Traffic Some possible future trends in avionics are examined. The and Transportation Technologies, Hamburg, West Germany, June impacts of avionics technology on flight guidance and control 18-20, 1979, Proceedings. Volume E. Bonn, sy stems are described with particular attention given to the evolution Bundesministerium für Forschung und Technologie, 1979, p. 25-48. of automatic flight control systems; the evolution of the guidance, The paper describes methods for determining and deciding on navigation, and communication function; and the evolution of the control capacity of ATC systems. The concept of a future ATC displays, controls, and warning systems. Cost and productivity are system is briefly discussed; some generalities concerning investment also examined with emphasis on trends influencing future ATC and personnel needs are presented. B.J. systems and envisaged automation levels. B.J.
A80-28489 # Airbus family concept for the 1990s. C. A80-28493 # Coming civil transport aircraft with 'active' Schubert (Deutsche Airbus GmbH, Munich, West Germany). In: control elements. D. Volk (Messerschmitt-Bölkow-Blohm GmbH, International Symposium on Traffic and Transportation Technolo- Hamburg, West Germany). In: International Symposium on Traffic gist, Hamburg, West Germany, June 18-20, 1979, Proceedings. and Transportation Technologies, Hamburg, West Germany, June Volume E. Bonn, Bundesministerium für For- 18-20, 1979, Proceedings. Volume E. Bonn, schung und Technologie, 1979, p.66-84. Bundesministerium für Forschung und Technologie, 1979, p. The A310, a smaller version of the A300, will be available for 160-182. 14 refs. delivery to airlines in 1983; there will be three basic versions. The Different active control applications in the area of civil transport introduction of further members of Airbus family is planned for the aircraft are reviewed with emphasis on risks, technical problems, and second half of the 1980s and for the 1990s. The new members will possible improvements in cost effectiveness. Maneuver load allevia- be the 89, a stretched version of the 300 B2 with a greater seating tion, gust load alleviation, yaw damping, the adaptive wing concept, capacity; the B1 1, a long-range aircraft developed from the A310; and direct lift control are considered. The maximum amount of and a version of the A300 constructed specifically for cargo static stability reduction is discussed for the A300. Particular purposes. The introduction of JET I and JET II will be a further consideration is given to the Advanced Control Transonic Transport expansion in the range of aircraft covered by the Airbus family. B.J. Aircraft program. B.J.
A80'28490 # Technological aspects of future very large A80-28494 # The aerodynamics of future transport aircraft airplanes. J. Spintzyk (Dornier GmbH, Friedrichshafen, West Ger- and the role of the wind tunnel during development. G. Krenz many). In: International Symposium on Traffic and Transportation (Vereinigte Flugtechnische Werke-Fokker GmbH, Bremen, West Technologies, Hamburg, West Germany, June 18-20, 1979, Proceed- Germany). In: International Symposium on Traffic andTransporta- ings. Volume E. - Bonn, Bundesministerium für tion Technologies, Hamburg, West Germany, June 18-20, 1979, Forschung und Technologie, 1979, 85-107. 9 refs. p. Proceedings. Volume E. - Bonn, Bundes- The design of very large transport aircraft is discussed with ministerium für Forschung und Technologie, 1979, p. 183-201. reference to Dornier proposals concerning a future international The aerodynamics of medium and large civil transports in the cargo transport system. It is found that very large cargo aircraft can narrow-body and wide-body classes is examined; specifically atten- be realized in a conventional fixed wing configuration, in seaplane as tion is given to such narrow-body aircraft as A300 and A310 and the well as in landplane version. Structural weight increases, especially of Boeing 767, and to such wide-body aircraft as JET I, JET II, and the the wings, can be limited by such measures as reduced load Boeing 757. Aerodynamic standards achieved in comparison with assumptions and maneuver load control. Modern active control past designs are described, and consideration is given to changes in
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geometry and corresponding gains in wing lift capacity, which can be different values of plunge/pitch frequency ratios are shown. The used for weight reduction and performance improvement. The role examples demonstrate the dip phenomenon of the curves for flutter of the wind tunnel in aircraft development is described, and some speed in the transonic regime. Flutter results of transonic codes are test results representing the aerodynamics for the next generation of compared with those obtained by linear flat plate theory. (Author) aircraft are presented. B.J. A80-28852 # Prandtl's biplane theory applied to canard and A80-28495 # New materials and methods for airframe con- tandem aircraft. E. V. Laitone (California, University, Berkeley, struction. H. W. Bergmann (Deutsche Forschungs- und Versuchs. Calif.). Journal of Aircraft, vol. 17, Apr. 1980, p. 233-237. 5 refs. anstalt für Luft. und Raumfahrt, Institut für Strukturmechanik, Prandtl's biplane theory for elliptic loadings is generalized to Braunschweig, West Germany). In: International Symposium on apply to nonelliptic spanwise load distributions. The induced drag is Traffic and Transportation Technologies, Hamburg, West Germany, calculated by assuming an infinite stagger distance so all of the June 18.20, 1979, Proceedings. Volume E. Bonn, mutually induced drag acts upon the rear surface which has no effect Bundesministerium für Forschung und Technologie, 1979, p. upon the front surface. Consequently, the mutually induced drag is 202.220. 6 refs. calculated by integrating the Trefftz-plane downwash of the front It is predicted that future airframe construction will receive a surface over the independent load distribution on the rear surface. great impetus from the combined use of new metal alloys and This procedure is verified by explicit solutions that give the same advanced composites. Current trends indicate the possibility of mutually induced drag irrespective of the fore and aft location of the significant savings in the production of metal components by larger span when carrying either an elliptic or a uniform load computerized matching operations, the more extended use of distribution. It was found that the mutually induced drag was less castings and forgings, and the use of such innovations as PM when the larger span had a uniform load distribution, but the total processes, superplastic forming, and diffusion bonding. Advanced induced drag was not decreased because of the additional self- composites are also attractive from a manufacturing viewpoint. They induced drag produced b y the change from the ideal elliptic loading can be produced in near-final shapes with relatively low expenditure to a uniform loading. However, when the larger span carried a of energy and lend themselves to integral-type construction. B.J. uniform loading it allowed the smaller span, when either fore or aft, to support more of the aircraft's weight at the minimum induced drag condition. (Author) A80-28500 Legal liability of the controller. I. E. McClus- key. The Controller, vol. 19, 1st Quarter, 1980, p . 23-25. Criminal liability of a controller is discussed with regard to A80-28853 # Measurements of cabin and ambient ozone on Roman law states, socialist systems, and Anglo-Saxon systems. The B747 airplanes. G. D. Nastrom (Control Data Corp., Minneapolis, unique position of the controller is considered, since several legal Minn.), J. D. Holdeman, and P. J. Perkins (NASA, Lewis Research systems may be involved even though he never leaves his place of Center, Combustion and Pollution Research Branch, Cleveland, work. Furthermore, the additional stress due to the possibility of Ohio). Journal of Aircraft, vol. 17, Apr. 1980, p. 246-249. 14 refs. criminal as well as civil liability is discussed, as well as the various FAA-supported research. interpretations of the controller's possible negligence in the event of In response to recent concerns over possibly high ozone levels in an air accident in socialist systems (criminal responsibility for rule the cabins of aircraft flying in the stratosphere, simultaneous violation), Roman law states (guilty, if there is reasonable certainty), measurements of the cabin and ambient ozone levels have been made and Anglo-Saxon law states (criminal guilt only if there was criminal as part of the NASA Global Atmospheric Sampling Program. intent). J.P.B. Examples of the data taken on commercially operated Boeing 747-100 and 747SP airplanes are given for selected flights, together with summary statistics of over 5600 observations. Cabin ozone A80-28819 # Wind-turbine power improvement with levels vary with the ambient level and, for unmodified aircraft, are modern airfoil sections and multiple-speed generators. B. F. Habron higher on the 747SP than on the 747-100. Modifications to the (Westinghouse Research and Development Center, Pittsburgh, Pa.), ventilation system of the 747SP reduced cabin ozone levels by F. R. Goldschmied, and H. S. Kirschbaum. In: Wind Energy varying amounts up to a factor of 14. )Author) Conference, Boulder, Cob., April 9. 11, 1980, Technical Papers. New York, American Institute of Aeronautics and Astronautics, Inc., 1980, 130-147. 11 refs. (AIAA 80-0633) p. A80.28854 # Avoiding divergent stall in control configured A brief study was conducted on the power improvement of aircraft by using a canard arrangement. C. W. McCutchen )National horizontal-axis wind turbines with modern airfoil sections and Institutes of Health, Laboratory of Experimental Pathology, multiple-speed PAM generators. On the basis of a reference single- Bethesda, Md.). Journal of Aircraft, vol. 17, Apr. 1980, p. 283, 284. speed variable-pitch ,wind turbine with NACA 23018 blades, the The use of an unstable canard configuration for pitch control in following improvements can be made with a three-speed PAM aircraft with automatically controlled stability is investigated. Auto- generator and NASA LS)1)-0417 blades: (1) 15% gain of plant matic, as opposed to inherent, stability permits the center of gravity factor, i.e., average annual energy generation, (2) 17% gain of power of an aircraft to be shifted aft, thus improving the lift/drag ratio and output at a rated wind speed of 25 mph, and (3) 70% gain of power maneuverability. However, increased loading on the rear surface output at a higher wind speed of 32 mph. (Author) makes this surface prone to stall and can lead to pitching moments which may be difficult or impossible to control. By using a canard layout, a pitching divergence can be checked or a stall recovery can A80.28851 # Flutter analysis of a NACA 64A006 airfoil in be made by reducing the lift of the canard surface, which is always small disturbance transonic flow. T. Y. Yang, P. Guruswamy, A. G. possible, rather than by increasing the lift of a tail surface, which Striz (Purdue University, West Lafayette, Ind.), and J. J. Olsen may be impossible. (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio). V. L. Journal of Aircraft, vol. 17, Apr. 1980, p . 225-232. 16 refs. Grant No. AF-AFOSR-78-3523. A80-28856 # Application of unsteady airfoil theory to Flutter analyses are performed for a NACA 64A006 airfoil rotary wings. W. Johnson (U.S. Army, Research and Technology pitching and plunging in small-disturbance, unsteady transonic flow. Laboratories, Moffett Field, Calif.). Journal of Aircraft, vol. 17, Apr. Flutter results are presented as plots of flutter speed and correspond- 1980, p. 285, 286. ing reduced frequency vs one of the four parameters: airfoil/air mass The correct application of unsteady airfoil theory to helicopter density ratio, position of mass center, position of elastic axis, and rotor load analysis is explained. It is shown that airfoil motion only freestream Mach number. In each figure, several sets of curves for enters the problem through the boundary condition, which involves
217 A80-28857
normal velocity. The equations of Theodorsen theory specifying lift and pitch moment from a thin, two-dimensional airfoil undergoing unsteady motion in an incompressible flow are rewritten to emphasize that the mean and linear normal velocity distribution components over the airfoil chord must be identified, rather than the airfoil section pitch and heave motions. The incorrect identification of these terms is shown to lead to serious errors in moment calculation, and the nonequivalence of flapping and feathering motion for an articulated rotor blade. The calculation is then illustrated for the case of the rigid flap and rigid pitch motion of an articulated rotor blade in forward flight. A.L.W.
A80-28857 .1/ Class of shockfree airfoils producing the same surface pressure. W. C. Chin (Boeing Co., Aerodynamics Research Group, Seattle, Wash.). Journal of Aircraft, vol. 17, Apr. 1980, p. 286. 288. 7 refs. The feasibility of shockfree airfoils producing the same surface pressure over a wide range of operating Mach numbers is investigated. Numerical results are presented for a series of airfoils corresponding to a known base-line shockfree pressure; it is shown that physically acceptable airfoils can be found. The results are significant in the engineering of adaptive wings aimed at fixing, throughout a range of Mach numbers, pressure distributions with desirable loading and boundary layer separation characteristics. V. L.
A80. 28862 The freight forwarder as an air carrier, D. Schoner. (International Bar Association, Seminar, Zurich, Switzer- land, Sept 19, 20, 1979.) Air Law, vol. 5, no. 1, 1980, p. 2. 15. 94 refs. The purpose of the paper is to describe the differences between the freight forwarder and the air carrier, in order to determine when the freight forwarder is to be considered an air carrier. Attention is given to the national laws of Switzerland, Belgium, Italy, and France as well as to the U.S. The question regarding the classification differences is discussed with respect to the Guadalajara Convention of 1961. C.F.W.
A80-28947 Experimental study of electrostatic dischargers for helicopters (Etude expérimentale d'un déchargeu r électrostatique pour hélicoptère). S. Lagrigaldie (ONERA, Chàtillon.sous.Bagneux, Hauts-de-Seine, France) and N. Fétici (CNJRS, Laboratoire d'Electro. statique, Grenoble, France). (Revue de Physique Appliquée, vol. 15, Jan. 1980, p. 81 .91.) ONERA TP no. 1980-5, 1980. ( p . 81-91) 12 p. 12 refs. In French. An electric discharge system which operates on the principle of atmospheric water vapor condensation and charged aerosol forma- tion has been developed. It is experimentally shown that it is possible to remove a current of 60 microamperes from a helicopter surface. Radio frequency interference associated with the operation of the discharger should be negligible. B. J.
218 N80-17987
radially distorted, and/or azimuthally distorted inflow was examined. Swirling flow and distortions in the axial velocity profile in the annulus upstream of the diffuser inlet were caused by the intrinsic flow patterns downstream of a fan in a duct and by artificial intensification of the distortions. Azimuthal distor- tions or defects were generated by the addition of four artificial devices (screens and fences(. Pressure recovery data indicated STAR ENTRIES beneficial effects of both radial distortion (for a limited range of distortion levels( and inflow swirl. Small amounts of azimuthal distortion created by the artificial devices produced only small effects on diffuser performance. A large artificial distortion device was required to produce enough azimuthal flow distortion to significantly degrade the diffuser static pressure recovery. Author
N80-17982# Loughborouh Univ. of Technology (England). N80-17985# Toronto Univ., Downsview (Ontario). Inst. for Dept. of Transport Technology. Aerospace Studies. A CONSIDERATION OF GENERAL AVIATION IN THE RESEARCH ON THE STABILITY OF AIR CUSHION UNITED KINGDOM SYSTEMS R. E. Caves May 1979 73 p refs P. A. Sullivan, M. Hinchey, I. Murra. and G. J. Parravano Nov. (TT-7902: ISSN-0140-9751( Avail: NTIS HC A04/MF AOl 1979 166 p refs A semistructural analysis of the operational and economic (UTIAS-238: ISSN-0082-5255( Avail: NTIS viability on 1978 data, is presented. Models of contemporary HC A08/MF AOl fare structures, block times, and costs are developed in order to Certain specified problems encountered in the development of determine break even values for third level scheduled opera- flexible multicell type skirted air cushions for overland use are tions Two potentially attractive routes from a theoretical stand described. The hysteresis mechanisms in static roll stiffness are point are examined to demonstrate the marginal nature of third included. A preliminary examination of the dynamics of a skirt level operations. Some attention is given to airport access, to developed for low speed operation is reported and the progress nonscheduled general aviation, and to the relevance of the results made on the analysis and prediction of self excited oscillations within present U.K. transport planning choices. Author (ESA) in heave is summarized. R.C.T.
N80-17983 Illinois Inst. of Tech.. Chicago. N80- 1 7986# National Aeronautics and Space Administration. DYNAMIC STALL ON OSCILLATING AIRFOILS IN OSCIL- Hugh L. Dryden Flight Research Center, Edwards, Calif. LATING FREE-STREAMS Ph.D. Thesis WIND-TUNNEL/FLIGHT CORRELATION STUDY OF AERO- Bang-Ji Hsieh 1979 278 p DYNAMIC CHARACTERISTICS OF A LARGE FLEXIBLE Avail: Univ. Microfilms Order No. 8003648 SUPERSONIC CRUISE AIRPLANE (XB-70-1). 3: A The dynamic stall phenomenon on an oscillating airfoil in COMPARISON BETWEEN CHARACTERISTICS PREDICTED the presence of the free stream oscillations was studied. The FROM WIND-TUNNEL MEASUREMENTS AND THOSE study was conducted on a NACA 0012 profile airfoil which MEASURED IN FLIGHT was oscillating in pitch around a mean angle of attack of Henry H. Arnaiz, John B. Peterson, Jr. (NASA. Langley Research 15 degrees with an amplitude of 10 degrees. The corresponding Center), and James C. Daugherty (NASA. Ames Research Center) range of angles extending from 5 to 25 degrees includes the Mar. 1980 59 p refs angle of stall of a stationary airfoil in steady flow which was (NASA-TP-1516; H-1079( Avail: NTIS HC A04/MF AOl CSCL about 12 degrees under present conditions. Tests were made in O1A both steady and oscillating free streams and at the two reduced A program was undertaken by NASA to evaluate the accuracy frequencies of 0.15 and 0.25. Education. i.e.. periodic sampling of a method for predicting the aerodynamic characteristics of and averaging was used to remove the nonphase related noise large supersonic cruise airplanes. This program compared predicted from the pressure signals providing an instantaneous ensemble and flight-measured lift, drag, angle of attack, and control surface average which was phase related to the oscillation of the airfoil, deflection for the XB-70- 1 airplane for 14 flight conditions with of the free stream, or both. The instantaneous distributions of a Mach number range from 0.76 to 2.56. The predictions were pressure coefficient, normal force coefficient and moment derived from the wind-tunnel test data of a 0.03-scale model of coefficient were computed from the instantaneous educted the XB-70-1 airplane fabricated to represent the aeroelastically pressure signals in terms of the instantaneous dynamic pressure deformed shape at a 2.5 Mach number cruise condition. of the free stream. Comparisons between tripped and untripped Corrections for shape variations at the other Mach numbers were flows and between the flows at the two reduced frequencies included in the prediction For most cases, differences between are discussed. Dissert. Abstr. predicted and measured values were within the accuracy of the comparison. However, there were significant differences at transonic Mach numbers. At a Mach number of 1.06 differences N8011984*# National Aeronautics and Space Administration. were as large as 27 percent in the drag coefficients and 20 Ames Research Center, Moffett Field, Calif. deg in the elevator deflections. A brief analysis indicated that a AN EXPERIMENTAL INVESTIGATION OF TWO LARGE significant part of the difference between drag coefficients was ANNULAR DIFFUSERS WITH SWIRLING AND DISTORTED due to the incorrect prediction of the control surface deflection INFLOW required to trim the airplane. ' Author William T. Eckert. James P. Johnston (Stanford Univ., Calif.), Tad D. Simons (Stanford Univ., Calif.), Kenneth W Mort. and V. N8017987*# National Aeronautics and Space Administration, Robert Page Feb. 1980 106 p refs Washington, D. C. (NASA-TP- 1628; AVRADCOM-TR-79-40; A-7436( Avail. NTIS BOUNDARY LAYER CONTROL BY MEANS OF SUCTION HC A06/MF AOl CSCL 01A G. Maillart Jan. 1980 45 p refs Transl. into ENGLISH from Two annular diffusers downstream of a nacelle-mounted fan Bull. des Services Techniques 106, Apr. 1947 35 p Original were tested for aerodynamic performance, measured in terms of language document was announced as N79-71086 Transl. by two static pressure recovery parameters (one near the diffuser Kanner (Leo( Associates. Redwood City, Calif. exit plane and one about three diameters downstream in the (Contract NASw-3199( settling duct) in the presence of several inflow conditions. The (NASA-TM-75502) Avail: NTIS HC A03/MF AOl CSCL two diffusers each had an inlet diameter of 1.84 m, an area O1A ratio of 2.3. and an equivalent cone angle of 11.5. but were The process of boundary layer control by means of suction distinguished by centerbodies of different lengths. The dependence is described. Its historical development is briefly traced, and its of diffuser performance on various combinations of swirling. application to airfoils and diffusers is discussed. Author
219 N80-17088
N80- 1 7988*/f National Aeronautics and Space Administration. A flow visualization method, similar to the vapor screen method Langley Research Center. Langley Station. Va. used in wind tunnels. was used to obtain trajectory data for a INTERACTION OF A TWO-DIMENSIONAL STRIP BOUNDA- range of flight speeds, airplane configurations, and wing loadings. RY LAYER WITH A THREE-DIMENSIONAL TRANSONIC Detailed measurements of the spanwise surface pressure SWEPT-WING CODE distribution were made for all test points. Further, a powered Perry A. Newman, James E. Carter. and Ruby M. Davis Mar. 1/8 scale model of the aircraft was designed, built, and used 1978 35 p refs to obtain tip vortex trajectory data under conditions similar to (NASA-TM-78640) Avail: NTIS NC A03/MF AOl CSCL that of the full scale test. The effects of light wind on the O1A vortices were demonstrated, and the interaction of the flap vortex A 3D inviscid transonic analysis code was combined with a and the tip vortex was clearly shown in photographs and plotted 2D strip integral boundary layer technique to form an approximate trajectory data. Author interaction procedure for analyzing the flow over a high aspect ratio wing near cruise conditions. Converged results obtained N80- 1 7993*/f National Aeronautics and Space Administration. using the procedure for an aspect ratio 10.3 supercritical wing Langley Research Center, Langley Station. Va. are discussed. Angle of attack adjustments were made during EFFECT OF SWEEP AND ASPECT RATIO ON THE LONGI- the iterative procedure in order to compensate for the viscous TUDINAL AERODYNAMICS OF A SPANLOADER WING IN- lift loss. A comparison of the calculations with experimental AND OUT-OF-GROUND EFFECT data is presented. A.W.H. Scott 0. Kjelgaard and John W. Paulson, Jr. Jan. 1980 166 p refs N8017989*fl Lockheed-Georgia Co., Marietta. (NASA-TM-80199) Avail: NTIS NC A08/MF AOl CSCL THE AERODYNAMIC DESIGN OF AN ADVANCED ROTOR O1A AIRFOIL A wind tunnel investigation was conducted to determine James A. Blackwell, Jr. and Bobby L. Hinson Mar. 1978 the effects of leading edge sweep, aspect ratio, flap deflection, 112 p and eleven deflection on the longitudinal aerodynamic characteris- (Contract NAS1-14597) tics of a span distributed load advanced cargo aircraft (spanloader). (NASA-CR-2961; LG77ER0208) Avail: NTIS Model configurations consisted of leading edge sweeps of 0. NC A06/MF AOl CSCL 01A 15. 30. and 45 deg and aspect ratios of approximately 2. 4. 6. An advanced rotor airfoil, designed utilizing supercritical and 8. Data were obtained for angles of attack of -8 to 18 deg airfoil technology and advanced design and analysis methodology Out of ground effect and at angles of attack of -2. 0. and 2 deg is described. The airfoil was designed subject to stringent in ground effect at Mach number equal 0.14. Flap and elevon aerodynamic design criteria for improving the performance over deflections ranged from -20 to 20 deg. The data presented in the entire rotor operating regime. The design criteria are discussed. tabulated form are intended for reference purposes and are The design was accomplished using a physical plane, viscous, presented without analysis. A.W.H. transonic inverse design procedure, and a constrained function minimization technique for optimizing the airfoil leading edge N8017994*// Pennsylvania State Univ., University Park. Dept. shape. The aerodynamic performance objectives of the airfoil of Aerospace Engineering. are discussed. A.W.H. COMPUTER PREDICTION OF THREE-DIMENSIONAL POTENTIAL FLOW FIELDS IN WHICH AIRCRAFT PROPEL- N8O17991*// National Aeronautics and Space Administration, LERS OPERATE: COMPUTER PROGRAM DESCRIPTION Washington, D. C. AND USERS MANUAL COMPARISON OF AERODYNAMIC COEFFICIENTS Stephen J. Jumper Aug. 1979 258 p refs OBTAINED FROM THEORETICAL CALCULATIONS WIND (Grant NsG-1308) TUNNEL TESTS AND FLIGHT TESTS DATA REDUCTION (NASA-CR-162816; PSU-Aero-R-79/80-5) Avail: NTIS FOR THE ALPHA JET AIRCRAFT HC Al2/MF AOl CSCLO1A A method was developed for predicting the potential flow R. Guiot and H. Wunnenberg Feb. 1980 31 p refs Transl. into ENGLISH of "Comparison des Coefficients Aerodynamiques velocity field at the plane of a propeller operating under the Issues des Calculs Theoretiques. Essais en Soufflerie et Depouille- influence of a wing-fuselage-cowl or nacelle combination. A ments d'Essais en vol Effectues sur 'Alpha Jet". Rept. computer program was written which predicts the three AGARD-CP-187 AGARD Presented at tft 46th Meeting of dimensional potential flow field. The contents of the program, the Flight Mech. Panel, Valloire, France, 9-13 Jun. 1975 p its input data, and its output results are described. R.E.S. 19-1 - 19-15 Original language document was announced as N76-25295 Transl. by Kanner (Leo) Associates Redwood City, N80-17996# Naval Surface Weapons Center, White Oak, Md. Calif. Original language document prepared by Avions Marcel AN EXPERIMENTAL STUDY OF TWO-DIMENSIONAL Dassault . Breguet Aviation, Saint-Cloud, France and Dornier-Werke SUPERSONIC JET IMPINGEMENT ON A FLAT PLATE G.m.b.H.. Friedrichshafen. West Germany T. F. Zien and R. T. Driftmyer Aug. 1979 95 p refs (Contract NASw-3199) (AD-AO76536; NSWC/TR-79-289) Avail: NTIS (NASA-TM-75237; AGARD-CP- 187) Avail: NTIS NC A05/MF AOl CSCL 20/4 NC A03/MF AOl CSCL O1A An experimental study of the flow field associated with a The methods by which aerodynamic coefficients are deter- two-dimensional, supersonic jet impinging normally on a flat plate mined and discussed. These include: calculations, wind tunnel is reported. Two wedge nozzles manufactured at the design Mach experiments and experiments in flight for various prototypes of numbers of 1.75 and 2.75, respectively, were used to provide the Alpha Jet. A comparison of obtained results shows good the jet. Extensive pitot surveys of the free jet were first conducted correlation between expectations and in-flight test results.J.M.S. to determine the quality of the free jet. Results indicate that the simple wedge nozzles were adequate in providing the desired two-dimensional jet in the free expansion configuration. Results N80.17992*// Mississippi State Univ., State College. Dept. of surface pressure measurements and schlieren photographs of of Aerospace Engineering. the impingement flow indicating the shock patterns are then FULL SCALE VISUALIZATION OF THE WING TIP VORTICES presented and discussed. Although the results are principally GENERATED BY A TYPICAL AGRICULTURAL AIRCRAFT reported for the case of the jet at isentropic exit conditions, Final Report some results of underexpanded and overexpanded jets are also Ernest J. Cross, Jr. Phillip D. Bridges, Joe A. Brownlee, W. included. Some discrepancies between the experiment and the Wayne Livingston et al Jan. 1980 102 p refs simple theory based in the method of integral relations and the (Contract NsG-151 1) inviscid flow model are noted and discussed. An 'effective' jet )NASA-CR-162796; M SSU-EIRS-ASE-8O-2) Avail: NTIS Mach number is introduced which accounts largely for the NC A06/MF AOl CSCL 01A discrepancy between experiments and theory, and its determina- The trajectories of the wing tip vortices of a typical tion is based on the measured stagnation point pressure on the agricultural aircraft were experimentally determined by flight test. plate surface. GRA
220 N80-18012
N80-18001# Neilsen Engineering and Research. Inc.. Mountain same airfoil moving forward-backwards in a uniform flow under View, Calif. the same conditions. As far as the mean effects on the lift, DATA REPORT FOR A TEST PROGRAM TO STUDY drag, pressure distribution, and vortex shedding mechanism on TRANSONIC FLOW FIELDS ABOUT WING-BODV/PYLON/ the upper side of the airfoil are concerned, the reciprocity of STORE COMBINATIONS. VOLUME 1: TUNNEL EMPTY the two kinds of flow is demonstrated, Author (ESA) FLOW SURVEY DATA, WING BODY FORCE/MOMENT/ SURFACE PRESSURE DATA, AND PRESSURE STORE FORCE/MOMENT/SURFACE PRESSURE DATA Interim N80-18008# Lockheed-California Co.. Burbank. Summary Report, 14-22 Feb. 1978 GENERAL AVIATION AIRPLANE STRUCTURAL CRASH- S. S. Stahara and A. J. Crisalli May 1978 256 p WORTHINESS PROGRAMMER'S MANUAL Final Report, Contract F44620-75-C-0047: AF Proj. 2307) Nov. 1977 - Dec. 1978 (AD-A077182; AFOSR-79- 1 O7OTR; NEAR-TR- 163-Vol-i) Avail: W. L. Labarge Jun. 1979 210 p Revised NTIS HC Al2/MF AOl CSCL 20/4 (Contract DOT-FA75WA-3707( Results are presented for transonic wind tunnel tests (A0-A075737: FAA-RD-78-120-Rev; LR-23683( Avail: NTIS conducted in the 4T Wind Tunnel at Arnold Engineering and HC AiO/MF AOl CSCL 13/12 Development Center for various wing-body/pylon store model A programming manual is presented to describe the program combinations. Experimental data were obtained at 0.2. and KRASH. Included are: systems requirements, input data deck, 5 degrees angle of attack of the model combinations and at and demonstration problems. M.M.M. Mach numbers of 0.925. 0.950. 1.05. and 1.10 in the transonic range. Pylon and store models were attached to a wing-body combination in two separate, systematic model build-up N8018010*# National Aeronautics and Space Administration. sequences. At each stage of the first sequence, flow velocities Ames Research Center, Moffett Field. Calif. and static pressures were obtained in the vicinity of the Store NASA AVIATION SAFETY REPORTING SYSTEM Quarterly or those regions normally occupied by S Store while force, moment, Report, 1 Apr. - 30 Jun. 1978 and surface pressure measurements were taken on the wing- Jun. 1979 54 p refs Prepared in cooperation with Battelle body model. Also, flow velocities and Static pressure were recorded Columbus Labs., Mountain View, Calif. on a cylindrical control surface far from the tunnel centerline to (NASA-TM-78608; A-7904: OR-9) Avail: NTIS provide Outer flow field conditions. The second model build-up HC A04/MF AOl CSCL O1C sequence involved a special pressure-instrumented store that was The human factors frequency considered a cause of or mounted on the captive trajectory system for simulating a contributor to hazardous events onboard air carriers are examined separating store Detailed pressure distributions and loading were with emphasis on distractions. Safety reports that have been obtained on the store. GRA analyzed, processed, and entered into the aviation safety reporting system data base are discussed. A sampling of alert bulletins N80-18002# Neilsen Engineering and Research. Inc.. Mountain and responses to them is also presented. J.M.S. View. Calif. DATA REPORT FOR A TEST PROGRAM TO STUDY N8018011*# National Aeronautics and Space Administration. TRANSONIC FLOW FIELDS ABOUT WING- BODY/ PYLON/ Langley Research Center. Langley Station, Va. STORE COMBINATIONS. VOLUME 2: FLOW FIELD THE AERIAL RELAY SYSTEM: AN ENERGY-EFFICIENT SURVEY DATA FOR CONFIGURATIONS 21 AND 22 Interim SOLUTION TO THE AIRPORT CONGESTION PROBLEM Report, 14-23 Feb. 1978 Albert C. Kyser Jan. 1980 24 p refs Presented at the AIAA S. S. Stahara and A. J. Crisalli May 1978 247 p Aircraft Systems and Technol. Meeting, New York, 22 Aug. )Contract F44620-75'C-0047: AF Proj. 2307) 1979 (AD-A077183 i AFOSR-79-1071TR: NEAR-TR- 163-Vol-2) Avail: (NASA-TM-80208( Avail: NTIS HC A02/MF AOl CSCL NTIS HC A11/MF AOl CSCL 20/4 17B This volume of the data report presentes the flow-field The ability to transfer airline passengers between aircraft in survey data for configurations 21 and 22 at Mach numbers Ml flight, if adequately developed and integrated into the national 0.925. M2 - 0.950. and M3 = 1.05 and angles of attack air transportation system, could provide significant improvements alpha 0. 2. and 5 degrees. The data were obtained in the 4T in transportation-system performance, in terms of airport Wind lunnel at Arnold Engineering and Development Center. congestion, fuel consumption, and passenger service. The proposed These tests, performed at a nominal Reynolds number per foot Aerial Relay System concept, which was developed as a means of 3.0 x 10 to the 6th power are indexed and outlined. GRA of exploiting inflight transfer, makes use of large 'cruise liner' aircraft which fly continuously along their routes. docking N80-18003# Institut de Mecanique des Fluides de Marseille periodically with short-haul feeder aircraft for exchange of (France). payloads. Preliminary vehicle designs for a representative system TRANSIENT EFFECTS ON A STALLED AIRFOIL IN A are described and the operational feasibility of the concept for PULSATING FLOW: COMPARISON WITH RESULTS FROM the United States in the 1990's is discussed. R.E.S. A SIMILAR AIRFOIL UNDERGOING HORIZONTAL SHAK- ING [EFFETS INSTATIONNAIRES SUR UN PROFIL EN DECROCHAGE DANS UN ECOULEMENT PULSE; COMPAR- N80-18012# Defence and Civil lost, of Environmental Medicine, ISON AVEC LE MOUVEMENT DE TAMIS] Downsview (Ontario). C. Maresca, D. Favier, and J. Rebont Paris Assoc. Aeron. et HUMAN FACTORS IN HIGH SPEED LOW LEVEL AC- Astronautique de Paris 1979 66 p refs In FRENCH: ENGLISH CIDENTS: A 15 YEAR REVIEW summary Presented at 15th Colloq. d'Aerodyn. AppI . Marseille. R. C. Rud and D. F. Leben Jul 1979 13 refs 7-9 Nov. 1978 p (AD-A07622 1: DCIEM-79-R35( Avail: NTIS (Contract STTA-77/98/31 3/00/481/75/86) HC A02/MF AOl CSCL 01/2 )AAAF-NT-79-1 3: ISBN-2-7170-0540-4) Avail: NTIS The Canadian Forces introduced the gf 104G into Squadron HC A04/MF AOl: CEDOCAR, Paris FF 29 (France and EEC) Operation in 1963 and since that time these aircraft have operated FF 33 (others) in the high-speed, low-level environment in both the strike/ The unsteady effects encountered by a symmetrical airfoil reconnaissance and tactical support roles. Fifty-seven accidents NACA 0012 set at fixed indicence (20 deg) in an oscillating involving these aircraft are reviewed with regard to cause factors. flow (delta V/V = 0,74: C sub omega/2V = 0.65: Re = Marginal weather appears to be the one most significant factor 70,000) were studied. The results were obtained through contribution to low-level, high-speed accidents however, several measurements of aerodynamic components (lift, drag, moment) human factors such as visual contrast problems. fatigue. stress, evidenced by distributions of the static pressure and skin reaction time. 'mission completion' syndrome, inattention and friction along the chord of the airfoil and through visualizations task overload were identified. Aspects of accidents which typify around the airfoil at different phases of the period. The results human factors problems are described. Suggested possible are discussed and compared with those already obtained on the preventive measures are outlined. Author (GRA)
221 N80-18013
N80-18013# Naval Air Development Center. Warminster. Pa. William F. White and Leonard Clark Jan. 1980 41 p refs Aircraft and Crew Systems Technology Directorate. )NASA-TM-80223) Avail: NTIS HC A03/MF AOl CSCL FEASIBILITY TESTING OF A BODY INFLATABLE BLADDER 17G (BIB) RESTRAINT DEVICE Phase Report The flight performance of the Terminal Configured Vehicle Marcus Schwartz Apr. 1979 46 p airplane is summarized. Demonstration automatic approaches and )WF4 1400000) landings utilizing time reference scanning beam microwave landing )AD . A078681; NADC.79241-60) Avail: NTIS system (TRSB/MLS) guidance are presented. The TRSB/MLS HC A03/MF AOl CSCL 06/17 was shown to provide the terminal area guidance necessary for A feasibility model of an inflatable type restraint system flying curved automatic approaches with final legs as short as was designed and developed for use with existing operational 2 km. R.E.S. restraint hardware to improve crewman safety during ejection. The vest type inflatable system is worn over the flight suit and under the MA-2 integrated torso harness. Upon inflation, the N80-18024# Atmospheric Sciences Lab.. White Sands Missile crewman is forced back into the suit while slack is removed Range, N. Mex. from the harness. Subsequent ejection tower testing has HELICOPTER REMOTE WIND SENSOR SYSTEM DESCRIP- demonstrated significant reductions in horizontal head and torso TION response during the catapult phase of the ejection.Author )GRA) O H. Dickson and Charles M. Sonnenschein Sep. 1979 57 p (DA Proj. 1L1-62111 -AH-7 1) Avail: NTIS N80-18014# Technische Hogeschool. Delft )Netherlands). Afdel. (AD . A076 153; ERADCOM/ASL-TR-0040) der Luchtvaart- en Ruimtevaarttechniek. HC A04/MF AOl CSCL 14/2 AVIATION SAFETY AND ITS IMPROVEMENT [DE The helicopter remote wind sensor (HRWS) is an application VEILIGHEID IN DE LUCHTVAART EN HAAR BEWAKINGI of a laser Doppler velocimeter. This system description describes H. Wittenberg Jan. 1978 55 p refs In DUTCH Presented the HRWS fabricated by Raytheon Company for the US Army at Symp. Veiligheid van de Vervoerssystemen. DeIft, 17 Mar. Atmospheric Sciences Laboratory. The HRWS was designed to 1978 measure wind fields in an aircraft turbulent environment. The (VTH . LR-260) Avail: NTIS HC A04/MF AOl operational emphasis is to augment an attack helicopter's fire A synopsis of 75 years of air transportation data was compiled control system. This CO2 laser heterodyne system remotely in relation to aircraft accidents and aviation safety. Regulations measures three dimensional winds from 1 to 33 meters in front covering aircraft construction, maintenance, aircraft control and of the sensor. The HAWS was mounted in an external pod navigation, training, and accident investigation are reviewed. compatible with AH-1. AAH and UH-1 wing stores or a fixed Author (ESA) wing aircraft equipped with standard wing shackles. The HRWS theory, functions, and subsystem are discussed. Data from flight N80. 18011# Federal Aviation Administration, Washington, D. C. and ground testing will be presented in a later report. GRA Office of Systems Engineering Management. REPORT ON THE TASK FORCE ON AIRCRAFT SEPARA- TION ASSURANCE, APPENDICES N80. 18028*# National Aeronautics and Space Administration. D. J. Bryant, D. G. Hamrick, W. D. Love. A L. McFarland, A. Langley Research Center, Langley Station. Va. D. Mundra, H. C. Strunz. and C. F. Swett Jan. 1979 334 p TERMINAL CONFIGURED VEHICLE PROGRAM: TEST ref FACILITIES GUIDE (AD-A077713; FAA-EM-78-19-Vol-3-App. AEM-2) Avail: Washington 1980 67 p refs NTIS HC A15/MF AOl CSCL 17/7 (NASA-SP-435( Avail: NTIS HC A04/MF AOl CSCL 01C An integrated aircraft separation assurance (ASA( system The terminal configured vehicle (TCV( program was established for the national airspace system is examined. The system element to conduct research and to develop and evaluate aircraft and requirements which are defined to provide two levels of backup. flight management system technology concepts that will benefit to the ATC system, a separation violation warning and a final conventional take off and landing operations in the terminal area. fail safe collision advisory and resolution function, are defined. Emphasis is placed on the development of operating methods Current A SA development programs are discussed and the for the highly automated environment anticipated in the future. changes required to make the transition to an integrated ASA The program involves analyses, simulation, and flight experiments. system are reported. This volume includes appendices for two Flight experiments are conducted using a modified Boeing previous volumes and defines in detail the specific interfaces 737 airplane equipped with highly flexible display and control and designs required for system integration. A.W.H. equipment and an aft flight deck for research purposes. The experimental systems of the Boeing 737 are described including N80. 18020*# Research Triangle Inst., Durham, N. C. the flight control computer systems, the navigation/guidance CONTINUED STUDY OF' NAVSTAR/GPS FOR GENERAL system, the control and command panel. and the electronic display AVIATION Final Report system. The ground based facilities used in the program are described including the visual motion simulator, the fixed base A. D. Alberts and W. H. Ruedger Dec. 1979 214 p refs (Contract NAS1-14719) simulator, the verification and validation laboratory, and the radio A. W. H. (NASA-CR- 159145; RTI-1404-00-01 F) Avail: NTIS frequency anechoic facility. HC A10/MF AOl CSCL 17G A conceptual approach for examining the full potential of Global Positioning Systems (G PS) for the general aviation N8018029*# Boeing Vertol Co., Philadelphia, Pa. community is presented. Aspects of an experimental program to SYNTHESIS OF ROTOR TEST DATA FOR REAL-TIME demonstrate these concepts are discussed. The report concludes SIMULATION with the observation that the true potential of GPS can only be M. A. McVeigh Mar. 1979 232 p refs exploited by utilization in concert with a data link. The capability (Contract NAS2-901 5) afforded by the combination of position location and reporting (NASA-CR-152311: D210-11505-1( Avail: NTIS stimulates the concept of GPS providing the auxiliary functions HC A11/MF AOl CSCLO1C of collision avoidance. and approach and landing guidance. A A mathematical model of a hingeless tilting rotor is pre- series of general recommendations for future NASA and civil sented. The model was obtained by a systematic curve fit community efforts in order to continue to support GPS for general procedure applied to an extensive set of model scale wind tunnel aviation are included. R.E.S. data. The math model equations were used in a real time flight simulation model of a hingeless tilt rotor XV- 15 to assess changes N8O18021*# National Aeronautics and Space Administration. in flying qualities compared to those obtained using a previous Langley Research Center, Langley Station, Va. rotor model. Extensive plots of the rotor derivatives are given. FLIGHT PERFORMANCE OF THE TCV B-737 AIRPLANE Discussions of attempts to apply multivariable linear regression AT JORGE NEWBERRY AIRPORT, BUENOS AIRES, technqiues to the data and the use of an analytical rotor ARGENTINA USING TRSB/MLS GUIDANCE representation are included. Author
222 N80-18036
N8018030*# Boeing Vertol Co.. Philadelphia. Pa. current inventory to establish an extensive data base relating A HINGELESS ROTOR XV-15 DESIGN INTEGRATION transparency maintenance activity and associated logistical support FEASIBILITY STUDY. VOLUME 1: ENGINEERING DESIGN costs. An important adjunct to this study was to research STUDIES Final Report design characteristics, perform a failure analysis, and identify J. P. Magee and H. R. Alexander Mar. 1978 473 p associated logistical support cost for each study aircraft. By using (Contract NAS2-901 5) a selective process of correlating the transparency failure modes (NASA-CR-152310; D210-11360-1 -Vol- 1) Avail: NTIS and maintenance costs with the relative stature of aircraft in HC A20/MF AOl CSCL 01C current inventory, corrective programs were established and A design integration feasibility study was carried Out to verified by life-cycle cost trades. These corrective programs investigate what modifications to the basic XV-15 were necessary entailed a comprehensive search for various design improvement to accomplish a flight demonstration of the XV- 15 with a Boeing that could be innovated to negate the reported failures. The hingeless rotor. Also investigated were additional modifications study results contained herein are an extension of objectives of which would exploit the full capability provided by the combination the original program and are directed at supplementing the of the new rotor and the existing T53 engine. An evaluation of corrective programs for six additional aircraft. GRA the aircraft is presented and the data indicate improved air vehicle performance, acceptable aeroeleastic margins, lower noise levels Naval Air Development Center, Warminster, Pa. and improved flying qualities compared with the XV-15 aircraft. N80-18034# DESIGN AND TEST OF A BORON - ALUMINUM HIGH Inspection of the rotor system data provided shows an essentially TEMPERATURE WING Final Report unlimited life rotor for the flight spectrum anticipated for the R. J. Richey and T. E. Hess May 1979 106 refs XV-15. R.E.S. p (AD-A075814: NADC-79 145-60) Avail: NTIS NC A06/MF AOl CSCL 01/3 N8018031*// Analytical Mechanics Associates, Inc., Mountain The feasibility of utilizing the high buckling stability character- View. Calif. istics of boron - aluminum advanced composite material in a CONCEPTS FOR GENERATING OPTIMUM VERTICAL simple, low-cost spar-rib-skin construction for a thin airfoil FLIGHT PROFILES structure was investigated for high temperature application up John A. Sorensen Sep. 1979 107 p refs to 589 K. The design concept developed consists of boron- (Contract NAS1-15497) aluminum skins, to carry the primary bending and torsion loads, (NASA-CR-159181) Avail: NTIS HC A06/MF AOl CSCL mechanically fastened to a light gage steel sub-structure, which O1C resists transverse shear and stabilizes the skins. The viability of Algorithms for generating optimum vertical profiles are derived the concept depends on whether this stabilization of the skin and examined. These algorithms form the basis for the design material can be accomplished with a practical number and spacing of onboard flight management concepts. The variations in the of substructure elements. A weight saving of one third in optimum vertical profiles (resulting from these concepts) due to comparison to the production article is projected in this variations in wind, takeoff weight, and range-to-destination are boron-aluminum version of the BYM-34E wing. A major wing presented. Further considerations for mechanizing two different subcomponent was fabricated and static tested to validate the onboard methods of computing near-optimum flight profiles are structural adequacy of the overall design. GRA then outlined. Finally, the results are summarized, and recom- mendations are made for further work. Technical details of N80-18035# Boeing Aerospace Co., Seattle, Wash. optimum trajectory design, steering requirements for following NEW REMOTELY PILOTED VEHICLE LAUNCH AND these trajectories, and off-line computer programs for testing RECOVERY CONCEPTS: COMPUTER PROGRAM LISTINGS the concepts are included J.M.S. Final Report, Mar, 1978 - Mar, 1979 Steven J. Baumgartner, Roger F. Yurczyk. James G. Brister. and N8018032*# National Aeronautics and Space Administration. Vinod K. Rajpaul Jun. 1979 173 p Langley Research Center, Langley Station, Va. (Contract F33615-78-C-3404, AF Proj. 2402) PERFORMANCE ESTIMATES OF A BOEING 747-100 )AD-A07661 1. AFFDL-TR-79-3069-VoI-2) Avail: NTIS TRANSPORT MATED WITH AN OUTSIZE CARGO POD HC A08/MF AOl CSCL 01/3 Lloyd S. Jernell Feb. 1980 20 p refs Dynamic analysis. preliminary design, and performance/cost (NASA-TM-80227( Avail: NTIS HC A02/MF AOl CSCL trade studies of air bag skid and air cushion concepts for launch 01C and recovery of Boeing and Rockwell advanced RPV concepts The design mission performance of a Boeing 747-100 aircraft have been conducted. Dynamic analysis was performed using mated with an outsize cargo pod was studied. The basic design the six degree-of-freedom computer program EASY. Dynamic requirement was the rapid deployment of a combat loaded mobile simulations included perturbations to steady state flight, landing, bridge launcher from a United States east coast staging base and takeoff simulations. Launch and recovery concepts investi- to Europe. Weight was minimized by stripping the aircraft of gated were air bag skid system, air cushion recovery system, unneeded, quick removal items and by utilizing graphite-epoxy integrated air cushion system, and air cushion launch platform. composite materials for most pod components. The mission Performance/ cost trade study factors investigated were complex- analysis was based on wind tunnel data and full scale carrier ity, fuel requirements, adverse weather capability, ground aircraft and engine data. The results are presented in tabular equipment and facility requirements, survivability, reliability and and graphic form. AWN. maintainability, and system acquisition and life cycle costs. Results of the study indicated that an air cushion system is a feasible means of recovery of an RPV such as the Boeing and Rockwell N80-18033# North American Rockwell Corp. El Segundo, Calif. ARPV concepts. An air bag skid with an arrestor system is a AIRCRAFT TRANSPARENCY FAILURE AND LOGISTICAL feasible approach when minimum field length is a major design COST ANALYSIS: SUPPLEMENTAL STUDY Final Report. factor. Integrated air cushion system for launch and recovery Feb. - Jun. 1979 are greatly affected by engine characteristics. In each case. the S. S. Brown Wright-Patterson AFB, Ohio AFFDL Jun. 1979 launch and recovery systems are shown to be an integral part 250 p refs of the total vehicle design and strongly influences the airframe (Contract F33615-77-C-3060; AF Proj. 2402( design. GRA (AD-A075500; NA-79-237; AFFDL-TR-79-3083( Avail: NTIS NC A11/MF AOl CSCLO1/3 N80-18036t National Aeronautics and Space Administration. Concern for increasing costs in maintenance of transparency Hugh L. Dryden Flight Research Center, Edwards, Calif. systems has prompted the Air Force Flight Dynamics Laboratory AIR SPEED AND ATTITUDE PROBE Patent to sponsor this study contract. The object of this study is to Gerald J. Baker and Merle A. Economu, inventors (to NASA) identify the high-cost, high maintenance transparency components; Issued 15 Jan. 1980 6 p Filed 30 May 1978 Supersedes identify cause of failures; and recommend corrective programs N78-25088 (16 - 16. p 2077) to reduce cost of ownership to the Air Force Logistics Com- (NASA-Case-FRC- 11009-1; US-Patent-4, 184,149: mand. The study involved the review of 20 selected aircraft in US-Patent-Appl-SN-9 10708; US-Patent-Class-340- 1 77VA,
223 N80- 18037
US-Patent-Class-73- 188; US-Patent-Class-73-189; N8018039* National Aeronautics and Space Administration. US-Patent-Class-73-212( Avail: US Patent and Trademark Lewis Research Center, Cleveland, Ohio. Office CSCL 010 METHOD AND APPARATUS FOR RAPID THRUST IN- An air speed and attitude probe characterized by a pivot CREASES IN A TURBOFAN ENGINE Patent shaft normally projected from a data boom and supported thereby Jack E. Cornett (GE. Cincinnati. Ohio). Ralph C. Corley (GE. for rotation about an axis of rotation coincident with (he Cincinnati. Ohio), Thomas 0. Fraley (GE. Cincinnati. Ohio). and longitudinal axis of the shaft is described. The probe is a tubular Andrew A. Saunders. Jr., inventors (to NASA) (GE. Cincinnati. body supported for angular displacement about the axis of rotation Ohio( Issued 22 Jan. 1980 9 p Filed 9 Dec. 1977 Sponsored and has a fin mounted on the body for maintaining one end of by NASA the body in facing relation with relative wind and has a pair of (NASA-Case- LE W- 12971-1: US-Patent-4,184,327 transducers mounted in the body for providing intelligence US-Patent-Appl-SN-858936: US- Patent- Class-60-240; indicative of total pressure and static pressure for use in US-Patent-Class-6O-39.03; US-Patent-Class-60-39.27 ) Avail: determining air speed. A stack of potentiometers coupled with US Patent and Trademark Office CSCL 21E the shaft to provide intelligence indicative of aircraft attitude. Upon a landing approach, the normal compressor stator and circuitry connecting the transducers and potentiometers to schedule of a fan speed controlled turbofan engine is temporarily suitable telemetry circuits are described. varied to substantially close the stators.to theieby increase the Official Gazette of the U.S. Patent and Trademark Office fuel flow and compressor speed in order to maintain fan speed and thrust. This running of the compressor at an off-design speed substantially reduces the time required to subsequently advance N8018037*# National Aeronautics and Space Administration. the engine speed to the takeoff thrust level by advancing, the Langley Research Center, Langley Station. Va. throttle and opening the compressor stators. EARLY FLIGHT TEST EXPERIENCE WITH COCKPIT Official Gazette of the U.S. Patent and Trademark Office DISPLAYED TRAFFIC INFORMATION (CDTI) Terence S. Abbott, Gene C. Moen (Army Res. and Technol. Labs.. Hampton, Va.), Lee H. Person, Jr., Gerald L. Keyser, Jr.. Kenneth N8O18040*# Little (Arthur D). Inc.. Cambridge, Mass. R. Yenni. and John F. Garren Feb 1980 31 p refs STUDY OF RESEARCH AND DEVELOPMENT REQUIRE- (DA Proj. 1 L2.62209-AH-76( MENTS OF SMALL GAS-TURBINE COMBUSTORS (NASA-TM-80221; AVRADCOM-TR . 80-13-2) Avail: NTIS E. P. Demetri, R. F. Topping, and R. P. Wilson, Jr. Jan. 1980 HC A03/MF AOl CSCL 010 69 p refs Coded symbology, based on the results of early human factors (Contract NAS3-21980( studies, was displayed on the electronic horizontal situation (NASA-CR-159796; ADL-83381 -21 Avail: NTIS indicator and flight tested on an advanced research aircraft in HC A04/MF AOl CSCL 21E order to subject the coded traffic symbology to a realistic flight A survey is presented of the major small-engine manufacturers environment and to assess its value by means of a direct and governmental users. A consensus was undertaken regarding comparison with simple, uncoded traffic symbology. The tests small-combustor requirements. The results presented are based consisted of 28 curved, decelerating approaches, flown by on an evaluation of the information obtained in the course of research-p, jpt flight crews. The traffic scenarios involved both the study. The current status of small-combustor technology is conflict-free and blunder situations. Subjective pilot commentary reviewed. The principal problems lie in liner cooling, fuel injection, was obtained through the use of a questionnaire and extensive part-power performance, and ignition. Projections of future engine pilot debriefing sessions. The results of these debriefing sessions requirements and their effect on the combustor are discussed. group conveniently under either of two categories: display factors The major changes anticipated are significant increases in or task performance. A major item under the display factor category operating pressure and temperature levels and greater capability was the problem of display clutter. The primary contributors to of using heavier alternative fuels. All aspects of combustor design clutter were the use of large map-scale factors, the use of traffic are affected, but the principal impact is on liner durability. An data blocks, and the presentation of more than a few aircraft. R&D plan which addresses the critical combustor needs is In terms of task performance, the cockpit displayed traffic described. The plan consists of 15 recommended programs for information was found to provide excellent overall situation achieving necessary advances in the areas of liner thermal design, awareness. R.E.S. primary-zone performance, fuel injection, dilution, analytical modeling, and alternative-fuel utilization. M.M.M. N8O- 1 8038*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. N8018042*// Vought Corp.. Dallas, Tex. THE EFFECT OF VIEWING TIME, TIME TO ENCOUNTER. LOW SPEED TEST OF THE AFT INLET DESIGNED FOR A AND PRACTICE ON PERCEPTION OF AIRCRAFT SEPARA- TANDEM FAN V/STOL NACELLE TION ON A COCKPIT DISPLAY OF TRAFFIC INFORMA- W. W. Rhoades and A. H. Ybarra Feb. 1980 79 p refs TION (Contract NAS3-21468( Sharon OConnor, Everett Palmer. Daniel Baty. and Sharon Jago )NASA-CR-159752: TR-2-30320/OR . 52360( Avail: NTIS Feb. 1980 17 p refs Prepared in cooperation with San Jose HC A05/MF AOl CSCL 21E State Univ.. Calif. An approximately .25 scale model of a Tandem Fan nacelle (Grant NsG-2269( designed for a Type A V/STOL aircraft configuration was tested (NASA-TM-81173; A-8072( Avail: NTIS HC A02/MF AOl in a 10-by-10 foot wind tunnel. A 12 inch. tip driven, turbofan CSCL 010 simulator was used to provide the suction source for the aft fan The concept of a cockpit display of traffic information ICDTII inlet. The front fan inlet was faired over for this test entry. includes the Integration of air traffic, navigation, and other pertinent Model variables consisted of a long aft inlet cowl, a short aft information in a single electronic display in the cockpit. Two inlet cowl, a shaft simulator, blow-in door passages and diffuser studies were conducted to develop a clear and concise display vortex generators. Inlet pressure recovery, distortion, inlet angle format for use in later full-mission simulator evaluations of the of attack separation limits were evaluated at tunnel velocities COTI concept. Subjects were required to monitor a CDTI for from 0 to 240 knots, angles of attack from -10 to 40 degrees specified periods of time and to make perceptual judgments and inlet flow rates representative of throat Mach numbers of concerning the future position of a single intruder aircraft in 0.1 to 0.6. High inlet performance and stable operation was relationship to their own aircraft. Experimental variables included: verified at all design forward speed and angle of attack conditions. type of predictor information displayed on the two aircraft symbols: The short aft inlet configuration provided exceptionally high time to encounter point: length of time subjects viewed the pressure recovery except at the highest combination of angle of display: amount of practice; and type of encounter (straight or attack and forward speed. The flow quality at the fan face was turning(. Results show that length of viewing time had little or somewhat degraded by the addition of blow-in door passages no effect on performance: time to encounter influenced perform- to the long aft inlet configuration due to the pressure disturbances ance with the straight predictor but did not with the curved generated by the flow entering the diffuser through the auxiliary predictor; and that learning occurred under all conditions. R.E.S. air passages. M M. M.
224 N80-18049
N80- 1 8043fl National Aeronautics and Space Administration. system on a 1/9-scale F-16 model and to determine the Lewis Research Center. Cleveland. Ohio. interference induced on the afterbody-nozzle region by a sting, AEROPROPULSION IN YEAR 2000 a wingtip, and a strut model support system. The investigation Richard J. Weber 1980 18 p refs Proposed for presentation was conducted over the Mach number range from 0.6 to 1.5 and at Global Technol. 2000. the 1980 Intern. Meeting of the Am. at angles of attack from 0 to 9 deg. Interference was evaluated Inst. of Aeron. and Astronautics. Baltimore. 5-11 May 1980 by comparison of nozzle-afterbody axial and normal forces obtained 21A from integrating pressure data. The results include parametric A sampling of probable future engine types, such as convert- studies of the effects of various components of the wingtip ible engines for helicopters. turboprops for fuel-conservative air- support system (i.e., the support blade axial position, wingtip liners, and variable-cycle engines for supersonic transports are boom diameter, boom spacing, and boom-tip axial location). presented. Related technology improvements in propellers, High-pressure air at ambient temperature was utilized for exhaust materials, noise suppression. etc, are reviewed. R.E.S. plume simulation. The results indicate that a sting support passing through the nozzle with the jet effects simulated by an annular N80-18044fi Ohio State Univ. Research Foundation, Columbus. jet appears to offer a minimum interference support system for INVESTIGATION OF THE BOUNDARY LAYER BEHAVIOR the type of nozzle -afterbody test described in this report. GRA ON TURBINE AIRFOILS Final Report, 16 Jun. 1975 - 15 Dec. 1978 Lit S. Han, Wesley R. Cox. and Amon Chait Aug. 1979 273 p refs N80-18047# National Aeronautics and Space Administration. (Contract F33615-75-C-2052; AF Proj. 3066) Ames Research Center, Moffett FieLd, Calif. )AD-A075501. OSURF/760256/784174: AFAPL-TR-79-201 1) V/STOLAND AVIONICS SYSTEM FLIGHT-TEST DATA ON Avail: NTIS HC Al2/MF AOl CSCL 20/4 A UH-1H HELICOPTER Smoke flow visualization, hot-wire anemometer, and pressure Fredric A. Baker, Dean N. Jaynes, Lloyd D. Corliss, Sam Liden distribution studies were conducted to determine some of the (Sperry Rand Corp.. Phoenix, Aniz.), Robert B. Merrick, and Daniel wake and pressure surface boundary layer transition region C. Dugan Feb. 1980 68 p refs characteristics along an enlarged two-dimensional turbine airfoil )NASA-TM-78591; A-7831) Avail: NTIS HC A04/MF AOl model in cascade. Smooth surface as well as rough surface CSCL O1C airfoils were used in the study, which utilized a continuous, The flight-acceptance test results obtained during the subsonic, specially built wind-tunnel. The flow provided a range acceptance tests of the V/STOL.AND (versatile simplex digital of blade chord Reynolds numbers from 7.9E - 5 1.5E - 6 at avionics system) digital avionics system on a Bell UN-1H helicopter turbulence levels of 0.6 to 0.8%. A pressure surface transition in 1977 at Ames Research Center are presented. The system region was found to exist from about S/C 0.43 to the trailing provides navigation, guidance, control, and display functions for edge for the smooth surface airfoil, and up to S/C 0.1 for a NASA terminal area VTOL research programs and for the Army rough surface airfoil. The transition region for a smooth surface handling qualities research programs at Ames Research Center. was initiated through the formation of Goertler vortices which The acceptance test verified system performance and contractual were found to break down through the action of traveling acceptability. The V/ STOLA ND hardware navigation, guidance, Tollmein . Schlichting waves. Other phenomena observed include and control laws resident in the digital computers are described. various trailing edge vortex formations which may be linked to Typical flight-test data are shown and discussed as documentation the intermittency of the boundary layer near the trailing edge, of the system performance at acceptance from the contractor. and a low frequency traveling wave formed in conjunction with M.M.M. the appearance of traveling waves. An empirical relationship was developed for the traveling wave frequency. Comparison was N8018048*# National Aeronautics and Space Administration. made with stability theory and empirical methods of predicting Langley Research Center, Langley Station. Va. transition. Linear stability theory was found to predict the Goertler THRUST AUGMENTED SPIN RECOVERY DEVICE Patent wavelength, but not that of the traveling waves. GRA Application Bobby L. Berrier, inventor (to NASA) Filed 27 Apr. 1979 15 p N80-18045# Aeronautical Systems Div., Wright-Patterson AFB. Ohio. )NASA-Case-LAR-1 1970-2: US- Patent -Appl-SN-0341O4) Avail: NTIS HC A02/MF AOl CSCL 01C PROCEEDINGS OF THE 7TH ANN. TRI-SERVICE MEETING A lightweight and drag-free yaw control system developed FOR AIRCRAFT ENGINE MONITORING AND DIAGNOS- TICS Final Report, 5-7 Dec. 1979 for a jet propelled aircraft is described. Emphasis is placed on providing 'aircraft attitude control at low flight speeds, at high James L. Pettigrew and Keith Hamilton Jul. 1979 284 p angles of attack, and during spin. The control system is comprised Meeting held at Arnold Air Force Station, Tenn., 5-7 Dec. 1978 of a vertical tail with a thrust augmented rudder and a thrust (AD-A076126; ASD-TR-79-5040) Avail: NTIS rudder tab. The jet exhaust stream is deflected by the thrust NC A13/MF AOl CSCL 21/5 vectoring rudder tab in a sideward direction to the aircraft, These proceedings contain an edited compilation of the producing a thrust vectored yawing moment and creating presentations of government agencies at the Seventh Tr-Service supercirculation about the vertical tail and thrust augmented Diagnostic Conference held at Arnold Engineering Development rudder. Supercirculation, a thrust-induced aerodynamic phenom- Center, Arnold Air Force Station Tennessee 5-7 Dec 1978. The enon. generates lift without increasing drag, enabling the rudder program themes were current experience service needs and to provide additional yawing force for attitude control. technology thrusts in aircraft turbine engine monitoring and J.M.S. diagnostics. Working level representatives from the maintenance N80-18049# Office National d'Etudes et de Recherches organization of operating and support commands gave their views Aerospatiales. Paris (France). on the requirements for specific diagnostic and maintenance UNSTEADY EFFECTS WITH CONTROL SURFACES [EFFETS decision information. GRA INSTATIONNAIRES DES GOUVERNES] Richard Grenon and Andre Desopper Assoc. Aeron. et N80-18046# ARO, Inc., Arnold Air Force Station, Tenn. Astronautique de France 1979 14 p refs In FRENCH Presented AN INVESTIGATION OF F-16 NOZZLE-AFTER BODY at 15th Colloq. d'Aerodyn. AppI.. Marseille, 7-9 Nov. 1978 FORCES AT TRANSONIC MACH NUMBERS WITH EMPHA- )AAAF-NT-79-01; ISBN-2-7170-0528-5) Avail: NTIS SIS ON SUPPORT SYSTEM INTERFERENCE Final Report. NC A02/MF AOl, CEDOCAR; Paris FF 17 )France and EEC) Jan, - Jul. 1978 FF 21 (bthers) Earl A. Price, Jr. AEDC Dec. 1979 207 p refs Sponsored The unsteady phenomena observable around control surfaces by the Air Force in subsonic and transonic flow is discussed. Results obtained (AD-A078693; AEDC-TR-79-56; AFAPL-TR . 79 . 2099) Avail: with an airfoil profile equipped with a trailing edge flap moving NTIS HC A1O/MF AOl CSCL 20/4 sinusoidally in a two dimensional subsonic or transonic flow A comprehensive experimental program was conducted to regime are reported. Steady and unsteady pressure measurements provide nozzle-afterbody data with a minimum interference support made during wind tunnel tests are given. A comparison is
225 N80-18050 made between these measurements and results for the steady shading, and image aberrations are discussed. Particular attention and unsteady flow field of a perfect fluid. An attempt is made is given to hierarchical environment structure, image coherence, to take into consideration viscous effects. Results show that shading functions, and area averaging edge smoothing tech- theory does not satisfactorily describe coupling phenomena, niques. A.W.H. notably flow separation and the interaction between the shock front and the boundary layer. Author (ESA) N80-18054# Aeronautical Research Labs.. Melbourne (Australia). PROGRAMS FOR THE TRANSONIC WIND TUNNEL DATA N80-18050# Aerospatiale Usines de Toulouse (France). PROCESSING INSTALLATION. PART 7: EXTENDED Helicopters Div. FOCAL ROTORS IN FORWARD FLIGHT AND DYNAMIC STALL N. Pollock Mar. 1979 44 p refs [PALE RECULANTE ET DECROCHAGE DYNAMIQUE) (AD-A073414; ARL/Aero-TM-3 14) Avail: NTIS J. Renaud Paris Assoc. Aeron. et Astronique de France 1979 HC A03/MF AOl CSCL 09/2 26 p refs In FRENCH Presented at 15th Colloq. dAerodyn. Since the transonic wind tunnel data processing installation. Appl.. Marseille, 7-9 Nov. 1978 which is based on a POP 8-I computer, was installed in 1968 IAAAF-NT-79-20; ISBN-2-7 170-0547-il Avail: NTIS a considerable library of standard programs have been produced. HC A03/MF AOl: CEDOCAR, Paris FF 17 (France and EEC) This program library covers all types of testing commonly carried FF 21 (others) out in the wind tunnel. However there remains the possibility of Dynamic stall of rotors in forward flight is studied in terms unusual tests being required which are not covered by existing of the limiting on helicopter performance. Manifestations of the programs. This memorandum describes modifications to the Digital phenomena depend on the characteristics of the rotors and on Equipment Corporation FOCAL language (FOCAL is a keyboard operating conditions. The lift of the rotor, forward velocity, engine oriented interpretive language similar to BASIC) which permit speed, and the interaction of vortices with the blade surface all the tunnel instrumentation, display and plotter to be operated contribute to the development of stall. Experiments demonstrating by FOCAL programs. Using this extended FOCAL language it the unsteady nature of the phenomena are reported. Simulation should be possible to rapidly write and de-bug programs to of dynamic stall phenomena on an oscillating model shows that meet unusual requirements not covered by the standard program the delay in unsteady stalling is associated with the development library. GRA of a system of vortices along the leading edge. A two dimensional analysis is used in modeling dynamic stall. Author )ESA) N80-18103# Lockheed-California Co., Burbank. ADVANCED. COMPOSITE AILERON FOR 1-1011 TRANS- N80-18051# Yang (Nai C.) 3nd Associates, New York, N.Y. PORT AIRCRAFT Quarterly Technical Report, 22 Dec. NONDESTRUCTIVE EVALUATION OF AIRPORT PAVE- 1973 - 24 Mar, 1978 MENTS. VOLUME 1: PROGRAM REFERENCES 14 Apr. 1978 54 p ref Nai C. Yang Sep 1979 173 p (Contract NAS1-15069l (Contract DOT.FA77WA.3964l (NASA-CR-162863; LR-28559: DLR-003; QTR-2l Avail: NTIS IAD.A078835: FAA-RD-78-1 54-11 Avail: NTIS HC A04/MF AOl CSCL 110 HC A08/MF AOl CSCL 13/2 Design and evaluation of alternate concepts for the major The concept of nondestructive evaluation and functional subcomponents of the advanced composite aileron (ACA) was pavement design was integrated into a computer program which completed. From this array of subcomponents, aileron assemblies is described. The program logic and operational procedures used were formulated and evaluated. Based on these analyses a multirib in the computer program are outlined as follows. The nondestruc- assembly with graphite tape/syntactic core covers, a graphite tive test INDTI is used as a substitute for the plate load test tape front spar, and a graphite fabric rib was selected for without interference to airport operation. The evaluation and design development. A weight savings of 29.1 percent 140.8 pounds segment evaluates the strength by cumulative stress damage per aileron) is predicted. Engineering cost analyses indicate that and progressive surface deformation. The final program output the production cost of the ACA will be 7.3 percent less than is the cost information for ten design alternatives of equal the current aluminum aileron. Fabrication, machining, and testing functional performance. The validation program makes the of the material evaluation specimens for the resin screening correlations between the NDT data and subgrage geology, regional program was completed. The test results lead to the selection climate, airport operation, existing pavements, and response of of Narmco 5208 resin for the ACA. Other activities completed airport bridges. A.W.H. include: the detailed design of the ACA, construction of a three dimensional finite element model for structural analysis, and formulation of detail plans for material verification and process N80-18052# Permali, Inc., Mount Pleasant, Pa. R.E.S. DEVELOPMENT AND TEST OF LOW-IMPACT RESISTANT development. TOWERS Final Report Eugene T Rogers, Jonathan A. Ross, and Kenneth M. Snyder N80-181 04*# Lockheed-California Co., Burbank. Aug. 1979 76 p ADVANCED MANUFACTURING DEVELOPMENT OF A Contract DOT-FA78WA-41 521 COMPOSITE EMPENNAGE COMPONENT FOR 1-1011 (AD-A077160, W79005: FAA-AF-79-1) Avail: NTIS AIRCRAFT Quarterly Technical Report, 1 Jan. 1978-31 Mar. HC A05/MF AOl CSCL 01/5 1978 A break-away fiberglass mast for use in low impact resistant 14 Apr. 1978 130 p I LI RI structures to support airport approach lighting systems (Contract NAS1 -140001 was developed. This design will withstand 100 mph winds )NASA-CR- 162862; LR-28573; DLR .003; QTR-9l Avail: NTIS (including gusts) without ice and 75 mph winds (including gusts) HC A07/MF AOl CSCL 11 with a 1/2 inch radial ice load. Yet, when struck by a light Tooling concepts were developed which would permit airplane wind, it breaks into pieces without catastrophic damage co-couring of the hat stiffeners to the skin to form the cover to thewing. It was observed that impact energy needed to assembly in a single autoclave cycle. These tooling concepts break the mast was in the order of 679 toot-pounds and that include the use of solid rubber mandrels, foam mandrels, and peak forces were in the order of 5,656 lbs. J.M.S. formed elastometric bladders. A simplification of the root end design of the cover hat stiffeners was accomplished in order to N80-18053# Aeronautical Research Labs.. Melbourne (Australia). facilitate fabrication. The conversion of the 3D NASTRAN model COMPUTER SYNTHESIS' OF FLIGHT SIMULATION VISU- from level 15 to level 16 was completed and a successful check ALS run accomplished. A detailed analysis of the thermal load John Sandor Feb. 1979 36 p refs requirement for the environmental chambers was carried out. )ARL/SYS. Note-6 1: AR-001 -5931 Avail: NTIS Based on the thermal analysis, best function requirements, load HC A03/MF AOl inputs and ease of access. a system involving four chambers, The principles of computer synthesis of external world visuals two for the covers containing 6 and 4 specimens, respectively, for faster display are reviewed. The areas of environment and two for the spares containing 6 and 4 specimens. respectively, description, edge and polygon clipping, hidden surface removal, evolved. R.E.S.
226 N80-18162
N80-1 81 06*# National Aeronautics and Space Administration. William E. Reed Dec. 1979 262 p Supersedes NTIS/PS.78/ Lewis Research Center. Cleveland, Ohio. 1051: NTI5/P5-77/0845; NTIS/ PS-76/0686: NTIS/P5.75/ APPLICATION OF COMPOSITE MATERIALS TO TURBOFAN 614: COM-74-11527 ENGINE FAN EXIT GUIDE VANES )PB80-802374: NTIS/PS-78/ 1051: NTIS/PS.77/0845: G. T. Smith 1980 19 p refs Presented at 35th Ann. Conf. NTIS/PS-76/0686: NTI5/PS-75/6 14: COM-74- 11527) Avail: of the Reinforced Plastics/ Composite Inst., New Orleans, 4-8 Feb. NTIS HC $30.00/MF $30.00 CSCL 118 1980: sponsored by Soc. of Plastics Industries Carbon and graphite composites are studied. Topics include (NASA-TM-81432; E-356) Avail: NTIS NC A02/MF AOl CSCL nonfiber carbon reinforcement, carbon or graphite matrix 110 composites, applications, properties, fabrication, and structural A program was conducted by NASA with the JT9D engine analysis. The majority of research concerns aircraft components manufacturer to develop a lightweight, cost effective, composite and ablative materials for rockets. This updated bibliography material fan exit guide vane design having satisfactory structural contains 262 abstracts. 48 of which are new entries to the durability for commerical engine use. Based on the results of a previous edition. GRA previous company supported program, eight graphite/epoxy and graphite 'glass/epoxy guide vane designs were evaluated and four were selected for fabrication and testing. Two commercial N80-18145# National Technical Information Service, Springfield, fabricators each fabricated 13 vanes. Fatigue tests were used Va. to qualify the selected design configurations under nominally CARBON AND GRAPHITE. PART 1: CARBON AND dry. 38 C (100 F) and fully wet and 60 C (140 F) environmental GRAPHITE FIBERS AND FIBER COMPOSITES, VOLUME conditions. Cost estimates for a production rate of 1000 vanes 4. A BIBLIOGRAPHY WITH ABSTRACTS Progress Report, per month ranged from 1.7 to 2.6 times the cost of an all Sep. 1977 - Oct. 1979 aluminum vane. This cost is 50 to 80 percent less than the William E. Reed Dec. 1979 249 p Supersedes NTIS/PS-78/ initial program target cost ratio which was 3 times the cost of 1050: NTIS/PS-77/0844: NTI5/ PS-76/0685: NTIS/PS-75/ an aluminum vane. Application to the JT9O commercial engine 613: COM-74-11527 is projected to provide a weight savings of 236 N (53 lb) per (P880-802366: NTIS/PS . 78/ 1050: NTI S/ PS-77/0844: engine. Author NTIS/ PS-76/O685: NTIS/ PS-75/613: COM . 74- 11527) Avail: NTIS HC $30.00/MF $30.00 CSCL 11B N8O18109*# National Aeronautics and Space Administration. Citations cover reinforcement of numerous polymers and Langley Research Center, Langley Station, Va. metals by carbon and graphite fibers. Topics include processing, THE POTENTIAL FOR DAMAGE FROM THE ACCIDENTAL design, properties, stress analysis, and performance of the RELEASE OF CONDUCTIVE CARBON FIBERS FROM composite structures or parts. Composites from polyimide, epoxy, BURNING COMPOSITES and aluminum matrices are among the types cited. Fabrication Vernon L. Bell Apr. 1980 23 p refs Proposed for presentation and testing of materials for rocket nozzles, reentry vehicles, aircraft at the AGARD Structures and Materials Panel Specialist's Meeting components, automobiles, and ships are included. This updated of Effect of Service Environment on Composite Materials, Athens, bibliography contains 241 abstracts, 100 of which are new entries Greece, 16 Apr. 1980 to the previous edition. GRA (NASA-TM-80213) Avail: NTIS HC A02/MF AOl CSCL 11 The potential damage to electrical equipment caused by the N80- i8161# Lockheed Missiles and Space Co.. Palo Alto, Calif. release of carbon fibers from burning commercial airliners is ADVANCED ALUMINUM ALLOYS FROM RAPIDLY SOLIDI- assessed in terms of annual expected costs and maximum losses FIED POWERS Research and Development Status Report, at low probabilities of occurrence. A materials research program 5 Mar. - 4 Jun. 1979 to provide alternate or modified composite materials for aircraft A. E. Lewis Jun. 1979 23 p refs structures is reviewed. K. L. (Contract F33615-78-C'5203: DARPA Order 3575) (AD-A077197 - LMSC'D677934) Avail: NTIS NC A02/MF AOl CSCL 11/6 N8018109*# National Aeronautics and Space Administration. Advanced aluminum alloys are to be developed that will Langley Research Center, Langley Station, Va. provide major payoffs for important new aircraft, spacecraft, and COMPOSITE COMPONENTS ON COMMERCIAL AIR- missile systems in the next decade. Payoffs will result from CRAFT weight savings of structural components which, in turn, lead to H. Benson Dexter Mar. 1980 24 p refs To be presented at increased range, payload, service life, and decreased life-cycle the AGARD Specialist Meeting on Effect of Service Environ, on cost. Recently conducted feasibility and design tradeoff studies Composite Mater., Athens, 13-18 Apr. 1980 provide a basis for selecting certain property goals for improved (NASA-TM-80231( Avail: NTIS HC A02/MF AOl CSCL 11 aluminum alloys that will result in significant weight savings. Commercial aircraft manufacturers are making production GRA commitments to composite structure for future aircraft and modifications to Current production aircraft. Flight service programs N80-18162# Lockheed Missiles and Space Co.. Palo Alto, Calif. with advanced composites sponsored by NASA during the past Research Lab. 10 years are described. Approximately 2.5 million total corn- DEVELOPMENT OF ADVANCED ALUMINUM ALLOYS posits component flight hours have been accumulated since 1970 FROM RAPIDLY SOLIDIFIED POWDERS FOR AEROSPACE on both commercial transports and helicopters. Design concepts STRUCTURAL APPLICATIONS Interim Technical Report, with significant mass savings were developed, appropriate 5 Mar. - 4 Sep. 1979 inspection and maintenance procedures were established, and R. E. Lewis Sep. 1979 137 p refs satisfactory service was achieved for the various composite (Contract F33615-78-C-5203: ARPA Order 3575) components. A major NASA/U.S. industry technology program )AD-A077800: LM5C-D678772) Avail: NTIS to reduce 'fuel consumption of commercial transport aircraft HC A07/MF AOl CSCL 11/6 through the use of advanced composites was undertaken. Ground Advanced aluminum alloys are being developed that will and flight environmental effects on the composite materials provide major payoffs in terms of weight savings for new aerospace used in the flight service programs supplement the flight service structures. The two property goals are: (1) a 30-percent increase evaluation. A,R.H. in modulus of elasticity-to-density ratio. and (2) a 20-percent increase in modulus of elasticity -to'density ratio plus a 20-percent N80'18144# National Technical Information Service, Springfield, increase in strength -to-density ratio, when compared to Va. Al 7075 . T76 and without a significant loss in other properties CARBON AND GRAPHITE. PART 2. CARBON AND important for structural applications. The program is organized GRAPHITE COMPOSITES - EXCLUDING CARBON FIBER into three phases: (1) a fundamental alloy and process develop- COMPOSITES. A BIBLIOGRAPHY WITH ABSTRACTS ment study: (2) scale-up of two best alloys and evaluation of Progress Report. 1964 - Oct. 1979 mill product forms: (3) design evaluation involving selected
227 N80-18205 redesign of aerospace components. analysis of payoffs, and P. Wayne Whaley and Michael W. Obal In Shock and Vibration recommendations for manufacturing technology development. Inform. Center The Shock and Vibration Bull., Pt. 4 Set). 1978 Phase 1 activity, to be completed in he first two years, is p 83-93 refs organized into four Tasks: (1) development of advanced aluminum Avail: NRL, Tech. Inform. Div., Washington. D.C. alloys containing lithium: (2) development of advanced aluminum Six angular vibration sensors are evaluated in light of the alloys that do not contain lithium; (3) quantitative microstructural requirements for measuring angular vibrations of aircraft Structures analyses and mechanical property correlations; (4) study of in order to describe optical package disturbances. In addition, aerospace structural applications for advanced aluminum alloys experience with differential angular vibration measurement using including development and application of a method for predicting conventional accelerometers is presented and evaluated. These weight savings. Phase 1 activity is described below; Phases 2 results indicate a strong need to develop a good, reliable, miniature and 3 have not been initiated. GRA angular vibration sensor for airborne measurements. K. L.
N8018205*// National Aeronautics and Space Administration. N80-18229 McDonnell-Douglas Astronautics Co.. St. Louis, Mo. Lewis Research Center, Cleveland, Ohio. TURBULENT-BOUNDARY-LAYER EXCITATION AND INITIAL CHARACTERIZATION OF AN EXPERIMENTAL RESPONSE THERETO FOR A HIGH-PERFORMANCE REFEREE BROADENED-SPECIFICATION (ERBS) AVIATION CONICAL VEHICLE TURBINE FUEL C. M. Ailman In Shock and Vibration Inform. Center The George M. Prok and Gary T. Seng Jan. 1980 10 p refs Shock and Vibration Bull., Pt. 4 Sep. 1978 p 159-169 refs (NASA-TM-81440, E-206) Avail: NTIS HC A02/MF AOl CSCL 21D Avail: NAL, Tech. Inform. Div., Washington, D.C. Characterization data and a hydrocarbon compositional A compiled data bank for describing the fluctuating pressures analysis are presented for a research test fuel designated as an that force the shell of a non-maneuvering reentry vehicle to experimental referee broadened-specification aviation turbine fuel. vibrate during reentry is presented, the use of local aerodynamic This research fuel, which is a special blend of kerosene and parameter values for the cone when predicting these pressures hydrotreated catalytic gas oil, is a hypothetical representation of is discussed, and the characteristics of shell-mode vibration a future fuel should it become necessary to broaden Current peculiar to a conical structure with a multilayered skin are kerojet specifications. It is used as a reference fuel in research described. Flight data are reported for such a structure maneuver- investigations into the effects of fuel property variations on the ing as a result of flow disturbance at the aft end. The data performance and durability of jet aircraft components, including suggest some angle of attack dependencies not previously combustors and fuel systems. J.M.S. detected, and indicate low frequency response of the vehicle as a beam. The beam response is analytically examined as to its N80-18206# Southwest Research Inst., San Antonio, Tex. Army probable cause. K. L. Fuels and Lubricants Research Labs. EVALUATION OF JP-5 TURBINE FUEL IN THE SINGLE N80-18259# Institute for Telecommrinication Sciences, Boulder, CYLINDER CUE 1790 DIESEL ENGINE Final Report. Jun. - Cob. Nov. 1979 COMPARISON OF MEASURED DATA WITH IF-77 PROPA- Richard B. Moon Nov. 1979 42 p refs GATION MODEL PREDICTIONS Final Report (Contract DAAK70-79-C-0060) M. E. Johnson and G. D. Gierhart Aug. 1979 443 p refs (AD-A078666: AFLRL-1 19) Avail: NTIS HC A03/MF AOl (Contracts DOT-FA78WAI'840; DOT-FA68WAI-145( CSCL 21/4 )AD-A076508; FAA-RD-79-9( Avail: NTIS HC A19/MF AOl _1!i ..p_ .!ormance test compared fuel consumption and CSCL 20/14 horsepower of the CUE 1970 when operating on JP-5 turbine Measured propagation data were compared with predictions fuel in place of diesel fuel while the endurance test compared made by the IF-77 (ITS-FAA-77) and other propagation models. engine wear and deposits when operating the CUE 1790 on Although IF-77 was developed for aeronautical applications, it JP-5 instead of diesel fuel. The performance test indicated no can be used for some point-to-point propagation paths, and the change in power and a 3 + or - 1 percent increase in fuel measured data selected for comparison includes point-to-point consumption. The endurance test indicated no change to slightly as well as aeronautical paths. Approximately 870.000 hours of less wear, less deposits, no change in the oil consumption rate, data are associated with the 242 paths used. Predictions made and nothing unusual or excessive in the used oil analyses. Analysis with IF-77 were always best or second best and were substan- of the JP-5 indicated a cetane number within diesel fuel tially better than those made for free space conditions. The specifications. Although further tests are necessary to define the IF-77 model has a wide range of application and provides effect of random variables on the test results, from this test it predictions compatible with the more specialized models tested. can be concluded that the use of JP-5 in the CUE 1790 resulted The aeronautical propagation data pool from which the data in no appreciable loss in performance or service life. As a result. were selected is an appendix. A.R.H. JP-5 is considered to be a satisfactory alternative fuel for use in the AVDS 1790-2C diesel engine. GRA N80- 1 8300*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. N80-18221 Boeing Aerospace Co., Seattle, Wash. LIQUID METAL SLIP RING Patent Application INCANDESCENT LAMP LIFE UNDER RANDOM VIBRA- Frank D. Berkopec, Robert R. Lovell, and David H. Culp, inventors TION (to NASA) Filed 21 Dec. 1979 11 p Clark J. Beck, Jr. In Shock and Vibration Inform. Center The refs (NASA-Case-LEW- 12277-3: US-Patent-Appl-SN- 106190) Avail: Shock and Vibration Bull.. Pt. 4 Sep. 1978 p 71-81 NTIS HC A02/MF AOl CSCL 09A Avail: NRL, Tech. Inform. Div.. Washington, D.C. The liquid metal slip ring described comprises a rotor in the Several sets of incandescent lamps were subjected to form of a range about an axis and a stator, the rotor being random vibration in order to generate a curve of lamp life rotatable relative to the stator. The rotor has a channel in which versus vibration level. The vibration levels were varied from the liquid metal is retained during operation by surface tension. 0.02 G sq/Hz to 1.6 G sq/Hz. Each set of lamps was vibrated The stator comprises a brush or probe which is partially until all lamps failed or for a maximum time of 2-1/2 hours. immersed in the metal in the channel and is bidirectionally The tests were conducted with lamps energized and not energized. symmmetrical so that whichever direction the rotor turns the The test results show that average operational life of a lamp probe presents the same physical resistance and affords the under random vibration differs significantly from lamp rated life. same electrical conductivity as a connection between the probe M.M.M. and the rotor. Author
N80-18222 Air Force Flight Dynamics Lab.. Wright-Patterson AFB, Ohio. N80-18311# Air Force Aero Propulsion Lab., Wright-Patterson ANGULAR VIBRATION MEASUREMENT TECHNIQUES AFB, Ohio.
228 N80-18395
PERMANENT MAGNET AND SUPERCONDUCTING orifice of the system to be tested. 0-rings ensure seating and a GENERATORS IN AIRBORNE. HIGH POWER SYSTEMS vacuum seal between the chambered end of the module and Interim Report, 1 Feb. 1978 - 31 Mar. 1979 the surface around the orifice: one 0-ring separates the outer Hugh L. Southall and Frederick C. Brockhurst Aug. 1979 99 p chamber from the outside environment. Ports lead from each of refs the chambers Out the other end of the module to tubes connected (AF Proj. 3145) to a control box consisting of calibration pressure and vacuum (AD-A078424; AFAPL-TR-79-2073) Avail: NTIS supply lines, bleeder valves, and gauges. HC A05/MF AOl CSCL 10/2 Official Gazette of the U.S. Patent and Trademark Office This report presents results of a study performed to compare airborne, high power supplies at power levels of 10 and 20 MW utilizing permanent magnet and superconducting generators. N80-183645 # National Aeronautics and Space Administration. Algorithms for the weight and volume of these electrical generators Pasadena Office, Calif. are presented and algorithms for the other power supply FREQUENCY-SCANNING PARTICLE SIZE SPECTROMETER components are used to predict total system weights for seven Patent Application point designs at the two power levels. GRA Alain L. Fymat, inventor (to NASA) (JPL( Filed 10 Aug. 1979 21 p (Contract NAS7-10011 N80-18327 Illinois Inst. of Tech.. Chicago. (NASA-Case-NPO- 13606-2; US-Patent-Appl-SN-065676( Avail: HEAT, MASS AND MOMENTUM TRANSFER THROUGH NTIS HC A02/MF AOl CSCL 146 SPRAYS Ph.D. Thesis A particle size spectrometer having a fixed field of view Mohan L. Jain 1979 293 p within the forward light scattering cone at an angle theta sub s Avail: Univ. Microfilms Order No. 8003649 between approximately 100 and 200 minutes of arc (preferably An experimental facility consisting of a subsonic wind tunnel, at 150 minutes), a spectral range extending approximately from a spray generation system and instrumentation was designed 0.2 to 4.0 inverse micrometers, and a spectral resolution between and constructed. A numerical-photographic procedure was about 0.1 and 0.2 inverse micrometers (preferably toward the developed for analyzing drop trajectories to imply drop drag lower end of this range of spectral resolution), is employed to coefficients. Experiments were conducted over a Reynolds number determine the distribution of particle sizes, independently of the range of 1000-3500, and it was found that the drops in the chemical composition of the particles, from measurements of sprays of the present type experience up to 18% higher drag incident light, at each frequency. sigma (= 1/lambda), and than single drops. Thermal experiments to determine average scattered light, l(sigma(. NASA heat and mass transfer through sprays were conducted over a Reynolds number range of 1000-2500 for three different spray N80- 1 8368*# configurations involving two volume fractions. It is shown that National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. the widely used Ranz-Marshall correlations for single drops give too high a prediction for heat and mass transfer in the present FIBER OPTIC SENSORS FOR MEASURING ANGULAR system. Only 36-67% of the calculated transport actually occurred POSITION AND ROTATIONAL SPEED Robert J. Baumbick Mar. 1980 13 p over the Reynolds number range studied. Dissent. Abstr. (NASA-TM-81454; E-381( Avail: NTIS HC A02/MF AOl CSCL •20F N80-18343# McDonnell-Douglas Research Labs., St. Louis, Mo. Two optical sensors, a 360 deg rotary encoder and a VISCOUS FLOWFIELDS INDUCED BY TWO- AND THREE- tachometer, were built for operation with the light source and, DIMENSIONAL LIFT JETS IN GROUND EFFECT Final detectors located remotely from the sensors. The source and Technical Report, 1 Feb. 1976 - 28 Feb. 1979 detectors were coupled to the passive sensing heads through W. W. Bower, R. K. Agarwal, G. R. Peters, and D. A. Kotansky 3.65 meter fiber optic cables. The rotary encoder and tachometer 1 Mar. 1979 38 p refs were subjected to limited environmental testing. They were (Contract N00014-76-C-0494; NR Proj. 215-246: installed on an air breathing engine during recent altitude tests. RRO141 184) Over 100 hours of engine operation were accumulated without (AD-A078782; ONR-CR-21 5-246-3F( Avail: NTIS any failure of either device. K. L. HC A03/MF AOl CSCL 20/4 An important consideration for VTOL aircraft design is the aerodynamic interaction between airframe undersurfaces and the ground. In an effort to predict this phenomenon, a second-order- N80-18369// Aeronautical Research Labs.. Melbourne (Australia). accurate, finite-difference scheme for solution of the two- and SPECIFICATION FOR THE INSTALLATION OF ELECTRICAL three-dimensional conservation equations of fluid mechanics, in RESISTANCE STRAIN GAUGES ON STRAIN PAIRS combination with a turbulence model, is described. The solution COUNTER AIRCRAFT technique is applied to a planar lift jet in ground effect for both S. W. Gee Mar. 1979 13 p incompressible and compressible flow and to two interacting (AD-A071363; ARL/Struc-TM-301 ( Avail: NTIS incompressible jets with fountain formation. Fluid properties that HC A02/MF AOl CSCL 14/2 characterize the jet impingement flowfields are given for a range A number of RAAF aircraft are to be Strain gauged as part of Reynolds numbers, and comparisons with measured data are of a program designed to monitor the in-flight fatigue damage presented. GRA accumulated by service aircraft during normal squadron usage. Flight strains are to be measured by gauges, strategically placed on the structure and monitored by strain pairs counters. The N80-18358 National Aeronautics and Space Administration. Langley Research Center, Langley Station, Va. materials and methods of application recommended in this memo, STATIC PRESSURE ORIFICE SYSTEM TESTING METHOD have been successfully used for flight trials over Several years AND APPARATUS Patent and have proved very reliable. Any deviations from the suggested Randolph F. Culotta and Donald L. Posey, inventors (to NASA) methods should be thoroughly checked before use on the aircraft. GRA Issued 8 Jan. 1980 7 p Filed 17 Aug. 1978 Supersedes N78-33123 116 - 24. 3179) (NASA-Case-LAR-12269-1, US-Patent-4,182,1 58. N80- 18395 Tennessee Technological Univ., Cookeville. US-Patent-Appl-SN-934576: US-Patent-Class-73-40: IDENTIFICATION OF NOISE SOURCES IN FC CENTRI- U S-Patent-Class-73-4R( Avail: U.S. Patent and Trademark FUGAL FAN ROTORS Ph.D. Thesis Office CSCL 146 David Raj 1978 263 p A method and apparatus are presented for pressure testing Avail: Univ. Microfilms Order No. 8004108 the static pressure orifices and associated connections used in The sources of broad band noise in forward curved centrifu- wind tunnels. A cylindrical module, having in one end an open gal fan rotors were studied using a 10.6 inch diameter fan. The hemispherical calibration pressure chamber separated from and flow field inside the fan was observed using flow visualization surrounded by an annular vacuum chamber is placed over the techniques. The velocity and velocity fluctuations of the rotor
229 N80-18400 exit flows were measured using a hot-wire anemometer. The Both gas and liquid seals are considered. Areas studied include blade-to-blade variation of the absolute velocity, both magnitude polymers, physical properties, glass metal seals, configurations. and direction, and the high level of velocity fluctuations made it test methods, and design. Applications involve such areas as necessary to develop a special sampling system for the velocity gas turbines, water pumps, shaft seals, spacecraft seals, and measurements. This system was successfully used to measure other specialized seals and gaskets. Highway joint seals are the rotor exit velocity levels. The separated flow over the blade excluded. This updated bibliography contains 21 3 abstracts. suction surface was the major broad band noise source. The 74 of which are new entries to the previous edition. GRA presence of circumferential and axial gradients in the mean flow also contributed to the problem. The rotor blades must be N80-18419# Arinc Research Corp.. Annapolis, Md. redesigned to eliminate the flow separation over the suction THE APPLICATION OF RELIABILITY IMPROVEMENT surfaces. Dissert. Abstr. WARRANTY TO DYNAMIC SYSTEMS Final Report, 26 Sep. 1978 - 4 Sep. 1919 National Aeronautics and Space Administration. A. A. Bilodeau, F. B. Crum, W. A. Dunphy, and A. A. Kowalski N80-18400t # 4 Sep. 1979 162 p Lewis Research Center, Cleveland, Ohio. GAS PATH SEAL Patent Application (Contract DAAK70-78-C-0200) Robert C. Bill and Robert D. Johnson. inventors (to NASA) Filed (AD-A075520; Rept-1 736-01-1-2025; MERADCOM-TQ-1) Avail: NTIS HC A08/MF AOl CSCL 14/4 20 Nov. 1979 8 p )NASA-Case-NPO- 12131-3; US-Patent-Appl-SN-096255) Avail: The Reliability Improvement Warranty (RIW) is currently used within the Department of Defense to provide an incentive to NTIS HC A02/MF AOl CSCL 20A A gas path seal suitable for use with a turbine engine or contractors to design and produce equipment that will have a compressor is described. A shroud wearable or abradable by low failure rate, as well as low costs of repair following failure in field or operational use. Current applications of RIW have the abrasion of the rotor blades of the turbine or compressor shrouds the rotor bades. A compliant backing surrounds the generally been restricted to initial production procurements of shroud. The backing is a yieldingly deformable porous material relatively small, transportable avionics equipment. The RIW covered with a thin ductile layer. A mounting fixture surrounds concept has potential applications for dynamic systems (e.g.. NASA transmissions, gearboxes, engines, etc.) procured by the U.S. the backing. Army Mobility Equipment Research and Development Command (ME R AD CO M). However, dynamic systems may differ from avionics in design and maintenance concepts, transportability N80- 1 8402*# National Aeronautics and Space Administration. features, and deployment and utilization philosophy. Therefore, Langley Research Center, Langley Station. Va. current criteria for using RIW and current guidelines for developing IMPROVED TIRE/WHEEL CONCEPT - Patent Application RIW terms and conditions should be reviewed and adapted for Philip M. Harper. Sr.. inventor )to NASA) (Boeing Commercial this new class of systems. This effort identified several differences Airplane Co.. Seattle, Wash.) Filed 12 Dec. 1979 12 p between the characteristics of dynamic systems and those of Sponsored by NASA RIW avionics equipment that are not emphasized in current RIW (NASA-Case- LAR- 11695-2; US-Patent-Appl-SN- 103836) Avail: guidelines. RIW application criteria for dynamic systems were NTIS HC A02/MF AOl CSCL 01C also developed. An existing life-cycle cost (LCC) model was A tire and wheel assembly is described which consists of a modified to address quantitative features of dynamic systems low profile pneumatic tire with sidewalls that deflect inwardly that should be considered in an economic analysis of RIW versus under a load and a wheel having a narrow central channel and organic maintenance Case studies were developed to demonstrate' extended rim flanges. The extended rim flanges support the tire the use of the RIW selection criteria and the LCC model. GRA sidewalls under static and dynamic loading conditions to produce a combination particularly suited to aircraft applications. NASA N80-18438# Laboratorium fuer Betriebsfestigkeit. Darmstadt (West Germany). MINITWIST: A SHORTENED VERSION OF TWIST N80- 1 84O4// National Aeronautics and Space Administration. H. Lowak, J. B. DeJonge, J. Franz, and D. Schuetz 1979 25 p Lewis Research Center, Cleveland, Ohio. refs In GREEK EVALUATION OF A HIGH PERFORMANCE FIXED-RATIO )LBF-TB-146) Avail: NTIS HC A02/MF AOl TRACTION DRIVE A description of the shortened version of the transport Stuart H. Loewenthal, Neil E. Anderson, and Douglas A. Rohn wing standard load program (TWIST), called MINITWIST, is 1980 32 p refs Proposed for presentation at 3d Intern. presented. In all cases where testing time is a prohibitive factor Power Transmission and Gearing Conf., San Francisco, Calif.. to use TWIST, it is proposed to use this shortened program 18-22 Aug. '1980; sponsored by Am. Soc. of Mech. Engr. The user of this shortened program should be aware though (NASA-TM-81425: E-349( Avail: NTIS HC A03/MF AOl CSCL that in most cases the load cycles with high frequency and low 131 amplitude omitted in MINITWIST would contribute to damage. The results of a test program to evaluate a compact, high thus the results will overestimate the fatigue life. R.E,S. performance, fixed ratio traction drive are presented. This transmission, the Nasvytis Multiroller Traction Drive, is a fixed ratio, single stage planetary with two rows of stepped planet N80-18449# Aeronautical Research Labs., Melbourne (Australia(. rollers. Two versions of the drive were parametrically tested A REVIEW OF AUSTRALIAN INVESTIGATIONS ON back-to-back at speeds to 73.000 rpm and power levels to AERONAUTICAL FATIGUE DURING THE PERIOD APRIL 180 kW (240 hp(. Parametric tests were also conducted with 1977 TO MARCH 1979 the Nasvytis drive retrofitted to an automotive gas turbine engine. G. S. Jost Apr. 1979 68 p refs The drives exhibited good performance, with a nominal peak (AD-A071641; ARL/Struc.TM-303( Avail: NTIS efficiency of 94 to 96 percent and a maximum speed loss due HC A04/MF AOl CSCL 01/3 to creep of approximately 3.5 percent. Author A summary is presented of the aircraft fatigue research and associated activities which form part of the programs of the Aeronautical Research Laboratories. Commonwealth Aircraft N80-18417# National Technical Information Service, Springfield, Corporation Pty. Ltd.. Department of Transport (Airworthiness Va. Branch), Royal Australian Air Force and the Government Aircraft SEALS AND GASKETS. A BIBLIOGRAPHY WITH AB- Factories. The major topics discussed include the fatigue of STRACTS Progress Report, Nov. 1976 - Nov. 1979 both civil and military aircraft structures, fatigue of materials William E. Reed Dec. 1979 125 p Supersedes NTIS/PS-78/ and components and fatigue life monitoring and assessment. 1251; NTIS/PS-77/ 1093; NTIS/PS-76/0938; NTIS/ PS-75/ G RA 838; NTIS/PS-75/140 (PB80-80201 0; NTIS/PS-78/ 1251; NTIS/ PS-77/1093: N80-18450# Army Research and Technology Labs.. Fort Eustis. NTIS/PS-76/0938; NTIS/PS-75/838; NTIS/PS-75/1401I Avail: Va. NTIS HC $30.00/MF $30.00 CSCL 11A HLH ROTOR BOX BEAM FATIQUE TEST
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M. Hanson Sep. 1979 21 p refs PUBLICATIONS IN ACOUSTIC AND NOISE CONTROL (DA Proj. 11-1-62209-AH-76) FROM NASA LANGLEY RESEARCH CENTER DURING (AD-A076931. USARTL-TN-35) Avail: NTIS 1940-1979 NC A02/MF AOl CSCL 20/11 Barbara A. Fryer. comp. Jan. 1980 104 p refs Update The purpose of this program was to evaluate the fatigue (NASA-TM-80211) Avail: NTIS NC A06/MF AOl CSCL properties of a fiberglass/ epoxy box beam specimen which was 20A similar in design to the Heavy Lift Helicopters (HLH) rotor blade Reference lists of approximately 900 published Langley spar. The fiberglass/ epoxy box beam was designed and fabri- Research Center reports in various areas of acoustics and noise cated by Boeing Vertol using a ply layup scheme similar to the control for the period 1940-1979 are presented. Specific topic rotor H LH blade spar but with a different preimpregnated fiberglass areas covered include: duct acoustics; propagation and operations; tape. The box beam was tested at a fatigue load level sufficient rotating blade noise; jet noise; sonic boom; flow surface interaction to cause failure within a reasonable number of fatigue cycles noise; structural response/ interior noise; human response; and (5 x 1000.000) to determine fatigue strength and observe failure noise prediction. J.M.S. modes and rates. Premature fatigue failure occurred in the box beam as the result of chordwise wrinkles occurring during fabrication. The Integral Spar Inspection System (ISIS). which depends on a pressure differential between the sealed spar and outside ambient pressure to detect leaks resulting from cracks or flaws, indicated that a leakage had occurred at approximately N80. 18985*# National Aeronautics and Space Administration. the same time the failure was observed. It was concluded that Ames Research Center, Moffett Field, Calif. the ISIS appeared to be a viable technique for signaling a structural AMES RESEARCH CENTER PUBLICATIONS: A CONTINU- failure of fiberglass spars. The presence of the wrinkles in the ING BIBLIOGRAPHY, 1978 spar which resulted in premature failure, however, precluded any Feb. 1980 139 p conclusions with regard to the fatigue strength of the preim (NASA-TM-81 175; A-8079) Avail: NTIS NC A07 CSCL 05B pregnated fiberglass tape used. GRA This bibliography lists formal NASA publications, journal articles, books, chapters of books, patents and contractor reports N80-18587// Air Force Engineering and Services Center, Tyndall issued by Ames Research Center which were indexed by Scientific and Technical Aerospace Abstracts, Limited Scientific and AFB, Fla. Engineering and Services Lab. CONTROL OF PARTICULATE EMISSIONS FROM TURBINE Technical Aerospace Abstracts, and International Aerospace ENGINE TEST CELLS BY COOLING WATER INJECTION Abstracts in 1978. Citations are arranged by directorate, type Final Report. Feb. - May 1979 of publication and NASA accession numbers. Subject, personal author, corporate source, contract number, and report/ accession Michael G. MacNaughton, James J. Tarquinio. and Joseph A. number indexes are provided. Author Martone Jul. 1979 77 p (AF Proj. 1900) (AD-A075947; AFESC/ESL/TR-79- 19) Avail: NTIS HC A05/MF AOl CSCL 13/2 The operation of DOD turbine engine test cells in California has been criticized by the State environmental regulatory agencies because smoke generated by some engines results in excessive N8O18988*# National Aeronautics and Space Administration. opacity (visibility) of the test cell exhaust plume. Since the plume Langley Research Center, Langley Station, Va. exceeds visibility standards for only a relatively small proportion COMPUTER PROGRAMS FOR ESTIMATING CIVIL AIR- of engines tested a low cost control technique which brings the CRAFT ECONOMICS test cell into compliance with opacity standards is required. Dal V. Maddalon. John K. Molloy. and Milton J. Neubawer Jan. This study was initiated to verify that, in addition to forming a 1980 51 p refs steam plume, water used to cool the test cell walls also removes (NASA-TM-80196( Avail: NTIS HC A04/MF AOl CSCL engine generated particulates and substantiates this procedure 05C as a legitimate pollution control technique. It can be concluded Computer programs for calculating airline direct operating from this study that water injection as practiced at McClellan cost, indirect operating cost, and return on investment were AFB test cell results in significant (approx. 50% by weight) control developed to provide a means for determining commercial aircraft of turbine engine particulate emissions. It is postulated that the life cycle cost and economic performance. A representative wide process could be made more efficient by the use of better designed body subsonic jet aircraft was evaluated to illustrate use of the spray nozzles which would increase water droplet particle contact programs. K. L. and inclusion of a demister to increase water removal from the exhaust. GRA
N80-18624# Photometrics. Inc.. Lexington, Mass. AIRCRAFT PROGRAM FOR TARGET BACKGROUND, AND SKY RADIANCE MEASUREMENTS Randall B. Sluder, W. Scott Andrus. and Irving L. Kofsky 15 Jun N8O19022*# National Aeronautics and Space Administration. 1979 28 p refs (Contract F19629-77-C-0168; ARPA Order 2656) Ames Research Center, Moffett Field, Calif. (AD-A076959; PHM-01-79; SCIENTIFIC-2, AFGL.TR-79-0139( ANALYSIS OF FUEL-CONSERVATIVE CURVED DECELER Avail NTIS HC A03/MF AOl CSCL 17/8 ATING APPROACH TRAJECTORIES FOR POWERED-LIFT A review of PhotoMetrics: field and data reduction work for AND CTOL JET AIRCRAFT the Air Force Geophysics Laboratory in the DNA-sponsored nuclear Frank Neuman Apr. 1980 38 p refs
effects simulations program and the ARPA .sponsored targets and (NASA-TP-1650; A . 798611 Avail NTIS NC A03/MF AOl CSCL 02A backgrounds measurements program during the period April A method for determining fuel conservative terminal 1978-April 1979 is presented. Data flights of USAF NKC- approaches that include changes in altitude, speed, and heading 135 53120 on which PhotoMetrics operated radiometric instruments, the design, fabrication and application of an optical are described. Three different guidance system concepts for STOL aircraft were evaluated in flight: (1) a fixed trajectory system: co-aligner for very narrow-angle aircraft instruments are (2) a system that included a fixed path and a real time synthesized documented, and modifications to an ISIT vidicon camera for capture flight path; and a trajectory synthesizing system. auroral imaging are reviewed GRA (3) Simulation results for the augmentor wing jet STOL research aircraft and for the Boeing 727 aircraft are discussed. The results N8O18884*# National Aeronautics and Space Administration, indicate that for minimum fuel consumption, two guidance Langley Research Center, Langley Station. Va. deceleration segments are required. A.W.H.
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N80-19023'fl National Aeronautics and Space Administration. INTERVALS Interim Report Langley Research Center. Langley Station, Va. I. K. Cohen and Eugene Poggio Oct. 1979 37 p AEROACOUSTIC WINO-TUNNEL TESTS OF A LIGHT (Contract F49620-77-C-0023) TWIN-BOOM GENERAL-AVIATION AIRPLANE WITH FREE (AD-A078606; RAND/N-1247-AF) Avail: NTIS OR SHROUDED-PUSHER PROPELLERS HC A03/MF AOl CSCL 15/5 H. Clyde McLemore and Robert J. Pegg Apr. 1980 88 p Typically, decisionmakers are called upon to make decisions refs on aircraft inspection intervals on the basis of very limited analytic (NASA-TM-80203; L-13371) Avail: NTIS HC A05/MF AOl information. Under such circumstances, decisionmakers are CSCL 0113 understandably concerned about the risks incurred in extending Tests were conducted in the Langley full-scale tunnel to inspection intervals. This note presents in some detail a discussion determine the aerodynamic performance and acoustic characteris- of the phenomenon that although an immediate change is made tics of four different pusher-propeller configurations on a twin in inspection intervals, it takes a considerable period of time for boom, general aviation airplane. The propellers included a 2-blade the fleet to transition to the changed interval. The slow fleet free propeller, two 3-blade shrouded propellers, and a 5-blade maturation may provide considerable opportunity to monitor and shrouded propeller. The tests were conducted for a range of control the condition of the fleet during the transition period. airplane angles of attack from about 0 deg to 16 deg for test Thus, in the case of extending inspection intervals, risk is reduced speeds from 0 to about 36 m/sec and for a range of propeller and spread over time while the payoff for the change is blade angles and rotation speeds. The free propeller provided immediate. GRA the best aerodynamic propulsive performance. For forward flight conditions, the free propeller noise levels were lower than those of the shrouded propellers. In the static conditions the free propeller noise levels were as low as those for the shrouded N80-19028 Engineering Sciences Data Unit. London (England). propellers, except for the propeller in-plane noise where the UNDERCARRIAGE DRAG PREDICTION METHODS shrouded propeller noise levels were lower. J.M.S. 1979 31 p (ESDtJ-7901 5; ISBN-0-85679-260-8; ISSN-0141-391-397X) For information on availability of series, sub-series, and other N80-19024# National Aeronautics and Space Administration. individual data items, write NTIS. Attn: ESDU, Springfield, Va. Langley Research Center, Langley Station, Va, 22161. HC $770.50 MILITARY AIRCRAFT AND MISSILE TECHNOLOGY AT THE A method for estimating the drag of an aircraft undercar- LANGLEY RESEARCH CENTER: A SELECTED BIBLIOGRA- riage is presented. The research is applied to the calculation of PHY the drag of an aircraft in the landing approach. The results can Dal V. Maddalon Jan. 1980 43 p be applied to virtually any type of fixed or retractable undercarriage (NASA-TM-80204) Avail: NTIS HC A03/MF AOl CSCL at low speeds. ESDU (GRA) 02A A compilation of reference material is presented on the Langley Research Center's efforts in developing advanced military aircraft and missile technology over the past twenty years. N8019030*# Bihrle Applied Research, Inc., Jericho, N. V. Reference material includes research made in aerodynamics, ROTARY BALANCE DATA FOR ATYPICAL SINGLE-ENGINE performance, stability, control, stall-spin, propulsion integration, GENERAL AVIATION DESIGN FOR AN ANGLE-OF-ATTACK flutter, materials, and structures. Author RANGE OF 8 DEG TO 90 DEG. 1: LOW-WING MODEL A Randy S. Hultberg and William Mulcay Feb. 1980 400 p refs N8019025*# National Aeronautics and Space Administration. (Contract NAS1-14849) Ames Research Center, Moffett Field. Calif. (NASA-CR-3100) Avail: NTIS HC A17/MF AOl CSCL 01A WORKSHOP ON AIRCRAFT SURFACE REPRESENTATION Aerodynamic characteristics obtained in a rotational flow FOR AERODYNAMIC COMPUTATION T. J. Gregory, ed. and John Ashbaugh, ed. Feb. 1980 560 p environment utilizing a rotary balance are presented in plotted Workshop held at Ames Research Center, Moffett Field, Calif.. form for a i/S scale, single engine, low-wing, general aviation 1-2 Mar. 1978 airplane model. The configuration tested included the basic airplane, various control deflections, tail designs, fuselage shapes, (NASA-TM-81170; A-8075) Avail: NTIS HC A24/MF AOl CSCL 02A and wing leading edges. Data are presented without analysis Papers and discussions on surface representation and its for an angle of attack range of 8 to 90 deg and clockwise and integration with aerodynamics, computers, graphics, wind tunnel counterclockwise rotations covering a range from 0 to 0.85. model fabrication, and flow field grid generation are presented A.W.H. Surface definition is emphasized. R.E.S. N8019033*# National Aeronautics and Space Administration. N8019026*# Michigan Univ., Ann Arbor. Langley Research Center, Langley Station, Va. TRAJECTORIES OPTIMIZATION IN HYPERSONIC FLIGHT A FLIGHT INVESTIGATION OF BLADE SECTION AERODY- Final Report NAMICS FOR A HELICOPTER MAIN ROTOR HAVING Nguyen X. Vinh Mar. 1980 5 p refs NLR-1T AIRFOIL SECTIONS (Grant N5G-1448) Charles E. K. Morris, Jr., Dariene D. Stevens, and Robert L. )NASA-CR-162846) Avail: NTIS HC A02/MF AOl CSCL Tomaine Jan. 1980 194 p refs Sponsored in part by 02A AVRADCOM. St. Louis, Mo. Equations of motion were derived for the three dimensional (DA Proj. TL2-62209-A-76) flight of a lifting vehicles, taking into consideration all the main (NASA-TM-80166: AVRADCOM-TR-80-B-2) Avail: NTIS effects of different forces acting on a vehicle at orbital speeds. HC A09/MF AOl CSCL 01A A set of equations was formulated which are valid for both the A flight investigation was conducted using a teetering-rotor flight with lift modulation inside a planetary atmosphere and AH-1G helicopter to obtain data on the aerodynamic behavior the Keplerian motion in the vacuum. The equations are in- of main-rotor blades with the NLR-1T blade section. The data dependent of the physical characteristics of the vehicle. The only system recorded blade-section aerodynamic pressures at parameters involved are the maximum lift to drag ratio of the 90 percent rotor radius as well as vehicle flight state, performance, vehicle and a constant characterizing the atmosphere. The results and loads. The test envelope included hover, forward flight, and obtained can be applied without modifications to any future reentry collective-fixed maneuvers. Data were obtained on apparent vehicle, regardless of its size, shape, and mass. A.R.H. blade-vortex interactions, negative lift on the advancing blade in high-speed flight and wake interactions in hover. In many cases, N80. 19027# RAND Corp., Santa Monica, Calif. good agreement was achieved between chordwise pressure ESTIMATING THE TIME REQUIRED TO TRANSITION distributions predicted by airfoil theory and flight data with no AIRCRAFT FLEETS TO NEW SCHEDULED MAINTENANCE apparent indications of blade-vortex interactions. R.E.S.
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N80-19040# ARO. Inc., Arnold Air Force Station, Tenn. N80-19044// Science Applications. Inc., Irvine, Calif. WIND TUNNEL TEST TO INVESTIGATE AERODYNAMIC HYPERSONIC INTERFERENCE FLOW FLIGHT EXPERIMENT HYSTERESIS PHENOMENA OF THE F-4 AND F-il DESIGN Final Report, 15 Jun. - 15 Apr. 1979 AIRCRAFT MODELS L. A. Cassel, T. C. Duncan, and E. H. Lahti Jun. 1979 244 p Joseph F. Herman AEDC 15 May 1979 37 p refs (AD-A077196; AEDC-TSR-79-P27) Avail: NTIS (Contract F33615'77-C-3043; AF Proj. 2404) HC A03/MF AOl CSCL 01/3 (AD-A078861; SAl- 1 75-80-008-R; AFFDL-TR-79-3065) Avail: Wind tunnel tests were conducted to investigate aerodynamic NTIS HC Ali/MF AOl CSCL 20/4 hysteresis phenomena found in other investigations of the F-4 An experiment has been defined to measure the aeroheating and F-ill aircraft models. A 1/20-scale model of the F-4C and loads resulting from three-dimensional shock wave/boundary aircraft was used to obtain static force, moment and wing pressure layer interference in hypersonic flight. This report describes the data in pitch and sideslip over a Mach number range from definition of this flight experiment, including the instrumentation 0.7 to 0.95. A 1/24-scale model of the F-ill aircraft was and electronics required to measure the interference heating and used to obtain static force and moment data for a Mach number loads and transmit those measurements by telemetry to ground range of 0.7 to 1.3. Data on the F-1 11 were obtained for wing stations. The measurements include quasi-steady heat transfer sweep angles of 26 and 54 deg. In addition, tuft and oil flow rates and pressures as well as fluctuating pressures. Additional visualization data were obtained for selected confugurations.GRA measurements are specified for specific definition of the experiment environment. The experiment is configured to investigate the interference flow at the base of a stabilizer on a N80-19041# Air Force Flight Dynamics Lab., Wright-Patterson missile launched from an F-4 aircraft. The missile is to be propelled AFB. Ohio. Recovery Crew Station Branch. to hypersonic speed by a solid propellant motor and the RECOVERY SYSTEM PRELIMIMINARY DESIGN. A measurements are to be made at altitudes between 50 KFT SIMPLIFIED APPROACH TO DETERMINING STAGING, and ground impact. The mechanical, structural, and thermal TIMING AND ALTITUDE REQUIREMENTS FOR FAST protection system specifications for the experiment carrier missile INFLATING PARACHUTES Final Report, 13 Feb. - 1 Jun. are provided in this report. Missile design and fabrication drawings 1976 Michael W. Higgins Sep. 1979 74 p are available under separate cover from the sponsoring agency. G RA (AF Proj. 6065) (AD-A077548; AFFD L-TR-79-3007) Avail: NTIS HC A04/MF AOl CSCL 01/3 N80-19045# Scientific Research Associates, Inc.. Glastonbury, Determining a recovery system design that will take a specified Conn. act of initial conditions and will operate within a given set of VISCOUS FLOW IN THE REGION OF A ROUNDED constraints to provide a required final condition is a complex TRAILING EDGE Final Report, 1 Jul. 1978 - 30 Jun. 1979 task To perform this task, current design practices make extensive Ralph Levy, W. Roger Briley, and Henry McDonald 31 Jul. use of both person hours and computer time in an analytical 1979 41 p refs 'Cut and try' process. This report documents an analytical technique (Contract N00019-78-C-0470( that takes a specified set of inputs (initial conditions, final (AD-A078588; R79-920003-F) Avail: NTIS conditions and operating constraints) and outputs a 'reasonable' HC A03/MF AOl CSCL 20/4 recovery system preliminary design for fast inflating parachutes. The Interactive Zone Embedding concept is a generalization The output includes the number of operating stages, the drag of concepts which have been used for some time with boundary area of each operating stage. the reefing cutter times, and resulting layer analyses. This concept has been extended to more complex altitude losses. The technique assumes a vertical trajectory, step flows using a potential flow for the outer zone and the function increases in parachute drag area, and that the recovery compressible Navier-Stokes equations for the inner zone. In this system is a point mass. The limitations of the analytical technique interactive manner the flow about rounded trailing edge was are discussed and recommendations are made with respect to computed for two locations of the outer boundary. The calculations reducing or removing the effects of these limitations. The analytical were performed on a 5:1 elliptic cylinder at a Mach number of technique is applied to three different sets of conditions and 0.2 and a Reynolds number based on chord of 1,000. A body constraints as example applications. Use of the analytical technique fitted conformal coordinate system was used. In the first instance documented in this report will significantly reduce the assets the outer boundary was located approximately one chord from required to arrive at a final recovery system design. GRA the ellipse and in the second the outer boundary was brought to about one-half chord of the ellipse. The displacement body was chosen as the interactive streamline and the potential flow N80-19042// Naval Postgraduate School, Monterey, Calif. over this streamline was computed as the sum of the analytic PROCEEDINGS OF A WORKSHOP ON V/STOL AIRCRAFT potential flow over the elliptic cylinder plus the flow from a AERODYNAMICS, VOLUME 2 series of sources. The strengths of these sources were determined C. Henderson and M. F. Platzer 18 May 1979 474 p refs to make the interaction streamline also be a streamline in the Workshop held in Monterey. Calif., 16-18 May 1979 potential flowfield. The resulting potential flow was used to (AD-A078909) Avail: NTIS HC A20/MF AOl CSCL 20/4 evaluate the static pressure at the outflow boundary of the Contents: Propulsion System/Airframe Interactions-- Recent Navier-Stokes zone. The calculations were performed with the Applications of Theoretical Analysis to V/STOL Inlet Design, Inlet large Navier-Stokes domain and were repeated with a smaller Operating Characteristics at High Angles of Attack. Low Speed Navier-Stokes domain. The flow properties in the vicinity of the Development of the Supersonic XFV-12A V/STOL Inlet, Subsonic body of the two calculations were in excellent agreement. GRA VTOL Inlet Experimental Results, Inlet Ram Forces and Moments and V/STOL Aircraft, Theoretical Fan Velocity Distortions Due to Inlets and Nozzles, Aerodynamics of a Tilt-Nacelle V/STOL N80-19046# Naval Ship Research and Development Center, Propulsion System, Isolated Deflector Nozzle Static Tests for Bethesda, Md. Aviation and Surface Effects Dept. V/STOL Aircraft; V/STOL Aircraft Configurational Considerations EXPERIMENTAL INVESTIGATION OF A CIRCULATION and Developments--High Angle of Attack Aerodynamics at CONTROL AILERON Final Report, Oct. 1977 - Sep. 1978 DTNSRDC, Development of High Lift Devices for Application to Steven W. Prince Jul. 1979 29 p refs Advanced Navy Aircraft. YC-14 Low Speed Test Techniques, (WF4142 1000) Vectored-Engine-Over-Wing Concept Development, Wind Tunnel (AD-A078825; DTNSRDC/ASED-79/08( Avail: NTIS Investigation of a Highly Maneuverable Supersonic V/STOL HC A03/MF AOl CSCL 20/4 Fighter, Transition Characteristics of the External-Aug mentor A Circulation Control (CC) aileron was tested on a semispan V/STOL Aircraft Concept. Calculation of Forces and Moments wing-fuselage model at a dynamic pressure equal to 20 lb/sq Acting on an Augmentor Wing for a VTOL Fighter in Hover or ft (957 N/sq m) and a Reynolds number of 0.8 million per ft Transition Flight. Aerodynamics of an Advanced Jet Flap and an (2.62 million per m). Three different trailing edge geometries Ultra-STOL Application, and High Speed Aerodynamic Technology were used on CC ailerons of 10 and 20 percent of the half for V/STOL Fighter Attack Aircraft. GRA span. Blowing was controlled to produce jet momentum
233 N80-19047 coefficients from 0.0017 to 0.0124. Rolling moment coefficients N80-19051# Perceptronics, Inc., Woodland Hills, Calif. as high as 0.035 were recorded for the 20 percent CC aileron AIRCRAFT EMERGENCY DECISIONS: COGNITIVE AND for angles of attack between 0 and 12 deg. The CC aileron SITUATIONAL VARIABLES Annual Technical Report was at least three times as effective as a pure reaction jet for Rosemarie Hopf-Weichel, Luigi Lucaccini, Joseph Saleh. and Amos the same amount of bleed air. Adverse yaw was large, on the Freedy Jul. 1979 171 p refs order of one-half of the rolling moment. GRA (Contract F49620-78-C-0067; AF Proj. 2313) (AD-A077413; PATR- 1065-79-7; AFOSA . 79- 11 75TR) Avail: NTIS HC A08/MF AOl CSCL 01/2 N80-19047# Advisory Group for Aerospace Research and Military aircraft accidents are important not only to the Development. Paris (France). individuals directly involved, but also to those responsible for PROPULSION AND ENERGETICS PANEL WORKING preparing and maintaining combat-ready forces for the nation's GROUP 11 ON AIRCRAFT FIRE SAFETY. VOLUME 2: MAIN defense. This report addresses problems underlying aircraft REPORT emergency situations. A literature review provided background B. P. Botteri. ed.. M. Gerstein, ed.. T. Horeff, ed.. and J. Parker. information, and an analysis of selected accident reports. A ed. Nov. 1979 167 p 2 Vol. workshop was convened to review the state-of-the-art of aircrew (AGARD-AR-132-Vol-2; ISBN .92-835-1344-4) Avail: NTIS emergency decision training, safety research, and behavioral HC A08/MF AOl decision theory. A selected set of emergency situations was the Recent aircraft fire experience was analyzed and areas in basis of a preliminary classification of aircraft emergency situations which fire protection enhancement is needed were delineated. in terms of several situational and decision making attributes. Technological opportunities that offer significant prospect for The classification is based on data derived from interviews with improvement of safety and personnel survivability were also experienced military flying personnel. A taxonomy of emergency identified. Because of the complexity of the overall problems, situation types was developed, incorporating both situational and attention was focused upon turbine engine powered transport task specific elements as cognitive attributes of the decision aircraft in a conventional (non-combat) operational environment. tasks performed under emergency conditions. On the basis of Conclusions and recommendations are summarized. R.E.S. the taxonomy, three classes of emergency situations were found to be of interest: Situation 1 (predictable) Situation 2 (partly N80, 19048*# TRW Defense and Space Systems Group, Redondo predictable), and Situation 3 (unpredictable). Initial training Beach, Calif. guidelines are suggested in light of the cognitive requirements DATA REDUCTION AND ANALYSIS OF GRAPHITE FIBER of each class. GRA RELEASE EXPERIMENTS Paul Lieberman, Albert A. Chovit, Benjamin Sussholz, and Howard F. Korman Jul. 1979 362 p refs N80-19052# RAND Corp.. Santa Monica, Calif. (Contract NAS1-15465) AIRCRAFT ICING DURING LOW-LEVEL FLIGHTS Interim (NASA-CA- 159032; NASA/TRW-79-2l Avail: NTIS Report HC A16/MF AOl CSCL 01C Robert R. Rapp Nov. 1979 19 p refs The burn and burn/explode effects on aircraft structures were (Contract F49620-77-C-0023( examined in a series of fifteen outdoor tests conducted to verify (AD-A078843; RAND/N-1311-AF) Avail: NTIS the results obtained in previous burn and explode tests of HC A02/MF AOl CSCL 91/2 carbon/graphite composite samples conducted in a closed The reasons why icing may hinder low and slow flights are chamber, and to simulate aircraft accident scenarios in which presented. A crude measure of the potential of icing near the carbon/graphite fibers would be released. The primary effects ground is presented and it is shown that, by this measure, icing that were to be investigaged in these tests were the amount may be a serious problem when flying over the higher terrain and size distribution of the conductive fibers released from the of central Europe. Some suggestions for improving the measure composite structures, and how these various sizes of fibers of icing potential are given. GRA transported downwind. The structures included plates, barrels, aircraft spoilers and a cockpit. The heat sources included a propane N80-19053# Stencel Aero Engineering Corp., Asheville, N. C. gas burner and 20 ft by 20 ft and 40 ft by 60 ft JP-5 pool PROTOTYPE DEVELOPMENT PASSIVE, SEAT-MOUNTED fires. The larger pool fire was selected to simulate an aircraft LIMB RETENTION SYSTEM Final Report, Sep. 1977 - May accident incident. The passive instrumentation included sticky 1979 paper and sticky bridal veil over an area 6000 ft downwind and May 1979 94 p refs 3000 ft crosswind. The active instrumentation included in- (Contracts N62269-77-C-0251; WF140000( strumented meteorological towers, movies, infrared imaging (AD-A076331. NADC-79201 -60) Avail: NTIS cameras. LADAR. high voltage ball gages, light emitting diode HC A05/MF AOl CSCL 01/3 gages, microwave gages and flame velocimeter. A.R.H. It has been well documented that the predominant cause of injury (both major and minor( occurring from combat ejections during the Southeast Asia conflict was due to flailing of the extremities as a result of increased ejection speed. A prototype N80-19049# Computer Sciences Corp. Huntington Valley, Pa. passive seat mounted limb retention system was developed and MICROPROCESSOR CONTROLLED EJECTION SEAT Final manufactured which does not require the aircrewman to wear Report any additional devices or fasten additional restraint connections. Kathleen M. Breakey 23 Oct. 1979 208 p refs It will not, in any way, compromise his movement in the cockpit (Contract N66269-78-C-0191) or his control of the aircraft. This functional prototype device (AD-A077479; NADC-79240-60) Avail: NTIS will undergo feasibility testing to determine acceptability for further HC A10/MF AOl CSCL 01/3 development. GRA The operation of an ejection seat depends on a number of devices on the seat performing certain tasks at specific times. Traditionally, the timing and sequencing of these tasks have N80-19054# Federal Aviation Administration. Washington, D. C. been controlled by fuses, gas lines and mechanical linkages. AIRBORNE RADAR APPROACH SYSTEM FLIGHT TEST with marginal accuracy and limited logic. This effort was EXPERIMENT Final Report undertaken to demonstrate the feasibility of using a microprocessor L. D. King and R. J. Adams Oct. 1979 127 p refs to control these functions with increased accuracy and more (Contract DOT-FA79WA-4293) sophisticated logic. The microprocessor provides timing by (AD-A077900; FAA-RD-79-99( Avail: NTIS electronic clock, event sequencing via electrical signals, and HC A07/MF AOl CSCL 17/7 sophisticated logic based on environmental inputs. In addition, The performance of airborne radar as an approach aid is the microprocessor, in conjunction with a gimballed rocket motor, analyzed using data from the airborne radar approach (ARA) provides the capability of performing a Vertical Seeking Maneuver system flight tests experiment. The experiment design, equipment in the event of an adverse attitude ejection. This report contains used, and test objectives are reviewed. The ARA tests were the software required to complement all these functions. GRA performed utilizing the Bendix RDR-1400a airborne radar system.
234 N80-19064
The test vehicle was a CH-53A helicopter. Test airspace a light jet trainer aircraft. It is carried out under realistic conditions environments included airport, remote sites, and offshore areas. by using the controls and the initial conditions of sixteen actual Flight tests for ARA accuracy and procedures development were T-2C flight test data records to generate the Sixteen synthetic performed in both skin paint and single beacon radar operating maneuvers used in the study. The synthetic data are corrupted modes. The technical and operating performance, in flight by realistic measurement noise levels representative of the actual. considerations, the development of pilot procedures, and detailed The EBM method is a two stage process. In the first stage, the accuracy data for each area of testing are discussed. A.W.H. corrupted data are processed one maneuver at a time using an extended Kalman-Bucy filter/Bryson-Frazier smoother to obtain N8019055*// Analytical Mechanics Associates, Inc.. Mountain estimated values of the states and of the forces and moments View, Calif. acting on the aircraft. In the second stage. subspace modeling NAVIGATION SYSTEMS FOR APPROACH AND LANDING together with a step-wise multiple linear regression technique is OF VTOL AIRCRAFT used to process the estimated values from all sixteen maneuvers Stanley F. Schmidt and Richard L. Mohr Oct. 1979 63 p together in parallel to identify a global state/control dependent refs model of the three force coefficients and the three moment (Contract NAS2-9430( coefficients. The identified global model compares well with the (NASA-CR-152335; AMA-79-15) Avail: NTIS true values of the T-2C wind tunnel model. The EBM method is HC A04/MF AOl CSCL hG demonstrated to accurately identify the high nonlinearities of The formulation and implementation of navigation systems the T-2C wind tunnel model. The prediction accuracy of the used for research investigations in the V/STOLAND avionics identified global model is shown to be excellent by a comparison system are described. The navigation systems prove position and of the responses for a new maneuver and for the original sixteen velocity in a cartestian reference frame aligned with the runway. maneuvers. GRA They use filtering techniques to combine the raw position data from navaids (e.g.. TACAN. MLS) with data from onboard inertial N80-19062# Drexel Univ., Philadelphia. Pa. sensors. The filtering techniques which use both complementary SIGNIFICANCE OF LARGE SCATTER OF COMPOSITE and Kalman filters, are described. The software for the navigation PROPERTIES TO AIRCRAFT RELIABILITY Final Report systems is also described. R.E.S. Pei Chi Chou and Robert Croman Sep. 1979 48 p refs (Contract N62269-78-C-0267) N8O-19059// Army Communications-Electronics Engineering )AD-A077804; NADC-78094-60) Avail: NTIS Installation Agency, Fort Huachuca, Ariz. HC A03/MF AOl CSCL 01/3 STANDARD ENGINEERING INSTALLATION PACKAGE. AIR Statistical calculations have been made for the static load TRAFFIC RADIO CHANNEL CONTROL (ATRCC) EQUIP- reliability of an aircraft fleet assuming typical metallic and MENT Final Report composite strength distributions. A factor of safety is defined as Nov. 1979 90 p refs the element strength divided by the 'weakest of the fleet' strength. (AD-A077648: USACEEIA-SEIP-036( Avail: NTIS Element strength is typical 'A' or 'B' basis material allowables. HC A05/MF AOl CSCL 17/7 'Weakest of the fleet' strength is calculated statistically assuming This Standard Engineering Installation Package SEIP provides each aircraft to be made up of a realistic arrangement (in-series information for the engineering and installation of ATRCC facilities or in-parallel) of critical elements. Similar calculations are also worldwide. Information provided Consists of site survey data. made for fatigue life. It is shown that the reliability of the current siting Criteria, installation specifications and instructions, a bill damage tolerant design, such as multiple load path and crack of materials, quality assurance procedures and Completion stoppers, can be specified in quantitative terms. GRA certification format. Information provided must be adapted to the Specific ATRCC facility/ location by the project engineer. Author (GRA) N8019063*# Bolt, Beranek, and Newman, Inc.. Cambridge, Mass. CLOSED LOOP MODELS FOR ANALYZING ENGINEERING N80-19060 Engineering Sciences Data Unit. London (England). REQUIREMENTS FOR SIMULATORS Final Report ESTIMATION OF THE ENDURANCE OF CIVIL AIRCRAFT Sheldon Baron, Ramal Muralidharan, and David Kleinman Feb. WING STRUCTURES 1980 232 p refs 1979 14 p (Contract NAS1-14449) )ESDU-79024; ISBN-0-85679-272-1; ISSN-0141-3996) For (NASA-CR-2965) Avail: NTIS HC Al 1/MF AOl CSCL 14B information on availability of series, sub-series, and other individual A closed loop analytic model, incorporating a model for the data items, write NTIS. Attn: ESDU, Springfield, Va. 22161. human pilot, (namely, the optimal control model) that would HC $386.50 allow certain simulation design tradeoffs to be evaluated A method of analyzing the cumulative frequency spectrum quantitatively was developed. This model was applied to a realistic for an aircraft wing station into discrete loading cycles in flight control problem. The resulting model is used to analyze preparation for a fatique damage calculation is described. The both overall simulation effects and the effects of individual calculations derive the mean life estimation of a wing structure. elements. The results show that, as compared to an ideal The results apply to civil or transport aircraft in which maneuver continuous simulation, the discrete simulation can result in loadings are small. ESDU significant performance and/or workload penalties. J.M.S.
N80-19061# Dynamics Research Corp., Wilmington, Mass. N80-1906441 Grumman Aerospace Corp., Bethpage, N.Y. Systems Div. CREW STATION DESIGN FACILITY FEASIBILITY STUDY APPLICATION OF THE ESTIMATION-BEFORE-MODELING Final Technical Report. Sep. 1977 - Dec. 1978 (EBM) SYSTEM IDENTIFICATION METHOD TO THE HIGH S. LaCarrubba May 1979 189 p ANGLE OF ATTACK/SIDESLIP FLIGHT OF THE T-2C JET (Contract F33615-77-C-3067: AF Proj. 2403: AF Proj. 6190) TRAINER AIRCRAFT. VOLUME 2: SIMULATION STUDY (AD-A078134; AFFDL-TR-79-3037) Avail: NTIS USING T-2C WIND TUNNEL MODEL DATA Final Report HC A09/MF AOl CSCL 01/3 Harold L. Stafford and S. Ramachandran 23 Jun. 1978 275 p This report addresses the feasibility of a new and unique refs 3 Vol. facility capable of simulating the total range of lighting conditions (Contract N62269-76-C-0342) experienced in military aircraft crew stations during operational (AD-A079923: R-254U-Vol-2: NADC-76097-30-Vol-2; flight. The facility would provide a means for evaluating the Rept-1273-Vol-2) Avail: NTIS HC Al2/MF AOl CSCL 20/4 impact of extreme illumination levels on the legibility of displays This report presents the results of a feasibility study of the and instruments/ panel lighting systems to be incorporated in Estimation-Before-Modeling )EBM) method for aerodynamic advanced crew stations. This facility would interface with the parameter identification in the stall/post stall flight regimes. The flight simulation test facilities already established at the Flight feasibility study is conducted by processing synthetic flight data Control Development Laboratory at WPAFB. At the beginning generated by exciting a wind tunnel model of the Navy's T-2C. of this effort, two baseline lighting simulation systems were
235 N80-19065 selected for development. One configuration uses an opaque dome ELECTRONIC WARFARE SYSTEM (MULTEWS) Final Report, shaped lighting enclosure with internal sky illumination sources. 13 Aug. - 2 Dec. 1977 The other configuration uses a translucent enclosure with external Vernon L. Diekmann, Sherwood C. Spring, Mathews S. Mathews, sky illumination sources. Techniques for simulating air-to-air and Ill. John F. Hagen. and John S. Tulloch May 1978 187 p air-to-ground visual effects, terrain, and motion simulation were refs investigated for each baseline configuration. The principal (AD-A078476; USAAEFA-77-09) Avail: NTIS conclusion of this study is that real levels of sky and sun luminance, HC A09/MF AOl CSCL 01/3 colors and color shading can be simulated and controlled (with The United States Army Aviation Engineering Flight Activity some limitations) utilizing the translucent dome lighting enclosure conducted a Preliminary Airworthiness Evaluation (PAE) of a with external sky illumination sources. GRA UH-1H helicopter equipped with a Multiple Target Electronic Warfare System (MULTEWS) from 13 August through 2 December 1977. The evaluation was conducted at Edwards Air Force Base. N80-19065# Air Force Flight Dynamics Lab., Wright-Patterson AFB, Ohio. California, and required 45 flights for a total productive flight USAF DAMAGE TOLERANT DESIGN HANDBOOK: time of 41 hours. The test program was terminated when the GUIDELINES FOR THE ANALYSIS AND DESIGN OF test aircraft sustained major damage during height-velocity testing. DAMAGE TOLERANT AIRCRAFT STRUCTURES. REVISION The addition of the MULTEWS equipment to the UH-1H airframe A Interim Report, Jan. 1977 - Nov. 1978 caused significant degradation in performance and handling Howard A. Wood and Robert M. Engle, Jr. Mar. 1979 447 p qualities. Changes in the operator's manual should be made to Revised reflect the changes in performance for MULTEWS configured (AF Proj. 2401) aircraft. The MULTEWS installation also generally degraded the )AD-A078216; AFFD L-TR-79-3O2 1-Rev-A) Avail: NTIS vibration characteristics of the UH-1H, increased structural loads, HC A19/MF AOl CSCL 01/3 increased the maintenance workload, and degraded aircraft This is the first edition of a handbook to support the USAF crashworthiness. The degradation in performance and handling Airplane Damage Tolerance Requirements contained in MIL-A- qualities as well as the excessive vibrations and structural loads 83444. It provides specific background data and justification for in the MULTEWS configured aircraft were attributed to the the detailed requirements of MIL-A-83444 and provides guidelines extremely high drag and turbulent wake of the externally mounted and state-of-the-art analysis methods to assist contractor and MULTEWS components. GRA USAF personnel in complying with the intent of the specification and in solving cracking problems in general, for metallic aircraft structures. The material in this document is general enough to N8O-19068// Air Force Flight Dynamics Lab., Wright-Patterson be useful in the evaluation of the damage tolerance of in- AFB, Ohio. service aircraft designed and qualified prior to the issuance of DIGITAL COMPUTER SOLUTION OF AIRCRAFT LONGITU- MIL-A-83444. The handbook was structured to provide a clear DINAL AND LATERAL DIRECTIONAL DYNAMIC CHARAC- and concise summary of the specification, MIL-A-83444, as well TERISTICS Final Report as supporting analysis methods, test techniques, and nondestruc- John M. Griffin, Robert B. Yeager, Larry B. Jordan, and David tive inspection (ND)). Methods are provided as state-of-the-art A. Ratino Jul. 1979 173 p refs Revised along with suggested and/or recommended practices, limita- (AD-A078672; AFFDL-TR-78-203) Avail: NTIS tions, etc. Copies of appropriate USAF structural specifications HC A08/MF AOl CSCL 01/3 are contained as an appendix. GRA Two FORTRAN IV computer programs are presented for the solution of aircraft longitudinal and lateral-directional transfer function factors and dynamic characteristics. The longitudinal N80-19066# Boeing Aerospace Co.. Seattle. Wash. NEW REMOTELY PILOTED VEHICLE LAUNCH AND program solves for the three-degree-of-freedom dynamic RECOVERY CONCEPTS. VOLUME 1: ANALYSIS, characteristics (phugoid damping ratio and natural frequency, short PRELIMINARY DESIGN AND PERFORMANCE/COST period damping ratio and natural frequency, etc.) and the TRADE STUDIES Final Report, Mar. 1978 - Mar. 1979 numerator factors of the alpha, u, theta, h, and vertical acceleration Steven J. Baumgartner, James G. Brister. Vinod K. Rajpaul. and transfer functions. The lateral-directional program solves for the three-degree-of-freedom characteristics (Dutch roll damping ratio Roger F. Yurczyk Jun. 1979 259 p refs )Contract 1`33615-78-C-3404 AF Proj. 2402) and natural frequency, roll and spiral mode time Constants. etc.) )AD-A077475; AFFDL-TR-79-3069-Vol-1) Avail: NTIS and the numerator factors of the beta, phi, y, and lateral HC Al2/MF AOl CSCL 01/3 acceleration transfer functions. In addition, some time histories Dynamic analysis, preliminary design, and performance/ cost and specialized handling qualities parameters can be computed trade studies of air bag skid and air cushion concepts for launch and printed Out. The equations and their underlying assumptions and recovery of Boeing and Rockwell advanced RPV concepts are discussed. The two complete computer programs are shown. have been conducted. Dynamic analysis was performed using and the input, output, and program functions are discussed.GRA the six degree-of-freedom computer program EASY. Dynamic simulations included perturbations to steady state flight, landing. and takeoff simulations. Launch and recovery concepts investig- ated were air bag skid system, air cushion recovery systems, N80-19069# Human Engineering Labs., Aberdeen Proving integrated air cushion system, and air cushion launch platform. Ground. Md. Performance/ cost trade study factors investigated were complex- A STUDY OF THE CANOPY DESIGN FOR THE ADVANCED ity, fuel requirements, adverse weather capability, ground ATTACK HELICOPTER BY USE OF COMPUTER GRAPHICS equipment and facility requirements. survivability/vulnerability, Final Report reliability and maintainability, and system acquisition and life Christopher C. Smith Aug. 1979 137 p refs cycle costs. Results of the study indicated that an air cushion (AD-A07829 1: HEL-TM- 13-79) Avail: NTIS system is a feasible means of recovery of an RPV such as the HC A07/MF AOl CSCL 01/3 Boeing and Rockwell ARPV concepts. An air bag skid with an A package of computer programs has been developed for arrestor system is a feasible approach when minimum field length use in helicopter canopy design. The programs compute point-wise is a major design factor. Integrated air cushion systems for launch measures of three important design factors for the transparent and recovery are greatly affected by engine characteristics. In surfaces of an attack helicopter canopy. These factors are: ( 1) the each case, the launch and recovery systems are shown to be internal glare; )2) the external glint; and (3) the optical distortions an integral part of the total vehicle design and strongly influence exhibited by the canopy design. The programs have been applied the airframe design. GRA to modifications in the present canopy design on the YAH-64 Advanced Attack Helicopter. The results suggest that reduced N80. 19067# Army Aviation Engineering Flight Activity. Edwards internal glare is possible with slight additional glint and distortion AFB, Calif. by displacing the side windows 4 inches from the plane of the PRELIMINARY AIRWORTHINESS EVALUATION UH-1H frame vertices and rotating the axis of curvature of the top HELICOPTER EQUIPPED WITH MULTIPLE TARGET window by 90 degrees and displacing it 1.5 inches. GRA
236 N80-19077
N80-19070// Aeronautical Systems Div., Wright-Patterson AFB, Harold L. Stafford 12 Nov. 1979 61 p refs 3 Vol. Ohio. Flight Systems Engineering. (Contract N62269-76-C-0342) DEVELOPMENT OF A NORMALIZED PROBABILITY (AD-A080025; R-3031.1-Vol-1; NADC-76097-30.Vol. 1; DISTRIBUTION FOR LATERAL LOAD FACTORS DUE TO Rept-1273-Vol-1) Avail: NTIS HC A04/MF AOl CSCL 20/4 AIRCRAFT GROUND TURNING Final Report This report (Volume 1) summarizes the development and John W. Rustenburg Aug. 1979 41 p refs application of the Estimation-Before-Modeling )EBM) method for (AF Proj. 139A) aircraft parameter identification in the non-linear flight regime. (AD-A077047; ASD-TR-79-5037) Avail: NTIS The method utilizes a Two-step approach wherein model HC A03/MF AOl CSCL 01/3 independent states, forces and moments are first estimated and It was desirable to determine the expected frequency of then state and control dependent model parametes are obtained occurrence of lateral load factors due to aircraft ground turning using a Stepwise Multiple Linear Regression )SLMR) approach. maneuvers for a specified airplane service life. In order to In the second step )SLMR) the angle of attack and sideslip and accomplish this determination, published and unpublished control input space for all available flight data is divided into ground operations data measured on a C-141-A, DC-9-15. small subspaces and force and moment coefficients are modeled 727-100, KC-135. and F-105D aircraft was condensed and within each subspace. The method is applied to both simulated evaluated, and used in the development of a normalized side and actual flight data for a T-2C jet trainer aircraft in the stall load factor probability distribution for ground turning. The and post-stall flight regimes. Volumes 2 and 3 of this report normalized distribution can be used to predict the expected lateral present detailed description of the EBM method and its load factor spectrum due to ground turns for any aircraft. A application. GRA subordinate analysis of KC-135 and FB-1 1 1A data provided a normalized probability distribution of lateral load factor applicable N80-19074# Naval Air Development Center. Warminster, Pa. to taxiing and landing. GRA PROCEEDINGS OF A WORKSHOP ON V/STOL AIRCRAFT AERODYNAMICS, VOLUME 1 N80-19071// Army Command and General Staff CoIl., Fort C. Henderson and M. F. Platzer May 1979 604 p refs Workshop Leavenworth, Kansas. held in Monterey. Calif., 16-18 May 1979 THE F-16 WILD WEASEL: A FEASIBILITY STUDY )AD-A079115( Avail: NTIS HC A99/MF AOl CSCL 01/3 M.S. Thesis. Final Report This report contains the proceedings of the Workshop on Byron L. Huff 8 Jun. 1979 63 p refs V/STOL Aircraft Aerodynamics held at the Naval Postgraduate (AD-A077050) Avail: NTIS HC A04/MF AOl CSCL 17/4 School on May 16 to 18. 1979. This workshop was sponsored This study attempts to determine the feasibility of the Wild by the Naval Air Development Center. The workshop participants Weasel proposal being made by General Dynamics Corporation. included representatives from industry, government, universities The investigation covers the NATO threat, a brief history of the and abroad. GRA Wild Weasel: the capabilities of the current Wild Weasel )F-4G Phantom); the capabilities of the F-16 Wild Weasel; and a cost comparison of the F-16 and F-4G Wild Weasel aircraft. The N80-19075# Foster-Miller Associates, Inc., Waltham. Mass. investigation reveals that an advanced Wild Weasel is necessary ANALYSIS OF TRUNK FLUTTER IN AN AIR CUSHION to contend with the Soviet air defense system and to be compatible LANDING SYSTEM Final Report with near-future Allied fighter aircraft. GRA Ashok B. Bogharii and Roger B. Fish Aug. 1979 114 p refs (Contract F33615-78-C-3412; AF Proj. 2307) (AD-A079008; WP-7819; AFFDL-TR-79-3 102) Avail: NTIS HC A06/MF AOl CSCL 01/3 N80. 19072# Dynamics Research Corp.. Wilmington, Mass. This report deals with explaining the occurrence of flutter in Systems Div. the Air Cushion Landing System (ACLS) trunks and suggesting APPLICATION OF THE ESTIMATION-BEFORE-MODELING means of suppressing it. Observations of flutter in several ACLS (EBM) SYSTEM IDENTIFICATION METHOD TO THE HIGH trunks indicate that the flutter is caused by the interaction ANGLE OF ATTACK/SIDESLIP FLIGHT OF THE T-2C JET between the trunk membrane and the flow at the trunk bottom. TRAINER AIRCRAFT. VOLUME 3: IDENTIFICATION OF The flow creates a negative stiffness effect at the bottom which. T-2C AERODYNAMICS STABILITY AND CONTROL CHAR- if larger than the positive stiffness due to the tension of the ACTERISTICS FROM ACTUAL FLIGHT TEST DATA Final trunk, induces flutter. A computer simulation based on this model Report succeeds in predicting the flutter observed in the XC-8A tests. Harold L. Stafford 11 Apr. 1979 254 p refs 3 Vol. Suggestions on solving the flutter problem are based on either )Contract N62269-76-C.0342) modifying the trunk or modifying the flow. Computer simulations (AD-A079924; R-287U-Vol-3; NADC-76097-30-Vol-3; of several suggestions indicate that: (1) Providing a minimum Rept-1273-Vol-3) Avail: NTIS HC Al2/MF AOl CSCL 20/4 gap; (2) Lowering the separation point; (3) chafing the operation This volume presents the results of the application of the conditions show good promise in suppressing the flutter. Two Estimation-Before-Modeling (EBM) System Identification Method other suggestions, not simulated, which also have good potential to high angle of attack/sideslip flight test data of the T-2C Jet for flutter suppression are: (1) Incorporating circular trunk, and Trainer aircraft. Eighteen maneuvers consisting of over (2) Incorporating hybrid trunk. GRA 600 seconds of 20 hertz data are processed. An extended Kalman-Bucy filter/ Bryson- Frazier smoother is used in the first N80. 19076# Boeing Military Airplane Development, Seattle, step to provide state estimates and measurement biases and Wash. scale factors. In the second step of the EBM method, the step-wise EASY ACLS DYNAMIC ANALYSIS, VOLUME 2. PART 2: multiple linear regression technique and subspace modeling are COMPONENT COMPUTER PROGRAMS Final Report, Apr. used to identify detailed models of C sub y, C sub I, C sub n 1977 - Jun. 1979 and C sub m. Partial results are given for C sub x and C sub z. M. K. Wahi, G. S. Duleba. and P. R. Perkins Sep. 1979 296 p The state and control derivatives of the identified model agree refs well with the wind tunnel model. Most of the identified dynamic (Contract F33615-77-C-3054; AF Proj. 2404) derivatives compare well with the theoretically predicted value (AD-A079803; AFFDL-TR-79-3 1 05-Vol-2-Pt-2) Avail: NTIS at low alpha and some compare well at high alpha. GRA HC A13/MF AOl CSCL 09/2 This volume contains a detailed description of the component N80-19073# Dynamics Research Corp.. Wilmington, Mass. subroutines and of other standard functions/subroutines which Systems Div. are used in the EASY dynamic analysis program. Macro-flow APPLICATION OF THE ESTIMATION-BEFORE-MODELING charts and some micro-flowcharts and listings are included. (EBM) SYSTEM IDENTIFICATION METHOD TO THE HIGH Sample Output is included where appropriate. GRA ANGLE OF ATTACK/SIDESLIP FLIGHT OF THE T-2C JET TRAINER AIRCRAFT. VOLUME 1: EXECUTIVE SUMMARY N80-19077# Air Force Inst. of Tech., Wright-Patterson AFB, Final Report Ohio. School of Engineering.
237 N80- 19078
THRUST VECTORING TO ELIMINATE THE VERTICAL James 0. Coast Aug. 1979 65 p refs STABILIZER M.S. Thesis (Contract DAAG46-78-C-0008) Roy Edward LaFroth Dec. 1979 134 p refs (AD-A077711; GERA-2378; USAAVRADCOM-TR-79-32; (AD-A079852; AFIT/GAE/AA/79D-9) Avail: NTIS AMMRC-TR-79-50) Avail: NTIS HC A04/MF AOl CSCL HC A07/MF AOl CSCL 01/3 01/3 Root locus analysis techniques are used to design an active This program was conducted to determine the feasibility of thrust vector control system to provide the directional stability fabricating helicopter windshields with a designated urethane sheet for an F-i 11 without the vertical stabilizer. A linear analysis of interlayer. Four sets of full-size UH-1 windshields consisting of the lateral-directional modes is performed for the aircraft both two each of two different constructions were fabricated and with and without the vertical stabilizer. The aircraft with the tested. GRA vertical stabilizer is used as a baseline. Computer histories for N80-19081# Lockheed-Georgia Co.. Marietta. discrete atmospheric turbulence and a covariance analysis for AERODYNAMIC INVESTIGATION OF C-141 LEADING EDGE random turbulence are used for the evaluation. It is found that MODIFICATION FOR CRUISE DRAG REDUCTION, VOLUME the thrust vector control produces a response as good as or 2 Final Report, Jun. 1977 - Sep. 1978 better than the baseline aircraft. Requirements for the thrust W. T. Blackerby and P. R. Smith Jun. 1979 319 p refs vector deflection and rate of deflection are generated. The lowest (Contract F09603-77-A-0204) possible rate of deflection for acceptable flying qualities is (Ab-A077688; LG78ER0233-Vol-2; AFFDL-TR-79-3059-Vol-2) shown to be 1 rad/sec. GRA Avail: NTIS HC A14/MF AOl CSCL 01/3 A study of the aerodynamic design and high speed wind N80-19078# Air Force Inst. of Tech.. Wright-Patterson AFB, tunnel investigation of wing leading edge modifications for-cruise Ohio. School of Engineering. drag reduction on the C-141 aircraft has been completed. Also MINIMUM TIME TURNS WITH THRUST REVERSAL investigated were the effects of a wing swept tip extension and M.S. Thesis trailing edge anti-drag bodies. These modifications were tested Thomas L. Johnson Dec. 1979 77 p refs in the AEDC 16-Foot Transonic Facility, using a 0.044 scale (AD-A079851; AFIT/GAE/AA/79D-6) Avail: NTIS C-141B model, to determine the effects on C-141 cruise HC A05/MF AOl CSCL 01/2 aerodynamic characteristics and wing chordwise pressure The object of this study is to find the optimal trajectories distributions. Design of the leading edge modifications was based and corresponding minimum turning times for a high performance on the use of transonic wing theory, transonic airfoil theory and aircraft with and without thrust reversal to perform a prescribed experience previously gained with a two-dimensional airfoil leading turn, and then to compare those trajectories and times to evaluate edge modification program. Force data results were analyzed to the benefit of thrust reversal. Optimal control theory is applied determine the effects on C . 141 cruise drag, drag rise characteris- to solve the minimum time to turn optimal control problem, tics and cruise performance. Correlations were made with transonic using a suboptimal control problem approach and a second-order theory using the measured chordwise pressure distributions. A parameter-Optimization method. The results of the study found fuel and cost savings evaluation was made of the selected leading that the suboptimal control approach was effective in solving edge configuration based on measured and predicted cruise the problem, that thrust reversal is beneficial in reducing turning performance improvements. GRA time if the aircraft's initial velocity is above the corner velocity, and that thrust reversal is not beneficial in performing a minimum time turn without losing energy. GRA N80-19082// Douglas Aircraft Co.. Inc.. Long Beach, Calif. EVALUATION OF AIRCRAFT WINDSHIELD MATERIALS IN A SIMULATED SUPERSONIC FLIGHT ENVIRONMENT Final N80-19079# Air Force Aero Propulsion Lab., Wright-Patterson Report, May 1978 - Mar. 1979 AFB, Ohio. Aerospace Power Div. J. B. Hoffman Jun. 1979 200 p refs AN ANALYTICAL AND EXPERIMENTAL STUDY OF (Contract F33615-75-C-3105; AF Proj. 2202) AIRCRAFT HYDRAULIC LINES INCLUDING THE EFFECT (AD-A078673; MDC-J7 186; AFFDL-TR-79-3058) Avail: NTIS OF MEAN FLOW Final Report, Jul. 1977 - Jul. 1979 HC A09/MF AOl CSCL 01/3 John H. Pletcher, Jr. Nov. 1979 204 p refs A series of wind tunnel tests were conducted at Mach 2.4. (AF Proj. 3145) 2.6 and 3.0 to determine material survivability and optical clarity )AD-A079746; AFAPL-TR-79-2 104) Avail: NTIS for a variety of small, flat laminated and monolithic specimens HC A11/MF AOl CSCLO1/3 of acrylic, urethane, glass, silicone and polycarbonate materials A mathematical model of a fluid transmission line was for potential use in the design of Mach 3.0 aircraft windshields. developed which included the effect of mean flow coupling with Twenty-seven specimens were tested to determine the material oscillatory flow. The analysis centered on solving the nonhomoge- limitations and capabilities, which included an investigation of neous confluent hypergeometric equation with complex parame- specific edge designs and the effect of edge structure on ters using an infinite series and evaluating the solution using temperature distribution. The tests were conducted in a Mach 6 Ward's method. Experiments were run using an aircraft hy- wind tunnel which utilized a shock generator to reduce the air draulic system. The frequency response, vibration displacement. stream to the desired flow across the outer surface of the and standing pressure half wave were measured in a straight specimens. The specimens were individually mounted in a line and a line with bends for flow rates up to 9.5 ppm. A pressurized box to provide a simulated cabin environment on clampon transducer, which did not disturb the flow and could their inner surface. Grid line photography was used to delineate be easily moved, was used for the pressure measurements. In inflight and permanent optical distortion. Material damage was the absence of vibration the clampon transducer measurements evaluated and thermal gradients were documented. Prior to this were within 5% of readings taken with a conventional Statham test program, the aerodynamic effect of a Mach 2.4 through in-line transducer. A sensitivity analysis showed the effect of Mach 3.0 flight environment on transparent plastic and interlayer small changes in geometry, temperature, steady-state pressure, materials was unknown. The survival of these specimens fluid properties, entrained air content, and element volume. Using demonstrated that laminated configurations consisting of the new mathematical model, the attenuation and phase constant acrylic/ silicone/ polycarbonate or urethane/urethane/ were calculated for hydraulic and air lines. Results compared polycarbonate, as well as glass/ silicone/ polycarbonate are viable well with experiment and published data. The new analysis and candidates for aircraft windshields that would be exposed to a line model provide a means for the fluid systems engineer to Mach 3.0 flight environment for short exposures. GRA accurately account for mean flow effects. GRA
N80-19080# Goodyear Aerospace Corp.. Litchfield Park, Ariz. N8O-19083# Sikorsky Aircraft, Stratford, Conn. Sikorsky Aircraft THE FABRICATION AND TESTING OF PROTOTYPE UH-1 Div. AIRCRAFT WINDSHIELDS MANUFACTURED WITH A NADC ABC ROTOR MAPS Final Report SHEET INTERLAYER Final Report, 29 Mar. 1978 - 29 Jan. David T. Balsh 29 Jun. 1979 32 p refs 1979 (Contract N62269-79-M-3221)
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(AD-A078802; SER-69060) Avail: NTIS HC A03/MF AOl were viewed through windscreens and the amount of distortion CSCL 01/3 was judged by a magnitude estimation procedure. Judgements This report is the formal documentation of the rotor were analyzed by discriminant analysis to identify the targets erformance maps and includes a description of the anticipated that best facilitated good discrimination among windscreens. A 1995 IOC rotor configuration on which the rotor maps are based psychophysical matching procedure was also evaluated. In some and substantiation for the methodology used in the generation conditions, photographic representations of the distortion patterns of the maps. The rotor maps themselves are presented in the were evaluated using the magnitude estimation procedures. The appendix of this report in both HESCOMP transcript sheet form results of the work show that windscreen-induced distortion is and in computer input code form. (the latter is a copy of the a multidimensional attribute and is best evaluated by multiple listing obtained from a set of punched computer cards which inspection procedures. Specific static and dynamic targets are will have been presented to NAVAIRDEVCEN. GRA recommended for use in evaluating distortion. Correlations between physical measures of distortion and psychophysical N80-19084# judgments are reported as well as reliabilities for selected RAND Corp., Santa Monica. Calif. experiments. Suggestions for improvements and further work are MEASURING TECHNOLOGICAL CHANGE IN JET FIGHTER included. AIRCRAFT Interim Report GRA William L. Stanley and Michael D. Miller Sep. 1979 124 p refs N80-19087# Kay and Associates, Inc.. Mount Prospect, Ill. (Contract F49620-77-C-0023) [AVIONICS LOGISTICS SUPPORT INCLUDING V/STOL, (AD-A077393; RAND/R-2249-AF) Avail: NTIS LAMPS, AND INSTRUMENT REPAIR) Final Report, 5 Dec. HC A06/MF AOl CSCL 01/3 1977 - 28 Aug. 1979 This report develops a technique to characterize the level of 2 Nov. 1979 30 p refs and change in jet fighter air vehicle technology. It complements (Contract N60921-78-C-0014) other methods used to assess technological risks of new fighter (AD-A077460( Avail: NTIS HC A03/MF AOl CSCL 01/3 concepts and to compare U.S. and foreign fighter technology. This unclassified report contains information on the contractual The technique uses multiple regression to relate time of effort of Kay and Associates. Inc. in support of the Naval Surface appearance of an aircraft design to its level of technology. Resulting Weapons Center and the Naval Air Systems Command. The expressions measure performance consequences of technological efforts encompassed a study concerning VSTOL vs LAMPS. Sea advance in terms of such parameters as specific power, sustained Based Air requirements. composition and configuration of future load factor, Breguet range, and payload fraction. Measured in ship weapons, and screening of Source. Maintenance and these terms, the rate of advance of U.S. fighter air vehicle Recoverability code changes. Additionally, this effort included the technology is declining. The monetary cost of increasing the research and analysis of candidate instrument repair facilities rate of advance could be very high. In the future, designers will with a view toward selecting specific instruments for various have to balance increasingly difficult improvements in air vehicle weapons systems for increased repair capability at the Intermediate technology against improvements in other technologies (such as level of Maintenance. GRA avionics or armament) that also enhance combat effectiveness. G RA N8O-19088# Air Force Aero Propulsion Lab., Wright-Patterson N80-19085# Systems Technology, Inc.. Hawthorne. Calif. AFB. Ohio. DEVELOPMENT OF VTOL FLYING QUALITIES CRITERIA A COMPUTER PROGRAM FOR ESTIMATING AIRCRAFT FOR LOW SPEED AND HOVER Final Report LANDING DISTANCE Interim Report, Aug. 1977 - Jul. Roger H. Hoh and Irving L. Ashkenas Dec. 1979 150 p refs 1979 (Contract N62269-77-C-0278) Kervyn D. Mach Aug. 1979 39 p (AD-A079911; STI-TR-1 116-1; NADC-77052-30) Avail: NTIS (AF Proj. 3066) HC A07/MF AOl CSCL 01/2 (AD-A077169; AFAL-TR-79-2086) Avail: NTIS A classification scheme has been developed to account for HC A03/MF AOl CSCL 01/2 outside visual cues and cockpit displays in determining the required This report describes a computer program which will estimate equivalent system forms for low speed and hover. Tentative criteria the runway length required to land a specified airplane. The are presented in terms of a visibility scale which quantifies program accepts inputs describing the aircraft gross weight, environmental conditions for the intended mission in a more velocity, drag, and engine performance and computes the fine-grained manner than simply specifying IMC or VMC. There landing distance on specified runway surfaces. Sample results are indications that rate and attitude systems may be used for for a time-engine STOL transport are included. The computer partial IMC conditions but that a translational rate command program is described along with instructions for its use. system is required for low speed and hover in zero visibility. In GRA general, most experiments indicate that advanced displays are not a substitute for augmentation. Tentative limiting conditions N80-19089# National Technical Information Service, Springfield, are defined for rate and attitude systems, but more data are Va. required to define handling qualities for translational rate command REMOTELY PILOTED VEHICLES, VOLUME 2. A BIBLIOGRA- systems. Since the existing data base is primarily oriented PHY WITH ABSTRACTS Progress Report, Nov. 1975 - Nov. toward command/ response characteristics, definition of the 1979 limiting conditions for turbulence and large discrete wind shears Guy E. Habercom, Jr. Dec. 1979 270 p Supersedes also requires more data. GRA NTIS/PS-78/1 246; NTIS/PS-77/1 143; NTI5/PS-76/1034; NTIS/PS75-876 (PB80-8021 19; NTIS/PS-78/1246; NTIS/PS-77/1 143; N80-19086# Systems Research Labs., Inc.. Dayton, Ohio. NTIS/PS-76/ 1034; NTIS/P5. 75/876) Avail: NTIS Electronic Warfare Center. NC 530.00/MF $30.00 CSCL 01C DEVELOPMENT OF A VISUAL INSPECTION TECHNIQUE Operation of vehicles under remote guidance and control is (OPTICAL ASSESSMENT OF AIRCRAFT TRANSPAREN- investigated. Aircraft, drones, and extraterrestrial explorers are CIES) among the areas researched. This updated bibliography contains Frank E. Ward, Anthony J. DeFrances. and Robert G. Eggleston 262 abstracts, 35 of which are new entries to the previous (AMRL) Wright-Patterson AFB, Ohio AMRL Oct. 1979 edition. GRA 129 p refs (Contract F33615-77-C-0535; AF Proj. 2313) N80-19090# Advisory Group for Aerospace Research and (AD-A079369; AM RL-TR-79-67( Avail: NTIS Development, Paris (France). MC A07/MF AOl CSCL 01/3 DYNAMIC ENVIRONMENTAL QUALIFICATION TECH- This work assessed the utility of different types of targets NIQUES and psychophysical procedures for evaluating optical distortions Nov. 1979 40 p refs Meeting held in Williamsburg, Va., Apr. induced by aircraft windscreens. Targets, both static and dynamic, 1979
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(AGARD-R-682; ISBN-92-835-1342-8) Avail: NTIS An overall view of the methods for the determination of HC A03/MF AOl aircraft flight mechanic parameters from flight tests and the Dynamic qualification test procedures are discussed with problems associated with them is given. Technologies in the emphasis on determining the resistance of equipment to the field of instrumentation, data handling, and data processing as effects of environments peculiar to military operations and well as improved methodologies for optimum control input design requirements. are covered. The application spectrum for parameter identifica- tion including aircraft handling qualities investigations and acceptance testing is emphasized. J.M.S. Aeronautical Systems Div., Wright-Patterson AFB, N80-19091// N80.19096*// National Aeronautics and Space Administration. Ohio. Langley Research Genter, Langley Station, Va. APPLICATION OF MIL-STD-810C DYNAMIC REQUIRE- IDENTIFICATION EVALUATION METHODS MENTS TO USAF AVIONICS PROCUREMENTS Vladislav Klein In AGARD Parameter Identification Nov. 1979 J. H. Wafford In AGARD Dyn. Environ. Qualification Tech. refs 21 p refs Nov. 1979 11 p Avail: NTIS HG A16/MF AOl GSGL 01G Methods for airplane parameter estimation, the equation error Avail: NTIS HG A03/MF AOl method, output error method, and two advanced methods are The vibration requirements and the application of these presented and their basic properties described. The advanced requirements to the procurement of avionics equipment are methods include the maximum likelihood and extended Kalman discussed. Data obtained from external noise measurements and R.C.T. filter method. For a better understanding of the estimation aerodynamically induced vibration are reported. techniques a first-order scalar differential equation is used as a model of the system under test. Application of the methods to N80-19092# Messerschmidt-Boelkow G.m.b.H., Munich (West a general multivariable linear system is briefly outlined. A note Germany). Unternehmensbereich Flugzeuge. on the parameter estimation in the frequency domain is also DYNAMIC ENVIRONMENTS AND TEST SIMULATION FOR presented. Numerical examples along with the comparison of QUALIFICATION OF AIRCRAFT EQUIPMENT AND EXTER- results from various methods are given. J.M.S. NAL STORES G. Haidi, C. Lodge (British Aerospace Aircraft Group, Warton, England). and H. Zimmermann (Vereinigte Flugtechnische N80-19097# Deutsche Forschungs- und Versuchsanstalt fuer Werke-Fokker G.m.b.H., Bremen, West Germany) In AGARD Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer Dyn. Environ. Qualification Tech. Nov. 1979 13 p refs (For Flugmechanik. primary document see N80-19090 10-05) PRACTICAL INPUT SIGNAL DESIGN Avail: NTIS HG A03/MF AOl E. Plaetschke and G. Schulz (DFVLR. Oberpfaffenhofen, West Equipment within an aircraft was exposed to a wide variety Germany) In AGARD Parameter identification Nov. 1979 of environments during ground and flight operations in order to 19 refs determine its reliability and performance under conditions which Avail: NTIS HG A16/MF AOl will be encountered during its service life. Test specifications The design of optimal inputs for identifying stability and based upon real environments, but simplified for simulation, were control derivatives of the longitudinal and lateral motion of an established. Significant observations and results are reported. aircraft is considered. First the purpose of input optimization, R.C.T. the constraints, and an overview of the literature is presented. Then two different procedures of input design are treated in N80-19093# British Aerospace Aircraft Group. Bristol (England). more detail. Starting with investigations in the frequency domain CIVIL AIRCRAFT EQUIPMENT ENVIRONMENT QUALIFICA- the first method yields a multistep input signal, which fulfills TION TECHNIQUES specific spectral requirements. The second way of input design B. W. Payne and G. H. F. Nayler In AGARD Dyn. Environ. is based on the Optimization of different measures of the Fisher Qualification Tech. Nov. 1979 10 p refs information matrix, such as determinant or trace. Depending on the measure used, the designed signals differ with respect to Avail: NTIS HG A03/MF AOl their spectral composition. The discussed input signals. which The vibration testing of civil aircraft equipment is discussed. were used in a flight test program, are compared with respect The environmental test levels that are existing in international to the achieved accuracy of the identified stability and control requirements for civil aircraft are presented. R.C.T. derivatives. J.M.S.
N80-19094# Advisory Group for Aerospace Research and N8O-19098# National Aerospace Lab.. Amsterdam (Netherlands). Development, Paris (France). ASPECTS OF FLIGHT TEST INSTRUMENTATION PARAMETER IDENTIFICATION J. H. Breeman, K. vanWoerkom, H. L. Jonkers, and J. A. Mulder Nov. 1979 353 p refs Lecture held in Delft, Netherlands, In AGARD Parameter Identification Nov. 1979 22 p refs 29-30 Oct. 1979 and in London, 1-2 Nov. 1979 Prepared in cooperation with Technische Hogeschool, Delft, (AGARD-LS- 104; ISBN-92-835-1340-1) Avail: NTIS Netherlands HG A16/MF AOl Avail: NTIS HG A16/MF AOl The present state of the art of aircraft parameter identification The design of the instrumentation system for parameter techniques is reviewed. A critical appraisal of current methods estimation tests is considered. Specifications of instrumentation developed and applied to the problems of analysis of flight test for nonsteady flight testing are discussed along with general data in a number of NATO countries is given. Particular emphasis aspects and selection criteria of various transducer types. As is placed on the practical aspects of aircraft parameter estimation practical examples parts of the high accuracy instrumentation to generate information useful for the flight test engineer. systems developed for the determination of performance and stability and control characteristics for dynamic maneuvers are described. Problems of signal conditioning are discussed. J.M.S.
N8O-19099// Technische Hogeschool. Delft (Netherlands). Dept. N80-19095# Deutsche Forschungs- und Versuchsanstalt fuer of Aerospace Engineering. Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer ANALYSIS OF AIRCRAFT PERFORMANCE STABILITY AND Flugmechanik. CONTROL MEASURES AIRCRAFT PARAMETER IDENTIFICATION METHODS AND J. A. MUlder, H. L. Jonkers, J. J. Horsten, J. H. Breeman, and THEIR APPLICATIONS: SURVEY AND FUTURE ASPECTS J. L. Simons In AGARD Parameter Identification Nov. 1979 P. G. Hamel In AGARD Parameter Identification Nov. 1979 87 p refs Prepared in cooperation with National Aerospace 26 p refs Lab.. Amsterdam Avail: NTIS HG A16/MF AOl Avail: NTIS HG A16/MF AOl
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An overview is presented of the nonsteady flight test R. A. Verbrugge, W. Charon, and M. Marchand )DFVLR. Brunswick) technique. Principal elements of this technique which is directed In AGARD Parameter Identification Nov. 1979 33 p refs towards time efficient and accurate determination of performance characteristics as well as stability and control characteristics from Avail: NTIS HC A16/MF AOl measurements in nonsteady or quasi-steady flight, are: application An overview of different experimental techniques used for of high quality flight test instrumentation systems: accurate parameter identification based on dynamic model tests in wind reconstruction of the aircraft's motions; identification of nonlinear tunnel or in free flight is presented. The specific domain of aerodynamic models; and calculation of performance, stability application is defined for each test technique. Particular aspects and control characteristics by correction of nonsteady or of semi-free and free model tests techniques in wind tunnel or quasi-steady flight conditions towards prespecified nominal laboratory experiences are described. Data processing from the conditions. Main emphasis is on a tutorial exposition of the first collection until the application of identification procedure is three of these elements. In addition to the tutorial presentation discussed in terms of (1) the nature and quality of the informa- some experimental results of various flight test programs are tion. (2) the data acquisition software. (3) the state vector presented. J.M.S. elaboration, and (4) some specific filter aspects and evaluation methods. A set of results illustrate each particular point. A review N8O19100*# National Aeronautics and Space Administration. of the present state of these techniques is given and future Hugh L. Dryden Flight Research Center, Edwards, Calif. field of application is discussed. R.E.S. AIRCRAFT IDENTIFICATION EXPERIENCE Kenneth W. luff In AGARD Parameter Identification Nov. N80-19104# Deutsche Forschungs- und Versuchsanstalt fuer 1979 35 p refs Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer Avail: NTIS NC A16/MF AOl CSCL O1C Flugmechanik. Important aspects of estimating the unknown coefficients of CLOSED LOOP ASPECTS OF AIRCRAFT IDENTIFICATION the aircraft equations of motion from dynamic flight data are R. Koehler and K. Wilhelm In AGARD Parameter Identification presented. The primary topic is the application of the maximum Nov. 1979 24 p refs likelihood estimation technique. Basic considerations that must be addressed in the estimation of stability and control derivatives Avail: NTIS HC A16/MF AOl from conventional flight maneuvers are discussed. Some complex Specific problems of system identification applied to highly areas of estimation (such as estimation in the presence of augmented aircraft with respect to flying qualities assessment atmospheric turbulence, estimation of acceleration derivatives, are discussed. An introduction to the influence of augmentation and analysis of maneuvers where both kinematic and aerodynamic system on dynamic response and flying qualities is given. The coupling are present) are also discussed. R.E.S. application of parameter estimation techniques to control loop systems and problems of control loop identification and equivalent system modellization are discussed. R.E.S. N80-19101// Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer N80-19105# Arinc Research Corp., Annapolis, Md. Flugmechanik. AVIONICS INTERFACE DATA SUMMARIES: A-10A. ROTORCRAFT IDENTIFICATION EXPERIENCE EF-111A. F-43, F-4G, F-15A, F-16A. F-111A. F-1I1E, F-111F. J. Kaletka In AGARD Parameter Identification Nov. 1979 RF-4C 32 p refs Oct. 1979 718p refs Avail: NTIS HC A16/MF AOl )Contract F33657-71-C-0567) An overview of the identification of stability and control (AD-A077388; derivatives of the rotorcraft with respect to practical aspects Rept- 1750-01 .2-2041) Avail: NTIS and applications is presented. First an introduction to the basic HC A99/MF AOl CSCL 01/3 dynamics and control of helicopters is given. The helicopter This document is one of a series of reports that describe characteristics causing difficulties in the identification are Avionics interfaces for various USAF aircraft. GRA discussed. Measurement and sensor problems are also discus- sed. Approaches to overcome the difficulties are presented. N80-19106# Naval Aerospace Medical Research Lab., Pensacola, Emphasis is placed on the following two key elements, of the Fla. identification procedure: ) 1) the selection of adequate mathemati- COMPARISON OF SPECIFICATIONS FOR HEAD-UP cal models and identifiable derivatives of the helicopter to isolate DISPLAYS IN THE NAVY A-4M. A-7E, AV-8A. AND F-14A significant model effects; and (2) possibilities of increasing the AIRCRAFT information content of flight test data by appropriate system Lawrence H. Frank Nov. 1979 65 p refs excitation and by multiple-run evaluations. Identification results )ZF51524004; SF55525401) obtained from simulated and flight test data of helicopters by )AD-A080047; NAMRL-SR-76-6) Avail: NTIS applying different identification methods are presented. R.E.S. NC A04/MF AOl CSCL 01/4 This report provides, within a single document, a compendium N80-19102# Royal Aircraft Establishment, Farnborough of data on Head-Up Displays (HUDs) in U.S. Navy and U.S. (England). Flight Systems Dept. Marine Corps aircraft that is germane to a Human Factors IDENTIFICATION EXPERIENCE IN EXTREME FLIGHT assessent of HUD design on pilot performance. The data in this REGIMES report are compiled from current Naval Air Training and Operating A. Jean Ross In AGARD Parameter Identification Nov. 1979 Procedures Standardization (NATO PS) manuals and design 15 p refs specifications for each of the HUD units. Operational HUDs were Avail: NTIS I-IC A16/MF AOl found to vary dramatically from each other and the military A mathematical model for identifying stability and control specification for HUDs, MIL-D-81641)AS), with respect to derivatives of fighter aircraft is presented. The principles of the symbology and formating. Furthermore, display clutter was statistical approach are described. The treatment of the nonlinear reported by pilots to be a major problem. A comprehensive terms is described and the tests which should be applied to information processing evaluation of virtual image symbols and assess the validity of the results are discussed. Selected results formating under dynamic conditions was recommended. Finally, from investigations of manoeuvres at high angles of attack are none of the current Navy aircraft has a HUD control panel that presented to show the types of problems which can be solved, complies to MIL-D-81641(AS), the military specification for and to illustrate some effects of nonlinearities. A.E.S. HUD5. Pilots are required to bring their eyes back into the cockpit to ensure proper switch selection and, consequently, negate the primary purpose of maintaining a head-up mode. GRA N80-19103# Institut de Mecanique des Fluides de Lille (France). N80-19107# Bunker-Ramo Corp.. Wright-Patterson AFB, Ohio. WIND TUNNEL AND FREE FLIGHT MODEL IDENTIFICA- FLIGHT PATH DISPLAYS Final Report, 15 Mar, - 1 Nov. TION EXPERIENCE 1978
241 N80-19109
A. Ogawa, Y. Sofue. and T. Isobe Oct. 1979 25 refs Debra A. Warner Jun. 1979 106 p refs p Transl. into ENGLISH of "Chukuyoku no Kozokaiseki.' Rept. (Contract F33615-78-C-3614; AF Proj. 2403) NAL-TR-533 NatI. Aerospace Lab., Tokyo, May 1977. 15 p (AD-A077181; AFFDL-TR-79-3075) Avail: NTIS Transl. by Kanner (Leo) Associates. Redwood City. Calif. HC A06/MF AOl CSCL 01/3 Aircraft display technology has advanced to the state where (Contract NASw-3 199) Avail: NTIS the flight path display--an integrated format on which both the (NASA-TM-75718; NAL-TR-533) vertical and horizontal path are graphically represented--is feasible. HC A02/MF AOl CSCL 21E This report researches efforts made to design flight paths for A torsional stress analysis of hollow fans blades by the use in both fixed wing and rotary wing aircraft. Results from finite element method is presented. The fans are considered to comparison evaluations of flight path and non-flight path displays be double circular arc blades, hollowed 30 percent, and twisted are discussed and conclusions drawn with respect to desirable by a component of the centrifugal force by the rated revolution. dsplay symbology. A hypothetical flight path display designed The effects of blade hollowing on strength and rigidity are as a result of the findings in the referenced studies is proposed discussed. The effects of reinforcing webs, placed in the hollowed section in varying numbers and locations, on torsional rigidity for future testing and evaluation. GRA and the convergence of stresses, are reported. A forecast of the 30 percent hollowing against torsional loadings is discussed. N80-19109// Calspan Advanced Technology Center, Buffalo, A.W.H. N.Y. Aerodynamic Research Dept. TESTS OF AN IMPROVED ROTATING STALL CONTROL SYSTEM ON A J-85 TURBOJET ENGINE Final Technical N80-191 12# Royal Aircraft Establishment. Farnborough Report, May 1976 - May 1979 (England). Gary R. Ludwig Wright-Patterson AFB, Ohio AFAPL Aug. CONTRIBUTION OF PHOTOELASTIC ANALYSIS TO THE 1979 76 p refs STUDY OF TURBO-ENGINE COMPONENTS (Contract F33615-76-C-2092; AF Proj. 3066) J. L. Guillo Nov. 1979 34 p Transl. into ENGLISH from (AD-A077704; CALSPAN-XE-5933-A-104; AGARD Conf. Proc. No. 248. Apr. 1979 AFAPL-TR-79-2060) Avail: NTIS NC A05/MF AOl CSCL (BR7 1985; RAE-Lib-Trans-2028) Avail: NTIS 21/5 HC A03/MF AOl This report presents the results of testing a fast-acting rotating Photoelastic measurements which determine the local stress stall control system on a J-85 turbojet engine under sea level concentrations, and the method of Stress freezing in the analysis static conditions, both with and without inlet distortion. The control of three dimensional stress states are discussed in relation to is an electronic feedback control system which uses unsteady jet engine components. The means employed for the prepara- pressure signals produced by pressure sensors within the tion and carrying Out of freezing operations and the equipment compressor to detect incipient rotating stall and provide a used in the operation are described. Examples of applying correction signal when such a condition occurs. On the J-85 photoelastic measurement and stress freezing operations are engine, the correction signal is used to drive a fast-response presented. Emphasis is placed on the determination of the stress hydraulic actuator which operates intermediate stage compressor intensity factor which governs crack propagation under cyclic bleed doors and inlet guide vane flaps. The performance of the stress application. A.W.H. stall control was tested by closing the bleed doors until rotating stall occurred or until the control anticipated stall and held the bleed doors open. The tests showed that the control is capable NBO-191 13*# Pratt and Whitney Aircraft Group, East Hartford, of anticipating stall before it occurs and keeping the engine Conn. Commercial Products Div. completely clear of stall at speeds up to 80 percent of design CORE COMPRESSOR EXIT STAGE STUDY. 1: AERODY- speed. No tests were performed above 80 percent of design NAMIC AND MECHANICAL DESIGN because opening the bleed doors at such speeds might aggravate E. A. Burdsall, E. Canal, Jr.. and K. A. Lyons Sep. 1979 128 p the stall rather than clear it. GRA ref (Contract NAS3-20578) N80_19110*# Nationar Aeronautics and Space Administration. (NASA-CR- 159714; PWA-556 1-55) Avail: NTIS Lewis Research Center, Cleveland, Ohio. NC A07/MF AOl CSCL 21E PRELIMINARY STUDY OF VTO THRUST REQUIREMENTS The effect of aspect ratio on the performance of core FOR A V/STOL AIRCRAFT WITH LIFT PLUS LIFT/CRUISE compressor exit stages was demonstrated using two three stage, PROPULSION highly loaded, core compressors. Aspect ratio was identified as George E. Turney and John L Allen Feb. 1980 23 p refs having a strong influence on compressors endwall loss. Both (NASA-TM-81429; E-351) Avail: NTIS HC A02/MF AOl CSCL compressors simulated the last three stages of an advanced 21E eight stage core compressor and were designed with the same A preliminary assessment was made of the VTO thrust 0.915 hub/tip ratio. 4.30 kg/sec (9.47 lbm/sec) inlet corrected requirements for a supersonic (Type 8) aircraft with a Lift plus flow, and 167 m/sec (547 ft/sec) corrected mean wheel speed. Lift/Cruise propulsion system. A baseline aircraft with a takeoff The first compressor had an aspect ratio of 0.81 and an overall gross weight (TOGW) of 13 608 kg (30.000 lb) was assumed. pressure ratio of 1.357 at a design adiabatic efficiency of 88.3% Pitch, roll, and yaw control thrusts (i.e.. the thrusts needed for with an average diffusion factor or 0.529. The aspect ratio of aircraft attitude control in the flight hover mode) were estimated the second compressor was 1.22 with an overall pressure ratio based on a specified set of maneuver acceleration requirements of 1.324 at a design adiabatic efficiency of 88.7% with an average for V/STOL aircraft. Other effects (such as installation losses, diffusion factor of 0.491. R.C.T. suckdown, reingestion, etc.), which add to the thrust requirements for VTO were also estimated. For the baseline aircraft, the excess thrust required for attitude control of the aircraft during VTO and flight hover was estimated to range from 36.9 to 50.9 percent N80-19114# American Inst. of Aeronautics and Astronautics, of the TOGW. It was concluded that the total thrust requirements New York. for the aircraft/ propulsion system are large and significant. In THE 4TH INTERNATIONAL SYMPOSIUM ON AIR BREATH- order to achieve the performance expected of this aircraft/ ING ENGINES propulsion system, reductions must be made in the excess thrust Apr. 1979 425 p refs Symp. held at Lake Buena Vista, requirements. J.M.S. Orlando, Fla., 1-6 Apr. 1979 (Grant N00014-77-G-0069) (AD-A078956( Avail: NTIS NC A18/MF AOl CSCL 21/5 N8019111*# National Aeronautics and Space Administration, Partial Contents: Inlet Flow Distortion; Operations/ Cost/ Washington, D. C. Maintenance; A eroelasticity/Vibrations; Systems Integration; STRUCTURAL ANALYSIS OF HOLLOW BLADES: TOR- Fuels and Combustion; 3 Dimensional Flow and Boundary SIONAL STRESS ANALYSIS OF HOLLOW FAN BLADES Layer/Shock Separation; Component Developements Compres- FOR AIRCRAFT JET ENGINES sors; and Ramjets. GRA
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N80-19115# Calspan Advanced Technology Center. Buffalo, multifunctional (i.e.. perform, in addition to control logic, data N.Y. Aerodynamic Research Dept. conditioning and fault diagnosis(. The development of such a BASIC STUDIES OF ROTATING STALL IN AXIAL FLOW full authority digital electronic controller must utilize demonstrated COMPRESSORS Final Report, Jun. 1976 - Apr. 1979 multivariable design techniques to integrate adequately these Gary R. Ludwig and Joseph P. Nenni Sep. 1979 150 p refs Complex system functions. A preliminary design of a controller (Contract F33615-76-C-2092; AF Prol. 3066) for this variable cycle engine is described. It is implementable (AD-A077690; CALSPAN-XE-5933-A-105; on a small digital computer (less than 16K words of storage). AFAPL-TR-79-2083) Avail: NTIS NC A07/MF AOl CSCL and is modular in design (subroutine format). Specific controller 21/5 functions of transient regulation, steady state regulation, trajectory This report presents the results of a theoretical and experimen- generation, signal processing, and fault detection and accommoda- tal program aimed at obtaining a sufficient understanding of the tion are incorporated in a way which allows experimentation rotating stall phenomena such that its onset and properties can with different techniques for each function without affecting the be predicted under a wide set of circumstances. The theoretical overall structure. Promising techniques for implementing each research covers the development of two dimensional stability function are discussed. GRA theories for compressible flows and the progress towards the development of a three dimensional theory for incompressible flow. The experimental work, performed in an annular cascade N80-19118# General Electric Co.. Cincinnati, Ohio. Aircraft Engine Group. facility, studied the effects of rotorstator interference both on the steady-state performance of the blade rows and on rotating NOVEL CERAMIC TURBINE ROTOR CONCEPTS Final stall. The influence of circumferential distortion on the rotating Technical Report, 22 Sep. 1978 - 22 May 1979 stall boundary for the stage was also determined. Comparisons L. J. Stoffer Wright-Patterson AFB. Ohio AFAPL Sep. 1979 93 refs are made between the experimental results and the predictions p (Contract F33615-78-C-2041; AF Proj. 3066) of a two dimensional rotating stall stability theory which had been developed previously for incompressible flows. GRA (AD-A078669; 879AEG527; AFAPL-TR-79-2074) Avail: NTIS NC A05/MF AOl CSCL 21/5 A novel design concept for a ceramic turbine rotor has been N80-19116# Caispan Advanced Technology Center, Buffalo. studied in detail for a non-man-rated, limited-life gas turbine N.Y. Aerodynamic Research Dept. engine application. The feature of the design involves keeping AERODYNAMIC AND ACOUSTIC INVESTIGATIONS OF the rotating ceramic components in a compression state at all AXIAL FLOW FAN AND COMPRESSOR BLADE ROWS, turbine operating conditions. An air-cooled composite material INCLUDING THREE-DIMENSIONAL EFFECTS Final Report, containment hoop is utilized at the outer diameter of ceramic 1 Jun. 1976 - 31 Mar. 1979 air-cooled fins which support ceramic turbine blades in compres- Gregory F. Homicz, John A. Lordi. and Gary R. Ludwig Aug. sion against a radially compliant wheel. The design study of this Compression Structured Ceramic Turbine Rotor included 1979 145 p refs (Contract F33615-76-C-2092; AF Proj. 3066) detailed material, heat transfer, and 3-0 stress analyses. The (AD-A077712; CALSPAN-XE-5933-A- 103; study effort also looked at the operational limits of the design AFAPL-TR-79-2061( Avail: NTIS HC A07/MF AOl CSCL and a performance and economic analysis comparison to a baseline 21/5 metal design Conclusions and recommendations for future This report presents the results of a program designed to development are also presented in this report. GRA study the influence of three-dimensional effects on the aerodyna- mics and acoustics of axial flow fans and compressors. To avoid numerical solutions of the full nonlinear three-dimensional N80-19119# General Electric Co.. Cincinnati. Ohio. Aircraft equations, a linearized analysis is employed. This is first applied Engine Group. to the determination of the steady loading on a three-dimensional EVALUATION OF FUEL CHARACTER EFFECTS ON J79 annular blade row with a prescribed chamber line in inviscid ENGINE COMBUSTION SYSTEM Final Technical Report, compressible flow. The blades are represented by pressure dipole 7 Jun. 1977 - 31 Aug. 1978 singularities in a lifting-surface formulation, and a collection C. C. Gleason, T. L. OIler, M. W. Shayerson, and D. W. Bahr procedure is presented for inverting the resulting integral equation. Jun. 1979 198 p refs Comparisons are presented between the present results and those (Contract F33615-77-C-2042; AF Proj 3048) of two-dimensional strip theory and an inverse three-dimensional (AD-A078440; R79AEG32 1; AFAPL-TR-79-201 5; theory. Next the analysis is extended to the case of unsteady CEEDO-TR-79-06( Avail: NTIS NC A09/MF AOl CSCL flow through the rotor, such as might be caused by inflow distortion 21/5 or blade flutter. The integral equation for this case is somewhat Results of a program to determine the effects of broad more complicated, but appears to be solvable by a suitable variations in fuel properties on the performance, emissions, and extension of the procedure developed in the steady problem. durability of the J79-17A turbojet engine combustion system Finally, further comparisons are presented between a theoretical are presented. Combustor tests conducted at engine idle, takeoff, model of rotor-stator interaction noise developed under a previous subsonic cruise, supersonic dash, cold day ground start, and program and a current series of measurements made in an altitude relight operating conditions with 13 different fuels are GRA annular cascade facility. described. The test fuels covered a range of hydrogen contents (12.0 to 14.5 percent), aromatic type (monocyclic and bicyclic), N80-19117# Systems Control, Inc.. Palo Alto, Calif. initial boiling point (285 to 393 K). final boiling point (552 to VARIABLE CYCLE ENGINE MULTIVARIABLE CONTROL 679 K( and viscosity (0.83 to 3.26 mm2/s at 300 K(. At high SYNTHESIS: CONTROL STRUCTURE DEFINITION Interim power operating conditions, fuel hydrogen content was found to Report, 1 Sep. 1977 - 31 Aug. 1978 be a very significant fuel property with respect to linear Stephen M. Rock and Ronald L. DeHoff Feb. 1979 174 p temperature, flame radiation, smoke, and NO sub x emission refs levels. Carbon monoxide and HC emissions were very low at (Contract F33615-77-C-2096; AF Proj. 3006) these conditions with all of the fuels. At engine idle operating )AD-A078670; AFAPL-TR-79-2043( Avail: NTIS conditions. CO. NC. and NO sub a emission levels were found HC A08/MF AOl CSCL 21/5 to be independent of fuel hydrogen content, but a small effect The variable cycle aircraft turbine engine. GE23-JTDE. of fuel volatility and/or viscosity was found. At cold day ground represents a prototype of future multimode propulsion plants. It start conditions (to 329 K) lightoff was obtained with all fuels, is a sophisticated design of highly variable geometry and multiple but the required fuel-air ratio increased with the more viscous control inputs. To control this engine, a large number of engine fuels. At altitude conditions, the current engine relight limits variables must be sensed. These include engine pressures, with JP-4/JP-5 fuel were essentially met or exceeded with all temperatures, rotor speeds, and airframe and inlet commands. of the JP-4 or JP-8 based fuel blends. However, a very significant A controller for this engine must therefore be multivariable (i.e.. reduction in altitude relight capability was found when a No. 2 manipulating large numbers of input and output variables) and diesel fuel was tested. GRA
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N80-19120# Pratt and Whitney Aircraft Group. West Palm M. E. Wilton Nov. 1979 235 p refs Beach. Fla. Government Products Div. (Contract N00140-76-C-1072) INVESTIGATION OF FAN BLADES SHROUD MECHANICAL (AD-A078436; R78AEG314) Avail: NTIS HC Al l/MF AOl DAMPING CSCL 17/5 Donald A. Rimkunas and H. Murray Frye Jun. 1979 79 p Current infrared-guided missiles can detect and destroy aircraft refs from relatively long distances. Future IR missiles will be even (Contract F33615-77-C-2086; AF Proj. 2307) more sensitive and destructive. The engine designer must select (AD-A078439; PWA-FR-1 1065; AFAPL-TR-79-2054) Avail: cycles and engine configurations that present as small a target NTIS HC A05/MF AOl CSCL 21/5 as possible to these missile threats. To accomplish this, he must This program was conducted to investigate the effect of dry know the IR emissions from the aircraft and be able to judge friction damping at the shroud interfaces on the structural dynamic the success of schemes to suppress these emissions. Measure- characleristics of shrouded fan blades typical of current high ments are invaluable in determining the IR emissions for selected performance jet engines. An analytical definition of the loads aircraft situations but cannot possibly be made for all aircraft generated at the shroud faces for a general stick-slip condition and for all situations. This is obviously true in the engine design was developed. The analytical load description includes the elastic phase. In addition, understanding of the fundamental sources of case of a stuck or locked shroud as well as the case of a these emissions is essential to the invention or evaluation of slipping shroud. These loads were used in a non-linear steady- new suppression concepts. An accurate prediction pool, therefore, state vibration analysis of the shrouded blade. Controlled vibration is vital to the process of reducing the vulnerability of an aircraft testing of the first-stage fan blade with a trailing edge shroud to IR-guided missiles. As a supplier of jet engines for military of a YF100 (prototype) turbofan engine was conducted. The aircraft, the General Electric Company has developed a series of blade was tested with variable shroud restraints to simulate the Computer programs to predict the IR signatures and vulnerability full range of boundary conditions from freely slipping to fully of lR'guided missiles. The SCORPIO-N computer program locked, including the intermediate condition of micro-Slipping. presented in this report is the latest in the series. It is an Outgrowth The testing of the blade with a freely slipping shroud was of the SCORPIO-lIlA program (Reference 1) and the SPRITE inconclusive because of repeatability problems. Good agreement program (Reference 2) with improvements to the plume module was found between the nonlinear analysis and test data for the which permit studies of truly three-dimensional flow fields. GRA stuck and micro-slip boundary conditions. GRA
N80-19122# Air Force Inst. of Tech.. Wright-Patterson AFB. N8O-19125# Vought Corp., Dallas, Tex. Ohio. School of Systems and Logistics. POWER SYSTEM CONTROL STUDY. PHASE 1: INTEGRAT- AN ANALYSIS AND SYNTHESIS OF ENGINE CONDITION ED CONTROL TECHNIQUES Interim Report, 1 Jul. MONITORING SYSTEMS M.S. Thesis 1978 - 15 Jun. 1979 Jack W. Chapman, Jr. and Charles L. Page. Jr. Sep. 1979 D. E. Lautrier, A. J. Marek, and J. R. Perkins Wright- Patterson 138 p refs AFB, Ohio AFAPL Jun. 1979 240 p refs (AD-A07753 1; AFIT-LSSR-27-79B) Avail: NTIS (Contract F33615-78-C-2018; AF Proj 3145) HC A07/MF AOl CSCL 21/5 (AD-A078629; AFAPL-TR-79-2084( Avail: NTIS Engine condition monitoring systems have been developed HC A11/MF AOl CSCLO1/3 to assist flight line maintenance activities and aid in the transition This report documents the Phase 1 results of a two phase of aircraft engine maintenance philosophy from that of maximum study program which addresses the integration of advanced power operating time to reliability centered or on condition maintenance. system control technologies into a reliable and fault tolerant This study includes a comprehensive review of past, current, system. The advanced control technologies integrated include and proposed Air Force applications of turbine engine monitoring electric engine start, automatic load management, microproces- systems to describe the major features of TEMS. Engine sor control implementations, design techniques for providing performance data output from TEMS to the various engine 'no-gap' power and an all 'solid state' electric power distribution management functions are analyzed. The authors conclude that system. Electric system performance requirements are established TEMS data and the existing or proposed engine management and preliminary designs of an integrated 'baseline' control system systems are not directly compatible. Moreover, the analysis for single and multiengine aircraft for the 1990 operational time indicates that implementation of TEMS and an on condition period are presented. Finally, stability analysis requirements and maintenance policy would require a greatly expanded data base procedures are established for each of the two designs. During to accomplish the required engine management record keeping, Phase 2. detail design of the power control system will be monitoring, and forecasting tasks. Several recommendations are completed and a stability analysis will be conducted. GRA offered for interfacing TEMS with the engine management systems. Areas for further research are suggested. GRA N80-19126# National Aeronautics and Space Administration. N80-19123// AiResearch Mfg. Co.. Phoenix, Ariz. Ames Research Center, Moffett Field, Calif. DEMONSTRATION PROGRAM FOR A FLEXIBLE DUCT APPLICATION OF THE CONCEPT OF DYNAMIC TRIM VALVE FOR RAMJET ENGINE FUEL CONTROLS Final CONTROL TO AUTOMATIC LANDING OF CARRIER Report, 15 Nov. 1978 - 28 Feb. 1979 AIRCRAFT James S. Roundy 14 Sep. 1979 67 p refs G. Allan Smith and George Meyer Apr. 1980 87 p refs (Contract N62269-77-C-0352) (NA5A-T p-1512; A-7801( Avail: NTIS HC A05/MF AOl CSCL (AD-A078529; AiResearch-4 1-2226; NADC-77 136-60) Avail: O1C NTIS HC A04/MF AOl CSCL 21/5 The results of a simulation study of an alternative design A demonstration program was conducted to develop a flex concept for an automatic landing control system are presented. duct-type metering valve for use in the fuel control of ramjet The alternative design concept for an automatic landing control engines for Navy missiles. This type valve has inherent advantages system is described. The design concept is the total aircraft of simplicity, low cost, and high reliability that make it parti- flight control system (TAFCOS(. TAFCOS is an open loop, feed cularly attractive for this application. This type valve functions forward system that commands the proper instantaneous thrust, best when the leakage flow from the metering gap is bypassed angli of attack, and roll angle to achieve the forces required to back upstream of the fuel pump. GRA follow the desired trajector. These dynamic trim conditions are determined by an inversion of the aircraft nonlinear force characteristics. The concept was applied to an A-7E aircraft N80-19124# General Electric Co., Cincinnati, Ohio. Aircraft approaching an aircraft carrier. The implementation details with Engine Group an airborne digital computer are discussed. The automatic ADVANCED INFRARED SIGNATURE PREDICTION PRO- carrier landing situation is described. The simulation results are GRAM. SPECTRAL CALCULATION OF RADIATION FROM presented for a carrier approach with atmospheric disturbances, A TURBINE PROPULSION SYSTEM AS INTERCEPTED BY an approach with no disturbances, and for tailwind and headwind AN OBSERVER (SCORPION). VOLUME 3: ANALYSIS gusts. AWl-I.
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N80,19127*// National Aeronautics and Space Administration. N80-19130# Federal Aviation Administration, Washington, D. C. Ames Research Center, Moffett Field, Calif. NONDESTRUCTIVE EVALUATION OF AIRPORT PAVE- FLIGHT EVALUATION OF CONFIGURATION MANAGE- MENTS. VOLUME 2: OPERATIONAL MANUAL FOR MENT SYSTEM CONCEPTS DURING TRANSITION TO THE PAVBEN PROGRAM AT TCC Final Report LANDING APPROACH FOR A POWERED-LIFT STOL David Yang Sep. 1979 123 p AIRCRAFT (Contract DOT-FA77WA-3964) James A. Franklin and Robert C. Innis Mar. 1980 32 p refs )AD-A079495; FAA-RD-78-154-Vol-2) Avail: NTIS (NASA-TM-81146; A-7957) Avail: NTIS HC A03/MF AOl HC A06/MF AOl CSCL 01/5 CSCL O1C The operation of PAVBEN program is presented. The job Flight experiments were conducted to evaluate two control inputs consist of: (1) field data; (2) types of existing pavements; concepts for configuration management during the transition to (3) facility classifications; (4) demand forecast and (5) local cost landing approach for a powered-lift STOL aircraft. NASA Ames values. The default system contains all design data for: (1) 15 air augmentor wing research aircraft was used in the program. transports; (2) 9 FAA regional cost values. (3) 8 types of pavement Transitions from nominal level-flight configurations at terminal design; (4) 22 layer components; (5) 20 types of existing pavement area pattern speeds were conducted along straight and curved and (6) universal mechanistic design model. The major Outputs descending flightpaths. Stabilization and command augmentation will be: (1) NOT inventory file; (2) present functional life; for attitude and airspeed control were used in conjunction with (3) computed engineering data: (4) pavement thickness and cost a three-cue flight director that presented commands for pitch, data and (5) cost/benefit analysis for four new pavements, three roll, and throttle controls. A prototype microwave system provided overlays and three keel Constructions. The program is written in landing guidance. Results of these flight experiments indicate a high level language FORTRAN IV. R.E.S. that these configuration management concepts permit the successful performance of transitions and approaches along curved N8O19131*# National Aeronautics and Space Administration. paths by powered-lift STOL aircraft. Flight director guidance Langley Research Center. Langley Station, Va. was essential to accomplish the task. Author A THEORETICAL ANALYSIS OF SIMULATED TRANSONIC BOUNDARY LAYERS IN CRYOGENIC-NITROGEN WIND N80-19128// Systems Research Labs.. Inc., Dayton. Ohio. TUNNELS HANDLING QUALITY REQUIREMENTS FOR ADVANCED Jerry B. Adcock and Charles B. Johnson Mar. 1980 40 p AIRCRAFT DESIGN LONGITUDINAL MODE Final Report, refs Feb. 1977 - Aug. 1978 (NASA-TP-1631; L-13364) Avail: NTIS HC A03/MF AOl Ralph H. Smith and Norman D. Geddes Aug 1979 185 p CSCL 148 refs A theoretical analysis was made to determine the real gas (Contract F33615-77-C-3011; AF Proj. 2090) effects on simulation of transonic boundary layers in wind tunnels (AD-A077858; AFFDL-TR-78- 154) Avail: NTIS with cryogenic nitrogen as the test gas. The analysis included HC A09/MF AOl CSCL 01/3 laminar and turbulent flat plate boundary layers and turbulent This report considers the problem of developing handling boundary layers on a two dimensional airfoil. The results indicate qualities specifications for aircraft with nonclassical dynamic that boundary layers in such wind tunnels should not be response to control. These include closed loop flight control system substantially different from ideal gas boundary layers at standard effects on basic airframe dynamics, direct force control applica- conditions. At a pressure of 9.0 atm, two separate effects produce tions, digital flight control, integrated fire-flight control, and deviations of real gas values from ideal gas values which are in integrated display-flight control. Only the longitudinal mode is the opposite direction from deviations at 1.0 atm and are of considered. Elements of classic pilot-vehicle analysis methodology the same insignificant order of magnitude. Results also show are distilled against a theoretical framework for the prediction that nonadiabatic boundary layers should be adequately simulated of pilot opinion rating to develop a simplified and practical if the enthalpy ratio is the correlating parameter rather than the approach to handling qualities prediction that is directly applicable temperature ratio. J.M.S. to the development of specificatons for aircraft flight ccntrol system design. The most important effects of motion cues on N80-19132# National Aeronautics and Space Administration. handling qualities are included within this model. The methods Langley Research Center, Langley Station. Va. proposed for the prediction and correlation of handling qualities DESIGN CONSIDERATIONS FOR ATTAINING 250-KNOT are validated against the largest and most appropriate base of TEST VELOCITIES AT THE AIRCRAFT LANDING DYNAMICS handling qualities data available; the agreement is nearly FACILITY 100 percent. GRA C. E. Gray, Jr.. R. E. Snyder, J. T. Taylor. A. Cires, A. L. Fitzgerald. and M. F. Armistead Feb. 1980 29 p refs N80-19129# Naval Academy, Annapolis. Md. (NASA-TM-80222( Avail: NTIS HC A03/MF AOl CSCL MICROF.00ESSOR CONTROL OF LOW SPEED V/STOL 14B FLIGHT Final Report. 1978 - 1979 Preliminary design studies are presented which consider the Robert V. Walters 8 Jun. 1979 203 p refs important parameters in providing 250 knot test velocities at (AD-A077661: USNA-TSPR- 100) Avail: NTIS the Aircraft Landing Dynamics Facility. Four major Components HC A10/MF AOl CSCL 01/4 of this facility are: the hydraulic jet catapult, the test carriage This paper considers the design of an improved three-axis structure, the reaction turning bucket, and the wheels. Using stability augmentation system (SAS( for the AV-8B Advanced the hydraulic-jet catapult characteristics, a target design point Harrier V/ STOL aircraft using microprocessor-based digital control. was selected and a carriage structure was sized to meet the It focuses on improving the handling qualities of the airplane required strength requirements. The preliminary design results through SAS redesign in the low speed flight regime. Particular indicate that to attain 250 knot test velocities for a given hydraulic attention is paid to the so-called 'weather-cocking' instability jet catapult system, a carriage mass of 25,424 kg (56.000 Ibm.) encountered in transition (hover to/from conventional) flight. There cannot be exceeded. R.E.S. was a dearth of information about the Harrier's flight characteristics until the development of MCAIR's X22A AV-881 mathematical model. which yielded a set of linearized stability derivatives for N80- 191 33*# National Aeronautics and Space Administration, the aircraft. The first step toward improvement of the AV-8131 Washington, D. C. SAS requires the use of these coefficients in the development METHODS OF SOUND SIMULATION AND APPLICATIONS of an analog/hybrid model of both the aircraft itself and of the IN FLIGHT SIMULATORS unmodified SAS. The controller design uses digital state feedback K.-P. Gaertner Jan. 1980 98 p refs Transl. into ENGLISH control to relocate the system closed loop poles. It is concluded of "Methoden der Gerawuschsimulation und ihre Anwendung in that this method of control represents a valid approach to the Flugsimulatoren", Rept . 22, Gesellschaft zur Foederund der final solution of the Harrier's stability and control problems and Astrophysikalischen forschung E. V., Forschungsinstitut fuer that this controller design Concept might be applied to future Antropotechnik, Meckenheim, West Germany. Apr. 1975 aerospace vehicles. GRA 105 p Translation was announced as N77-29179 Transl. by
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Kanner (Leo) Associates. Redwood City. Calif. (LUDWIEG TUBE. EVANS CLEAN TUNNEL AND INJECTOR (Contract NASw-3199) DRIVEN TUNNEL) (NASA-TM-75768: Rept-22) Avail: NTIS HC A05/MF AOl P. G. Pugh, H. Grauer-Carstensen )DFVLR. Goettingen. West CSCL 14B Germany). and C. Quemard (CERT. Toulouse) In AGARD Towards An overview of methods for electronically synthesizing New Transonic Windtunnels Nov. 1979 23 p refs sounds is presented. A given amount of hardware and computer capacity places an upper limit on the degree and fidelity of Avail: NTIS HC A05/MF AOl realism of sound simulation which is attainable. Good sound Flow quality in three wind tunnels with differing drive systems realism for aircraft simulators can be especially expensive because is examined. The investigation included measurements of of the complexity of flight sounds and their changing patterns (1) fluctuating static pressure on the sidewall of the test section; through time. Nevertheless, the flight simulator developed at the (2) turbulence immediately upstream of the contraction and in Research Institute for Human Engineering, West Germany. shows the test section: (3) fluctuations of flow angle (both pitch and that it is possible to design an inexpensive sound simulator yaw) in the test section: and (4) fluctuations of both pitot and with the required acoustic properties using analog computer static pressures in the test Section flow. Factors important to elements. The characteristics of the sub-sound elements produced the description of wind tunnel flow quality are also discussed. It by this sound simulator for take-off, cruise and approach are is shown that the use of fluctuating static pressure as in index discussed. Author of flow quality in invalid when comparing wind tunnels having different forms of drive system or, possibly, even widely different N80-19135# ARO. Inc.. Arnold Air Force Station. Tenn. types of test section. Fluctuations in flow angle are of much LASER-RAMAN FLOW-FIELD DIAGNOSTICS OF TWO more direct consequence to the gathering of the usual types of LARGE HYPERSONIC TEST FACILITIES Final Report, data and can be measured using either appropriately designed 13 Apr. 1977 - 10 Jul. 1978 yawmeters or with hot-film probes. M. H. W. D. Williams. D. A. Wagner. H. M. Powell. and L. L. Price AEDC Dec. 1979 41 p refs N80, 19139*# National Aeronautics and Space Administration. (AD-A078289; AEDC-TR-7988) Avail: NTIS Langley Research Center, Langley Station, Va. HC A03/MF AOl CSCL 14/2 DEVELOPMENT OF THE CRYOGENIC TUNNEL CONCEPT Laser-Raman scattering has been utilized to discover AND APPLICATION TO THE US NATIONAL TRANSONIC nonequilibrium N2 vibrational levels in a Continuous, resistance- FACILITY heated wind tunnel (Tunnel C) and in an arc-heated wind tunnel Robert A. Kilgore In AGARD Towards New Transonic (Tunnel F). Vibrational temperatures of up to two times the bulk Windtunnels Nov. 1979 27 p refs reservoir temperature have been measured in the Tunnel F free stream. A double-diaphragm device for delay of the Tunnel F Avail: NTIS HC A05/MF AOl CSCL 14B nozzle expansion was found to significantly reduce the vibrational A fan-driven, high Reynolds number, transonic cryogenic wind temperature level. In tunnel C. the vibrational temperatures were tunnel is described. The tunnel has a 2.5- by 2.5 m test section found to be dependent upon the water vapor concentration in and is capable of operating from ambient to cryogenic tempera- the flow. It is hypothesized that water vapor-induced de-excitation tures at stagnation pressures up to 8.8 atm. An overview of of the vibrationally excited nitrogen molecules results in a the cryogenic concept and discussions of drive power require- significant rise in local static temperature and corresponding ments, support systems, and operating characteristics and reduction in Mach number. GRA performance of the wind tunnel are included. M.G.
N80-19136# Air Force Flight Dynamics Lab., Wright-Patterson AFB, Ohio. N80- 191 40# National Aerospace Lab.. Amsterdam (Netherlands). THE HISTORY OF STATIC TEST AND AIR FORCE STRUC- THE CRYOGENIC WIND TUNNEL: ANOTHER OPTION FOR TURES TESTING Final Technical Report THE EUROPEAN TRANSONIC FACILITY Bernard C. Boggs Jun. 1979 299 p refs J. P. Hartzuiker, J. Christophe )ONERA. Paris), W. Lorenz-Meter )AD-A077029: AFFDL-TR-79-307 1) Avail: NTIS (DFVLR. Goettingen. West Germany), and P. G. Pugh (RAE. HC A13/MF AOl CSCL 14/2 Bedford, England) In AGARD Towards New Transonic Wintunnels This report traces the history of aircraft static testing from Nov. 1979 15 p refs its early beginning and follows the development of structures testing in the United States Air Force from 1917 to 1979. Avail: NTIS HC A05/MF AOl Those technologies that are related to structures testing are A cryogenic wind tunnel concept is discussed. The tunnel included which were important to airplane structures strength. should have a maximum stagnation pressure of 6 bars. 10 seconds Test technology development which provided test facilities, tests running time, and the Reynolds number (based on mean systems and test methods are covered for the static, dynamic, aerodynamic chord) should be variable between 25 and 40 million, fatigue, and environmental simulation of subsonic, sonic, to enable extrapolation of test results to full scale Conditions. supersonic, hypersonic and re-entry aircraft missions. GRA The advantages and drawbacks of cryogenic testing as well as fundamental aspects of cryogenic aerodynamics are discussed. Advisory Group for Aerospace Research and Comparative estimates for capital and operating costs are finally N80-19137# presented. Development. Paris (France). M.G. TOWARD NEW TRANSONIC WINOTUNNELS J. P. Hartzuiker, ed. (National Aerospace Lab., Amsterdam) Nov. 1979 78 p refs 93*// (AGARD-AG-240: ISBN-92-835-1343-6) Avail: NTIS N80- 191 National Aeronautics and Space Administration. HC A05/MF AOl Langley Research Center, Langley Station, Va. Cryogenic concepts for transonic wind tunnels are examined ASSESSMENT OF CARBON FIBER ELECTRICAL EFFECTS including discussions of tunnel drive and support systems, tunnel Washington Mar. 1980 278 p refs Conf. held in Hampton. performance, and cryogenic aerodynamics. Also presented is an Va., 4-5 Dec. 1979 investigation of the flow quality of three transonic tunnels with (NASA-CP-21 19: L-13503) Avail: NTIS HC A13/MF AOl differing drive mechanisms. Factors effecting a more complete CSCL liD determination of tunnel flow quality are discussed. 'he risks associated with the use of carbon fiber composites in civil aircraft are discussed along with the need for protection of civil aircraft equipment from fire-released carbon fibers. The size and number of carbon fibers released in civil aircraft crash fires, N80-19138# Royal Aircraft Establishment, Bedford (England). the downwind dissemination of the fibers, their penetration into AN INVESTIGATION OF THE QUALITY OF THE FLOW buildings and equipment, and the vulnerability of electrical/ GENERATED BY THREE TYPES OF WIND TUNNEL electronic equipment to damage by the fibers are assessed.
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N80_19194*// National Aeronautics and Space Administration. The impact of the entry of graphite fibers into workplaces Langley Research Center, Langley Station, Va. in the United States is discussed. Areas where an electrical APPROACH TO THE ASSESSMENT OF THE HAZARD failure could cause major problems include process and production Robert J. Huston In its Assessment of Carbon Fiber Elec. Effects systems, hospitals, and police/fire emergency communication Mar. 1980 p 11-27 refs systems. K. L.
Avail: NTIS NC A13/MF AOl CSCL liD N8019200*// Operations Research. Inc.. Silver Spring. Md. An overview of the carbon fiber hazard assessment is ASSESSMENT OF THE RISK DUE TO RELEASE OF CARBON presented. The potential risk to the civil sector associated with FIBER IN CIVIL AIRCRAFT ACCIDENTS, PHASE 2 the accidental release of carbon fibers from aircraft having Leon S. Pocinki, Merrill E. Cornell. and Lawrence Kaplan In Composite structures was assessed along with the need for NASA. Langley Res. Center Assessment of Carbon Fiber Elec. protection of civil aircraft from carbon fibers. K. L. Effects Mar. 1980 p 157-182 refs
N8O- 19195*1/ National Aeronautics and Space Administration. (Contract NAS1-15379( Langley Research Center. Langley Station. Va. Avail: NTIS NC A13/MF AOl CSCL liD RELEASE OF CARBON FIBERS FROM BURNING COM- The risk associated with the potential use of carbon fiber POSITES composite material in commercial jet aircraft is investigated. A Vernon L. Bell In its Assessment of Carbon Fiber Elec. Effects simulation model developed to generate risk profiles for several airports is described. The risk profiles show the probability that Mar. 1980 p 29-57 the cost due to accidents in any year exceeds a given amount. Avail: NTIS NC A13/MF AOl CSCL liD The computer model simulates aircraft accidents with fire, release The results of a burn/explosion test program are presented. of fibers, their downwind transport and infiltration of buildings, The amount of fiber released and the physical characteristics of equipment failures, and resulting ecomomic impact. The individual the fibers are among the data reported. K. L. airport results were combined to yield the national risk profile. A.W,H. N8O19196*// National Aeronautics and Space Administration. N8019201*// Little (Arthur D.(. Inc.. Boston. Mass. Langley Research Center. Langley Station, Va. ASSESSMENT OF RISK DUE TO THE USE OF CARBON DISSEMINATION, RESUSPENSION, AND FILTRATION OF FIBER COMPOSITES IN COMMERCIAL AND GENERAL CARBON FIBERS AVIATION Wolf Elber In its Assessment of Carbon Fiber Elec. Effects J. Fiksel, Donald Rosenfield, and A. Kalelkar In NASA. Langley Mar. 1980 59-71 p Res. Center Assessment of Carbon Fiber Elec. Effects Mar. 1980 183 . 211 refs Avail: NTIS HC A13/MF AOl CSCL 110 p Carbon fiber transport was studied using mathematical models Avail: NTIS NC A13/MF AOl CSCL 110 established for other pollution problems. It was demonstrated The development of a national risk profile for the total annual that resuspension is not a major factor contributing to the risk. aircraft losses due to carbon fiber composite (CFC) usage through Filtration and fragmentation tests revealed that fiber fragmentation 1993 is discussed. The profile was developed using separate shifts the fiber spectrum to shorter mean lengths in high simulation methods for commercial and general aviation aircraft. velocity air handling systems. K. L. A Monte Carlo method which was used to assess the risk in commercial aircraft is described The method projects the N8O19197*# Bionetics Corp.. Hampton, Va. potential usage of CEC through 1993, investigates the incidence EVALUATION OF EQUIPMENT VULNERABILITY AND of commercial aircraft fires, models the potential release and POTENTIAL SHOCK HAZARDS dispersion of carbon fibers from a fire, and estimates potential Israel Taback In NASA. Langley Res. Center Assessment of economic losses due to CFC damaging electronic equipment. Carbon Fiber Elec. Effects Mar. 1980 p 73-99 The simulation model for the general aviation aircraft is described. The model emphasizes variations in facility locations and release Avail: NTIS HC A13/MF AOl CSCL 110 conditions, estimates distribution of CFC released in general The vulnerability of electric equipment to carbon fibers aviation aircraft accidents, and tabulates the failure probabilities released from aircraft accidents is investigated and the parameters and aggregate economic losses in the accidents. A.W.H. affecting vulnerability are discussed. The shock hazard for a hypothetical set of accidents is computed. K. L. N8019202*# National Aeronautics and Space Administration. N80-19198t # National Aeronautics and Space Administration. Langley Research Center. Langley Station, Va. Langley Research Center, Langley Station, Va. PERSPECTIVE ON THE RESULTS LARGE-SCALE FIBER RELEASE AND EQUIPMENT EXPO- Robert J Huston In its Assessment of Carbon Fiber Elec. Effects SURE EXPERIMENTS Mar. 1980 p 213-223 refs R. A. Pride In its Assessment of Carbon Fiber Elec. Effects Mar. 1986 p 101-136 refs Avail: NTIS NC A13/MF AOl CSCL 110 The results of studies on the risk due to the use of carbon Avail: NTIS HC A13/MF AOl CSCL 11 fibers in aircraft are assessed. Assumptions such as additional Outdoor tests were conducted to determine the amount of fire protection in the aircraft, new structural concepts, and the fiber released in a full scale fire and trace its dissemination development of unique carbon composites are evaluated. Some away from the fire. Equipment vulnerability to fire released fibers findings from the national risk profile including equipment was assessed through shock tests. The greatest fiber release vulnerability and economic impact are discussed. A.W.H. was observed in the shock tube where the composite was burned with a continuous agitation to total consumption. The largest average fiber length obtained outdoors was 5 mm K. L. N80-19239# Colt Industries, Inc.. Pittsburgh, Pa. Crucible Materials Research Center. N8O19199*// Bionetics Corp., Hampton, Va. CONSOLIDATION OF TITANIUM POWDER TO NEAR NET SURVEYS OF FACILITIES FOR THE POTENTIAL EFFECTS SHAPES Final Report, 1 Feb. 1974 - 1 Mar. 1978 FROM THE FALLOUT OF AIRBORNE GRAPHITE FIBERS J. H. Schwertz, V. K. Chandhok, V. C. Peterson, and V. R. Thompson Ansel J. Butterfield In NASA. Langley Res Center Assessment May 1978 333 p refs of Carbon Fiber Elec. Effects Mar. 1980 p 137-149 (Contract F33615-74-C-5114) (AD-A078039; AFM L-TR-78-4l ( Avail: NTIS Avail: NTIS NC A13/MF AOl CSCL 110 NC A15/MF AOl CSCL 11/6
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This program was conducted to develop the technology A major problem with instrument landing system slide path necessary to establish a cost effective approach to the production is the dependence of the signal quality upon site conditions. of titanium alloy parts for both aircraft engine and airframe Unwanted scattering from the surroundings causes error in the applications. This approach was based on a PM near-net shape guidance signal. A new method to analyze the problem is process utilizing ceramic mold techniques in conjunction with described. For practical use, the surroundings are modeled as a HIP (Hot Isostatic Pressing) to a minimum machining envelope. set of plane wedges. The scattering from each wedge is Program objectives included: (1) the optimization of an existing analyzed using uniform theory of diffraction (UTD), which assumes PM process for the HIP of near-net shapes of titanium using smooth, sharp and perfectly conducting wedges. Theoretical and low-cost tooling: (2) the reduction of the process to an efficient, practical work was carried Out to study the influence of finite cost effective, manufacturing procedure: and (3) thorough conductivity, surface roughness and round edges on the scattered characterization of the end product. In cooperation with General signal. The conclusion is that for most glide path surroundings, Electric (GE) and McDonnell-Douglas (MCAIR) as sub-contractors. UTD gives adequate accuracy. An effective UTD computer representative components and alloys were selected for this program for analysis of glide path performance was developed. program. These were a Ti-17 compressor stub shaft and a Comparisons between computed and measured results show good Ti-6-4 keel splice former. Hot Isostatic Pressing parameters agreement. R.E.S. were optimized for both the Ti-17 and Ti-6-4 alloy using the ceramic mold process. Si02 was chosen as the most promising N80-19373# Royal Aircraft Establishment, Farnborough mold material. The ability to produce near-net shapes of both (England). engine and airframe components was successfully demonstrated. THE ROLE OF HF IN AIR-GROUND COMMUNICATIONS: Both parts exhibited comparable properties to cast and wrought AN OVERVIEW material with the exception of low cycle fatigue requirements B. Burgess In AGARD Spec. Topics in HF Propagation Nov. on the engine stub shaft. The results indicate that a potential 1979 6 p refs exists for the HIP process to reduce both input material and Avail. NTIS HC A25/MF AOl machining costs compared to Current cast and wrought product. High frequency radio is a prime means for beyond line-of-eight G RA air-ground communications and will remain as such into the foreseeable future, complementing Satellite communications N80-19266# Naval Postgraduate School, Monterey, Calif. ACCURACY AND REPEATABILITY INDICES FOR JOINT OIL where this latter system is employed. Various aspects that make ANALYSIS PROGRAM DATA M.S. Thesis up an HF communciations system and the contribution that they make to the overall system performance are reviewed. The needs Douglas Carlton Hatcher Sep. 1979 49 p refs (AD-A078156) Avail: NTIS HC A03/MF AOl CSCL 11/8 of the modern user in the use of HF communications are This thesis examines spectrometric oil analysis data in an considered with emphasis on the changing requirements on the attempt to construct tables of statistical estimates for use in HF link that the use of digital Communications brings. Error rate evaluating a laboratory's performance individually and in compar- performance, avoidance of interference, HF prediction techniques ison to control laboratory. Tables of estimates were obtained for Northern latitudes, and the role of channel evaluation techniques are addressed in order to acquaint the research worker from data provided by twenty six laboratories. GRA with the status and trends in airborne HF Communications and to indicate where further work may profitably be undertaken to eventually improve system performance. A.R.H. N80-19268# Douglas Aircraft Co.. Inc.. Long Beach, Calif. PRIMARY ADHESIVELY BONDED STRUCTURE TECHNOL- N80-19374// Royal Aircraft Establishment, Farnborough OGY (PABST). GENERAL MATERIAL PROPERTY DATA (England). Radio and Navigation Dept. Final Report, Feb. 1975 - Sep. 1978 HF COMMUNICATION TO SMALL LOW FLYING AIR- A. W. Shannon, P. Stifel, R. Beger, E. J. Hughes. and J. L. CRAFT Rutherford Wright-Patterson AFB, Ohio AFFDL Sep 1978 N. M. Maslin 408 p In AGARD Spec. Topics in HF Propagation Nov. 1979 13 refs (Contract F33615-75-C-3016) p (AD-A077891; MDC-J6065A; AFFDL-TR-77-107( Avail: NTIS Avail: NTIS HC A25/MF AOl HC A18/MF AOl CSCL 11/1 HF (2-30 mHz( radio communication is a principal means This program investigated state-of-the-art adhesives, adhesive primers, surface treatments, and coatings to determine, through of beyond line of sight communication to aircraft. There are particularly serious problems for the small aircraft. Many factors durability testing, a system that could be used to adhesively bond a primary aircraft structure. Test methods were also degrade the overall received signal-to-noise ratio both at the ground and in the aircraft. To achieve satisfactory results, evaluated. Previous work indicated cyclic-stressed testing in hostile environments and, specifically, high moisture environments careful consideration should be given not only to the terminal reduced the life and durability of a given adhesive system over radio equipment but also to the long term geographic planning the same system load to the same level at constant stress. and to the management of the frequencies to be used over mobile HF links. The worst HF communication problems occur Conclusions include: (1) stressed durability testing is required to determine if a given surface treatment is durable; (2) normal Or a short range air-ground sky-wave link at night which requires industry accepted processing tolerances on surface treatments I equencies at the low end of the HF band. Working over a are too wide to produce consistently durable bonded joints; longer range link Increasing the 'optimum working frequency', thus avoiding the poor antenna efficiencies and generally reducing (3) handling of surface treated details must be designed to prevent external noise levels. It is shown that good frequency management, mechanical damage and contamination; (4) phosphoric acid anodize process was the surface treatment most tolerant to ground antenna directivity and the use of a number of geographi- cally separated remote receiving stations are vital in providing processing variations andinspectable; (5) adhesive primers from different Suppliers demonstrated a large variation in environment satisfactory communications reliability to the small aircraft. resistance and corrosion protection capabilities; (6) the type of Author carrier used in adhesive films has a large effect on the moisture resistance of the adhesives; and (7) cyclic stressed testing in a N80-19375// Army Avionics Research and Development Activity, hostile environment is necessary to determine the optimum Fort Monmouth, N. J. Communication and Sensor Div. adhesive durability, GRA MODERN HF COMMUNICATIONS FOR LOW FLYING AIRCRAFT N80-19354# Norsk Marconi AS., Oslo. John F. Brune and Bernard V. Ricciardi In AGARD Spec. MULTIPATH ANALYSIS OF ILS GLIDE PATH Topics in HF Propagation_ Nov., 1979 15 p refs T. Breien In AGARD Terrain Profiles and Contours in Electromag- Avail. NTIS HC A25/MF AOl netic Wave Propagation Dec. 1979 10 p refs An application of the HF propagation phenomenon that can provide relatively short range, reliable, terrain independent Avail: NTIS HC A17/MF AOl communications is described. It has been shown that communica-
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tions Out to ranges of 50 km, under varying terrain conditions, Susan Braden 25 Apr. 1980 39 p refs Presented at the to and from low flying aircraft, is an extremely difficult problem AIAA Southeastern Regional Student Conf.. Atlanta, 24-25 Apr. especially for air mobile tactical forces. The US Army under the 1980 Nap-of-the- Earth Communications (NOE Comm) System program (Grant NsG-2288) conducted extensive tests and analysis using the HF media for (NASA-CR-162855) Avail: NTIS HC A03/MF AOl CSCL tactical communications with low-flying aircraft. The use of the 200 near-vertical-incidence skywave (NVIS) portion of the HF channel Vortex patterns from multiple subsonic jets exiting perpendic- for aircraft communications is described. The H F-SSB radio ularly through a flat plate into a subsonic crossflow were systems have the capability of operating in either a ground wave investigated. Tandem and transverse jet configurations were or NVIS mode. For the NVIS mode, the energy is directed vertically examined using a paddle wheel sensor to indicate the presence to the ionosphere and returned to the surface of the earth. The and relative magnitude of streamwise vorticity in the flow. Results NVIS mode provides umbrella type coverage. Because of NVIS are presented in the form of contour plots of rotational speed propagation. HF . SSB systems with appropriate antennas have of the paddle wheel as measured in planes downstream from the capability of providing communications coverage out to ranges the jetsand' perpendicular to the crossflow. Well developed greater than 50 km in any type of terrain. The NVIS mode is diffuse contrarotating vortices were observed for the configurations terrain independent. The characteristics of the HF NVIS mode studied. The location and strength of these vortices depended are considered and the features required of a modern HF radio on the multiple jet configuration and the distance downstream system to make efficient and practical utilization of the already from the jets. K. L. overcrowded HF band are noted. A.R.H. N8O19495*# National Aeronautics and Space Administration. N80-19377# Royal Aircraft Establishment. Farnborough Lewis Research Center. Cleveland, Ohio. (England). Radio and Navigation Dept. DAMPING IN TAPERED ANNULAR SEALS FOR AN ASSESSMENT OF HF COMMUNICATIONS RELIABILITY INCOMPRESSIBLE FLUID N. M. Maslin In AGARD Spec. Topics in HF Propagation David P. Fleming Apr. 1980 22 p refs Nov. 1979 12 p refs )NASA-TP-1646; E-124) Avail. NTIS HC A02/MF AOl CSCL 11A Avail: NTIS HC A25/MF AOl Damping in annular seals is calculated for an incompressible The concept of circuit reliability for an HF sky-wave link is fluid. Results show that damping in tapered seals optimized for discussed. Its frequency dependence is considered together with stiffness is considerably less than that in straight seals for the the relationship to the median received signal-to-noise ratio for same minimum clearance. Damping in rotating seals can promote a given HF circuit. The importance of a study of this kind is the fractional frequency whirl. Neglecting fluid acceleration makes ability to be able to quantify changes that could be made for solution much easier, but leads to errors in calculated damping an HF circuit, in terms of reliability improvements, and hence to of up to 16 percent. K. L. make decisions of the cost effectiveness of increasing transmitter power, antenna efficiencies, directional antenna design. A.R.H. N80-19497# National Aeronautics and Space Administration. N80-19429# Autonetics, Anaheim, Calif. Strategic Systems Lewis Research Center, Cleveland, Ohio. Div. FERROGRAPHIC AND SPECTROGRAPHIC ANALYSIS OF SOLID STATE POWER CONTROLLER VERIFICATION OIL SAMPLED BEFORE AND AFTER FAILURE OF A JET STUDIES Final Technical Report, Oct. 1978 - Jan. 1979 ENGINE Carl 0. Linder Jan. 1979 195 p William R. Jones, Jr. Feb. 1980 20 p refs (Contract F33615-78-C-2065; AF Proj. 3145) (NASA-TM-81430: E-353) Avail: NTIS HC A02/MF AOl CSCL (AD-A078238; C79-85/201; AFAPL-TR-79-2029) Avail: NTIS 21E HC A09/MF AOl CSCL 01/3 An experimental gas turbine engine was destroyed as a result This report documents the design and test of the Solid State of the combustion of its titanium components. Several engine Power Controllers )SSPC5) for the B-i aircraft. The SSPCs were oil samples (before and after the failure) were analyzed with a in qualification testing when the B-i program was terminated. Ferrograph as well as plasma, atomic absorption, and emission The testing and comjletion of the B-i SSPC program, considered spectrometers. The analyses indicated that a lubrication system crucial to the advancement of the state-of-the-art in SSPC failure was not a causative factor in the engine failure. Neither technology, is concluded and documented in this report. This an abnormal wear mechanism, nor a high level of wear debris report documents the accomplishments of the B-I SSPC program was detected in the oil sample from the engine just prior to the together with the results of the tests completed during the study. test in which the failure occurred. However, low concentrations Recommendations for future SSPC activities are included in the of titanium were evident in this sample and samples taken earlier. final section. A proposed MIL-P-81653 specification is attached After the failure, higher titanium concentrations were detected as Appendix A. Author (GRA) in oil samples taken from different engine locations. Ferrographic analysis indicated that most of the titanium was contained in N80-19435# Autonetics, Anaheim, Calif. Strategic Systems spherical metallic debris after the failure. K. L. Div. FLAT BUS FAULT SENSORS Final Report, Oct. 1978 - N80-19499'# Jet Propulsion Lab., California Inst. of Tech., Oct. 1979 Pasadena. Carl 0. Linder Oct. 1979 48 p ON THE CHARACTERISTICS OF CENTRIFUGAL- (Contract N62269-78-C-0213) RECIPROCATING MACHINES )AD-A077060; C79-951/201; NADC-77336-60) Avail: NTIS W. H. Higa 1 Feb. 1980 28 p HC A03/MF AOl CSCL 09/3 (Contract NAS7-100) This report documents the development of an electric power (NASA-CR- 162881; JPL-Pub-79- 108) Avail: NTIS distribution fault sensing technique for use on a 270 Vdc, two HC A03/MF AOl CSCL 131 wire, flat bus, ungrounded aircraft power distribution system for A method of compressing helium gas for cryogenic coolers operation in composite aircraft structures. The effort, performed is presented which uses centrifugal force to reduce the forces by the Strategic Systems Division of Rockwell International, on the connecting rod and crankshaft in the usual reciprocating included the development, fabrication and delivery of six fault compressor. This is achieved by rotating the piston-cylinder sensor breadboards. Author (GRA) assembly at a speed sufficient for the centrifugal force on the piston to overcome the compressional force due to the working N8019454*# Florida Univ.. Gainesville. Dept. of Engineering fluid. The rotating assembly is dynamically braked in order to Sciences. recharge the working space with fluid. The intake stroke consists VORTICITY ASSOCIATED WITH MULTIPLE JETS IN A of decelerating the rotating piston-cylinder assembly and the CROSSF LOW exhaust stroke consists of accelerating the assembly. K.L.
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N80-19509fl SKF Industries, Inc., King of Prussia. Pa. N80-19522// Naval Postgraduate School. Monterey, Calif. ESTABLISHMENT OF ENGINEERING DESIGN DATA FOR RELIABILITY GROWTH MODELS HYBRID STEEL/CERAMIC BALL BEARINGS Final Report. W. M. Woods In AGARD Avionics Reliability, Its Tech, and Apr. 1978 - Aug. 1979 Related Disciplines Oct. 1979 21 p refs F. A. Morrison. J. Pirvics. and T. J'onushonis Sep. 1979 63 p refs Avail: NTIS HC A23/MF AOl (Contract N00019-78-C-0304) The concept of reliability growth models is introduced. Two (AD-A078934; SKF-AL79T033) Avail: NTIS reliability growth models are presented, one for time data and HC A04/MF AOl CSCL 11/6 one for attributes data. Their uses are discussed and the methods A hybrid steel/ceramic angular contact ball bearing was for evaluating them are presented in graphical and tabular form. designed for optimum performance at 2.5 x 10 to the 6th power Both models show reasonable accuracy for reasonable amounts DN. A lot of bearings was fabricated to this design and life of testing under a wide variety of actual reliabilty growth and tests were conducted under two different loads. A detailed failure nongrowth. J.M.S. anlaysis was completed to define the causes for the premature silicon nitride ball failures. GRA N8O-19523// Elektronik'System G.m.b.H.. Munich (West Germany). A SIMULATION PROGRAM FOR THE DETERMINATION OF SYSTEM RELIABILITY OF COMPLEX AVIONIC SYS- Advisory Group for Aerospace Research and N80-19519# TEMS Development. Neuilly- Sur- Seine (France). AVIONICS RELIABILITY, ITS TECHNIQUES AND RELATED Christian Krause and Hubert Limbrunner In AGARD Avionics DISCIPLINES Reliability, Its Tech, and Related Disciplines Oct. 1979 9 p Manfred C. Jacobson (AeG'Telefunken. Ulm, West Germany) Oct. ref 1979 536 p refs In ENGLISH and FRENCH Conf. held in Avail: NTIS HC A23/MF AOl Ankara. 9-13 Apr. 1979 The simulation program SIMZUV which computes system IAGARD-CP-26 1; ISBN-92-835-0254-Xl Avail: NTIS reliability according to the Monte Carlo method is described. HC A23/MF AOl This program enables the realistic consideration of complex failure A state of the art review of topics related to reliability and logics of meshed systems, couplings of failures of different units logistics in avionics systems is given. General concepts, reliability/ and different mission phases, which is possible by the selection availability requirements and demonstration, reliability and of a certain formulation of these marginal conditions. In its capacity maintainability practices and effects in avionics design, develop- as a simulation program. SIMZUV is capable of considering ment and production, software reliability, and logistics support condition and time dependent failure rates and various unit aspects are among the topics discussed. reliability functions. It is shown that it is possible to perform the simulation of a substitute system of higher failure rates with short computer time, after a transformation of the failure rates. It is demonstrated that the reliability curve of the actual system Naval Postgraduate School, Monterey, Calif. N80'19520# can be computed from the reliability curve of the substitute AN ANALYSIS OF THE EVOLUTION OF THE RELIABILITY system via a linear system of equations. AND MAINTAINABILITY DISCIPLINES M. B. Kline, J. Di Pasquale, T. A. Hamilton. and R. L. Masten N80-119532# Thomson-CSF, Malakoff (France). In AGARD Avionics Reliability, Its Tech, and Related Disciplines METHODS USED FOR DISCERNING THE RELIABILITY OF Oct. 1979 24 p Prepared in cooperation with Naval Weapons MILITARY AIRCRAFT RADAR (METHODES UTILISEES Center POUR CONNAITRE LA FIABILITE DUN RADAR D'AVION Avail: NTIS HC A23/MF AOl DARMES) The results of a study of the development of the reliability J. C. CharIot In AGARD Avionics Reliability, Its Tech, and and maintainability (R&M( disciplines are presented. The Related Disciplines Oct. 1979 20 p In FRENCH exponential rate of growth shown during this period is an indication of the dynamic nature and importance of these disciplines to Avail: NTIS HC A23/MF AOl system development, design, and operation. Family trees of each In an effort to ascertain the reliability of a radar onboard a discipline developed to indicate the growth and branching of military aircraft. Thomson-CFS formed an organization to collect the relevant subject matter are presented. The direction and and process the information necessary to measure the mean rate of growth of these disciplines in each of the decades of time of good operation The methods for data acquisition, the interest are analyzed along with projections of current and future members of the organization in 1979, the data management, trends. Applications of R&M in both the private and public sectors, and prospects for the future (extension to other equipment and including defense, space, energy, transportation, industrial and information concerning component fabrication( are discussed. consumer items, are examined. J.M.S Transi. by A.R.H.
N8O-19521H Royal Signals and Radar Establishment, Malvern N80-19533f/ Draper (Charles Stark) Lab., Inc., Cambridge. Mass. (England). A FAULT TOLERANT ARCHITECTURE APPROACH TO DIFFICULTIES IN PREDICTING AVIONICS RELIABILITY AVIONICS RELIABILITY IMPROVEMENT J. E. Green In AGARD Avionics Reliability, Its Tech, and Donald C. Fraser and John J. Deyst In AGARD Avionics Related Disciplines Oct 1979 7 p refs Reliability, Its Tech, and Related Disciplines Oct. 1979 9 p refs Avail: NTIS HC A23/MF AOl Avail: NTIS HC A23/MF AOl Avionics reliability prediction techniques are considered with A difficult technology challenge in the reliability of avionics particular attention given to factors which significantly influence systems for advanced aircraft is identified. Three architectures reliability. These include types of aircraft, the duration and type are compared on the basis of a number of criteria which together of sortie, the frequency of use, and the incidence of reported constitute the issues which must be examined when considering but unconfirmed failures which nevertheless result in maintenance the overall reliability. maintenance, and support problem. It is actions. It is shown that failures are nonexponentially distributed concluded from these comparisons and the limitations identified during a sortie, although conventional predictions are based on in contemporary approaches that the only effective and practical the exponential distribution Therefore, various proposals for solution to the reliability challenge is through architecture. An predicting avionics reliability are presented to overcome this advanced integrated, distributed fault and damage tolerant digital discrepancy. The difficulties in making predictions for the latest avionics system architecture is summarized which shows promise microelectronic devices are considered with reference to of meeting this challenge. Author MIL-HDBK . 21 B and emphasis on the potential reliability of LSI and microprocessors. The significance of the choice of quality N80. 19534*# National Aeronautics and Space Administration. factors is noted. J.M.S. Langley Research Center, Langley Station. Va.
250 N80-19546
TRENDS IN RELIABILITY MODELING TECHNOLOGY FOR N80-19538# Westinghouse Defense and Electronic Systems FAULT TOLERANT SYSTEMS Center. Baltimore, Md. Salvatore J Bavuso In AGARD Avionics Reliability, Its Tech. RELIABILITY GROWTH THROUGH ENVIRONMENTAL and Related Disciplines Oct. 1979 12 P refs SIMULATION Avail: NTIS HC A23/MF A01SCL 140 Lawrence J. Phaller In AGARD Avionics Reliability, Its Tech. Developments in reliability modeling for large fault tolerant and Related Disciplines Oct. 1979 8 p refs avionic computing systems are presented. Issues of state size Avail: NTIS HC A23/MF AOl and complexity, fault coverage, and practical computation are addressed. A two-fold developmental effort is described based Field data were used to identify unreliable line replaceable on the structural and fault coverage modeling approaches. A units and implement design improvements. The rate of reliability technique which was successfully applied to an 865 state pure growth was found to be dependent on the unit complexity and the death stationary Markov model is presented. Of particular state of the art of the unit. Reliability growth occurred in both design and quality control. interest is a short computer program which executes very quickly K. L. to produce reliability results of a large state space model. This model also incorporates fault coverage states for processor, N80-19539# Marconi-Elliott Avionic Systems Ltd.. Rochester memory, and bus line replaceable units. A second structural (England). reliability modeling scheme is aimed at solving nonstationary THE A-7 HEAD-UP DISPLAY RELIABILITY PROGRAMME Markov models. This technique provides the tool required for K. W. Boardman In AGARD Avionics Reliability, Its Tech. and studying the reliability of systems with nonconstant failure rates Related Disciplines Oct. 1979 14 p refs and includes intermittent/ transient faults, electronic hardware which exhibits decreasing failure rates, and hydromechanical Avail: NTIS HC A23/MF AOl devices which typically have wearout failure mechanisms. Several The evolution of the head-up display from earlier forms of aspects of fault coverage, including modeling and data measure- weapon aiming techniques is described. The A-7 head-up display ment of intermittent/transient faults and latent faults, are is then introduced in terms of the reliability requirements and elucidated and illustrated. The CARE II (computer-aided reliability the contracting environment. Technical innovations introduced to estimation) coverage is presented and shortcomings to be meet the reliability requirements are described with emphasis eliminated are discussed. K. L. on thermal design, ruggedized long life cathode ray tube technology, and durability of low voltage printed circuit connectors. The cost benefit of the reliability program is discussed. K. L. N80-19536# Dowty Boulton Paul Ltd., Wolvenhampton (England). N80-19540# Army Avionics Research and Development Activity, NONELECTRONIC ASPECTS OF AVIONIC SYSTEM Fort Monmouth, N. J. RELIABILITY MILITARY ADAPTION OF A COMMERCIAL VOR/ILS C. V. Kenmir. R. G. Hilton, and H. H. Dixon In AGARD Avionics AIRBORNE RADIO WITH A RELIABILITY IMPROVEMENT Reliability, Its Tech, and Related Disciplines Oct. 1979 12 p WARRANTY Earl I. Feder and Douglas L. Niemoller (Bendix Corp., Fort Avail: NTIS HC A23/MF AOl Lauderdale, Fla.) In AGARD Avionics Reliability, Its Tech, and Methods of obtaining actuation system integrity by means Related Disciplines Oct. 1979 8 p of redundancy are examined. The effects of control surface layout, number of power supplies, and the form of the avionics Avail: NTIS HC A23/MF AOl on the chosen solution are investigated. The effect of redundancy Low cost, small, lightweight airborne navigation receivers on defect rates is also discussed. Developments which improve were acquired and reconfigured to meet U.S. Army aircraft reliability and remove constraints are considered, K. L. specifications. The contract includes a clause requiring the manufacturer to assume responsibility for the field reliability and N80-19536// Electronique Marcel Dassault, St. Cloud (France). repair of each receiver for a minimum of four years. If successfully IMPACTS OF TECHNOLOGIES SELECTED ON THE RELI- implemented, the reliability improvement warranty should increase ABILITY AND OPERATIONAL AVAILABILITY OF EQUIP- reliability, availability, and maintainability and reduce the overall equipment life cycle costs. MENTS. COST CONSIDERATIONS K. L. J. M. Girard and M. Giraud In AGARD Avionics Reliability, Its Tech, and Related Disciplines Oct. 1979 17 p refs NBO-19543# Thomson-CSF, Paris (France), Electron Tube Div. Avail: NTIS HC A23/MF AOl RELIABILITY OF HIGH-BRIGHTNESS CRTS FOR AIRBORNE A single criterion. V. is proposed to allow manufacturers to DISPLAYS evaluate the merits of technological variants once an equipment J. P. Galves and J. Brun In AGARD Avionics Reliability, Its baseline version is designed and quoted. The V factor is computed Tech, and Related Disciplines Oct. 1979 14 p for an airborne digital computer, a Doppler navigational radar, and a search and rescue beacon, each considered in three different Avail: NTIS HC A23/MF AOl versions. K. L. The reliability of high brightness monochrome or color cathode ray tubes (CRT's) for aircraft head-up display and head-down display systems is examined. The specification, which includes N80-19537// Rome Air Development Center, Griffiss AFB. N.Y. electrooptical performance and environmental conditions, defines the tube quality at zero operating time. Two typical examples of A NEW APPROACH TO MAINTAINABILITY PREDICTION Joseph J. Naresky In AGARD Avionics Reliability, Its Tech. specifications are given. The problems encountered in designing tubes, and the solutions used to obtain the desired level of and Related Disciplines Oct. 1979 14 p refs quality are briefly discussed. Reliability testing concerns random Avail: NTIS HC A23/MF AOl failures that occur during normal operation of the tube. After a A time synthesis maintainability prediction method was short mathematical treatment of the principles involved, three developed which directly relates diagnostic, isolation, and test examples of reliability tests carried out on CRT's are given. The subsystem characteristics to equipment/ system maintainability electrooptical characteristics of CRT change during operation. parameters. A comprehensive set of time standards applicable This is mainly a cathode and screen wearing-out phenomenon. to physical maintenance actions associated with equipment The life expectancy of a CRT depends on this evolution, and is construction and packaging procedures is also provided. Predicted thus a function of tube operating conditions, M.G. parameters include mean time to repair, maximum time to repair, N80-19546# Elliott-Automation Space and Advanced Military mean maintenance man hours per repair, and fault isolation Systems Ltd., Camberley (England). resolution. The method includes techniques for use with both RELIABILITY MANAGEMENT OF THE AVIONIC SYSTEM preliminary and final design data. K. L. OF A MILITARY STRIKE AIRCRAFT
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A. P. White and J. D. Pavier In AGARD Avionics Reliability, An effective procurement strategy for reliability and maintain- Its Tech, and Related Disciplines Oct. 1979 13 p refs ability is discussed as documented in the DCAD Technical Publication 1/77: Achievement of Avionic Reliability and Avail: NTIS HC A23/MF AOl Maintainability through Integrated Management. The evolution The system management techniques to achieve the reliability of the strategy is reviewed, the requirements of the strategy are requirements for the avionic system of the Panavia Tornado aircraft discussed, and the implementation of the strategy is examined. are described. The method of apportionment of these requirements AWN. to each of the constituent parts of the system is explained. The aims, cost effectiveness, and experience to date of reliability N80-19560# Ministry of Defence. London (England). demonstrations are outlined. M.G. COMPUTER SIMULATION MODEL OF THE LOGISTIC SUPPORT SYSTEM FOR ELECTRICAL ENGINEERING TEST EQUIPMENT N80-19549# SRI International Corp.. Menlo Park, Calif. C. J. P. Haynes In AGARD Avionics Reliability, Its Tech, and Computer Science Lab. Related Disciplines Oct. 1979 13 p FORMAL METHODS FOR ACHIEVING RELIABLE SOFT- WARE Avail: NTIS HC A23/MF AOl Jack Goldberg . In AGARD Avionics Reliability. Its Tech, and A simulation model of the existing logistic support system Related Disciplines Oct. 1979 9 p rets for electrical engineering test equipment, developed as a research tool for evaluating the adequacy of analytical provisioning (Contracts NAS1-13792: N00123-76.C-0195) models is described. Two further simulations, developed to model Avail' NTIS HC A23/MF AOl alternative logistic support systems and to compare these with Requirements for reliable avionic systems are discussed in the current maintenance organization, are also described. The terms of the effectiveness of programming methodology. The present logistic support system, the development of the three need for methods to cope with the complexity of critical real-time simulation models, and their potential uses are discussed. systems is emphasized. Some general concepts about formal AWN. methods are presented and an example is given of the SRI hierarchical development methodology taken from the executive N8019566*# Boeing Co.. Wichita, Karis, system of the SIFT fault tolerant computer. Formal methods DEVELOPING, MECHANIZING AND TESTING OF A DIGITAL with alternatives are compared and the prospects for introducing ACTIVE FLUTTER SUPPRESSION SYSTEM FOR A MODI- formal methods into practice are considered. R.C.T. FIED B-52 WIND-TUNNEL MODEL Final Report. Jul. 1975 - Jan. 1980 John R. Matthew Mar, 1980 129 refs N80-19551# Rome Air Development Center. Griffiss AFB. N.Y. p AN ANALYSIS OF SOFTWARE RELIABILITY PREDICTION (Contract NAS1.14031) (NASA-CR . 159155; D3-1168-1) Avail: NTIS MODELS HC A07/MF AOl CSCLO1A Alan N. Sukert In AGARD Avionics Reliability, Its Tech. and A digital flutter suppression system was developed and Related Disciplines Oct. 1979 11 p refs mechanized for a significantly modified version of the 1/30-scale B . 52E aeroelastic wind tunnel model. A model configuration was Avail: NTIS NC A23/MF AOl Several mathematical models for predicting the reliability and identified that produced symmetric and antisymmetric flutter mQdes'that occur at 2873N/sq m 160 psf) dynamic pressure error content of a software package were evaluated against error data extracted from the formalized testing of four software with violent onset. The flutter suppression system, using one trailing edge control surface and the accelerometers on each development projects. The results of the data collected are wing, extended the flutter dynamic pressure of the model beyond described using both Maximum Likelihood and Least Squares methods for estimating model parameters. Model predictions are the design limit of 4788N/sq m (100 psf). The hardware and compared on a total project, functional and error severity basis. software required to implement the flutter suppression system Model predictions are also compared on an errors/day and were designed and mechanized using digital computers in a errors/week basis for defining model time intervals. Conclusions fail-operate configuration. The model equipped with the system concerning the application of these models are presented. R.C.T. was tested in the Transonic Dynamics Tunnel at NASA Langley Research Center and results showed the flutter dynamic pressure of the model was extended beyond 4884N/sq m (102 psf). N80-19554# Elliott-Automation Space and Advanced Military J.M.S. Systems Ltd.. Camberley (England). SOFTWARE DEVELOPMENT FOR TORNADO: A CASE N80-19567# General Dynamics Corp. Fort Worth, Tex. HISTORY FROM THE RELIABILITY AND MAINTAINABILITY FASTENER HOLE QUALITY, VOLUME 1 Final Technical ASPECT Report, Jun. 1976 - Oct. 1978 D. J Harris In AGARD Avionics Reliability, Its Tech, and P. J. Noronha, S. P. Henslee, D. E. Gordon. Z. R. Wolanski, and Related Disciplines Oct. 1979 23 p B. G. W. Lee Wright-Patterson AFB, Ohio AFFDL Dec. 1978 165 p Avail: NTIS HC A23/MF AOl (Contract F33615-76-C-3113; AF Proj. 4861.11 The methods and procedures adopted in the development (AD-A077859; FZM -6809-Vol-i; AFFDL-TR-78.206-Vol-1l program for the TORNADO aircraft are presented. Software Avail: NTIS HC A08/MF AOl CSCL 13/5 development for TORNADO has been undertaken in four This report describes the development of the equivalent initial successive, but overlapping phases, namely definition, writing, flaw size concept as a potential design tool and the generation testing and delivery. The key features in these four phases are of equivalent initial flaw size data as a function of several given that have contributed to software reliability and maintainabil- manufacturing and design variables. Several factors or mecha- ity. R.C.T. nisms that strongly affected the fatigue behavior of fastener holes have been identified and corrected to achieve a 100% improvement in fatigue life. Some of these improvements are being implemented in the F . 16 production program and the improved drilling will N80-19558# Ministry of Defence. London (England). Procure- be implemented in the C5A-H Modification Program. GRA ment Div. THE INTEGRATED MANAGEMENT OF RELIABILITY AND MAINTAINABILITY IN PROCUREMENT NBO-19569# Air Force Materials Lab., Wright-Patterson AFB, S E. Shapcott and K. A. Brown In AGARD Avionics Reliability, Ohio. Its Tech, and Related Disciplines Oct. 1979 4 p AN ANALYSIS OF RESIDUAL STRESSES AND DISPLACE- MENTS DUE TO RADIAL EXPANSION OF FASTENER Avail. NTIS HC A23/MF AOl HOLES Final Report, Jan. 1975 - Dec. 1978
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A. F. Grandt and R. M. Potter Jul. 1979 37 p refs The state of the art in the field of joint damping is illustrated (AF Proj. 2307) with reference to several theories on damping mechanisms. Results (AD-A076370; AFM L-TR-79-4048) Avail: NTIS of tests carried Out on specimens with riveted joints are HC A02/MF AOl CSCL 01/3 discussed. K L Pre-expanding fastener holes with an oversize mandrel has received considerable attention for use in aircraft structures, since this process has been shown to greatly improve the fatigue life N80-19693# SRI International Corp.. Menlo Park, Calif. of fastener holes. The deformation theory of plasticity is used ATMOSPHERIC ELECTRICITY AND MILITARY OPERA- here to determine the residual stress and displacement field caused TIONS Final Report by this process. Employing plane stress assumptions, general J. E. Nanevicz Nov. 1978 8 p refs results are obtained for various interference levels and are (Contract N00014-77-C-0326) presented in a graphical form useful to the designer. In addition, (AD-A078482( Avail: NTIS HC A02/MF AOl CSCL 04/2 this analysis indicates that there is an optimum level of interference Contents: An Airborne Electric Field-Meter System Used for dependent primarily on the plate geometry. The optimum Studying Electric Field Structure Near Thunderstorm Cells; A interference levels agree well with experience values established Triggered Lightning Strike to an Instrumented Learjet Aircraft; by fatigue testing in aircraft structural alloys. GRA and Instrumented Learjet Aircraft Measurements of Static Electric Fields in and Around Florida Thunderstorm anvils, GRA
N80-19576# British Aerospace Aircraft Group. Brough (England). SOME RECENT MEASUREMENTS OF STRUCTURAL N80-19703// FWG Associates, Inc., Tullahoma, Tenn. DYNAMIC DAMPING IN AIRCRAFT STRUCTURES FOG DISPERSION Final Report E. J. Phillips In AGARD Damping Effects in Aerospace Struct. Larry S. Christensen and Walter Frost Mar. 1980 128 p refs Oct. 1979 15 p refs (Contract NAS8-33095) (NASA-CR-3255) Avail: NTIS HC A07/MF AOl CSCL 04B Avail: NTIS HC A09/MF AOl The concept of using the charged particle technique to disperse Values of structural damping obtained during a flutter warm fog at airports is investigated and compared with other investigation of a strike aircraft in several wing store configurations, techniques. The charged particle technique shows potential for in which the wings were excited by impulses at the wing tips warm fog dispersal, but experimental verification of several are presented. A vibration test on a large underwing pylon mounted significant parameters, such as particle mobility and charge density, pod during which three suspensions were represented, and a is needed. Seeding and helicopter downwash techniques are also vibration test on a box section shelf mounted on antivibration effective for 'warm fog disperals, but presently are not believed mounts are described. During the flutter investigation the structural to be viable techniques for routine airport operations. Thermal damping was determined from the time decay of filtered systems are currently used at a few overseas airports; however. accelerometer signals. In the vibration tests, the test items were they are expensive and pose potential environmental problems. excited sinusoidally and damping was obtained from accelerometer K. L. response curves at resonance. A.W.H. N80-19706# Air Force Geophysics Lab., Hanscom AFB, Mass. N80-19580# Politecnico di Milano (Italy). Istituto di lngegneria PRELIMINARY ASSESSMENT OF AN AUTOMATED Aerospaziale. SYSTEM FOR DETECTING PRESENT WEATHER Instrumen- DAMPING PROBLEMS IN ACOUSTIC FATIGUE tation Paper Vittorio Giavotto, Marco Born, and Giorgio Cavallini )Pisa Univ.) H. Albert Brown 26 Jun. 1979 37 p refs In AGARD Damping Effects in Aerospace Struct. Oct. 1979 (AD-A078031; AFG L-TR-79-Ol 37; AFGL-lP-276) Avail: NTIS lip refs HC A03/MF AOl CSCL 04/2 Avail: NTIS HC A09/MF AOl The determination of subjective weather observations through Damping information necessary for the fatigue design of the use of an automated array of weather sensors coupled with wideband noise excited structures is identified. Damping a decision tree program was examined through analysis of data mechanisms are considered and damping test results are presented gathered at the AFGL Weather Test Facility at Otis AFB. Mass. for stiffened panels typical of aerospace structures. The need This report describes the instruments used in the array, the for models capable of accurately estimating damping effects is response of the instruments to type of weather observed, and emphasized. K.L. the decision tree programs. Preliminary results indicate that a computer-controlled weather sensor array has potential value in N80-19582# Air Force Materials Lab., Wright-Patterson AFB. determining objectively those types of weather previously Ohio. relegated to human responsibility. Author (GRA) VISCOELASTIC DAMPING IN USAF APPLICATIONS D. I. G. Jones, J. P. Henderson, and L. C. Rogers (AFFDL. N80-19809// Wright-Patterson AFB, Ohio) In AGARD Damping Effects in Advisory Group for Aerospace Research anc Development, Paris (France). Aerospace Struct. Oct. 1979 24p refs MODELING AND SIMULATION OF AVIONICS SYSTEMS AND COMMAND, CONTROL AND COMMUNICATIONS Avail: NTIS HC A09/MF AOl SYSTEMS The use of viscoelastic damping technology for vibration Jan. 1980 553 control in the United States Air Force is reviewed. The potential p refs Presented at the Meeting of the Avionics Panel, Paris, 15 . payoff in improved performance and maintainability of vibration 19 Oct. 1979 (AGARD-C p-268 ISBN-92 . 835-02558( Avail: NTIS critical systems such as large flexible spacecraft structures, digital HC A24/MF AOl electronics systems, and rotating jet engine components is very Simulation techniques and their applications to avionics and high. K.L. command, control, and communication systems associated with airborne operations are addressed. Modeling methodology. N80-19584# Istituto di Tecnologia Aerospaziale, Rome (Italy). experimentation, validation, and applications are covered DAMPING EFFECTS IN JOINTS AND EXPERIMENTAL Emphasis is on avionics and airborne command and control, TESTS ON RIVETED SPECIMENS including the range from large-scale force-effectiveness and air Luigi Balis Creme. Antonio Castellani, and Alfonso Nappi (SIAI defense simulations through flight simulators and real time avionics Marchetti) In AGARD Damping Effects in Aerospace Struct. simulations Oct. 1979 17 p refs N80-19812# Industrieanla g en . Betriebsgesellschaft m.b.H., Avail: NTIS HC A09/MF AOl Ottobrunn (West Germany). The importance of dynamic damping is highlighted with REMARKS ON SIMULATION, OBJECTIVES/AREAS OF emphasis on the effect of riveted joints on energy dissipation. USE/POSSIBILITIES/LIMITATIONS: AN OVERVIEW
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Hans M. Franke In AGARD Modeling and Simulation of Avionics Richard D. Healy and Samuel Newman In AGARD Modeling Systems and Command. Control and Commun. Jan. 1980 and Simulation of Avionics Systems and Command. Control and 27 p refs (For primary document see N80-19809 10-59) Commun. Jan. 1980 8 p refs Prepared in cooperation with Avail: NTIS HC A24/MF AOl NADC. Warminster, Pa. An overview of the extensive application of computerized simulation to the study of flight mechanics is presented with (Contract N62269-79-C-0020( special interest given to avionics and command and control and Avail: NTIS HC A24/MF AOl communication. Areas of use of simulation covered include: the A software life-cycle support facility under development for field of research; planning pre-design, assessment, and feasibility; the E-3A navigational computer system includes a real-time the development phase: testing; and the training simulator. environmental simulator which is used to simulate both E-3A Systems analysis and systems engineering activities in the planning avionics and the operational environment so that software of new weapon systems are discussed in terms of the use of problems with the included AN/ARN-120 Omega Navigation simulation. J.M.S. Equipment (ONE) can be investigated and that the impact of software changes can be assessed by a simulated mission refly. N80-19814# General Research Corp.. Santa Barbara, Calif. The environmental simulator is a hybrid system hosted in two VERIFICATION AND VALIDATION OF AVIONIC SIMULA- digital computers connected by a specially designed real-time TIONS digital data link. Real-time simulation software performs two Sabina H. Saib In AGARD Modeling and Simulation of Avionics distinct functions: provides computer-controlled analog and Systems and Command. Control and Commun. Jan. 1980 6 p digital input data to the ONE and respond to ONE guidance (For primary document see N80-19809 10-59) outputs, and provides truth-model aircraft data which can be Avail: NTIS HC A24/MF AOl used as a precision navigation reference. Preliminary experience Avionic simulations require verification and validation so that related to the design and construction of the environmental the simulation results can be applied reliably to actual avionic simulator for the software life-cycle support facility is presented, systems. Software design methods as well as currently available some of the practical problems encountered in developing the automated aids for verification and validation are described. simulator are described, interim resolution and potential long-term Reverification and revalidation of a simulation after changes are solutions and current status are discussed. Particular emphasis made is discussed. Simulations can be designed for ease of is placed on describing procedures used for implementing the verification and validation. Guidelines to show how simulation simulator development guidelines: maximum flexibility and software can be developed with verification in mind are minimum essential design. A.R.H. presented. R.E.S. N80-19825# Boeing Aerospace Co.. Seattle, Wash. N80-19820# Institute of Aviation Medicine. Farnborough A JTIDS PERFORMANCE MODEL FOR THE E-3A (England). James G. Taylor In AGARD Modeling and Simulation of Avionics REAL-TIME SIMULATION: AN INDISPENSABLE BUT Systems and Command, Control and Commun. Jan. 1980 OVERUSED EVALUATION TECHIOUE 13 p refs V. David Hopkin and A. J. McClumpha In AGARD Modeling Avail: NTIS HC A24/MF AOl and Simulation of Avionics Systems and Command. Control and The communications link performance model developed to Commun. Jan. 1980 6 p refs predict performance of joint tactical information distribution system (JTIDS) links between the E-3A and other aircraft and ground Avail: NTIS HC A24/MF AOl stations is described. The JTIDS is a time division multiple access Real time simulation is evaluated in relation to large man system operating in the radio frequency band 962 to machine systems, particulary air traffic control systems. The 1213 MHz and employs spread spectrum techniques. The model limitations to using real time simulation to study computer includes the performance effects on the JTIDS wideband frequency assistance, system capacity, workloads, stress, boredom, and hopping receiver due to both the E-3A dual antenna system attitudes are discussed. K. L. and specular and diffuse multipath signals. Laboratory tests were conducted which provided receiver performance data for signals N80-19821# Elektronik- System G.m.b.H., Munich (West routed through dual antenna and multipath simulators. This Germany). simulator approach was also used in similar tests conducted by DESIGN AND SIMULATION OF A C3 SYSTEM FOR SHAPE Technical Centre for NATO. The results were essentially SURVEILLANCE PURPOSE identical in the two test programs. A flight test program was Franz Herzmann and Helmut Sanders In AGARD Modelling conducted which validated the link performance model. This and Simulation of Avionics Systems and Command. Control and validated model has greatly reduced costly E-3A flight testing Commun. Jan. 1980 13 p refs and has provided predictions of JTIDS performance over a variety of communication link scenarios and flight conditions. Author Avail: NTIS HC A24/MF AOl Communications, command, and control problems associated N80-19826// Marconi Space and Defence Systems Ltd.. Hillend with the operation of a surveillance network and weapon systems (Scotland). are discussed. Tracing and allocation algorithms are designed A MISSION TRAINING SIMULATOR FOR THE NIMROD and improved by simulating network operation. Weapon system MR MK 2 AND SOME ASPECTS OF THE DERIVATION operation, including coordination and target allocation, is also AND VERIFICATION OF ITS SYSTEM MODELS simulated. The system performance is tested using radar derived K. Wells In AGARD Modeling and Simulation of Avionics data. K. L. Systems and Command, Control and Commun. Jan. 1980 6 p N80-19823# Mitre Corp.. Bedford, Mass. THE APPLICATION OF MODELING AND SIMULATION TO Avail: NTIS HC A24/MF AOl THE DEVELOPMENT OF THE E-3A Three MK. 1 simulators are undergoing a major avionics refit to reflect the changes in the RAF's Nimrod MR Mk. 2. A. R. Shanahan In AGARD Modeling and Simulation of Avionics Systems and Command. Control and Commun. Jan. 1980 This refit necessitates the modification to Mk. 2 standard of the two prime sensor systems; acoustics and radar. In addition, the 14 p Avail: NTIS HC A24/MF AOl navigation and central tactical systems are being updated. The The role of modelling and simulation in developing an modifications both to the acoustics and to the radar are airborne radar, communications, and command-control system is discussed. The definition of operations requirement and engineer- discussed. The modelling diversity required during different stages ing implementation specifications for both hardware and software of system development is emphasized. K. L. are described. The need to verify models to reflect the continuously changing design baseline as a result of aircraft development A.R.H. N80-19824# Analytic Sciences Corp.. Reading. Mass. and user experience is discussed. E .3A NAVIGATIONAL COMPUTER SYSTEM REAL-TIME N80-19829# Societe Nationale I ndustrielle A erospatiale. ENVIRONMENTAL SIMULATOR Marignane (France.) Div. Helicopteres.
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DESIGN OF A SIMULATOR FOR STUDYING THE HELICOP- The development of an air to air engagement simulation TER - SDVEH [CONCEPTION DUN SIMULATEUR DE VOL multiduel model which considers the aircraft, its avionics, D'ETUDE POUR HELICOPTER - SOUEHJ armament, and the pilots behavior is discussed. The model will JI. Masc)e. G. Catani, M. Sellier, and Jp. Letouzey In AGARD also consider the phase prior to combat including the fighter Modeling and Simulation of Avionics Systems and Command, allocation, combat air patrol, ground controlled intercept capability. Control and Commun. Jan. 1980 13 p In FRENCH influence of early warning systems. etc. Assumptions, problems. and applications of the model are discussed. A.W.H. Avail; NTIS HC A24/MF AOl The conceptual stages in the design of a flight simulator (SDVEH), which will study the specific problems in the design N80-19836# Societe Nationale Industrielle Aerospatiale. and flight operations of military helicopters are reported. The Toulouse (France). principle characteristics of the flight simulator are delineated NEW POSSIBILITIES OFFERED BY A RADIO-INERTIAL and points considered critical to the development of a helicopter HYBRID GUIDANCE SYSTEM DIGITAL SIMULATION program are discussed. The development and organization of STUDY [NOUVELLES POSSIBILITIES OFFERTES PAR UN the project are reported and a preliminary analysis of the exact SYSTEME DE GUIDAGE.HYBRIDE RADIO - INERTIEL needs of the SDVEH are presented. Transl. by A.W.H. ETUDIE EN SIMULATION NUMERIQUE] D. Buisson, J. Irvoas. and J. Grossin In AGARD Modeling and N80-19830# Institute for Defense Analyses, Arlington, Va. Simulation of Avionics Systems and Command. Control and COST-EFFECTIVENESS OF FLIGHT SIMULATORS FOR Commun. Jan. 1980 25 p In FRENCH : ENGLISH MILITARY TRAINING summary refs Jesse Orlansky and Joseph String In AGARD Modeling and Avail: NTIS HC A24/MF AOl Simulation of Avionics Systems and Command. Control and A radio inertial guidance system was studied to increase Commun. Jan. 1980 13 p refs the accuracy of aircraft guidance along the ILS beams and to ensure continuation of automatic landing in the event of a localizer Avail: NTIS HC A24/MF AOl transmitter failure. Developments in the guidance system are The cost and effectiveness of flight simulators used for military discussed including the detection of the Loc beam centerline training are evaluated. Recent cost data of modern flight simulators after an undetected failure in the monitoring of the Loc axis are analyzed. A comparison of the skills learned in flight simulators alignment with the runway axis. A digital simulation study which and the effectiveness with which they are performed in actual demonstrated the system performance is described. A.W.H. flight versus the skills learned in actual flight only is discussed. Results show that pilots trained in the simulators use less flight N80-19837# British Aerospace Aircraft Group, Brough (England). time to perform various tasks than do those trained only in THE ROLE OF THE AIRCRAFT MODEL IN AVIONIC aircraft. A.W.H. SYSTEMS SIMULATION J. D. Bannister and R. Hicks In AGARD Modeling and Simulation N80-19831// Le Materiel Telephonique. Trappes (France). of Avionics Systems and Command. Control and Commun. Jan. USING A LANGUAGE DEVELOPED FOR AIRCRAFT 1980 14p refs SIMULATORS [UTILISATION D'UN LANGAGE EVOLUE Avail: NTIS HC A24/MF AOl POUR LES SIMULATEURS DAVIONS] The relevance and use of the aircraft model in avionics systems Michel G. Dreyfus In AGARD Modeling and Simulation of simulation is discussed. The interaction between elements of Avionics Systems and Command. Control and Commun. Jan. the avionic systems, the vehicle dynamics and the outside world, 1980 7 p In FRENCH: ENGLISH summary and simulation is described. The aircraft model is discussed to indicate the choice to be made in determining the level of Avail: NTIS HC A24/MF AOl complexity required to fulfill differing objectives. Aircraft models The advantages and disadvantages of flight simulator of different types are described. Some algorithms and solution computers using assembler languages and simulation computers techniques are presented along with an indication of the limitations using FORTRAN are discussed. The impact of each method on inherent in the models. Two contrasting simulations are discussed the analytical and programming methods employed at each stage to show the significance of the aircraft model in relation to the of program writing, debugging, and modification is reviewed. avionic system simulation. The first example illustrates the use The consequences of computing power and memory capacity of an aircraft model in a GP computer simulation of the interception are also discussed. A.W.H. of invading aircraft. The second example discusses the aircraft model used in a pilot in the loop real time simulation of the N80-19832# Royal Aircraft Establishment, Farnborough avionics system for an attack aircraft. In both examples practical (England). considerations are included such as processor requirements and SIMULATION OF A NIGHT VISION SYSTEM FOR LOW simulation system architecture. A.W. H. LEVEL HELICOPTER OPERATIONS N80-19838# Battelle Columbus Labs., Ohio. J. N. Barrett In AGARD Modeling and Simulation of Avionics AVIONICS EVALUATION PROGRAM: SIMULATION Systems and Command. Control and Commun. Jan. 1980 MODELS FOR THE EFFECTIVENESS ANALYSIS OF 24 p AVIONICS Avail: NTIS HC A24/MF AOl David WeIp. Ken Almquist, and Larry Rainey In AGARD Modeling The development of night vision piloting aids to enable and Simulation of Avionics Systems and Command, Control and helicopters to operate at low altitude by night is discussed. An Commun. Jan. 1980 4 p Prepared in cooperation with AFAL. experiment which explored the problems and possibilities of a Wright-Patterson AFB. Ohio helmet mounted display for such helicopter night piloting tasks, using real time simulation techniques is described. The develop- Avail: NTIS HC A24/MF AOl ment of the helicopter simulation, and how the various components The avionics evaluation program )AEP), a library of seven of the proposed night vision system were modelled and detailed avionics performance assessment models all driven by incorporated into the simulation are reported. The experimental a common, interactive software package is examined. The AEP design for the trials and how the limitations of the simulation provides an efficient means for performing tradeoff analyses among were taken into account are discussed. A.W.H. cost, reliability, maintainability, and performance of avionic configurations. The models are the air to ground mission analysis N80-19834# lndustrieanlagen-Betriebsgesellschafj m.b.H., Ottobrunn (West Germany). program, target acquisition, weapon delivery, survivability, AIR-TO-AIR ENGAGEMENT SIMULATION communications, air to air mission analysis, and dogfight analysis. Each model is described. Goetz Wunderlich and Roland Braun In AGARD Modeling and A.W.H. Simulation of Avionics Systems and Command. Control and N80-19839# British Aerospace Dynamics Group. Bristol Commun. Jan. 1980 14 (England). Avail: NTIS HC A24/MF AOl SIMULATION FOR WHOLE LIFE DEVELOPMENT
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R. J. Morrow and R. Richards In AGAR Modeling and Simulation George T. Schmidt and Roy H. Setterlund In AGARD Modeling of Avionics Systems and Command. Control and Commun. Jan. and Simulation of Avionics Systems and Command. Control and 1980 11 p refs Commun. Jan. 1980 10 p refs Avail: NTIS HC A24/MF AOl (Contract F33657-78-C-0473) A special prupose, real time simulator suitable for whole Avail: NTIS HC A24/MF AOl life development of complex avionics control systems is described. The modeling, simulation, and performance predictions used Software flexibility, a current equipment selling point, demands in determining aircraft avionics and transfer alignment require- a reappraisal of previous equipment development procedures. ments for a generic aircraft that would launch cruise missiles Problems with high speed information handling will occur during over water a considerable distance from a first TERCOM update the development of new digital controllers when used for command area are discussed. The methodology used in allocating the and control. ESM and EW system are discussed. The need to allowable navigation errors between the CM guidance system simulate those real world factors that load the information to and the cruise missile carrier aircraft avionics system is de- the digital processing system under development. R.C.T. scribed. R.C.T.
N80-19840fl Air Force Avionics Lab., Wright-Patterson AFB, N80-19844# National Aerospace Lab.. Amsterdam (Netherlands). Ohio. A FLIGHT SIMULATION INVESTIGATION ON THE FEASI- A SIMULATION SUPPORT SYSTEM, THE DEVELOPMENT BILITY OF CURVED APPROACHES UNDER MIS GUID- TOOL FOR AVIONIC SYSTEMS AND SUBSYSTEMS ANCE In AGARD Modeling and Simulation of John C. Ostgaard L. J. J. Erkelens In AGARD Modeling and Simulation of Avionics Avionics Systems and Command. Control and Commun. Jan. Systems and Command. Control and Commun. Jan. 1980 1980 11 refs p 18 p refs Avail: NTIS HC A24/MF AOl Avail: NTIS HC A24/MF AOl The simulation support facility required for the development A simulation investigation concerning the possibilities of and validation of the digital avionics information system are executing laterally curved approaches with a wide body type of discussed. The design requirements for an integrated simulation aircraft in a microwave landing system environment is described. support system are given with emphasis on the following: The approach path variables were: final approach intercept altitude avionic system support; prototype system software support; and angle of the turn. An Earth fixed circular segment connected prototype system hardware support; engineering studies; the straight preturn segment with the final segment. A flight R.C.T. maintenance augmentation; and training assistance. director operating in the instrument landing system tracking mode, supplied with minor modifications in the roll bar drive, is used N8O-19841# lndustrieanlagen-Betriebsgesellschaft m.b.H.. as the primary instrument for guidance. Additional provisions Ottobrunn (West Germany). are made to enable the pilot to monitor the approach. A total FIRE CONTROL FOR AIR-TO-AIR GUNNERY IN HIGH number of about 450 curved approaches, performed by three PERFORMANCE FIGHTER AIRCRAFT pilots, are flown on the simulator under various weather Hans W. Pongratz In AGARD Modeling and Simulation of conditions. In addition to tracking data, subjective information Avionics Systems and Command. Control and Commun. Jan. like pilot ratings and comments are gathered. Curved approaches, 1980 13 p with turn angles up to 180 deg can be carried Out safely, provided Avail: NTIS HC A24/MF AOl that the altitude at which the turn is completed is not less than A survey on some of the aspects in air-to-air gunnery initiated 305 m (1000 ft). Special provisions are needed with respect to by improvements in gun fire control are summarized. The the flight director roll bar drive, in order to achieve accurate simulation models used in the TKF simulation for gun fire control tracking on the curved segment in strong wind conditions. M.G. and gun scoring are presented. The necessary and the possible detail and accuracy of the implemented models is considered. R.C.T. N80-19845// Boston Univ., Mass. MODELING AND FLIGHT SIMULATION OF AN ACTIVE N80-19842// Electronique Marcel Dassault, St. Cloud (France). CONFIGURED AIRCRAFT UNDER M.L.S. GUIDANCE SIMULATION FOR INTEGRATION WITH DYNAMIC TESTS A. Danesi, S. Smolka. and U. Chinappi In AGARD Modeling OF THE LOGICAL ELEMENTS OF PRINCIPAL ONBOARD and Simulation of Avionics Systems and Command, Control and COMPUTERS [SIMULATEUR POUR INTEGRATION AVEC Commun. Jan. 1980 16 p Prepared in cooperation with TESTS DYNAMIQUES DES LOGICIELS DE CALCULATEURS Rome Univ., Italy ENTRAUX EMBARQUES] Avail: NTIS HC A24/MF AOl E. Bouthors In AGARD Modeling and Simulation of Avionics A mathematical formulation is presented to integrate the Systems and Command. Control and Commun. Jan. 1980 differential equations modeling a vehicle automatically guided 11 p In FRENCH along a curvilinear trajectory by a microwave landing system Avail: NTIS HC A24/MF AOl (M.LS.(. The augmented linear state equation, representing the A system is described which was designed to simulate the open loop vehicle M.L.S. observer system, is given in standard environment of onboard computers and to furnish control methods phase variable form in which the altitude perturbations from the which permit the adjustment and validation of logical elements reference trajectory and numbers of its successive derivatives before the effective integration of computers in real equipment are assumed as state variables involved in a multifeedback flight environments. The essential characteristics of the system is to control system. The state equation taken into consideration in simulate the equipment environments, not at the level of their system modeling handles separately the transfer function intrinsic operation, but at that of their interface with the computer characteristics polynomial while the dynamical effects of the in temporal. interactive, and information aspects. The simulation system zeros are included in the algebraic output equation relating is made by the fusion of operator information with information the actual altitude perturbations to the state variables defined, registered on magnetic tape. This latter information simulates in a rather fictitious fashion, in a state equation. The initial the different flight phases envisaged by tests while the operator conditions to be imposed in the integration process must be information recreates in real-time, the action of the pilot and consistent with the physical initial conditions on the actual equipment. The possibilities of operating slowly and step-by-step trajectory considered in the problem at hand and for that purpose confer a particular efficiency to the simulation and adjustment mathematical solution to the problem of transforming the initial and validation of logical elements. Transl. by A.R.H. conditions imposed on the physical state variables to the correspondent fictitious ones, is advanced. M.G.
N80. 19843// Draper (Charles Stark) Lab., Inc.. Cambridge. Mass. Guidance and Navigation Advanced Programs Div. N80-19846# Naval Air Development Center, Warminster, Pa. CRUISE-MISSILE-CARRIER NAVIGATION REQUIRE- MODELING THE HUMAN OPERATOR: APPLICATIONS TO MENTS SYSTEM COST EFFECTIVENESS
256 N80-19998
Norman E. Lane, Melvin I. Strieb (Analytics. Inc.. Willow Grove. Daniel T. Valentine Nov. 1979 19 p refs Pa.), and Walter Leyland In AGARD Modeling and Simulation (Contract N00014-77-C-0062) of Avionics Systems and Command. Control and Commun. Jan. (AD-A077809; SIT-DL-7-899) Avail: NTIS HC A02/MF AOl 1980 13 refs CSCL 09/2 Avail: NTIS HC A24/MF AOl This manual accompanies the program listings and a magnetic A technique for predicting system effectiveness which includes tape containing two files, one of program OBLIQUE and one a consideration of realistic operator/system interactions is (the second) of program OBLIQ02. The programs OBLIQUE and described. Operator interface cost effectiveness analysis (OICEA) OBLIQ02 plus the program PPEXACT are used in the procedure combines system modeling with cost projections to evaluate the described herein to compute the blade bending moments of a cost benefits of alternative proposed designs within appropriate propeller operating in an oncoming flow inclined to the propeller mission contexts. Major avionics variables are integrated into a shaft. The theoretical analyss leading to and the operating of cohesive approach which simulates hardware and software PPEXACT have been described by Tsakonas, at al. GRA functions and the performance of an operator interacting with these components, using a model called the human operator simulator. OICEA allows for systematic variation of key factors that influence ffectiveness, including degree and type of task N80-19948# Morgan Semiconductor. Inc., Garland, Tex. automation, equipment and human reliability, scenarios and GE-SI SUPERSONIC FLIR WINDOW Final Report, 1 Jul. tactical doctrine, and operator characteristics. The OICEA 1978 - 31 Mar, 1979 A. R. Hilton Jul. 1979 49 p methodology is summarized and applications to avionics and (Contract F33615-78-C-5105) sensor improvements on a fixea wing antisubmarine warfare (AD-A07837 1; AFML-TR-79-4085) Avail: platform are documented. NTIS M.G. HC A03/MF AOl CSCL 17/5 The purpose of the program was to evaluate the infrared N80-19847# Naval Air Development Center, Warminster, Pa. PREDICTING FIELD OF VIEW REQUIREMENTS FOR VSTOL Optical properties and related physical properties of melt formed AIRCRAFT APPROACH AND LANDING Germanium-Silicon alloys as potential supersonic FUR window materials. The approach was to combine the infrared transparency Paul M. Linton and Warren F. Clement In AGARD Modeling of germanium with the excellent physical properties of silicon to and Simulation of Avionics Systems and Command. Control and produce a window material capable of withstanding the Commun. Jan. 1980 17 refs Prepared in cooperation with p temperature excursions and rain drop impact occuring during Systems Technology, Inc.. Mountain View, Calif. supersonic flight. Attention was confined to alloys with silicon Avail: NTIS HC A24/MF AOl content below 50 atom % to avoid the intrinsic lattice absorption that occurs at 9 micrometers in the infrared for silicon or A rationale for quantitatively determining fixed-wing, vertical/ silicon rich alloys. A zone levelling technique was selected and short take-off and landing aircraft field of view requirements is modified in a manner expected to yield materials free of oxide developed. The interactions between human visual processes, absorption. A melt form method was selected rather than vapor the vehicle approach profile, and the operator flight path control performance are considered. A model specifies precise visual phase because of the potential problems in scaling up to produce requirements for recovery aboard defined shipboard pads or large FUR windows. Unfortunately, the growth of alloy composi- tions with silicon content above 5% proved to be impossible to forward sites. M.G. do at least under the operating conditions and with the equipment used. Major problems were long term temperature stability, zoning N80- 19861 // Intermetrics. Inc., Huntsville, Ala. rates and reactivity of the molten alloys with quartz boats and NSSC-2 OPERATING SYSTEM DESIGN REQUIREMENTS ampoules. Although the concentration range up to 50 atom % SPECIFICATION Final Report silicon was covered, infrared transmission was not obtained for T. T. Schansman and J. R. Bounds 15 Aug. 1979 78 p refs any compositions with silicon content above 5 atom%. Rain erosion (Contract NAS8-33382) samples were submitted for evaluation covering five compositions. (NASA-CR-161396; IR-432) Avail: NTIS HC A05/MF AOl Discussions related to the best Ge-Si alloy composition for CSCL 098 FUR applications are presented along with a projection of the The design requirements and implementation standards for related physical-optical parameters expected for that composi- an NSSC-2 operating system are defined. An operating system tion. GRA diagram is presented along with system concepts and terminol- ogy. K. L. N80-19978 Wisconsin Univ. - Madison. STRUCTURES IN AERONAUTICAL PHRASEOLOGY: FROM N80-19863'# National Aeronautics and Space Administration. ENGLISH TO SPANISH Ph.D. Thesis Lewis Research Center, Cleveland, Ohio. Francisco Xavier Almeida 1978 425 p ALGORITHM FOR CALCULATING TURBINE COOLING Avail: Univ. Microfilms Order No. 7915065 FLOW AND THE RESULTING DECREASE IN TURBINE The creation of an English Phraseology, its adoption as the EFFICIENCY International Language for Aviation, and the establishment of James W. Gauntner Feb. 1980 23 p refs the official ICAO (International Civil Aviation Organization) Spanish (NASA-TM-81453; E-384) Avail: NTIS HC A02/MF AOl CSCL Phraseology are traced. The regulations and Structures governing 098 civil aviation are surveyed and some of the more important studies An algorithm is presented for calculating both the quantity on the formulation of the Phraseology and on its applications to of compressor bleed flow required to cool the turbine and the actual flight conditions are examined. An unexpected result of decrease in turbine efficiency caused by the injection of cooling the investigation is that aeronautical radio can be a fertile ground air into the gas stream. The algorithm, which is intended for an in which to observe without interfering with the observation, axial flow, air routine in a properly written thermodynamic cycle the phenomena of dialects in contact, and the modification of code. Ten different cooling configurations are available for each certain dialects as a result of sociolinguistic pressures. Some row of cooled airfoils in the turbine. Results from the algorithm confirmation is provided for a stratification scheme for Spanish are substantiated by comparison with flows predicted by major dialects which reflects a popularly held view of many native engine manufacturers for given bulk metal temperatures and given speakers of Spanish. Dissert. Abstr. cooling configurations. A list of definitions for the terms in the subroutine is presented. K. L. N80-19988# Committee on Science and Technology (U. S. House). NASA AUTHORIZATION, 1981, PROGRAM REVIEW, N80-19880# Stevens Inst. of Tech., Hoboken, N. J. VOLUME 2 FORTRAN PROGRAM OBLIQUE IN PL-FORMAT USER'S Washington GPO 1980 275 p refs Hearings before the MANUAL Subcomm. on Transportation, Aviation and Communications of
257 N80-19991 the Comm. on Sci. and Technol.. 96th Congr.. 1st Sess., 30-31 Oct. 1979 (GPO-56-220) Avail: Subcomm. on Transportation. Aviation and Communications A program review of NASA activities is presented with emphasis on the progress made in aeronautics during the past 12 months. Aerodynamics, materials and structures, aeronautical propulsion, and avionics and human factors are among the topics covered. Also, advances in vehicle technology are discussed including transport aircraft, general aviation aircraft, low speed aircraft, and high speed aircraft. J.M.S.
N80-19991# Systems Technology, Inc.. Hawthorne. Calif. DEVELOPMENT OF AERODYNAMIC DISTURBANCE TEST PROCEDURES, VOLUME 1: EXECUTIVE SUMMARY Final Report, 30 Sep. 1977 - 30 Mar. 1979 Richard H. Klein and Jeffrey R. Hogue Aug. 1979 33 p refs (Contract DOT-HS-7-01716) (P680-108145; STI-TR-1 117-1-Vol-i: DOT-HS-805078( Avail: NTISHC A03/MF AOl CSCL 13F The crosswind responses of twenty different vehicles were surveyed. Three test procedures were used in three different crosswind disturbance configurations. These were steering fixed, steering free, and driver control of lane position. The crosswind configurations were straight pulse, doublet pulse, and a shaped profile. Results show that passenger cars, station wagons, trucks. and most vans have virtually no crosswind sensitivity problems, whereas the VW Microbus, the pick/up camper (in winds higher than 35 mph), cars pulling trailers, and mopeds do have potential problems. GRA
N80-20018/gl Association for Unmanned Vehicle Systems, Dayton, Ohio. PROCEEDINGS OF THE ASSOCIATION FOR UNMANNED VEHICLE SYSTEMS AUVS P79: 6TH ANNUAL CONVEN- TION 1979 165 p refs Cony, held at San Diego, Calif., 29 May - 1 Jun. 1979 )AD-A077877( Avail: NTIS HC A08/MF AOl CSCL 01/3 Contents: Unmanned Vehicles on the Tactical Battlefield - Another Beginning: Why Unmanned Vehicles Can Be Effective: Unmanned Battlefield Reconnaissance Systems For The German Army: Automated Guidance for Ground Vehicles. Cruise Missile Air Launch In the Operational Environment: Advances In Anti-Jam Transmission of Reconnaissance Imagery Data: Unmanned Seaplanes For Naval Operations: Unmanned Systems For Reducing Our Taxes, and Cruising The Planets. GRA
N80-20020# Air Force Flight Dynamics Lab., Wright-Patterson AFB, Ohio. AIR FORCE FLIGHT DYNAMICS LABORATORY FISCAL YEAR 1981. TECHNICAL OBJECTIVE DOCUMENT Dec. 1979 87 p refs Supersedes AFFDL-TR-78-181 (AD-A078973; AFFDL-TR-79-3133; AFFDL-TR-78-181) Avail: NTIS HC A05/MF AOl CSCL 01/3 The document presents an overview of the four Technical Planning Objectives (TPO( and supporting data for each. These are extracted from the technical plan of the Air Force Flight Dynamics Laboratory (AFFDL(. Information is largely based on AFFDL fiscal 1981 technology plan omitting specific funding and timing information of an 'Official Use Only' nature. Techni- cal Objectives are described for the technical areas of Structures and Dynamics. Vehicle Equipment/ Subsystems, Flight Control and Aeromechanics. Points of contact for more information in each of the areas are identified. GRA
258 SUBJECT INDEX
AERONAUTICAL ENGINEERING / A Continuing Bibliography (Suppl. 123) JUNE 1980 Typical Subject Index Listing
SUBJECT
ITERATIOM AERIAL PHOTOGRAPHY The analysis of wing-body combinations at n,,d,,t, The Surface Contour Radar, a unique remote sensing angles of attack --- tiissile bodies instrument [80-8074284] 1180-11040 880-26085 AEBOACOOSTICS Effect of temperature on surface noise 880-28419 CCESSION Publications in acoustic and noise control from LjTMBER NUMBER NASA Langley Research Center during 19110-1979 bibliographies NASA-TN-80211) 1180-18884 Aeroacoustic wind-tunnel tests of a light The title is used to provide a description of the subject matter. When the title is twin-boom general-aviation airplane with free or insufficiently descriptive of the document content, a title extension is added, shrouded-pusher propellers --- in the Langley full-scale tunnel separated from the title by three hyphens. The NASA or AIAA accession number [NASA-TM-80203] N80-19023 is included in each entry to assist the user in locating the abstract in the abstract AERODYNAMIC CHARACTERISTICS section of this supplement. If applicable, a report number is also included as an Increasing aircraft efficiency through laminar aid in identifying the document. flow control 880-24899 A system for measuring and recording wind-tunnel balance data 880-25221 A Yawed slender wings at small angles of attack A-i AIRCRAFT 880-26268 The 8-7 bead-up display reliability programme One-dimensional aerodynamic control calculations 880-19539 for cooled gas turbines 8-10 AIRCRAFT A80-26305 Development and flight test of a two-place Aerodynamic Testing Conference, 11th, Colorado night/adverse weather 8-10 for the close-air Springs, Cob., March 18-20, 1980, Technical support and battlefield attack mission Papers [SAE PAPER 791069] 880-26632 A80-26929 Night/adverse weather A-10 evaluator program Newrequirements, test techniques, and development /A-108/. B. H. Shawler methods for high fidelity flight simulaticn of 880-27378 commercial transports Avionics interface data summaries: 5-108, [AIAA 80-0445] 880-26949 SF-111A, F-43, P-4G, F-15A, F-16A, F-111A, The influence of wing, fuselage and tail design on F-ills, F-111F, IIF-4C rotational flow aerodynamics data obtained [AD-A077388] N80-19105 beyond maximum lift with general aviation ACCELERATED LIFE TESTS configurations Advanced composites serviceability program - [AIAA 80-0455] 880-26955 Status review --- inspection of aircraft Measurements of the dynamic performance of the structures main drive fan of the RAE 5 metre pressurised 580-26890 low speed wind tunnel ACOUSTIC EXCITATION [AIAA 80-0456] 880-26956 Damping problems in acoustic fatigue Selected wind-tunnel testing developments at the 880-19580 Boeing Aerodynamics Laboratory ACOUSTIC MEASUREMENTS (AIAA 80-0458] 880-26958 Aerodynamic and acoustic investigations of axial A new rig for flight mechanics studies in the flow fan and compressor blade rows, including ONERA Aerothermodynamic Test Center of Modane three-dimensional effects [AIAA 80-0464] 880-26961 [AD-A077712] 1180-19116 A system for the measurement of the attitude of ACOUSTIC SIMULATION wind tunnel models Methods of sound simulation and applications in [AIAA 80-0465] 880-26962 flight simulators The development of a self-streamlining flexible [NASA-TM-75768] 1180-19133 walled transonic test section ACTUATION [8188 80-0440] 880-26964 Nonelectronic aspects of avionic system reliability Analytical determination of the influence of actuation elasticity and mass distribution on the N80-19535 aerodynamic characteristics of an aircraft in ADHESIVE BONDING quasi-steady motion Primary Adhesively Bonded Structure Technology A80-27132 (PABST) . General material property data Hysteresis of aerodynamic characteristics --- for bonding airframes wing models and segmented conical bodies of (AD-A077891] N80-19268 revolution ADHESIVES 880-27167 The fabrication and testing of prototype UH-1 Similarity of the aerodynamic characteristics of aircraft windshields manufactured with a sheet delta wings at supersonic speeds interlayer 880-27168 (AD-A077711) 1180-19080 Method of determining steady-state aerodynamic Primary Adhesively Bonded Structure Technology characteristics for an elastic aircraft in free (PABST) - General material property data longitudinal motion bonding airframes 880-27173 [AD-A077891] 1180-19268
A-i AERODYNAMIC COEFFICIENTS SUBJECT INDEX
An osperiinental investigation of two large annular Hypersonic interference flow flight experiment diffusers with swirling and distorted inflow design --- investigating aerodynamic heating and [NASA-rP-1628] 880-17984 loads Rind-tunnel/flight correlation study of [AD-1078861) 880-19044 aerodynamic characteristics of a large flexible AERODYNAMIC STABILITY supersonic cruise airplane (XB-70-1) 3: A Description of a new high-alpha, high-load, comparison between characteristics predicted pitch-yaw dynamic stability test mechanism at AEDC from wind-tunnel measurements and those measured [AIAA 80-0451] A80-26952 in flight Application of the Estimation-Before-Modeling (NASA-TP-1516] 880-17986 (EBM) system identification method to the high Rotary balance data for a typical single-engine angle of attack/sideslip flight of the T-2C jet general aviation design for an angle-of-attack trainer aircraft. Volume 3: Identification of range of 8 deg to 90 deg. 1: Low-wing model A 7-2C aerodynamics stability and control fluid flow and vortices data for general characteristics from actual flight test data aviation aircraft to determine aerodynamic [AD-A079924] 880-19072 characteristics for various designs Development of aerodynamic disturbance test (NASA-CB-3100] 880-19030 procedures, volume 1: Executive summary A flight investigation of blade section (PB80-108145] 880-19991 aerodynamics for a helicopter main rotor having AERODYNAMIC STALLING NLR-1T airfoil sections NCAIR design philosophy for fighter aircraft (NASA-Til-80166] N80-19033 departure and spin resistance Wind tunnel test to investigate aerodynamic (SAE PAPER 791081] A80-26637 hysteresis phenomena of the F-U and F-il Control system techniques for improved aircraft models departure/spin resistance for fighter aircraft [AD-A077196) 880-19040 (SAE PAPER 7910833 A80-26639 Proceedings of a Workshop on V/STOL Aircraft CL-600 Challenger Aerodynamics, volume 2 --- conferences A80-27387 (AD-A078909] 880-19042 Straight-walled, two-dimensional diffusers - Core compressor exit stage study. 1: Aerodynamic Transitory stall and peak pressure recovery and mechanical design A80-27746 [NASA-CR-159714] 880-19113 Effect of wake-type nonuniform inlet velocity AERODYNAMIC COEFFICIENTS profiles on first appreciable stall in Comparison of aerodynamic coefficients obtained plane-wall diffusers from theoretical calculations wind tunnel tests A80-27747 and flight tests data reduction for the alpha Dynamic stall on oscillating airfoils in jet aircraft oscillating free-streams ( NASA-TM-75237] 880-17991 880-17983 Aircraft identification experience Transient effects on a stalled airfoil in a 880-19100 pulsating flow: Comparison with results from a Rotorcraft identification experience similar airfoil undergoing horizontal shaking N80-19101 during wind tunnel tests Identification experience in extreme flight regimes [AAAF-NT-79-13] 880-18003 880-19102 Rotors in forward flight and dynamic stall Wind tunnel and free flight model identification (AAAF-NT-79-20] 880-18050 experience AERODYNAMICS N80-19103 Aircraft store separation motion prediction via Closed loop aspects of aircraft identification grid data trajectories N80-19104 [AIAA 80-0462] A80-26959 AERODYNAMIC DRAG Computational aerodynamics on large computers Wind tunnel and flight test drag comparisons for a A80-27415 guided projectile with cruciform tails Workshop on Aircraft Surface Representation for [AIAA 80-0426] A80-26968 Aerodynamic Computation Influence of the empennage on the effective thrust NASA-TR-811701 880-19025 of jet engine exhaust nozzles Digital computer solution of aircraft longitudinal A80-27139 and lateral directional dynamic characteristics Induced drag and lift-drag ratio of swept wings at [AD-A078672] 880-19068 supersonic speeds Application of the Estimation-Before-modeling A80-27175 (ERR) system identification method to the high Class of shockfree airfoils producing the same angle of attack/sideslip flight of the T-2C jet surface pressure trainer aircraft. Volume 1: Executive summary A80-28 857 [AD-A080025] 880-19073 Undercarriage drag prediction methods Proceedings of a Workshop on V/STOL Aircraft [ESDU-79015] 880-19028 Aerodynamics, volume 1 AERODYNAMIC FORCES [AD-A079115] 880-19074 An investigation of F-16 nozzle-afterbody forces FORTRAN program oblique in P1-format user's manual at transonic Mach numbers with emphasis on [AD-A077809) 880-19880 support system interference NASA authorization, 1981, program review, volume 2 [AD-A078693] 880-18046 [GPO-56-220) 880-19988 AERODYNAMIC HEAT TRANSFER Air Force Flight Dynamics Laboratory fiscal year A study of nonadiabatic boundary-layer 1981. Technical objective document stabilization time in a cryogenic tunnel for [AD-A078973] 880-20020 typical wing and fuselage models AEROELASTICITY [AIAA 80-0417] A80-26932 Analytical determination of the influence of AERODYNANIC HEATING elasticity and mass distribution on the Hypersonic interference flow flight experiment aerodynamic characteristics of an aircraft in design --- investigating aerodynamic heating and quasi-steady notion loads A80-27132 (AD-A078861] 880-19044 Method of determining steady-state aerodynamic AERODYNAMIC INTERFERENCE characteristics for an elastic aircraft in free Numerical simulation of the wind tunnel longitudinal motion environment by a panel method A80-27173 [AIAA 80-0419] A80-26933 AERONAUTICAL ENGINEERING The simulation and modeling of jet plumes in wind Major areas of research in aeronautics and air tunnel facilities traffic at the German Aerospace Research [AIAA 80-0430] A80-26941 Establishment /DFVLR/ AERODENANIC LOADS A80-28491 Structural design of transport airplanes for NASA authorization, 1981, program review, volume 2 transient environments [GPO-56-220] 880-19988 A80-27898
A-2
SUBJECT INDEX AIR TRAFFIC CONTROL
Air Force Flight Dynamics Laboratory fiscal year AIR LAUNCHING 1981. Technical objective document Control and data acquisition aircraft for ALCM [AD-A078973] 880-20020 flight tests --- Air Launched Cruise Missile AEROTHEBMOD!NAMICS [AIRA 80-0446] A80-26950 A new rig for flight mechanics studies in the AIR NAVIGATION ONERA Aerothermodynamic Test Center of Modane Outlook for Global Positioning System /GPS/ in [AIAA 80-0464] 880-26961 civil aircraft operations Influence of the angle of attack on the thermal A80-25158 flux at the stagnation point at supersonic speeds The Federal Aviation Administration navigation 880-27138 program APTERBODIES 880-26819 An investigation of F-16 nozzle-afterbody forces Tactical navigation system testing at transonic Mach numbers with emphasis on A80-27237 support system interference The laser gyro and its application to an [AD-A078693] 880-18046 helicopter navigation system AGRICULTURAL AIRCRAFT 880-28221 Development of test methods for scale model The introduction of new systems in international simulation of aerial applications in the NASA civil aviation Langley Vortex Facility 880-28383 (AIAA 80-01427] 880-26939 AIR TRAFFIC Full scale visualization of the wing tip vortices The future development of air traffic as seen by generated by a typical agricultural aircraft airline companies [NASA-CR-162796] 880-17992 A80-28487 AH-1G HELICOPTER Influence of air traffic on the concept of air A flight investigation of blade section traffic control aerodynamics for a helicopter main rotor having 880-284 88 NLR-1T airfoil sections Major areas of research in aeronautics and air [NASA-TM-80166] 880-19033 traffic at the German Aerospace Research AILERONS Establishment /DPVLR/ Advanced composite aileron for L-1011 transport A80-28491 aircraft AIR TRAFFIC CONTROL [NASA-CR-162863] N80-18103 Optical design of airport control tower cabs Experimental investigation of a circulation 880-24746 control aileron A collision avoidance system using Navstar/GPS and [AD-A078825] 880-19046 ATCRBS AIR BAG RESTRAINT DEVICES A80-25157 Feasibility testing of a Body Inflatable Bladder Present-day problems of air traffic control in (BIB) restraint device ground-to-air communications (80-8078681) N80-18013 A80-26221 AIR BREATHING ENGINES Theoretical limitations on collision avoidance Fiber optic sensors for measuring angular position systems and rotational speed --- air breathing engines 880-26811 [NASA-TN-81 1454] 880-18368 The use of computer systems in air traffic contrcl The 4th International Symposium on Air Breathing 880 -27 223 Engines Airport radio navigation systems --- Russian book [AD-A078956] 880-19114 A80-27716 AIR CARGO The role of research applied to the air traffic The freight forwarder as an air carrier control system A80-28862 A80-28050 AIR CONDITIONING EQUIPMENT Capacity payoffs at large hub airports from ATC Air supply system approach for the Boeing Model initiatives 767 Airplane 880-28380 (SAE PAPER 791068] 880-26631 Primary radar in ATC AIR COOLING 88 0-2 8 3 8 1 One-dimensional aerodynamic control calculations Electronic flight rules /EFI4/ - A concept fcr for cooled gas turbines enhanced freedom of airspace A80-26305 880- 28 382 Algorithm for calculating turbine cooling flow and The introduction of new systems in international the resulting decrease in turbine efficiency civil aviation [NASA-TM-81453] 880-19863 A80-28383 AIR CUSHION LANDING SYSTEMS Adding more automation to the air traffic control New remotely piloted vehicle launch and recovery system concepts: Computer program listings A80-28384 [AD-A076611] 880-18035 Influence of air traffic on the concept of air New remotely piloted vehicle launch and recovery traffic control concepts. Volume 1: Analysis, preliminary A80-28486 design and performance/cost trade studies Avionics - The leading technology in flight [AD-A077475] N80-19066 guidance and air traffic control Analysis of trunk flutter in an air cushion A80-28492 landing system Report on the task force on aircraft separation (80-8079008) 880-19075 assurance, appendices --- systems analysis of Easy ACLS dynamic analysis, volume 2. Part 2: collision avoidance systems integration in the Component computer programs air traffic control airspace utilization system [80-8079803) 880-19076 [80-8077713] N80-18017 AIR DEFENSE Early flight test experience with Cockpit Fighter options for tactical air defense, Displayed Traffic Information (CDII) [SAE PAPER 791108] 880-26650 [NASA-TM-80221] 880-18037 The F-16 Wild Weasel: A feasibility study The effect of viewing time, time to encounter, and [AD-A077050] 880-19071 practice on perception of aircraft separation on AIR FILTERS a cockpit display of traffic information Dissemination, resuspension, and filtration of (NASA-TM-81173] 880-18038 carbon fibers --- aircraft fires Standard engineering installation package. Air 880-19196 Traffic Radio Channel Control (ATRCC) equipment AIR INTAKES (AD-A077648) 880-19059 Numerical method for calculating supersonic flow Structures in aeronautical phraseology: From past a plane air intake with detached shock wave English to Spanish A80-27148 880-19978
8-3 AIR TRAFFIC CONTROLLERS (PERSONNEL) SUBJECT INDEX
AIR TRAFFIC CONTROLLERS (PERSONNEL) Factorial design of experiments in the test and Legal liability of the controller. I evaluation of a complex control system --- for A80-28500 carrier-based aircraft landing AIR TRANSPORTATION 880-27242 Legal liability of the controller. I AIRCRAFT COMMUNICATION 880-28 500 Error rate performance of M-ary DPSK systems in The freight forwarder as an air carrier satellite/aircraft communications 880-28862 880-25945 The aerial relay system: An energy-efficient Application of Nd:YAG optical communications solution to the airport congestion problem technology for aircraft to satellite links [NASA-TM-80208] N80-18011 880-26797 AIRBORNE EQUIPMENT Modelling of aircraft responses to EMP A tine-shared monopulse approach to air/surface 880-27778 radar ranging Buoyant module VHF antenna design for submerged A80-26791 systems/aircraft communications Airborne video instrumentation/data reduction A80-28254 A80-27232 The role of BF in air-ground communications: An Angular vibration measurement techniques overview airborne electro-optical package disturbances H80-19373 N80-18222 HF communication to small low flying aircraft Military adaption of a commercial VOR/ILS airborne 1180-19374 radio with a reliability improvement warranty Modern HF communications for low flying aircraft 880-19540 880-19375 AIRBORNE SURVEILLANCE RADAR Modeling and Simulation of Avionics Systems and Airborne radar approach system flight test Command, Control and Communications systems experiment conferences (AD-A077900] N80-19054 [AGARD-CP-268] 880-19809 The application of modeling and simulation to the A JTIDS performance model for the B-38 development of the E-3A R80-19825 B80-19823 AIRCRAFT COMPARTMENTS AIRBORNE/SPACEBORNE COMPUTERS Measurements of cabin and ambient ozone on 8747 On-board precision approach system using NAVSTAR GPS airplanes A80-25162 880-28853 E-38 navigational computer system real-time Evaluation of aircraft windshield materials in a environmental simulator simulated supersonic flight environment 880-19824 [80-8078673] 880-19082 Simulation for integration with dynamic tests of AIRCRAFT CONFIGURATIONS the logical elements of principal onboard Multirole cargo aircraft options and configurations computers [SAE PAPER 791096) 880-26645 880-19842 Future large cargo aircraft technology NSSC-2 operating system design requirements 880-27269 specification Technological aspects of future very large airplanes [NASA-CR-161396] 880-19861 880-28490 AIRCRAFT ACCIDENT INVESTIGATION Workshop on Aircraft Surface Representation for Aircraft motion analysis using limited flight and Aerodynamic Computation radar data (NASA-TM-81170] 880-19025 880-27241 A fault tolerant architecture approach to avionics Human factors in high speed low level accidents: reliability improvement A 15 year review N80-19533 [AD-A076221] 880-18012 AIRCRAFT CONSTRUCTION MATERIALS Aviation safety and its improvement The cautious course to introducing new SDM [VTH-LR-260] 880-18014 technology into production systems AIRCRAFT ACCIDENTS Structures, Dynamics and Materials Aircraft emergency decisions: Cognitive and 880-26343 situational variables Induced effects of lightning on an all composite (80-8077413] 880-19051 aircraft Assessment of Carbon Fiber Electrical Effects 880-27783 (NASA-CP-2119] N80-19193 The potential for damage from the accidental Approach to the assessment of the hazard --- fire release of conductive carbon fibers from burning released carbon fiber electrical effects composites 880-19 194 [NASA-TM-80213] 880-18108 Release of carbon fibers from burning composites Advanced aluminum alloys from rapidly solidified 880-19 195 powers Dissemination, resuspension, and filtration of [80-8077197] 880-18161 carbon fibers --- aircraft fires Development of advanced aluminum alloys from 880-19 196 rapidly solidified powders for aerospace Large-scale fiber release and equipment exposure structural applications experiments --- aircraft fires [AD-A077800] 880-18162 N80-19198 A review of Australian investigations on Surveys of facilities for the potential effects aeronautical fatigue during the period April from the fallout of airborne graphite fibers 1977 to March 1979 --- structural strain and 880-19199 fatigue life studies on aircraft structures and Assessment of the risk due to release of carbon construction materials fiber in civil aircraft accidents, phase 2 (AD-A071641] 880-18449 880-19 200 AIRCRAFT CONTROL AIRCRAFT ANTENNAS Aircraft instruments and automatic systems /3rd Experimental procedure to determine limits of ISM revised and enlarged edition/ --- Russian book interference affecting navigational ILS equipment 880-26350 Industrial, Scientific and Medical Control system techniques for improved 880-27760 departure/spin resistance for fighter aircraft Comparison of measured data with IF-77 propagation [SAE PAPER 791083] 880-26639 model predictions Control and data acquisition aircraft for ALCM (AD-A076508) 880-18259 flight tests --- Air Launched Cruise Missile AIRCRAFT CARRIERS [AIAA 80-0446] 880-26950 Breaking V/STOL free of Catch 22 --- technology Singularities of the numerical solution of the utilization and assessment algebraic Riccati equation in matrix form by a 880-26342 modification of the Lax-Wendroff method --- for automatic aircraft control A80-27134
8-4
SUBJECT INDEX AIRCRAFT EQUIPMENT
Implicit model following and parameter The energy problem: Its effect on aircraft design. identification of unstable aircraft I - Supply and demand A80-28019 880-27752 Application of the Estimation-Before-Modeling Structural design of transport airplanes for (ERR) system identification method to the high transient environments angle of attack/sideslip flight of the I-2C jet A80-27898 trainer aircraft. Volume 3: Identification of Major areas of research in aeronautics and air T-2C aerodynamics stability and control traffic at the German Aerospace Research characteristics from actual flight test data Establishment /DFVLR/ [80-80799214] 1480-19072 880-281491 Parameter Identification --- conference on Coming civil transport aircraft with active techniques applied to aircraft flight test data control elements (AGARD-LS-104) 980-190914 880-28493 Aircraft parameter identification methods and The aerodynamics of future transport aircraft and their applications: Survey and future aspects the role of the wind tunnel during development 980-19095 880-281494 Identification evaluation methods The aerial relay system: An energy-efficient 980-19096 solution to the airport congestion problem Practical input signal design --- for identifying [NASA-TN-80208] 980-18011 stability and control derivatives Rotary balance data for a typical single-engine N80-19097 general aviation design for an angle-of-attack Aircraft identification experience range or 8 deg to 90 deg. 1: Low-wing model A 980-19100 fluid flow and vortices data for general Rotorcraft identification experience aviation aircraft to determine aerodynamic N80-19101 characteristics for various designs Identification experience in extreme flight regimes [NASA-CB-3100] 980-19030 980-19102 The F-16 Wild Weasel: A feasibility study Wind tunnel and free flight model identification [AD-A077050] 980-19071 experience Thrust vectoring to eliminate the vertical 980-19103 stabilizer --- to provide directional stability Closed loop aspects of aircraft identification for f-ill aircraft while decreasing radar 980-191014 detectability AIRCEAPT DESIGN [AD-A079852] 1480-19077 Increasing aircraft efficiency through laminar NASA authorization, 1981, program review, volume 2 flow control [GP0-56-220] 1480-19988 A80-24899 AIRCRAFT DETECTION CADO on the F-18 program --- Computer Aided Design Hybrid optical/digital processing for target and Drafting identification A80-26345 880-26867 NCAIR design philosophy for fighter aircraft Thrust vectoring to eliminate the vertical departure and spin resistance stabilizer --- to provide directional stability (SAE PAPER 791081) 880-26637 for f-ill aircraft while decreasing radar High-angle-of-attack flying qualities - An detectability overview of current design considerations [AD-A079852] 1480-19077 [SAE PAPER 791085] A80-26640 AIRCRAFT ENGINES Future multi-mission transport aircraft - Theory of by-pass ducted-fan engines --- Russian Requirements and design possibilities book [SAE PAPER 791097] 880-26646 A80-26349 Reliability and maintainability design standards Constant speed 400 Hz aircraft electric generation from readiness-related goals --- for naval system aircraft weapon systems (SAE PAPER 791067] 880-26630 [SAE PAPER 791109] A80-26651 Opportunistic maintenance policies for economic The influence of wing, fuselage and tail design on replacement of internal life-limited components rotational flow aerodynamics data obtained in modular aircraft engines beyond maximum lift with general aviation [SAE PAPER 791101] 880-26647 configurations On-condition maintenance - Review of military [AIAA 80-0455] 880-26955 engines A single-step method of optimizing statically [SAE PAPER 791102] 880-26648 indeterminate minimum-volume systems Simulating the shock protection performance of A80-27135 large transit packs by means of small scale Minimum-weight wing in the presence of lift laboratory models --- applicable to aircraft constraints engine power plant design 880-27136 880-27790 Application of geometrical programming to problems Wear of seal materials used in aircraft propulsion of optimal design systems A80-27137 880-28010 Improvement of the convergence of the method of Aeropropulsion in year 2000 polynomials in designing small-aspect-ratio wings (NASA-TM-81416) 1480-18043 880-27183 Accuracy and repeatability indices for joint oil The Quiet Short-Haul Research Aircraft /QSBA/ analysis program data A80-27384 [AD-A078156] 4180-19266 The development of the worlds first triengine AIRCRAFT EQUIPMENT business jet, the Nystere Falcon 50 Air supply system approach for the Boeing Model 880-27386 767 Airplane Crossing the Channel in the Gossamer Albatross [SAE PAPER 791068] A80-26631 A80-27389 Flight recording in the UK. I - Evolution Fundamentals of design. V - Fin design for combat A80-27751 aircraft Air speed and attitude probe A80-27725 (NASA-CASE-FEC-11009-1 ) 1480-18036 767 - A Hoeing for the eighties Specification for the installation of electrical 880-27726 resistance strain gauges on strain pairs counter The light fighter market . . . and a European aircraft --- to monitor fatigue damage proposal [AD-A071363J 1480-18369 880-27727 Airborne radar approach system flight test Fundamentals of design. VI - Tailplanes, tailless experiment and canard design [80-8077900] 4180-19054 880-27728 The F-16 Wild Weasel: A feasibility study [AD-A077050] 1480-19071
A-S
AIRCRAFT FUELS SUBJECT INDEX
An analytical and experimental study of aircraft A flight simulation investigation on the hydraulic lines including the effect of mean flow feasibility of curved approaches under MIS [AD-A079796] N80-19079 guidance Dynamic Environmental Qualification Techniques 1180-19844 [AGB0-R-682] N80-19090 Modeling and flight simulation of an active Dynamic environments and test simulation for configured aircraft under R.L.S. guidance qualification of aircraft equipment and external H80-19845 stores Predicting field of view requirements for VSTOL N80-19092 aircraft approach and landing Civil aircraft equipment environment qualification N80-19847 techniques AIRCRAFT MAINTENANCE 1180-19093 The practical aircraft hydraulic test stand comparison of specifications for Head-Up Displays (SAE PAPER 791079] A80-26636 in the Navy A-AN, A-7E, AV-8A, and F-14A aircraft Opportunistic maintenance policies for economic (AD-A080347] 1180-19106 replacement of internal life-limited components Flight path displays in modular aircraft engines (AD-A077181] 1180-19107 [SAE PAPER 791101] A80-26647 Power system control study. Phase 1: Integrated On-condition maintenance - Review of military control techniques engines EAD-A0 7 8 1129] 1180-19125 [SAE PAPER 791102] A80-26648 Simulation for integration with dynamic tests of Repair of advanced composite structure --- in the logical elements of principal onboard aircraft computers A80-26888 1180-19842 Have Bounce --- validation of computer simulations AIRCRAFT FUELS of P-4 dynamic response to multiple runway repairs A mass flowmeter with compensation for thermal A80-27382 density variations of the fluid Aircraft transparency failure and logistical cost A80-25220 analysis: Supplemental study The energy problem: Its effect on aircraft design. [AD-A075500] 1180-18033 I - Supply and demand Proceedings of the 7th Ann. Tr-Service Meeting A80-27752 for Aircraft Engine Monitoring and Diagnostics Initial characterization of an Experimental conferences Referee Broadened-Specification (ERRS) aviation [AD-A076126] 1180-18045 turbine fuel Estimating the time required to transition [NASA-TN-81440] N80-18205 aircraft fleets to new scheduled maintenance AIRCRAFT GUIDANCE intervals Electronic flight rules /EFR/ - A concept for [AD-A078606] N80-19027 enhanced freedom of airspace AIRCRAFT MANEUVERS A80-28382 Minimum time turns with thrust reversal --- using Avionics - The leading technology in flight control theory guidance and air traffic control [AD-A079851] 1180-19078 A80-28492 AIRCRAFT MODELS AIRCRAFT INDUSTRY Development of test methods for scale model Pratt and Whitney innovations --- turbomachine simulation of aerial applications in the NASA blade casting and hot isostatic pressing of Langley Vortex Facility turbine disks [AIAA 80-0427] A80-26939 A80-25448 The role of the aircraft model in avionic systems Value analysis and the optimum cost concept simulation applied to aerospace N80-19837 A80-27 202 AIRCRAFT NOISE AIRCRAFT INSTRUMENTS Local ground noise generated by supersonic An induction gyrocompass transport planes A80-2521 4 A80-26206 Aircraft instruments and automatic systems /3rd Methods of sound simulation and applications in revised and enlarged edition/ --- Russian book flight simulators A80-26350 [NASA-TM-75768] N80-19133 Aircraft program for target background, and sky AIRCRAFT PARTS radiance measurements The fatigue performance of service aircraft and [AD-A076959] 1180-18624 the relevance of laboratory data Methods used for discerning the reliability of A80-27789 military aircraft radar AIRCRAFT PERFORMANCE N80-19532 Production Eagle and its potential Reliability of high-brightness CRTs for airborne [SAN PAPER 791071] A80-26634 displays VSTOL test techniques utilizing laser tracking N80-19543 AIRCRAFT LANDING A80-27234 Testing the F-18 at the U.S. Naval Air Test Center Design of an electronic model of a microwave A80-27239 aircraft landing system F/A-18 status report A80-26471 A80-27377 Airport radio navigation systems --- Russian book F-16 European test and evaluation A80-27716 A80-27380 Development of a normalized probability YAV-8B status report distribution for lateral load factors due to A80-27381 aircraft ground turning The Quiet Short-Haul Research Aircraft /QSRA/ [AD-A077047] 1180-19070 A80-27384 Easy AdS dynamic analysis, volume 2. Part 2: The development of the world's first triengine Component computer programs business jet, the Mystere Falcon 50 [AD-A079803] 1180-19076 A80-27386 A computer program for estimating aircraft landing Technological aspects of future very large airplanes distance A80-28490 (AD-A077169] 1180-19088 Parameter Identification --- conference on Application of the concept of dynamic trim control techniques applied to aircraft flight test data to automatic landing of carrier aircraft AGAED-LS-104) 1180-19094 utilizing digital feedforeward control Aspects of flight test instrumentation --- methods [NASA-TP-1512) 1180-19126 to derive aircraft performance and stability and Design considerations for attaining 250-knot test control characteristics velocities at the aircraft landing dynamics 1180-19098 facility [NASA-TM-80222] 1180-19132
A-6
SUBJECT INDEX AIRCRAFT SURVIVABILITY
Analysis of aircraft performance stability and AIRCRAFT STRUCTURES control measures NAVAIR pushes SPF/DB for structures --- in naval N80-19099 aircraft design and construction AIRCRAFT PRODUCTION A80-24739 New materials and methods for airframe construction Rain erosion of lightning protection coatings for A80-28495 carbon fibre composites Fastener hole quality, volume 1 --- design A80-25059 analysis of fatigue life and drilling techniques AV-8B - A second generation V/STOL for fasteners in aircraft production [SAN PAPER 791070] A80-26633 [AD-A077859] N80-19567 Fatigue in machines and structures - Aircraft AIRCRAFT RELIABILITY A80-26731 Problems of older jet aeroplanes - A regulatory Failure mechanisms for advanced composite sandwich authority view construction in hostile environments --- naval A80-2511145 aircraft structures Production Eagle and its potential 880-26884 [SAE PAPER 791071] A80-26634 Repair of advanced composite structure --- in NRC in lightweight helicopters - Special problems aircraft and experience in design and control 880-26888 A 80-27773 Advanced composites serviceability program - The fatigue performance of service aircraft and Status review --- inspection of aircraft the relevance of laboratory data structures A80-27789 A80-26890 Aviation safety and its improvement Nondestructive evaluation of graphite composite (VTH-LP.-260] N80-18014 aircraft structures Significance of large scatter of composite 880-26891 properties to aircraft reliability Measurements of control stability characteristics (AD-A077804] N80-19062 of a wind-tunnel model using a transfer function Preliminary Airworthiness Evaluation UH-1R method helicopter equipped with Multiple Target [AIAA 80-0457] 880-26957 Electronic Warfare System (RULTEWS) Analytical determination of the influence of [AD-A078476] N80-19067 elasticity and mass distribution on the Reliability management of the avionic system of a aerodynamic characteristics of an aircraft in military strike aircraft quasi-steady motion N80-19546 A80-27132 AIRCRAFT SAFETY The use of the spectral summation of fatigue Theoretical limitations on collision avoidance damages in order to examine the combined stress systems state of structures A80-26811 880-27152 Lightning protection for aircraft Method of determining steady-state aerodynamic A80-27021 characteristics for an elastic aircraft in free The potential for damage from the accidental longitudinal motion release of conductive carbon fibers from 880-27173 aircraft composites Applying pressure . - . Relieving stress A80-27596 stress coining aircraft structures NASA aviation safety reporting system 880-27251 [NASA-TM-78608] N80-18010 The potential for damage from the accidental Aviation safety and its improvement release of conductive carbon fibers from [VTB-LR-260] N80-18014 aircraft composites Propulsion and energetics panel Working Group 11 A80-27596 on aircraft fire safety. Volume 2: Rain report Composite components on commercial aircraft (AGARO-AR-132-VOl-2] N80-19047 880-27597 Assessment of the risk due to release of carbon Cast aluminum primary aircraft structure fiber in civil aircraft accidents, phase 2 880-27875 N80-19 200 Technological aspects of future very large airplanes Assessment of risk due to the use of carbon fiber A80-28490 composites in commercial and general aviation New materials and methods for airframe construction N80-19201 880-28495 AIRCRAFT SPECIFICATIONS Composite components on commercial aircraft Production Eagle and its potential (NASA-TM-80231] N80-18 109 (SAN PAPER 791071] A80-26634 Angular vibration measurement techniques AIRCRAFT SPIN airborne electro-optical package disturbances Thrust augmented spin recovery device N80-18222 [NASA-CASE-LAR-11970-2] N80-18048 A review of Australian investigations on AIRCRAFT STABILITY aeronautical fatigue during the period April On the equations of motion about the mass centre 1977 to March 1979 --- structural strain and of the jet aircraft considered as variable mass fatigue life studies on aircraft structures and system construction materials A80-26325 (AD-A071641] N80-18449 Control system techniques for improved Significance of large scatter of composite departure/spin resistance for fighter aircraft properties to aircraft reliability (SAN PAPER 791083] A80-26639 (80-8077804] N80-19062 Description of a new high-alpha, high-load, USAF damage tolerant design handbook: Guidelines pitch-yaw dynamic stability test mechanism at AEDC for the analysis and design of damage tolerant (ATAA 80-0451] A80-26952 aircraft structures, revision A Measurements of control stability characteristics [80-8078216) N80-19065 of a wind-tunnel model using a transfer function The history of static test and Air Force method structures testing [AIAA 80-0457] A80-26957 (AD-A077029] N80-19136 Implicit model following and parameter Some recent measurements of structural dynamic identification of unstable aircraft damping in aircraft structures A80-28019 N80-19576 Aircraft identification experience Damping problems in acoustic fatigue N80-19100 N80-19580 Rotorcraft identification experience AIRCRAFT SURVIVABILITY N80-19101 General aviation airplane structural Identification experience in extreme flight regimes crashworthiness programmers manual N80-19102 (AD-8075737) N80-18008 Perspective on the results N80-19202
A-i AIRCRAFT TIRES SUBJECT INDEX
AIRCRAFT TIRES The re-organization of airport administration in Improved tire/wheel concept --- pneumatic aircraft Canada tire ( NASA-CASE-LAR-11695-2] A80-25245 N80-18402 Simulation defines alternatives for Copenhagen AIRFOIL PROFILES terminal expansion Visualization of the laminar-turbulent transition 480-27221 in the flow over an airfoil using the smoke-wire Aeropuerto de Caracas - An unusual new general technique aviation facility near the city (AIAA 80-0421] 480-26935 AR 0-2722 2 High-resolution LDA measurements of Reynolds Primary radar in ATC stress in boundary layers and wakes A80-28381 [AIAA 80-0436] 480-26967 AIRPORT TONERS Wind-turbine power improvement with modern airfoil Development and test of low-impact resistant towers sections and multiple-speed generators (AD-1077160] 880-18052 (AIAA 80-0633] 480-28819 AIRPORTS Flutter analysis of a RACA 64A006 airfoil in small Aeropuerto de Caracas - An Unusual new general disturbance transonic flow aviation facility near the city A80-28851 AR 0-27222 Application of unsteady airfoil theory to rotary Capacity payoffs at large hub airports from ATC wings initiatives 480-28856 A80-28380 Class of shockfree airfoils producing the same Nondestructive evaluation of airport pavements. surface pressure Volume 1: Program references A 80-28857 [AD-A078835] 880-18051 Identification of noise sources in FC centrifugal Nondestructive evaluation of airport pavements. fan rotors Volume 2: Operational manual for PAVBEN program N80-18395 at ICC AIRFOILS [AD-4079495] N80-19130 New approaches to sailing AIRSHIPS A80-26344 New approaches to sailing Laminar separation bubble with transition /theory A80-2634'4 and experiment/ Airships - Basis for a new oceanic capability [08884, TP NO. 1980-20] A80-27203 A80-28269 The aerodynamic design of an advanced rotor airfoil AIRSPEED [NASA-CR-2961] N80-17989 Air speed and attitude probe Transient effects on a stalled airfoil in a [NASA-CASE-FRC-11009-1) N80-18036 pulsating flow: Comparison with results from a ALGORITHMS similar airfoil undergoing horizontal shaking Concepts for generating optimum vertical flight during wind tunnel tests profiles (AAAF-HT-79-13) N80-18003 (NASA-CR-159181] N80-18031 Investigation of the boundary layer behavior on Algorithm for calculating turbine cooling flow and turbine airfoils the resulting decrease in turbine efficiency [AD-A075501] 880-18044 (NASA-TN-81453) 880-19863 A flight investigation of blade section ALL-NEATHER AIR NAVIGATION aerodynamics for a helicopter main rotor having Development and flight test of a two-place NLR-1T airfoil sections night/adverse weather A-10 for the close-air [NASA-TN-80166] 880-19033 support and battlefield attack mission AIRFRAME MATERIALS (SAE PAPER 791069) A80-26632 New materials and methods for airframe construction Night/adverse weather 4-10 evaluatcr program 480-28 495 /4-108/. V. H. Shawler AIRFRAMES 48 0-27 378 Handling quality requirements for advanced The Tornado all-weather high-speed low-level system aircraft design longitudinal mode A80-27379 [40-4077858] N80-19128 ALPHA JET AIRCRAFT Primary Adhesively Bonded Structure Technology Comparison of aerodynamic coefficients obtained (PABST) . General material property data from theoretical calculations wind tunnel tests bonding airframes and flight tests data reduction for the alpha [AD-A077891] N80-19268 jet aircraft AIRLINE OPERATIONS [ NASA-Tn-75237] N80-17991 Outlook for Global Positioning System /GPS/ in ALTITUDE civil aircraft operations Recovery system prelimiminary design. A A80-25158 simplified approach to determining staging, Problems of older jet aeroplanes - A regulatory timing and altitude requirements for fast authority view inflating parachutes 480-25445 [AD-A0775138] 880-19041 Simulation defines alternatives for Copenhagen ALUMINUM terminal expansion Design and test of a boron - aluminum high A80-27221 temperature wing Capacity payoffs at large hub airports from ATC (40-4075814) 880-18034 initiatives ALUMINUM ALLOYS A80-28380 Acceleration of multicycle fatigue testing on The future development of air traffic as seen by aluminum structural alloys airline companies A80-27479 A80-28 487 Cast aluminum primary aircraft structure A consideration of general aviation in the United Kingdom A80-27875 Advanced aluminum alloys from rapidly solidified (TT-7902] 880-17982 powers AIRPLANE PRODUCTION COSTS (AD-A077197] 880-18161 Value analysis and the optimum cost concert Development of advanced aluminum alloys from applied to aerospace rapidly solidified powders for aerospace 480-27202 structural applications AIRPORT BEACONS [AD-A077800] N80-18162 Airport radio navigation systems --- Russian book ANGLE OF ATTACK A80-27716 Effects of forebody, wing and wing-body-LEX AIRPORT PLANNING flowfields on high angle of attack aerodynamics Optical design of airport control tower cabs Leading Edge extensions A80-24746 [SAE PAPER 791082] 480-26638
4-8 SUBJECT INDEX AUTOMATIC TEST EQUIPMENT
Control system techniques for improved ASPECT RATIO departure/spin resistance for fighter aircraft Effect of sweep and aspect ratio on the (SAE PAPER 791083] A80-26639 longitudinal aerodynamics of a spanloader wing High-angle-of-attack flying qualities - An in- and out-of-ground effect --- conducted in - overview of current design considerations Langley V/STOL wind tunnel [SAE PAPER 791085] A80-26640 (NASA-TM-80199] 1180-17993 Exploratory investigation of the effects of vortex Core compressor exit stage study. 1: Aerodynamic bursting on the high angle-of-attack and mechanical design lateral-directional stability characteristics of [NASA-CE-159714] 1180-19113 highly-swept wings ASSEMBLY LANGUAGE [AIAA 80-0463] A80-26960 Using a language developed for aircraft simulators Influence of the angle of attack on the thermal advantages and disadvantages of using flux at the stagnation point at supersonic speeds FORTRAN and assembly language A80-27138 N80-19831 Application of the Estimation-Before-Modeling ATMOSPHERIC DIFFUSION (REM) system identification method to the high Dissemination, resuspension, and filtration of angle of attack/sideslip flight of the T-2C jet carbon fibers --- aircraft fires trainer aircraft. Volume 2: Simulation study B80-19196 using T-2C wind tunnel model data Large-scale fiber release and equipment exposure [AD-A079923] 1180-19061 experiments --- aircraft fires Application of the Estimation-Before-Modeling N80-19198 (ERR) system identification method to the high Surveys of facilities for the potential effects angle of attack/sideslip flight of the T-2C jet from the fallout of airborne graphite fibers trainer aircraft. Volume 3: Identification of 1180-19199 T-2C aerodynamics stability and control ATMOSPHERIC ELECTRICITY characteristics from actual flight test data Atmospheric electricity and military operations [AD-A079924] 1180-19072 (AD-A078482) 1180-19693 Application of the Estimation-Before-modeling ATOMIC CLOCKS (EBN) system identification method to the high The Navstar Global Positioning System and time angle of attack/sideslip flight of the 1-2C jet A80-25146 trainer aircraft. Volume 1: Executive summary ATTACK AIRCRAFT [AD-A080025] 1180-19073 An approach to the runway denial problem ANGULAR VELOCITY [SAE PAPER 791107] A80-26649 Angular vibration measurement techniques ATTITUDE CONTROL airborne electro-optical package disturbances A system for the measurement of the attitude of 1180-18222 wind tunnel models Fiber optic sensors for measuring angular position [AIAA 80-0465] A80-26962 and rotational speed --- air breathing engines Thrust augmented spin recovery device [NASA-TM-81454] 1180-18368 [NASA-CASE-LAR-11970-2J 1180-18048 ANTENNA DESIGN ATTITUDE INDICATORS Buoyant module VHF antenna design for submerged Air speed and attitude probe systems/aircraft communications [NASA-CASE-FRC-11009-1) 1180-18036 A80-28254 ATTITUDE STABILITY ANTENNA RADIATION PATTERNS Fundamentals or design. V - Fin design for combat Experimental procedure to determine limits of ISM aircraft interference affecting navigational ILS equipment A80-27725 Industrial, Scientific and Medical AUTOMATIC CONTROL A80-27760 Advanced computer program --- for future Buoyant module VHF antenna design for submerged automation and system performance improvements systems/aircraft communications A80-26810 A80-28254 Automatic control of NASA Langleys 0.3-meter Comparison of measured data with IF-77 propagation cryogenic test facility model predictions [AIAA 80-0416] A80-26931 [AD-A076508] 1180-18259 Adding more automation to the air traffic control ANTENNAS system Shipboard antenna tests for GPS 180-28384 A80-25144 Influence of air traffic on the concept of air ANTISUBMARINE WARFARE AIRCRAFT traffic control A mission training simulator for the Nimrod HR MK A80-28488 2 and some aspects of the derivation and AUTOMATIC FLIGHT CONTROL verification of its system models Aircraft instruments and automatic systems /3rd 1180-19826 revised and enlarged edition/ --- Russian book APPROACH 180-26350 Analysis of fuel-conservative curved decelerating Singularities of the numerical solution of the approach trajectories for powered-lift and CTOL algebraic Riccati equation in matrix form by a jet aircraft modification of the Lax-Wendroff method --- for [NASA-TP-1650] 1180-19022 automatic aircraft control Flight evaluation of configuration management A80-27134 system concepts during transition to the landing Avionics - The leading technology in flight approach for a powered-lift STOL aircraft guidance and air traffic control [NASA-TM-811146] 1180-19127 A80-28492 APPROACH CONTROL AUTOMATIC LANDING CONTROL On-board precision approach system using NAVSTAR GPS Factorial design of experiments in the test and A80-25162 evaluation of a complex control system --- for A flight simulation investigation on the carrier-based aircraft landing feasibility of curved approaches under MIS 180-27242 guidance Application of the concept of dynamic trim control 1180-19844 to automatic landing of carrier aircraft Predicting field of view requirements for VSTOL Utilizing digital feedforeward control aircraft approach and landing (NASA-TP-1512] 1180-19126 1180-19847 AUTOMATIC PILOTS ARCHITECTURE (COMPUTERS) Aircraft instruments and automatic systems /3rd A fault tolerant architecture approach to avionics revised and enlarged edition/ ---- Russian reliability improvement book A83-2635Q N80-19533 AUTOMATIC TEST EQUIPMENT Preliminary assessment of an automated system for detecting present weather [AD-A078031] 1180-19706
A-9
AUTOMOBILES SUBJECT INDEX
AUTOMOBILES Modeling and Simulation of Avionics Systems and 1'evelopment of aerodynamic disturbance test Command, Control and Communications systems procedures, volume 1: Executive summary conferences [0590-108145] N80-19991 [AGARD-CP-268] 1180-19809 AUXILIARY POWER SOURCES Verification and validation of avionic simulations Improved MPG for the BAe 146 feeder-let 1180-19814 880-25449 E-3A navigational computer system real-time AVIONICS environmental simulator Development and flight test of a two-place 1180-19824 night/adverse weather A-10 for the close-air A mission training simulator for the Nimrod MR MK support and battlefield attack mission 2 and some aspects of the derivation and (SAE PAPER 791069] 880-26632 verification of its system models Experience from testing the Viggen electronic 1180-19826 systems utilizing existing computer capacity The role of the aircraft model in avionic systems 880-27235 simulation Firebrand anti-ship missile target - Flight test 1180-19837 program objectives and vehicle instrumentation Avionics evaluation program: Simulation models requirements for the effectiveness analysis of avionics 880-27236 1180-19838 Night/adverse weather A-10 evaluator program Simulation for whole life development /8-106/. N. B. Shawler N80-19839 880-27378 A simulation support system, the development tool Reliability growth testing of avionic equipment for avionic systems and subsystems A80-27612 1180-19840 EMC in lightweight helicopters - Special problems Fire control for air-to-air gunnery in high and experience in design and control performance fighter aircraft 880-27773 N80-19841 Avionics - The leading technology in flight Simulation for integration with dynamic tests of guidance and air traffic control the logical elements of principal onboard A80-28492 computers Navigation systems for approach and landing of 1180-19842 VTOL aircraft Cruise-missile-carrier navigation requirements [NASA-CR-152335] N80-19055 1180-19843 Dynamic Environmental Qualification Techniques Modeling the human operator: Applications to [AGARD-R-682] 1180-19090 system cost effectiveness Application of MIL-STD-810C dynamic requirements N80-19846 to USA? avionics procurements AXIAL COMPRESSION LOADS N80-19091 Minimum-mass designs of stiffened Civil aircraft equipment environment qualification graphite/polyimide compression panels techniques A80-27992 N80-19093 AXIAL PLOW Avionics interface data summaries: A-10A, Aerodynamic and acoustic investigations of axial EF-111A, F- 143, F-4G, ?-15A, F-16A, F-111A, flow fan and compressor blade rows, including F-111E, F-ill?, RF-4C three-dimensional effects [AD-A077388] N80-19105 (AD-8077712] 1180-19116 Flat bus fault sensors AXIAL PLOW TURBINES [AD-A077060] N80-19435 Optimal twisting of blades in axial turbomachines Avionics Reliability, Its Techniques and Related 880-21797 Disciplines --- conferences Algorithm for calculating turbine cooling flow and [AGABD-CP-261] N80-19519 the resulting decrease in turbine efficiency An analysis of the evolution of the reliability NASA-TM-81453] 1180-19863 and maintainability disciplines AXISYMMETRIC PLOW N80-19520 Evaluation of an analysis for axisymmetric Difficulties in predicting avionics reliability internal flows in turbomacbinery ducts N80-19521 880-27742 Reliability growth models N80-19522 A simulation program for the determination of B system reliability of complex avionic systems B-i AIRCRAFT N80-19523 Achieving effective Radar Cross Section flight A fault tolerant architecture approach to avionics pofiles on the B-i aircraft reliability improvement A80-27 227 N80-19533 Review of five years of flight testing the E-1 Trends in reliability modeling technology for A80-27388 fault tolerant systems Solid state power controller verification studies N80-19534 [AD-8078238] 1180-19429 Nonelectronic aspects of avionic system reliability 8-52 AIRCRAFT actuation Developing, mechanizing and testing of a digital N80-19535 active flutter suppression system for a modified Impacts of technologies selected on the B-52 wind-tunnel model reliability and operational availability of (NASA-CR-159155] 1180-19566 equipments. Cost considerations 8-70 AIRCRAFT 1180-19536 Wind-tunnel/flight correlation study of A new approach to maintainability prediction aerodynamic characteristics of a large flexible avionics, ground, and shipboard electronics supersonic cruise airplane (lB-b-i). 3: A N80-19537 comparison between characteristics predicted Reliability growth through environmental simulation from wind-tunnel measurements and those measured electronic equipment in flight N80-19538 [NASA-TP-1516] 1180-17986 The A-7 head-up display reliability programme BACKGROUND RADIATION N80-19539 Aircraft program for target background, and sky Reliability management of the avionic system of a radiance measurements military strike aircraft [AD-A076959] 1180-18624 N80-19546 BALL BEARINGS Formal methods for achieving reliable software Establishment of engineering design data for 1180-19 549 hybrid steel/ceramic ball bearings Software development for TORNADO: A case history (AD-A078934] 1180-19509 from the reliability and maintainability aspect N80-19554
A-i 0 SUBJECT INDEX CANOPIES
BALLISTICS BORON Fire control for air-to-air gunnery in high Design and test of a boron - aluminum high performance fighter aircraft temperature wing 880-19841 [AD-A075814] 880-18034 BEAMS (SUPPORTS) BORON REINFORCED MATERIALS Measurement of stress distribution in sandwich Composite components on commercial aircraft beans under four-point bending A80-27597 A80-25498 BOUNDARY LAYER CONTROL BENDING Increasing aircraft efficiency through laminar Measurement of stress distribution in sandwich flow control beams under four-point bending A80-24899 880-25498 Future large cargo aircraft technology BIBLIOGRAPHIES A80-27269 Carbon and graphite. Part 2. Carbon and graphite Boundary layer control by means of suction composites - excluding carbon fiber composites. [NASA-TM-75502] A 880-17987 bibliography with abstracts Experimental investigation of a circulation [P880-802374) 880-18144 control aileron Carbon and graphite. Part 1: Carbon and graphite [AD-A078825] 880-19046 fibers and fiber composites, volume U. A BOUNDARY LAYER FLOW bibliography with abstracts Laminar separation bubble with transition /theory [P880-802366] 880-18145 and experiment, Seals and gaskets. A bibliography with abstracts [ONERA, TP NO. 1980-20] [PB80-802010] 880-27203 880-18417 Investigation of the boundary layer behavior on Publications in acoustic and noise control from turbine airfoils NASA Langley Research Center during 1940-1979 (AD-A075501] 880-18044 bibliographies BOUNDARY LAYER STABILITY [NASA-TM-80211] N80-18884 A study of nonadiabatic boundary-layer Ames Research Center publications: A continuing stabilization time in a cryogenic tunnel for bibliography, 1978 typical wing and fuselage models [NASA-TM-81175] N80-18985 [AIAA 80-0417] 880-26932 Military aircraft and missile technology at the BOUNDARY LATER TRANSITION Langley Research Center: A selected bibliography Laminar separation bubble with transition /theory [NASA-TM-80204] 880-19024 and experiment/ Remotely piloted vehicles, volume 2. A [ONENA, PP NO. 1980-20] 880-27203 bibliography with abstracts Investigation of the boundary layer behavior on [P880-802119] 880-19089 turbine airfoils BIPLANES [AD-A075501] N80-18044 Prandtl's biplane theory applied to canard and BOX BEAMS tandem aircraft BIB rotor box beam fatigue test A80-28852 [An-A076931] 880-18450 BLUNT BODIES BROADBAND Influence of the angle of attack on the thermal Identification of noise sources in PC centrifugal flux at the stagnation point at supersonic speeds fan rotors 880-27138 880-18395 BODIES OF REVOLUTION BUBBLES Hysteresis of aerodynamic characteristics --- for Laminar separation bubble with transition /theory wing models and segmented conical bodies of and experiment/ revolution [ONEBA, PP NO. 1980-20) A80-27203 880-27167 BUS CONDUCTORS BODY-WING AND TAIL CONFIGURATIONS Flat bus fault sensors 767 - A Boeing for the 'eighties [AD-A077060] 880-19435 880-27 726 BODY-WING CONFIGURATIONS Effects of forebody, wing and wing-body-LET C flowfields on high angle of attack aerodynamics C-135 AIRCRAFT Leading Edge eXtensions The EC-135 - A successful multirole transport [SAE PAPER 791082] A80-26638 aircraft Analysis of the nonunigueness of solutions to the [SAE PAPER 791093] 880-26644 problem of flow separation for small-aspect C-141 AIRCRAFT delta wings Investigation of engine performance degradation of 880-27127 1F33-P-7 engines Data report for a test program to study transonic A80-27233 flow fields about wing-body/pylon/store Aerodynamic investigation of C-141 leading edge combinations. Volume 1: Tunnel empty flow modification for cruise drag reduction, volume 2 survey data, wing body force/moment/surface [80-8077688] 880-19081 pressure data, and pressure store CABIN ATMOSPHERES force/moment/surface pressure data Measurements of cabin and ambient ozone on 8747 [AD-A077182] 880-18001 airplanes Data report for a test program to study transonic 880-28 853 flow fields about wing-body/pylon/store CANADA combinations. Volume 2: Flow field survey data The re-organization of airport administration in for configurations 21 and 22 Canada [AD-A077183] 880-18002 A80-25245 Experimental investigation of a circulation CANADAIR AIRCRAFT control aileron Human factors in high speed low level accidents: [AD-A078825) N80-19046 A 15 year review BOEING AIRCRAFT [80-8076221] 880-18012 767 - A Boeing for the 'eighties CANARD CONFIGURATIONS A80-27726 Fundamentals of design. VI - Tailplanes, tailless BOEING 747 AIRCRAFT and canard design Measurements of cabin and ambient ozone on B747 airplanes A80-27728 Prandtl's biplane theory applied to canard and A80-28853 tandem aircraft Performance estimates of a Boeing 747-100 A80-28852 transport mated with an outsize cargo pod CANOPIES [NASA-TM-80227] 880-18032 A study of the canopy design for the advanced attack helicopter by use of computer graphics [An-A078291] 880-19069
A-li CARBON SUBJECT INDEX
CARBON Aerodynamic performance of a centrifugal Carbon and graphite. part 2. Carbon and graphite compressor with vaned diffusers composites - excluding carbon fiber composites. #80-27735 A bibliography with abstracts identification of noise sources in PC centrifugal N80-181114 fan rotors [PB80-802374] E80-18395 CARBON FIBER REINFORCED PLASTICS Rain erosion of lightning protection coatings for On the characteristics of carbon fibre composites centrifugal-reciprocating machines --- cryogenic 880-25059 coolers Graphite-epoxy panel compression strength [NASA-CR-162881] 880-19499 reduction due to local impact CENTRIFUGAL FORCE 880-27 598 Rotating stall in a vaneless diffuser of a CARBON FIBERS centrifugal fan The potential for damage from the accidental #8 0-27 73 4 release of conductive carbon fibers from CENTRIFUGAL PURRS aircraft composites Effect of non-rotating passages on performance of A 80-27596 centrifugal pumps and subsonic compressors The potential for damage from the accidental 880-27733 release of conductive carbon fibers from burning CERAMICS Novelceramic turbine rotor concepts composites N80-19118 [NASA-TN-80213] 880-18108 [AD-8078669] Carbon and graphite. Part 1: Carbon and graphite Establishment of engineering design data for fibers and fiber composites, volume 4. A hybrid steel/ceramic ball bearings bibliography with abstracts (#0-8078934) N80-19509 [PB80-802366] 880-18145 CESSNA AIRCRAFT Data reduction and analysis of graphite fiber Full scale visualization of the wing tip vortices release experiments generated by a typical agricultural aircraft 880-17992 [NASA-CE-159032] N80-19048 [NASA-CE-162796] Assessment of Carbon Fiber Electrical Effects CHARGED PARTICLES (NASA-CP-2119) 880-19193 Fog dispersion --- charged particle technique Approach to the assessment of the hazard --- fire (NASA-CR-3255] N80-19703 released carbon fiber electrical effects CHEMICAL COMPOSITION 880-19194 Initial characterization of an Experimental Release of carbon fibers from burning composites Referee Broadened-SpeCificatiCn (ERRS) aviation N80-19195 turbine fuel Dissemination, resuspension, and filtration of [NASA-TR-81440] 880-18205 carbon fibers --- aircraft fires CIRCUIT PROTECTION N80-19196 Flat bus fault sensors Evaluation of equipment vulnerability and (AD-A017060) 880-19435 potential shock hazards --- carbon fibers CIRCULATION N80-19197 Experimental investigation of a circulation Large-scale fiber release and equipment exposure control aileron experiments --- aircraft fires (80-8078825] N80-19046 880-19 198 CIVIL AVIATION Surveys of facilities for the potential effects Outlook for Global Positioning System /GPS/ in from the fallout of airborne graphite fibers civil aircraft operations N80-19199 A80-25158 Assessment of the risk due to release of carbon Nultirole cargo aircraft options and configurations fiber in civil aircraft accidents, phase 2 [SAE PAPER 791096] 880-26645 880-19200 The introduction of new systems in international Assessment of risk due to the use of carbon fiber civil aviation composites in commercial and general aviation A80-28383 N80-19201 Adding more automation to the air traffic control Perspective on the results system N80-19202 A80-28384 CARGO AIRCRAFT Coning civil transport aircraft with 'active' Nultirole cargo aircraft options and configurations control elements #80-28493 (SAP PAPER 791096] 880-26645 Future large cargo aircraft technology The aerial relay system: An energy-efficient 880-27269 solution to the airport congestion problem The changing horizons for technical progress. II (NASA-TN-80208] 880-18011 880-27270 Continued study of NAVSTAR/GPS for general aviation Airbus family concept for the 1990s (NASA-CR-159145] 880-18020 880-28489 Aeropropulsion in year 2000 Technological aspects of future very large airplanes [NASA-TN-81416] N80-18043 880-28490 Propulsion and energetics panel Working Group 11 Performance estimates of a Boeing 747-100 on aircraft fire safety. Volume 2: Main report transport mated with an outsize cargo pod ( AGARD-AB-132-VOL-2) R80-19047 (NASA-TM-80227) 880-18032 Structures in aeronautical phraseology: From CASCADE FLOW English to Spanish One-dimensional aerodynamic control calculations N80-19978 for cooled gas turbines CLUTTER A80-26305 Radiometric measurements of targets and clutter The experimental modeling of unstalled supersonic #80-26802 turbofan flutter COCKPITS [AIAA 80-04541 A80-26963 Early flight test experience with Cockpit CAST ALLOTS Displayed Traffic Information (CDTI) Cast aluminum primary aircraft structure (NASA-TN-80221] N80-18037 880-27875 The effect of viewing time, time to encounter, and CATHODE RAT TUBES practice on perception of aircraft separation on Reliability of high-brightness CRT5 for airborne a cockpit display of traffic information displays (NASA-TN-81173] R80-18038 880-19543 Crew station design facility feasibility study 1180-19064 CENTRIFUGAL COMPRESSORS [AD-A078134] Effect of non-rotating passages on performance of COINING centrifugal pumps and subsonic compressors Applying. pressure . . . Relieving stress A80-27733 stress coining aircraft structures A80-27257
8-12
SUBJECT INDEX COMPRESSIVE STRENGTH
COLD WORKING COMPLEX SYSTEMS Applying pressure . . . Relieving stress Factorial design of experiments in the test and stress coining aircraft structures evaluation of a complex control system --- for A80-27257 carrier-based aircraft landing COLLISION AVOIDANCE 880-27242 A collision avoidance system using Navstar/GPS and COMPONENT RELIABILITY ATCRBS VJSIOLAND avionics system flight-test data on a 880-25157 OH-1H helicopter Theoretical limitations on collision avoidance (NASA-TM-78591] 880-18047 systems COMPOSITE MATERIALS 880-26811 The cautions course to introducing new SOB Report on the task force on aircraft separation technology into production systems assurance, appendices --- systems analysis of Structures, Dynamics and Materials collision avoidance systems integration in the 880-26343 air traffic control airspace utilization system Advanced composites - Special topics; Proceedings [AD-A077713] 880-18017 of the conference, El Segundo, Calif., December COMBAT 4-6, 1979 Avionics evaluation program: Simulation models 880-26878 for the effectiveness analysis of avionics Influence of interface on composite failure N80-19838 880-26895 COMBINED STRESS The potential for damage from the accidental The use of the spectral summation of fatigue release of conductive carbon fibers from damages in order to examine the combined stress aircraft composites state of structures 880-27596 A80-27152 The potential for damage from the accidental COMBUSTION CHAMBERS release of conductive carbon fibers from burning Effect of wake-type nonuniform inlet velocity composites profiles on first appreciable stall in (NASA-TN-80213) 880-18108 plane-wall diffusers Carbon and graphite. part 2. Carbon and graphite 880-27747 composites - excluding carbon fiber composites. Study of research and development requirements of A bibliography with abstracts small gas-turbine combustors P880-802374] 860-18144 (NASA-CR-159796] 880-18040 Evaluation of aircraft windshield materials in a Evaluation of fuel character effects on 379 engine simulated supersonic flight environment combustion system [AD-8078673] 880-19082 (80-8078440) 880-19119 Assessment of Carbon Fiber Electrical Effects COMBUSTION PRODUCTS (NASA-CP-2119) 880719193 Characteristics of burning Jet A fuel and Jet A Approach to the assessment of the hazard --- fire fuel-water emulsion sprays released carbon fiber electrical effects A80-24817 880-19 194 Data reduction and analysis of graphite fiber Release of carbon fibers from burning composites release experiments 880-19195 [NASA-CR-159032] 880-19048 COMPOSITE STRUCTURES COMMAND AND CONTROL Advanced composites - Special topics; Proceedings Modeling and Simulation of Avionics Systems and of the Conference, El Segundo, Calif., December Command, Control and communications systems 4-6, 1979 conferences 880-26878 [AGARD-CP-268] 880-19809 Repair of advanced composite structure --- in Design and simulation of a C3 system for aircraft surveillance purpose A80-26888 N80-19821 Advanced composites serviceability program - Simulation for whole life development Status review --- inspection of aircraft 880-19839 structures COMMERCIAL AIRCRAFT 880-26890 Problems of older jet aeroplanes - A regulatory Composite components on commercial aircraft authority view 880-27597 880-25445 Induced effects of lightning on an all compcsite Constant speed 400 Hz aircraft electric generation aircraft system A80-27783 (SAP PAPER 791067) 880-26630 minimum-mass designs of stiffened Future multi-mission transport aircraft - graphite/polyimide compression panels Requirements and design possibilities 880-27992 [SAP PAPER 791097] A80-26646 Advanced composite aileron for L-1011 transport The aerodynamics of future transport aircraft and aircraft the role of the wind tunnel during development [NASA-cR-162863] 880-18103 A80-28494 Advanced manufacturing development of a composite Composite components on commercial aircraft empennage component for 1-1011 aircraft [NASA-TN-80231) N80-18109 [NASA-CR-162862] 880-18104 Computer programs for estimating civil aircraft Composite components on commercial aircraft economics [NASA-TN-80231] 880-18109 (NASA-TM-80196] 880-18988 Data reduction and analysis of graphite fiber Assessment of risk due to the use of carbon fiber release experiments composites in commercial and general aviation (NASA-cR-159032] 880-19048 N80-19201 Significance of large scatter of composite COMMUNICATION NETWORKS properties to aircraft reliability Design and simulation of a c3 system for [AD-A077804] 880-19062 surveillance purpose COMPRESSIBLE PLOW 880-19821 Numerical prediction of compressible potential COMMUNICATION SATELLITES flow for arbitrary geometries --- in airliner Error rate performance of M-ary DPSK systems in air-intake systems satellite/aircraft communications A80-27743 A80-25945 Three-dimensional inviscic3 compressible rotational Application of Nd:YAG optical communications flows Numerical results and comparison with technology for aircraft to satellite links analytical solutions 880-26797 880-27745 COMMUNICATION THEORY COMPRESSIVE STRENGTH Structures in aeronautical phraseology: From Graphite-epoxy panel compression strength English to Spanish reduction due to local impact 880-19978 A80-27598
1-13
COMPRESSOR BLADES SUBJECT INDEX
COMPRESSOR BLADES Permanent magnet and superconducting generators in Core compressor exit stage study. 1: Aerodynamic airborne, high power systems --- computer and mechanical design program to predict weight of the generators and (NASA-CR-159714) N80-19113 component systems Aerodynamic and acoustic investigations of axial (AD-A078424J N80-18311 flow fan and compressor blade rows, including Computer programs for estimating civil aircraft three-dimensional effects economics [AD-A077712) N80-19116 [NASA-TM-80196] N80-18988 COMPRESSOR EFFICIENCY Digital computer solution of aircraft longitudinal Aerodynamic performance of a centrifugal and lateral directional dynamic characteristics compressor with vaned diffusers AD-A078672] N80-19068 A80-27735 A computer program for estimating aircraft landing COMPRESSOR ROTORS distance Identification of noise sources in PC centrifugal [AD-A077169] N80-19088 fan rotors Advanced infrared signature prediction program. Spectral calculation of radiation from a turbine COMPUTATIONAL FLUID DYNAMICS propulsion system as intercepted by an observer One-dimensional aerodynamic control calculations (SCORPION) . Volume 3: Analysis for cooled gas turbines (AD-A078436] N80-191214 A80-26305 Using a language developed for aircraft simulators Analysis of the nonunigueness of solutions to the advantages and disadvantages of using problem of flow separation for small-aspect FORTRAN and assembly language delta wings A80-27127 COMPUTER SYSTEMS DESIGN Numerical modeling of supersonic flow near a thin CADD on the P-18 program --- Computer Aided Design delta wing with discontinuous edge and Drafting A80-27147 A80-26345 Numerical method for calculating supersonic flow Advanced computer program --- for future past a plane air intake with detached shock wave automation and system performance improvements A80-27148 A80-26B10 Computational aerodynamics on large computers Experience from testing the Viggen electronic A80-27415 systems utilizing existing computer capacity Evaluation of an analysis for axisymmetric A80-27235 internal flows in turbomachinery ducts From tape measure to computer tape --- development A80-27742 of flight recorders Numerical prediction of compressible potential A80-27243 flow for arbitrary geometries --- in airliner NSSC-2 operating system design requirements air-intake systems specification A80-27743 (NASA-CR-161396] N80-19861 Three-dimensional inviscid compressible rotational COMPUTER SYSTEMS PROGRAMS flows Numerical results and comparison with The use of computer systems in air traffic control analytical solutions A80-27223 A80-27745 Computer prediction of three-dimensional potential Evaluation of finite element formulations for flow fields in which aircraft propellers transient conduction forced-convection analysis operate: Computer program description and users of heat transfer for active cooling of manual hypersonic airframe and engine structures (NASA-CE-162816] N80-17994 A80-28284 MINIINIST: A shortened version of TWIST COMPUTER GRAPHICS CLEF-TB-146] 580-18438 CADD on the F-18 program --- Computer Aided Design Nondestructive evaluation of airport pavements. and Drafting Volume 2: Operational manual for PAVBEN program A80-26345 at TCC A study of the canopy design for the advanced [AD-A079495] N80-19130 attack helicopter by use of computer graphics Formal methods for achieving reliable software [AD-A078291] N80-19069 580-19549 COMPUTER PROGRAMMING An analysis of software reliability prediction Application of geometrical programming to problems models of optimal design N80-19551 A80-27137 Software development for TORNADO: A case history Numerical prediction of compressible potential from the reliability and maintainability aspect flow for arbitrary geometries --- in airliner N80-19554 air-intake systems E-3A navigational computer system real-time A80-27743 environmental simulator FORTRAN program oblique in PL-format user's manual N80-19824 (AD-A077809) N80-19880 Simulation for whole life development COMPUTER PROGRAMS N80-19839 Advanced computer program --- for future A simulation support system, the development tool automation and system performance improvements for avionic systems and subsystems A80-26810 580-19840 Interaction of a two-dimensional strip boundary FORTRAN program oblique in PL-format user's manual layer with a three-dimensional transonic [AD-A077809] N80-19880 swept-wing code COMPUTER TECHNIQUES {NASA-TM-78640) N80-17988 Computational aerodynamics on large computers General aviation airplane structural A80-27415 crashworthiness programmer's manual Computer synthesis of flight simulation visuals (AO-A075737] N80-18008 IARL/SYS-NOTE-61) N80-18053 Nondestructive evaluation of airport pavements. COMPUTERIZED DESIGN Volume 1: Program references CADD on the F-18 program --- Computer Aided Design [AO-A078835] N80-18051 and Drafting Programs for the transonic wind tunnel data A80-26345 processing installation. Part 7: Extended focal Minimum-mass designs of stiffened (AD-A073414] N80-18054 graphite/polyimide compression panels Comparison of measured data with IF-77 propagation A80-27992 model predictions A study of the canopy design for the advanced fAD-A076508] N80-18259 attack helicopter by use of computer graphics (AD-A078291) N80-19069
A-ill SUBJECT INDEX CONTROL STABILITY
Nondestructive evaluation of airport pavements. Proceedings of the 7th Ann. fri-Service Meeting Volume 2: Operational manual for PAVBEN program for Aircraft Engine Monitoring and Diagnostics at TCC conferences (80-8079495) N80-19130 [AD-A076126] 880-180115 COMPUTERIZED SIMULATION Workshop on Aircraft Surface Representation for Design of an electronic model of a microwave Aerodynamic Computation aircraft landing system (NASA-TM-81170] 880-19025 A80-26471 Proceedings of a Workshop on V/STOL Aircraft Simulation defines alternatives for Copenhagen Aerodynamics, volume 2 --- conferences terminal expansion [AD-8078909] 880-19042 A80-27221 Proceedings of a Workshop on V/STOL Aircraft Have Bounce --- validation of computer simulations Aerodynamics, volume 1 of F-4 dynamic response to multiple runway repairs [AD-A079115] 880-19079 A80-27382 Parameter Identification --- conference on Computational techniques for EMP interaction techniques applied to aircraft flight test data 880-27777 (AGARD-LS-104) 880-19094 New remotely piloted vehicle launch and recovery The 4th International Symposium on Air Breathing concepts: Computer program listings Engines (AD-A076611] 880-18035 [AD-A078956) 880-19114 Easy ACLS dynamic analysis, volume 2. Part 2: Avionics Reliability, Its Techniques and Related Component computer programs Disciplines --- conferences [AD-A079803] 880-19076 [AGARO-CP-261] 880-19519 A simulation program for the determination of Modeling and Simulation of Avionics Systems and system reliability of complex avionic systems Command, Control and Communications systems N80-19523 conferences Computer simulation model of the logistic support [AGARD-CP-268] 880-19809 system for electrical engineering test equipment Proceedings of the Association for Unmanned 880-19560 Vehicle Systems AUVS 2 79: 6th Annual Convention Modeling and Simulation of Avionics Systems and [AD-8077877] 880-20018 Command, Control and Communications systems CONFIGURATION MANAGEMENT conferences Flight evaluation of configuration management AGARD-CP-2681 880-19809 system concepts during transition to the landing Remarks on simulation. Objectives/areas of approach for a powered-lift STOL aircraft use/possibilities/limitations: An overview [NASA-TM-81146] 880-19127 N80-19812 CONGRESSIONAL REPORTS Neal-time simulation: An indispensable but NASA authorization, 1981, program review, volume 2 overused evaluation techique [GPO-56-220] 880-19988 880-19820 CONICAL BODIES Design and simulation of a C3 system for Hysteresis of aerodynamic characteristics --- for surveillance purpose wing models and segmented conical bodies of N80-19821 revolution The application of modeling and simulation to the A80-27167 development of the E-3A CONICAL SHELLS 880-19823 Turbulent-boundary-layer excitation and response Air-to-air engagement simulation thereto for a high-performance conical vehicle N80-19834 reentry The role of the aircraft model in avionic systems 880-18229 simulation CONTROL 880-19837 Power system control study. Phase 1: Integrated Avionics evaluation program: Simulation models control techniques for the effectiveness analysis of avionics (AD-8078629] 880-19125 880-19838 CONTROL CONFIGURED VEHICLES Simulation for whole life development Coming civil transport aircraft with 'active' N80-19 839 control elements A simulation support system, the development tool A80-28493 for avionic systems and subsystems A fault tolerant architecture approach to avionics N80-19840 reliability improvement CONDUCTIVE HEAT TRANSFER 880-19533 Evaluation of finite element formulations for CONTROL EQUIPMENT transient conduction forced-convection analysis Flight control design based on nonlinear model of heat transfer for active cooling of with uncertain parameters hypersonic airframe and engine structures 880-28018 A80-28284 Influence of air traffic on the concept of air CONFERENCES traffic control Navigation satellite users; Proceedings of the A80-28488 Rational Aerospace Symposium, Springfield, Va., Microprocessor controlled ejection seat March 6-8, 1979 [AD-A077479] 880-19049 A80-25141 CONTROL STABILITY Fatigue and microstructure; Proceedings of the Control system techniques for improved Materials Science Seminar, St. Louis, No., departure/spin resistance for fighter aircraft October 14, 15, 1978 [SAE PAPER 791083] 880-26639 A80-26730 Measurements of control stability characteristics Advanced composites - Special topics; Proceedings of a wind-tunnel model using a transfer function of the Conference, El Segundo, Calif., December method 4-6, 1979 (AIAA 80-0457] 880-26957 880-26878 Fundamentals of design. V - Fin design for combat Aerodynamic Testing Conference, 11th, Colorado aircraft Springs, Cob., March 18-20, 1980, Technical A80-27725 Papers Coming civil transport aircraft with 'active' A80-26929 control elements Flow in primary, non-rotating passages in A80-28493 turbomachines; Proceedings of the Winter Annual Practical input signal design --- For identifying Meeting, New York, N.Y., December 2-7, 1979 stability and control derivatives 880-27732 880-19097 Avoiding divergent stall in control configured Aspects of flight test instrumentation --- methods aircraft by using a canard arrangement to derive aircraft performance and stability and A80-28854 control characteristics 860-19098
8-15
CONTROL SURFACES SUBJECT INDEX
Analysis of aircraft performance stability and CRACK INITIATION control measures Avoiding divergent stall in control configured W80-19099 aircraft by using a canard arrangement CONTROL SURFACES 880-28854 Effect of temperature on surface noise CRACK PROPAGATION A80-28419 Crack development in panels of a pressurized Coming civil transport aircraft with lactivet fuselage under the combined effect of control elements pressurization-induced cyclic loads and A80-28 493 high-frequency vibrations Developing, mechanizing and testing of a digital A80-26195 active flutter suppression system for a modified The fatigue performance of service aircraft and 0-52 wind-tunnel model the relevance of laboratory data [NASA-CR-159155] 880-19566 880-27789 CONTROL THEORY CRACKING (FRACTURING) Minimum time turns with thrust reversal --- using USA? damage tolerant design handbook: Guidelines control theory for the analysis and design of damage tolerant (AD-A079851) 880-19078 aircraft structures, revision A Developing, mechanizing and testing of a digital [AD-1078216] 880-19065 active flutter suppression system for a modified CRASHES B-52 wind-tunnel model Helicopter crash position indicator flight trials [NASA-CR-159155) 880-19566 880-27240 CONTROLLABILITY General aviation airplane structural Flight evaluation of configuration management crashworthiness programmers manual system concepts during transition to the landing [AD-8075737] 880-18008 approach for a powered-lift STOL aircraft CROSS PLOW (NASA-TM-81146] 880-19127 Experimental investigation of the CONTROLLERS interference-free flow field around a lifting Solid state power controller verification studies wing-body model to establish cross flow [AD-A078238] N80-19429 characteristics for ventilated wind tunnel walls CONVECTIVE HEAT TRANSFER at low supersonic Mach numbers Evaluation of finite element formulations for [8188 80-0444] 880-26948 transient conduction forced-convection analysis Heat, mass and momentum transfer through sprays of heat transfer for active cooling of cross flow hypersonic airframe and engine structures N80-18327 A80-28284 Vorticity associated with multiple jets in a CONVENTIONS crossflow --- vertical takeoff aircraft The freight forwarder as an air carrier (NASA-CB-162855] 1180-19454 A80-28862 CRUCIFORM WINGS COOLING SYSTEMS Wind tunnel and flight test drag comparisons for a On the characteristics of guided projectile with cruciform tails centrifugal-reciprocating machines --- cryogenic [AIAA 80-0426] 880-26968 coolers CRUISE MISSILES [NASA-CR-162881] R80-19499 Control and data acquisition aircraft for ALCM CORROSION RESISTANCE flight tests --- Air Launched Cruise Missile Fiberglass rotor produced (AIAA 80-0446] 880-26950 A80-2L4740 Cruise-missile-carrier navigation requirements Rain erosion of lightning protection coatings for N80-19843 carbon fibre composites Proceedings of the Association for Unmanned A80-25059 Vehicle Systems AUVS 79: 6th Annual Convention The fatigue performance of service aircraft and [AD-A077877] 880-20018 the relevance of laboratory data CRYOGENIC WIND TUNNELS A80-27789 Automatic control of NASA Langleys 0.3-meter COST ANALYSIS cryogenic test facility Value analysis and the optimum cost concept [AIAA 80-0416] A80-26931 applied to aerospace A study of nonadiabatic boundary-layer A80-27202 stabilization time in a cryogenic tunnel for Cost-effectiveness of flight simulators for typical wing and fuselage models military training [AIAA 80-0417] 880-26932 S80-19830 A theoretical analysis of simulated transonic COST EFFECTIVENESS boundary layers in cryogenic-nitrogen wind tunnels Are we spending too much on flight test (NASA-TP-1631] 880-19131 instrumentation Toward new transonic windtunnels 880-27229 [AGABD-AG-240] 880-19137 Reliability growth testing of avionic equipment Development of the cryogenic tunnel concept and 880-27612 application to the US National Transonic Facility Impacts of technologies selected on the N80-19139 reliability and operational availability of The cryogenic wind tunnel: another option for the equipments. Cost considerations European Transonic Facility N80-19536 1180-19140 Cost-effectiveness of flight simulators for CRYOGENICS military training On the characteristics of N80-19830 centrifugal-reciprocating machines --- cryogenic Modeling the human operator: Applications to coolers system cost effectiveness (NASA-CR-162881 ] 1180-191199 N80-19846 CUMULATIVE DAMAGE COST ESTIMATES The use of the spectral summation of fatigue Value analysis and the optimum cost concept damages in order to examine the combined stress applied to aerospace state of structures A80-27202 880-27 152 Adding more automation to the air traffic control CURVE FITTING system Synthesis of rotor test data for real-time A80-28384 simulation COST REDUCTION (NASA-CR-152311) 1180-18029 Improved MPG for the BAe 146 feeder-jet CYCLIC LOADS A80-25449 Crack development in panels of a pressurized The practical aircraft hydraulic test stand fuselage under the combined effect of (.SAE PAPER 791079] 880-26636 pressurization-induced cyclic loads and high-frequency vibrations A80-26195
A-16
SUBJECT INDEX DIFFUSION FLARES
Acceleration of multicycle fatigue testing on DELTA WINGS aluminum structural alloys Experimental investigation of the 880-27479 interference-free flow field around a lifting wing-body model to establish cross flow characteristics for ventilated wind tunnel walls D at low supersonic Mach numbers DAMPING fRIAR 80-0444] 880-26948 Damping in tapered annular seals for an Analysis of the nonuniqueness of solutions to the incompressible fluid problem of flow separation for small-aspect [NASA-TP-1646] N80-19495 delta wings DAMPING TESTS 880-27127 Damping effects in joints and experimental tests Numerical modeling of supersonic flow near a thin on riveted specimens delta wing with discontinuous edge 880-19584 880-27147 DASSAULT AIRCRAFT Calculation of minimum-weight and maximum-rigidity The development of the worlds first triengine structures in the presence of design constraints business jet, the Rystere Falcon 50 880-2716S 880-27386 Similarity of the aerodynamic characteristics of DATA ACQUISITION delta wings at supersonic speeds Control and data acquisition aircraft for ALCM A80-27168 flight tests --- Air Launched Cruise Missile DR NE A B K [8188 80-0446) 880-26950 Simulation defines alternatives for Copenhagen Are we spending too much on flight test terminal expansion instrumentation 880-27221 880-27229 DENSITY MEASUREMENT A low cost airborne data acquisition system A mass flowmeter with compensation for thermal 880-27231 density variations of the fluid Wind tunnel and free flight model identification A80-25220 experience DEPLOYMENT N80-19103 Recovery system prelimiminary design. A DATA CORRELATION simplified approach to determining staging, Achieving effective Radar Cross Section flight timing and altitude requirements for fast profiles on the B-i aircraft inflating parachutes 880-27227 (AD-8077548] 880-19041 Investigation of engine performance degradation of DESCENT TRAJECTORIES TF33-P--7 engines Analysis of fuel-conservative curved decelerating 880-27233 approach trajectories for powered-lift and CTOL Wind-tunnel/flight correlation study of jet aircraft aerodynamic characteristics of a large flexible [NASA-lP-1650] 880-19022 supersonic cruise airplane (XB-70-1) - 3: A DESIGN ANALYSIS comparison between characteristics predicted New remotely piloted vehicle launch and recovery from wind-tunnel measurements and those measured concepts. Volume 1: Analysis, preliminary in flight design and performance/cost trade studies [NASA-TP-1516] 880-17986 [AD-A077475] 880-19066 DATA LINKS The F-16 Wild Weasel: A feasibility study Application of Nd:YAG optical communications (AD-8077050) 880-19071 technology for aircraft to satellite links Aerodynamic investigation of c-141 leading edge 880-26797 modification for cruise drag reduction, vclume 2 Influence of air traffic on the concept of air [AD-A077688] 880-19081 traffic control Software development for TORNADO: A case history 880-28488 from the reliability and maintainability aspect DATA PROCESSING N80-19554 Programs for the transonic wind tunnel data Fastener hole quality, volume 1 --- design processing installation. Part 7: Extended focal analysis of fatigue life and drilling techniques [AD-A073414] N80-18054 for fasteners in aircraft production DATA RECORDING (AD-A077859) 880-19567 A system for measuring and recording wind-tunnel DETECTORS balance data Preliminary assessment of an automated system for 880-25221 detecting present weather DATA REDUCTION (AD-8078031] 880-19706 First experience with telemetry and real time data DIESEL ENGINES reduction at Gates Learjet Evaluation of JP-5 turbine fuel in the single 880-27228 cylinder cue 1790 diesel engine Airborne video instrumentation/data reduction [AD-A078666] 880-18206 880-27232 DIESEL FUELS Aircraft motion analysis using limited flight and Evaluation of fuel character effects on .379 engine radar data combustion system 880-27241 [AD-A078440] 880-19119 Data reduction and analysis of graphite fiber DIFFERENTIAL EQUATIONS release experiments Singularities of the numerical solution of the [NASA-CR-159032] 880-19048 algebraic Niccati equation in matrix form by a DECISION RAKING modification of the Lax-Wendroff method --- for Aircraft emergency decisions: Cognitive and automatic aircraft control situational variables A80-27134 [AD-A077413] 880-19051 DIFFUSERS Impacts of technologies selected on the Effect of non-rotating passages on performance of reliability and operational availability of centrifugal pumps and subsonic compressors equipments. Cost considerations 880- 27 7 33 N80-19536 Straight-walled, two-dimensional diffusers - DEFECTS Transitory stall and peak pressure recovery Advanced composites serviceability program - 88 0-2 7 74 6 Status review --- inspection of aircraft Effect of wake-type nonuniform inlet velocity structures profiles on first appreciable stall in 880-26890 plane-wall diffusers 880-277117 DIFFUSION FLARES Local laminarization in turbulent diffusion flames A80-24819
A-li
DIFFUSION WELDING SUBJECT INDEX
DIFFUSION WELDING DRILLING NAVAIR pushes SPF/DB for structures --- in naval Fastener hole quality, volume 1 --- design aircraft design and construction analysis of fatigue life and drilling techniques A80-24739 for fasteners in aircraft production DIGITAL COMMAND SISTERS [AD-A077859] 880-19567 Variable cycle engine multivariable control DROPS (LIQUIDS) synthesis: Control structure definition Heat, mass and momentum transfer through sprays [AD-8078670] 4480-19117 cross flow DIGITAL COMPUTERS 4480-18327 Fire control for air-to-air gunnery in high DUCT GEOMETRY performance fighter aircraft Numerical prediction of compressible potential 880-19841 flow for arbitrary geometries --- in airliner DIGITAL NAVIGATION air-intake systems Navigation systems for approach and landing of 880-27743 VTOL aircraft DUCTED PAN ENGINES [NASA-C8-152335] N80-19055 Theory of by-pass ducted-fan engines --- Russian DIGITAL SIMULATION book Closed loop models for analyzing engineering A80-26349 requirements for simulators DUCTED PANS [NASA-CF-2965] 4480-19063 Investigation of fan blades shroud mechanical Verification and validation of avionic simulations damping 880-19814 (AD-8078439) 880-19120 New possibilities offered by a radio-inertial DUCTED PLOW hybrid guidance system digital simulation study Effect of non-rotating passages on performance of 880-19836 centrifugal pumps and subsonic compressors DIGITAL SYSTEMS A80-27733 V/STOLAND avionics system flight-test data on a Evaluation of an analysis for axisymmetric 118-111 helicopter internal flows in turbomachinery ducts [NASA-TM-78591] 880-180147 A80-27742 Trends in reliability modeling technology for DYNAMIC CHARACTERISTICS fault tolerant systems Dynamic Environmental Qualification Techniques 880-19534 [AGBRD-R-682] 880-19090 DIGITAL TECHNIQUES Application of MIL-STD-810C dynamic requirements Application of the concept of dynamic trim control to USAF avionics procurements to automatic landing of carrier aircraft 880-19091 utilizing digital feedforeward control Dynamic environments and test simulation for (NASA-TP-1512] 880-19126 qualification of aircraft equipment and external Developing, mechanizing and testing of a digital stores active flutter suppression system for a modified 4480-19092 B-52 wind-tunnel model Aircraft parameter identification methods and (NASA-CR-159155] 880-19566 their applications: Survey and future aspects DIRECTIONAL STABILITY 880-19095 Exploratory investigation of the effects of vortex Simulation for integration with dynamic tests of bursting on the high angle-of-attack the logical elements of principal onboard lateral-directional stability characteristics of computers highly-swept wings N80-19842 [AIAB 80-0463] 880-26960 DYNAMIC CONTROL Thrust vectoring to eliminate the vertical Application of the concept of dynamic trim control stabilizer --- to provide directional stability to automatic landing of carrier aircraft for f-ill aircraft while decreasing radar utilizing digital feedforeward control detectability (NASA-TP-1512] 880-19126 [80-8079852] 880-19077 DYNAMIC RESPONSE DISCHARGERS Have Bounce --- validation of computer simulations Experimental study of electrostatic dischargers of P-4 dynamic response to multiple runway repairs for helicopters A80-27382 [ONERA, TP NO. 1980-5] 880-28947 Damping in tapered annular seals for an DISPLAY DEVICES incompressible fluid Avionics - The leading technology in flight [NASA-TP-1646] 880-191495 guidance and air traffic control DYNAM[C STABILITY 880-28492 Research on the stability of air cushion systems Early flight test experience with Cockpit UIIAS-238] 880-17985 Displayed Traffic Information (CDTI) DYNAMIC STRUCTURAL ANALYSIS [NASA-TN-80221] 880-18037 The cautious course to introducing new SUN The effect of viewing time, time to encounter, and technology into production systems practice on perception of aircraft separation on Structures, Dynamics and Materials a cockpit display of traffic information A80-26343 [NASA-TM-81173] 880-18038 Computer synthesis of flight simulation visuals [ARL/SYS-NOTE-61 ] 880-18053 E Flight path displays E-3& AIRCRAFT [AD-A077181] 880-19107 E-38 navigational computer system real-time Simulation of a night vision system for low level environmental simulator helicopter operations --- using helmet mounted 880-19824 display device A JTIDS performance model for the E-38 880-19832 880-19825 DISTANCE ECONOMIC ANALYSIS A computer program for estimating aircraft landing Opportunistic maintenance policies for economic distance replacement of internal life-limited cornpcnents [80-8077169] 880-19088 in modular aircraft engines DRAFTING MACHINES [SAE PAPER 791101] 880-26647 CADD on the P-18 program --- Computer Aided Design Computer programs for estimating civil aircraft and Drafting economics 880-26345 NASA-T8-80196] 880-18988 DRAG REDUCTION ECONOMIC IMPACT Aerodynamic investigation of C-141 leading edge The energy problem: Its effect on aircraft design. modification for cruise drag reduction, volume 2 I - Supply and demand (80-8077688] 880-19081 88 0-27752
8-18
SUBJECT INDEX ENGINE DESIGN
EIGBNVALUES ELECTROMAGNETIC FIELDS Computational techniques for EMP interaction Experimental measurement of fields excited inside A80-27777 the fuselage of an aircraft EJECTION SEATS A80-27306 Microprocessor controlled ejection seat Swedish EMP research [AD-A077479] N80-19049 A80-27766 Prototype development passive, seat-mounted limb ELECTROMAGNETIC INTERACTIONS retention system Computational techniques for EMP interaction [A0-A076331] N80-19053 A80-27777 ELASTIC EARS ELECTROMAGNETIC INTERFERENCE A single-step method of optimizing statically Experimental procedure to determine limits of ISM indeterminate minimum-volume systems interference affecting navigational ILS equipment A80-27135 Industrial, Scientific and Medical ELASTIC SYSTEMS A80-27760 Method of determining steady-state aerodynamic Atmospheric electricity and military operations characteristics for an elastic aircraft in free [AD-A078482] t180-19693 longitudinal motion ELECTROMAGNETIC MEASUREMENT A80-27173 Experimental procedure to determine limits of ISM ELECTRIC CONTACTS interference affecting navigational ILS equipment Liquid metal slip ring --- aerospace environments Industrial, Scientific and Medical (NASA-CASE-LEW-12277-3] N80-18300 A80-27760 ELECTRIC DISCHARGES ELECTROMAGNETIC PULSES Experimental study of electrostatic dischargers Swedish EMP research for helicopters A80-27766 (ONERA, PP NO. 1980-5] A80-28947 Computational techniques for EMP interaction ELECTRIC EQUIPMENT AS 0-27 77 7 The potential for damage from the accidental Modelling of aircraft responses to IMP release of conductive carbon fibers from burning A80-27778 composites Induced effects of lightning on an all composite [NASA-TM-80213) N80-18108 aircraft Assessment of Carbon Fiber Electrical Effects 580-27783 [NASA-CP-2119] N80-19193 ELECTRONIC CONTROL Approach to the assessment of the hazard --- fire Electronic flight rules /EFR/ - A concept for released carbon fiber electrical effects enhanced freedom of airspace N80-19194 580-28382 Evaluation of equipment vulnerability and ELECTRONIC COUNTERMEASURES potential shock hazards --- carbon fibers The F-16 Wild Weasel: A feasibility study N80-19197 (AD-5077050] 1480-19071 Large-scale fiber release and equipment exposure ELECTRONIC EQUIPMENT experiments --- aircraft fires A new approach to maintainability prediction N80-19198 avionics, ground, and shipboard electronics Surveys of facilities for the potential effects P80-19537 from the fallout of airborne graphite fibers Reliability growth through environmental simulation N80-19 199 electronic equipment ELECTRIC GENERATORS P80-19538 Permanent magnet and superconducting generators in ELECTRONIC EQUIPMENT TESTS airborne, high power systems --- computer Experience from testing the Viggen electronic program to predict weight of the generators and systems utilizing existing computer capacity component systems 580-27235 [AD-A078424] N80-18311 Reliability growth testing of avionic equipment Power system control study. Phase 1: Integrated A80-27612 control techniques Experimental procedure to determine limits of ISM (AD-A078629] N80-19125 interference affecting navigational ILS equipment ELECTRIC POWER SUPPLIES Industrial, Scientific and Medical Constant speed 400 Hz aircraft electric generation 580-27 760 system Swedish EMP research (SAE PAPER 791067] A80-26630 A80-27766 ELECTRIC POWER TRANSMISSION EMERGENCIES Flat bus fault sensors Aircraft emergency decisions: Cognitive and (AD-A077060] N80-19435 situational variables ELECTRICAL EEGINEERING [AD-A077413] 1480-19051 Computer simulation model of the logistic support EMULSIONS system for electrical engineering test equipment Characteristics of burning Jet A fuel and Jet A N80- 19560 fuel-water emulsion sprays ELECTRICAL FAULTS A80-24817 Evaluation of equipment vulnerability and ENERGY REQUIREMENTS potential shock hazards --- carbon fibers The energy problem: Its effect on aircraft design. N80-19197 I - Supply and demand Surveys of facilities for the potential effects A80-27752 from the fallout of airborne graphite fibers ENGINE ANALYZERS NOD- 19199 An analysis and synthesis of engine condition ELECTRICAL RESISTANCE monitoring systems Specification for the installation of electrical [AD-A077531] 1480-19122 resistance strain gauges on strain pairs counter ENGINE DESIGN aircraft --- to monitor fatigue damage One-dimensional aerodynamic control calculations [AD-A071363] N80-18369 for cooled gas turbines ELECTRO-OPTICS 580-26305 Angular vibration measurement techniques Theory of by-pass ducted-fan engines --- Russian airborne electro-optical package disturbances book N80-18222 A80-26349 ELECTROMAGNETIC COMPATIBILITY Opportunistic maintenance policies for economic INC in lightweight helicopters - Special problems replacement of internal life-limited components and experience in design and control in modular'aircraft engines A80-27773 (SAE PAPER 791101] 580-26647 Modelling of aircraft responses to EMP Method and apparatus for rapid thrust increases in A80-27778 a turbofan engine System EEC - Tendencies of a worldwide [NASA-CASE-LEW-12971-1] 1480-18039 standardization and cooperation A80-27784
A-19
ENGINE FAILURE SUBJECT INDEX
The application of reliability improvement Reliability growth through environmental simulation warranty to dynamic systems electronic equipment [AD-1075520] 1180-18419 B80-19538 The 4th International symposium on Air Breathing EPDXY RESINS Engines Development and test of low-impact resistant towers [AD-A078956] 1180-19114 (AD-A077160) 1180-18052 Novel ceramic turbine rotor concepts EQUATIONS OF MOTION [AD-A078669] 1180-19118 On the equations of motion about the mass centre ENGINE FAILURE of the jet aircraft considered as variable mass Ferrographic and spectrographic analysis of oil system sampled before and after failure of a jet engine 880-26325 [NASA-TN-81430] 1180-19497 EQUIPMENT SPECIFICATIONS ENGINE INLETS Comparison of specifications for Read-Up Displays Transonic inlet flow calculations using a general in the Navy A-LIE, A-7E, AV-8A, and Y-141 aircraft grid-generation scheme [AD-A080047] N80-19106 180-27744 ERROR ANALYSIS ENGINE MONITORING INSTRUMENTS Error rate performance of M-ary DPSK systems in An analysis and synthesis of engine condition satellite/aircraft communications monitoring systems 180-25945 [10-1077531] 1180-19122 ERROR DETECTION CODES ENGINE NOISE An analysis of software reliability prediction Methods of sound simulation and applications in models flight simulators N80-19551 [NASA-TN-757681 1180-19133 ESTIMATING ENGINE PARTS A computer program for estimating aircraft landing Opportunistic maintenance policies for economic distance replacement of internal life-limited components [80-1077169] N80-19088 in modular aircraft engines EUROPEAN hEEDS [SAN PAPER 791101] 180-26647 Airbus family concept for the 1990s Wear of seal materials used in aircraft propulsion 180-281489 systems EXHAUST DIFFUSERS 180-28010 An experimental investigation of two large annular Gas path seal diffusers with swirling and distorted inflow [NASA-CASE-NPO-12131-3) 1180-18400 (NASA-TP-1628] 1180-17984 Contribution of photoelastic analysis to the study EXHAUST EMISSION of turbo-engine components Control of particulate emissions from turbine [BR71985] N80-19112 engine test cells by Cooling water injection ENGINE STARTERS [80-1075947] 1180-18587 Power system control study. Phase 1: Integrated EXHAUST NOZZLES control techniques Influence of the empennage on the effective thrust [10-1078629] 1180-19125 of jet engine exhaust nozzles ENGINE TESTING LABORATORIES 180-27139 Transparent engines at Rolls-Royce - The EXPANSION application of high energy X-ray technology to An analysis of residual stresses and displacements gas turbine development due to radial expansion of fastener holes 180-251447 [10-1076370] 1180-19569 ENGINE TESTS EXPERIMENTAL DESIGN Investigation of engine performance degradation of Hypersonic interference flow flight experiment TF33-P-7 engines design --- investigating aerodynamic heating and 180-27233 loads Evaluation of JP-5 turbine fuel in the single [10-1018861] 1180-19044 cylinder cue 1790 diesel engine EXTERNAL STORE SEPARATION [AD-1078666] N80-18206 Aircraft store separation motion prediction via Tests of an improved rotating stall control system grid data trajectories on a 3-85 turbojet engine [lIlA 80-0462] 180-26959 [AD-A077704) 1180-19109 EXTERNAL STORES Contribution of photoelastic analysis to the study Data report for a test program to study transonic of turbo-engine components flow fields about wing-body/pylon/store (BR71985] 1180-19112 combinations. Volume 1: Tunnel empty flow ENVIRONMENT EFFECTS survey data, wing body force/moment/surface Structural design of transport airplanes for pressure data, and pressure store transient environments force/moment/surface pressure data A80-27898 [10-1077182] 1180-18001 ENVIRONMENT SIMULATION Data report for a test program to study transonic Simulating the shock protection performance of flow fields about wing-body/pylon/store large transit packs by means of small scale combinations. Volume 2: Flow field survey data laboratory models --- applicable to aircraft for configurations 21 and 22 engine power plant design [10-1077183] 1180-18002 180-27790 Dynamic environments and test simulation for Reliability growth through environmental simulation qualification of aircraft equipment and external electronic equipment stores N80-19538 N80-19092 ENVIRONMENTAL CONTROL Improved MPG for the RAe 146 feeder-jet 180-25449 F ENVIRONMENTAL TESTS F-4 AIRCRAFT Failure mechanisms for advanced Composite sandwich Tactical navigation system testing construction in hostile environments --- naval 180-27233 aircraft structures Have Bounce --- validation of computer simulations A80-26884 of P-4 dynamic response to multiple runway repairs Dynamic environments and test simulation for 180-27382 qualification of aircraft equipment and external Wind tunnel test to investigate aerodynamic stores hysteresis phenomena of the F-LI and P-il W80-19092 aircraft models Civil aircraft equipment environment qualification [10-1077196] 1180-19040 techniques Avionics interface data summaries: 1-101, N80-19093 EP-111A, P-43, P-4G, F-15A, P-16A, P-111A, F-111E, F-111F, RF-4C [10-1077388] 1180-19105
1-20
SUBJECT INDEX FIGHTER AIRCRAFT
F-15 AIRCRAFT Specification for the installation of electrical Production Eagle and its potential resistance strain gauges on strain pairs counter (SAE PAPER 791071] A80-26634 aircraft --- to monitor fatigue damage Avionics interface data summaries: A-10A, [AD-8071363] 880-18369 Er-111A, F-43, F-4G, F-15A, F-16A, F-111A, FATIGUE LIFE F-111E, F-ill?, R?-4C Fiberglass rotor produced [AD-A077388] N80-19105 A80-24740 F-16 AIRCRAFT Applying pressure . . . Believing stress F-16 European test and evaluation stress coining aircraft structures A80-27380 880-27257 An investigation of F-16 nozzle-afterbody forces Acceleration of multicycle fatigue testing co at transonic Each numbers with emphasis on aluminum structural alloys support system interference A80-27479 [AD-A078693] 880-18046 The fatigue performance of service aircraft and The F-16 Wild Weasel: A feasibility study the relevance of laboratory data [AD-A077050] 880-19071 A80-27 789 Avionics interface data summaries: A-10A, Avoiding divergent stall in control configured EF-111A, F-43, F-4G, F-15A, P-16A, F-111A, aircraft by using a canard arrangement F-111E, F-ill?, RF-4C A80-28854 (AD-A077388] 880-19105 A review of Australian investigations on F-18 AIRCRAFT aeronautical fatigue during the period April CADD on the F-18 program --- Computer Aided Design 1977 to March 1979 --- structural strain and and Drafting fatigue life studies on aircraft structures and A80-26345 construction materials Testing the r-18 at the U.S. Naval Air Test Center [AD-A071641] 880-18449 A80-27239 Fastener hole quality, volume 1 --- design F/A-18 status report analysis of fatigue life and drilling techniques A80-27377 for fasteners in aircraft production F-104 AIRCRAFT (AD-A077859] 880-19567 Roman factors in high speed low level accidents: FATIGUE TESTS A 15 year review Evaluation of the effectiveness of case-hardening (AD-A076221] 880-18012 gas-turbine-engine components on the basis of F-ill AIRCRAFT fatigue-failure similarity equations Modelling of aircraft responses to EMP 880-26193 A80-27778 Acceleration of multicycle fatigue testing on Wind tunnel test to investigate aerodynamic aluminum structural alloys hysteresis phenomena of the F-4 and F-li 880-27479 aircraft models Cast aluminum primary aircraft structure (AD-A077196] N80-19040 A80-27875 Thrust vectoring to eliminate the vertical Application of composite materials to turbofan stabilizer --- to provide directional stability engine fan exit guide vanes for f-ill aircraft while decreasing radar (NASA-TM-81432] 880-18106 detectability HLH rotor box beam fatigue test [AD-A079852] N80-19077 [AD-A076931] N80-18450 Avionics interface data summaries: A-10A, FEEDBACK CONTROL EF-111A, F-43, F-4G, F-15A, F-16A, F-111A, Measurements of control stability characteristics T-lllE, P-111F, R?-4C of a wind-tunnel model using a transfer function [AD-A077388] 880-19105 method FACTORIAL DESIGN (AIAA 80-0457] 880-26957 Factorial design of experiments in the test and Closed loop models for analyzing engineering evaluation of a complex control system --- for requirements for simulators carrier-based aircraft landing [NASA-CR-2965] 880-19063 A80-27242 Closed loop aspects of aircraft identification FAILURE ANALYSIS 880-19 104 Evaluation of the effectiveness of case-hardening Tests of an improved rotating stall control system gas-turbine-engine components on the basis of on a 3-85 turbojet engine fatigue-failure similarity equations [AD-A077704] 880-19109 880-26193 Variable cycle engine multivariatle control Acceleration of multicycle fatigue testing on synthesis: Control structure definition aluminum structural alloys [AD-A078670] 880-19117 A80-27 479 FEEDFORWABD CONTROL Ferrographic and spectrographic analysis of oil Application of the concept of dynamic trim control sampled before and after failure of a jet engine to automatic landing of carrier aircraft [NASA-TM-81430] 880-19497 utilizing digital feedforeward control A simulation program for the determination of (NASA-TP-1512] 880-19126 system reliability of complex avionic systems FIBER COMPOSITES 880-19523 Application of composite materials to turbofan FAILURE NODES engine fan exit guide vanes Incandescent lamp life under random vibration [NASA-TM-81432] 880-18106 W80-18221 Carbon and graphite. Part 1: Carbon and graphite FANS fibers and fiber composites, volume 4. A Rotating stall in a vaneless diffuser of a bibliography with abstracts centrifugal fan [P880-802366] N80-18145 A80-27734 Assessment of risk due to the use of carbon fiber FASTENERS composites in commercial and general aviation Fastener hole quality, volume 1 --- design 880-19201 analysis of fatigue life and drilling techniques Perspective on the results for fasteners in aircraft production B80-19202 (AD-A077859] 880-19567 FIBER OPTICS An analysis of residual stresses and displacements Fiber optic sensors for measuring angular position due to radial expansion of fastener holes and rotational speed --- air breathing engines [AD-A076370] 880-19569 (NASA-TM-81454] 880-18368 FATIGUE (MATERIALS) FIGHTER AIRCRAFT The use of the spectral summation of fatigue ECAIR design philosophy for fighter aircraft damages in order to examine the combined stress departure and spin resistance state of structures [SAE PAPER 791081] 880-26637 A80-27152
A-2l
FINITE DIFFERENCE THEORY SUBJECT INDEX
Effects of forebody, wing and wing-body-LEX FLIGHT CHARACTERISTICS flowfields on high angle of attack aerodynamics High-angle-of-attack flying qualities - An Leading Edge eXtensions overview of current design considerations [SAE PAPER 791082] A80-26638 [SAE PAPER 791085] A80-26640 Control system techniques for improved easurements of control stability characteristics departure/spin resistance for fighter aircraft of a wind-tunnel model using a transfer function (SAE PAPER 791083] A80-26639 method An approach to the runway denial problem (AIAA 80-0457] A80-26957 (SAF PAPER 791107] A80-26649 Review of five years of flight testing the 8-1 Fighter options for tactical air defense, A80-27388 (SAE PAPER 791108] A80-26650 Implicit model following and parameter Experience from testing the Viggen electronic identification of unstable aircraft systems utilizing existing computer capacity A80-28019 A80-27235 Flight performance of the TCV B-737 airplane at Fundamentals of design. V - Fin design for combat Jorge Newberry Airport, Buenos Aires, Argentina aircraft using TRSE/NLS guidance A80-27725 (NASA-TM-80223) 880-18021 The light fighter market . - . and a European Proceedings of a Workshop on V/STOL Aircraft proposal Aerodynamics, volume 2 --- conferences A80-27727 [AD-A078909] 880-19042 Induced effects of lightning on an all composite Development of VTOL flying qualities criteria for aircraft low speed and hover A80-27783 [AD-A079911] 880-19085 Measuring technological change in jet fighter Parameter Identification --- conference on aircraft techniques applied to aircraft flight test data [AD-077393] N80-19084 [AGARO-LS-104] R80-19094 Identification experience in extreme flight regimes Aircraft parameter identification methods and N80-19102 their applications: Survey and future aspects Air-to-air engagement simulation N80-19095 880-19834 Identification evaluation methods Fire control for air-to-air gunnery in high N80-19096 performance fighter aircraft Analysis of aircraft performance stability and N80-19841 control measures FINITE DIFFERENCE THEORY 880-19099 Transonic inlet flow calculations using a general Wind tunnel and free flight model identification grid-generation scheme experience A80-27744 N80-19103 Computational techniques for EMP interaction Closed loop aspects of aircraft identification A80-27777 N80-19104 FINITE ELEMENT METHOD Handling quality requirements for advanced Evaluation of finite element formulations for aircraft design longitudinal mode transient conduction forced-convection analysis [AD-A077858] 880-19128 of heat transfer for active cooling of FLIGHT CONDITIONS hypersonic airframe and engine structures Strouhal number influence on flight effects on jet A80-28284 noise radiated from convecting quadrupoles FINS 880-28418 Fundamentals of design. V - Fin design for combat Aircraft icing during low-level flights aircraft AD-A078843] 880-19052 A80-27725 PLIGHT CONTROL Advanced manufacturing development of a composite High-angle-of-attack flying qualities - An empennage component for 1-1011 aircraft overview of current design considerations [NASA-CR-162862] 880-18104 [SAE PAPER 791085) 880-26640 FIRE CONTROL Flight control design based on nonlinear model Fire control for air-to-air gunnery in high with uncertain parameters performance fighter aircraft 880-28018 N80-19841 V/STOLAND avionics system flight-test data on a FIRES UN-1H helicopter The potential for damage from the accidental [NASA-TM-78591] 880-16047 release of conductive carbon fibers from burning Closed loop models for analyzing engineering composites requirements for simulators (NASA-TM-80213] N80-18108 (NASA-CE-2965] 1180-19063 Propulsion and energetics panel Working Group 11 Handling quality requirements for advanced on aircraft fire safety. Volume 2: Main report aircraft design longitudinal node (AGARD-AR-132-VOL-2] N80-19047 (80-8077858] N80-19128 Assessment of Carbon Fiber Electrical Effects Microprocessor control of low speed V/STOL flight (NASA-CP-2119] N80-19193 [AD-1077661] R80-19129 Approach to the assessment of the hazard --- fire Nonelectronic aspects of avionic system reliability released carbon fiber electrical effects actuation 880-19 194 N80-1 9535 Release of carbon fibers from burning composites Air Force Flight Dynamics Laboratory fiscal year N80-19195 1981. technical objective document Dissemination, resuspension, and filtration of [80-8078973] 880-20020 carbon fibers --- aircraft fires PLIGHT HAZARDS N80-19196 Lightning protection for aircraft Large-scale fiber release and equipment exposure 880-27021 experiments --- aircraft fires Aircraft icing during low-level flights N80-19 198 [AD-A078843] 880-19052 PLANE PROPAGATION PLIGHT INSTRUMENTS Characteristics of burning Jet A fuel and Jet A Aspects of flight test instrumentation --- methods fuel-water emulsion sprays to derive aircraft performance and stability and A80-24817 control characteristics PLANE STABILITY 1180-19098 Local laminarization in turbulent diffusion flames FLIGHT MECHANICS A80-24819 Pressure distribution in rectangular wing /tlade/ PLAY PLATES sections during curvilinear motion in an An experimental study of two-dimensional incompressible medium supersonic jet impingement on a flat plate 880-27157 [A0-A076536] N80-17996
8-22
SUBJECT INDEX FLIGHT TESTS
Concepts for generating optimum vertical flight From tape measure to computer tape --- development profiles of flight recorders [NASA-CR-159181] 880-18031 *8 0-2 7 243 FLIGHT PATHS FLIGHT TESTS Flight path displays Development and flight test of a two-place [AD-A077181) N80-19107 night/adverse weather 1-10 for the close-air FLIGHT RECORDERS support and battlefield attack mission Are we spending too much on flight test [SAE PAPER 791069] *80-26632 instrumentation Local skin friction and static pressure on a swept *80-27229 wing in flight BIDS - The right tool for small test jobs (AIAA 80-0423) *80-26937 Miniature Integrated Data Systems for inflight New requirements, test techniques, and development testing methods for high fidelity flight simulaticn of A80-27230 commercial transports Airborne video instrumentation/data reduction (AIAA 80-0445] *80-26949 A80-27232 Control and data acquisition aircraft for ALCM Aircraft notion analysis using limited flight and flight tests --- Air Launched Cruise Missile radar data (AIAA 80-0446] *80-26950 *80-27241 Wind tunnel and flight test drag comparisons for a From tape measure to computer tape --- development guided projectile with cruciform tails of flight recorders [AIAA 80-0426] *80-26968 A80-27243 Achieving effective Radar Cross Section flight Flight recording in the UK. I - Evolution profiles on the B-i aircraft *80-27 751 A80-27227 FLIGHT RULES First experience with telemetry and real time data Electronic flight rules /EFR/ - A concept for reduction at Gates Learjet enhanced freedom of airspace *8 0-27 228 A80-28382 Tactical navigation system testing FLIGHT SIMULATION A80-27237 Tactical navigation system testing Testing the P-la at the U.S. Naval Air Test Center A80-27237 A80-27239 Application of the Estimation-Before-Modeling Helicopter crash position indicator flight trials (EBB) system identification method to the high A80-27240 angle of attack/sideslip flight of the T-2C jet Aircraft motion analysis using limited flight and trainer aircraft. Volume 2: Simulation study radar data using T-2C wind tunnel model data *80-27241 (AD-A079923] 880-19061 F/A-la status report Evaluation of aircraft windshield materials in a A80-27377 simulated supersonic flight environment Night/adverse weather A-10 evaluator program (AD-A078673) 880-19082 /A-10H/. N. H. Shawler Remarks on simulation. Objectives/areas of A80-27378 Use/possibilities/limitations: An overview F-16 European test and evaluation N80-19812 *80-27380 Simulation of a night vision system for low level General aviation icing flight test helicopter operations --- using helmet mounted *80-27383 display device The development of the world's first triengine N80'-19832 business jet, the Mystere Falcon 50 FLIGHT SIMULATORS A80-27386 New requirements, test techniques, and development CL-600 Challenger methods for high fidelity flight simulation of *80-27387 commercial transports Review of five years of flight testing the 8-1 [AIAA 80-0445] *80-26949 A80-27388 Computer synthesis of flight simulation visuals Composite components on commercial aircraft [ARL/STS-NOTE-61] N80-18053 *80-27597 Methods of sound simulation and applications in Wind-tunnel/flight correlation study of flight simulators aerodynamic characteristics of a large flexible [NASA-TM-75768) 880-19133 supersonic cruise airplane (XB-70-1). 3: A Design of a simulator for studying the helicopter comparison between characteristics predicted - SDVEH from wind-tunnel measurements and those measured N80-19829 in flight Cost-effectiveness of flight simulators for [NASA-TP-1516] 1480-17986 military training Comparison of aerodynamic coefficients obtained N80-19830 from theoretical calculations wind tunnel tests Using a language developed for aircraft simulators and flight tests data reduction for the alpha advantages and disadvantages of using jet aircraft FORTRAN and assembly language [NASA-TM-75237J 880-17991 N80-19831 Synthesis of rotor test data for real-time FLIGHT TEST INSTRUMENTS simulation Are we spending too much on flight test (NASA-CR-152311] 1180-18029 instrumentation Airborne radar approach system flight test A80-27229 experiment BIDS - The right tool for small test jobs [AD-A077900) 880-190514 Miniature Integrated Data Systems for inflight Preliminary Airworthiness Evaluation UH-1H testing helicopter equipped with Multiple Target A80-27230 Electronic Warfare System (NULTEWS) A low cost airborne data acquisition system AD-A078476] 880-19067 *80-27231 Application of the Estimation-Before-Modeling Airborne video instrumentation/data reduction (EBB) system identification method to the high *80-27232 angle of attack/sideslip flight of the T-2C jet VSTOL test techniques utilizing laser tracking trainer aircraft. Volume 3: Identification of *80-27234 T-2C aerodynamics stability and control Experience from testing the Viggen electronic characteristics from actual flight test data systems utilizing existing computer capacity [AD-A079924] 880-19072 A80-27235 Parameter Identification --- conference on Firebrand anti-ship missile target - Flight test techniques applied to aircraft flight test data program objectives and vehicle instrumentation [AGARD-LS-104] 880-19094 requirements A80-27236
A-23
FLIGHT TRAINING SUBJECT INDEX
As pects of flight test instrumentation --- methods FLOW VELOCITY to derive aircraft performance and stability and Additional flow quality measurements in the control characteristics Langley Research center 8-Foot Transonic N80-19098 Pressure Tunnel Analysis of aircraft performance stability and [AIAA 80-0434] A80-26944 control measures Laser anemometer measurements at the exit of a 163 N80-19099 combustor FLIGHT TRAINING A80-27737 New requirements, test techniques, and development Effect of wake-type nonuniform inlet velocity methods for high fidelity flight simulation of profiles on first appreciable stall in commercial transports plane-wall diffusers [AIAA 80-014145] A80-26949 A80-27747 FLIR DETECTORS Computer prediction of three-dimensional potential GE-ST supersonic FLIR window flow fields in which aircraft propellers [AD-A078371] 1480-19948 operate: computer program description and users FLOW CHARACTERISTICS manual Experimental investigation of the (NASA-CB-162816) 1180-17994 interference-free flow field around a lifting An analytical and experimental study of aircraft wing-body model to establish cross flow hydraulic lines including the effect of mean flow characteristics for ventilated wind tunnel walls EAD-A079746] 1180-19079 at low supersonic Hach numbers FLOW VISUALIZATION [AIRA 80-0444] A80-26948 On the historical development of apparatus and Rotating stall in a vaneless diffuser of a techniques for smoke visualization of subsonic centrifugal fan and supersonic flows A80-27734 [AIAA 80-0 1420] A80-26934 FLOW DISTORTION Visualization of the laminar-turbulent transition Analysis of the nonunigueness of solutions to the in the flow over an airfoil using the smoke-wire problem of flow separation for small-aspect technique delta wings (AIAA 80-0421] A80-26935 A80-27127 Development of test methods for scale model An experimental investigation of two large annular simulation of aerial applications in the NASA diffusers with swirling and distorted inflow Langley Vortex Facility (NASA-TP-1628] 1180-17984 [AIAA 80-0427] A80-26939 FLOW DISTRIBUTION Full scale visualization of the wing tip vortices Effects of forebody, wing andwing-body-LEX generated by a typical agricultural aircraft flowfields on high angle of attack aerodynamics (NASA-CE-162796] 1180-17992 Leading Edge eXtensions FLOWNETEBS [SAE PAPER 791082] A80-26638 A mass flowmeter with compensation for thermal Selected wind tunnel testing developments at the density variations of the fluid Boeing Aerodynamics Laboratory A80-25220 [AIAA 80-0458] A80-26958 FLUID FLOW Transonic inlet flow calculations using a general Rotary balance data for a typical single-engine grid-generation scheme general aviation design for an angle-of-attack A80-27744 range of 8 deg to 90 deg. 1: Low-wing model A Computer prediction of three-dimensional potential fluid flow and vortices data for general flow fields in which aircraft propellers aviation aircraft to determine aerodynamic operate: computer program description and users characteristics for various designs manual [NASA-CE-3100] 1180-19030 (RASA-CR-162816) 1100-17994 FLUTTER An experimental study of two-dimensional CL-600 Challenger supersonic let impingement on a flat plate A80-27387 [AD-A076536] 1480-17996 Analysis of trunk flutter in an air cushion Data report for a test program to study transonic landing system flow fields about wing-body/pylon/store [AD-A079008] 1180-19075 combinations. Volume 1: Tunnel empty flow Developing, mechanizing and testing of a digital survey data, wing body force/moment/surface active flutter suppression system for a modified pressure data, and pressure store 8-52 wind-tunnel model force/moment/surface pressure data [NASA-CR-159155J N80-19566 [AD-A077182] 1180-18001 Some recent measurements of structural dynamic Viscous flowfields induced by two- and damping in aircraft structures three-dimensional lift lets in ground effect N80-19576 [AD-A078782] 1480-18343 FLUTTER ANALYSIS Laser-Raman flow-field diagnostics of two large Flutter analysis of a NACA 64A006 airfoil in small hypersonic test facilities disturbance transonic flow [AD-A078289] 1480-19135 A80-28851 An investigation of the quality of the flow Analysis of trunk flutter in an air cushion generated by three types of wind tunnel (Ludwieg landing system tube, Evans clean tunnel and injector driven [AD-A079008] 1180-19075 tunnel) Some recent measurements of structural dynamic 1480-19138 damping in aircraft structures FLOW EQUATIONS N80-19576 Viscous flow in the region of a rounded trailing FLYING PLATFORMS edge A low cost airborne data acquisition system [AD-A078588] 1180-19045 A80-27231 FLOW MEASUREMENT FOG Additional flow quality measurements in the Fog dispersion --- charged particle technique Langley Research Center 8-Foot Transonic [NASA-CE-32551 1480-19703 Pressure Tunnel FOG DISPERSAL [AIAA 80-01434] A80-26944 Fog dispersion --- charged particle technique Laser anemometer measurements at the exit of a 163 (NASA-CE-3255] 1180-19703 combustor FORCE DISTRIBUTION A80-27737 Distribution of forces and stresses along rows of Flow measurements in a turbine scroll bolted connections A80-27738 A80-27143 An investigation of the quality of the flow generated by three types of wind tunnel (Ludwieg tube, Evans clean tunnel and injector driven tunnel) N80-19138
A-24 SUBJECT INDEX GENERAL AVIATION AIRCRAFT
FORCED CONVECTION FUSELAGES Evaluation of finite element formulations for Crack development in panels of a pressurized transient conduction forced-convection analysis fuselage under the combined effect of of heat transfer for active cooling of pressurization-induced cyclic loads and hypersonic airframe and engine structures high-frequency vibrations A80-28284 A80-26195 FORCED VIBRATION A study of nonadiabatic boundary-layer Description of a new high-alpha, high-load, stabilization time in a cryogenic tunnel for pitch-yaw dynamic stability test mechanism at AFDC typical wing and fuselage models [AIAA 80-0451] A80-26952 (EIAA 80-0417] a80-26932 FOREBODI ES The influence of wing, fuselage and tail design on Effects of forebody, wing and wing-body-LEE rotational flow aerodynamics data obtained flowfields on high angle of attack aerodynamics beyond maximum lift with general aviation Leading Edge extensions configurations (SAE PAPER 791082] A80-26638 (AIEA 80-0455] A80-26955 FORTRAN Experimental measurement of fields excited inside Using a language developed for aircraft simulators the fuselage of an aircraft advantages and disadvantages of using A80-27306 FORTRAN and assembly language N80-19831 r FRACTURE MECHANICS Fatigue and microstructure; Proceedings of the GALLIUM Materials Science Seminar, St. Louis, Ho., Liquid metal slip ring --- aerospace environments October 14, 15, 1978 [NASA-CASE-LEW-12277-3) R80-18300 A80-26730 GAS TURBINE ENGINES USAF damage tolerant design handbook: Guidelines Transparent engines at Rolls-Royce - The for the analysis and design of damage tolerant application of high energy X-ray technology to aircraft structures, revision A gas turbine development [AD-A078216] N80-19065 A80-25447 FRACTURE STRENGTH Source book on materials for elevated-temperature Avoiding divergent stall in control configured applications: A comprehensive collection of aircraft by using a canard arrangement outstanding articles from the periodical and A80-28854 reference literature FREE FLOW A80-27622 Evaluation of a new concept for reducing Effect of wake-type nonuniform inlet velocity free-stream turbulence in wind tunnels profiles on first appreciable stall in [AIAA 80-0432] A80-26942 plane-wall diffusers Experimental investigation of the A80-27747 interference-free flow field around a lifting Wear of seal materials used in aircraft propulsion wing-body model to establish cross flow systems characteristics for ventilated wind tunnel walls A80-28010 at low supersonic Mach numbers Study of research and development requirements of [AIAA 80-0444] A80-26948 small gas-turbine combustors Influence of the empennage on the effective thrust [ NASA-CR-159796] N80-18040 of jet engine exhaust nozzles Proceedings of the 7th Ann. Tr-Service Meeting A80-27139 for Aircraft Engine Monitoring and Diagnostics Dynamic stall on oscillating airfoils in conferences oscillating free-streams [AD-A076126] N80-18045 N80-17983 GAS TURBINES FREQUENCY SCANNING One-dimensional aerodynamic control calculations Frequency-scanning particle size spectrometer for cooled gas turbines [NASA-CASE-NPO-13606-2] N80-18364 A80-26305 FUEL COMBUSTION Novel ceramic turbine rotor concepts Local laminarization in turbulent diffusion flames [AD-A078669] N80-19118 A80-24819 GASKETS FUEL CONSUMPTION Seals and gaskets. A bibliography with abstracts Improved MPG for the BEe 146 feeder-jet [P880-802010] N80-18417 A80-25449 GENERAL AVIATION AIRCRAFT The energy problem: Its effect on aircraft design. The influence of wing, fuselage and tail design on I - Supply and demand rotational flow aerodynamics data obtained A80-27752 beyond maximum lift with general aviation Analysis of fuel-conservative curved decelerating configurations approach trajectories for powered-lift and CTOL [ElBA 80-0455] A80-26955 jet aircraft General aviation icing flight test (NASA-TP-1650) N80-19022 A80-27383 FUEL CONTROL The development of the world's first triengine Demonstration program for a flexible duct valve business jet, the Mystere Falcon 50 for ramjet engine fuel controls A80-27386 [AD-A078529] N80-19123 CL-600 Challenger FUEL FLOW A80-27387 A mass flowmeter with compensation for thermal A consideration of general aviation in the United density variations of the fluid Kingdom A80-25220 [TT-7902] N80-17982 FUEL SPRAYS General aviation airplane structural Characteristics of burning Jet A fuel and Jet A crashworthiness programmer's manual fuel-water emulsion sprays (AD-A075737] N80-18008 A80-24817 Study of research and development requirements cf FUEL TESTS small gas-turbine combustors Evaluation of JP-5 turbine fuel in the single [NASA-CR-159796] N80-18040 cylinder cue 1790 diesel engine Aeroacoustic wind-tunnel tests of a light [AD-A078666] N80-18206 twin-boom general-aviation airplane with free or FUEL VALVES shrouded-pusher propellers --- in the Langley Demonstration program for a flexible duct valve full-scale tunnel for ramjet engine fuel controls [ NASA-TM-80203] N80-19023 [AD-A078529] N80-19123
A-25
GERMANIUM ALLOTS SUBJECT INDEX
Rotary balance data for a typical single-engine GREAT BRITAIN general aviation design for an angle-of-attack Problems of older jet aeroplanes - A regulatory range of 8 deg to 90 deg. 1: Low-wing model A authority view fluid flow and vortices data for general A80-25445 aviation aircraft to determine aerodynamic Flight recording in the UK. I - Evolution characteristics for various designs A80-2775 1 (4ASA-CR-3100] 880-19030 GROUND EFFECT Estimation of the endurance of civil aircraft wing Operational implications of some NACA/NASA rotary structures --- life estimate method for wing wing induced velocity studies loading on general aviation aircraft A80-27599 (ESDU-79024] 880-19060 GROUND EFFECT (AERODYNAMICS) Assessment of risk due to the use of carbon fiber Effect of sweep and aspect ratio on the composites in commercial and general aviation longitudinal aerodynamics of a spanloader wing 880-19201 in- and out-of-ground effect --- conducted in GERMANIUM ALLOYS Langley V/STOL wind tunnel OR-SI supersonic FITS window [NASA-TM-80199] 880-17993 (AD-A078371] 880-19948 Viscous flowfields induced by two- and GLASS FIBER REINFORCED PLASTICS three-dimensional lift jets in ground effect Fiberglass rotor produced AD-A078782] 880-18343 A80-24740 GROUND EFFECT MACHINES Development and test of low-impact resistant towers Research on the stability of air cushion systems [AD-A077160] 880-18052 [UTIAS-238] 880-17985 Application of composite materials to turbofan GROUND STATIONS engine fan exit guide vanes Standard engineering installation package. Air (NASA-TM-81432] 880-18106 Traffic Radio Channel Control (ATRCC) equipment GLIDE PATHS (AD-A077648] 880-19059 Multipath analysis of ILS glide path GROUND TESTS 880-19354 The practical aircraft hydraulic test stand GLOBAL AIR SAMPLING PROGRAM [SAE PAPER 791079] A80-26636 Measurements of cabin and ambient ozone on 0747 Have Bounce --- validation of computer simulations airplanes of F-4 dynamic response to multiple runway repairs A80-28853 A80-27382 GLOBAL POSITIONING SYSTEM GROUND-AIR-GROUND COMMUNICATIONS Navigation satellite users; Proceedings of the Present-day problems of air traffic control in National Aerospace Symposium, Springfield, Va., ground-to-air Communications March 6-8, 1979 A80-26221 A80-25141 Comparison of measured data with IF-77 propagation Navstar field test results model predictions A80-25143 (AD-A076508) 880-18259 Shipboard antenna tests for GPS HF communication to small low flying aircraft A80-25 144 880-19374 The Navstar Global Positioning System and time GUIDE VANES A80-25 146 Flow measurements in a turbine scroll A collision avoidance system using Navstar/GPS and A80-27738 ATC RB S Application of composite materials to turbofan A80-25157 engine fan exit guide vanes Outlook for Global Positioning System /GPS/ in NASA-TM-81432] 880-18106 civil aircraft operations GTE OCO N PA SSE S A80-25158 An induction gyrocompass On-board precision approach system using NAVSTAR GPS A80-2521 4 A80-25162 GYROSCOPES The impact of CPS on CV mission effectiveness Experience based upon experimental dry tuned gyros A80-25165 A80-28212 Continued study of NAVSTAR/GPS for general aviation The experimental strapdown system of DFVLR --- for [NASA-CR-159145] N80-18020 inertial guidance and navigation of civil aircraft GOVERNMENT/INDUSTRY RELATIONS A80-28218 Problems of older jet aeroplanes - A regulatory authority view A80-25445 H Military adaption of a commercial VOR/ILS airborne HARDENING (MATERIALS) radio with a reliability improvement warranty Evaluation of the effectiveness of case-hardening 880-19540 gas-turbine-engine components on the basis of GRAPHITE fatigue-failure similarity equations Minimum-mass designs of stiffened A80-26 193 graphite/polyimide compression panels HARMONIC OSCILLATION A80-27992 Unsteady pressure measurements on wing-store Carbon and graphite. Part 2. Carbon and graphite combinations in incompressible flow composites - excluding carbon fiber composites. A80-26269 A bibliography with abstracts HARRIER AIRCRAFT [PB80-802374] N80-18144 Breaking V/STOL free of Catch 22 --- technology Carbon and graphite. Part 1: Carbon and graphite utilization and assessment fibers and fiber composites, volume 4. A A80-26342 bibliography with abstracts AV-BB - A second generation V/STOL (PB80-802366] 880-18145 [SAE PAPER 791070] A80-26633 GRAPHITE-EPDXY COMPOSITE MATERIALS VSTOL test techniques utilizing laser tracking AV-8B - A second generation V/STOL A80-27234 [SAE PAPER 791070] A80-26633 rA y -8B status report Nondestructive evaluation of graphite composite A80-27381 aircraft structures Microprocessor control of low speed V/STOL flight A80-26891 (AD-A077661] B80-19129 Composite components on commercial aircraft HAZARDS A80-27597 Evaluation of equipment vulnerability and Graphite-epoxy panel compression strength potential shock hazards --- carbon fibers reduction due to local impact N80-19197 A80-27598 BEAD-UP DISPLAYS Application of composite materials to turbofan Comparison of specifications for Head-Up Displays engine fan exit guide vanes in the Navy A-4M, A-7E, AV-8A, and F-14A aircraft [NASA-TM-81432] 880-18106 (AD-A080047) N80-19106
A-26 SUBJECT INDEX HUMAN PERFORMANCE
The A-i head-up display reliability programme HIGH FREQUENCIES 880-19539 The role of II? in air-ground communications: An Reliability of high-brightness CRTs for airborne overview displays N80-19373 880-195113 BF communication to small low flying aircraft HEAT FLUX 880-19374 Influence of the angle of attack on the thermal Modern HR communications for low flying aircraft flux at the stagnation point at supersonic speeds 880-19375 880-27138 Assessment of HR communications reliability HEAT RESISTANT ALLOYS 880-1937 7 Source book on materials for elevated-temperature HIGH STRENGTH STEELS applications: A comprehensive collection of Source book on materials for elevated-temperature outstanding articles from the periodical and applications: A comprehensive collection of reference literature outstanding articles from the periodical and 880-21622 reference literature HEAT TRANSFER 880-27622 Heat, mass and momentum transfer through sprays HIGH TEMPERATURE ENVIRONMENTS cross flow Source book on materials for elevated-temperature 880-18327 applications: A comprehensive collection of HEAVY LIFT HELICOPTERS outstanding articles from the periodical and MLII and beyond --- Heavy Lift Helicopter reference literature (SAE PAPER 791086] 880-26641 A80-27622 Single rotor options for heavy lift and potential HIGH TEMPERATURE TESTS of multi lift Design and test of a boron - aluminum high [SAE PAPER 791087] A80-26642 temperature wing Multi rotor options for heavy lift [AD-A075814] 1180-18034 [SAE PAPER 791089] 880-26643 HISTORIES MLII rotor box beam fatigue test On the historical development of apparatus and [AD-A076931] 880-18450 techniques for smoke visualization of subsonic HELICOPTER CONTROL and supersonic flows ENC in lightweight helicopters - Special problems (AIAA 80-0420) A80-26934 and experience in design and control HOLES A80-27773 An analysis of residual stresses and displacements HELICOPTER DESIGN due to radial expansion of fastener holes HLH and beyond --- Heavy Lift Helicopter AD-A076370] 880-19569 [SAE PAPER 791086] 880-26641 HOLOGRAPHY Single rotor options for heavy lift and potential Nondestructive evaluation of graphite composite of multi lift aircraft structures [SAE PAPER 791087] 880-26642 880-26891 Multi rotor options for heavy lift HONEYCOMB STRUCTURES [SAE PAPER 791089] A80-26643 Evaluation of a new concept for reducing EMC in lightweight helicopters - Special problems free-stream turbulence in wind tunnels and experience in design and control [AIAA 80-0432] 880-26942 880-27773 A comparison of experimental and theoretical Experimental study of electrostatic dischargers turbulence reduction from screens, honeycomb and for helicopters honeycomb-screen combinations [ONERA, TP NO. 1980-5) A80-28947 [AIAA 80-0433] A80-26943 A hingeless rotor XV-15 design integration HORIZONTAL TAIL SURFACES feasibility study. Volume 1: Engineering The influence of wing, fuselage and tail design on design studies rotational flow aerodynamics data obtained [NASA-CE-152310] 880-18030 beyond maximum lift with general aviation HELICOPTER PERFORMANCE configurations Single rotor options for heavy lift and potential [AIAA 80-0455) 880-26955 of multi lift Fundamentals of design. VI - Tailplanes, tailless [SAE PAPER 791087] 880-26642 and canard design Preliminary Airworthiness Evaluation UH-1B 880-27728 helicopter equipped with Multiple Target HOT PRESSING Electronic Warfare System (MULTEWS) Pratt and Whitney innovations --- turbomachine [AD-A078476] 880-19067 blade casting and hot isostatic pressing of HELICOPTER TAIL ROTORS turbine disks HIll and beyond --- Heavy Lift Helicopter A80-25448 [SAE PAPER 791086) 880-26641 HOT-FILM ANEMOMETERS Application of unsteady airfoil theory to rotary Flow measurements in a turbine scroll wings A80-27738 880-28856 HOVERING HELICOPTERS Development of VTOL flying qualities criteria for A scientific approach to defeating helicopter low speed and hover vibration [AD-A079911] 880-19085 880-25446 HOVERING STABILITY Helicopter crash position indicator flight trials Operational implications of some NACA/NASA rotary A80-27240 wing induced velocity studies A study of the canopy design for the advanced A80-27599 attack helicopter by use of computer graphics HUMAN FACTORS ENGINEERING [AD-A078291) 880-19069 High-angle-of-attack flying qualities - An NADC ABC rotor maps overview of current design considerations [AD-A078802] 880-19083 [SAE PAPER 791085] 880-26640 Simulation of a night vision system for low level NASA aviation safety reporting system helicopter operations --- using helmet mounted [NASA-TM-78608] 880-18010 display device Feasibility testing of a Body Inflatable Bladder 880-19832 (BIB) restraint device HELMETS [AD-A078681] 1180-18013 Simulation of a night vision system for low level Early flight test experience with Cockpit helicopter operations.--- using helmet mounted Displayed Traffic Information (COTI) display device NASA-TM-80221] 880-18037 880-19832 HUMAN PERFORANCE HIGH ALTITUDE TESTS The effect of viewing time, time to encounter, and Swedish EM? research practice on perception of aircraft separation on A 80-27766 a cockpit display of traffic information [NASA-TM-81173] 880-18038
A-27
HYBRID NAVIGATION SYSTEMS SUBJECT INDEX
HYBRID NAVIGATION SYSTEMS Specification for the installation of electrical On the NNSS application research in Japan --- Navy resistance strain gauges on strain pairs counter Navigation Satellite System aircraft --- to monitor fatigue damage A80-25164 [AD-A071363] 1180-18369 New possibilities offered by a radio-inertial Aspects of flight test instrumentation --- methods hybrid guidance system digital simulation study to derive aircraft performance and stability and 1180-19836 control characteristics HYDRAULIC EQUIPMENT N80-19098 The practical aircraft hydraulic test stand INCANDESCENCE (SAE PAPER 791079] A80-26636 Incandescent lamp life under random vibration An analytical and experimental study of aircraft N80-l8221 hydraulic lines including the effect of mean flow INCOMPRESSIBLE FLOW [AD-A079746] N80-19079 Unsteady pressure measurements on wing-store HYDROFOIL CRAFT combinations in incompressible flow New approaches to sailing A80-26269 A80-26344 INCOMPRESSIBLE FLUIDS HYDROGEN FUELS Damping in tapered annular seals for an Future large cargo aircraft technology incompressible fluid A80-27269 [NASA-TP-1646] 1180-19495 The changing horizons for technical progress. II INDUSTRIAL MANAGEMENT A80-27 270 The future development of air traffic as seen by HYPERSONIC FLIGHT airline companies Trajectories optimization in hypersonic flight 1180-28487 [NASA-CE-162846] 1180-19026 INERTIAL GUIDANCE Hypersonic interference flow flight experiment New possibilities offered by a radio-inertial design --- investigating aerodynamic heating and hybrid guidance system digital simulation study loads N80-19836 [AD-A078861] 1180-19044 INERTIAL NAVIGATION HYPERSONIC NOZZLES The experimental strapdown system of DFVLR --- for .Laser-Raman flow-field diagnostics of two large inertial guidance and navigation of civil aircraft hypersonic test facilities 1180-28218 [AD-A078289] 1180-19135 Cruise-missile-carrier navigation requirements HYSTERESIS 1180-19843 Hysteresis of aerodynamic characteristics --- for INFLATABLE STRUCTURES wing models and segmented conical bodies of Feasibility testing of a Body Inflatable Bladder revolution (BIB) restraint device A80-27167 [AD-A078681] 1180-18013 Research on the stability of air cushion systems INFLATING [UTIAS-238) 1180-17985 Recovery system prelimiminary design. A Rind tunnel test to investigate aerodynamic simplified approach to determining staging, hysteresis phenomena of the F-4 and F-li timing and altitude requirements for fast aircraft models inflating parachutes [AD-A077196] N80-19040 [AD-A077548] 1180-19041 INFRARED RADIATION Advanced infrared signature prediction program. Spectral calculation of radiation from a turbine ICE FORMATION propulsion system as intercepted by an observer General aviation icing flight test (SCORPION). Volume 3: Analysis A80-27383 [110-11078436] 1180-19124 Aircraft icing during low-level flights INFRARED WINDOWS [AD-A078843] 1180-19052 GE-SI supersonic PLIR window IDEAL GAS [AD-A078371] 1180-19948 Numerical method for calculating supersonic flow INLET FLOW past a plane air intake with detached shock wave The experimental modeling of unstalled supersonic A80-27 148 turbofan flutter 1FF SYSTEMS (IDENTIFICATION) [1111111 80-0454] 1180-26963 Hybrid optical/digital processing for target Numerical prediction of compressible potential identification flow for arbitrary geometries --- in airliner A80-26867 air-intake systems ILLUMINATING 1180-27743 Crew station design facility feasibility study Transonic inlet flow calculations using a general [AD-A078134) 1180-19064 grid-generation scheme IMAGE ENHANCEMENT 1180-27744 Transparent engines at Rolls-Royce - The Effect of wake-type nonuniform inlet velocity application of high energy X-ray technology to profiles on first appreciable stall in gas turbine development plane-wall diffusers A80-25447 1180-27747 IMAGE MOTION COMPENSATION INLET NOZZLES Hybrid optical/digital processing for target Straight-walled, two-dimensional diffusers - identification Transitory stall and peak pressure recovery A80-26867 1180-27746 IMAGE PROCESSING INSTRUMENT LANDING SYSTEMS Hybrid optical/digital processing for target Factorial design of experiments in the test and identification evaluation of a complex control system --- for A80-26867 carrier-based aircraft landing Methodology for target discrimination A80-27242 1180-27347 Experimental procedure to determine limits of ISM IMPACT RESISTANCE interference affecting navigational ILS equipment Development and test of low-impact resistant towers Industrial, Scientific and Medical [AD-A077160] N80-18052 A80-27160 IMPACT TESTS Multipath analysis of 115 glide path Graphite-epoxy panel compression strength 1180-19354 reduction due to local impact INTAKE SYSTEMS A80-27598 Low speed test of the aft inlet designed for a IN-FLIGHT MONITORING tandem fan V/STOL nacelle Flight recording in the UK. I - Evolution (NASA-CE-159752] 1180-180112 A80- 27 751 INTEGRAL EQUATIONS Computational techniques for EMP interaction 1180-27777
A-28
SUBJECT INDEX LARDING RADAR
INTERFACIAL TENSION Effect of temperature on surface noise Liquid metal slip ring --- aerospace environments A80-28419 (NASA-CASE-LEW-12277-3] N80-18300 Viscous flowfields induced by two- and INTERNATIONAL COOPERATION three-dimensional lift jets in ground effect System EEC - Tendencies of a worldwide [AD-1078782] 1180-18343 standardization and cooperation Vorticity associated with multiple jets in a A80-27784 crossflow --- vertical takeoff aircraft INTERNATIONAL LAW [NASA-CR-162855] 1180-19454 Legal liability of the controller. I JET IMPINGEMENT A 80-28500 An experimental study of two-dimensional The freight forwarder as an air carrier supersonic jet impingement on a flat plate 180-28862 [AD-A076536] N80-17996 INVERTED CONVERTERS (DC TO AC) JET THRUST A rotary inverter system for a multiple-electrode Influence of the empennage on the effective thrust END generator of jet engine exhaust nozzles A80-25093 180-27139 INVESTMENT CASTING Method and apparatus for rapid thrust increases in Pratt and Whitney innovations --- turbomachine a turbofan engine blade casting and hot isostatic pressing of [NASA-CASE-LEW-12971-1] 1180-18039 turbine disks JOINTS (JUNCTIONS) A80-25448 Distribution of forces and stresses along rows of INVISCID FLOW bolted connections Three-dimensional inviscid compressible rotational A80-27 143 flows Numerical results and comparison with JP-5 JET FUEL analytical solutions Evaluation of JP-5 turbine fuel in the single A80-27745 cylinder cue 1790 diesel engine IONOSPHERIC PROPAGATION (AD-A078666) 1180-18206 Modern HF communications for low flying aircraft N80-19375 Assessment of HF communications reliability K N80-19377 KEYLAR (TRADEHARK) Composite components on commercial aircraft 180-27597 J-79 ENGINE Evaluation of fuel character effects on 379 engine L combustion system 1-1011 AIRCRAFT [AD-A078440] N80-19119 Advanced composite aileron for L-1011 transport 3-85 ENGINE aircraft Tests of an improved rotating stall control system [NASA-CR-162863J 1180-18103 on a 3-85 turbojet engine Advanced manufacturing development of a composite (10-1077704] N80-19109 empennage component for 1-1011 aircraft JET AIRCRAFT [NASA-CR-162862] 1180-18104 On the equations of motion about the mass centre LAMINAR BOUIDARI LAYER of the jet aircraft considered as variable mass Laminar separation bubble with transition /theory system and experiment! 180-26325 [ONEBA, TP NO. 1980-20] A80-27203 Wind tunnel test to investigate aerodynamic A theoretical analysis of simulated transonic hysteresis phenomena of the P-U and F-il boundary layers in cryogenic-nitrogen wind tunnels aircraft models [NASA-TP-1631] N80-19131 (AD-A077196) N80-19040 LAMINAR PLOW Measuring technological change in jet fighter Local laminarization in turbulent diffusion flames aircraft A80-24819 (AD-A077393) N80-19084 Increasing aircraft efficiency through laminar JET AIRCRAFT NOISE flow control Strouhal number influence on flight effects on jet A80-24899 noise radiated from convecting quadrupoles The development of a self-streamlining flexible A80-28418 walled transonic test section Effect of temperature on surface noise [AIlA 80-0440) 180-26964 A80-28419 LAMINAR PLOW AIRFOILS Publications in acoustic and noise control from Visualization of the laminar-turbulent transiticn NASA Langley Research Center during 1940-1979 in the flow over an airfoil using the smoke-wire bibliographies technique [NASA-Tfl-80211] 1180-18884 [AIAA 80-0421] A80-26935 JET ENGINE FUELS LAMINATES Characteristics of burning Jet A fuel and Jet A Failure mechanisms for advanced composite sandwich fuel-water emulsion sprays construction in hostile environments --- naval A80-24817 aircraft structures Local laminarization in turbulent diffusion flames 180-26884 A80-24819 Graphite-epoxy panel compression strength Initial characterization of an Experimental reduction due to local impact Referee Broadened-Specification (EBBS) aviation A80-27598 turbine fuel LANDING AIDS [NASA-TN-81440] 1180-18205 The introduction of new systems in international JET ENGINES civil aviation Structural analysis of hollow blades: 7arsional A80-28383 stress analysis of hollow fan blades for LANDING GEAR aircraft jet engines Have Bounce --- validation of computer simulations [NASA-TN-75718] 1180-19111 of F-U dynamic response to multiple runway repairs Ferrographic and spectrographic analysis of oil 180-27382 sampled before and after failure of a jet engine LANDING LOADS (NASA-TM-81430] 1180-19497 Have Bounce --- validation of computer simulations JET FLOW of F-U dynamic response to multiple runway repairs The simulation and modeling of jet plumes in wind A80-27382 tunnel facilities LANDING RADAR [AIAA 80-0430] 180-26941 Primary radar in ATC Strouhal number influence on flight effects on jet 180-28381 noise radiated from convecting quadrupoles 180-28418
1-29
LANDING SIMULATION SUBJECT INDEX
LANDING SIMULATION Computer programs for estimating civil aircraft Design of an electronic model of a microwave economics aircraft landing system [NASA-TM-80196] N80-18988 480-26471 LIFE SUPPORT SYSTEMS A flight simulation investigation on the Improved MPG for the BAe 146 feeder-jet feasibility of curved approaches under HIS 880-254449 guidance LIFT 880-19844 Minimum-weight wing in the presence of lift Modeling and flight simulation of an active constraints configured aircraft under M.L.S. guidance 880-27136 880-19845 LIFT DRAG RATIO LANGUAGES Induced drag and lift-drag ratio of swept wings at Structures in aeronautical phraseology: From supersonic speeds English to Spanish A80-27175 880-19978 LIFT FANS LASER ANEMOMETERS Measurements of the dynamic performance of the High-resolution LDA measurements of Reynolds main drive fan of the RAE 5 metre pressurised stress in boundary layers and wakes low speed wind tunnel (4188 80-0436] 480-26967 (8188 80-0 4456] 480-26956 LASER APPLICATIONS LIFTING BODIES VSTOL test techniques utilizing laser tracking Trajectories optimization in hypersonic flight 480-27234 [NASA-CE-162846] 880-19026 LASER DOPPLER VELOCIBETERS LIGHT AIRBORNE MULTIPURPOSE SYSTEM High-resolution LDA measurements of Reynolds Avionics logistics support including V/STOL, stress in boundary layers and wakes LAMPS, and instrument repair (4144 80-0436] 880-26967 [80-8077460] 880-19087 Laser anemometer measurements at the exit of a 163 LIGHT AIRCRAFT combustor An induction gyrocompass A80-27737 480-25214 Helicopter remote wind sensor system description EMC in lightweight helicopters - Special prcblems (AD-8076153] 880-18024 and experience in design and control LASER GUIDANCE A80-27773 The laser gyro and its application to an HP communication to small low flying aircraft helicopter navigation system 880-19374 880-28221 LIGHT TRANSMISSION LATERAL STABILITY Optical design of airport control tower cabs ECAIR design philosophy for fighter aircraft A80-24746 departure and spin resistance LIGHT TRANSPORT AIRCRAFT (SAE PAPER 791081] 880-26637 Aeroacoustic vind-tunnel tests of a light Exploratory investigation of the effects of vortex twin-boom general-aviation airplane with free or bursting on the high angle-of-attack shrouded-pusher propellers --- in the Langley lateral-directional stability characteristics of full-scale tunnel highly-swept wings (NASA-TM-80203] 880-19023 [AIAA 80-0463] 880-26960 LIGHTNING Digital computer solution of aircraft longitudinal Rain erosion of lightning protection coatings for and lateral directional dynamic characteristics carbon fibre composites [AD-A078672] 880-19068 A80-25059 LAUNCH ESCAPE SYSTEMS Lightning protection for aircraft Prototype development passive, seat-mounted limb A80-27021 retention system Induced effects of lightning on an all composite [AD-A076331] 880-19053 aircraft LAUNCHING A80-27783 New remotely piloted vehicle launch and recovery Atmospheric electricity and military operations concepts. Volume 1: Analysis, preliminary (80-8078482] 880-19693 design and performance/cost trade studies LINGUISTICS [AD-A077 4475] 880-19066 Structures in aeronautical phraseology: From LEADING EDGES English to Spanish Effects of forebody, wing and wing-body-LEE N80-19978 flowfields on high angle of attack aerodynamics LIQUID COOLING Leading Edge extensions Control of particulate emissions from turbine (SAE PAPER 791082] 480-26638 engine test cells by cooling water injection Numerical modeling of supersonic flow near a thin [80-8075947] 880-18587 delta wing with discontinuous edge LIQUID METALS A80-27147 Liquid metal slip ring --- aerospace environments Laminar separation bubble with transition /theory [NASA-CASE-LEW-12277-3] 880-18300 and experiment/ LOAD DISTRIBUTION (FORCES) [ONERA, PP NO. 1980-20] 880-27203 Prandtls biplane theory applied to canard and Aerodynamic investigation of C-141 leading edge tandem aircraft modification for cruise drag reduction, volume 2 480-28852 (80-4077688] N80-19081 LOADS (FORCES) LEAR JET AIRCRAFT MINITWISI: A shortened version of TWIST First experience with telemetry and real time data (LBP-TB-1 446) 880-18438 reduction at Gates Learjet Development of a normalized probability 480-2722 8 distribution for lateral load factors- due to Atmospheric electricity and military operations aircraft ground turning [40-8078482] 880-19693 [AD-A077047] 880-19070 LEGAL LIABILITY LOGISTICS Legal liability of the controller. I Computer simulation model of the logistic support A80-28500 system for electrical engineering test equipment LIFE (DURABILITY) M80-19560 Composite components on commercial aircraft LOGISTICS MANAGEMENT [RASA-TN-80231] 880-18109 Avionics logistics support including V/STOL, Estimation of the endurance of civil aircraft wing LAMPS, and instrument repair structures --- life estimate method for wing [80-4077460] 880-19087 loading on general aviation aircraft LONGITUDINAL STABILITY ESDU-79024] 880-19060 MCAIB design philosophy for fighter aircraft LIFE CYCLE COSTS departure and spin resistance Fiberglass rotor produced [SAE PAPER 791081] 880-26637 A80-24740
4-30
SUBJECT INDEX MATHEMATICAL MODELS
Fundamentals of design. VI - Tailplanes, tailless The integrated management of reliability and and canard design maintainability in procurement A80-27728 880-19558 Effect of sweep and aspect ratio on the MAINTENANCE longitudinal aerodynamics of a spanloader wing Investigation of engine performance degradation of in- and out-of-ground effect --- conducted in TF33-P-7 engines Langley V/STOL wind tunnel A80-27233 (NASA-TN-80199] 880-17993 MAN MACHINE SYSTEMS Digital computer solution of aircraft longitudinal The effect of viewing time, time to encounter, and and lateral directional dynamic characteristics practice on perception of aircraft separation on (AD-A078672] 880-19068 a cockpit display of traffic information Handling quality requirements for advanced [NASA-TM-81173] 880-18038 aircraft design longitudinal mode Closed loop models for analyzing engineering (AD-A077858) 880-19128 requirements for simulators LOW ALTITUDE [NASA-CE-2965] 880-19063 Aircraft icing during low-level flights Real-time simulation: An indispensable but [AD-A0788 143] 880-19052 overused evaluation techique HF communication to small low flying aircraft 180-19820 N80-19374 Modeling the human operator: Applications to Modern HF communications for low flying aircraft system cost effectiveness H80-19375 880-19846 LOW ASPECT RATIO WINGS MAN OPERATED PROPULSION SYSTEMS Analysis of the nonuniqueness of solutions to the Crossing the Channel in the Gossamer Albatross problem of flow separation for small-aspect A80-27389 delta wings MANAGEMENT A80-27 127 The re-organization of airport administration in Improvement of the convergence of the method of Canada polynomials in designing small-aspect-ratio wings A80-252145 A80-27183 MANAGEMENT METHODS LOW SPEED WIND TUNNELS The integrated management of reliability and Measurements of the dynamic performance of the maintainability in procurement main drive fan of the RAE 5 metre pressurised N80-19558 low speed wind tunnel MANAGEMENT PLANNING [AIAA 80-0456) A80-26956 Estimating the time required to transition A new rig for flight mechanics studies in the aircraft fleets to new scheduled maintenance ONERA Aerothermodynamic Test Center of Nodane intervals [AIAA 80-0464] A80-26961 [AD-A078606) N80-19027 A system for the measurement of the attitude of MANIPULATORS wind tunnel models Evaluation of a new concept for reducing (AIAA 80-0465) A80-26962 free-stream turbulence in wind tunnels Low speed test of the aft inlet designed for a [AIAA 80-0 4432] A80-26942 tandem fan V/STOL nacelle MANUAL CONTROL (NASA-CR-159752] 880-180442 Automatic control of NASA Langleys 0.3-meter LUBRICATING OILS cryogenic test facility Accuracy and repeatability indices for joint oil (AIAA 80-0416] A80-26931 analysis program data MARINE BIOLOGY [AD-A078156] 880-19266 Airships - Basis for a new oceanic capability Ferrographic and spectrographic analysis of oil A80-28269 sampled before and after failure of a jet engine MARKET RESEARCH (NASA-TN-81430] 880-191497 The future development of air traffic as seen by LUMINAIRES airline companies Incandescent lamp life under random vibration A80-28481 880-18221 A consideration of general aviation in the United Kingdom [11-7902] 880-17982 M MASS DISTRIBUTION MACH NUMBER Analytical determination of the influence of Influence of the empennage on the effective thrust elasticity and mass distribution on the of jet engine exhaust nozzles aerodynamic characteristics of an aircraft in A80-27 139 quasi-steady motion MAGNETOH!DRODYNAMIC GENERATORS A80-27132 A rotary inverter system for a multiple-electrode MASS PLOW RATE MilD generator A mass flowmeter with compensation for thermal A80-25093 density variations of the fluid MAGNETS A80-25220 Permanent magnet and superconducting generators in MASS TRANSFER airborne, high power systems --- computer Heat, mass and momentum transfer through sprays program to predict weight of the generators and cross flow component systems 880-18327 [AD,-A078424] 880-18311 MATCHED FILTERS MAINTAINABILITY Methodology for target discrimination Reliability and maintainability design standards A80-27347 from readiness-related goals --- for naval MATHEMATICAL MODELS aircraft weapon systems Numerical simulation of the wind tunnel [SAE PAPER 791109] A80-26651 environment by a panel method Advanced composites serviceability program - [AIAA 80-0419] A80-26933 Status review --- inspection of aircraft Flight control design based on nonlinear model structures with uncertain parameters A80-26890 A80-28018 Avionics Reliability, Its Techniques and Related Implicit model following and parameter Disciplines --- conferences identification of unstable aircraft [AGARD-CP-261] 880-19519 A80-28019 An analysis of the evolution of the reliability An analytical and experimental study of aircraft and maintainability disciplines hydraulic lines including the effect of mean flow 880-19520 [A0-A079746] 880-19079 A new approach to maintainability prediction Identification evaluation methods avionics, ground, and shipboard electronics 880-19096 880-19537 Identification experience in extreme flight regimes N80-19102
A-31
MATRICES (MATHEMATICS) SUBJECT INDEX
Multipath analysis of ILS glide path MICROWAVE LANDING SYSTEMS 1480-19354 Design of an electronic model of a microwave Reliability growth models aircraft landing system 1480-19522 880-26471 Trends in reliability modeling technology for A flight simulation investigation on the fault tolerant systems feasibility of curved approaches under MLS N80-19534 guidance Modeling and Simulation of Avionics Systems and 1480-19844 Command, Control and Communications systems Modeling and flight simulation of an active conferences configured aircraft under M.L.S. guidance [AGARD-CP-268] N80-19809 N80-19845 Verification and validation of avionic simulations MICROWAVE RADIOMETERS 1480-19814 Radiometric measurements of targets and clutter The application of modeling and simulation to the 880- 26 802 development of the E-3A NICROWAVE SCANNING BEAM LANDING SYSTEM 1480-19823 Flight performance of the OCT B-737 airplane at MATRICES (MATHEMATICS) Jorge Newberry Airport, Buenos Aires, Argentina Singularities of the numerical solution of the using TBSB/MLS guidance algebraic Hiccati equation in matrix form by a [NASA-TM-80223] 1480-18021 modification of the Lax-Wendroff method --- for MICROWAVE TRANSMISSION automatic aircraft control Error rate performance of M-ary DPSK systems in 880-27 134 satellite/aircraft communications MAXIMUM LIKELIHOOD ESTIMATES A80-25945 Aircraft identification experience MILITARY AIR FACILITIES N80- 19100 Breaking V/STOL free of Catch 22 --- technology MEASURING INSTRUMENTS utilization and assessment Aircraft instruments and automatic systems /3rd 880-26 342 revised and enlarged edition! --- Russian book The history of static test and Air Force A80-26350 structures testing MECHANICAL DRIVES [AD-A077029] 1480-19136 Evaluation of a high performance fixed-ratio MILITANT AIRCRAFT traction drive High-angle-of-attack flying qualities - An [NASA-TM-81425] 1480-18404 overview of current design considerations The application of reliability improvement [SAE PAPER 791085] A80-26640 warranty to dynamic systems HLH and beyond --- Heavy Lift Helicopter [AD-A075520] 1480-18419 (SAE PAPER 791086] 880-26641 MECHANICAL PROPERTIES Multirole cargo aircraft options and configurations Cast aluminum primary aircraft structure (SAE PAPER 791096) A80-266145 Future multi-mission transport aircraft - METAL FATIGUE Requirements and design possibilities Evaluation of the effectiveness of case-hardening (SAE PAPER 791097] 880-26646 gas-turbine-engine components on the basis of On-condition maintenance - Review of military fatigue-failure similarity equations engines A80-26193 (SAE PAPER 791102] 880-26648 Fatigue and microstructure; Proceedings of the Reliability and maintainability design standards Materials Science Seminar, St. Louis, No., from readiness-related goals --- for naval October 114, 15, 1978 aircraft weapon systems 880-26730 (SAE PAPER 791109] 880-26651 Fatigue in machines and structures - Aircraft Fatigue in machines and structures - Aircraft 880-26731 880-26131 Applying pressure . . . Relieving stress Military aircraft and missile technology at the stress coining aircraft structures Langley Research Center: A selected bibliography 880-27257 [NASA-TN-80204] 1480-19024 Acceleration of multicycle fatigue testing on Military adaption of a ccnmercial VOR/ILS airborne aluminum structural alloys radio with a reliability improvement warranty A80-27479 N80-19540 The fatigue performance of service aircraft and MILITANT HELICOPTERS the relevance of laboratory data The laser gyro and its application to an 880-27789 helicopter navigation system Avoiding divergent stall in control configured 880-28221 aircraft by using a canard arrangement Helicopter remote wind sensor system description A80-28854 (AD-A076153] 1480-18024 METAL SHELLS Design of a simulator for studying the helicopter Experimental measurement of fields excited inside - SDVEH the fuselage of an aircraft N80-19829 MILITANT OPERATIONS METAL SURFACES Atmospheric electricity and military operations Evaluation of the effectiveness of case-hardening [AD-A078482] 1480-19693 gas-turbine-engine components on the basis of MILITARY TECHNOLOGY fatigue-failure similarity equations Fighter options for tactical air defense, A80-26 193 (SAE PAPER 791108] 880-26650 METEOROLOGICAL INSTRUMENTS Viscoelastic damping in USAF applications Preliminary assessment of an automated system for B80-19582 detecting present weather Air Force Flight Dynamics Laboratory fiscal year (AD-A078031) 1480-19706 1981. lechnical objective document METEOROLOGICAL RADAR AD-A078973] B80-20020 Reliability growth testing of avionic equipment MILLIMETER WAVES 880-27612 Radiometric measurements of targets and clutter MICROPROCESSORS A80-26802 Microprocessor controlled ejection seat MISSILE COMPONENTS [AD-A077479] 1480-19049 Firebrand anti-ship missile target - Flight test Microprocessor control of low speed V/STCL flight program objectives and vehicle instrumentation (140-8077661] 1480-19129 requirements MICROSTRUCTURE A80-27236 Fatigue and microstructure; Proceedings of the MISSILE CONFIGURATIONS Materials Science Seminar, St. Louis, Mo., Firebrand anti-ship missile target - Flight test Cctober 14, 15, 1978 program objectives and vehicle instrumentation A80-26730 requirements A80-27236
A-32
SUBJECT INDEX NUMERICAL PLOW VISUALIZATION
MISSILES On-board precision approach system using NAVSIAR GPS Military aircraft and missile technology at the A80-25162 Langley Research Center: A selected bibliography The impact of GPS on CV mission effectiveness (NASA-TM-80204) 1180-19024 A80-25165 Demonstration program for a flexible duct valve Continued study of NAVSTAB/GPS for general aviation for ramjet engine fuel controls [NASA-CR-159145] 1180-18020 [AD-A078529] N80-19123 NETWORK ANALYSIS MISSION PLANNING The experimental strapdovn system of DPVLR --- for The impact of GPS on CV mission effectiveness inertial guidance and navigation of civil aircraft A80-25165 A80-28218 MODELS NIGHT PLIGHTS (AIRCRAFT) Computer simulation model of the logistic support Development and flight test of a two-place system for electrical engineering test equipment night/adverse weather 1-10 for the close-air B80-19560 support and battlefield attack mission Avionics evaluation program: Simulation models (SIR PAPER 791069) 180-26632 for the effectiveness analysis of avionics NIGHT VISION U80-19838 Simulation of a night vision system for low level MOISTURE helicopter operations --- using helmet mounted Failure mechanisms for advanced composite sandwich display device construction in hostile environments --- naval N80-19832 aircraft structures NITROGEN A80-26884 A theoretical analysis of simulated transonic MOMENTUM TRANSFER boundary layers in cryogenic-nitrogen wind tunnels Heat, mass and momentum transfer through sprays [NASA-TP-1631 ] 1180-19131 cross flow NOISE GENERATORS 1180-18327 Identification of noise sources in PC centrifugal MONOPULSE RADAR fan rotors A time-shared monopulse approach to air/surface N80-18395 radar ranging NOISE INTENSITY 180-26791 Strouhal number influence on flight effects on jet MRCA AIRCRAFT noise radiated from convecting guadrupoles The Tornado all-weather high-speed low-level system A80-28418 180-27379 NOISE POLLUTION MULTIPATH TRANSMISSION Local ground noise generated by supersonic Multipath analysis of US glide path transport planes N80-19354 A80-26206 NOISE REDUCTION Local ground noise generated by supersonic N transport planes NASA PROGRAMS A80-26206 Composite components on commercial aircraft Publications in acoustic and noise control from (NASA-TH-80231] 1180-18109 NASA Langley Research Center during 1940-1979 Ames Research Center publications: A Continuing bibliographies bibliography, 1978 [NASA-TM-80211 ] 1180-18884 (NASA-TM-81175) 1180-18985 NOISE SPECTRA NASA authorization, 1981, program review, volume 2 The duration of false alarms in surveillance radar [GPO-56-220] 1180-19988 A80-27902 NASTRAN Effect of temperature on surface noise Investigation of fan blades shroud mechanical A80-28419 damping NORADIABATIC THEORY [AD-A078439] 1180-19120 A study of nonadiabatic boundary-layer NATIONAL AIRSPACE UTILIZATION SYSTEM stabilization time in a cryogenic tunnel for Report on the task force on aircraft separation typical wing and fuselage models assurance, appendices --- systems analysis of (AIAA 80-0417] 180-26932 collision avoidance systems integration in the NONDESTRUCTIVE TESTS air traffic control airspace utilization system Nondestructive evaluation of graphite composite [AD-A077713] N80-18017 aircraft structures NAVIGATION AIDS 180-26891 An induction gyrocompass Nondestructive evaluation of airport pavements. A80-25214 Volume 1: Program references NAVIGATION INSTRUMENTS [AD-1078835] 1180-18051 The impact of GPS on CV mission effectiveness Nondestructive evaluation of airport pavements. A80-25165 Volume 2: Operational manual for PAVBEN program The Federal Aviation Administration navigation at TCC program [10-1079495] N80-19130 180-26819 NONLINEAR EQUATIONS Tactical navigation system testing Plight control design based on nonlinear model A80-27237 with uncertain parameters Airport radio navigation systems --- Russian book A80-28018 180-27716 NONUNIFORM FLOW NAVIGATION SATELLITES Effect of wake-type nonuniform inlet velocity Navigation satellite users; Proceedings of the profiles on first appreciable stall in National Aerospace Symposium, Springfield, Va., plane-wall diffusers March 6-8, 1979 A80-27747 A80-25141 NUCLEAR EXPLOSIONS EAVSTAR SATELLITES Swedish ESP research Navigation satellite users; Proceedings of the 180-27766 National Aerospace Symposium, Springfield, Va., NUCLEAR PROPELLED AIRCRAFT March 6-8, 1979 The changing horizons for technical progress. TI 880-251111 A80-27270 Navstar field test results NUMERICAL FLUB VISUALIZATION A80-25143 Numerical simulation of the wind tunnel Shipboard antenna tests for GPS environment by a panel method 180-25144 [AIAA 80-0419] 180-26933 The Navstar Global Positioning System and time Numerical modeling of supersonic flow near a thin 180-25146 delta wing with discontinuous edge A collision avoidance system using Navstar/GPS and A80-27147 ATC 1185 180-25157
A-33
0 RING SEALS SUBJECT INDEX
Transonic inlet flow calculations using a general Transient effects on a stalled airfoil in a grid-generation scheme pulsating flow: Comparison with results from a A80-27744 similar airfoil undergoing horizontal shaking during wind tunnel tests (AAAF-NT-79-13) N80-18003 0 OUTLET FLOW O RING SEALS Laser anemometer measurements at the exit of a 163 Damping in tapered annular seals for an combustor incompressible fluid A80-27737 [NASA-TP-1646] N80-19495 OZONORETR! OCEAN SURFACE Measurements of cabin and ambient ozone on B747 The Surface Contour Radar, a unique remote sensing airplanes instrument A80-28853 A80-26085 OCEANOGRAPHY Airships - Basis for a new oceanic capability p A80- 28 269 PANAVIA MILITARY AIRCRAFT OMEGA NAVIGATION SYSTEM Reliability management of the avionic system of a On the NNSS application research in Japan --- Navy military strike aircraft Navigation Satellite System N80-19546 A80-25164 PANELS OPERATING SYSTEMS (COMPUTERS) Crack development in panels of a pressurized NSSC-2 operating system design requirements fuselage under the combined effect of specification pressurization-induced cyclic loads and (NASA-CR-161396] N80-19861 high-frequency vibrations OPERATIONAL PROBLEMS A80-26195 Operational implications of some NACA/NASA rotary Application of geometrical programming to problems wing induced velocity studies of optimal design A80-27599 A80-27137 OPERATIONS RESEARCH PARACHUTE DESCENT Estimating the time required to transition Recovery system prelimiminary design. A aircraft fleets to new scheduled maintenance simplified approach to determining staging, intervals timing and altitude requirements for fast (AD-A078606] N80-19027 inflating parachutes OPTICAL COMMUNICATION (AD-A077548] N80-19041 Application of Nd:YAG optical communications PARAMETERIZATION technology for aircraft to satellite links Parameter Identification --- conference on A 80-26797 techniques applied to aircraft flight test data OPTICAL DATA PROCESSING (AGARD-LS-104] N80-19094 Hybrid optical/digital processing for target Aircraft parameter identification methods and identification their applications: Survey and future aspects A80-26867 N80-19095 OPTICAL GYROSCOPES Identification evaluation methods The laser gyro and its application to an N80-19096 helicopter navigation system Practical input signal design --- For identifying 8O-28221 stability and control derivatives OPTICAL RADAR N80-19097 Methodology for target discrimination Closed loop aspects of aircraft identification A80-27347 N80-19104 OPTICAL TRACKING PARTICLE SIZE DISTRIBUTION VSTOL test techniques utilizing laser tracking Frequency-scanning particle size spectrometer A80-27234 [NASA-CASE-NPO-13606-2] N80-18364 OPTIMAL CONTROL Data reduction and analysis of graphite fiber A single-step method of optimizing statically release experiments indeterminate minimum-volume systems (NASA-CR-159032) H80-190148 A80-27135 PASSENGER AIRCRAFT Minimum-weight wing in the presence of lift Increasing aircraft efficiency through laminar constraints flow control A80-27136 A80-24899 Application of geometrical programming to problems 767 - A Boeing for the 'eighties of optimal design A80-27726 A80-27137 PAVEMENTS Flight control design based on nonlinear model Nondestructive evaluation of airport pavements. with uncertain parameters Volume 1: Program references A80-28018 [AD-A078835] N80-18051 Implicit model following and parameter Nondestructive evaluation of airport pavements. identification of unstable aircraft Volume 2: Operational manual for PAVBEN program A80-28019 at ICC Closed loop models for analyzing engineering (AO-A079495] N80-19130 requirements for simulators PERFORMANCE PREDICTION [NASA-cR-2965] N80-19063 Simulating the shock protection performance of OPTIMIZATION large transit packs by means of small scale Value analysis and the optimum cost concept laboratory models --- applicable to aircraft applied to aerospace engine power plant design A60-27202 £80-27790 Optimal twisting of blades in axial turbomachines Performance estimates of a Boeing 747-100 A80-27797 transport mated with an outsize cargo pod ORBITAL VELOCITY [NASA-TM-80227] N80-18032 Trajectories optimization in hypersonic flight NADC ABC rotor maps (NASA-CR-162846) N80-19026 [AD-1078802] N80-19083 OSCILLATING FLOW Difficulties in predicting avionics reliability Additional flow quality measurements in the N80-19521 Langley Research center 8-Foot Transonic Methods used for discerning the reliability of Pressure Tunnel military aircraft radar [AIAA 80-0434] A80-26944 N8O- 19532 Dynamic stall on oscillating airfoils in A .JrIDS performance model for the E-3A oscillating free-streams N80-19825 B80-17983
A-34
SUBJECT INDEX PREDICTION ANALYSIS TECHNIQUES
PERFORMANCE TESTS POSITION (LOCATION) Navstar field test results Fiber optic sensors for measuring angular position A80-25143 and rotational speed --- air breathing engines Shipboard antenna tests for GPS (NASA-TN-81454] N80-18368 A80-25 144 POSITION INDICATORS Aerodynamic Testing Conference, 11th, Colorado Helicopter crash position indicator flight trials Springs, Cob., March 18-20, 1980, Technical A80-27240 Papers POSITIONING DEVICES (MACHINERY) A80-26929 Navigation satellite users; Proceedings of the Investigation of engine performance degradation of National Aerospace Symposium, Springfield, Va., TF33-P-7 engines March 6-8, 1979 A80-27233 A80-25141 Factorial design of experiments in the test and POTENTIAL FLOW evaluation of a complex control system --- for Numerical prediction of compressible potential carrier-based aircraft landing flow for arbitrary geometries --- in airliner A80-27242 air-intake systems Experience based upon experimental dry tuned gyros A80-27743 A80-28212 POWDER METALLURGY PHASE SHIFT KEYING Advanced aluminum alloys from rapidly solidified Error rate performance of M-ary UPSE systems in powers satellite/aircraft communications (AD-A077197) N80-18161 A80-25945 Development of advanced aluminum alloys from PHOTOELASTIC ANALYSIS rapidly solidified powders for aerospace Measurement of stress distribution in sandwich structural applications beams under four-point bending [AD-A077800] 880-18162 A80-25498 Consolidation of titanium powder to near net shapes PHOTOYLASTICITY [AD-A078039] N80-19239 Distribution of forces and stresses along rows of POWDERED ALUMINUM bolted connections Advanced aluminum alloys from rapidly solidified A80-27143 powers Contribution of photoelastic analysis to the study [AD-A077197] 880-18161 of turbo-engine components Development of advanced aluminum alloys from (BR71985) 880-19112 rapidly solidified powders for aerospace PHOTOMAPPING structural applications The Surface Contour Radar, a unique remote sensing [ID-A077800] N80-18162 instrument POWER CONDITIONING A80-26085 A rotary inverter system for a multiple-electrode PHOTOMETRY MUD generator Aircraft program for target background, and sky A80-25093 radiance measurements POWER EFFICIENCY [AD-A076959) 880-18624 Wind-turbine power improvement with modern airfoil PILOT ERROR sections and multiple-speed generators NASA aviation safety reporting system [AIAA 80-0633] 180-28819 [NASA-TM-78608] 880-18010 POWER PLANTS PILOT PERFORMANCE Simulating the shock protection performance of Aircraft emergency decisions: Cognitive and large transit packs by means of small scale situational variables laboratory models --- applicable to aircraft [AD-A077413] 880-19051 engine power plant design Modeling the human operator: Applications to A80-27790 system cost effectiveness POWERED LIFT AIRCRAFT N80-19846 Analysis of fuel-conservative curved decelerating PILOT TRAINING approach trajectories for powered-lift and CTOL Aircraft emergency decisions: Cognitive and jet aircraft situational variables [NASA-TP-1650] N80-19022 [AD-A077413] 880-19051 Plight evaluation of configuration management PITCHING ROBERTS system concepts during transition to the landing Description of a new high-alpha, high-load, approach for a powered-lift STOL aircraft pitch-yaw dynamic stability test mechanism at AEDC [NASA-TM-81146] N80-19127 [AIAA 80-0451] A80-26952 PREDICTION ANALYSIS TECHNIQUES PLASMA ELECTRODES Aircraft store separation notion prediction via A rotary inverter system for a multiple-electrode grid data trajectories MHD generator (AIRA 80-0462] A80-26959 A80-25093 Avoiding divergent stall in control configured PLUMES aircraft by using a canard arrangement The simulation and modeling of jet plumes in wind A80-28854 tunnel facilities Undercarriage drag prediction methods [AIAA 80-04301 A80-26941 [ ESDU-79015] N80-19028 PNEUMATIC EQUIPMENT Application of the Estimation-Before-Nodeling Air supply system approach for the Boeing Model (EBM) system identification method to . the high 767 Airplane angle of attack/sideslip flight of the T-2C jet [SAN PAPER 791068] A80-26631 trainer aircraft. Volume 2: Simulation study Improved tire/wheel concept --- pneumatic aircraft using T-2C wind tunnel model data tire [AD-A079923] 880-19061 [NASA-CASE-LAR-11695-2] 880-18402 Application of the Estimation-Before-Modeling POLLUTION CONTROL (EBB) system identification method to the high Control of particulate emissions from turbine angle of attack/sideslip flight of the T-2C jet engine test cells by cooling water injection trainer aircraft. Volume 3: Identification of [AD-A075947] 880-18587 T-2C aerodynamics stability and control POLTIMIDE RESINS characteristics from actual flight test data Minimum-mass designs of stiffened [AD-A079924] 880-19072 graphite/polyimide compression panels Advanced infrared signature prediction program. A80-27992 Spectral calculation of radiation from a turbine POLYNOMIALS propulsion system as intercepted by an observer Improvement of the convergence of the method of (SCORPION). Volume 3: Analysis polynomials in designing small-aspect-ratio wings [AD-A078436] 880-19124 A80-27183 Avionics Reliability, Its Techniques and Related Disciplines --- conferences [AGABD-CP-261] N80-19519
A-35
PREDICTIONS SUBJECT INDEX
PREDICTIONS PROGRAMMING LANGUAGES A new approach to maintainability prediction Programs for the transonic wind tunnel data avionics, ground, and shipboard electronics processing installation. Part 7: Extended focal N80-19537 [AD-8073414] 880-18054 PRESSURE DISTRIBUTION PROJECTILES Unsteady pressure measurements on wing-store Wind tunnel and flight test drag comparisons for a combinations in incompressible flow guided projectile with cruciform tails A80-26269 [AIAA 80-0426]. 880-26968 Pressure distribution in rectangular wing /blade/ PROPELLER EFFICIENCY sections during curvilinear motion in an Aeroacoustic wind-tunnel tests of a light incompressible medium twin-boom general-aviation airplane with free or A80-27157 shrouded-pusher propellers --- in the Langley Hysteresis of aerodynamic characteristics --- for full-scale tunnel wing models and segmented conical bodies of [NASA-TM-80203] 880-19023 revolution PROPULSION SYSTEM CONFIGURATIONS 880-27 167 Single rotor options for heavy lift and potential Unsteady effects with control surfaces of multi lift measured in a wind tunnel (SAE PAPER 791087) 880-26642 [AAAF-NT-79-01) 880-18049 Multi rotor options for heavy lift PRESSURE EFFECTS [SAE PAPER 791089] 880-26643 Class of shockfree airfoils producing the same Future large cargo aircraft technology surface pressure - 880-27269 A80-28857 PROPULSION SYSTEM PERFORMANCE PRESSURE MEASUREMENTS Preliminary study of VTO thrust requirements for a Unsteady pressure measurements on wing-store V/STOL aircraft with lift plus lift/cruise combinations in incompressible flow propulsion A80-26269 [NASA-TN-81429] 880-19110 Static pressure orifice system testing method and PROTECTIVE COATINGS apparatus Rain erosion of lightning protection coatings for (NASA-CASE-LAR-12269-1 ] 880-18358 carbon fibre composites PRESSURE RECOVERY A80-25059 Straight-walled, two-dimensional diffusers - P SYC HO ACO U S TICS Transitory stall and peak pressure recovery Methods of sound simulation and applications in 880-27746 flight simulators PRESSURIZED CABINS [NASA-TM-75768] N80-19133 Air supply system approach for the Boeing Model PSYCHOPHYSICS 767 Airplane Development of a visual inspection technique [SAE PAPER 791068] A80-26631 (optical assessment of aircraft transparencies) PRESSURIZING [AD-A079369] 880-19086 Crack development in panels of a pressurized PULSE COMMUNICATION fuselage under the combined effect of The role of HP in air-ground communications: An pressurization-induced cyclic loads and overview high-frequency vibrations N80-19333 A80-26195 PULSE RADAR PROBABILITY DISTRIBUTION FUNCTIONS The duration of false alarms in surveillance radar Development of a normalized probability 88 0-2 79 0 2 distribution for lateral load factors due to aircraft ground turning [80-8077047] 880-19070 W,Ki PROCUREMENT QUASI-STEADY STATES The integrated management of reliability and Analytical determination of the influence of maintainability in procurement elasticity and mass distribution on the 880-19558 aerodynamic characteristics of an aircraft in PRODUCT DEVELOPMENT quasi-steady motion Development and flight test of a two-place A80-27132 night/adverse weather 8-10 for the close-air support and battlefield attack mission [SAE PAPER 791069] 880-26632 R Crossing the Channel in the Gossamer Albatross RADAR APPROACH CONTROL 880-27 389 Airborne radar approach system flight test Flight- recording in the UK. I - Evolution experiment A80-27 751 [AD-8077900] N80-19054 Airbus family concept for the 1990s RADAR BEACONS A80-28489 A collision avoidance system using Navstar/GPS and The aerodynamics of future transport aircraft and AT CR OS the role of the wind tunnel during development 880-25157 A80-28494 RADAR CROSS SECTIONS PRODUCTION ENGINEERING Achieving effective Radar Cross Section flight NAVAIR pushes SPF/DB for structures --- in naval profiles on the B-i aircraft aircraft design and construction A80-27227 A80-24739 RADAR DATA Fiberglass rotor produced Aircraft motion analysis using limited flight and 880-24740 radar data Pratt and Whitney innovations --- turbomachine 88 0-27 24 1 blade casting and hot isostatic pressing of RADAR DETECTION turbine disks Hybrid optical/digital processing for target A80-25448 identification CADD on the F-18 program --- Computer Aided Design A80-26867 and Drafting Methodology for target discrimination A80-26345 A80-27347 New materials and methods for airframe construction RADAR EQUIPMENT 880-28495 Methods used for discerning the reliability of Advanced manufacturing development of a composite military aircraft radar empennage component for 1-1011 aircraft 880-19532 [NASA-CF-162862] 880-18104 RADAR IMAGERY PROGRAM VERIFICATION (COMPUTERS) The Surface Contour Radar, a unique remote sensing Verification and validation of avionic simulations instrument N80-19814 A80-26085
A-36
SUBJECT INDEX RELIABILITY ANALYSIS
RADAR MEASUREMENT Application of MIL-STD-810C dynamic requirements Radiometric measurements of targets and clutter to USAF avionics procurements 180-26802 880-19091 RADAR NAVIGATION REAL TIME OPERATION Primary radar, in ATC Hybrid optical/digital processing for target 180-28381 identification RADAR RANGE A80-26867 A tine-shared nonopulse approach to air/surface First experience with telemetry and real time data radar ranging reduction at Gates Learjet 180-26791 A80-27228 RADAR TARGETS Real-time simulation: An indispensable but Radiometric measurements of targets and clutter overused evaluation techigue A80-26802 N80-19820 RADAR TRACKING E-3A navigational computer system real-time A tine-shared monopulse approach to air/surface environmental simulator radar ranging 880-198211 180-26791 Simulation for whole life development Primary radar in ATC N80-19839 180-28381 RECEPTION DIVERSITY RADIAL FLOW Error rate performance of M-ary DPSE systems in Flow measurements in a turbine scroll satellite/aircraft communications 180-27738 180-25945 RADIATION MEASUREMENT RECIPROCATION Experimental measurement of fields excited inside On the characteristics of the fuselage of an aircraft centrifugal-reciprocating machines --- cryogenic 180-27306 coolers RADIO BEACONS [NASA-CR-162881 ] 880-19499 Airport radio navigation systems --- Russian book RECONNAISSANCE AIRCRAFT A80-27716 A mission training simulator for the Nimrod ME ME RADIO COMMUNICATION 2 and some aspects of the derivation and The role of BF in air-ground communications: An verification of its system models overview 880-19826 880-19373 Proceedings of the Association for Unmanned HF communication to small low flying aircraft Vehicle Systems AUVS '19: 6th Annual Convention 880-19374 [AD-A077877] 880-20018 Assessment of HF communications reliability RECOVERABILITY 880-19 377 New remotely piloted vehicle launch and recovery RADIO EQUIPMENT concepts. Volume 1: Analysis, preliminary Standard engineering installation package. Air design and performance/cost trade studies Traffic Radio Channel Control (ATRCC) equipment (AD-A077475] 880-19066 [10-1077648] 880-19059 RECOVERY PARACHUTES RADIO FREQUENCY INTERFERENCE Recovery system prelimiminary design. A Comparison of measured data with IF-77 propagation simplified approach to determining staging, model predictions timing and altitude requirements for fast (AD-A076508] 880-18259 inflating parachutes RADIO NAVIGATION (10-1071548) 880-19041 The Federal Aviation Administration navigation RECTANGULAR WINGS program Pressure distribution in rectangular wing /blade/ 180-26819 sections during curvilinear motion in an Airport radio navigation systems --- Russian book incompressible medium A80-27716 A80-27157 New possibilities offered by a radio-inertial REENTRY VEHICLES hybrid guidance system digital simulation study Turbulent-boundary-layer excitation and response R80-19836 thereto for a high-performance conical vehicle RADIO RECEIVERS reentry Military adaption of a commercial VOR/ILS airborne N80-18229 radio with a reliability improvement warranty REGRESSION ANALYSIS 880-19540 Measuring technological change in jet fighter RADIO TRANSMISSION aircraft Present-day problems of air traffic control in (10-1077393] 880-19084 ground-to-air communications REGULATIONS 180-26221 Problems of older jet aeroplanes - A regulatory Comparison of measured data with IF-77 propagation authority view nodal predictions A80-25445 (AD-&076508] 880-18259 RELIABILITY Modern HF communications for low flying aircraft Accuracy and repeatability indices for joint oil N80-19375 analysis program data RADIOGRAPHY (10-1078156] 880-19266 Transparent engines at Rolls-Royce - The Assessment of HF communications reliability application of high energy X-ray technology to 880-19371 gas turbine development Methods used for discerning the reliability of A80-25441 military aircraft radar RAIN EROSION 880-19532 Rain erosion of lightning protection coatings for A fault tolerant architecture approach to avionics carbon fibre composites reliability improvement A80-25059 N80-19533 RANAN SPECTRA Impacts of technologies selected on the Laser-Raman flow-field diagnostics of two large reliability and operational availability of hypersonic test facilities equipments. Cost considerations [AD-A078289] 880-19135 880-19536 RAMJET ENGINES Military adaption of a commercial VOB/ILS airborne Demonstration program for a flexible duct valve radio with a reliability improvement warranty for ramjet engine fuel controls 880-19540 (AD-A078529) 880-19123 RELIABILITY ANALYSIS RANDOM VIBRATION Reliability growth testing of avionic equipment Incandescent lamp life under random vibration A80-21612 880-18221 Reliability of high-brightness CRTs for airborne displays 880-19543
A-31 RELIABILITY ENGINEERING SUBJECT INDEX
Reliability management of the avionic system of a The role of research applied to the air traffic military strike aircraft control system 1180-19546 A80-28050 An analysis of software reliability prediction Study of research and development requirements of models small gas-turbine combustors N80-19551 (NASA-CE-159796] 1180-18040 Software development for TORNADO: A case history Ames Research Center publications: A continuing from the reliability and maintainability aspect bibliography, 1978 1180-19554 NASA-TM-81175] 1180-18985 RELIABILITY ENGINEERING RESEARCH FACILITIES Reliability and maintainability design standards Lightning protection for aircraft from readiness-related goals --- for naval A80-27021 aircraft weapon systems Design considerations for attaining 250-knot test [SAE PAPER 791109] 880-26651 velocities at the aircraft landing dynamics Advanced computer program --- for future facility automation and system performance improvements (NASA-TM-80222] 1180-19132 A80-26810 Air Force Flight Dynamics Laboratory fiscal year The application of reliability improvement 1981. Technical objective document warranty to dynamic systems [AD-A078973] 1180-20020 [AD-A075520) 1180-18419 RESEARCH MANAGEMENT Avionics Reliability, Its Techniques and Related The cautious course to introducing new SDM Disciplines --- conferences technology into production systems [AGARD-CP-261] 1180-19519 Structures, Dynamics and Materials An analysis of the evolution of the reliability 880-26343 and maintainability disciplines Major areas of research in aeronautics and air N80-19520 traffic at the German Aerospace Research Difficulties in predicting avionics reliability Establishment /DFVLR/ 1180-19521 A80-28491 Reliability growth models The aerodynamics of future transport aircraft and 1180-19522 the role of the wind tunnel during development A simulation program for the determination of A80-28494 system reliability of complex avionic systems RESIDUAL STRESS U80-19523 Applying pressure . . . Relieving stress Trends in reliability modeling technology for stress coining aircraft structures fault tolerant systems A80-27251 1180-19534 An analysis of residual stresses and displacements Nonelectronic aspects of avionic system reliability due to radial expansion of fastener holes actuation [AD-A076370] 1180-19569 N80-19535 REYNOLDS STRESS Reliability growth through environmental simulation High-resolution LDA measurements of Reynolds electronic equipment stress in boundary layers and wakes N80-19538 [AIAA 80-0436] 880-26961 The A-7 head-up display reliability programme EICCATI EQUATION 1180-19 539 Singularities of the numerical solution of the Formal methods for achieving reliable software algebraic Riccati equation in matrix form by a 1180-19 549 modification of the Lax-Wendroff method --- for The integrated management of reliability and automatic aircraft control maintainability in procurement A80-27134 1180-19558 RIGID ROTORS REMOTE SENSORS A hingeless rotor XV-15 design integration The Surface Contour Radar, a unique remote sensing feasibility study. Volume 1: Engineering instrument design studies A80-26085 (NASA-CB-152310J 1180-18030 Helicopter remote wind sensor system description RIGID STRUCTURES [AD-A076153] 1180-18024 Calculation of minimum-weight and maximum-rigidity Fiber optic sensors for measuring angular position structures in the presence of design constraints and rotational speed --- air breathing engines 880-27165 [NASA-TM-81454] 1180-18368 RISK REMOTELY PILOTED VEHICLES Assessment of the risk due to release of carbon Firebrand anti-ship missile target - Flight test fiber in civil aircraft accidents, phase 2 program objectives and vehicle instrumentation N80-19200 requirements Assessment of risk due to the use of carbon fiber A80-27236 composites in commercial and general aviation New remotely piloted vehicle launch and recovery N80-19201 concepts: Computer program listings RIVETED JOINTS [AD-A076611] 1180-18035 Damping effects in joints and experimental tests New remotely piloted vehicle launch and recovery on riveted specimens concepts. Volume 1: Analysis, preliminary 1180-19584 design and performance/cost trade studies ROLLING MOMENTS [AD-A077475] 1180-19066 Experimental investigation of a circulation Remotely piloted vehicles, volume 2. A control aileron bibliography with abstracts [AD-8078825] 1180-19046 [PB80-802119] 1180-19089 ROTARY WING AIRCRAFT Proceedings of the Association for Unmanned Rotorcraft identification experience Vehicle Systems AUVS 0 79: 6th Annual Convention B80-19101 [AD-A077877] 1180-20018 ROTARY WINGS RESCUE OPERATIONS Fiberglass rotor produced Helicopter crash position indicator flight trials A80-24740 A80-27240 Pressure distribution in rectangular wing /blade/ RESEARCH AIRCRAFT sections during curvilinear motion in an General aviation icing flight test incompressible medium 880-27383 Aao-27 157 The Quiet Short-Haul Research Aircraft /QSRA/ Operational implications of some NACA/NASA rotary 880-27384 wing induced velocity studies RESEARCH AND DEVELOPMENT A80-27599 HLH and beyond --- Heavy Lift Helicopter Application of unsteady airfoil theory to rotary [SAY PAPER 791086] A80-26641 wings 88 0-28 8 5 6
8-38
SUBJECT INDEX SHOCK NAVES
Dynamic stall on oscillating airfoils in SANDWICH STRUCTURES oscillating free-streams Measurement of stress distribution in sandwich N80-17983 beams under four-point bending The aerodynamic design of an advanced rotor airfoil A80-25498 [NASA-CR-2961] N80-17989 Failure mechanisms for advanced composite sandwich Rotors in forward flight and dynamic stall construction in hostile environments --- caval [AAAP-NT-79-20] N80-18050 aircraft structures A flight investigation of blade section 880-26884 aerodynamics for a helicopter main rotor having Graphite-epoxy panel compression strength NLR-1T airfoil sections reduction due to local impact (NASA-TN-80166) N80-19033 A80-27598 NADC ABC rotor maps SATELLITE NAVIGATION SYSTEMS [AD-A078802] N80-19083 On the NNSS application research in Japan --- Navy ROTATING FLUIDS Navigation Satellite System Three-dimensional inviscid compressible rotational A80-25164 flows Numerical results and comparison with SCALE MODELS analytical solutions Development of test methods for scale model A80-27745 simulation of aerial applications in the NASA ROTATING STALLS Langley Vortex Facility Rotating stall in a vaneless diffuser of a [AIAA 80-0427] 880-26939 centrifugal fan Simulating the shock protection performance of 880-27734 large transit packs by means of small scale Rotors in forward flight and dynamic stall laboratory models --- applicable to aircraft [AAAF-NT-79-20] N80-18050 engine power plant design Tests of an improved rotating stall control system A80-27790 on a J-85 turbojet engine Low speed test of the aft inlet designed for a (AD-A077704] N80-19109 tandem fan V/STOL nacelle Basic studies of rotating stall in axial flow [NASA-CR-159152] N80-18042 compressors SCREEN EFFECT [AD-A077690] N80-19115 A comparison of experimental and theoretical ROTOR AENODYNAHICS turbulence reduction from screens, honeycomb and Aerodynamic performance of a centrifugal honeycomb-screen combinations compressor with vaned diffusers [AIAA 80-0433) 880-26943 A80-27735 SEALS (STOPPERS) Optimal twisting of blades in axial turbornachines Wear of seal materials used in aircraft propulsion A80-27797 systems Application of unsteady airfoil theory to rotary 880-28010 wings Gas path seal A80-28856 [NASA-CASE-NPO-12131-3] N80-18400 Aerodynamic and acoustic investigations of axial Seals and gaskets. A bibliography with abstracts flow fan and compressor blade rows, including [2B80-802010] N80-18417 three-dimensional effects SEPARATED PLOW [LD-A077712] N80-19116 Analysis of the nonuniqueness of solutions to the ROTOR BLADES (TURBOHACHINENY) problem of flow separation for small-aspect Rotating stall in a vaneless diffuser of a delta wings centrifugal fan 880-27127 A80-27734 Identification of noise sources in PC centrifugal ROTOR LIFT fan rotors Synthesis of rotor test data for real-time N80-18395 simulation SERVICE LIFE (NASA-CE-152311] N80-18029 Opportunistic maintenance policies for economic ROTORS replacement of internal life-limited components A rotary inverter system for a multiple-electrode in modular aircraft engines RHO generator [SAN PAPER 191101] A80-26647 A80-25093 Advanced composites serviceability program - Liquid metal slip ring --- aerospace environments Status review --- inspection of aircraft (NASA-CASE-LEW-12217-3] N80-18300 structures RUDDERS 880-26890 Fundamentals of design. V - Fin design for combat SHAPES aircraft Consolidation of titanium powder to near net shapes A80-27725 [AD-A078039] N80-19239 Thrust augmented spin recovery device SHEAR STRESS [NASA-CASE-hR-11970-2] N80-18048 Improvement of the convergence of the method of RUNWAY CONDITIONS polynomials in designing small-aspect-ratio wings Have Bounce --- validation of computer simulations A80-27183 of F-4 dynamic response to multiple runway repairs SHIP HULLS A80-27 382 New approaches to sailing RUNWAYS 880-26344 An approach to the runway denial problem SHIPS [SAN PAPER 791107] A80-26649 Shipboard antenna tests for GPS Nondestructive evaluation of airport pavements. 880-25144 Volume 1: Program references SHOCK LAYERS [AD-A078835] N80-18051 Similarity of the aerodynamic characteristics of A computer program for estimating aircraft landing delta wings at supersonic speeds distance 880-27168 (AD-A077169) N80-19088 SHOCK RESISTANCE Simulating the shock protection performance of large transit packs by means of small scale S laboratory models --- applicable to aircraft SAFETY MANAGEMENT engine power plant design Propulsion and energetics panel Working Group 11 A80-27790 on aircraft fire safety. Volume 2: Rain report SHOCK NAVE PROPAGATION (AGARD-AR-132-VOL-2] N80-19047 Numerical method for calculating supersonic flow SAILS past a plane air intake with detached shock wave New approaches to sailing 880-27148 A80-26344 SHOCK NAVES Class of shockfree airfoils producing the same surface pressure A80-28857
A-39 SHORT HAUL AIRCRAFT SUBJECT INDEX
SHORT HAUL AIRCRAFT SOLID STATE DEVICES Improved MPG for the BAe 146 feeder-jet Power system control study. Phase 1: Integrated A80-25449 control techniques The Quiet Short-Haul Research Aircraft /QSRA/ (AD-A078629] N80719125 A80-27384 Solid state power controller verification studies SHORT TAKEOFF AIRCRAFT (AD-A078238] N80-19429 An approach to the runway denial problem SOLID-SOLID INTERFACES (SAY PAPER 791107] A80-26649 Influence of interface on composite failure The Quiet Short-Haul Research Aircraft /QSRA/ A80-26895 A80-27 384 SOUND INTENSITY V/STOLAND avionics system flight-test data on a Methods of sound simulation and applications in UR-1H helicopter flight simulators [NASA-TM-78591] N80-18047 [NASA-TM-75768] N80-19133 Flight evaluation of configuration management SPACECRAFT STRUCTURES system concepts during transition to the landing Damping problems in acoustic fatigue approach for a powered-lift STOL aircraft H80-19580 [NASA-TM-81146] N80-19127 SPANLOADER AIRCRAFT SHROUDED TURBINES The changing horizons for technical progress. II Gas path seal A80-27270 (NASA-CASE-NPO-12131-3] N80-18400 - Effect of sweep and aspect ratio on the SHROUDS longitudinal aerodynamics of a spanloader wing Investigation of fan blades shroud mechanical in- and out-of-ground effect --- conducted in damping Langley V/STOL wind tunnel [AD-A078439] N80-19120 [NASA-TM-80199] N80-17993 SIDESLIP SPECIFICATIONS Application of the Estimation-Before-Modeling NSSC-2 operating system design requirements (EBB) system identification method to the high specification angle of attack/sideslip flight of the -2C jet [NASA-CR-161396] H80-19861 trainer aircraft. Volume 2: Simulation study SPECTROMETERS using T-2C wind tunnel model data Frequency-scanning particle size spectrometer [AD-A079923] N80-19061 [NASA-CASE-NPO-13606-2] N80-18364 Application of the Estimation-Before-Modeling S P ECTR 0 5CC P T (EBB) system identification method to the high Ferrographic and spectrographic analysis of oil angle of attack/sideslip flight of the T-2C jet sampled before and after failure of a jet engine trainer aircraft. Volume 3: Identification of [NASA-TM-81430] N80-19497 T-2C aerodynamics stability and control SPIN REDUCTION characteristics from actual flight test data Control system techniques for improved [AO-A079924] N80-19072 departure/spin resistance for fighter aircraft Application of the Estimation-Before-modeling [SAE PAPER 791083] A80-26639 (EBN) system identification method to the high SPRAYERS angle of attack/sideslip flight of the I-2C jet Heat, mass and momentum transfer through sprays trainer aircraft. Volume 1: Executive summary cross flow (AD-A080025) N80-19073 NBO-18327 SIGNAL PROCESSING SPREAD SPECTRUM TRANSMISSION The duration of false alarms in surveillance radar Applications of the spread-spectrum signals from A80-27902 the NOVA satellites SIGNAL TRANSMISSION A80-25149 Design of an electronic model of a microwave STABILITY AUGMENTATION aircraft landing system Microprocessor control of low speed V/STOL flight A80-26471 (AD-A077661] N80-19 129 SIGNATURE ANALYSIS STABILITY DERIVATIVES Advanced infrared signature prediction program. Practical input signal design --- For identifying Spectral calculation of radiation from a turbine stability and control derivatives propulsion system as intercepted by an observer N80- 19097 (SCORPION) . Volume 3: Analysis STABLE OSCILLATIONS [AD-A078436] N80-19124 Stationary movement of wings in the transonic regime SILICON ALLOTS Spanish thesis GE-SI supersonic FLIR window A80-27723 [AD-A078371] N80-19948 STAGNATION POINT SIMULATION Influence of the angle of attack on the thermal Simulation for integration with dynamic tests of flux at the stagnation point at supersonic speeds the logical elements of principal onboard A80-27138 computers STANDARDIZATION N80-19842 System BBC - Tendencies of a worldwide SIMULATORS standardization and cooperation Crew station design facility feasibility study A80-27784 (AD-A078134] N80-19064 The introduction of new systems in international 8-3A navigational computer system real-time civil aviation environmental simulator A80-28383 N80-19824 STATIC ELECTRICITY SKIN FRICTION Lightning protection for aircraft Local shin friction and static pressure on a swept A80-27021 wing in flight Induced effects of lightning on an all composite {AIAA 80-0423] A80-26937 aircraft SKY RADIATION A80-27783 Aircraft program for target background, and sky Experimental study of electrostatic dischargers radiance measurements for helicopters [AD-A076959] N80-18624 [ONENA, TP NO. 1980-5] A80-28947 SLENDER WINGS STATIC PRESSURE Yawed slender wings at small angles of attack Local skin friction and static pressure on a swept A80-26268 wing in flight SLOT ANTENNAS [AIAA 80-0423] A80-26937 Buoyant module VHF antenna design for submerged Static pressure orifice system testing methcd and systems/aircraft communications apparatus A60-28254 [NASA-CASE-LAR-12269-1 ] N80-18358 SMALL PERTURBATION FLOW Flutter analysis of a RACA 64A006 airfoil in small disturbance transonic flow A80-28851
A-40 SUBJECT INDEX SUBSONIC WIND TUNNELS
STATIC STABILITY Advanced composite aileron for 1-1011 transport Exploratory investigation of the effects of vortex aircraft bursting on the high angle-of-attack [NASA-CR-162863] 1480-18103 lateral-directional stability characteristics of Design considerations for attaining 250-knot test highly-swept wings velocities at the aircraft landing dynamics [8188 80-0463] 880-26960 facility STATIC TESTS [NASA-TN-80222] 1480-19132 The history of static test and Air Force STRUCTURAL DESIGN CRITERIA structures testing The cautious course to introducing new SON [AD-A077029] N80-19136 technology into production systems STATORS Structures, Dynamics and Materials Liquid metal slip ring --- aerospace environments 18 0-2634 3 (NASA-CASE-LEW-12277-3] N80-18300 The aerodynamic design of an advanced rotor airfoil STEELS [NASA-CE-2961] 1480-17989 Establishment of engineering design data for STRUCTURAL ENGINEERING hybrid steel/ceramic ball bearings Improvement of the convergence of the method of [AD-A078934] N80-19509 polynomials in designing small-aspect-ratio wings STIFFNESS A80-27183 Calculation of minimum-weight and maximum-rigidity STRUCTURAL FAILURE structures in the presence of design constraints Crack development in panels of a pressurized 880-27165 fuselage under the combined effect of STRAIN GAGES pressurization-induced cyclic loads and Specification for the installation of electrical high-frequency vibrations resistance strain gauges on strain pairs counter 880-26195 aircraft --- to monitor fatigue damage Failure mechanisms for advanced composite sandwich [80-8071363] N80-18369 construction in hostile environments --- naval STEAK ES aircraft structures Effects of forebody, wing and wing-body-LEX A80-26884 flovfields on high angle of attack aerodynamics Influence of interface on composite failure Leading Edge extensions 880-26895 (SAE PAPER 791082] 880-26638 Damping problems in acoustic fatigue STRAPDOWN INERTIAL GUIDANCE B80-19580 The experimental strapdown system of DFVLB --- for STRUCTURAL RELIABILITY inertial guidance and navigation of civil aircraft Fatigue in machines and structures - Aircraft A80-28218 180-26731 The laser gyro and its application to an STRUCTURAL STABILITY helicopter navigation system minimum-weight wing in the presence of lift 880- 28 22 1 constraints STRESS ANALYSIS 880-27136 Influence of interface on composite failure Application of geometrical programming to problems 180-26895 of optimal design Structural analysis of hollow blades: Torsional A80-27137 stress analysis of hollow fan blades for Distribution of forces and stresses along rows of aircraft jet engines bolted connections (NASA-TM-75716] N80-19111 180-27143 An analysis of residual stresses and displacements STRUCTURAL STRAIN due to radial expansion of fastener holes A review of Australian investigations on [10-8076370] N80-19569 aeronautical fatigue during the period April STRESS CONCENTRATION 1977 to March 1979 --- structural strain and Measurement of stress distribution in sandwich fatigue life studies on aircraft structures and beams under four-point bending construction materials A80-25498 [10-1071641] 1480-18449 Distribution of forces and stresses along rows of STRUCTURAL VIBRATION bolted connections A scientific approach to defeating helicopter A80-27143 vibration STRESS CYCLES 880-251446 Applying pressure . . . Relieving stress Turbulent-boundary-layer excitation and response stress coining aircraft structures thereto for a high-performance conical vehicle A80-272 57 reentry STRODRAL NUMBER 1480-18229 Strouhal number influence on flight effects on jet STRUCTURAL WEIGHT noise radiated from convecting guadrupoles A single-step method of optimizing statically A80-28418 indeterminate minimum-volume systems STRUCTURAL ANALYSIS 880-27135 Structural analysis of hollow blades: Torsional SUBMARINES stress analysis of hollow fan blades for Buoyant module VHF antenna design for submerged aircraft jet engines systems/aircraft communications (RASA-TM-75718] N80-19111 A80-28254 The history of static test and Air Force SUBROUTINES structures testing Easy ACLS dynamic analysis, volume 2. Part 2: [80-1077029] N80-19136 Component computer programs STRUCTURAL DESIGN [10-1079803] 1480-19076 Calculation of minimum-weight and maximum-rigidity SUBSONIC PLOW structures in the presence of design constraints Effect of non-rotating passages on performance of 880-27165 centrifugal pumps and subsonic compressors 767 - A Boeing for the eighties A80-27733 180-27726 Unsteady effects with control surfaces Structural design of transport airplanes for measured in a wind tunnel transient environments [AAAF-NT-79-01 ] 1480-18049 880-27898 SUBSONIC WIND TUNNELS Minimum-mass designs of stiffened Numerical simulation of the wind tunnel graphite/polyimide compression panels environment by a panel method 880-27992 [AIAA 80-0419] 880-26933 The aerodynamic design of an advanced rotor airfoil On the historical development of apparatus and [NASA-CR-2961] 1480-17989 techniques for smoke visualization of subsonic Design and test of a boron - aluminum high and supersonic flows temperature wing [8118 80-0420] 180-26934 [80-1075814] 1480-18034
A-41
SUCTION SUBJECT INDEX
SUCTION SWEEP EFFECT Boundary layer control by means of suction Effect of sweep and aspect ratio on the [NASA-TN-75502] 880-17987 longitudinal aerodynamics of a spanloader wing SUPERCONDUCTING POWER TRAISNISSION in- and out-of-ground effect --- conducted in Permanent magnet and superconducting generators in Langley V/STOL wind tunnel airborne, high power systems --- computer (NASA-TB-80199] N80-17993 program to predict weight of the generators and SWEPT WINGS component systems Local skin friction and static pressure on a swept [AD-A078424) 880-18311 wing in flight SUPERCRITICAL WINGS [8188 80-0423] 880-26937 AV-85 - A second generation V/STOL Exploratory investigation of the effects of vortex [SAE PAPER 791070] 880-26633 bursting on the high angle-of-attach SUPERPLASTICITY lateral-directional stability characteristics of NAVAIR pushes SPF/DB for structures --- in naval highly-swept wings aircraft design and construction [AflA 80-0463] 880-26960 880-24739 Induced drag and lift-drag ratio of swept wings at SUPERSONIC AIRCRAFT supersonic speeds Local ground noise generated by supersoric 880-27175 transport planes Interaction of a two-dimensional strip boundary A80-26206 layer with a three-dimensional transonic SUPERSONIC PLIGHT swept-wing code Evaluation of aircraft windshield materials in a (NASA-TM-78640] 880-17988 simulated supersonic flight environment SWIRLING [AD-A078673) 880-19082 An experimental investigation of two large annular GE-SI supersonic FIlE window diffusers with swirling and distorted inflow (AD-A078371] 880-19948 [NASA-TP-1628] 880-17984 SUPERSONIC FLOW SWITCHING CIRCUITS The experimental modeling of unstalled supersonic Solid state power controller verification studies turbofan flutter [AO-A078238] N80-19429 [8188 80-04511] 880-26963 SYSTEM EFFECTIVENESS Influence of the angle of attack on the thermal Advanced computer program --- for future flux at the stagnation point at supersonic speeds automation and system performance improvements A80-27138 880-26810 Numerical modeling of supersonic flow near a thin Theoretical limitations on collision avoidance delta wing with discontinuous edge systems 880-27147 880-26811 Numerical method for calculating supersonic flow The Federal Aviation Administration navigation past a plane air intake with detached shock wave program A80-27148 A80-26819 Similarity of the aerodynamic characteristics of SYSTEMS ANALYSIS delta wings at supersonic speeds The experimental strapdovn system of DFVLR --- for A80-27168 inertial guidance and navigation of civil aircraft SUPERSONIC FLUTTER A80-26218 The experimental modeling of unstalled supersonic Report on the task force on aircraft separation turbofan flutter assurance, appendices --- systems analysis of [8188 80-04541 880-26963 collision avoidance systems integration in the SUPERSONIC JET FLOW air traffic control airspace utilization system An experimental study of two-dimensional (AD-A077713) N80-18017 supersonic jet impingement on a flat plate Helicopter remote wind sensor system description [80-8076536] N80-17996 [80-8076153] 880-18024 SUPERSONIC SPENDS Application of the Estimation-Before-Modeling Induced drag and lift-drag ratio of swept wings at (EBB) system identification method to the high supersonic speeds angle of attack/sideslip flight of the T-2C jet A80-27175 trainer aircraft. Volume 2: Simulation study SUPERSONIC TRANSPORTS using T-2C wind tunnel model data The changing horizons for technical progress. II (80-8079923] 880-19061 A80-27270 Application of the Estimation-Before-Modeling SUPERSONIC WIND TUNNELS (EBB) system identification method to the high A system for measuring and recording wind-tunnel angle of attack/sideslip flight of the T-2C jet balance data trainer aircraft. Volume 3: Identification of 880-25221 l-2c aerodynamics stability and control On the historical development of apparatus and characteristics from actual flight test data techniques for smoke visualization of subsonic (AD-A079924] 880-19072 and supersonic flows Application of the Estimation-Before-modeling [AIAA 80-0420] 880-26934 (EBB) system identification method to the high The simulation and modeling of jet plumes in wind angle of attack/sideslip flight of the T-2C jet tunnel facilities trainer aircraft. Volume 1: Executive summary [8188 80-0430] 880-26941 [80-8080025] 880-19073 SURFACE GEONETEY An analysis and synthesis of engine condition The Surface Contour Radar, a unique remote sensing monitoring systems instrument [AD-A077531] 880-19 122 A80-26085 Simulation of a night vision system for low level Workshop on Aircraft Surface Representation for helicopter operations --- using helmet mounted Aerodynamic computation display device [NASA-TN-81170] N80-19025 1180-19832 SURFACE NAVIGATION Avionics evaluation program: Simulation models Shipboard antenna tests for GPS for the effectiveness analysis of avionics A80-25144 H80-19838 On the NNSS application research in Japan --- Navy SYSTEMS COMPATIBILITY Navigation Satellite System System ENC - Tendencies of a worldwide A80-25164 standardization and cooperation SURVEILLANCE RADAR 180-27784 The duration of false alarms in surveillance radar SYSTEMS ENGINEERING 880-27902 Aircraft instruments and automatic systems /3rd revised and enlarged edition/ --- Russian book 880-26350 Air supply system approach for the Boeing Model 767 Airplane [SAE PAPER 791068] 880-26631
8-42 SUBJECT INDEX TELEMETRY
Influence of air traffic on the concept of air Tactical navigation system testing traffic control A80-28488 *80-27237 A hingeless rotor XV-15 design integration The Tornado all-weather high-speed low-level system *80-27379 feasibility study. Volume 1: Engineering TARGET RECOGNITION design studies Hybrid optical/digital processing for target [NASA-CB-152310) 880-18030 identification Prototype development passive, seat-mounted limb retention system A80-26867 Methodology for target discrimination [AD-A076331] N80-19053 Tests of an improved rotating stall control system 880-27347 on a .1-85 turbojet engine Aircraft program for target background, and sky [AD-A077704] radiance measurements 880-19109 [AD-A076959] 880-18624 Trends in reliability modeling technology for TARGET SIMULATORS fault tolerant systems Firebrand anti-ship missile target - Flight test N80-19534 program objectives and vehicle instrumentation Nonelectronic aspects of avionic system reliability requirements actuation A80-27236 N80-19535 TAXIING Design and simulation of a C3 system for surveillance purpose Development of a normalized probability distribution for lateral load factors due to N80-19821 aircraft ground turning The application of modeling and simulation to the [AD-A077047) 880-19070 development of the E-3A TECHNOLOGICAL FORECASTING 880-19823 Single rotor options for heavy lift and potential Design of a simulator for studying the helicopter of multi lift - SDVEH [SAE PAPER 791087] 880-26642 N80-19829 Nultirole cargo aircraft Options and configurations [SAE PAPER 791096] 880-26645 II Future multi-mission transport aircraft - T-2 AIRCRAFT Requirements and design possibilities (SAE PAPER 791097] 880-26646 Application of the Estimation-Before-Modeling Advanced computer program --- for future (EBM) system identification method to the high angle of attack/sideslip flight of the I-2c jet automation and system performance improvements trainer aircraft. Volume 2: Simulation study A80-26810 using T-2C wind tunnel model data Future large cargo aircraft technology [AD-A079923] 880-27269 880-19061 The changing horizons for technical progress. II Application of the Estimation-Before-Modeling A80-27270 (EBM) system identification method to the high The future development of air traffic as seen by angle of attack/sideslip flight of the T-2C jet airline companies trainer aircraft. Volume 3: Identification of T-2C aerodynamics stability and control A80-28487 characteristics from actual flight test data Technological aspects of future very large airplanes [AD-A079924] 880-28490 N80-19072 Major areas of research in aeronautics and air Application of the Estimation-Before-modeling traffic at the German Aerospace Research (EBH) system identification method to the high Establishment /DFVLR/ angle of attack/sideslip flight of the T-2C jet A80-28491 trainer aircraft. Volume 1: Executive summary Aeropropulsion in year 2000 [AD-8080025] 880-19073 (NASA-T8-81416) T-63 ENGINE 1180-18043 Measuring technological change in jet fighter Laser anemometer measurements at the exit of a T63 aircraft combustor (AD-A077393] A80-27737 880-19084 TACAN Air Force Flight Dynamics Laboratory fiscal year 1981. Technical objective document Fighter options for tactical air defense, [AD-A078973] [SAE PAPER 7911081 A80-26650 880-20020 TAIL ASSEMBLIES TECHNOLOGY ASSESSMENT Breaking V/STOL free of Catch 22 --- technology Wind tunnel and flight test drag comparisons for a utilization and assessment guided projectile with cruciform tails [AIAR 80-0426] A80-26968 A80-26342 TAIL SURFACES AV-8B - A second generation V/STOI. [SAN PAPER 791070) 880-26633 Influence of the empennage on the effective thrust Multi rotor options for heavy lift of jet engine exhaust nozzles [SAE PAPER 791089] *80-26643 A80-27139 The Federal Aviation Administration navigation Thrust augmented spin recovery device program [NASA-CASE-LAR-1 1970-2) 880-18048 TAILLESS AIRCRAFT Avionics - The leading technology in flight A80-26819 Fundamentals of design. VI - Tailplanes, tailless and canard design guidance and air traffic control 880-281192 A80-27728 TANDEM ROTOR HELICOPTERS Continued study of NAVSTAR/GPS for general aviation [NASA-CR-159145) N80-18020 Low speed test of the aft inlet designed for a Composite components on commercial aircraft tandem fan V/ST0L nacelle [NASA-TM-80231] (RASA-CR-159752) 880-18042 880-18109 TANDEM WING AIRCRAFT Primary Adhesively Bonded Structure Technology (PABST). General material property data Prandtls biplane theory applied to canard and bonding airframes tandem aircraft (AD-A077891) 880-19268 A80-28852 TECHNOLOGY UTILIZATION TANKER AIRCRAFT Application of Nd:YAG optical communications The KC-135 - A successful multirole transport aircraft. technology for aircraft to satellite links [SAE PAPER 791093] 880-26797 880-26644 Coming civil transport aircraft with 'active' General aviation icing flight test control elements A80-27383 A80-28493 TARGET ACQUISITION TELEMETRY Experience from testing the Viggen electronic First experience with telemetry and real time data systems utilizing existing computer capacity reduction at Gates Learjet A80-27235 A80-27228
8-43
TELEVISION CAMERAS SUBJECT INDEX
BIDS - The right tool for small test jobs THRUST REVERSAL Miniature Integrated Data Systems for inflight Minimum time turns with thrust reversal --- using testing control theory A80-21230 [AD-A079851] NHO-19078 TELEVISION CAMERAS THRUST VECTOR CONTROL Aircraft program for target background, and sky Thrust vectoring to eliminate the vertical radiance measurements stabilizer --- to provide directional stability (AD-A076959] N80-18624 for f-ill aircraft while decreasing radar TEMPERATURE EFFECTS detectability Effect of temperature on surface noise [AD-A079852) N80-19077 A80-28419 THRUST-WRIGHT RATIO TERMINAL CONFIGURED VEHICLE PROGRAM Preliminary study of rIO thrust requirements for a Flight performance of the TCV B-737 airplane at V/STCL aircraft with lift plus lift/cruise Jorge Newberry Airport, Buenos Aires, Argentina propulsion using TRSB/MLS guidance (NASA-TM-81429] A80-19110 [NASA-TM-80223] N80-18021 THUNDEB S TORN S Terminal configured vehicle program: Test Lightning protection for aircraft facilities guide A80-27021 (NASA-SP-435] N80-18028 TILT ROTOR AIRCRAFT TERRAIN FOLLOWING AIRCRAFT Multi rotor options for heavy lift The Tornado all-weather high-speed low-level system [SAE PAPER 791089] A80-26643 A80-27379 TIME DIVISION MULTIPLE ACCESS TEST EQUIPMENT A .JTIDS performance model for the E-3A A low cost airborne data acquisition system V80-19825 A80-27231 TIME MEASUREMENT Control of particulate emissions from turbine Recovery system prelimiminary design. A engine test cells by cooling water injection simplified approach to determining staging, ( AD-A075947] N80-18587 timing and altitude requirements for fast Computer simulation model of the logistic support inflating parachutes system for electrical engineering test equipment [AD-A077548] N80-19041 N80-19560 TIME SHARING TEST FACILITIES A time-shared tionopulse approach to air/surface The simulation and modeling of jet plumes in wind radar ranging tunnel facilities A80-26791 [AIAA 80-0430) A80-26941 TIME SIGNALS Testing the F-18 at the U.S. Naval Air Test Center The Navstar Global Positioning System and time A80-27239 A80-25146 Major areas of research in aeronautics and air Applications of the spread-spectrum signals from traffic at the German Aerospace Research the NOVA satellites Establishment /DFVLR/ A80-25149 A80-28491 TITANIUM ALLOTS Terminal configured vehicle program: Test NAVAIR pushes SPF/DB for structures --- in naval facilities guide aircraft design and construction (NASA-SP-435] N80-18028 A80-24739 Crew station design facility feasibility study Consolidation of titanium powder to near net shapes [AD-A078134] N80-19064 [AD-A078039] N80-19239 Laser-Raman flow-field diagnostics of two large TOLERANCES (MECHANICS) hypersonic test facilities USAF damage tolerant design handbook: Guidelines [AD-A078289) N80-19135 for the analysis and design of damage tolerant TEST STANDS aircraft structures, revision A The practical aircraft hydraulic test stand [ AD-A078216] N80-19065 (SAE PAPER 791079) A80-26636 TOOLING THERMODYNAMIC EFFICIENCY Advanced manufacturing development of a composite Algorithm for calculating turbine cooling flow and empennage component for 1-1011 aircraft the resulting decrease in turbine efficiency (NASA-CR-162862] N80-18104 [NASA-TM-81453) N80-19863 TORSIONAL STRESS THIN WINGS Structural analysis of hollow blades: Torsional Numerical modeling of supersonic flow near a thin stress analysis of hollow fan blades for delta wing with discontinuous edge aircraft jet engines A80-27147 [NASA-TM-75718] N80-19111 THREE DIMENSIONAL FLOW TRACKING NETWORKS Computational aerodynamics on large computers Design and simulation of a C3 system for A80-27415 surveillance purpose Three-dimensional inviscid compressible rotational N80-l9821 flows Numerical results and comparison with TRACTION analytical solutions Evaluation of a high performance fixed-ratio A80-27745 traction drive Interaction of a two-dimensional strip boundary [NASA-TM-81425] N80-18404 layer with a three-dimensional transonic TRAILING EDGES swept-wing code Viscous flow in the region of a rounded trailing [NASA-TB-78640] N80-17988 edge Computer prediction of three-dimensional potential [AD-A078588] N80-19045 flow fields in which aircraft propellers TRAILING-EDGE FLAPS operate: Computer program description and users Unsteady effects with control surfaces manual measured in a wind tunnel [NASA-CR-162816] N80-17994 [AAAP-NT-79-01 ) N80-18049 Aerodynamic and acoustic investigations of axial TRAINING DEVICES flow fan and compressor blade rows, including Cost-effectiveness of flight simulators for three-dimensional effects military training [AD-A077712] N80-19116 N80-19830 THRUST AUGMENTATION TRAINING SIMULATORS method and apparatus for rapid thrust increases in A mission training simulator for the Nimrod MR ME a turbofan engine 2 and some aspects of the derivation and verification of its system models [NASA-CASE-LEW-12971-1 ) N80-18039 rhrust augmented spin recovery device N8O-19826 [ NASA-CASF-LAR-11970-2] N80-18048 TRAJECTORY ANALYSIS Aircraft store separation motion prediction via grid data trajectories [AIAA 80-0462] R80-26959
A-44
SUBJECT INDEX TURBINE ENGINES
Full scale visualization of the wing tip Vortices TRANSONIC WIND TUNNELS generated by a typical agricultural aircraft The National Transonic Facility - Status and (NASA-CE-162796] N80-17992 operational planning Analysis of fuel-conservative curved decelerating (AIAA 80-0415] A80-26930 approach trajectories for powered-lift and CTOL Automatic control of NASA Langley's 0.3-meter jet aircraft cryogenic test facility (NASA-TP-1650) 880-19022 [AIAA 80-0416] A80-26931 TRAJECTORY OPTIMIZATION A comparison of experimental and theoretical Concepts for generating optimum vertical flight turbulence reduction from screens, honeyccmb and profiles honeycomb-screen combinations (NASA-CE-159181] N80-18031 [AIAA 80-0433] A80-26943 Trajectories optimization in hypersonic flight Additional flow quality measurements in the [NASA-CR-162846] 880-19026 Langley Research Center 8-Foot Transonic TRANSFER FUNCTIONS Pressure Tunnel Digital computer solution of aircraft longitudinal [AIAA 80-0434] A80-26944 and lateral directional dynamic characteristics Selected wind tunnel testing developments at the (AD-A018672) 880-19068 Boeing Aerodynamics Laboratory TRANSIENT RESPONSE [AIAA 80-04583 A80-26958 Structural design of transport airplanes for The development of a self-streamlining flexible transient environments walled transonic test section A80-27898 [AIAA 80-0440] A80-26964 Evaluation of finite element formulations for Programs for the transonic wind tunnel data transient conduction forced-convection analysis processing installation. Part 7: Extended focal of heat transfer for active cooling of [AD-A073 1414] 880-18054 hypersonic airframe and engine structures A theoretical analysis of simulated transonic A80-28284 boundary layers in cryogenic-nitrogen wind tunnels Transient effects on a stalled airfoil in a [NASA-TP-1631] 880-19131 pulsating flow: Comparison with results from a Toward new transonic windtunnels similar airfoil undergoing horizontal shaking (AGARE-AG-240] 880-19137 during wind tunnel tests An investigation of the quality of the flow [AAAF-NT-79-13] 880-18003 generated by three types of wind tunnel (Ludwieg TRANSIT SATELLITES tube, Evans clean tunnel and injector driven Applications of the spread-spectrum signals from tunnel) the NOVA satellites N80-19138 A80-25149 Development of the cryogenic tunnel concept and TRANSITION FLOW application to the US National Transonic Facility Visualization of the laminar-turbulent transition N80-19139 in the flow over an airfoil using the smoke-wire The cryogenic wind tunnel: another option for the technique European Transonic Facility [AIAA 80-0421] A80-26935 N80-19140 TRANSMISSION EFFICIENCY TRANSPARENCE Error rate performance of M-ary DPSK systems in Aircraft transparency failure and logistical cost satellite/aircraft communications analysis: Supplemental study A80-25945 [AD-A075500] 880-18033 Assessment of HF communications reliability TRANSPORT AIRCRAFT N80-19377 Local ground noise generated by supersonic TRANSMISSIONS (MACHINE ELEMENTS) transport planes Evaluation of a high performance fixed-ratio A80-26206 traction drive Future multi-mission transport aircraft - [NASA-TN-81425] N80-18404 Requirements and design possibilities TRANSONIC FLOW [SAE PAPER 791097] A80-26646 Stationary movement of wings in the transonic regime Structural design of transport airplanes for Spanish thesis transient environments A80-27723 A80-27898 Transonic inlet flow calculations using a general MINITWIST: A shortened version of TWIST grid-generation scheme [LBF-TB-146] 880-18438 A80-27744 Propulsion and energetics panel Working Group 11 Flutter analysis of a NACA 64A006 airfoil in small on aircraft fire safety. Volume 2: Main report disturbance transonic flow [AGARD-AB-132-VOL-2] N80-19047 A80-28851 TRANSPORTATION ENERGY Class of shockfree airfoils producing the same The aerial relay system: An energy-efficient surface pressure solution to the airport congestion problem A80-28857 [NASA-TM-80208] 680-18011 Interaction of a two-dimensional strip boundary TURBINE BLADES layer with a three-dimensional transonic Pratt and Whitney innovations --- turbomachine swept-wing code blade casting and hot isostatic pressing of (NASA-TM-78640) N80-17988 turbine disks Data report for a test program to study transonic A80-25448 flow fields about wing-body/pylon/store Optimal twisting of blades in axial turbomachines combinations. Volume 1: Tunnel empty flow A80-27797 survey data, wing body force/moment/surface Investigation of the boundary layer behavior on pressure data, and pressure store turbine airfoils force/moment/surface pressure data [AD-A075501] N80-18044 [AD-A077182] 880-18001 Structural analysis of hollow blades: Torsional Data report for a test program to study transonic stress analysis of hollow fan blades for flow fields about wing-body/pylon/store aircraft jet engines combinations. Volume 2: Flow field survey data [NASA-TN-75718] 880-19111 for configurations 21 and 22 Novel ceramic turbine rotor concepts (AD-A077183] N80-18002 (AD-A078669] 880-19118 An investigation of F-16 nozzle-afterbody forces Investigation of fan blades shroud mechanical at transonic Mach numbers with emphasis on damping support system interference (AD-A078439] 880-19120 [AD-A078693] N80-18046 TURBINE ENGINES Unsteady effects with control surfaces Advanced infrared signature prediction program. measured in a wind tunnel Spectral calculation of radiation from a turbine (AAAF-NT-79-01J 880-18049 propulsion system as intercepted by an observer (SCORPION). Volume 3: Analysis [AD-A078436] N80-19124
A-'45
TURBINE EXHAUST NOZZLES SUBJECT INDEX
TURBINE EXHAUST NOZZLES TURBULENT FLOW An investigation of F-16 nozzle-afterbody forces Visualization of the laminar-turbulent transition at transonic Mach numbers with emphasis on in the flow over an airfoil using the smoke-wire support system interference technique [AD-11078693] 1180-18046 [AIAR 80-0421] A80-26935 TURBINES Evaluation of a new concept for reducing Flow measurements in a turbine scroll free-stream turbulence in wind tunnels A80-27738 [AIAA 80-0432] A80-26942 TURB OCO N PRES SONS Computational aerodynamics on large computers Basic studies of rotating stall in axial flow A80-27415 compressors Evaluation of an analysis for axisymmetric [AD-A077690] 1180-19115 internal flows in turbomachinery ducts Aerodynamic and acoustic investigations of axial A80-27742 flow fan and compressor blade rows, including TURBULENT WAKES three-dimensional effects High-resolution LDA measurements of Reynolds [AD-A077712] 880-19116 stress in boundary layers and wakes TURBOFAN AIRCRAFT [AIAR 80-0436] E80-26967 A mission training simulator for the Nimrod MR NK TURNING FLIGHT 2 and some aspects of the derivation and Fundamentals of design. V - Fin design for combat verification of its system models aircraft N80-19826 A80727725 TURBOFAN ENGINES Minimum time turns with thrust reversal -- using Air supply system approach for the Boeing Model control theory 767 Airplane [AD-A079851] 1180-19078 (SAE PAPER 791068] A80-26631 TWISTING Investigation of engine performance degradation of Optimal twisting of blades in axial turbomachines ri'33-P-7 engines A80-27797 A80-27233 TWO DIMENSIONAL BOUNDARY LAYER Method and apparatus for rapid thrust increases in Interaction of a two-dimensional strip boundary a turbofan engine layer with a three-dimensional transonic [NASA-CASE-LEW-12971-1] 1180-18039 swept-wing code Proceedings of the 7th Ann. Tr-Service Meeting [NASA-TM-78640] N80-17988 for Aircraft Engine Monitoring and Diagnostics TWO DIMENSIONAL FLOW conferences Straight-walled, two-dimensional diffusers - [AB-A076126] R80-18045 Transitory stall and peak pressure recovery Application of composite materials to turbofan A80-27746 engine fan exit guide vanes An experimental study of two-dimensional [NASA-TM-81432] N80-18106 supersonic jet impingement on a flat plate Novel ceramic turbine rotor concepts [AD-A076536] 1180-17996 [AD-A078669] 1180-19118 F UR B 0 FAN S The experimental modeling of unstalled supersonic U turbofan flutter OH-i HELICOPTER [AIRA 80-01454] A80-26963 V/SIOLAND avionics system flight-test data on a TURBOJET ENGINES UN-1H helicopter Control of particulate emissions from turbine [NASA-TM-78591] N80-18047 engine test cells by cooling water injection Navigation systems for approach and landing of [AD-A075947] 1180-18587 VTOL aircraft Contribution of photoelastic analysis to the study [NASA-CR-152335] 1180-19055 of turbo-engine components Preliminary Airworthiness Evaluation UN-ill [8871985] N80-19112 helicopter equipped with Multiple Target Evaluation of fuel character effects on J79 engine Electronic Warfare System (MULTEWS) combustion system [AD-A078476] 1180-19067 [AD-A078440] N80-19119 The fabrication and testing of prototype UN-i TURBONACHINERY aircraft windshields manufactured with a sheet Plow in primary, non-rotating passages in interlayer turbonachines; Proceedings of the Winter Annual [AD-A077711] 1180-19080 Meeting, New York, N.Y., December 2-7, 1979 ULTRAHIGH FREQUENCIES A80-27732 Present-day problems of air traffic control in Evaluation of an analysis for axisymmetric ground-to-air communications internal flows in turbornachinery ducts A80-26221 A80-27742 ULTRASONIC FLAW DETECTION Optimal twisting of blades in axial turbomachines Nondestructive evaluation of graphite composite A80-27797 aircraft structures Wind-turbine power improvement with modern airfoil A80-2689 1 sections and multiple-speed generators UNDERCARRIAGES [AIAA 80-0633] A80-28819 Undercarriage drag prediction methods TURBULENCE EFFECTS [ESDU-79015] 1180-19028 Evaluation of a new concept for reducing UNMANNED SPACECRAFT free-stream turbulence in wind tunnels Proceedings of the Association for Unmanned [AIAA 80-0932] A80-26942 Vehicle Systems AUVS 79: 6th Annual Convention A comparison of experimental and theoretical [AD-A077877] 1180-20018 turbulence reduction from screens, honeycomb and UNSTEADY FLOW honeycomb-screen combinations Application of unsteady airfoil theory to rctary [AIRA 80-0433] A80-26943 wings TURBULENT BOUNDARY LAYER A80-28856 Nigh-resolution IDA measurements of Reynolds UNSTEADY STATE stress in boundary layers and wakes Unsteady effects with control surfaces [AIAA 80-0436] A80-26967 measured in a wind tunnel Turbulent-boundary-layer excitation and response [AAAF-NT-79-01] N80-18049 thereto for a high-performance conical vehicle URETHANES reentry The fabrication and testing of prototype UN-i 1180-18229 aircraft windshields manufactured with a sheet A theoretical analysis of simulated transonic interlayer boundary layers in cryogenic-nitrogen wind tunnels [AD-A077111] 1180-19080 [NASA-TP-1631] 1180-19131 USER MANUALS (COMPUTER PROGRAMS) TURBULENT DIFFUSION General aviation airplane structural Local laminarization in turbulent diffusion flames crashworthiness programmer's manual A80-24819 [AD-A075737] N80-18008
A-46 SUBJECT INDEX VIDEO EQUIPMENT
USER REQUIREMENTS VENEZUELA Breaking V/ST0I. free of Catch 22 --- technology Aeropuerto de Caracas - An unusual new general utilization and assessment aviation facility near the city A80-26342 A80-27222 The C-135 - A successful wultirole transport VERBAL COMMUNICATION aircraft Structures in aeronautical phraseology: From (RAE PAPER 791093] A80-26644 English to Spanish Airbus family concept for the 1990s B80-19978 AB0-28489 VERTICAL TAKEOFF Preliminary study of VTO thrust requirements for a V/STOL aircraft with lift plus lift/cruise V propulsion V/STOL AIRCRAFT [NASA-TM-81429] 1180-19110 Breaking V/STOL free of Catch 22 --- technology VERTICAL TAKEOFF AIRCRAFT utilization and assessment Viscous flowfields induced by two- and A80-26342 three-dimensional lift jets in ground effect AV-8B - A second generation V/STOL [AD-A078782] 1180-18343 (SAE PAPER 791070] A80-26633 Navigation systems for approach and landing of Multi rotor options for heavy lift VIOL aircraft [SAE PAPER 791089) A80-26643 [NASA-CE-152335] 1180-19055 VSTOL test techniques utilizing laser tracking Development of VIOL flying qualities criteria for A80-27234 low speed and hover The changing horizons for technical progress. II [AD-A079911] N80-19085 A80-27270 Vorticity associated with multiple jets in a YAV-8B status report crossflov --- vertical takeoff aircraft A80-27381 (NASA-CE-162855) 1180-19454 Low speed test of the aft inlet designed for a VERY HIGH FREQUENCIES tandem fan V/STOL nacelle Present-day problems of air traffic control in [NASA-CR-159752] N80-18042 ground-to-air communications Proceedings of a Workshop on V/STOL Aircraft A80-26221 Aerodynamics, volume 2 --- conferences VERY HIGH FREQUENCY RADIO EQUIPMENT (AD-A078909] N80-19042 First experience with telemetry and real time data Proceedings of a Workshop on V/STOL Aircraft reduction at Gates Learjet Aerodynamics, volume 1 A80-27228 [AD-A079115] N80-19074 Buoyant module VHF antenna design for submerged Avionics logistics support including V/STOL, systems/aircraft communications LAMPS, and instrument repair 580-28254 [AD-A077460] N80-19087 VESTS Preliminary study of VTO thrust requirements for a Feasibility testing of a Body Inflatable Bladder V/STOL aircraft with lift plus lift/cruise (BIB) restraint device propulsion [AD-A078681] 1180-18013 [NASA-TM-81429] N80-19110 VIBRATION DAMPING Microprocessor control of low speed V/STOL flight A scientific approach to defeating helicopter (AD-A077661) N80-19129 vibration Predicting field of view requirements for VSTOL 580-25446 aircraft approach and landing Investigation of fan blades shroud mechanical N80-19 847 damping VANELESS DIFFUSERS [AD-A0781439] 1180-19120 Rotating stall in a vaneless diffuser of a Some recent measurements of structural dynamic centrifugal fan damping in aircraft structures A80-27734 1180-19576 Aerodynamic performance of a centrifugal Damping problems in acoustic fatigue compressor with vaned diffusers N80-19580 A80-27735 Viscoelastic damping in USA? applications VARIABLE CYCLE ENGINES B80-19582 Variable cycle engine multivariable control Damping effects in joints and experimental tests synthesis: Control structure definition on riveted specimens [AD-A078670] N80-19117 1180-19584 VARIABLE MASS SYSTEMS VIBRATION EFFECTS On the equations of notion about the mass centre Crack development in panels of a pressurized of the jet aircraft considered as variable mass fuselage under the combined effect of system pressurization-induced cyclic loads and A80-26 325 high-frequency vibrations VARIABLE SWEEP WINGS A80-26 195 Minimum-weight wing in the presence of lift VIBRATION ISOLATORS constraints Viscoelastic damping in USA? applications A80-27136 1180-19582 Induced drag and lift-drag ratio of swept wings at VIBRATION MEASUREMENT supersonic speeds Angular vibration measurement techniques A80-27175 airborne electro-optical package disturbances VEHICLE WHEELS 1180-18222 Improved tire/wheel concept --- pneumatic aircraft VIBRATION TESTS tire Dynamic Environmental Qualification Techniques [NASA-CASE-LAB-11695-2) N80-18402 AGAED-B-682] 1180-19090 VELOCITY DISTRIBUTION Application of MIL-STD-810C dynamic requirements Operational implications of some NACA/NASA rotary to USA? avionics procurements wing induced velocity studies 1180-19091 A80-27599 Civil aircraft equipment environment qualification Flow in primary, non-rotating passages in techniques turbomachines; Proceedings of the Winter Annual N80-19093 Meeting, New York, N.Y., December 2-7, 1979 VIDEO COMMUNICATION A80-27732 The duration of false alarms in surveillance radar Flow measurements in a turbine scroll A80-27902 A80-27738 VIDEO DATA VELOCITY MEASUREMENT Airborne video instrumentation/data reduction Air speed and attitude probe 580-27232 (NASA-CASE-FRC-11009-1] N80-18036 VIDEO EQUIPMENT Airborne video instrumentation/data reduction 580-27232
A-47
VISCOELASTIC DAMPING SUBJECT INDEX
VISCOELASTIC DAMPING Remarks on simulation. Objectives/areas of Viscoelastic damping in USAF applications use/possibilities/limitations: An overview N80-19582 N80-19812 VISCOUS PLOW WEAR TESTS Viscous flowfields induced by two- and Wear of seal materials used in aircraft propulsion three-dimensional lift jets in ground effect systems [AD-8078782] 880-18343 A80-28010 Viscous flow in the region of a rounded trailing WEATHER STATIONS edge Preliminary assessment of an automated system for [80-8078588) 880-19045 detecting present weather VISIBILITY [AD-A078031] 880-19706 Optical design of airport control tower cabs WEIGHT ANALYSIS A80-24746 Permanent magnet and superconducting generators in VISUAL FIELDS airborne, high power systems --- computer Predicting field of view requirements for VSTOL program to predict weight of the generators and aircraft approach and landing component systems N80-19847 [80-8078424] 880-18311 VISUAL PERCEPTION WRIGHT REDUCTION Development of a visual inspection technique A single-step method of optimizing statically (optical assessment of aircraft transparencies) indeterminate minimum-volume systems [AD-A079369) 880-19086 880-27135 VISUAL TASKS Minimum-weight wing in the presence of lift Optical design of airport control tower cabs constraints A80-24746 880-27136 VORTEX BREAKDOWN Calculation of minimum-weight and maximum-rigidity Exploratory investigation of the effects of vortex structures in the presence of design constraints bursting on the high angle-of-attack 880-27165 lateral-directional stability characteristics of Minimum-mass designs of stiffened highly-swept wings graphite/polyimide compression panels [8188 80-0463] 880-26960 A80-27992 VORTEX GENERATORS WIND (METEOROLOGY) Effects of forebody, wing and wing-body-LEX Development of aerodynamic disturbance test flowfields on high angle of attack aerodynamics procedures, volume 1: Executive summary Leading Edge extensions [P880-108145] N80-19991 [SAE PAPER 791082] 880-26638 WIND MEASUREMENT VORTEX SHEETS Helicopter remote wind sensor system description Yawed slender wings at snail angles of attack [80-8076153] 880-18024 880-26268 WIND TUNNEL APPARATUS VORTICES A system for measuring and recording wind-tunnel Development of test methods for scale model balance data simulation of aerial applications in the NASA 880-25221 Langley Vortex Facility On the historical development of apparatus and [8188 80-0427] 880-26939 techniques for smoke visualization of subsonic Three-dimensional inviscid compressible rotational and supersonic flows flows Numerical results and comparison with [8188 80-0420] 880-26934 analytical solutions Evaluation of a new concept for reducing A80-27745 free-stream turbulence in wind tunnels Rotary balance data for a typical single-engine [8188 80-0432) 880-26942 general aviation design for an angle-of-attack A comparison of experimental and theoretical range of 8 deg to 90 deg. 1: Low-wing model A turbulence reduction from screens, honeyccmb and fluid flow and vortices data for general honeycomb-screen combinations aviation aircraft to determine aerodynamic [8188 80-0433] 880-26943 characteristics for various designs Toward new transonic windtunn€ls [NASA-CR-3100] 880-19030 [AGARD-AG-240) N80-19137 VORTICITY Development of the cryogenic tunnel concept and Vorticity associated with multiple jets in a application to the US National Transonic Facility crossflow --- vertical takeoff aircraft B80-19139 [NASA-CR-162855] N80-19454 WIND TUNNEL DRIVES VULNERABILITY Measurements of the dynamic performance of the Evaluation of equipment vulnerability and main drive fan of the RAE 5 metre pressurised potential shock hazards --- carbon fibers low speed wind tunnel N80-19197 [8188 80-0456] 880-26956 An investigation of the quality of the flow generated by three types of wind tunnel (Ludwieg W tube, Evans clean tunnel and injector driven WALL PLOW tunnel) Straight-walled, two-dimensional diffusers - U80-19138 Transitory stall and peak pressure recovery WIND TUNNEL MODELS 880-27 746 Aerodynamic Testing Conference, 11th, Colorado WAR GAMES Springs, Cola., March 18-20, 1980, Technical Production Eagle and its potential Papers (SAE PAPER 791071] 880-26634 A80-26929 Air-to-air engagement simulation Experimental investigation of the 880-19834 interference-free flow field around a lifting WARNING SYSTEMS wing-body model to establish cross flow Theoretical limitations on collision avoidance characteristics for ventilated wind tunnel walls systems at low supersonic Mach numbers 880-26811 [AIAA 80-0444] 880-26948 WEAPON SYSTEMS Measurements of control stability characteristics Production Eagle and its potential of a wind-tunnel model using a transfer function [SAE PAPER 791071] A80-26634 method Reliability and maintainability design standards [8188 80-04573 A80-26957 from readiness-related goals --- for naval A new rig for flight mechanics studies in the aircraft weapon systems ONFRA Aerothermodynaiuic Test Center of Hodane ':SAE PAPER 791109] 880-26651 [AIAA 80-0464] 880-26961 Testing the F-18 at the U.S. Naval Air Test Center A system for the measurement of the attitude of A80-27239 wind tunnel models [8188 80-0465] 880-26962
A-48
SUBJECT INDEX WING LOADING
Application of the Estimation-Before-Bodeling Data report for a test program to study transonic (EBB) system identification method to the high flow fields about wing-body/pylon/store angle of attack/sideslip flight of the T-2C let combinations. Volume 2: Flow field survey data trainer aircraft. Volume 2: Simulation study for configurations 21 and 22 using T-2C wind tunnel model data (AD-A077183) N80-18002 [AD-A079.923] 880-19061 Programs for the transonic wind tunnel data Developing, mechanizing and testing of a digital processing installation. Part 7: Extended focal active flutter suppression system for a modified (AD-A073414] 880-18054 B-52 wind-tunnel model Aeroacoustic wind-tunnel tests of a light (NASA-CR-159155) 880-19566 twin-boom general-aviation airplane with free or WIND TUNNEL STABILITY TESTS shrouded-pusher propellers -- in the Langley Description of a new high-alpha, high-load, full-scale tunnel pitch-yaw dynamic stability test mechanism at AEDC [NASA-TB-80203] 880-19023 [AIAA 80-0451] A80-26952 Experimental investigation of a circulation WIND TUNNEL TESTS control aileron Unsteady pressure measurements on wing-store (AD-A078825] 880-19046 combinations in incompressible flow The cryogenic wind tunnel: another option for the A80-26269 European Transonic Facility Effects of forebody, wing and wing-body-LEX N80-19140 flowfields on high angle of attach aerodynamics WIND TUNNEL WALLS Leading Edge eltensions Experimental investigation of the (SAP PAPER 791082) A80-26638 interference-free flow field around a lifting Aerodynamic Testing Conference, 11th, Colorado wing-body model to establish cross flow Springs, Cob., March 18-20, 1980, Technical characteristics for ventilated wind tunnel walls Papers at low supersonic Bach numbers A80-26929 (AIAA 80-0444] A80-26948 The National Transonic Facility - Status and The development of a self-streamlining flexible operational planning walled transonic test section (AIAA 80-0415] A80-26930 (AIAA 80-0440] A80-26964 Automatic control of NASA Langleys 0.3-meter WIND TUNNELS cryogenic test facility Static pressure orifice system testing method and (AIAA 80-0416) A80-26931 apparatus Numerical simulation of the wind tunnel [NASA-CASE-LAR--12269-1] 880-18358 environment by a panel method Laser-Raman flow-field diagnostics of two large [AIAA 80-0419] A80-26933 hypersonic test facilities On the historical development of apparatus and [AD-A078289] 880-19135 techniques for smoke visualization of subsonic WINDOWS (APERTURES) and supersonic flows Aircraft transparency failure and logistical cost [AIAA 80-0420) A80-26934 analysis: Supplemental study Local skin friction and static pressure on a swept [AD-A075500] 880-18033 wing in flight WINDPOWER UTILIZATION (AINA 80-0423] A80-26937 New anproaches to sailing The simulation and modeling of jet plumes in wind A80-26344 tunnel facilities WINDPOWERED GENERATORS (AIAA 80-0430] A80-26941 Wind-turbine power improvement with modern airfcil Additional flow quality measurements in the sections and multiple-speed generators Langley Research Center 8-Foot Transonic (AIAA 80-0633] A80-28819 Pressure Tunnel WINDSHIELDS [AIAA 80-0434] A80-26944 Aircraft transparency failure and logistical cost New requirements, test techniques, and development analysis: Supplemental study methods for high fidelity flight simulation of [AD-A075500] 880-18033 commercial transports The fabrication and testing of prototype Un-i (AIAA 80-0445] A80-26949 aircraft windshields manufactured with a sheet Selected wind tunnel testing developments at the interlayer Boeing Aerodynamics Laboratory (AD-A077711) 880-19080 [AIAA 80-0458] A80-26958 Evaluation of aircraft windshield materials in a A new rig for flight mechanics studies in the simulated supersonic flight environment ONERA Aerothermodynainic Test Center of Bodane (AD-A078673] 880-19082 [AIAA 80-0464] A80-26961 Development of a visual inspection technique A system for the measurement of the attitude of (optical assessment of aircraft transparencies) wind tunnel models [AD-A079369] 880-19086 [AIAA 80-0465] A80-26962 WING FLOW BETHOD TESTS The development of a self-streamlining flexible Visualization of the laminar-turbulent transition walled transonic test section in the flow over an airfoil using the smoke-wire [AIAA 80-0440] A80-26964 technique Wind tunnel and flight test drag comparisons for a (AIAA 80-0421] 880-26935 guided projectile with cruciform tails Development of test methods for scale model (AIAA 80-0426] A80-26968 simulation of aerial applications in the NASA Operational implications of some NACA/NASA rotary Langley Vortex Facility wing induced velocity studies [8188 80-0427] 880-26939 A80-27599 The development of a self-streamlining flexible The aerodynamics of future transport aircraft and walled transonic test section the role of the wind tunnel during development (8188 80-0440] 880-26964 A80-28494 The aerodynamics of future transport aircraft and Wind-tunnel/flight correlation study of the role of the wind tunnel during development aerodynamic characteristics of a large flexible 880-284914 supersonic cruise airplane (XB-70-1) . 3: A Dynamic stall on oscillating airfoils in comparison between characteristics predicted oscillating free-streams from wind-tunnel measurements and those measured N80-17983 in flight WING LOADING [NASA-TP-1516] N80-17986 Pressure distribution in rectangular wing /blade/ Comparison of aerodynamic coefficients obtained sections during curvilinear notion in an from theoretical calculations wind tunnel tests incompressible medium and flight tests data reduction for the alpha 880-27157 jet aircraft Effect of sweep and aspect ratio on the [NASA-TB-75237] N80-17991 longitudinal aerodynamics of a spanboader wing in- and out-of-ground effect --- conducted in Langley V/STOL wind tunnel [NASA-Tli-80199] N80-17993
WING OSCILLATIONS SUBJECT INDEX
Estimation of the endurance of civil aircraft wing structures --- life estimate method for wing loading on general aviation aircraft (FSDU-79024) N80-19060 WING OSCILLATIONS Stationary movement of wings in the transonic regime Spanish thesis A80-27723 Application of unsteady airfoil theory to rotary wings A80-28856 WING PANELS Calculation of minimum-weight and maximum-rigidity structures in the presence of design constraints A80-27165 Minimum-mass designs of stiffened graphite/polyimide compression panels A80-27992 WING PROFILES A study of nonadiatatic boundary-layer stabilization time in a cryogenic tunnel for typical wing and fuselage models [AIAA 80-0417] A80-26932 The influence of wing, fuselage and tail design on rotational flow aerodynamics data obtained beyond maximum lift with general aviation configurations [ATAA 80-0455] A80-26955 WING ROOTS NINITWIST: A shortened version of TWIST [LBF-TB-146] N80-18438 WING TIP VORTICES Full scale visualization of the wing tip vortices generated by a typical agricultural aircraft [NASA-CR-162796] N80-17992 WING-FUSELAGE STORES Unsteady pressure measurements on wing-store combinations in incompressible flow A80-26269 WINGS Hysteresis of aerodynamic characteristics --- for wing models and segmented conical bodies of revolution A80-27167 Design and test of a boron - aluminum high temperature wing [AD-A075814] N80-18034 X I RAT INSPECTION Transparent engines at Rolls-Royce - The application of high energy X-ray technology to gas turbine development A80-25447 XV-15 AIRCRAFT Synthesis of rotor test data for real-time simulation [NASA-CR-152311] N80-18029 A hingeless rotor XV-15 design integration feasibility study. volume 1: Engineering design studies [NASA-CR-152310] N80-18030 V TAG LASERS Application of Nd:YAG optical communications technology for aircraft to satellite links A80-26797 YAWING MOMENTS Description of a new high-alpha, high-load, pitch-yaw dynamic stability test mechanism at AEDC [AIAA 80-0451] A80-26952
A-50 PERSONAL AUTHOR INDEX
AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 123) JUNE 1980
Typical Personal Author Index Listing
NAUTHOR *80Th, K. K._ Studies of the acoustic transmission ALMQUIST, K. characteristics of coaxial nozzles with inverted Avionics evaluation program: Simulation models I velocity profiles, volume 1 for the effectiveness analysis of avionics I(NASA-CF-159698) 880-11870 880-19838 ALTMAN, J. N. Advanced composites serviceability program - Status review I NA 7 A80-26890 NUMBER I ACCESSION ANIRIANTS, G. A. NUMBER Analytical determination of the influence of elasticity and mass distribution on the aerodynamic characteristics of an aircraft in Listings in this index are arranged alphabetically by personal author. The title quasi-steady motion of the document provides the user with a brief description of the subject matter. A80-27132 ANDERSON, N. B. The report number helps to indicate the type of document cited (e.g., NASA Evaluation of a high performance fixed-ratio report, translation. NASA contractor report). The accession number is located traction drive beneath and to the right of the title. e.g. N80-1 1870. Under any one author's [NASA-TM-81425] 880-18404 name the accession numbers are arranged in sequence with the fAA accession ANDERSON, 0. L. numbers appearing first. Evaluation of an analysis for axisymmetric internal flows in turbomachinery ducts £8 0-2774 2 ANDEUS, N. S. A Aircraft program for target background, and sky ABBOTT, T. S. radiance measurements Early flight test experience with cockpit [AD-A076959] ' 880-18624 Displayed Traffic Information (CDII) APPICE, V. B., 38. (NASA-TM-80221) 880-18037 Wind tunnel and flight test drag comparisons for a ADAMS, B. J. guided projectile with cruciform tails Airborne radar approach system flight test [NINA 80-0426] A80-26968 experiment ARNISINAD, N. F. (AD-A077900] 880-19054 Design considerations for attaining 250-knot test ADCOCK, J. B. velocities at the aircraft landing dynamics A theoretical analysis of simulated transonic facility boundary layers in cryogenic-nitrogen wind tunnels NASA-TM-80222] N80-19132 [NASA-TP-1631] 880-19131 ARMOUR, T. N. ADKINS, P. D. Modelling of aircraft responses to EBB CL-600 Challenger A80-27778 A80-27387 ANNAlS, B. B. AGARWAL, B. K. wind-tunnel/flight correlation study of Viscous flowfields induced by two- and aerodynamic characteristics of a large flexible three-dimensional lift jets in ground effect supersonic cruise airplane (18-70-1). 3: A [AD-A078782] N80-18343 comparison between characteristics predicted AGNEN, J. from wind-tunnel measurements and those measured MCAIE design philosophy for fighter aircraft in flight departure and spin resistance [NASA-TP-1516] 880-17986 (SAE PAPER 791081] A80-26637 ASBBAUGH, J. AGRELL, J. Workshop on Aircraft Surface Representation fat The simulation and modeling of jet plumes in wind Aerodynamic Computation tunnel facilities [NASA-TM-81170] 880-19025 [AlAN 80-0430] A80-26941 ASB3A2E, J. AILMAN, C. N. Straight-walled, two-dimensional diffusers - Turbulent-boundary-layer excitation and response Transitory stall and peak pressure recovery thereto for a high-performance conical vehicle *80-27746 880-18229 ASUKENAS, I. L. AKITA, N. N. Development of VTOL flying qualities criteria for Shipboard antenna tests for GPS low speed and hover A80-25144 (AD-A079911) 880-19085 ALBERTS, B. D. Continued study of RAVSTAR/GPS for general aviation [NASA-CR-159145] 880-18020 B ALEXANDER, B. B. BACH, B. E., 38. A hingeless rotor XV-15 design integration Aircraft motion analysis using limited flight and feasibility study. Volume 1: Engineering radar data design studies A80-27241 [NASA-CB-152310J 880-18030 BAHR, D. N. ALLEN, J. A. Evaluation of fuel character effects on 379 engine Preliminary study of VTO thrust requirements for a combustion system V/STOL aircraft with lift plus lift/cruise (AD-A078440] 880-19119 propulsion BAILEY, P. R. [NASA-TN-81429] 880-19110 Computational aerodynamics on large computers ALMEIDA, P. X. A80-27415 Structures in aeronautical phraseology: From English to Spanish N80-19978
B-i
BAKER, F. A. PERSONAL AUTHOR INDEX
BAKER, P. A. The potential for damage from the accidental V/STOLAND avionics system flight-test data on a release of conductive carbon fibers from burning OH-1H helicopter composites [NASA-TN-78591] N80-18047 (NASA-TM-80213) N80-18108 BAKER, C. J. Release of carbon fibers from burning composites Air speed and attitude probe B80-19195 (NASA-CASE-FEC-11009-1] N80-18036 BNRGNANW, B. N. BALAKEISONA, S. New materials and methods for airframe construction Automatic control of NASA Langleys 0.3-meter 18 0-28495 cryogenic test facility BERKOPEC, P. D. [AIAA 80-0416] A80-26931 Liquid metal slip ring BALLARD, J. D. [NASA-CASE-LEW-12277-3] N80-18300 Measurements of control stability characteristics BERRIEB, B. L. of a wind-tunnel model using a transfer function Thrust augmented spin recovery device method (NASA-CASE-LAE-11970-2) W80-18048 [AIAA 80-0457] A80-26957 BERTRLRUD, A. BALLRAUS, N. F. Local skin friction and static pressure on a swept Computational aerodynamics on large computers wing in flight A80-27415 (AIAA 80-0423] A80-26937 BALSE, D. T. BEST, J. V. NADC ABC rotor maps Aircraft store separation motion prediction via [AD-A078802] N80-19083 grid data trajectories BANICHUK, N. V. [AIAA 80-0462] A80-26859 Minimum-weight wing in the presence. of lift BICKER, K. J. constraints From tape measure to computer tape A80-27136 A80-27243 BANNISTER, J. D. BIBRLE, N., JR. The role of the aircraft model in avionic systems The influence of wing, fuselage and tail design cm simulation rotational flow aerodynamics data obtained N80-19837 beyond maximum lift with general aviation BARBER, V. J. configurations Evaluation of an analysis for axisymnetric [AIAA 80-0455] A80-26955 internal flows in turbomachinery ducts BILL, R. C. A80-27742 Wear of seal materials used in aircraft propulsion BARON, S. systems Closed loop models for analyzing engineering A80-28010 requirements for simulators Gas path seal (NASA-CR-2965] N80-19063 [ NASA-CASE-NPO-12131-3] 880-18400 BARRETT, J. N. BILLINGSLEY, J. P.P. Simulation of a night vision system for low level Aircraft store separation motion prediction via helicopter operations grid data trajectories N80-19832 [AIAA 80-0462] A80-26959 BASTIANSEN, E. BILODEAU, A. A. Simulation defines alternatives for Copenhagen The application of reliability improvement terminal expansion warranty to dynamic systems A80-27221 [AD-A075520] 880-18419 BATILL, S. N. BIRIUK, V. I. Visualization of the laminar-turbulent transition Minimum-weight wing in the presence of lift in the flow over an airfoil using the smoke-wire constraints technique A80-27136 [ATAA 80-0421] A80-26935 BLACKERB!, W. I. BAT!, D. Aerodynamic investigation of C-141 leading edge The effect of viewing time, time to encounter, and modification for cruise drag reduction, vclume 2 practice on perception of aircraft separation on (2D-A077688) N80-19081 a cockpit display of traffic information RLACKNELL, 3. A., JR. [NASA-TN-81173] N80-18038 The aercdynamic design of an advanced rotor airfoil BAURBICK, B. J. [NASA-CB-2961] N80-17989 Fiber optic sensors for measuring angular position BLAKE, N. A. and rotational speed Advanced computer program [NASA-TM-81454] N80-18368 A80-26810 BAONGARDNEE, P. S. The Federal Aviation Administration navigation Fiberglass rotor produced program A80-24740 A80-26e19 BADEGARTNER, S. J. BOARDEAN, K. N. New remotely piloted vehicle launch and recovery The A-7 head-up display reliability programme concepts: Computer program listings N80-19539 [AD-A076611] N80-18035 B000S, B. C. New remotely piloted vehicle launch and recovery The history of static test and Air Force concepts. Volume 1: Analysis, preliminary structures testing design and performance/cost trade studies [AD-A077029] N80-19136 [AD-A077475] N80-19066 BOGHANI, A. B. BAVUSO, S. J. Analysis of trunk flutter in an air cushion Trends in reliability modeling technology for landing system fault tolerant systems [AD-A079008] N80-19075 N80-19534 BONNET, J.-L. BECK. C. .3., JR. Laminar separation bubble with transition /theory Incandescent lamp life under random vibration and experiment/ N80-18221 (ONBEA, TV NO. 1980-20] A80-27203 BEGER, R. BOBOWSKI, N. A. Primary Adhesively Bonded Structure Technology Have Bounce (PABST) . General material property data A80-27382 [AS-A077891] N80-19268 BORRI, N. BELL, V. L. Damping problems in acoustic fatigue The potential for damage from the accidental N80-19 580 release of conductive carbon fibers from BOTTERI, B. P. aircraft composites Propulsion and energetics panel Working Group 11 A80-27596 on aircraft fire safety. Volume 2: Main report [AGAEC-AR-132-VOL-2] N80-19047
B-2
PERSONAL AUTHOR INDEX CARLSOB, D. N.
BOUNDS, J. B. BROWN, H. A. NSSC-2 operating system design requirements Prelimiliary assessment of an automated system for specification detecting present weather [NASA-CR-161396] N80-19861 [AD-A078031] 880-19706 BOUTBORS, E. BROWN, K. A. Simulation for integration with dynamic tests of The integrated management of reliability and the logical elements of principal onboard maintainability in procurement computers N80-19 558 N80-19842 BROWN, S. S. BOWER, V. N. Aircraft transparency failure and logistical cost Viscous flowfields induced by two- and analysis: Supplemental study three-dimensional lift jets in ground effect [AD-A075500] N80-18033 [AD-A078782] N80-18343 BRONNLEE, J. A. BOWMAN, J. S., JR. Full scale visualization of the wing tip vortices The influence of wing, fuselage and tail design on generated by a typical agricultural aircraft rotational flow aerodynamics data obtained (NASA-CR- 162796] 880-17992 beyond maximum lift with general aviation BRUN, J. configurations Reliability of high-brightness CRTs for airborne (AIAR 80-0455] A80-26955 displays SHADER, S. N80-19543 Vorticity associated with multiple jets in a BRUNE, J. F. crossflow Modern HF communications for low flying aircraft [NASA-CR-162855] N80-19454 880-19375 BRADLEY, N. F. BRYANT, D. J. Source book on materials for elevated-temperature Report on the task force on aircraft separation applications: A comprehensive collection of assurance, appendices outstanding articles from the periodical and [AD-A077713] 880-18017 reference literature BUCHANAN, T. D. A80-27 622 Description of a new high-alpha, high-load, BRASLAYSKIX, D. A. pitch-yaw dynamic stability test mechanism at AEDC Aircraft instruments and automatic systems /3rd [AIAA 80-0451] A80-26952 revised and enlarged edition/ BUDDE, H. V. A80-26350 Optical design of airport control tower cabs BRAUN, B. A80-24 746 Air-to-air engagement simulation BUISSON, D. N80-19834 New possibilities offered by a radio-inertial RERUN!, K. N. hybrid guidance system digital simulation study Microprocessor controlled ejection seat N80-19836 [AD-A077479] N80-19049 BURDSALL, N. A. BREENAN, J. H. Core compressor exit stage study. 1: Aerodynamic Aspects of flight test instrumentation and mechanical design N80-19098 (NASA-CR-159714] 880-19113 Analysis of aircraft performance stability and BURGESS, B. control measures The role of HP in air-ground communications: An N80-19099 overview BRRIEN, T. 880-19373 Nultipath analysis of ILS glide path BURNS, B. H. A. 880-19354 Fundamentals of design. V - Pin design for combat BREUSOVA, H. A. aircraft Induced drag and lift-drag ratio of swept wings at A80-27725 supersonic speeds Fundamentals of design. VI - Tailplanes, tailless A80-27175 and canard design BRIDGES, P. D. A80-27728 Full scale visualization of the wing tip vortices BURT, H. H. generated by a typical agricultural aircraft Aircraft store separation notion prediction via [NASA-CR-162796] N80-17992 grid data trajectories BRILEY, N. B. (AIAA 80-0462] A80-26959 Viscous flow in the region of a rounded trailing BUTTERFIELD, A. J. edge Surveys of facilities for the potential effects (AD-A078588) N80-19045 from the fallout of airborne graphite fibers BRISTER, J. G. 880-19199 New remotely piloted vehicle launch and recovery concepts: Computer program listings [AD-A076611] N80-18035 New remotely piloted vehicle launch and recovery CALERO, F. J. S. concepts. Volume 1: Analysis, preliminary Stationary movement of wings in the transonic regime design and performance/cost trade studies A80-27723 [AD-A077475] N80-19066 CALZADILLA, A. BROCKHURS?, F. C. Aeropuerto de Caracas - An unusual new general Permanent magnet and superconducting generators in aviation facility near the city airborne, high power systems A80-27222 (AD-A078424] N80-18311 CANAL, E., JR. BROOKS, C. V., JR. Core compressor exit stage study. 1: Aerodynamic Additional flow quality measurements in the and mechanical design Langley Research Center 8-Foot Transonic (NASA-CB-159714] 880-19113 Pressure Tunnel CARD, N. P. [AIAA 80-0434] A80-26944 Graphite-epoxy panel compression strength BROOKS, J. D. reduction due to local impact A comparison of experimental and theoretical A80-27598 turbulence redaction from screens, honeycomb and CAREL, 0. honeycomb-screen combinations The introduction of new systems in international [AIAA 80-0433] A80-26943 civil aviation Additional flow quality measurements in the A80-28383 Langley Research Center 8-Foot Transonic CARLSON, D. N. Pressure Tunnel Tactical navigation system testing (AIAA 80-0434] A80-269144 A80-27237
B-3 C&RLSON, E. P. PERSONAL AUTHOR INDEX
CARLSON, E. P. CEOPRA, I. New requirements, test techniques, and development Measurements of control stability characteristics methods for high fidelity flight simulation of of a wind-tunnel model using a transfer function commercial transports method [8188 80-0445] 880-26949 [AIAA 80-0457] 880-26957 CARMAN, P. D. CR00, P. C. Optical design of airport control tower cabs Significance of large scatter of composite 880-24746 properties to aircraft reliability CARTER, B. S. [AD-A077804] 880-19062 Single rotor options for heavy lift and potential CHOVIT, A. R. of multi lift Data reduction and analysis of graphite fiber (SAE PAPER 791087] 880-26642 release experiments CARTER, J. E. [NASA-CB-159032] 880-19048 Interaction of a two-dimensional strip boundary CHRISTENSEN, L. S. layer with a three-dimensional transonic Fog dispersion swept-wing code [NASA-CE-3255) 880-19703 (NASA-TM-78640] 880-17988 CHEISTOPHE, J. CASSEL, 1. A. A new rig for flight mechanics studies in the Hypersonic interference flow flight experiment ONERA Aerothermodynamic Test Center of Nodane design [AIAA 80-0464] 880-26961 (AD-A078861] 880-190144 The cryogenic wind tunnel: another option for the CASTELLANI, A. European Transonic Facility Damping effects in joints and experimental tests N80-19140 on riveted specimens CABS, A. 880-19584 Design considerations for attaining 250-knot test CASTILLO, J. P. velocities at the aircraft landing dynamics Computational techniques for EMP interaction facility 880-27777 (NASA-TM-80222) N80-19132 CATANI, G. CLARK, L. Design of a simulator for studying the helicopter Flight performance of the TCV 8-737 airplane at - SDVEH Jorge Newberry Airport, Buenos Aires, Argentina 880-19829 using TRSB/MLS guidance CAUGHET, D. A. [NASA-TM-80223] 880-18021 Transonic inlet flow calculations using a general CLEMENT, V. P. grid-generation scheme Predicting field of view requirements for VSTOL 880-27744 aircraft approach and landing CAVALLINI, G. N80-19847 Damping problems in acoustic fatigue CLUB, A. N80-19580 Methodology for target discrimination CAVES, N. E. 880-273147 A consideration of general aviation in the United COAST, J. O Kingdom The fabrication and testing of prototype Un-i [TT-7902] 880-17982 aircraft windshields manufactured with a sheet CHAIT, A. interlayer Investigation of the boundary layer behavior on [80-8077711] N80-19080 turbine airfoils COHEN, I. K. [AD-A075501] 880-18044 Estimating the time required to transition CHANOHOK, V. K. aircraft fleets to new scheduled maintenance Consolidation of titanium powder to near net shapes intervals [AD-A078039] 880-19239 [AD-A078606] 880-19027 CHAPLIN, J. C. COLASORDO, C. Problems of older jet aeroplanes - A regulatory Three-dimensional j nviscid compressible rotational authority view flows Numerical results and comparison with A80-25445 analytical solutions CHAPRAN, J. N., JR. A80-27745 An analysis and synthesis of engine condition CONNER, D. V. monitoring systems Multirole cargo aircraft options and configurations [AD-A077531] 880-19122 (SAE PAPER 791096] 880-26645 CHARIOT, J. C. CONNOLLY, P. E. Methods used for discerning the reliability of The impact of GPS on CV mission effectiveness military aircraft radar 880-25165 N80-19532 COOK, N. CHARON, V. Induced effects of lightning on an all composite Wind tunnel and free flight model identification aircraft experience 880-27783 880-19103 COOPER, D. E. CHEW, L. T. Single rotor options for heavy lift and potential Transonic inlet flow calculations using a general of multi lift grid-generation scheme (SAE PAPER 791087] 880-26642 880-27744 COOPER, T. D. CHEREMUKRIN, C. A. Fatigue in machines and structures - Aircraft Local ground noise generated by supersonic 880-26731 transport planes CORLET, R. C. A80-26206 Method and apparatus for rapid thrust increases in CHERVETSOV, V. V. a turbofan engine Airport radio navigation systems [NASA-CASE-LEN- 1297 1-1] 880-18039 A80-27716 COELISS, L. D. CHIN, V. C. V/SIOLAND avionics system flight-test data on a Class of shockfree airfoils producing the same OH-1H helicopter surface pressure [NASA-TM-78591] 880-18047 880-28857 CORNELL, N. E. CHINAPPI, U. Assessment of the risk due to release of carbon Modeling and flight simulation of an active fiber in civil aircraft accidents, phase 2 configured aircraft under M.L.S. guidance 880-19200 N80-19845 CORNETT, J. L Method and apparatus for rapid thrust increases in a turbofan engine [NASA-CASE-LEW-12971-1 ] 880-18039
B-4 PERSONAL AUTHOR INDEX DULEHA, C. S.
CORONA, P. DR SALABERBY, B. Experimental procedure to determine limits of ISM The laser gyro and its application to an interference affecting navigational ItS equipment helicopter navigation system A80-27760 A80-28221 COTTA, B. DECESABI, R. J. Increasing aircraft efficiency through laminar Buoyant module VHF antenna design for submerged flow control systems/aircraft communications A80-24899 A80-28254 COULTER, S. N. DEPRANCES, A. J. Description of a new high-alpha, high-load, Development of a visual inspection technique pitch-yaw dynamic stability test mechanism at AEDC (optical assessment of aircraft transparencies) [AIAA 80-0451] A80-26952 (AD-A079369] N80-19086 COUSTEIX, J. DEHOPP, R. L. Laminar separation bubble with transition /theory Variable cycle engine multivariable control and experiment/ synthesis: Control structure definition (ONERA, IP NO. 1980-20] A80-27203 [AD-A078670] 880-19117 COY, N. H. DEITCHEAN, N. B. Investigation of the boundary layer behavior on VSTOL test techniques utilizing laser tracking turbine airfoils A80-27234 [AD-A075501] 880-18044 DEJONGE, J. B. CRENA, L. B. HINIIWIST: A shortened version of TWIST Damping effects in joints and experimental tests [LBF-TB-146) N80-18438 on riveted specimens DENENCHENOK, V. P. 880-19584 Theory of by-pass ducted-fan engines CRISALLI, A. J. A80-26349 Data report for a test program to study transonic DENETBI, E. P. flow fields about wing-body/pylon/store Study of research and development requirements of combinations. Volume 1: Tunnel empty flow small gas-turbine combustors survey data, wing body force/moment/surface [NASA-CB-159796] 880-18040 pressure data, and pressure store DENSPORD, N. C. force/moment/surface pressure data NIDS - The right tool for small test jobs [AD-A077182] 880-18001 A8O-27230 Data report for a test program to study transonic DESOPPER, A. flow fields about wing-body/pylon/store Unsteady effects with control surfaces combinations. Volume 2: Flow field survey data [AAAP-NT-79-01] 880-18049 for configurations 21 and 22 DETORE, J. [AD-A077183) 880-18002 Multi rotor options for heavy lift CRONAN, B. (SAE PAPER 791089) A80-26643 Significance of large scatter of composite DEXTER, H. B. properties to aircraft reliability Composite components on commercial aircraft [AD-A077804] 880-19062 A80-27597 CROSS, E. .7., .IB. Composite components on commercial aircraft Pull scale visualization of the wing tip vortices [NASA-TN-80231] 880-18109 generated by a typical agricultural aircraft DEYST, J. J. (NASA-CP-162796) N80-17992 A fault tolerant architecture approach to avionics CROWDER, J. P. reliability improvement Selected wind tunnel testing developments ai the 880-19533 Boeing Aerodynamics Laboratory DICKSON, D. H. (AIAA 80-0458) A80-26958 Helicopter remote wind sensor system description CRU!, P. B. [AD-8076153] 880-18024 The application of reliability improvement DIEKNANN, V. L. warranty to dynamic systems Preliminary Airworthiness Evaluation OH-ill (AD-A075520] 880-18419 helicopter equipped with Multiple Target CULOTTA, B. P. Electronic Warfare System (NULTEWS) Static pressure orifice system testing method and [AD-A078476] 880-19067 apparatus DIXON, H. H. [NASA-CASE-LAR-12269-1) 880-18358 Nonelectronic aspects of avionic system reliability CDL?, D. B. 880-19535 Liquid metal slip ring DOLLOPP, J. T. [NASA-CASE-LEW-12277-3] N80-18300 The Navstar Global Positioning System and time A80-25146 DBETPOS, N. C. D Using a language developed for aircraft simulators DABLEN, C. 880-1983 1 Swedish EHP research DRIFTN!ER, R. T. A80-27766 An experimental study of two-dimensional DANESI, A. supersonic jet impingement on a flat plate Modeling and flight simulation of an active [AD-A076536] 880-17996 configured aircraft under M.L.S. guidance DROUILHET, P. B., JR. 880- 19845 Electronic flight rules /EFR/ - A concept for DASH, R. enhanced freedom of airspace Strouhal number influence on flight effects on jet A80-28382 noise radiated from convecting quadrupoles DBOZHININ, L. N. A80-28418 Theory of by-pass ducted-fan engines DAUGHERTY, J. C. A80-26349 Wind-tunnel/flight correlation study of DUCKWORTH, G. aerodynamic characteristics of a large flexible The duration of false alarms in surveillance radar supersonic cruise airplane (XB-70-1). 3: A A80-27902 comparison between characteristics predicted DUGAN, D. C. from wind-tunnel measurements and those measured V/STOLAND avionics system flight-test data on a in flight OH-ill helicopter (NASA-TP-1516) 880-17986 NASA-TN-78591] 880-18047 DAVIS, N. N. DULBBA, C. S. Interaction of a two-dimensional strip boundary Easy ACLS dynamic analysis, volume 2. Part 2: layer with a three-dimensional transonic Component computer programs swept-wing code [AD-A079803] 880-19076 (NASA-TM-78640] 880-17988
8-5
DUNCAN, T. C. PERSONAL AUTHOR INDEX
DUNCAN, T. C. FIKSEL, J. Hypersonic interference flow flight experiment Assessment of risk due to the use of carbon fiber design composites in commercial and general aviation [AD-A078861] N80-19044 N80-19201 DUNN, J. C. FILZ, J. Tactical navigation system testing Avionics - The leading technology in flight A80-27237 guidance and air traffic control DUNN, J. L. A80-28492 Testing the F-18 at the U.S. Naval Air Test Center FISH, B. B. A80-27 239 Analysis of trunk flutter in an air cushion DUNPH!, N. A. landing system The application of reliability improvement (AD-A079008] N80-19075 warranty to dynamic systems FITZGERALD, A. L. [AD-A075520] N80-18419 Design considerations for attaining 250-knot test DETER, j P. velocities at the aircraft landing dynamics First experience with telemetry and real time data facility reduction at Gates Learjet [14ASA-TN-80222] N80-19132 A80-27228 FLEETER, S. The experimental modeling of unstalled supersonic turbofanflutter E [AIAA 80-0454] A80-26963 EBERT, H. FLEEING, D. P. The use of computer systems in air traffic control Damping in tapered annular seals for an A80-27223 incompressible fluid ECKENT, N. T. [NASA-TP-1646] N80-19495 An experimental investigation of two large annular FORD, T. E. diffusers with swirling and distorted inflow Flight recording in the UK. I - Evolution [NASA-TP-1628] N80-17984 A80-27751 ECONOMU, N. A. FORESTER, C. K. Air speed and attitude probe Numerical prediction of compressible potential [NASA-CASE-FRC-11009-1) N80-18036 flow for arbitrary geometries HGGLESTOE, B. G. A80-27743 Development of a visual inspection technique FORSYTH, P. J. E. (optical assessment of aircraft transparencies) The fatigue performance of service aircraft and [AD-A079369] N80-19086 the relevance of laboratory data ELBER, V. AR 0-2778 9 Dissemination, resuspension, and filtration of FRALEY, T. 0. carbon fibers Method and apparatus for rapid thrust increases in N80-19 196 a turbofan engine ELPEBINA, A. S. (NASA-CASE-LEW-12971-1] N80-18039 Theory of by-pass ducted-fan engines FRANK, L. H. A80-26349 Comparison of specifications for Head-Op Displays ENGLE, H. N., JR. in the Navy A-4N, A-7E, AT-BA, and P-14A aircraft USA? damage tolerant design handbook: Guidelines [AD-A080047] N80-19106 for the analysis and design of damage tolerant FRARKE, H. N. aircraft structures, revision A Remarks on simulation. Objectives/areas of (AD-A078216) N80-19065 use/possibilities/limitations: An overview ERICKSON, G. H. N80-19812 Effects of forebody, wing and wing-body-LEE FRANKLIN, J. A. flowfields on high angle of attack aerodynamics Plight evaluation of configuration management (SAE PAPER 791082) A80-26638 system concepts during transition to the landing ERKELENS, L. J. J. approach for a powered-lift STOL aircraft A flight simulation investigation on the [NASA-TM-81146] N80-19127 feasibility of curved approaches under NLS FRANZ, J. guidance NINITNIST: A shortened version of TWIST N80-19844 [LEF-T8-146] N80-181438 EVSEEV, D. D. FRASER, D. C. Method of determining steady-state aerodynamic A fault tolerant architecture approach to avionics characteristics for an elastic aircraft in free reliability improvement longitudinal motion N80-19533 A80-27173 FREED!, A. ETSTRATOVA, S. P. Aircraft emergency decisions: Cognitive and Acceleration of nulticycle fatigue testing on situational variables aluminum structural alloys [AD-A077413) N80-19051 A80-27479 FRIES, G. B. HLH and beyond [SAE PAPER 791086] A80-26641 F FROST, N. PAGAN, J. H. Fog dispersion The impact of CPS on CV mission effectiveness [NASA-CR-3255] N80-19703 A80-25165 FRYE, H. N. PAVIER, D. Investigation of fan blades shroud mechanical Transient effects on a stalled airfoil in a damping pulsating flow: Comparison with results from a [AD-A078439] N80-19120 similar airfoil undergoing horizontal shaking FRYER, B. A. [AAAF-NT-79-13J N80-18003 Publications in acoustic and noise control from PEDER, N. I. NASA Langley Research Center during 1940-1979 Military adaption of a commercial VOR/ILS airborne [NASA-TM-80211] N80-18884 radio with a reliability improvement warranty FYNAT, A. L. N80-19540 Frequency-scanning particle size spectrometer PELICI, N. [NASA-CASE-NPO-13606-2] 1180-18364 Experimental study of electrostatic dischargers for helicopters [ONERA, TP NO. 1980-5) A80-28947 G FIEDLER, P. A. GAERTEEB, K. P. Review of five years of flight testing the 8-1 Methods of sound simulation and applications in A80-27388 flight simulators [NASA-TN-75768) N80-19133
8-6
PERSONAL AUTHOR INDEX HAGER, J. P.
GALBRAITH, T. J. GORDON, D. N. New requirements, test techniques, and development Fastener hole quality, volume 1 methods for high fidelity flight simulation of [80-8077859] 880-19567 commercial transports GOVINDANAJ, K. S. [AIAA 80-0445] A80-26949 Implicit model following and parameter GALVES, J. P. identification of unstable aircraft Reliability of high-brightness CRTs for airborne A80-28019 displays GEAPTOR, S. 8.. H80-19543 Exploratory investigation of the effects of vortex GARBLE, N. B. bursting on the high angle-of-attack Reliability growth testing of avionic equipment lateral-directional stability characteristics of 880-27612 highly-swept wings GAPBARDT, N. D. (AIAA 80-0463) 880-26960 The impact of GPS on CV mission effectiveness GRANDT, A. P. A80-25165 An analysis of residual stresses and displacements GARNER, J. P. due to radial expansion of fastener holes Early flight test experience with Cockpit (80-8076370] 880-19569 Displayed Traffic Information (CDTI) GRAUER-CARSTENSEN, H. [NASA-TM-80221) 880-18037 An investigation of the quality of the flow GAUNYNER, J. V. generated by three types of wind tunnel (Ludwieg Algorithm for calculating turbine cooling flow and tube, Evans clean tunnel and injector driven the resulting decrease in turbine efficiency tunnel) [NASA-TN-81453] 880-19863 N80-19138 GEDDES, N. D. GRAY, C. B., JR. Handling quality requirements for advanced Design considerations for attaining 250-knot test aircraft design longitudinal mode velocities at the aircraft landing dynamics (80-8077858] 880-19128 facility GEE, S. V. [NASA-TN-80222] 880-19132 Specification for the installation of electrical GREEN, J. N. resistance strain gauges on strain pairs counter Difficulties in predicting avionics reliability aircraft 880-19521 [80-8071363] 880-18369 GREGORY, T. J. GERSTEIN, N. Workshop on Aircraft Surface Representation for Propulsion and energetics panel Working Group 11 Aerodynamic Computation on aircraft fire safety. Volume 2: Main report [NASA-TN-81170] N80-19025 (AGARD-AR-132-VOL-2] 880-19047 GRENOR, N. GIAVOTTO, V. Unsteady effects with control surfaces Damping problems in acoustic fatigue [AAAF-NT-79-01] 880-18049 N80-19580 CRIPPlE, J. N. GIERBART, G. D. Digital computer solution of aircraft longitudinal Comparison of measured data with IF-77 propagation and lateral directional dynamic characteristics model predictions [AD-A078672] 880-19068 [AD-8076508] 880-18259 GROSSIN, J. GILES, C. New possibilities offered by a radio-inertial Improved MPG for the RAe 146 feeder-jet hybrid guidance system digital simulation study A80-25449 880-19836 GIRARD, J. N. GUILLO, J. L. Impacts of technologies selected on the Contribution of photoelastic analysis to the study reliability and operational availability of of turbo-engine components equipments. Cost considerations [8871985] 880-19112 880-19536 GUXOT, B. GIRAUD, N. Comparison of aerodynamic coefficients obtained Impacts of technologies selected on the from theoretical calculations wind tunnel tests reliability and operational availability of and flight tests data reduction for the alpha equipments. Cost considerations jet aircraft N80-19536 [NASA-TN-75237] 880-17991 GLEASON, C. C. GUNYBEB, C. K. Evaluation of fuel character effects on 379 engine Cast aluminum primary aircraft structure combustion system 880-27875 [AD-A078440] 880-19119 GURUSNANY, P. GLETZES, C. Flutter analysis of a NACA 648006 airfoil in small Laminar separation bubble with transition /theory disturbance transonic flow and experiment/ 880-28851 (ONERA, TP NO. 1980-20) 880-27203 CIOBU, I. COLD, J. Aerodynamic performance of a centrifugal Reliability and maintainability design standards compressor with vaned diffusers from readiness-related goals A80-27735 (SAE PAPER 791109] 880-26651 GOLDBERG, J. Formal methods for achieving reliable software H N80-19549 HABERCON, C. N., JR. GOLDSCHNIED, P. B. Remotely piloted vehicles, volume 2. A Wind-turbine power improvement with modern airfoil bibliography with abstracts sections and multiple-speed generators [PB80-802119] 880-19089 (AIAA 80-0633] A80-28819 HARBOR, B. P. GOLLAHALLI, S. N. Wind-turbine power improvement with modern airfoil Characteristics of burning Jet A fuel and Jet A sections and multiple-speed generators fuel-water emulsion sprays [AIAA 80-0633] A80-28819 880-24817 HADCOCK, B. N. GOLUBET, B. The cautious course to introducing new SOB Flight control design based on nonlinear model technology into production systems with uncertain parameters A80-26343 880-28018 HAGER, J. P. 000DYER, N. J. Preliminary Airworthiness Evaluation UN-ill The development of a self-streamlining flexible helicopter equipped with Multiple Target walled transonic test section Electronic Warfare System (NULTEWS) [8188 80-0440] 880-26964 [80-8078476] 880-19067
B-i HAIDL, G. PERSONAL AUTHOR INDEX
HAIDL, G. HERNAN, J. P. Dynamic environments and test simulation for Wind tunnel test to investigate aerodynamic qualification of aircraft equipment and external hysteresis phenomena of the F-4 and P-li stores aircraft models N80-19 092 [AD-A077196] 880-19040 HAREL, P. G. HERRING, H. 3. Aircraft parameter identification methods and Flow in primary, non-rotating passages in their applications: Survey and future aspects turbomachines; Proceedings of the Winter Annual N80-19095 Meeting, New York, N.Y., December 2-7, 1979 HAMILTON, K. 180-27732 Proceedings of the 7th Ann. Tr-Service meeting BERZRANN, P. for Aircraft Engine Monitoring and Diagnostics Design and simulation of a C3 system for [A0-A076126] N80-18045 surveillance purpose HAMILTON, T. A. N80-19821 An analysis of the evolution of the reliability BESS, T. N. and maintainability disciplines Design and test of a boron - aluminum high N60-19520 temperature wing BANRICK, U. C. [AD-A075814] N80-18034 Report on the task force on aircraft separation HETSON, H. H. assurance, appendices Operational implications of some NACA/NASA rotary [AD-1077713] N80-18017 wing induced velocity studies BAN, L. S. 180-27599 Investigation of the boundary layer behavior on HICKS, B. turbine airfoils The role of the aircraft model in avionic systems [AD-A075501] N80-18044 simulation HANSON, N. N80-19837 HLH rotor box beam fatigue test BIGA, N. B. (AD-A0769311 N80-18450 On the characteristics of HARPER, P. N., SR. centrifugal-reciprocating machines Improved tire/wheel concept [NASA-CR-1628811 N80-19499 (NASA-CASE-LAN-11695-2] N80-18402 HIGGINS, N. 1. HARPER, R. N. Recovery system prelimiminary design. A On-board precision approach system using NAVSTAR GPS simplified approach to determining staging, A80-25162 timing and altitude requirements for fast HARRIS, D. J. inflating parachutes Software development for TORNADO: A case history [AD-A077548] 1180-19041 from the reliability and maintainability aspect HIGBBERGBR, U. T. N80-195514 NAVAIR pushes SPP/DB for structures HART, R. E. 180-24739 Investigation of engine performance degradation of BILDBET, B. L. TF33-P-7 engines Factorial design of experiments in the test and 180-27233 evaluation of a complex control system HARTZUIKBR, J. P. • 180-27242 Toward new transonic windtunnels HILL, E. G. [AGARD-AG-240] N80-19137 Selected wind tunnel testing developments at the The cryogenic wind tunnel: another option for the Boeing Aerodynamics Laboratory European Transonic Facility [AIAA 80-0458] 180-26958 N80-19i40 HILTON, A. B. HATCHER, D. C. GE-SI supersonic FUR window Accuracy and repeatability indices for joint oil [AD-A078371] N80-19948 analysis program data HILTON, B. C. [AD-A0781561 N80-19266 Nonelectronic aspects of avionic system reliability HAYNES, C. J. P. N80-19535 Computer simulation model of the logistic support BINCHEY, N. system for electrical engineering test equipment Research on the stability of air cushion systems N80-19560 [UTIAS-238] 1180-17985 HAZER, D. C. HINSON, B. L. Breaking V/STOL free of Catch 22 The aerodynamic design of an advanced rotor airfoil 180-26342 [NASA-CN-2961] N80-17989 HEAL!, B. D. BOCKADAT, S. L. N. E-3A navigational computer system real-time Capacity payoffs at large hub airports from ATC environmental simulator initiatives N80-19824 A80-28380 HEFFLET, N. K. BOPEB, K. E., .IR. High-angle-of-attack flying qualities - An Failure mechanisms for advanced composite sandwich overview of current design considerations construction in hostile environments [SAE PAPER 791085] 180-26640 A80-26884 HENDERSON, C. BOPPRAN, J. B. Proceedings of a Workshop on V/STOL Aircraft Evaluation of aircraft windshield materials in a Aerodynamics, volume 2 simulated supersonic flight environment [AD-A078909] N80-19042 [AD-A078673] 1180-19082 Proceedings of a Workshop on V/STOL Aircraft BOGLUND, L. Aerodynamics, volume 1 Swedish ERP research [AD-A079115] N80-19074 A80-27766 HENDERSON, D. N. ROGUE, J. B. Navstar field test results Development of aerodynamic disturbance test A80-25143 procedures, volume 1: Executive summary HENDERSON, J. P. [FB80-108145] N80-19991 Viscoelastic damping in USAF applications BOB, B. H. N80-19 582 Development of VTOL flying qualities criteria for HENSLEE, S. P. low speed and hover Fastener hole quality, volume 1 [AD-1079911] N80-19085 [AD-A077859] N80-19567 BOLDENAN, J. D. BENSON, D. J. Measurements of cabin and ambient ozone on E747 The Navstar Global Positioning System and time airplanes 180-25146 180-28853 BOLLINGER, J. P. Radiometric measurements of targets and clutter 180-26802
8-8 PERSONAL AUTHOR INDEX JOHNSTON, D. B.
HO!ICZ, G. F. INAICHX, K. Aerodynamic and acoustic investigations of axial Rotating stall in a vaneless diffuser of a flow fan and compressor blade rows, including centrifugal fan three-dimensional effects 180-27734 [AD-A077712] N80-19116 INNIS, H. C. BOPF'-WEICHEL, H. Flight evaluation of configuration management Aircraft emergency decisions: Cognitive and system concepts during transition to the landing situational variables approach for a powered-lift STOL aircraft [AD-A077413] 1180-19051 NASA-TH-81146] H80-19127 BOPKIN, V. D. IBVOAS, J. Real-time simulation: An indispensable but New possibilities offered by a radio-inertial overused evaluation techique hybrid guidance system digital simulation study 1180-19820 1180-19836 HOPPS, H. H. ISHIOI A. The changing horizons for technical progress. II Local laminarization in turbulent diffusion flames A80-27270 1 80-24819 HOREFF, T. ISOBE, T. Propulsion and energetics panel Working Group 11 Structural analysis of hollow blades: Torsional on aircraft fire safety, volume 2: main report stress analysis of hollow fan blades for (AGAHD-AR-132-voL-2] 1180-19047 aircraft jet engines HOROWITZ, B. N. (NASA-TM-75718] Adding more automation to the air traffic control 1180-19111 system 180-28384 HOROWITZ, I. J JACOBSON, N. C. Flight control design based on nonlinear model Avionics Reliability, Its Techniques and Related with uncertain parameters Disciplines 180-28018 [AGARD-CP-261] 1180-19519 HORSTEN, J. J. JAGO, S. Analysis of aircraft performance stability and The effect of viewing time, time to encounter, and control measures practice on perception of aircraft separation on N80-19099 HOWELL, N. N. a cockpit display of traffic information [NASA-TN-81173] 1180-18038 The National Transonic Facility - Status and JAHANI, H. operational planning Characteristics of burning Jet A fuel and Jet A [1111 80-0415] 180-26930 fuel-water emulsion sprays HSIEB, B. J. 180-24817 Dynamic stall on oscillating airfoils in 31111, B. L. oscillating free-streams Heat, mass and momentum transfer through sprays N80-17983 1180-18327 HUFF, B. L. JATNES, D. N. The F-16 Wild Weasel: A feasibility study V/STOLAND avionics system flight-test data on a [AD-A071050] N80-19071 UN-is helicopter HUGHES, B. J. [NASA-TB-78591] 1180-18047 Primary Adhesively Bonded Structure Technology JEFFERT, N. V. (PABST). General material property data [10-1077891] measurements of the dynamic performance of the 1180-19268 main drive fan of the RAE 5 metre pressurised HULTBERG, R. S. low speed wind tunnel Notary balance data for a typical single-engine [lilA 80-0456] 180-26956 general aviation design for an angle-of-attack A system for the measurement of the attitude of range of 8 deg to 90 deg. 1: Low-wing model A wind tunnel models [NASA-CR-3100] 1180-19030 [lilA 80-0465] 180-26962 BUSTER, I. N. .JENNELL, L. S. Achieving effective Radar Cross Section flight Performance estimates of a Boeing 747-100 profiles on the B-i aircraft transport mated with an outsize cargo pod A80-27227 [NASA-TN-80227] 1180-18032 BOSTON, N. J. JOHNSON, C. B. Approach to the assessment of the hazard A study of nonadiahatic boundary-layer 1180-19194 stabilization time in a cryogenic tunnel for Perspective on the results typical wing and fuselage models 1180-19202 [lilA 80-0417] HVIID, J. 180-26932 A theoretical analysis of simulated transonic Simulation defines alternatives for Copenhagen terminal expansion boundary layers in cryogenic-nitrogen wind tunnels [NASA-TP-1631 ] 1180-19131 180-27221 JOHNSON, J. L., JR. Exploratory investigation of the effects of vortex bursting on the high angle-of-attack lateral-directional stability characteristics of IARERCHOK, IU. F. highly-swept wings liethodof determining steady-state aerodynamic (lilA 80-0463] 180-26960 characteristics for an elastic aircraft in free JOHNSON, M. B. longitudinal motion Comparison of measured data with IF-77 propagation 180-27173 model predictions IATSENKO, V. K. [10-1076508] 1180-18259 Evaluation of the effectiveness of case-hardening JOHNSON, B. D. gas-turbine-engine components on the basis of Gas path seal fatigue-failure similarity equations [NASA-CASE-NPO-12131-3] 1180-181100 A80-26193 JOHNSON, T. L. ILICHET, V. D. Minimum time turns with thrust reversal The use of the spectral summation of fatigue [10-1079851] 1180-19078 damages in order to examine the combined stress JOHNSON, V. state of structures Application of unsteady airfoil theory to rotary 180-27152 wings ILIFP, K. N. A80-28856 Aircraft identification experience JOHNSTON, D. B. 1180-19 100 High-angle-of-attack flying qualities - An overview of current design considerations [SAN PAPER 791085] 180-26640
B9 JOHNSTON, J. P. PERSONAL AUTHOR INDEX
JOHNSTON, J. P. KENNEl, J. E. Straight-walled, two-dimensional diffusers - The Surface Contour Radar, a unique remote sensing Transitory stall and peak pressure recovery instrument 880-27746 880-26085 An experimental investigation of two large annular KEYSER, C. A., JR. diffusers with swirling and distorted inflow Early flight test experience with Cockpit [NASA-TP-1628] 1180-17984 Displayed Traffic Information (COTI) JONES, D. I. C. [NASA-T8-80221] 880-18037 Viscoelastic damping in USAF applications KILGORE, N. A. N80-19582 Development of the cryogenic tunnel concept and JONES, D. L. application to the US National Transonic Facility MIDS - The right tool for small test jobs B80-19139 A80-27230 KINURA, K. JONES, N. N., JR. On the NNSS application research in Japan Ferrographic and spectrographic analysis of oil 180-25164 sampled before and after failure of a jet engine KING, A. D. [NASA-TM-81430] 880-19497 Airborne radar approach system flight test JONKERS, H. A. experiment Aspects of flight test instrumentation [AD-A077900] 880-190511 N80-19098 KIRSCBBAU!, H. S. Analysis of aircraft performance stability and Wind-turbine power improvement with modern airfoil control measures sections and multiple-speed generators N80-19099 (8188 80-0633] 880-28819 JONUSHONIS, T. KJELGAARD, S. 0. Establishment of engineering design data for Effect of sweep and aspect ratio on the hybrid steel/ceramic hail bearings longitudinal aerodynamics of a spanloader wing [AD-A078934] 880-19509 in- and out-of-ground effect JORDAN, P. A., JR. [NASA-TM-80199] 880-17993 Development of test methods for scale model - KLEIN, N. H. simulation of aerial applications in the NASA Development of aerodynamic disturbance test Langley Vortex Facility procedures, volume 1: Executive summary [8188 80-0427] 880-26939 [2880-108145] 880-19991 JORDAN, L. B. KLEIN, V. Digital computer solution of aircraft longitudinal Identification evaluation methods and lateral directional dynamic characteristics 880-19096 [AD-A078672] 880-19068 KLEINEAN, D. JOST, C. S. Closed loop models for analyzing engineering A review of Australian investigations on requirements for simulators aeronautical fatigue during the period April [NASA-CR-2965] 880-19063 1977 to March 1979 KLINE, N. B. [AD-A071641] N80-18449 An analysis of the evolution of the reliability JUMPER, S. J. and maintainability disciplines Computer prediction of three-dimensional potential N80-19520 flow fields in which aircraft propellers KNAPP, A. G. operate: Computer program description and users Single rotor options for heavy lift and potential manual of multi lift (NASA-CR-162816] 880-179914 (SAE PAPER 791087] 880-26642 KOANDE, I. I. Minimum-weight wing in the presence of lift K constraints KAISER, K. P. A80-27136 Effect of wake-type nonuniform inlet velocity KOEHLEE, N. profiles on first appreciable stall in Closed loop aspects of aircraft identification plane-wall diffusers 880-19104 880-27747 KOPSKY, I. A. KALELKAR, A. Aircraft program for target background, and sky Assessment of risk due to the use of carbon fiber radiance measurements composites in commercial and general aviation [80-8016959] 880-18624 880-19201 KONOPSKA, D. KALEYKA, J. A system for measuring and recording wind-tunnel Rotorcraft identification experience balance data N80-19101 880-25221 KAPLAN, A. KOPELMAE, T. Assessment of the risk due to release of carbon Flight control design based on nonlinear model fiber in civil aircraft accidents, phase 2 with uncertain parameters N80-19200 880-28018 KARLSSON, T. KOREAN, H. F. Swedish SLIP research Data reduction and analysis of graphite fiber A80-27766 release experiments KARNICK, N. (NASA-CR-159032] 880-19048 Experience based upon experimental dry tuned gyros KORST, H. H. 880-28212 The simulation and modeling of jet plumes in wind KAY, I. N. tunnel facilities Theoretical limitations on collision avoidance (AIAA 80-01130] 880-26941 Systems KOSEKI, P. 880-26811 Aerodynamic performance of a centrifugal KELTO, C. A. compressor with vaned diffusers Fatigue in machines and structures - Aircraft 880-27735 880-26731 KOTANSKY, D. B. KENMOCHI, K. Viscous flowfieids induced by two- and Measurement of stress distribution in sandwich three-dimensional lift jets in ground effect beams under four-point bending [AD-A078782] 880-18343 A80-25498 KOVATS, A. KENMIN, C. V. Effect of non-rotating passages on performance of Nonelectronic aspects of avionic system reliability centrifugal pumps and subsonic compressors 880-19535 180-27733
B-10 PERSONAL AUTHOR INDEX LINTON, P. N.
KOWALSKX, H. A. LAUTNEB, D. E. The application of reliability improvement Power system control study. Phase 1: Integrated warranty to dynamic systems control techniques (AD-A075520] 880-18419 (10-1078629) 880-19125 KOZHEVNIKOV, V. F. LAW, B. D. Distribution of forces and stresses along rows of A system for the measurement of the attitude of bolted Connections wind tunnel models A80-27143 [AIAA 80-0465] 180-26962 KRAUSE, C. LAWTON, R. B. A simulation program for the determination of General aviation icing flight test system reliability of complex avionic systems 180-27383 880-19523 LATNE, I. P. KBENZ, G. Simulating the shock protection performance of The aerodynamics of future transport aircraft and large transit packs by means of small scale the role of the wind tunnel during development laboratory models 180-28494 A8 0-27 790 KEINGS, J. H. LEBACQZ, J. V. F/A-18 status report Implicit model following and parameter 180-27377 identification of unstable aircraft KRIUCRKOV, E. I. A80-28019 Improvement of the convergence of the method of LEBEN, D. P. polynomials in designing small-aspect-ratio wings Human factors in high speed low level accidents: A80-27183 A 15 year review EROLL, K. [10-1076221] 880-18012 Flow measurements in a turbine scroll LEE, B. G. V. A80-27738 Fastener hole quality, volume 1 KUBIANOV, A. I. (10-1077859) 880-19567 Hysteresis of aerodynamic characteristics LEE, K. A80-27167 Induced effects of lightning on an all composite KUTZ, G. H. aircraft Fighter options for tactical air defense, A80-27783 (SIB PAPER 791108] 180-26650 LEE, K. D. KUVSBINOV, V. N. Numerical simulation of the wind tunnel Singularities of the numerical solution of the environment by a panel method algebraic Riccati equation in matrix form by a (AIAA 80-0419) 180-26933 modification of the Lax-Wendroff method LEBNAN, L. 0. A80-27134 Firebrand anti-ship missile target - Plight test KYSEN, A. C. program objectives and vehicle instrumentation The aerial relay system: An energy-efficient requirenents solution to the airport congestion problem 180-27236 [NASA-TN-80208] N80-18011 LESOK8IN, T. A. Optimal twisting of blades in axial turboinachines A80-27797 L LETOUZET, J. LABARGE, N. A. Design of a simulator for studying the helicopter General aviation airplane structural - SDVEB crashworthiness programmer's manual 880-19829 (AD-A075737) 880-18008 LET!, B. LABOR, J. D. Viscous flow in the region of a rounded trailing Repair of advanced composite structure edge A80-26888 [Av-A078588] 880-19045 LACABBUBBA, S. LEN, B. K. Crew station design facility feasibility study Applying pressure . . . Relieving stress [AD-A078134] N80-19064 A80-27257 LAFROTH, B. N. LEWIS, B. B. Thrust vectoring to eliminate the vertical Advanced aluminum alloys from rapidly solidified stabilizer powers [AD-A079852] 880-19077 (10-1077197] 880-18161 LAGRIGALDIE, S. Development of advanced aluminum alloys from Experimental study of electrostatic dischargers rapidly solidified powders for aerospace for helicopters structural applications [ONEBA, PP 80. 1980-5] 180-28947 [AD-1077800] 880-18162 LABTI, H. B. LEYLAND, N. Hypersonic interference flow flight experiment Modeling the human operator: Applications to design system cost effectiveness [10-1078861) 880-19044 N80-19846 LAITONE, H. V. AIDER, S. Prandtls biplane theory applied to canard and V/STOLAND avionics system flight-test data on a tandem aircraft UN-1H helicopter A80-28852 [NASA-TN-78591] 880-18047 LAMB, C. S. J. LIBBEENAN, P. A rotary inverter system for a multiple-electrode Data reduction and analysis of graphite fiber WHO generator release experiments 180-25093 [NASA-CE-159032) 880-19048 LANE, N. E. LI!BBUNNEB, B. Modeling the human operator: Applications to A simulation program for the determination of system cost effectiveness system reliability of complex avionic systems N80-19 846 N80-19523 LANG, J. D. LINDEN, C. 0. Control and data acquisition aircraft for ALCM Solid state power controller verification studies flight tests [10-1078238] N80-19429 [AIAA 80-0446] 180-26950 Flat bus fault sensors LANGE, H. B. [AD-A077060] 880-19435 Future multi-mission transport aircraft - LINTON, P. N. Requirements and design possibilities Predicting field of view requirements for VSTOL [SAE PAPER 791097] A80-26646 aircraft approach and landing Future large cargo aircraft technology N80-19847 A80-27269
B-li
LIPIN, N. K. PERSONAL AUTHOR INDEX
LIPIN, N. K. Military aircraft and missile technology at the A single-step method of optimizing statically Langley Research Center: A selected bibliography indeterminate minimum-volume systems [NASA-TH-80204] 880-19024 A80-27135 MADDEN, J. L. LITTLE, P. Opportunistic maintenance policies for economic Lightning protection for aircraft replacement of internal life-limited compcnents A80-27021 in modular aircraft engines LIVINGSTON, V. V. (SAE PAPER 791101) A80-26647 Full scale visualization of the wing tip Vortices NAGEE, J. P. generated by a typical agricultural aircraft A hingeless rotor XV-15 design integration [NASA-CR-162796] N80-17992 feasibility study. Volume 1: Engineering LODGE, C. design studies Dynamic environments and test simulation for (NASA-CE-152310] 880-18030 qualification of aircraft equipment and external NAIKAPAB, G. I. stores Influence of the angle of attack on the thermal 880-19092 flux at the stagnation point at supersonic speeds LOEWENTHAL, S. H. A80-27138 ?valuation of a high performance fixed-ratio MAILLART, G. traction drive Boundary layer control by means of suction [NASA-TM-81425] 880-18404 [NASA-TM-75502] 880-17987 LOGUNOV, S. S. NAJOB, B. V. Aircraft instruments and automatic systems /3rd Shipboard antenna tests for GPS revised and enlarged edition/ A80-25144 A80-26350 MAKAROV, K. V. LORDI, J. A. Airport radio navigation systems Aerodynamic and acoustic investigations of axial A80-27716 flow fan and compressor blade rows, including MABCHAND, N. three-dimensional effects Wind tunnel and free flight model identification (A0-A077712] 880-19116 experience LORENZ-METER, V. N80-19103 The cryogenic wind tunnel: another option for the MAREK, A. J. European Transonic Facility Power system control study. Phase 1: Integrated 880-19140 control techniques LORINCZ, D. J. [AD-A078629] 880-19125 Effects of forebody, wing and wing-body-LEX MARESCA, C. flowfields on high angle of attack aerodynamics Transient effects on a stalled airfoil in a [SAE PAPER 791082) A80-26638 pulsating flow: Comparison with results from a LOVE, V. U. similar airfoil undergoing horizontal shaking Report on the task force on aircraft separation (AAAF-NT-79-13] 880-18003 assurance, appendices MARTIN, J. L. [AD-A077713] 880-18017 The Quiet Short-Haul Research Aircraft /QSRA/ LOVELL, B. B. A80-27384 Liquid metal slip ring MARTIN, S., JR. (NASA-CASE-LEW-12277-3] 880-18300 Multi rotor options for heavy lift LOWAK, H. (SAE PAPER 791089] A80-26643 MINITWIST: A shortened version of TWIST NABTONE, J. A. (LBF-TB-146] 880-18438 Control of particulate emissions from turbine LUCACCINI, L. engine test cells by cooling water injection Aircraft emergency decisions: Cognitive and [AD-A075947] 880-18587 situational variables MASCLE, J. (AD-A077413] 880-19051 Design of a simulator for studying the helicopter LUDWIG, G. R. - SDVEH Tests of an improved rotating stall control system 880-19829 on a J-85 turbojet engine NASLIN, N. N. (AD-A077708] 880-19109 BF communication to small low flying aircraft Basic studies of rotating stall in axial flow 880-19374 compressors Assessment of HF communications reliability [AD-A077690] 880-19115 N80-19377 Aerodynamic and acoustic investigations of axial HASTEN, B. L. flow fan and compressor blade rows, including An analysis of the evolution of the reliability three-dimensional effects and maintainability disciplines [AD-A077712] 880-19116 880-19 520 LUDWIG, L. P. NATHENS, N. S., III Wear of seal materials used in aircraft propulsion Preliminary Airworthiness Evaluation UH-1H systems helicopter equipped with Multiple Target A80-28010 Electronic Warfare System (NULTEWS) LYONS, K. A. [AD-A078476] 880-19067 Core compressor exit stage study. 1: Aerodynamic MATTHEW, J. B. and mechanical design Developing, mechanizing and testing of a digital [NASA-CR-159714] 880-19113 active flutter suppression system for a modified B-52 wind-tunnel model (NASA-CH-1591551 880-19566 M MATTHIESEN, P. MACCREADY, P. Simulation defines alternatives for Copenhagen Crossing the Channel in the Gossamer Albatross terminal expansion A80-27389 A80-27221 MACH, K. D. MCATEE, T. P. A computer program for estimating aircraft landing F-16 European test and evaluation distance A80-27380 [An-A077169] 880-19088 HCCLUNPHA, A. J. MACNAUGHTON, I. G. Neal-time simulation: An indispensable but Control of particulate emissions from turbine overused evaluation techique engine test cells by cooling water injection N80-19820 (AD-A075947] 880-18587 NCCLUNG, B. C. MADDALON, D. V. Constant speed 1400 Hz aircraft electric generation Computer programs for estimating civil aircraft system economics [SAE PAPER 791067] A80-26630 [NASA-TM-80196] N80-18988
8-12 PERSONAL AUTBOR INDEX NOBEl, I.
ECCLOSKE!, B. BORN, G. C. Legal liability of the controller. I Early flight test experience with Cockpit A80-28500 Displayed Traffic Information (CDTI) MCCOY, B. L. [NASA-TN-80221] 1180-18033 Wind tunnel and flight test drag comparisons for a ROBE, B. I. guided projectile with cruciform tails Navigation systems for approach and landing of [AIAA 80-0426] A80-26968 VIOL aircraft NCCDTCHBN, C. V. (NASA-CE-152335) 1180-19055 Avoiding divergent stall in control configured MOLLO!, J. K. aircraft by using a canard arrangement Computer programs for estimating civil aircraft A80-28854 economics NCDONALD, A. T. [NASA-TH-80196] 1180-18988 Effect of wake-type nonuniform inlet velocity NOON, B. B. profiles on first appreciable stall in Evaluation of JP-5 turbine fuel in the single plane-wall diffusers cylinder cue 1790 diesel engine A80-27747 [AD-A078666] 1180-18206 NCDONALD, H. MOORE, V. A. Viscous flow in the region of a rounded trailing Effects of forebody, wing and wing-body-LEE edge flowfields on high angle of attack aerodynamics [AD-A078588] N80-19045 (SAE PAPER 791082] A80-26638 NCPARLANO, A. L. NORINAGA, N. Report on the task force on aircraft separation Error rate performance of N-ary DPSK systems in assurance, appendices satellite/aircraft communications [AD-A077713] 1180-18017 A80-25945 ECLENOBE, H. C. NOBLE!, B. A. Aeroacoustic wind-tunnel tests of a light The practical aircraft hydraulic test stand twin-boom general-aviation airplane with free or (SAE PAPER 791079] A80-26636 shrouded-pusher propellers MORRIS, C. B. K., JR. (NASA-TM-80203] N80-19023 A flight investigation of blade section ECROLYT, P. aerodynamics for a helicopter main rotor having Methodology for target discrimination NLR-1T airfoil sections A80-27347 [NASA-TM-80166] 1180-19033 NCVEIGH, N. A. NORRISON, P. B. Synthesis of rotor test data for real-time Establishment of engineering design data for simulation hybrid steel/ceramic ball bearings (NASA-CR-152311] 1180-18029 (AD-A0789314] 1180-19509 HELLO, J. MORROW, B. J. ECAIR design philosophy for fighter aircraft Simulation for whole life development departure and spin resistance 1180-19839 (SAE PAPER 791081] A80-26637 NOEl, K. V. NERRICK, B. N. An experimental investigation of two large annular V/STOLAND avionics system flight-test data on a diffusers with swirling and distorted inflow 08-18 helicopter (NASA-TP-1628] 1180-17984 (NASA-TM-78591) 1180-18047 NOIRE, B. I., JR. NESSERLE, H. K. Influence of interface on composite failure A rotary inverter system for a multiple-electrode 180-26895 NHD generator NOZZHEROVA, I. A. A80-25093 Crack development in panels of a pressurized MEYER, G. fuselage under the combined effect of Application of the concept of dynamic trim control pressurization-induced cyclic loads and to automatic landing of carrier aircraft high-frequency vibrations [NASA-TP-1512] 1180-19126 180-26195 NIKHAILOV, B. N. MUELLER, I. J. Influence of the empennage on the effective thrust On the historical development of apparatus and of jet engine exhaust nozzles techniques for smoke visualization of subsonic A80-27 139 and supersonic flows NIKOLOWSEY, V. T. [AIAA 80-0420] 180-26934 Future multi-mission transport aircraft - Visualization of the laminar-turbulent transition Requirements and design possibilities in the flow over an airfoil using the smoke-wire (SAE PAPER 791097] A80-26646 technique MILLER, C. N. [AIlA 80-0421] 180-26935 Are we spending too much on flight test NULCAY, V. instrumentation Rotary balance data for a typical single-engine A80-27229 general aviation design for an angle-of-attack BILLER, N. D. range of 8 deg to 90 deg. 1: Low-wing model A Measuring technological change in. jet fighter (NASA-CE-3100] 1180-19030 aircraft NULDER, J. A. [AD-A077393] N80-19084 Aspects of flight test instrumentation MIHAILOS, A. N. N80-19098 Numerical modeling of supersonic flow near a thin Analysis of aircraft performance stability and delta wing with discontinuous edge control measures A80-27 147 N80-19099 Similarity of the aerodynamic characteristics of MUNDBA, A. D. delta wings at supersonic speeds Report on the task force on aircraft separation A80-27168 assurance, appendices NIRONOV, A. A. [AD-1077713] 1180-18017 Minimum-weight wing in the presence of lift NUNIN, A. C. constraints Local ground noise generated by supersonic A80-27136 transport planes NISHINA, H. 180-26206 Aerodynamic performance of a centrifugal NURALIDHABAN, B. compressor with vaned diffusers Closed loop models for analyzing engineering A80-27735 requirements for simulators NITAGAKI, T. [NASA-CR-2965] 1180-19063 Error rate performance of N-ary DPSK systems in NURRA, I. satellite/aircraft communications Research on the stability of air cushion systems A80-259145 (UIIAS-238) 1180-17985
8-13
NAGIB, H. H. PERSONAL AUTHOR 18DB!
HYBERG, S.-E. The simulation and modeling of jet plumes in wind N tunnel facilities NAGIB, H. N. (8188 80-0430] 880-26941 Evaluation of a new concept for reducing Experimental investigation of the free-stream turbulence in wind tunnels interference-free flow field around a lifting [.8188 80-0432] 880-26942 wing-body model to establish cross flow NAMEKAWA, T. characteristics for ventilated wind tunnel walls Error rate performance of M-ary DPSK systems in at low supersonic Mach numbers satellite/aircraft communications (8188 80-0444) 880-26948 880-25945 NANEVICZ, J. E. Atmospheric electricity and military operations 0 (80-8078482) 880-19693 OBAL, H. N. NAPPI, A. Angular vibration measurement techniques Damping effects in joints and experimental tests 880-18222 on riveted specimens OBERNEXER, L. 880-19584 The Tornado all-weather high-speed low-level system NABESKI, J. J. 880-27379 A new approach to maintainability prediction OCONNOR, S. N80-19537 The effect of viewing time, time to encounter, and NASTNOM, G. D. practice on perception of aircraft separation on Measurements of cabin and ambient ozone on 8747 a cockpit display of traffic information airplanes [NASA-TH-81173] 880-18038 880-28853 OGAWA, A. NASU, H. Structural analysis of hollow blades: Torsional On the NNSS application research in Japan stress analysis of hollow fan blades for A80-25164 aircraft jet engines NATLER, G. H. F. [NASA-TM-75718] 880-19111 Civil aircraft equipment environment qualification OILER, T. L. techniques Evaluation of fuel character effects on J79 engine 880-19 093 combustion system NELSON, K. D. (AD-8078440] 880-19119 Helicopter crash position indicator flight trials OLSEN, J. J. A80-27240 Flutter analysis of a NACA 648006 airfoil in small NENNI, J. P. disturbance transonic flow Basic studies of rotating stall in axial flow 88 0-28 85 1 compressors OLSEN, N. [80-8077690] 880-19115 Effect of temperature on surface noise NEUBAWER, N. J. 880-28419 Computer programs for estimating civil aircraft OLSON, L. B. economics High-resolution LDA measurements of Reynolds (NASA-TM-80196] N80-18988 stress in boundary layers and wakes NEUMAN, P. [8188 80-0436] 880-26967 Analysis of fuel-conservative curved decelerating ORLANSK!, J. approach trajectories for powered-lift and CTOL Cost-effectiveness of flight simulators for jet aircraft military training [NASA-TP-1650] N80-19022 880-19830 NEWMAN, P. A. 0810FF, K. L. Interaction of a two-dimensional strip boundary High-resolution LDA measurements of Reynolds layer with a three-dimensional transonic stress in boundary layers and wakes swept-wing code (8188 80-0436) 880-26967 [NASA-TM-78640] 880-17988 ORMAN, J. C. NEWMAN, S. Capacity payoffs at large hub airports from AIC E-3A navigational computer system real-time initiatives environmental simulator 880-28380 N80-19624 OSIPIAK-CHMIELENSKA, I. NGUYEN, L. T. A system for measuring and recording wind-tunnel Control system techniques for improved balance data departure/spin resistance for fighter aircraft A80-25221 (SAE PAPER 791083) 880-26639 OSTGAARD, J. C. NIENOLLEB, D. L. A simulation support system, the development tool Military adaption of a commercial VOR/ILS airborne for avionic systems and subsystems radio with a reliability improvement warranty 880-19840 N80-19540 OSTROFF, H. H. NIKITIN, A. I. An approach to the runway denial problem Design of an electronic model of a microwave [SAE PAPER 791107] 880-26649 aircraft landing system 880-2647 1 NISHI, S. P On the NESS application research in Japan PAGE, C. L., JR. A80-25164 An analysis and synthesis of engine condition NISHIDA, N. monitoring systems Aerodynamic performance of a centrifugal [80-8077531] 880-19122 compressor with vaned diffusers PAGE, V. B. A80-27735 An experimental investigation of two large annular NITA, N. N. diffusers with swirling and distorted inflow On the equations of notion about the mass centre NASA-TP-1628] 880-17984 of the jet aircraft considered as variable mass PALMER, B. A. system The effect of viewing time, time to encounter, and 880-26325 practice on perception of aircraft separation on HOE, P. S. a cockpit display of traffic information A collision avoidance system using Navstar/GPS and [NASA-TM-81173] 880-18038 A IC P OS PANDOLPI, N. A80-25157 Three-dimensional inviscid compressible rotational 8080888, P. J. flows Numerical results and comparison with Patener hole quality, volume 1 analytical solutions [AD-A077859) 880-19567 A80-27745
B-14
PERSONAL AUTHOR INDEX POTTER, N. N.
PAOLINI, B. PERSSON, B. Experimental procedure to determine limits of ISM Swedish EM? research interference affecting navigational ILS equipment A80-27766 *80-27760 PETERS, G. 8.. PARKER, J. Viscous flowfields induced by two- and Propulsion and energetics panel Working Group 11 three-dimensional lift jets in ground effect on aircraft fire safety. Volume 2: Rain report [AD-A078782] N80-18343 [AGARD-AE-132-VOL-2] 880-19047 PETERSON, J. 8., JR. PARKHOMOV, A. L. Wind-tunnel/flight correlation study of Theory of by-pass ducted-fan engines aerodynamic characteristics of a large flexible A80-26349 supersonic cruise airplane (18-70-1). 3: A PARKS, B. K. comparison between characteristics predicted Aircraft motion analysis using limited flight and from wind-tunnel measurements and those measured radar data in flight A80-27241 [NASA-TP-1516] 880-17986 PARRAVANO, G. J. PETERSON, V. C. Research on the stability of air cushion systems Consolidation of titanium powder to near net shapes (UTIAS-238) 880-17985 (AD-A078039] 880-19239 PASQUALE, J. D. PETTIGEEW, J. A. An analysis of the evolution of the reliability Proceedings of the 7th Ann. Tr-Service Meeting and maintainability disciplines for Aircraft Engine Monitoring and Diagnostics 880-19520 [AD-A076126] 880-18045 PATRICK, J. P. PHALLEE, L. J. Air supply system approach for the Boeing Model Reliability growth through environmental simulation 767 Airplane 880-19538 [SAE PAPER 791068) *80-26631 PHILLIPS, B. J. PAULSON, 3. V., .3N. Some recent measurements of structural dynamic Effect of sweep and aspect ratio on the damping in aircraft structures longitudinal aerodynamics of a spanloader wing 880-19576 in- and out-of-ground effect PINVICS, .1. [NASA-TM-80199] N80-17993 Establishment of engineering design data for PAUTLER, J. A. hybrid steel/ceramic ball bearings Application of Nd:IAG optical communications [AD-A078934] 880-19509 technology for aircraft to satellite links PITZER, B. A. *80-26797 Control and data acquisition aircraft for ALCM PAVIEB, J. D. flight tests Reliability management of the avionic system of a [AIAA 80-0446] *80-26950 military strike aircraft PLAETSCBKE, B. 880-19546 Practical input signal design PAYLIUKOT, B. V. N80-19097 Influence of the empennage on the effective thrust PLATZ, K. of jet engine exhaust nozzles Influence of air traffic on the concept of air *80-27139 traffic control PAVLOV, L. S. A80-28488 Pressure distribution in rectangular wing /blade/ PLATZEE, N. F. sections during curvilinear motion in an Proceedings of a Workshop on V/STOL Aircraft incompressible medium Aerodynamics, volume 2 *80-27157 [AD-A078909] 880-19042 PAVLOV, V. A. Proceedings of a Workshop on V/STOL Aircraft Application of geometrical programming to problems Aerodynamics, volume 1 of optimal design [AD-A079115] 880-19074 *80-27137 PLETCHER, J. H., JR. PAYNE, B. V. An analytical and experimental study of aircraft Civil aircraft equipment environment qualification hydraulic lines including the effect of mean flow techniques [AD-A079746] 880-19079 880-19 093 PLUMBER, C. A.., JR. PEGG, R. J. TAV-88 status report Aeroacoustic wind-tunnel tests of a light *80-21381 twin-boom general-aviation airplane with free or POCINKI, L. S. shrouded-pusher propellers Assessment of the risk due to release of carbon (NASA-TM-80203] 880-19023 fiber in civil aircraft accidents, phase 2 PELPOR, D. S. 880-19200 Aircraft instruments and automatic systems /3rd POGGIO, B. revised and enlarged edition/ Estimating the time required to transition *80-26350 aircraft fleets to new scheduled maintenance PERALA, R. A. intervals Induced effects of lightning on an all composite [AD-A078606] 880-19027 aircraft POLLOCK, N. • A80-27783 Programs for the transonic wind tunnel data PERINI, J. processing installation. Part 7: Extended focal Experimental measurement of fields excited inside [AD-A013414] 880-18054 the fuselage of an aircraft POND, C. B. *80-27306 Selected wind tunnel testing developments at the PERKINS, J. R. Boeing Aerodynamics Laboratory Power system control study. Phase 1: Integrated (AIAA 80-0458) A80-26958 control techniques PONGRATZ, H. V. [AD-A078629] R80-19125 Fire control for air-to-air gunnery in high PERKINS, P. J. performance fighter aircraft Measurements of cabin and ambient ozone on B747 880-19841 airplanes POSE!, D. I. A80-28853 Static pressure orifice system testing method and PERKINS, P. N. apparatus Easy ACLS dynamic analysis, volume 2. Part 2: [NASA-CASE-LAR-12269-1] 880-18358 Component computer programs POTTER, B. N. (AD-A079803] 880-19076 An analysis of residual stresses and displacements PERSON, L. H., JR. due to radial expansion of fastener holes Early flight test experience with Cockpit [AD-A076370] 880-19569 Displayed Traffic Information (CDTI) [NASA-TM-80221] 880-18037
8-15 POWELL, H. H. PERSONAL AUTHOR INDEX
POWELL, H. H. RAPP, H. B. Laser-Raman flow-field diagnostics of two large Aircraft icing during low-level flights hypersonic test facilities [AD-A078843] 1180-19052 (A0-A078289] 1180-19135 BATINO, D. A. PRICE, E. A., JR. Digital computer solution of aircraft longitudinal An investigation of F-16 nozzle-afterbody forces and lateral directional dynamic characteristics at transonic Mach numbers with emphasis on [AD-A078672] N80-19068 support system interference - BEBONT, J. [AD-A078693] N80-18046 Transient effects on a stalled airfoil in a PRICE, L. I. pulsating flow: Comparison with results from a Laser-Raman flow-field diagnostics of two large similar airfoil undergoing horizontal shaking hypersonic test facilities (AAAF-NT-79-13] N80-18003 [AD-A078289] 1180-19135 REED, N. B. PRIDE, R. A. Carbon and graphite. Part 2. Carbon and graphite Large-scale fiber release and equipment exposure composites - excluding carbon fiber composites. experiments A bibliography with abstracts N80-19198 [P880-802374] 1180-18144 PRINCE, S. N. Carbon and graphite. Part 1: Carbon and graphite Experimental investigation of a circulation fibers and fiber composites, volume 4. A control aileron bibliography with abstracts [AD-A078825] N80-19046 [PB80-802366] 1180-18145 PROK, G. N. Seals and gaskets. A bibliography with abstracts Initial characterization of an Experimental [2880-802010) 1180-18417 Referee Broadened-Specification (EBBS) aviation BENAUD, J. turbine fuel Rotors in forward flight and dynamic stall [NASA-TM-814 140] N80-18205 (AAAP-NT-79-20] 1180-18050 PROZELLER, B. F. RESAL, J. A. Applications of the spread-spectrum signals from The development of the world's first triengine the NOVA satellites business jet, the Mystere Falcon 50 A80-25149 A80-27386 PUGH, P. G. BHOADES, V. N. An investigation of the quality of the flow Low speed test of the aft inlet designed for a generated by three types of wind tunnel (Ludvieg tandem fan V/STOL nacelle tube, Evans clean tunnel and injector driven (NASA-CE-159752] 1180-18042 tunnel) RHODES, N. D. 1180-19138 Graphite-epoxy panel compression strength The cryogenic wind tunnel: another option for the reduction due to local impact European Transonic Facility A80-27598 N80-19 140 RICCIABDI, B. V. Modern HF communications for low flying aircraft 1180-19375 RICHARDS, B. QUEMARD, C. Simulation for whole life development An investigation of the quality of the flow 1180-19839 generated by three types of wind tunnel (Ludwieg NICHE!, B. J. tube, Evans clean tunnel and injector driven Design and test of a boron - aluminum high tunnel) temperature wing 1180-19138 [AD-A07581 14] 1180-18034 EIFFEL, B. E. The experimental-modeling of unstalled supersonic R turbofan flutter RADON, A. (AIAA 80-0454] A60-26963 An induction gyrocompass BINKUNAS, D. A. A80-252114 Investigation of fan blades shroud mechanical RAGHURANAN, P. damping Evaluation of an analysis for axisymmetric [AD-A078439) 1180-19120 internal flows in turbomachinery ducts BIPPL, K. H. A80-27742 EMC in lightweight helicopters - Special prcblems RAHLFS, D. and experience in design and control The experimental strapdovn system of DFVLR A80-27773 A80-28218 BOCK, S. N. BAIRN!, L. Variable cycle engine nultivariable control Avionics evaluation program: Simulation models synthesis: Control structure definition for the effectiveness analysis of avionics [AD-A078670] N80-19117 N80-19B38 RODE, B. RAJ, D. System ENC - Tendencies of a worldwide Identification of noise sources in PC centrifugal standardization and cooperation fan rotors A80-27784 1180-18395 ROGERS, B. T. RAJPADL, V. K. Development and test of low-impact resistant towers New remotely piloted vehicle launch and recovery [AD-A077160] 1180-18052 concepts: Computer program listings ROGERS, L. C. [AD-A076611] N80-18035 Viscoelastic damping in USAF applications New remotely piloted vehicle launch and recovery 1180-19582 concepts. Volume 1: Analysis, preliminary BOGIN, L. design and performance/cost trade studies Reliability and maintainability design standards (AD-A077475] 1180-19066 from readiness-related goals BANACRANDRAN, S. [SAE PAPER 791109] R80-26651 Application of the Estimation-Before-Modeling BOHR, D. A. (EBN) system identification method to the high Evaluation of a high performance fixed-ratio angle of attack/sideslip flight of the T-2C jet traction drive trainer aircraft. Volume 2: Simulation study [NASA-TM-81425] 1180-18404 using T-2C wind tunnel model data ROSENPIELD, D. (AD-A079923) N80-19061 Assessment of risk due to the use of carbon fiber RAMAKRISHNAN, S. composites in commercial and general aviation A rotary inverter system for a multiple-electrode N80-19201 MilD generator ROSS, A. J. A80-25093 Identification experience in extreme flight regimes 1180-19102
8-16
PERSQNAL AUTHOR INDEX 5301101!, B.
ROSS, J. A. SCHWERTZ, J. H. Development and test of low-impact resistant towers Consolidation of titanium powder to near net shapes [AD-A077160] 980-18052 [AD-A078039] 1180-19239 ROUND!, J. S. SEIBANIAN, A. P. Demonstration program for a flexible duct valve minimum-weight wing in the presence of lift for ramjet engine fuel controls constraints [AD-A078529] 1180-19123 A80-27136 ROD, B. C. SELLIER, N. Human factors in high speed low level accidents: Design of a simulator for studying the helicopter A 15 year review - SDVEH [AD-A076221) 1180-18012 180-19829 RUEDGEB, I. H. SEEG, U. T. Continued study of NAVSTAR/GPS for general aviation Initial characterization of an Experimental (NASA-CN-159145] 1180-18020 Referee Broadened-Specification (EBBS) aviation RUNSEY, P. C. turbine fuel New requirements, test techniques, and development NASA-TN-8 1440) 1180-18205 methods for high fidelity flight simulation of SETTERLUND, B. H. commercial transports Cruise-missile-carrier navigation requirements [AIAA 80-0445] 180-26949 1180-19843 RUSTBEBURG, J. V. SHANAHAN, A. B. Development of a normalized probability The application of modeling and simulation to the distribution for lateral load factors due to development of the E-3A aircraft ground turning 1180-19823 [AD-A077047] 1180-19070 SHANNON, B. N. RUTHERFORD, J. L. Primary Adhesively Bonded Structure Technology Primary Adhesively Bonded Structure Technology (PABST). General material property data (PABST). General material property data [AD-A077891] 1180-19268 [AD-A077891] 1180-19268 SHAPCOTV, S. B. The integrated management of reliability and maintainability in procurement S B80-19558 SAIB, S. H. SHAWLER, V. Verification and validation of avionic simulations Development and flight test of a two-place N80-19814 night/adverse weather A-10 for the close-air SALEH, J. support and battlefield attack mission Aircraft emergency decisions: Cognitive and (SAE PAPER 791069] A80-26632 situational variables SHATESOB, N. V. (AD-A077413) 1180-19051 Evaluation of fuel character effects on .379 engine SANDERS, H. combustion system Design and simulation of a C3 system for [AD-A078440] 1180-19119 surveillance purpose SHEFTEL, D. J. N80-19821 Outlook for Global Positioning System /GPS/ in SAEDOR, J. civil aircraft operations Computer synthesis of flight simulation visuals A80-25158 CARL/STS-NOTE-61] 1180-18053 SHELDON, N. H. SAUNDERS, A. A., .IR. Nondestructive evaluation of graphite composite Method and apparatus for rapid thrust increases in aircraft structures a turbofan engine A80-26891 [NASA-CASE-LEW-12971-1] 1180-18039 SHEORAN, I. SCHANSHAN, T. T. Flow measurements in a turbine scroll NSSC-2 operating system design requirements A80-27738 specification SBESHIN, I. P. [NASA-CR-161396] 1180-19861 Airport radio navigation systems SCHEINAN, J. A80-27716 A comparison of experimental and theoretical SHIN, 8.-B. turbulence reduction from screens, honeycomb and Local laminarization in turbulent diffusion flames honeycomb-screen combinations A80-24819 [AIAA 80-0433] A80-26943 SHIEINIANTS, V. A. SCHHID!, U. V. Application of geometrical programming to problems Cruise-missile-carrier navigation requirements of optimal design 1180-19843 A80-27137 SCHHIDT, S. F. SHLIAKHTENKO, S. N. Navigation systems for approach and landing of Theory of by-pass ducted-fan engines VTOL aircraft A80-26349 [NASA-CR-152335] 1180-19055 SHTEINBEBG, B. I. SCHNEIDER, J. J. Hysteresis of aerodynamic characteristics HLH and beyond A80-27167 (SAE PAPER 791086) A80-26641 Induced drag and lift-drag ratio of swept wings at SCHONEB, D. supersonic speeds The freight forwarder as an air carrier A80-27175 A80-28862 SIB, G. C. SCHROEDER, H. V. Influence of interface on composite failure Rain erosion of lightning protection coatings for A80-26895 carbon fibre composites SINONS, J. L. A80-25059 Analysis of aircraft performance stability and SCHUBERT, C. control measures Airbus family concept for the 1990s 1180-19099 A80-28489 SINONS, V. D. SCHOE!Z, D. An experimental investigation of two large annular NINITRIST: A shortened version of TWIST diffusers with swirling and distorted inflow [LBF-TB-146) 1180-18438 [NASA-TP-1628] 1180-17984 SCHULZ, C. SIROTKIN, IA. A. Practical input signal design One-dimensional aerodynamic control calculations H80-19097 for cooled gas turbines SCHWARTZ, N. A80-26305 Feasibility testing of a Body Inflatable Bladder 530801!, B. (BIB) restraint device Swedish EMP research [AD-A078681] 1180-18013 A80-27766
B-17
SNOW, A. B. PERSONAL AUTHOR INDEX
SNOW, A. H. SPRING, S. C. Effects of forebody, wing and wing-body-LU Preliminary Airworthiness Evaluation OH-la flowfields on high angle of attack aerodynamics helicopter equipped with Multiple Target [SAP PAPER 791082] A80-26638 Electronic Warfare System (NULTEWS) SLUDER, B. B. [AD-A078476] 1180-19067 Aircraft program for target background, and sky STAHARA, S. S. radiance measurements Data report for a test program to study transonic [AD-A076959] 1180-18624 flow fields about wing-body/pylon/store SMITH, B. combinations. Volume 1: Tunnel empty flow New approaches to sailing survey data, wing body force/moment/surface pressure data, and pressure store SMITH, C. C. force/moment/surface pressure data A study of the canopy design for the advanced [AD-A077182] N80-18001 attack helicopter by use of computer graphics Data report for a test program to study transonic [AD-A078291] 1180-19069 flow fields about wing-body/pylon/store SMITH, G. A. combinations. Volume 2: Flow field survey data Application of the concept of dynamic trim control for configurations 21 and 22 to automatic landing of carrier aircraft (AD-A077183] N80-18002 [NASA-TP-1512] 4480-19126 STAINBACK, P. C. SMITH, C. T. Additional flow quality measurements in the Application of composite materials to turbofan Langley Research Center 8-Foot Transonic engine fan exit guide vanes Pressure Tunnel [NASA-TM-81432] 1180-18106 [AIAA 80-0 1434] A80-26944 SMITH, J. H. STALFORD, H. L. The duration of false alarms in surveillance radar Application of the Estimation-Before-Modeling A80-27902 (EBB) system identification method to the high SMITH, J. S., III angle of attack/sideslip flight of the T-2C jet Review of five years of flight testing the B-i trainer aircraft. Volume 2: Simulation study A80-27388 using T-2C wind tunnel model data SMITH, P. B. [AO-A079923] N80-19061 Aerodynamic investigation of C-i'll leading edge Application of the Estimation-Before-Modeling modification for cruise drag reduction, volume 2 (EBB) system identification method to the high [AD-A077688] 1180-19081 angle of attack/sideslip flight of the T-2C jet SMITH, N. H. trainer aircraft. Volume 3: Identification of Handling quality requirements for advanced ¶I-2C aerodynamics stability and control aircraft design longitudinal mode characteristics from actual flight test data [AD-8077858] 1180-19128 [AD-A0799214] 1180-19072 SMOLKA, S. Application of the Estimation-Before-modeling Modeling and flight simulation of an active (EBN) system identification method to the high configured aircraft under N.L.S. guidance angle of attack/sideslip flight of the T-2c jet N80-19845 trainer aircraft. Volume 1: Executive summary SNYDER, K. M. [AD-A080025] N80-19073 Development and test of low-impact reCistant towers STANLEY, N. L. [AD-A077160] 1180-18052 Measuring technological change in jet fighter SNYDER, B. E. aircraft Design considerations for attaining 250-knot test [AD-A077393] 1180-19084 velocities at the aircraft landing dynamics STARCH, S. facility The KC-135 - A successful multirole transport [NASA-TN-80222] 1180-19132 aircraft SOPOR, Y. [SAP PAPER 791093] A80-26644 Structural analysis of hollow blades: Torsional STELTZ, W. G. stress analysis of hollow fan blades for Flow in primary, non-rotating passages in aircraft jet engines turbomachines; Proceedings of the Winter Annual [NASA-TM-75718] 1180-19111 Meeting, New York, N.Y., December 2-7, 1979 SOLER, A. A80-27732 Flow in primary, non-rotating passages in STEPWOV, H. N. turbomachines; Proceedings of the Winter Annual Acceleration of multicycle fatigue testing on Meeting, New York, N.Y., December 2-7, 1979 aluminum structural alloys A80-27732 A80-27479 SOLLEB, J. E. STEVENS, U. U. Airborne video instrumentation/data reduction A flight investigation of blade section A80-27232 aerodynamics for a helicopter main rotor having SONNENSCREIN, C. H. NLR-1T airfoil sections Helicopter remote wind sensor system description [NASA-TH-80166] 1180-19033 [AD-A076153] N80-18024 STEWART, P. A. N. SORENSEN, B. Transparent engines at Rolls-Royce - The Experimental investigation of the application of high energy X-ray technology to interference-free flow field around a lifting gas turbine development wing-body model to establish cross flow A80-25447 characteristics for ventilated wind tunnel walls STIPEL, P. at low supersonic Mach numbers Primary Adhesively Bonded Structure Technology [AIAA 80-04414] A80-26948 (PABST) . General material property data SORENSEN, J. A. (AD-A077891] N80-19268 Concepts for generating optimum vertical flight STOPPER, I. J. profiles Novel ceramic turbine rotor concepts [NASA-CE-1591813 N8O-18031 [AD-A078669] 1180-19118 SOSUNOV, V. A. STOLIABOV, G I. Theory of by-pass ducted-fan engines Hysteresis of aerodynamic characteristics A80-263149 A80-27167 SOUTHALL, H. L. STORY, D. H. Permanent magnet and superconducting generators in On-condition maintenance - Review of military airborne, high power systems engines [AD-A078142 14] 1180-18311 [RAE PAPER 791102] A80-26648 SPINTZYK, J. STEACCA, G. B. Technological aspects of future very large airplanes Present-day problems of air traffic control in A80-28490 ground-to-air communications A80-26221
B-18
PERSONAL AUTHOR INDEX UHLIN, J. G.
STRADA, J. A. THORNBURG, D. D.- Navstar field test results The Navstar Global Positioning System and time 880-25143 A80-25146 SThIEB, N. I. THORNTON, B. A. Modeling the human operator: Applications to Evaluation of finite element formulations for system cost effectiveness transient conduction forced-convection analysis V80-19846 880-28284 STRING, J. TILLIAEVA, N. I. Cost-effectiveness of flight simulators for Numerical method for calculating supersonic flow military training past a plane air intake with detached shock wave N80-19830 880-27148 STRIZ, A. G. TIM!, L. Flutter analysis of a NACA 648006 airfoil in small P-16 European test and evaluation disturbance transonic flow A80-27380 880-28851 TONAINE, R. L. STRUNZ, H. C. A flight investigation of tlade section Report on the task force on aircraft separation aerodynamics for a helicopter main rotor having assurance, appendices NLR-1T airfoil sections [AD-A077713] 880-18017 [NASA-TM-80166] 880-19033 SUKERT, A. N. TOOLEY, N. An analysis of software reliability prediction First experience with telemetry and real time data models reduction at Gates Learjet H80-19551 A80-27228 SULLIVAN, P. A. TOPPING, B. P. Research on the stability of air cushion systems Study of research and development requirements of (UTLAS-238] 880-17985 small gas-turbine combustors SUSSHOLZ, B. (NASA-CR-159796] 880-18040 Data reduction and analysis of graphite fiber TEAHOCCO, R. release experiments Failure mechanisms for advanced composite sandwich (NASA-CR-159032) 880-19048 construction in hostile environments SWET!, C. P. A80-26884 Report on the task force on aircraft separation TRIEBSTEIN, H. assurance, appendices Unsteady pressure measurements on wing-store [80-8077713] 880-18017 combinations in incompressible flow SZTMANSKI, N. A80-26269 A mass flovmeter with compensation for thermal TRIGG, N. N. density variations of the fluid A scientific approach to defeating helicopter A80-25220 vibration 880-25446 TRIEBA,A. K. T Air supply system approach for the Boeing Model TABACK, I. 767 Airplane Evaluation of equipment vulnerability and (SAE PAPER 791068] 880-26631 potential shock hazards TROT, B. F. B80-19197 Radiometric measurements of targets and clutter TABAKOPP, V. A80-26802 Flow measurements in a turbine scroll TSKHOVBEBOV, N. N. 180-27738 Theory of by-pass ducted-fan engines TAKAGI, T. 88 0-26 349 Local laminarization in turbulent diffusion flames TSURQSAKI, B.- 880-24819 Rotating stall in a vaneless diffuser of a TAN-ATICRAT, J. centrifugal fan Evaluation of a nw concept for reducing 880-27734 free-stream turbulence in wind tunnels TUCK, A. N. [8188 80-0432] 880-26942 A system for the measurement of the attitude of TARQUINIO, J. J. wind tunnel models Control of particulate emissions from turbine [AIAA 80-0465] 880-26962 engine test cells by cooling water injection TULLOCH, J. S. [80-8075947] 880-18587 Preliminary Airworthiness Evaluation 08-18 TASSINARI, B. helicopter equipped with Multiple Target Value analysis and the optimum cost concept Electronic Warfare System (NULTEWS) applied to aerospace [80-8078476] 880-19067 880-27202 TUPOLEV, A. A. TAYLOR, J. G. Local ground noise generated by supersonic A JTIDS performance model for the 8-38 transport planes 880-19825 880-26206 TAYLOR, J. T. TUNNEl, G. B. Design considerations for attaining 250-knot test Preliminary study of VTO thrust requirements for a velocities at the aircraft landing dynamics V/STOL aircraft with lift plus lift/cruise facility propulsion [NASA-TM-80222] N80-19132 [NASA-TM-81429] 880-19110 TESCNE, P. N. TIE, V. Computational techniques for EMP interaction The energy problem: Its effect on aircraft design. A80-27777 I - Supply and demand THIBODEAUX, J. J. A80-27752 Automatic control of NASA Langley's 0.3-meter cryogenic test facility [8188 80-0416] 880-26931 U THOMAS, D. D. DENDRA, N. Primary radar in ATC Measurement of stress distribution in sandwich 880-28381 beams under four-point bending THOMAS, P. 88 0-25498 Major areas of research in aeronautics and air UHLIN, J. G. traffic at the German Aerospace Research Experience from testing the Viggen electronic Establishment /DPVLR/ systems utilizing existing computer capacity 880-28491 A80-27235 THOMPSON, V. B. Consolidation of titanium powder to near net shapes [80-8078039] 880-19239
B-19
ULIANA, N. A. PERSONAL AUTHOR INDEX
ULIANA, N. A. WARAKONSKI, J. The Surface Contour Radar, a unique remote sensing AV-8B - A second generation V/STOL instrument (SAE PAPER 791070] 880-26633 880-26085 WARD, F. E. Development of a visual inspection technique (optical assessment of aircraft transparencies) V [80-8079369] 880-19086 VADALA, E. WARING, G. Failure mechanisms for advanced composite sandwich Failure mechanisms for advanced composite sandwich construction in hostile environments construction in hostile environments A80-26884 A80-26884 VAETH, J. C. WARNER, D. A. Airships - Basis for a new oceanic capability Flight path displays A80-28269 (AD-8077181) 1180-19107 VALDONI, P. WASHINGTON, V. D. The role of research applied to the air traffic Wind tunnel and flight test drag comparisons for a control system guided projectile with cruciform tails 880-28050 [1181 80-0426] 880-26968 VALENTINE, D. T. WASSERBAOEE, C. FORTRAN program oblique in PL-format users manual Effect of temperature on surface noise [80-8077809] N80-19880 A80-28419 VANWOERKON, K. WEAVER, C. G., II Aspects of flight test instrumentation Minimum-mass designs of stiffened N80-19098 graphite/polyimide compression panels VART!, D. A80-27992 The re-organization of airport administration in NEBB, B. N. Canada A low cost airborne data acquisition system 880-25245 A80-27231 VAUGHN, J. C., III WEBER, B. J. Hultirole cargo aircraft options and configurations Aeropropulsion in year 2000 [SAE PAPER 791096] 880-26645 [NASA-TH-81416] N80-18043 VEDENEEVA, N. P. WELLS, K. Induced drag and lift-drag ratio of swept wings at A mission training simulator for the Nimrod HR BK supersonic speeds 2 and some aspects of the derivation and 880-27175 verification of its system models VERBBUGGE, R. A. 1180-19826 Wind tunnel and free flight model identification WELP, D. experience Avionics evaluation program: Simulation models 1180- 19103 for the effectiveness analysis of avionics VINH, N. I. 1180-19838 Trajectories optimization in hypersonic flight VERNE!, N. [NASA-CR-162846] 1180-19026 The future development of air traffic as seen by VINSON, J. R. airline companies minimum-mass designs of stiffened A80-28487 graphite/polyinide compression panels WHALE!, P. V. 880-27992 Angular vibration measurement techniques VOEVODIN, A. V. 1180-18222 Analysis of the nonuniqueness of solutions to the WHITE, A. P. problem of flow separation for small-aspect Reliability management of the avionic system of a delta wings military strike aircraft 880-27127 1180-19546 VOLE, D. WHITE, R. A. Coming civil transport aircraft with active' The simulation and modeling of jet plumes in wind control elements tunnel facilities A80-28493 [8188 80-0430] 180-26941 VOLYNETS, V. A. WHITE, B. W. Airport radio navigation systems Production Eagle and its potential 880-27716 [SAE PAPER 791071] 180-26634 WHITE, W. P. Flight performance of the TCV 8-737 airplane at W Jorge Newberry Airport, Buenos Aires, Argentina WAFFORD, J. H. using TRSB/NLS guidance Application of MIL-STD--810C dynamic requirements [NASA-TH-80223] 1180-18021 to USAF avionics procurements WIETING, A. B. 1180-19091 Evaluation of finite element formulations for WAGNER, B. transient conduction forced-convection analysis Yawed slender wings at small angles of attack A80-28284 A80-26268 WIGELAND, N. A. WAGNER, D. A. Evaluation of a new concept for reducing Laser-Raman flow-field diagnostics of two large free-stream turbulence in wind tunnels hypersonic test facilities [AIAA 80-0432] 180-26942 [80-8078289) 1180-19135 WIGNOT, J. R. EARl, !. K. Structural design of transport airplanes for Easy ACLS dynamic analysis, volume 2. Part 2: transient environments Component computer programs A80-27898 [80-8079803] 1180-19076 WILCOX, B. N. WALKINCTON, J. N. A time-shared monopulse approach to air/surface Achieving effective Radar Cross Section flight radar ranging profiles on the-B-1 aircraft A80-26791 880-27227 WILHELN, K. WALSH, E. J. Closed loop aspects of aircraft identification The Surface Contour Radar, a unique remote sensing N80-19104 instrument WILLIAMS, V. D. A80-26085 Laser-Raman flow-field diagnostics of two large WALTERS, B. V. hypersonic test facilities microprocessor control of low speed V/STOL flight [80-8078289] 1180-19135 [AD-A077661] 1180-19129
8-20 PERSONAL AUTHOR INDEX ZUNARY, I.-G..
WILLIANSON, J. N. YENNI, N. N. Development and flight test of a two-place Early flight test experience with Cockpit night/adverse weather A-10 for the close-air Displayed Traffic Information (CDTI) support and battlefield attack mission [NASA-TN-80221] N80-18037 [SAN PAPER 791069] A80-26632 YIP, I. P. WILSON, N. P., JR. Exploratory investigation of the effects of vortex Study of research and development requirements of bursting on the high angle-of-attack small gas-turbine combustors lateral-directional stability characteristics of (NASA-CE-159796] N80-18040 highly-swept wings WILTON, N. N. [AIAA 80-0463) A80-26960 Advanced infrared signature prediction program. TOSHINAGA, Y. Spectral calculation of radiation from a turbine Aerodynamic performance of a centrifugal propulsion system as intercepted by an observer compressor with vaned diffusers (SCORPION). Volume 3: Analysis A80-27735 (AD-A078436) N80-19124 !UNCZTK, N. P. WIIDHAN, J. N. New remotely piloted vehicle launch and recovery Application of Nd:YAG optical communications concepts: Computer program listings technology for aircraft to satellite links [AD-A076611] N80-18035 A80-26797 New remotely piloted vehicle launch and recovery WINGNOVE, B. C. concepts. Volume 1: Analysis, preliminary Aircraft motion analysis using limited flight and design and performance/cost trade studies radar data (AD-A077475] N80-19066 A80-27241 NITTENBERG, N. Aviation safety and its improvement (VTH-LR-260] N80-18014 ZADANIONSKI, J. B. WOLANSEI, N. N. CADD on the F-IS program Fastener hole quality, volume 1 A80-26345 (AD-A077859] N80-19567 ZHNOLIN, B. N. WOLF, J. D. Local ground noise generated by supersonic Application of Nd:YAG optical communications transport planes technology for aircraft to satellite links A80-26206 A80-26797 ZIEN, T. P. WOLF, S. N. D. An experimental study of two-dimensional The development of a self-streamlining flexible supersonic jet impingement on a flat plate walled transonic test section [AD-A016536] N80-17996 (AIAA 80-0440] A80-26964 ZINNENNAN, 0. N. WOOD, B. A. Laser anemometer measurements at the exit of a 163 USAF damage tolerant design handbook: Guidelines combustor for the analysis and design of damage tolerant A80-27737 aircraft structures, revision A ZINBEN!ANN, U. [AD-A078216] N80-19065 Dynamic environments and test simulation for WOOD, N. qualification of aircraft equipment and external Hybrid optical/digital processing for target stores identification 1180-19092 A80-26867 ZUNAEV, T. C. WOODS, N. N. Calculation of minimum-weight and maximum-rigidity Reliability growth models structures in the presence of design Constraints N80-19522 A80-27165 WUNDERLICH, C. Air-to-air engagement simulation N80-19834 WUNNENBENG, H. Comparison of aerodynamic coefficients obtained from theoretical calculations wind tunnel tests and flight tests data reduction for the alpha jet aircraft [NASA-TN-75237] N80-17991 Y YANG, D. Nondestructive evaluation of airport pavements. Volume 2: Operational manual for PAVEEN program at TCC [AD-A079 1495] N80-19130 YANG, N. C. Nondestructive evaluation of airport pavements. Volume 1: Program references [AD-A078835] N80-18051 YANG, T. Y. Flutter analysis of a NACA 64A006 airfoil in small disturbance transonic flow A80-28851 YAPLEE, B. S. Radiometric measurements of targets and clutter A80-26802 YBANBA, A. N. Low speed test of the aft inlet designed for a tandem fan V/STOL nacelle [NASA-CB-159752] B80-18042 YEACEN, N. B. Digital computer solution of aircraft longitudinal and lateral directional dynamic characteristics [AD-A078672] N80-19068 YENONET, A. I. A collision avoidance system using Navstar/GPS and ATCEBS A80-25 157
8-21 CONTRACT NUMBER INDEX
AERONAUTICAL ENGINEERING IA Continuing Bibliography (Supp/. 123) JUNE 1980
Typical Contract Number Index Listing E33615-77—C-2086 NSG-1511 880-17992 S80-19120 NSG-2269 880-18038 F33615-77—C-2096 RSG-2288 880-194514 NAS2-9344 880-11097 880-19 117 NSG-3066 A80-27738 F33615-77—C-3011 RSG-3179 A80-26895 H80-19128 NSG-7172 A80-26964 CONTRACT I NASA ACCESSION F33615-77—C-3043 N00014-76—C-0494 NUMBER NUMBER [ N80-19044 880-18343 F33615-77—C-3054 N00014-77—C-0062 880-19076 880-19880 Listings In this index are arranged alphanumerically by contract number. F33615-77—C-3060 U00014-77—C-0326 880-18033 Under each contract number, the accession numbers denoting documents 880-19693 F33615-77—C-3067 N00014-77—G-0069 that have been produced as a result of research dove under that contract 880-19064 880-19114 are arranged in ascending order with the /AA accession numbers appearing F33615-77—C-5169 N00019-78—C-0304 lust. The accession number denotes the number by which the citation is A80-27783 880-19509 identified in either the IAA or STAR section. F33615-78—C-2018 N00019-78—c-0470 1180-19 125 880-19045 F33615-78—C-2041 1100123-76—C-0195 Al PROJ. 139A DA PROJ. 1L1-62209—Ali-76 880-19118 N80-19549 - 880-19070 880-18450 F33615-78—C-2065 N00140-76—C-1072 1? PROJ. 14860 DA PROJ. 1L2-62209—AH-76 1180-19429 N80-19124 880-19567 880-18037 F336 15-78—C-3404 N60921-78—C-0014 Al PROJ. 1900 N80-19033 N80-18035 880-19087 880-18587 DA—ERO-78—G-028 880-19066 1162269-76—C-0342 Al PROJ. 2090 A80-26941 F33615-78—C-3412 N80-19061 N80-19128 DAAA09-76--2001 180-19075 880-19072 'Al PROJ. 2202 A80-26968 F33615-78—C-3604 880-19073 880-19082 DAAG29-76—G-0209 A80-26640 N62269-77—C-0251 Al PROJ. 2307 A80-26941 F33615-78—C-3614 880-19053 880-18001 DAAG46-78—C-0008 N60-19107 N62269-77—C-0278 880-18002 N80-19080 F33615-78—c-5105 R8G-19085 880-19075 DAAK70-78—C-0200 880-19948 N62269-77—C-0352 N80-19120 880-18419 F33615-78—C-5203 880-19123 880-19569 DAAK70-79—C-0060 N80-18161 N62269-77—D-0118 A? PROJ. 2313 N80-18206 S80-18162 A80-25165 880-19051 DARPA ORDER 3575 P33615-79—C-3217 N62269-78—C-0213 880-19086 N80-18161 A80-26888 N80-19435 A? PROJ. 2401 DOT—FA68WAI-145 F33657-7 1—c-0567 N62269-78—C-0267 N80-19065 N80-18259 880-19105 880-19062 A? PROJ. 2402 DOT-1A75WA-3707 F33657-78—C-0473 N62269-79—C-0020 880-18033 N80—i8008 880-19843 N80-19824 880-18035 DOT-1A778A-3964 F44 620-75—C-0047 862269-79-8-3221 880-19066 880-18051 N80-18001 880-19083 Al PROJ. 2403 880-19130 1180-18002 N66269-78—C-0191 880-19064 DOT—PA78WA-4152 149620-77—C-0023 880-19049 N80-19107 880-18052 N80-19027 PROJECI SQUID A? PROJ. 2404 DOT-1A788A1-840 N80-19052 A80-27746 880-19044 880-18259 880-19084 RR0141184 880-18343 880-19076 DOT-1A798A-4293 F49620-78—C-0067 SF55525401 880-19106 A? PROJ. 3006 880-19054 880-19051 STTA-77/98/3 13/00/481/75/86 N80-19117 DOT—HS-7-01716 NASW-3199 880-17987 1180-18003 A? PROJ. 3048 N80-19991 N80-17991 81140000 1180-19053 880-19119 FNV— ?— INK-82223-76-001-21 —001 880-19111 8141400000 1180-18013 Al PROJ. 3066 A80-26937 880-19 133 8141421000 1180-19046 880-18044 ?RV— F— INK-82223-77-00 1-21 —001 NAS1-13792 880-19549 ZP51524004 880-19106 880-19088 A80-26937 NAS1-14000 880-18104 505-04 1180-19495 N80-19109 ?NV—F — INK-82223-77-1 16-21-001 NAS1-14031 880-19566 505-06-13-01 880-17988 N80-19115 A80-26937 NAS1-14449 N80-19063 505-10-13-07 880-19030 N80-19116 FNV— ?— IRK-82223-78— 003 — 21-001 NAS1-14597 880-17989 505-10-27 1180-18030 880-19118 A80-26937 NAS1-14719 880-18020 505-11-41 880-19126 A? PROJ. 3145 P09603-77—A-0204 NAS1-14849 880-19030 505-31-3 880-17984 880-18311 N80-19081 NAS1-15069 880-18103 505-31-53-01 880-19131 N80-19079 F19629-77—C-0168- NAS1-15319 880-19200 505-32-03-03 880-18884 N80-19125 N80-16624 NAS1-15465 880-19048 505-33-43 880-18109 N80-19429 F33615-74—C-5114 NAS1-15497 880-18031 505-35-21 880-18038 Al PROJ. 6065 880-19239 NAS2-9015 880-18029. 505-41-13-02 880-19023 N80-19041 F33615-75—C-2052 880-18030 505-42-62 880-18042 A? PROJ. 6190 880-18044 NAS2-9430 880-19055 505-43-23-04 880-17993 N80-19064 133615-75—C-3016 NAS3-20578 R80-19113 505-43-24-00 R80-17986 Al—A POSR-77-3355 880-19268 NAS3-21267 A80-27737 513-54-11 880-18047 A80-28018 F33615-75—C-3105 RAS3-21468 880-18042 514-50-01 880-18030 Al—A P038-77-3412 880-19082 NAS3-21980 880-18040 516-58-11 880-19127 A80-26934 ?33615-76—c-1002 NAS7-100 880-18364 530-03-13-02 880-19024 A?—APOSR-78-3523 A80-26797 880-19499 530-04-13-01 880-18011 A80-28851 F33615-76—C-2092 NAS8-33095 880-19703 1180-18032 ARPA ORDER 2656 880-19 109 NAS8-33382 880-19861 532-02-11 880-19022 880-18624 880-19115 88 PROJ. 215-246 534-03-23-01 880-19193 ASPA ORDER 3575 N80-19116 880-18343 534-04-13-57 880-18037 N80-18162 F33615-76—C-3113 NSG-1308 1180-17994 534-04-13-62 880-18021 CNR-78,02427,07 880-19567 NSG-1321 A80-28284 791-40-43-01 880-18988 A80-27745 F33615-77—C-0535 830-1419 A80-26935 992-23-10-90-03 DR PROJ. 1L1-62111—AH-71 NB 0-19 086 NSG-1448 880-19026 N80-18985 880-18024 F33615-77—C-2042 NSG-1451 A80-26942 N80-19119 NSG-1488 A80-27992
c—i 3. Recipients Catalog No. 1. Report No. 2. Government Accession No. NASA SP-7073 (123) 5. Report Date 4. Title and Subtitle June 1980 AERONAUTICAL ENGINEERING 6. Performing Organization Code A Continuing Bibliography (Supplement 123)
8. Performing Organization Report No. 7. Author(s)
10. Work Unit No. 9. Performing Organization Name and Address Aeronautics and Space Administration National 11. Contract or Grant No. Washington, D. C. 205+6
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 529 reports, articles, and other documents introduced into the NASA scientific and technical information system in May 1980.
17. Key Words (Suggested by Author(s)) 18. Distribution Statement Aerodynamics Unclassified — Unlimited Aeronautical Engineering Aeronautics Bibliographies
19. Security Oassif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price Unclassified Unclassified 156. $5.00 HC
For sale by the National Technical information Service. Springfield, Virginia 21 €i NASA-Langley, 1980 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC NASA distributes its technical documents and bibliographic tools to eleven special libraries located in the organizations listed below. Each library is prepared to furnish the public such services as reference assistance, interlibrary loans, photocopy service, and assistance in obtaining copies of NASA documents for retention.
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An extensive collection of NASA and NASA-sponsored documents and aerospace publications available to the public for reference purposes is maintained by the American Institute of Aeronautics and Astronautics. Technical Information Service. 555 West 57th Street, 12th Floor, New York, New York 10019 EUROPEAN
An extensive collection of NASA and NASA-sponsored publications is maintained by the British Library Lending Division, Boston Spa, Wetherby, Yorkshire, England By virtue of arrangements other than with NASA. the British Library Lending Division also has available many of the non-NASA publications cited in STAR. European requesters may purchase facsimile copy of microfiche of NASA and NASA-sponsored documents, those identified by both the symbols "i" and "s". from. ESA - Information Retrieval Service, European Space Agency. 8-10 rue Mario-Nikis, 75738 Paris CEDEX 15, France. ,,ritional Aeroncuucs dflCi Th-cHD-CLASS BULK HATE 3 r National Aeronautics and Space Administration Space Administration Washington, D.C. NASA-451 20546 U.S. MAn. Official Business ,
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NUMBER TITLE FE NASA SP-7011 AEROSPACE MEDICINE ANI Aviation medicine, space medic space biology NASA SP-7037 AERONAUTICAL ENGINLtc Engineering, design, and operation of aircraft and aircraft components NASA SP-7039 NASA PATENT ABSTRACTS BIBLIOGRAPHY Semiannually NASA patents and appiicatijr,s (us patent NASA SP-7011 EARTH RESOURCES Quarterly Remote sensing of earth resources by aircraft and spacecraft NASA SP-7043 ENERGY Energy sources, solar energy, conversion, transport, and storage NASA SP-750{) MANAGEMENT Program, contract, anl management, and marsa
DeWils on ih ovcia/abil:ty of these pr.rblica?fons may be oOtG 7- 7 SCIENTIFIC AND TECHNICAL INFORMATION OFFIC NATIONAL AERONAUTICS AND SPACE ADMiNISTRA Washington, D.C. 20546