ft • f^^m Jt Aeronautical NASA SP-7037(145) \\ I/%%i/\ Engineering February 1982 eg ^VV ^^•Pv % A Continuin9 Bibliography with Indexes

National Aeronautics and Space Administration

i' c Aeronautica• ^ l Engineerin•• ^^ • ^"— *g ^^ Aero* n (NASA-SP-7037 (1U5) ) AERONAUTICAL N82-21138 •^I ENGINEERING. A CONTINUING BIBLIOGRAPHY WITH _ ^NDEXFS (National Aeronautics and Space \ p^^^il Administration) 100 p HC $5.00 CSCL 01A ^al Engineering Aeronautical Er lautical Engineering Aeronautic Aeronautical Engineering Aeror sring Aeronautical Engineering ngineering Aeronautical Engine :al Engineering Aeronautical Er lautical Engineering Aeronauts Aeronautical Engineering Aeror 3ring Aeronautical Engineering NASASP-7037(145)

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

(Supplement 145)

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

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

Scientific and Technical Information Branch 1982 National Aeronautics and Space Administration Washington, DC This supplement is available as NTISUB/141/093 from .the National Technical Information Service (NTIS), Springfield, Virginia 22161 at the price of $5.00 domestic; $10.00 foreign. INTRODUCTION

Under the terms of an interagency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering. The first issue of this bibliography was published in September 1970 and the first supplement in January 1971. This supplement to Aeronautical Engineering -- A Continuing Bibliography (NASA SP- 7037) lists 326 reports, journal articles, and other documents originally announced in January 1982 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. .It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged in two major sections, IAA Entries and STAR Entries, in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally in IAA and STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes -- subject, personal author, and contract number -- are included. An annual cumulative index will be published. AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A82-10000 Series) All publications abstracted in this Section are available from the Technical Information Service, American Institute of Aeronautics and Astronautics, Inc. (AIAA), as follows: Paper copies of accessions are available at $8.00 per document. Microfiche*1) of documents announced in IAA are available at the rate of $4.00 per microfiche on.demand, and at the rate of $1.35 per microfiche for standing orders for all IAA microfiche. ...

Minimum air-mail postage to foreign countries is $2.50 and all foreign orders are shipped on payment of pro-forma invoices.

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

STAR ENTRIES (N82-10000 Series) One or more sources-from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviations are listed below. If the publication is available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line.

Avail: NTIS. Sold by the National Technical Information Service. Prices for hard copy (HC) . and microfiche (MF) are indicated by a price code preceded by the letters HC or MF in the STAR citation..Current values for the.price codes are given in the tables onpagevii. 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 $4.00 price, for those documents identified by a # symbol.)

Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration, Public Document Room (Room 126), 600 Independence Ave., S.W., 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.

(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). 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.

GENERAL AVAILABILITY

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

American Institute of Aeronautics and National Technical Information Service Astronautics 5285 Port Royal Road Technical Information Service Springfield, Virginia 22161 555 West 57th Street, 12th Floor New York, New York 10019

Pendragon House, Inc. British Library Lending Division, 899 Broadway Avenue Boston Spa, Wetherby, Yorkshire, Redwood City, California 94063 England

Commissioner of Patents and Superintendent of Documents Trademarks U.S. Government Printing Office U.S. Patent and Trademark Office Washington, D.C. 20402 Washington, D.C. 20231

University Microfilms Department of Energy A Xerox Company Technical Information Center 300 North Zeeb Road P.O. Box 62 Ann Arbor, Michigan 48106 Oak Ridge, Tennessee 37830

ESA-lnformation Retrieval Service University Microfilms, Ltd. ESRIN Tylers Green Via Galileo Galilei London, England 00044 Frascati (Rome) Italy

Fachinformationszentrum Energie, Physik, U.S. Geological Survey Mathematik GMBH 1033 General Services Administration 7514 Eggenstein Leopoldshafen Building Federal Republic of Germany Washington, D.C. 20242

Her Majesty's Stationery Office P.O. Box 569, S.E. 1 U.S. Geological Survey London, England 601 E. Cedar Avenue Flagstaff, Arizona 86002

NASA Scientific and Technical Information Facility P.O. Box 8757 U.S. Geological Survey B.W.I. Airport; Maryland 21240 345 Middlefield Road Menlo Park, California 94025

National Aeronautics and Space Administration Scientific and Technical Information U.S. Geological Survey Branch (NST-41) Bldg. 25, Denver Federal Center Washington, D.C. 20546 Denver, Colorado 80225 NTIS PRICE SCHEDULES

Schedule A STANDARD PAPER COPY PRICE SCHEDULE

(Effective January 1. 1982)

Price Page Range North American Foreign Code Price Price A01 Microfiche S 4.00 S 8.00 A02 001-025 6.00 12.00 A03 026-050 7.50 15.00 A04 051-075 9.00 18.00 A05 076-100 10.50 21.00 A06 101-125 12.00 24.00

A07 126-150 13.50 27.00 A08 151-175 15.00 30.00 A09 176-200 16.50 33.00 A10 201-225 18.00 36.00 A11 226-250 19.50 39.00

A12 251-275 21.00 42.00 At3 276-300 22.50 45.00 A14 301-325 24.00 48.00 A15 326-350 25.50 51.00 A16 351-375 27.00 54.00

A17 376-400 28.50 57.00 A18 401-425 30.00 60.00 A19 426-450 31.50 63.00 A20 451:475 33.00 66.00 A21 476-500 34.50 69.00

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

A99- Write for quote

1/ Add $1.50 for each additional 25 page increment or portion thereof for 601 pages up.

21 Add $3.00 for each additional 25 page increment or portion thereof for 601 pages and more

Schedule E EXCEPTION PRICE SCHEDULE Paper Copy & Microfiche

Price North American Foreign Code Price Price E01 $ 6.50 $ 13.50 £02 7.50 15.50 E03 9.50 19.50 E04 11.50 23.50 EOS 13.50 27.50

E06 15.50 31.50 E07 17.50 35.50 £08 19.50 39.50 £09 21.50 43.50 £10 23.50 47.50

E11 25.50 51.50 E12 28.50 57.50 £13 31.50 63.50 £14 34.50 69.50 £15 37.50 75.50

E16 40.50 81.50 E17 43.50 88.50 E18 46.50 93.50 E19 51.50 102.50 £20 61.50 123.50

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

Page IAA ENTRIES (A82-10000) 1 STAR ENTRIES (N82-10000) 25

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

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED DOCUMENT -AVAILABLE ON MICROFICHE - N82-10021*|C Kansas Univ. Center for Research, Inc.. Lawrence. Flight Research Lab." NASA ACCESSION •ICING TUNNEL TEST OF A GLYCOL EXUDING POROUS NUMBER LEADING EDGE ICE PROTECTION SYSTEM ON A GENERAL CORPORATE AVIATION AIRFOIL Final Report SOURCE - David L Kohlman. William G. Schweikhard. and Alan E. Albright TITLE - Sep. 1981>'37 p refs -(Grant NAG3-71) - (NASA-CR-165444: KU-FRL-464-11 Avail: NTIS- -PUBLICATION HC A03/MF A01 CSCL 01C-" DATE AUTHORS- Test results show that the system is very effective in preventing ice accretion (anti-ice mode) or removing ice from an airfoil. Minimum glycol flow rates required for antiicing are a CONTRACT function of velocity, liquid water content in the air. ambient -AVAILABILITY OR GRANT- temperature, and droplet size. Large ice caps were removed in SOURCE only a few minutes using anti-ice flow rates, with the shed time being a function of the type of ice. size of the ice cap. angle of attack, and glycol flow rate. Wake surveys measurements REPORT show that no significant drag penalty is associated with the -COS ATI NUMBER- installation or operation of the system tested. T.M CODE

TYPICAL CITATION AND ABSTRACT FROM IAA

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

ENGINEERING A Continuing Bibliography (Suppl. 145) FEBRUARY 1982

telemetry links. A backup flight control system for emergency operation resides in one of two onboard computers. Other functions IAA ENTRIES of the onboard computer system are uplink processing, downlink processing, engine control, failure detection, and redundancy man- agement. This paper describes the architecture, functions, and flight qualification of the HiMAT onboard flight computer systems. (Author)

A82-10049 Three navigation systems and their costs of A82-10083 H Synchronous fault-tolerant flight control acquiring remote sensing data. D. L. Hawley (EG & G, Inc., Las systems. T. B. Smith (Charles Stark Draper Laboratory, Inc., Vegas, NV). In: American Society of Photogrammetry, Annual Cambridge, MA). In: Computers in Aerospace Conference, 3rd, San Meeting, 46th, St. Louis, MO, March 9-14, 1980, ASP Technical Diego, CA, October 26-28, 1981, Collection of Technical Papers. Papers. Falls Church, VA, American Society of New York, American Institute of Aeronautics Photogrammetry, 1980, p. 426-431. and Astronautics. 1981, p. 55-60. 5 refs. (AIAA 81-2109) Three types of navigational systems have been analyzed and Synchronous fault-tolerant systems have some unique advan- evaluated as to their capabilities for data acquisition. Two basic tages over asynchronous systems, particularly as the flight control systems, visual navigation and strobe-aided navigation, are useful for task becomes more complex. One of the advantages is related to daylight photographic flights. One additional system, more technical, channel fault-detection. Asynchronous systems must rely upon is the microwave ranging system, crucial to the acquisition of setting fault thresholds for detecting computational failure within a multiple nighttime scanner data flights. These systems have been channel. The design of the threshold can be a difficult problem. analyzed as to their capabilities and costs. A table of mission There is a rule that a fault must be present for a number of frames to requirements and navigation techniques is presented. These types of be significant. These problems are largely avoided with synchronous studies are not unique, however in this paper, the information is systems, outputs are identical, and a single test of exact agreement is presented in a comparison unique to the equipment involved. This a perfect test. Noisy and skew effects which plague asynchronous comparison is presented relating the cost of the navigation systems fault detection have no effect. Other advantages of synchronous and the costs of their use. The result is a time and dollar comparison fault-tolerant systems are related to sensor fault-detection and of these navigation systems. (Author) multimode operation. Attention is given to the reasons for the present preponderance of asynchronous designs, and the use of A82-10081 H KC-135 Avionics Modernization Hot Bench. J. tightly synchronized processing. G.R. L. Archdeacon and C. E. Wilent (TRW Defense and Space Systems Group, Dayton, OH). In: Computers in Aerospace Conference, 3rd, A82-10096 H Integration of computer graphics design with San Diego, CA, October 26-28, 1981, Collection of Technical Papers. analytical models. R. J. Ricci (Lockheed-California Co., Burbank, New York, American Institute of Aeronautics CA). In: Computers in Aerospace Conference. 3rd, Sari Diego, CA, and Astronautics, 1981, p. 32-40. 10 refs. Contract No. F33600-80-C-0473. (AIAA 81-2105) October 26-28, 1981, Collection of Technical Papers. The U.S. Air Force has embarked upon an avionics update New York, American Institute of Aeronautics and program for the KC-135 Stratotanker fleet. An overview is provided Astronautics, 1981, p. 144-149. (AIAA 81-2134) of the KC-135 Avionics Modernization Hot Bench (AMHB). The The development of Computer-Augmented Design and Manufac- objective of the AMHB is to support conceptual definition of a turing (CADAM), an interactive computer graphics system is dis- representative KC-135 modernized avionics system. The KC-135 cussed. The system is used throughout the design process from AMHB consists of the Modernization Avionics Suite (MAS), Environ- conceptual design through product support. In the conceptual design mental Systems Simulation (ESS), and the Hot Bench Monitor phase, basic three-view general arrangement drawings are developed. (HBM). Attention is given to actual avionics hardware, simulated These can be quickly and accurately converted into a three- avionic subsystems, avionic application tasks, system control, cockpit dimensional mathematical surface definition. From this information, device management, guidance and performance management, flight analysis data models are generated semi-automatically for input to •plan management, backup control, and hot bench performance batch computing programs. Major areas where analysis modelers have monitoring. The navigation system is also considered. TACAN, been developed include: parametric mission analysis, aerodynamic Doppler, and Digital Scan Converter data are preprocessed and drag modelers, structural finite element modelers, 1 g load and mass compared with INS data. G.R. distribution modelers, fuel tank and volume analyzers, and weight and balance modelers. (Author) A82-10082 ' 8 HiMAT onboard flight computer system archi- tecture and qualification. A. F. Myers, M. R. Earls (NASA, Flight A82-10100 ft The Space Shuttle vehicle checkout involving Research Center, Edwards, CA), and L. A. Callizo (Rockwell flight avionics software. J. T. B. Mayer (Intermetrics, Inc., Cam- International Corp., Los Angeles, CA). In: Computers in Aerospace bridge, MA). In: Computers in Aerospace Conference, 3rd, San Conference, 3rd, San Diego, CA, October 26-28, 1981, Collection of Diego, CA, October 26-28, 1981, Collection of Technical Papers. Technical Papers. New York, American Institute New York, American Institute of Aeronautics of Aeronautics and Astronautics, 1981, p. 41-54. (AIAA 81-2107) and Astronautics, 1981, p. 173-178. (AIAA 81-2141) Two highly maneuverable aircraft technology (HiMAT) remote- A description is presented of the process employed in generating ly piloted research vehicles (RPRV's) are being flight tested at NASA a vehicle test using the flight avionics software. The three types of Dryden Flight Research Center, Edwards, California, to demonstrate onboard software available to the verification engineer include flight and evaluate a number of technological advances applicable to future avionics software, vehicle utility software, and dynamic integrated fighter aircraft. Closed-loop primary flight control is performed from test software. In most cases the flight software was modified to a ground-based cockpit utilizing a digital computer and up/down perform the desired functions in a manner devised by the test A82-10101

engineer. Attention is given to vehicle test development, test painting facilities used in the fabrication of aircraft parts. These verification, vehicle test execution, and vehicle test considerations. parts, and especially those of major weapon systems, are not, The reported investigation shows that it should be possible in future however, easily amenable to automation. Critical operations are systems to control the cost of verification and checkout by designing automated by a five-level control hierarchy developed for a new the verification process in conjunction with the operational software. Automated Paint and Process Line with advanced software which There are operational tradeoffs that can greatly reduce the costs of provides operating flexibility. A variety of part sizes and shapes are verification, which in the long run can reduce the total program cost. transformed into uniform handling units by special part holders. The G.R. chemical processing computer is programmed to handle ten loads of work simultaneously. A painting robot is programmed by painting a A82-10101 /! Bridging the gap from aircraft to space com- selected target with a spray gun attached to the arm of the puters. P. Mitchell and C. Vlcek (Itek Corp., Applied Technology manipulator with the robot in a 'teach' mode. Systems will be added Div., Sunnyvale, CA). In: Computers in Aerospace Conference, 3rd, later to automatically track shop orders and control chemical San Diego, CA, October 26-28, 1981, Collection of Technical Papers. solutions. J.F. New York, American Institute of Aeronautics and Astronautics, 1981, p. 179-186. 7 refs. (AIAA 81-2142) A82-10125 H Use of Space Shuttle technology in conven- This paper investigates the design problems associated with tional aircraft. W. A. Ragsdale (Intermetrics, Inc., Houston, TX). In: avionics and space computers, and identifies those which are Computers in Aerospace Conference, 3rd, San Diego, CA, October common to both, versus those which are unique to a specific 26-28, 1981, Collection of Technical Papers. application. Based on historical developments and predictions of New York, American Institute of Aeronautics and Astronautics, future needs, a plan is presented which resolves many of these 1981, p. 358-361. 7 refs. (AIAA 81-2176) problems and supports real-time technology insertion in a low cost, A number of advances in the state-of-the-art for aircraft systems rapid deployment approach. A computer development program is and procedures have been implemented in the Space Shuttle. Much described which utilizes a modular family of functional elements, of the new technology used would benefit conventional aircraft, allowing a wide variety of space and aircraft requirements to be met especially airliners. Automatic systems management as employed for using common hardware. Continuing development activities have the Shuttle would simplify the task of flying an airliner. The pilot is expanded this system architecture into a highly fault tolerant and given by the computer only the information he needs to know. The flexible family of computers with incremental design steps depending area navigation (RNAV) system used by the Space Shuttle is heavily on existing qualified hardware and software elements. three-dimensional RNAV. It steers the Space Shuttle not only to a (Author) latitude and longitude, but to a specific altitude. The use of a four-dimensional RNAV, including also the monitoring of time, would provide additional advantages. A use of RNAV systems in A82-10104 # Airborne associative processor /ASPRO/. T. aircraft makes possible savings in the consumption of fuel and leads DiGiacinto (Goodyear Aerospace Corp., Digital Technology Dept., to simplifications-in air traffic control. Further reduction in fuel Akron, OH). In: Computers in Aerospace Conference, 3rd, San consumption can be obtained with the aid of energy management Diego, CA, October 26-28, 1981, Collection of Technical Papers. approaches. Additional advantages for aircraft operations can be New York, American Institute of Aeronautics obtained by the employment of the Microwave Landing System and and Astronautics, 1981, p. 202-205. (AIAA 81-2145) digital fly-by-wire flight controls. G.R. The ASPRO associative processor is designed for an airborne early warning radar surveillance, command and control application. It augments the existing data processors aboard a surveillance A82-10126 # A microprocessor-based data acquisition sys- aircraft. The functional requirements of ASPRO call for extraordi- tem for stall/spin research. M. Sri-Jayantha and R. F. Stengel nary processing capacity for its volume, weight and power con- (Princeton University, Princeton, NJ). In: Computers in Aerospace straints (less than 1/2 cubic foot). ASPRO development was made Conference, 3rd, San Diego, CA, October 26-28, 1981, Collection of feasible by designing the architecture to make use of available LSI Technical Papers. New York, American Institute components for arithmetic operations, addressing, program and of Aeronautics and Astronautics, 1981, p. 362-372. 25 refs. Research interrupt control. The memory and parallel processing sections of supported by the Shultz Foundation. (AIAA 81-2177) ASPRO required development of two special components, a multi- Accurate data are necessary for the identification of aero- chip memory package, and a custom 32-PE chip for the parallel dynamic parameters at high angle of attack and in spinning flight. processor. (Author) Modern sensors and microelectronic devices are employed in a stall/spin data acquisition system that will be tested in a Schweizer A82-10116 H Controlling the software/hardware interface 2-32 sailplane. This instrumentation package will use a quaternion- for the validation of avionics systems. T. G. Lahn and E. R. Rang based 'strapdown I ML)' algorithm to derive vehicle attitude from (Honeywell, Inc., Minneapolis, MN). In: Computers in Aerospace angular rate data, and it will use fault-detection logic to identify Conference, 3rd, San Diego, CA, October 26-28, 1981, Collection of in-flight sensor failures. Details of the system and flight test program Technical Papers. New York, American Institute are presented, together with results of pre-flight digital simulation of Aeronautics and Astronautics, 1981, p. 283-287. (AIAA 81-2159) analysis. (Author) A methodology is outlined for designing critical embedded avionics by exposing the hardware/software interface during the design and validation of the system. The proposed approach involves A82-10127 fi Real-time, on-line digital simulation of op- timum maneuvers of supersonic aircraft. C.-F. Lin (Applied Dynam- the development of a finite-state machine representation for the control of flow of the system's functions and implementation of the ics International, Ann Arbor, Ml). In: Computers in Aerospace finite-state machine by hardware and software. This produces a Conference, 3rd, San Diego, CA, October 26-28, 1981, Collection of complete structure that is easy to review and validate. The approach Technical Papers. New York, American Institute is demonstrated for a triply-redundant flight augmentation system. of Aeronautics and Astronautics, 1981, p. 373-381. (AIAA 81-2178) V.L. This paper discusses real-time simulation of automatic guidance and control computer system of a supersonic fighter including a complete simulation of the mission computer and the flight control A82-10120 H Automated Paint and Process Line /APPLA N. computer before connecting them as hardware in the loop. In this E. Manion (Lockheed-Georgia Co., Marietta, GA). In: Computers in simulation the mission computer generates real-time, on-line optimal Aerospace Conference, 3rd, San Diego, CA, October 26-28, 1981, trajectories. These trajectories include maximum range glide and Collection of Technical Papers. New York, minimum time zoom climb. They are then tracked by the flight American Institute of Aeronautics and Astronautics, 1981, p. 319, control computer. For this kind of simulation it is essential that the 321, 323 (3 ff.). (AIAA 81-2166) computational speed be very fast, thus a very fast computer with In an effort to control costs, the military and industry are real-time, on-line capabilities is used for the simulation. Results of pursuing ways to improve production efficiency by increasing the the simulation show that the mission computer is capable of degree of automation of factory operated chemical processing and generating online optimal trajectories much faster than real time, and A82-10220

that the flight control computer is capable of following very closely ry to help provide improved operational procedures for aviation these trajectories at the same speed. (Author) support are summarized. Quantitative data presentation and informa- tion assimilation now have greater importance, since Doppler radar is A82-1014Q § Performance analysis of enroute air traffic evolving toward operational use by weather services. Wind shear, control computers in the National Airspace System. J. Press (FAA, vortices, and turbulence, which constitute weather hazards to Systems Research and Development Service, Atlantic City, NJ). In: aviation, must be identified and measured, and effective ways to Computers in Aerospace Conference, 3rd, San Diego, CA, October disseminate information on the location, intensity, and movement of 26-28, 1981, Collection of Technical Papers. these hazards to the forecaster and pilot must be found. Despite the New York, American Institute of Aeronautics and Astronautics, progress made thus far, research is still required to better validate 1981, p. 485-495. 12refs. (AIAA 81-2203) radar signatures which identify storm hazards uniquely; even greater This paper describes a computer performance analysis recently advances are needed in the design of displays and types of data completed at the Federal Aviation Administration Technical Center parameterizations which will present significant information effi- for all twenty enroute air traffic control centers in the National ciently to the interpreter. It is suggested that user requirements be Airspace System. Based on linear regression, the analysis relied on included in the designs of future radar systems at an early stage to field data collected nationwide in order to quantify the performance reduce irrelevant information which complicates displays. J.F. of the central computer complex operating at each facility. The data was recorded every minute for several days while the computers were A82-10217 Description of the meteorological research supporting air traffic control operations. Graphs and tables sum- radar system aboard NOAA/Research Facilities Center WP-3D marize the study's results which will serve as a basis for management aircraft. J. D. DuGranrut (NOAA, Environmental Research Labora- plans concerning future system acquisition. As a major conclusion, tories, Miami, FL). In: Conference on Radar Meteorology, 19th, the methodology developed in this study applies consistently to all Miami Beach, FL, April 15-18, 1980, Preprints. enroute traffic control centers. (Author) Boston, MA, American Meteorological Society, 1980, p. 115-117. The radar system developed for the Research Facilities Center's A82-10143 # Interoperability testing of decentralized com- WP-3D airborne research platform provides data from three radar sets mand, control, communications and intelligence /C3I/ systems. E. G. recorded on computer-compatible media: the nose radar scans Ries (System Development Corp., McLean, VA) and R. C. Bjorklund horizontally over the range + or • 120 deg from the aircraft, heading (USAF, Tactical Air Command, Langley AFB.'VA). In: Computers at tilt angles of + or - 20 deg from the horizon. It operates at C-band in Aerospace Conference, 3rd, San Diego, CA, October 26-28, 1981, frequency (5445 MHz) and has a processed range of 100 nautical Collection of Technical Papers. New York, miles. The lower fuselage radar scans a full 360 deg horizontally at American Institute of Aeronautics and Astronautics, 1981, p. tilt angles of + or - 10 deg from the horizon; it also operates at 513-520. 8 refs. (AIAA 81-2205) C-band frequency (5370 MHz) and has a processed range of 200 The testing of complex, real-time C3I systems by conventional nautical miles. The tail radar scans a plane perpendicular to the methods requires considerable resources, time, and realistic opera- longitude axis of the aircraft; it operates at X-band frequency (9315 tional conditions. The decentralization of systems among diverse MHz) and has a processed range of 50 nautical miles. The data locations imposes further demands. Tactical Air Command is processing equipment of the radar data system is controlled by video developing the Simulation, Monitoring, and Analysis, Reduction, and integrator processors, scan converter display units, and magnetic tape Test System (SMARTS) to provide a controlled test environment for units. The radars may be operated without the data system for C3I systems, a design incorporating an operations-scenario generator display of weather avoidance and navigation information when data for efficient test design and analysis. SMARTS is a flexible test processing and recording are not required. A more detailed descrip- platform for Air Force and Joint interoperability testing, configura- tion is given of the receiver/transmitters, the antennas and antenna tion management, system testing, and software maintenance. The control units, the video integrator processors, the recording system, design of SMARTS provides intercommunications between geograph- and the real-time display system. J.F. ically separated test nodes, test control, recording, analysis, and simulation of radar and data communications for a synchronized test A82-10219 Airborne weather radar and severe weather environment. (Author) penetration. J. I. Metcalf (Georgia Institute of Technology, Atlanta, GA). In: Conference on Radar Meteorology, 19th, Miami Beach, FL, April 15-18, 1980, Preprints. Boston, MA, A82-10214 * Downbursts and microbursts • An aviation American Meteorological Society, 1980, p. 125-129. 6 refs. hazard. T. T. Fujita (Chicago, University, Chicago, IL). In: Confer- The effect of rain on airborne weather radar performance and its ence on Radar Meteorology, 19th, Miami Beach, FL, April 15-18, practical implications are examined. It is shown that whenever the 1980, Preprints. Boston, MA, American Meteoro- actual reflectivity is greater than 45 dBZ (rainfall rate in excess of 25 logical Society, 1980, p. 94-101. 12 refs. NSF Grant No. ATM-78- mm/hr), significant attenuation (greater than 0.5 dB/km one way) 01074; Grants No. NOAA-04-4-158-1; No. NGR-14-001-008. can be expected, leading to major distortions of the reflectivity Downburst and microburst phenomena occurring since 1975 are pattern observed with a 3-cm radar. Examples discussed illustrate the studied, based on meteorological analyses of aircraft accidents, aerial need for aircrews to obtain additional weather information including surveys of wind effects left behind downbursts, and studies of data from ground-based weather radars at any time when the sub-mesoscale wind systems. It is concluded that microbursts on-board radar shows weather echoes near the projected flight path, beneath small, air mass thunderstorms are unpredictable in terms of particularly when weather penetration is contemplated. V.L. weather forecast. Most aircraft incidents, however, were found to have occurred in the summer months, June through August. An intense microburst could produce 150 mph horizontal winds as well A82-10220 * An airport wind shear detection and warning as 60 fps downflows at the tree-top level. The largest contributing system using Doppler radar. J. McCarthy (National Center for factor to aircraft difficulties seemed to be a combination of the Atmospheric Research, Boulder, CO), W. Frost, B. Terkel (Ten- headwind decrease and the downflow. Anemometers and/or pressure nessee, University, Tullahoma, TN), R. J. Doviak (NOAA, National sensors placed near runways were found effective for detecting gust Severe Storms Laboratory, Norman, OK), D. W. Camp (NASA, fronts, but not for detecting downbursts. It is recommended that Marshall Space Flight Center, Huntsville, AL), E. F. Blick. and K. L. new detection systems placed on the ground or airborne, be Elmore (Oklahoma, University, Norman, OK). In: Conference on developed, and that pilots be trained for simulated landing and Radar Meteorology, 19th, Miami Beach, FL, April 15-18, 1980, go-around through microbursts. J.F. Preprints. Boston, MA, American Meteorological Society, 1980, p. 135-142. 7 refs. NSF Grants No. ATM- A82-10215 Applications of conventional and Doppler 74-03406-A02; No. ATM-78-12401; Contracts No. NAS8-31377; No. radars for aviation safety. J. T. Lee and K. E. Wilk (NOAA, National N AS 8-334 58. Severe Storms Laboratory, Norman, OK). In: Conference on Radar Two numerical models of aircraft performance are developed to Meteorology, 19th, Miami Beach, FL, April 15-18, 1980, Preprints. relate atmospheric wind signals in wind-shear situations to aircraft Boston, MA, American Meteorological Society, response. Both models produce time histories of pitch angle, 1980, p. 102-109. 24 refs. airspeed, height above the ground, and other parameters for Past and present efforts at the National Severe Storms Laborato- simulating aircraft making precision approaches along a 3-deg glide A82-10221 slope to the runway. Simulations conducted using thunderstorm shears invisible to the pilot's eye can be hazardous during takeoff and environment wind data indicate that the horizontal wind component approach maneuvers at low altitudes. M.S.K. is at least as important as the vertical component in determining aircraft response to wind shear. Obtaining quantitative measurements A82-10225 The evolution of airborne weather avoidance of aircraft approach or departure quality is found to depend on radar toward a calibrated remote rain gauge using REACT. J. F. several factors, including the knowledge of winds along the expected Clark (RCA, Princeton, NJ). In: Conference on Radar Meteorology, flight track, clear-air detection in a quasi-horizontal path, and a near 19th, Miami Beach, FL, April 15-18, 1980, Preprints. continuous estimate of approach deterioration due to shear condi- Boston, MA, American Meteorological Society, 1980, tions. D.L.G. p. 169-175. 5 refs. REACT (Rain Echo Attenuation Compensation Technique) is a A82-10221 * Instrumented aircraft verification of dear-air new digital system that compensates for precipitation attenuation in radar detection of low-level wind shear. J. McCarthy (National each small-range increment of each sweep by adaptively increasing Center for Atmospheric Research, Boulder, CO), K. L. Elmore the radar receiver sensitivity for the next range increment by an (Oklahoma, University, Norman, OK), R. J. Doviak, and D. S. Zrnic amount equal to the two-way attenuation through the original range (NOAA, Severe Storms Laboratory, Norman, OK). In: Conference increment. A Probable Ground Track and Weather Radar Plot of the on Radar Meteorology, 19th, Miami Beach, FL, April 15-18, 1980, Apr. 4, 1977 storm near New Hope, GA was published and used as Preprints. Boston, MA, American Meteorological the ground truth in plotting rainfall data. The storm was first Society, 1980, p. 143-149. NSF Grants No. ATM-74-03406-A02; No. depicted by conventional X-band and C-band radar, and the ATM-78-12401; Contracts No. NAS8-31377; No. NAS8-33458. resolution and range of these bands are compared. REACT was then A technique is described in which the longitudinal wind used with the PriMUS 708 solid-state radar; the plotted result of component at airports, measured by Doppler radar, is put through a precipitation attenuation was shown to agree well with the assumed Fourier transformation to produce an energy density spectrum. The ground truth. The PriMUS 708 airborne radar, compensated with result is multiplied by the aircraft response characteristics to produce REACT, combines the X-band advantage of higher resolution and quantitative data on aircraft performance in a wind shear situation. antenna gain with an accurate rainfall rate calibration. J.F. The Doppler radar measurements are made along the intended flight path. Two case studies, along a 3 deg approach path, are described from measurements in two modes: Lagrangian, where predictions A82-10292 Multiple Doppler radar observations of PBL were computed one range gate ahead of the plane, and Eulerian, structure. P. H. Hildebrand (National Center for Atmospheric where samples were measured instantaneously along the flight path. Researcn, Boulder, CO). In: Conrerence on Radar Meteorology, Wind data obtained every second were interpolated to fit a numerical 19th, Miami Beach, FL, April 15-18, 1980, Preprints. model by using a cubic spline. Eulerian data were superior to Boston, MA, American Meteorological Society, 1980, Lagrangian data in terms of ranging, and nearly equal for wind p. 656-661. NSF Grant No. ATM-76-24236. speeds. Improvements in current 75% accuracy are noted to be It is noted that during May and June of 1977, multiple Doppler possible with shrouded antennas to reduce sidelobes and use of radars, aircraft and other instrumentation were used to observe the Doppler radar with higher resolution to eliminate effects of small characteristics of the convectively growing planetary boundary layer scale disturbances within the pulse volume. M.S.K. (PBL) in Central Oklahoma. The observations were made between midmorning and afternoon when the PBL was growing quickly. A preliminary analysis of the data from one of the days is given. It is A82-10222 Detection and display of wind shear and found that data collected using such a large radar separation appear turbulence. J. Wilson, R. Carbone, and R. Serafin (National Center to be usable to describe large scale PBL kinematics. C.R. for Atmospheric Research, Boulder, CO). In: Conference on Radar Meteorology, 19th, Miami Beach, FL, April 15-18, 1980, Preprints. Boston, MA, American Meteorological Society, A82-10304 Helicopter engine technology - With particular 1980, p. 150-156. 9 refs. reference to the Rolls-Royce Gem engine. D. Lewis (Rolls-Royce, Displays of wind shear are given which are obtained by a Ltd., Watford, Herts., England). Aeronautical Journal, vol. 85, Sept. method for certain cases collected by NCAR 5 cm wavelength radars. 1981, p. 313-319. A Doppler radar located at an airport or in an aircraft measures the A description is presented of the design features incorporated by wind shear along flight paths on scales critical to aircraft operations. the Rolls-Royce Gem helicopter engine in light of the following The magnitude of the shear on the desired scale is then obtained by criteria: (1) high structural strength, to withstand low frequency measuring the wind shear over a distance of one-half the aircraft vibration and maneuvering loads; (2) optimization of low altitude phugoid wavelength. Four cases classified as severe storms show that performance; (3) operation over a wide power range; (4) high fuel significant wind changes occur within 0.5 to 3.0 km, which includes efficiency at part load power; (5) fast and surge-free acceleration and the phugoid wavelength of modern aircraft. It is suggested that a deceleration; (6) insensitivity to intake pressure disturbances; (7) practical solution for the detection of hazardous wind shear is to resistance to contaminated intake air; and (8) stability of control. It locate a scanning Doppler at an airport so that quantitative displays is observed that in general, the complexities introduced into of wind changes at the phugoid wavelength can be generated. D.L.G. helicopter engines of the last design generation to improve fuel consumption will be diminished in the next generation of engines for the sake of cost reduction. In addition to the Gem, these engines A82-10223 Gust front structure observed by Doppler include the GE T700 and U.S. Army ATDE. O.C. radar. R. J. Donaldson, Jr. and C. L. Bjerkaas (USAF, Geophysics Laboratory, Bedford, MA). In: Conference on Radar Meteorology, A82-10305 The application of improved aluminium alloys 19th, Miami Beach, FL, April 15-18, 1980, Preprints. and steels in aircraft structures. C. J. Peel and D. S. McDarmaid Boston, MA, American Meteorological Society, 1980, (Royal Aircraft Establishment, Materials Dept., Farnborough, Hants., p. 157-161. 6 refs. England). (Royal Aeronautical Society, Symposium on Develop- Two gust fronts (April 30 and May 2, 1978) are discussed as ments in Structures and Manufacturing Techniques, London, En- representative samples of operational data taken during the Joint gland, Apr. 14, 1981.) Aeronautical Journal, vol. 85, Sept. 1981, p. Doppler Operational Project of 1977-1979. Readings from the 10cm 320-326. 16 refs. Doppler radar at Norman, OK, during continuous recording at five or It is shown that development efforts in aircraft aluminum alloys six elevation angles were color coded and displayed for speeds in m/s, and steels over the last 20 years have generally sought to overcome range marked at one km intervals, and dated, with time of day such problems as a lack of resistance to fatigue and stress corrosion indicated. Charts provided show wind direction changes with the cracking rather than achieve increases in specific strength. Significant passage of a gust front and windspeeds at 0.3 km altitude to be improvements in fracture toughness and stress corrosion resistance double that of surface wind speeds, a factor considered important for have been achieved, and improved surface treatments are appearing aviators. Extreme wind shears within the fronts were taken as for steel products. Attention is given to new aluminum alloys evidence for severe vertical shears, which were not sensed by resulting from the addition of up to 3 wt % Li to AI-Mg, AI-Cu, and horizontally scanning radar. The effectiveness of the Doppler radar in AI-Cu-Mg systems, yielding increased stiffness and reduced density. identifying and ranging gust fronts commends it to airport use, where Improvements to 2000- and 7000-series aluminum alloys, rapid A82-10396

solidification production techniques, and corrosion protection for A82-10310 Optimal flight paths for winged, supersonic aircraft steels are also covered. O.C. flight vehicles • Extension to the case where thrust can be vectored. E. Large (Marconi Space and Defence Systems, Ltd., Stanmore, A82-10306 Design aspects of non rigid airship envelopes. Middx., England). Aeronautical Journal, vol. 85, Sept. 1981, p. J. A. I. Reid (Airship Industries, Ltd., London, England). (Royal 343-348. 5 refs. Aeronautical Society, Symposium on Developments in Structures A method for determining the optimal trajectory and thrust and Manufacturing Techniques, London, England, Apr. 14, 1981.) program of an aircraft or rocket employing vectored thrust is Aeronautics/Journal, vol. 85, Sept. 1981, p. 327, 328. derived, for the practical cases in which the entire thrusting phase is The design requirements of nonrigid airship envelopes are supersonic. It is shown that finding the burning program which gives addressed in light of recent advances in both (1) the estimation of the Hamiltonian function a zero value automatically satisfies the airship hull loadings under maneuvering and gusts and (2) high- optimal flight path conditions and makes the final fuel consumption strength fabrics for airship construction woven from polyamide, independent of time. It is found that the optimal burning program is polyester, and Kevlar fibers. Attention is given to the degree of not, except in special cases, one that employs constant thrust, the permeability by helium of hull and ballonet materials. When general optimum instead being a linear rate of thrust increase with determining safety factors for use with such nonmetallic materials, a time. O.C. factor characterizing the degradation of material strength with age must be added to those normally associated with strength calcula- A82-10362 H The use of the Weber method for tions. O.C. minicomputer-assisted numerical analysis of airfoils (Zastosowanie melody Webera do numerycznej analizy aerodynamicznej profili na A82-10307 Some possibilities for composite light aircraft minikomputerach). K. Czyzewski and M. Lukaszewicz. Instytut construction. J. H. Webb (Cranfield Institute of Technology, Lotnictwa, Prace, no. 85, 1981, p. 9-21. 21 refs. In Polish. Cranfield, Beds., England). IRoyal Aeronautical Society, Symposium A numerical version of the Weber method is developed for on Developments in Structures and Manufacturing Techniques, calculating pressure distribution over an airfoil in subsonic flow. The London, England, Apr. 14, 1981.j Aeronautical Journal, vol. 85, method is based on the fact that singularities representing the flow at Sept. 1981, p. 328-331. the airfoil surface are distributed chordwise, and a correction Alternative methods for the design and construction of light coefficient is introduced, with allowance for airfoil thickness. If the aircraft and remotely piloted vehicles with composite materials are airfoil shape is approximately represented by spline functions, described, with attention to the minimization of tooling, materials numerical analysis is simplified considerably and the accuracy is and construction man-hour costs. A four-seat, single-engine light improved. The present numerical results are compared with other aircraft is assumed for comparison of conventional metal and numerical results for subcritical and supercritical flow conditions, glass-reinforced plastic composite wing structure construction costs. and with wind-tunnel-test results. In addition, an iteration method Weight comparisons are also presented for three novel wing structure for determining the critical Mach number has been developed. B.J. design concepts: (1) a tubular spar with plastic foam core and fiberglass-reinforced skin; (2) a similar arrangement incorporating a A82-10363 I: Experimental study of subsonic and transonic metal spar; and (3) fiberglass-reinforced plastic foam sandwich skins flows past a wing (Eksperymentalne badania pod- i przydzwiekowego with a metal spar. The mixed metal/plastic composite structure is oplywu skrzydla). W. Kania and A. Krzysiak. Instytut Lotnictwa, incorporated into the Machan RPV, and has proven to be satisfactory Prace, no. 85, 1981, p. 23-44. 10 refs. In Polish. in recent flight trials. O.C. The paper reports aerodynamic balance measurements of aero- dynamic characteristics and flow visualization tests on a plane A82-10308 Light aircraft structural design in non-metallics trapezoidal uniform-section wing with a small sweepback angle. Tests - Use of composite honeycomb for light aircraft. G. E. Woodley were performed in a transonic wind tunnel for Mach numbers ranging (Ciba-Geigy Plastics and Additives Co., Duxford, Cambs., England). from 0.3 to 0.96 under conditions of fixed boundary layer (Royal Aeronautical Society, Symposium on Developments in transition. Lift, drag, and pitching moment were determined, with Structures and Manufacturing Techniques, London, England, Apr. attention given to the effect of Mach number. Shock wave formation 14. 1981.1 Aeronautical Journal, vol. 85, Sept. 1981, p. 332, 333. on the wing is examined, and flow separation and drag rise are Recommendations are made toward the application of high- determined. Four types of flow separation, depending on Mach technology prepreg composite systems for the production of number, are revealed; it is found that there is a correlation between nonmetallic honeycomb light aircraft structures. Attention is given the type of flow separation and the value of the lift coefficient at the to design and assembly methods for wings and control surfaces, with onset of separation, which depends on the Mach number. B.J. emphasis on the reduction of production costs "rather than weight saving. It is shown that the designer's aim should cut down the honeycomb panel piece parts required, thereby reducing the man- A82-10364 If Analytical determination of undercarriage re- hours cost of production, and that the use of composite honeycomb traction kinematics (Analityczne okreslanie kinematyki chowania materials results in a more damage-tolerant surface than conventional podwozia). R. Stanczak. Instytut Lotnictwa, Prace, no. 85, 1981, p. light aircraft structures, with a more accurate overall shape and 45-53. In Polish. reductions of both corrosion and fatigue. • O.C. An analytical method is developed for calculating the kinematics of undercarriage retraction. The method is particularly suitable for the design of high-wing and mid-wing monoplanes, the undercarriages A82-10309 Sophisticated aircraft structure developments - of which cannot be attached to the wing. Attention is given to Combat aeroplanes. R. J. Sellars and G. Terry (British Aerospace undercarriages with one and two rotation axes. B.J. Public, Ltd., Co., Warton Div., Preston, Lanes., England). (Royal Aeronautical Society, Symposium on Developments in Structures and Manufacturing Techniques, London, England, Apr. 14, 1981.) A82-10396 FAA developing new collision avoidance, data Aeronautical Journal, vol. 85, Sept. 1981, p. 334-342. Research acquisition and transmission systems. A. C. Schwartz. Airport supported by the Ministry of Defence (Procurement Executive). Forum, vol. 11, Aug. 1981, p. 93, 94, 96, 97. Comparisons of the structural materials and fabrication process- The U.S. Federal Aviation Agency (FAA) is concerned with the es currently under development and assessment in Britain for future development of an aircraft collision avoidance system which, it is combat aircraft construction are presented, with attention to the hoped, will be universally accepted as an aviation standard system. demonstration of carbon fiber reinforced composites (CFC) and The Discrete Address Beacon System (DABS) contains advanced superplastic forming/diffusion bonding of titanium alloy (SPF/DB) flight and data link equipment. According to the FAA program. in existing aircraft. CFC and SPF/DB structures are compared with DABS is to become the basis for a ground-based collision avoidance respect to specific tensile and compressive strengths and moduli, system called the Automatic TrafficAdvisory and Resolution Service specific shear strength and modulus, buckling, and ultimate design (ATARS). However, it was recently decided to review the DABS strengths and design criteria in the application of the materials to the ground station program before a final decision is made regarding the stabilized skins of combat-aircraft surfaces. Emphasis is put on the ground installations. Another decision is concerned with the imple- possibility of aeroelastic tailoring that is introduced by the applica- mentation of an airborne collision avoidance system called Threat tion of CFC to wing structures. O.C. Alert and Collision Avoidance System (TCAS). The TCAS is to take A82-10401 the place of the Beacon Collision Avoidance System (BCAS). TCAS performance characteristics thus determined as a function of the arm will operate independently of ground stations and use a highly ratio. (Author) directional transmitting antenna. To provide better information for en route air traffic controllers when the main radar system fails, FAA A82-10406 # Experimental determination of parachute is installing the Direct Access Radar Channel (DARC) at its 20 apparent mass and its significance in predicting dynamic stability. T. centers in the continental U.S. G.R. Yavuz and D. J. Cockrell (Leicester, University, Leicester, England). American Institute of Aeronautics and Astronautics, Aerodynamic Decelerator and Balloon Technology Conference, 7th, San Diego, A82-10401 * ft The balloon and the airship technological CA, Oct. 21-23, 1981, Paper 81-1920. 9 p. 6 refs. Research heritage. N. J. Mayer (NASA, Washington, DC). American Institute supported by the Ministry of Defence (Procurement Executive) and of Aeronautics and Astronautics, Aerodynamic Decelerator and Deutsche Forschungs- und Versuchsanstalt fiir Luft- und Raumfahrt. Balloon Technology Conference. 7th. San Diego, CA, Oct. 21-23, Experimental techniques to measure the components of the 1981, Paper 81-1912. 8 p. 7 refs. apparent mass tensor for parachutes are descrbed. They are evaluated The balloon and the airship are discussed with emphasis on the by force and moment measurement during relative motion of identification of commonalities and distinctions. The aerostat tech- parachutes submerged in water in a ship tank. Results show that the nology behind the shape and structure of the vehicles is reviewed, components depend on canopy shape, angle of attack and accelera- including a discussion of structural weight, internal pressure, buck- tion modulus and, except at high values of the latter, can be ling, and the development of a stable tethered balloon system. Proper considerably in excess of potential flow evaluations. The effect of materials for the envelope are considered, taking elongation and these results on the dynamic stability of descending parachutes is stress into account, and flight operation and future developments are demonstrated by reference to an appropriate computer model. reviewed. Airships and tethered balloons which are designed to carry General conclusions are drawn relevant to canopies whose shapes high operating pressure with low gas loss characteristics are found to differ from those tested. (Author) share similar problems in low speed flight operations, while possess- ing interchangeable technologies. D.L.G. A82-10407 H Development of new lifting parachute designs A82-10403 ft Air bag impact attenuation system for the with increased trim angle. W. R. Bolton (Sandia Laboratories, AQM-34V remote piloted vehicle. C. T. Turner (Teledyne Ryan Livermore, CA) and I. T. Holt (Sandia Laboratories, Albuquerque, Aeronautical, San Diego, CA) and L. A. Girard, Jr. (Goodyear NM). American Institute of Aeronautics and Astronautics, Aero- Aerospace Corp.. Akron, OH). American Institute of Aeronautics dynamic Decelerator and Balloon Technology Conference, 7th, San and Astronautics, Aerodynamic Decelerator and Balloon Technology Diego, CA, Oct. 21-23, 1981. Paper 81-1921. 12 p. Research Conference, 7th. San Diego, CA, Oct. 21-23, 1981. Paper 81-1917. 8 supported by the U.S. Department of Energy. P. A development program is being conducted by Sandia National This paper describes the air bag impact attenuation system Laboratories on a lifting parachute system which allows aircraft (ABIAS) for the AQM-34V remote piloted vehicle. The developed delivery of a payload at high speed from low altitude. Candidate hardware, consisting of the main bag, tail bag, and inflation systems, lifting parachute designs, which included ram air inflated leading is described. Operation of the system from electrical initiation, edge chambers and flow-directing side vents, were evaluated in small through cover deployment, main and tail bag inflation, and ground and full-scale wind tunnel tests, in whirl tower flight tests, and in impact is discussed. Development ground drop tests, environmental aircraft flight tests. The results of these testing activities will be tests, structural tests, and the contractor flight tests are summarized. discussed along with the method of using test results to predict Test results substantiated system performance. (Author) system performance. (Author)

A82-10404 " Limiting payload deceleration during ground A82-10408 H The effects of flexibility on the steady-state impact. A. Mironer (Analytical Systems Engineering Corp., Burling- performance of small ribbon parachute models. T. Weber (McDonnell ton; Lowell, University, Lowell, MA), R. Urquhart (Analytical Aircraft Co., St. Louis, MO) and W. L. Garrard (Minnesota, Systems Engineering Corp.; Burlington, MA), and R. Walters (USAF, University, Minneapolis, MN). American Institute of Aeronautics and Geophysics Laboratory, Bedford, MA). American Institute of Aero- Astronautics, Aerodynamic Decelerator and Balloon Technology nautics and Astronautics, Aerodynamic Decelerator and Balloon Conference, 7th, San Diego, CA, Oct. 21-23, 1981, Paper 81-1923. 7 Technology Conference, 7th, San Diego, CA, Oct. 21-23, 1981, p. 5 refs. Research supported by the U.S. Department of Energy. Paper 81-1918.1 p. Small textile ribbon parachute models were shown to exhibit This paper considers the problem of limiting the deceleration of steady-state aerodynamic coefficients similar to those of rigid balloon and sounding-rocket instrument payloads during ground parachute models. Since no detailed study of the effects of model impact by adding energy-dissipating, deformable structures. The flexibility on the steady-state aerodynamic performance of a basic physics of the two-step deceleration/energy-dissipation process parachute model has been reported, several ribbon parachute models is analyzed and simple force and energy-balance relationships are of varying flexibility and equal geometric porosity were constructed developed. The pertinent equations are organized in a form that is and tested in the wind tunnel. No correlation was found between conducive for computer computation. Two example problems, one model flexibility and measured aerodynamic performance. (Author) of a sounding-rocket payload and the other of a balloon payload are calculated and the results presented in the form of a performance A82-10409 t- Comparison of simulation and experimental map. (Author) data for a gliding parachute in dynamic flight. T. F. Goodrick (U.S. Army, Natick Research and Development Laboratories, Natick, MA). A82-10405 f Aerodynamics and performance of cruciform : American Institute of Aeronautics and Astronautics, Aerodynamic parachute canopies. D. S. Jorgensen and D. J. Cockrell (Leicester, Decelerator and Balloon Technology Conference,'7th, San Diego, University, Leicester, England). American Institute of Aeronautics CA, Oct. 21-23, 1981, Paper 81-1924. 5 p. and Astronautics, Aerodynamic Decelerator and Balloon Technology Comparisons are presented of descent rate, total airspeed, Conference, 7th, San Diego, CA, Oct. 21-23, 1981, Paper 81-1919. horizontal airspeed, yaw rate, pitch rate and roll rate between 10 p. 8 refs. Research supported by the Ministry of Defence computer simulation in 6 DOF and flight data for a 200 square foot (Procurement Executive). Parafoil of aspect ratio 2.0 carrying a 350-pound stabilized payload. Effects of changing the ratio of the arm length and width (the The payload is specially designed to measure and record all essential 'arm ratio') on the aerodynamics of cruciform (cross-shaped) parameters of dynamic flight independent of atmospheric wind. The parachute canopies are described. Forces and moments were deter- comparison indicates a high degree of agreement in high-rate turns mined from measurements made when fabric canopies were towed varying greatly from steady-state conditions. Thus, the 6 DOF under water in a ship tank as well as from integrated pressure simulation has been validated. (Author) distributions determined by using specially-designed pressure trans- ducers fixed in fabric wind tunnel models. Using both techniques, the existence of stochastic variations in aerodynamic behavior was A82-10410 ft Theoretical analysis of parachute inflation investigated. Experimental results will be analysed using an appropri- including fluid kinetics. J. W. Purvis (Sandia Laboratories, Albuquer- ate computer performance model and the variation of dynamic que, NM). American Institute of Aeronautics and Astronautics, A82-10425

Aerodynamic Decelerator and Balloon Technology Conference, 7th, wind tunnel testing of up to 123 different configurations is San Diego, CA, Oct. 2J-23, 1981, Paper 81-1925. 12 p. 25 refs. discussed. (Author) Research supported by the U.S. Department of Energy. An analysis is presented for predicting parachute inflation. A82-10417 H Reductions in parachute drag due to forebody Equations of motion for the complete system are developed from wake effects. C. W. Peterson and D. W. Johnson (Sandia Labora- first principles, and are solved with no experimental inputs. Ballistic tories, Albuquerque, NM). American Institute of Aeronautics and equations of motion are derived for the canopy, payload, and Astronautics, Aerodynamic Decelerator and Balloon Technology suspension line masses. However, the enclosed fluid mass is not Conference, 7th, San Diego, CA, Oct. 21-23, 1981, Paper 81-1939. lumped with the canopy as an apparent mass term. Instead, the fluid 11 p. 10 refs. Research supported by the U.S. Department of Energy. conservation equations for a deforming, accelerating control volume The paper evaluates approximate analytic methods for predict- are solved to determine the behavior of the captured fluid and its ing reduction in parachute drag due to forebody wake effects. interaction with the canopy. Only first order effects are included, Velocity distributions are measured behind realistic forebody con- and the analysis is limited to inviscid, incompressible flow. Results figurations, and are compared to three turbulent wake velocity for both porous and nonporous canopies are compared with models. The velocities are integrated to determine the average experimental data. (Author) effective dynamic pressure acting on the parachute, and comparisons are made of drag loss data and effective dynamic pressure ratios. A82-10411 * // A new thermal and trajectory model for high Predictions are also made for no-fin and finned forebodies with 0 altitude balloons. L. A. Carlson and W. J. Horn (Texas A & M deg, 10 deg, and 20 deg angles of attack. The ratio of measured University, College Station, TX). American Institute of Aeronautics parachute drag behind a forebody divided by the wake free drag is and Astronautics, Aerodynamic Decelerator and Balloon Technology found to equal the ratio of the average dynamic pressure acting on Conference, 7th, San Diego, CA. Oct. 21-23, 1981. Paper 81-1926. the parachute divided by the freestream dynamic pressure. Good 10 p. 17 refs. Contract No. NAS6-3072. agreement is found between wake velocity data and theoretical A new computer model for the prediction of the trajectory and predictions, and the maximum angle of attack providing accurate thermal behavior of high altitude balloons has been developed. In predictions is determined. D.L.G. accord with flight data, the model permits radiative emission and absorption of the lifting gas and daytime gas temperatures above that A82-10420

Sonobuoys are blunt nose right circular cylinders, 4-7/8 inches in across the duct at four different fan speeds were determined utilizing diameter, 36 inches long ranging in weight from 12 to 39 pounds. a signal enhancement technique. The shapes of the waveforms of the Testing established that 3-foot long decelerators are suitable replace- mean rotor relative and mean upwash velocities were shown to ments for the existing configurations. Drag coefficient, opening load, change significantly across the span of the blades. In addition, an high altitude air descent characteristics, and stability data were increase in fan rotational speed caused an increase in the maximum determined for different types of decelerators with various area and wake turbulence intensity levels near the hub and tip. Spectral length. (Author) analysis was used to describe the complex nature of the rotor wake. (Author) A82-10427 ff Development of a nylon-Kevlar recovery system for the CL-289 /AN/USD 502/ surveillance drone. D. B. A82-10457 * ,'/ Effects of vane/blade ratio and spacing on fan Webb and L. Palm (Irvin Industries Canada, Ltd., Fort Erie, Ontario, noise. R. A. Kantola (General Electric Co., Power Generation Group, Canada). American Institute of Aeronautics and Astronautics, Lynn, MA) and P. R. Gliebe (General Electric Co., Aircraft Engine Aerodynamic Dece/erator and Balloon Technology Conference, 7th, Group, Cincinnati, OH). American Institute of Aeronautics and San Diego, CA, Oct. 21-23, 1981, Paper 81-1952. 12 p. Astronautics, Aeroacoustics Conference, 7th, Palo Alto, CA, Oct. An innovative optimized system has been developed for the 5-7, 1981, Paper 81-2033. 16 p. 11 refs. Contract No. NAS3-22062. automatic recovery of a small (500 Ib.) high speed surveillance drone The effects of vane/blade ratio and spacing on fan noise are along a precise trajec.tory. The system requires the use of advanced investigated to develop a fan noise prediction scheme which is materials and techniques in order to meet stringent system weight, calibrated against experimental data. A 44 blade, 0.504 diameter fan volume and performance limitations and consists of a two stage is used to demonstrate the production of fan noise data free from highly pressure packed unitized parachute package plus dual landing excess noise caused by rotor turbulence interaction. Two statorsets bags. The specification weight and volume constraints made the consisting of a cut-off set with 86 vanes, and a cut-on set of 48 vanes maximum use of Kevlar material mandatory for the entire system. are used, with a total range of spacing from 0.5 to 2.3 rotor chords. Other innovative techniques required included stretch fabric orifices The model includes viscous wake interaction noise and the potential for the landing bags and main parachute opening control features; field interactions of both the rotor and stator. A free-field acoustic i.e., continuously variable geometric porosity and use of a special environment is achieved by covering the walls, ceiling and floor with type of auxiliary parachute (Webb chute) positioned in the mouth of 0.7 m polyurethane foam wedges, providing less than + or - 1 dB the canopy. (Author) standing wave ratio at 200 Hz. Only a 3 dB drop in tone level occurs as the spacing is increased from 0.5 to 2.3 rotor chords, and results A82-10428 H Inflatable system for fast deployment of para- indicate that the rotor wakes impinging on the stator vanes are the principal noise source for subsonic rotor speeds. D.L.G. chutes at low altitudes from slow moving aircraft or stationary supports. H. 0. Bucker. American Institute of Aeronautics and Astronautics, Aerodynamic Dece/erator and Balloon Technology A82-10462 * # Analysis of augmented aircraft flying qualities Conference, 7th, San Diego, CA, Oct. 21-23, 1981, Paper 81-1953. 6 through application of the Neal-Smith criterion. R. E. Bailey and R. p. 5 refs. E. Smith (Calspan Advanced Technology Center, Buffalo, NY). A preinflated system has been developed for fast expansion and American Institute of Aeronautics and Astronautics, Guidance and deployment of emergency parachute canopies from buildings or Control Conference, Albuquerque, NM, Aug. 19-21, 1981, Paper slow-moving aircraft. The model is based on the concept of a quick 81-1776. 26 p. 9 refs. USAF-NASA-supported research. shape recovery of restrained folded inflated flexible tubing and is The Neal-Smith criterion is examined for possible applications in tested using modified conventional circular canopies. Three suspen- the evaluation of augmented fighter aircraft flying qualities. Longi- sion lines are used on buildings at altitudes as low as 25 m, with a 55 tudinal and lateral flying qualities are addressed. Based on the kg load. Canopies achieve full deployment at 11 m at normal landing application of several longitudinal flying qualities data bases, speeds of 4.6 m/sec with a frame expansion time of 0.35 sec. revisions are proposed to the original criterion. Examples are given Prototypes tested for slow aircraft achieve a speed of 50 km/hr, with which show the revised criterion to be a good discriminator of pitch a frame pressure of 4.3 kg/sq cm, and a deployment time of 2 sec. flying qualities. Initial results of lateral flying qualities evaluation Results indicate that fast expansion and subsequent deployment of through application of the Neal-Smith criterion are poor. Lateral canopies operated with portable gas sources can be useful in such aircraft configurations whose flying qualities are degraded by roll sports as hang gliding, or as emergency equipment for firemen in ratcheting effects map into the Level 1 region of the criterion. A rescue operations. D.L.G. third dimension of the criterion for flying qualities specification is evident. Additional criteria are proposed to incorporate this dimen- A82-10455 * f; Helicopter rotor trailing edge noise. R. H. sion into the criterion structure for flying qualities analysis. (Author) Schlinker and R. K. Amiet (United Technologies Research Center, East Hartford, CT). American Institute of Aeronautics and Astronau- A82-10463 -f How large should a commuter transport be. R. tics, Aeroacoustics Conference, 7th, Palo Alto, CA, Oct. 5-7, 1981, D. FitzSimmons, J. Seif, and S. C. Nelson (Douglas Aircraft Co., Paper 81-2001. 26 p. 44 refs. Contract No. NAS1-15730. Long Beach, CA). American Institute of Aeronautics and Astro- An experimental and theoretical study was conducted to assess nautics, Aircraft Systems and Technology Conference, Dayton, OH, the importance of trailing edge noise as a helicopter main rotor Aug. 11-13, 1981, Paper 81-1732. 12 p. 11 refs. broadband noise source. The noise mechanism was isolated by testing Definitions of a commuter transport are examined from the a rotor blade segment in an open jet acoustic wind tunnel at close to viewpoint of a major airframe manufacturer. Selected milestones in full scale Reynolds numbers. Boundary layer data and acoustic data commuter air service are reviewed. The impact of deregulation is were used to develop scaling laws and assess a first principles trailing creating new opportunities for commuter airlines to expand services, edge noise theory. Conclusions from the isolated blade study were resulting in new economic and operating problems. Problems of analytically transformed to the rotating frame coordinate system to acquisition and operating costs are discussed. Considerations for develop a generalized rotor noise prediction. Trailing edge noise was commuter transport capacity include number of passengers, frequen- found to contribute significantly to the total helicopter noise cy of service, airport facilities, and community compatibility. spectrum at high frequencies. (Author) Capacity variations are explored in the 1980s and the 1990s. Some conceptual commuter transport candidates for the future are A82-10456 * ,7 Rotor wake characteristics relevant to rotor- presented. (Author) stator interaction noise generation. L. M. Shaw and J. R. Balombin (NASA, Lewis Research Center, Cleveland, OH). American Institute A82-10465 it Design considerations for duty cycle, life and of Aeronautics and Astronautics, Aeroacoustics Conference, 7th, reliability of small limited life engines. D. A. Gries (Williams Palo Alto. CA, Oct. 5-7, 1981, Paper 81-2031. 24 p. 23 refs. International Corp., Walled Lake, Ml). AIAA, SAE, andASME, Joint Mean and turbulence wake properties at three axial locations Propulsion Conference, 17th, Colorado Springs, CO, July 27-29, behind the rotor of an aerodynamically loaded 1.2 pressure ratio fan 1981. AIAA Paper 81-1402. 4 p. were measured using a stationary cross film anemometer in an Design requirements, design criteria and verification methods anechoic wind tunnel. Wake characteristics at four radial immersions related to preliminary design and program planning for small limited A82-10649 life turbine engines have significant differences from other engine Astronautics, 1981. 100 p. Members, $12.50; nonmembers, $15. technologies. Design operating life of components is defined by Results are presented of discussions concerning existing and development test requirements, rather than mission life require- proposed training, equipment and methods for supplying the forecast ments. Interpolation between operating mission limits is required to demand for airline pilots for the period 1985-2000 from the cadre of demonstrate operating life for limited life engines rather than general aviation. Areas covered include aeromedical education, extrapolation of accelerated testing required for long life. Storage life training and equipment, the air traffic control system, the training requirements are very stringent. The correlation of reliability and safety aspects associated with cockpit design analysis, pilot and prediction versus accelerated verification testing for engines requiring maintenance personnel training accomplished by the fixed base extended dormant storage is being validated. (Author) operator, the effects of differences in flying qualities and perfor- mances between aircraft on safety and training effectiveness, pilot operating handbooks, regulatory aspects of pilot training and A82-10466 * g Propfan installation aerodynamics of a super- equipment, training and flight simulation programs for commercial critical swept wing transport configuration. R. C. Smith and A. D. pilots, and pilot weather knowledge. A.L.W. Levin (NASA, Ames Research Center, Moffett Field, CA). AIAA, SAE, and ASMS, Joint Propulsion Conference, 17th, Colorado Springs, CO, July 27-29. 1981, AIAA Paper 81-1563. 14 p. 6 refs. A82-10545 Implementation of AVRADCOM MM&T. G. A semispan model with a powered propeller has been tested to A. Gorline (U.S. Army, Aviation Research and Development Com- provide data on the installation drag penalty of advanced propfan- mand, St. Louis, MO). ManTech Journal, vol. 6, no. 1, 1981, p. 3-6. powered transports designed to cruise at a Mach number of 0.8. The general implementation plan of the Army Aviation Re- These tests, conducted in 14-foot and 11-foot transonic wind search and Development Command's (AVRADCOM) efforts in tunnels, are a part of a NASA program to develop efficient, manufacturing methods and technology (MM&T) programs is de- high-speed propellers for more fuel-efficient commercial transports scribed. A flowchart of the implementation procedure is presented, for the 1990s and beyond. The model is instrumented for measuring and attention is given to several examples of implementation, propeller forces, wing/nacelle forces and moments, and pressure including a compressor casing, a titanium casting, and aluminum PM distributions over the wing and nacelle. The body in these tests was parts. B.J. nonmetric, being connected to the wing by an RTV seal at the wing/body juncture. Tests were run at angles of attack from -3 to +5 A82-10547 Composite main rotor tubular braided. M. deg over the Mach number range 0.6 to 0.85 at a Reynolds number White (Kaman Aerospace Corp., Bloomfield, CT). ManTech Journal, of about 9,000,000. Results of these tests indicate that the nacelle vol. 6, no. 1, 1981, p. 14-16. Army-supported research. interference drag can be quite large relative to an uninstalled nacelle. Mechanical tubular braiding has been demonstrated to be a However, the losses due to the nacelle were reduced to acceptable viable blade spar manufacturing process after the completion of a levels by changes to the wing leading edge and nacelle intersection. program that included preliminary design of an improved main rotor The propeller slipstream causes substantial changes in the wing span blade for the OH-58 helicopter. The blade incorporates an advanced load distribution indicating that twist modifications are needed to aerodynamic shape and has as its primary structural member a Kevlar recover a more favorable span load distribution. (Author) 49/epoxy spar fabricated by braiding. The achievement of an analytically acceptable blade and spar design satisfying critical A82-10495 # Characteristics and trends of energy consump- structural and dynamic requirements was not hindered by braiding process constraints. B.J. tion in transport missions with aircraft and surface vehicles (Carat- teristiche e tendenze del consume energetico nelle missioni di trasporto con aeroplani e con veicoli di superficial. G. Gabrielli. A82-10646 Navigation task partitioning in distributed- Ingegneria, July-Aug. 1981, p. 193-198. 6 refs. In Italian. processing avionics systems. J. L. Center (JAYCOR, Woburn, MA). A nondimensional factor is defined which characterizes energy (Institute of Navigation, National Aerospace Meeting, Warminster, consumption in transport missions. Values of this energy utilization Pa., Apr. 8-10, 1981.) Navigation, vol. 28, Summer 1981, p. 93-100. factor are given for a number of aircraft and surface vehicles (e.g., 10 refs. Contract No. N62269-80-C-0146. automobiles, buses, and trains). Particular attention is given to the An approach is presented for allocating navigation tasks among energy utilization factor of turbofan and turbojet aircraft. B.J. multiple processors prior to detailed design and implementation. The method is based on applying rate-distortion techniques from commu- A82-10496 ft The possibility of using deformable rubber nication theory to navigation system design. All navigation activities components in landing gear (Possibilita di impiego di elementi are broken down into elementary functions, and rate-distortion deformabili in gomma in carrelli di atterraggio). C. Caprile and L. methods are used to access the impact on rms position and velocity Salvioni (Milano, Politecnico, Milan, Italy). Ingegneria, July-Aug. errors of limiting communication bandwidths among elementary 1981, p. 201-212, In Italian. functions. Groups of functions that require high-bandwidth commu- A test program was devised to evaluate the use of precompressed nication are assigned to the same microprocessor, while those that rubber components as vibration dampers in landing gear for light can perform effectively with lower-bandwidth links are separated. aircraft. The test program is described, and dynamic and static test The method is illustrated for aircraft motion and sensor errors in the results are presented. A dissipationless model is developed which is north channel. J.F. shown to satisfactorily describe the behavior of the rubber com- ponents. B.J. A82-10649 * improving the MLS through enhanced cockpit displays. R. S. Jensen (Ohio State University, Columbus, OH). (Institute of Navigation, National Aerospace Meeting, Warminster, A82-10497 ff Problems relating to the classical rate-gyro Pa., Apr. 8-10, 1981.) Navigation, vol. 28, Summer 1981, p. (Problematiche relative al rate-gyro di tipo dassico). L. Borello 138-146. 8 refs. NASA-sponsored research. (Torino, Politecnico, Turin, Italy). Ingegneria, July-Aug. 1981, p. A simulator investigation of various prediction and quickening 225-229. In Italian. algorithms in computer-generated forward-looking displays is pre- A mathematical model is developed for evaluating the accuracy sented; the algorithms are used to improve manual aircraft control on of classical rate-gyros. An analysis is presented of the influence of curved microwave landing system approaches. The experimental secondary input signals associated with the angular velocity com- facility consisted of a Link GAT-2 simulator, a POP 11/40 ponents of the platform. Ways to minimize the effects of these minicomputer, a high-speed graphic display, a TV camera, and a CRT secondary signals are examined. B.J. monitor. Results indicate that second- and third-order predictor displays provide the best lateral performance and that intermediate A82-10500 Test Pilots' Aviation Safety Workshop, U.S. levels of prediction and quickening provide the best vertical control. Naval Postgraduate School, Monterey, CA, February 25-28, 1981, Prediction/quickening algorithms of increasing computational order Proceedings. Workshop sponsored by the Society of Experimental were found to significantly reduce aileron, rudder, and elevator Test Pilots and American Institute of Aeronautics and Astronautics. control responses. The conventional crosspointer displays yielded an Edited by C. Tuomela (California Agricultural Aircraft Association, average 2-sigma lateral error of + or 200 over all wind conditions at Sacramento, CA), New York, American Institute of Aeronautics and 500 m from touchdown, and was therefore unable to meet FAA A82-10650 requirements (+ or - 22.9 m); the pictorial-preview display yielded A82-10853 High-efficiency hydraulic power transfer units much better results: an average 2-sigma lateral error of + or - 27 m. for multisystem aircraft W. E. Boehringer (Douglas Aircraft Co., Neither display was able to approach the FAA specified accuracy Long Beach. CA). In: Fluid power technology for the '80s. requirement in the vertical dimension (+ or • 3.7 m). J.F. Warrendale, PA, Society of Automotive Engi- neers, Inc., 1980, p. 15-20. A82-10650 Discrete address beacon, navigation and land- Multiple pumps are generally employed to provide fully pow- ing system. R. P. Crow. (Institute of Navigation, National Aerospace ered aircraft flight controls with a redundant power source. The Meeting, Warminster, Pa.. Apr. 8-10, 1981.) Navigation, vol. 28, prime hydraulic source is, in most cases, a pump driven directly by Summer 1981, p. 147-162. one of the aircraft's engines. This approach provides the most The Discrete Address Beacon, Navigation and Landing System efficient method of converting engine horsepower to hydraulic (DABNLS) is an integrated system which will provide not only air horsepower. The secondary hydraulic power source is generally not traffic control surveillance data and a two-way data link of the as efficient. Investigations were conducted with the objective to find FAA's developmental Discrete Address Beacon System, but will sources of alternate hydraulic power with improved efficiency. The provide precision area navigation and versatile landing guidance with reasons for the inefficiency of current secondary hydraulic power a full Category I lie capability. The DABNLS will utilize a single pair sources were exolored to obtain a basis for the design of systems of L-band frequencies for the discretely addressed up-link interroga- with a better performance. A unit consisting basically of two tions and down-link replies. A ground facility will make precise hydraulic cylinders mounted back to back was designed and azimuth and range measurements on the bi-phase coded reply pulses, manufactured. The design of this unit was subsequently further as well as digitally process the reported altitude data to obtain the improved. It is pointed out that the new hydraulic power transfer aircraft's latitude/longitude and other parameters. The data will be units obtained have a comparatively high running efficiency. G.R. used for navigation, collision avoidance and ATC purposes. Multiple channels would be used in terminal areas, each having elevation A82-10854 'Quiet please'. S. J. Skaistis (Sperry Corp., facilities for landing guidance. Block diagrams of the DABNLS Sperry Vickers Div.. Troy. Ml). In: Fluid power technology for the ground subsystem and air-borne transponders are given. J.F. '80s. Warrendale, PA, Society of Automotive Engineers, Inc., 1980, p. 21-26. The considered investigation has the objective to indicate that A82-10816 t Optimization of the principal design param- noise control is the product of good engineering. It does not depend eters of a passenger aircraft (Optimizatsiia osnovnikh proektnikh on learning a whole new discipline nor does it depend on invention. parametriv pasazhirskogo litaka). V. S. Mikalevich, G. M. lun, and V. M. Kuz'menko. Akademiia Nauk Ukrain'skoi RSR. Visnik, vol. 45, Because of the increasing use of hydraulics and the growth of noise Aug. 1981, p. 39-43. 7 refs. In Ukrainian. sensitivity in aircraft, it was felt that aircraft hydraulic engineers should be aware of the desirability of noise control. A booklet was written for the general practitioner in aerospace hydraulics engineer- A82-10821 ff Strong matching method for computing tran- ing. The first principle of quieting is that the most favorable sonic viscous flows including wakes and separations - Lifting airfoils. cost-effectiveness ratio is achieved when noise control engineering is J. C. Le Balleur (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, part of the original design effort. The second principle of quieting is France). La Recherche Aerospatiale (English Edition), no. 3, 1981, that the loudest noise component must be reduced before apprecia- p. 21-45. 46 refs. Research supported by the Direction des ble quieting can be achieved. G.R. Recherches, Etudes et Techniques. A method is presented for computing two-dimensional lifting steady viscous flows with wakes and possibly separations inside the A82-10855 Developments in boundary layer Thrust Vec- viscous layer. A transonic potential calculation is used, which tor Control. R. E. Fitzgerald and R. F. Kampe (Chandler Evans, Inc., strongly interacts with a defect integral method. A mathematical West Hartford, CT). In: Fluid power technology for the '80s. model is also presented for matching the viscous model for averaged Warrendale, PA, Society of Automotive Engi- mean velocities with reverse flow, and for turbulent closure in neers, Inc.. 1980, p. 27-35. 7 refs. nonequilibrium layers. Numerical coupling is reached through an Thrust Vector Control (TVC) is commonly employed on a iterative relaxation technique, and the wake geometry is calculated. vehicle to provide larger magnitude steering forces during low The viscous mean flow is determined, and examples of applications velocity flight than can be obtained with aerodynamic fins. A to subsonic or supercritical airfoils are given. D.L.G. method of thrust vectoring called boundary layer thrust vector control (BLTVC) is considered. BLTVC involves a variation of the A82-10822 « Electrical ground testing of aircraft antistatic secondary injection procedure. The limited deflection and flow ratio protection. A. Bruere (ONERA, Chatillon-sous-Bagneux, Hauts-de- is amplified by means of an approach including an injection into a Seine, France). La Recherche Aerospatiale (English Edition), no. 3, highly overexpanded nozzle. Deflections of 15 degrees are possible 1981, p. 47-56. 5 refs. — and ambient air is used as the injectant. Attention is given to the After a review of the methods suggested to ensure aircraft principles of BLTVC operation, a breakthrough in reducing nozzle protection regarding electrostatic spurious phenomena, one describes size, and a scheme for producing roll control. Rocket applications of one of the two devices developed at ONERA for ground testing of BLTVC cover a range in size from microthruster to remote piloted this protection. These methods give the external surface of the vehicle booster. BLTVC can be used on aircraft gas turbines also. aircraft a conductivity sufficient enough to enable on the one hand Drawbacks of BLTVC are related to the necessity to employ very the measurement of the surface resistivity of the protected parts even large nozzles for high-altitude applications. These drawbacks can be if they are coated with a finishing layer of paint, and, on the other overcome with the aid of Confined Jet Thrust Vector Control. G.R. hand, to check the good electrical continuity of each structure element and the aircraft potential reference point. (Author) A82-10889 H A new APU for medium place aircraft environ- mental control systems. C. Rodgers (Solar Turbines International. A82-10851 Fluid power technology for the '80s. Warren- Turbomach Div., San Diego, CA). American Society of Mechanical dale, PA. Society of Automotive Engineers, Inc. (SAE Proceedings Engineers, Intersociety Conference on Environmental Systems, San P-85), 1980. 38 p. $8.00. Francisco, CA, July 13-15, 1981. Paper 81-ENAs-1. 7 p. Members, $2.00; nonmember, $4.00. Aspects of energy conservation with variable displacement New small auxiliary power units (APU) are sought to provide pumps and motors are examined, taking into account approaches for aircraft pneumatic power for environmental control and start hydraulic power generation, friction loads, elastic loads, regenerative systems. A new small gas turbine APU in the 20-50 hp class has been braking, gravity loads, inertia loads, variable displacement pump developed to meet the smaller aircraft secondary power require- characteristics, integrated actuator packages, a servopump analysis, a ments. The Gemini APU utilizes a single-stage radial compressor and valve analysis, and the computation of pump and motor parameters. a single-stage radial turbine wheel; it incorporates a single-can High-efficiency hydraulic power transfer units for multisystem combustor with a unique spinning cup fuel atomizer. The electrical aircraft are discussed along with basic approaches for reducing control provides for shutdown in case of malfunctions and also has hydraulic system noise in aircraft. A description of developments in an automatic bleed load control system. The load control valve boundary layer thrust vector control is also provided. G.R. permits greater operational flexibility by modulating flow to

10 A82-10901 maintain rated turbine exhaust temperature under varying electrical are developed, analyzed, and revised in an iterative process until loads. The engine is available in two configurations: one for visual, structural, thermal, weight, and cost analyses show that the combined bleed/shp applications and the other for shaftpower design requirements are satisfied. Design details on two windshield applications. Silent power versions of the Gemini military ground systems are presented. Because a successful windshield design for generator sets have been developed which produce an overall noise high speed aircraft depends, to a great extent, on the ability of the level as low as 60 dB, and fuel and oil requirements for the Gemini windshield to withstand the high temperatures associated with are compatible with those of most main propulsion gas turbines. supersonic flight, the aerothermodynamic analysis method and Successful starting has been demonstrated by the APU from -65 F results are emphasized. (Author) through 125 F, as well as through 2000 start-stop cycles. J.F. A82-10894 tt Design challenges of high performance aircraft A82-10890 ff Closed loop environmental control systems for POD EOCM cooling systems. R. D. Buckingham (Fairchild Indus- fighter aircraft. G. S. Tsujikawa and V. K. Rajpaul (Boeing Military tries, Inc., Fairchild Stratos Div., Manhattan Beach, CA). American Airplane Co., Seattle, WA). American Society of Mechanical Engi- Society of Mechanical Engineers. Intersociety Conference on Envi- neers, Intersociety Conference on Environmental Systems, San ronmental Systems, San Francisco, CA, July 13-15, 1981, Paper Francisco, CA, July 13-15, 1981. Paper 81-ENAs-2. 6 p. Members, 81-ENAs-6. 7 p. Members, $2.00; nonmembers, S4.00. S2.00; nonmembers, $4.00. USAF-sponsored research. Modern high performance aircraft and associated Electro- A favorable thermal environment for aircraft avionics imple- Optical/Countermeasure (EOCM) pods have introduced very com- mented in an energy efficient manner is an important factor in plex, high heat density electronics and avionics equipment, which reducing aircraft life cycle costs through improved avionic reliability. requires mechanically refrigerated cooling to reject large amounts of This paper discusses the application of closed loop environmental heat from relatively small confined areas because of: insufficient/no control systems (CECS) to a tactical mission aircraft. The specific cooling air from the host aircraft; miniaturization/high heat density objective was to determine CECS configurations which would of electronics; high temperature heat sink of high performance provide significant savings in fuel consumption and life cycle costs fighter-type aircraft, precluding ram air cooling; need for increased while maintaining stable, low temperature, clean and dry environ- electronics/avionics reliability through lower operating temperature ment for avionics equipment. Preliminary designs were developed for ranges. Electrically driven vapor compression systems are-most a positive displacement rotary vaned air cycle machine system, effective for the EOCM-type pod missions, operating well at high and hybrid air/vapor cycle system, centrifugal Freon compressor vapor low altitudes, as well as at high and low flight speeds. Vapor cycle cycle system and a turbo-machinery air cycle machine system. systems provide full ground cooling performance capability. (Author) System characteristics, details of design, performance and life cycle cost data were compared with an existing open loop air cycle system. A82-10895 # Air supply system bite for Boeing 767 air- The study showed that closed loop system configurations and close plane. J. P. Patrick and G. F. Atkinson (United Technologies Corp., avionic temperature control resulted in substantial life cycle cost Hamilton Standard Div., Windsor Locks, CT). American Society of savings. (Author) Mechanical Engineers, Intersociety Conference on Environmental Systems, San Francisco, CA, July 13-15, 1981, Paper 81-ENAs-7. 7 A82-10892 -' Towards minimum power for environmental p. Members, S2.00; nonmembers, $4.00. control in transport aircraft D. Pierrepont (British Aerospace Public, Modern airplane air supply systems regulate the temperature and Ltd., Co., Weybridge, Surrey, England). American Society of pressure of engine bleed air extracted for cabin pressurization, air Mechanical Engineers, Intersociety Conference on Environmental conditioning, anti-icing, cross-engine starting, air-driven hydraulic Systems, San Francisco, CA. July 13-15, 1981, Paper 81-ENAS-4. 7 pumps and other pneumatic demands. The air supply system for the p. Members, $2.00; nonmembers, $4.00. Boeing Model 767 airplane consists of a set of equipment for each of The minimization of the power consumed by the pneumatically the airplane's two engines and a remotely located built-in-test- powered environmental control system (ECS) on board transport equipment (BITE) module. The air supply BITE system isolates over aircraft, primarily the air conditioning system, is considered. It is 95 percent of all failures to the line replaceable unit (LRU) level. The noted that the development of a low-bleed ECS with subzero air BITE system achieves this fault isolation via a modern digital cycle machine exit temperatures, condensing heat exchangers and electronic BITE module that continuously monitors inputs on a recirculation leading to the doubling of the temperature difference time-shared basis from dedicated BITE elements which are integrally between the fresh air supply and passenger and crew compartments contained in the air supply system LRUs. The operation of the has resulted in the halving of the fuel penalty associated with the all-pneumatic bleed air supply system is unaffected by the BITE ECS, (from 4% to 2%) while an additional halving of the penalty is system. Faults detected during bleed air system operation are stored possible by further reducing air flow or using a shaft-driven in the BITE module nonvolatile memory for interrogation by the centrifugal compressor to provide the fresh air supply. Relative fuel ground crew. Provisions are also made to allow BITE detected faults savings to be had from air bleed reduction are shown to be significant to be used as inputs to aircraft airborne integrated data systems with respect to those to be obtained in the areas of engines, (AIDS). (Author) aerodynamics and structures. The minimum fresh air flow required for the efficient operation of air supply systems within limits of A82-10896 # Air-film cooling returns to ramjets. W. E. passenger health and comfort is considered, and pneumatic and Roberts and S. Wasserberg (Marquardt Co., Van Nuys, CA). electrical means for the transmission of shaft power to the ECS are American Society of Mechanical Engineers, Intersociety Conference compared. The operating principles of air- and vapor-cycle cooling on Environmental Systems, San Francisco, CA, July 13-15, 1981, systems are then reviewed with respect to their performances, and Paper 81-ENAs-S. 6 p. Members, $2.00; nonmembers, $4.00. advantages of the air cycle in the areas of complexity, maintenance A ramjet engine was configured for the Navy Firebrand program and weight are noted. Consideration is also given to alternatives to to propel an antiship target missile. After years of using insulation to bleed for anti-icing applications. A.L.W. thermally protect engine combustor/nozzle assemblies, air-film cool- ing was used in the Firebrand engine. A combustor liner causes a A82-10893 H Design analysis of high temperature transpar- layer of cool air to be injected between the combustion gas and ent windshields for high performance aircraft. V. E. Wilson, A. J. combustor/nozzle structural shell. As this film flows downstream, Bockstahler (Rockwell International Corp., North American Aircraft mixing and reaction with combustion gas causes its cooling effective- Div., Los Angeles, CA), and C. A. Babish, III ( USAF, Wright ness to deteriorate. A satisfactory structural design requires shell Aeronautical Laboratories, Wright-Patterson AFB, OH). American temperature prediction. Using three film cooling correlations, a . Society of Mechanical Engineers, Intersociety Conference on Envi- method of defining the Firebrand film cooling effectiveness is shown. ronmental Systems, San Francisco, CA, July 13-15, 1981, Paper Thermal models are presented which utilize this effectiveness and 81*ENAs-5. 11 p. 10 refs. Members, S2.00; nonmembers, S4.00. provide shell temperature predictions under ground test conditions. Contract No. F33615-68-C-3421. This analytical method is shown to be sufficient when predicted Design criteria and analysis methods that are required to extend temperatures are compared with shell temperatures measured during the thermal performance capabilities of lightweight, large field-of- these ground tests. (Author) view transparent windshield systems of Air Force aircraft into the Mach 2.5 to 3.5 speed regime are developed and demonstrated. A82-10901 # In-situ calibration of flight heat transfer instru- Windshield system design requirements are established and designs mentation. H. W. Kipp and E. A. Eiswirth (McDonnell Douglas

11 A82-10920

Astronautics Co., St. Louis, MO). American Society of Mechanical Analysis was made of the heat transfer and pressure drop Engineers, Intersociety Conference on Environmental Systems, San through turbine vanes made of a sintered, porous metal coated with a Francisco, CA, July 13-15, 1981, Paper 81-ENAs-13. 5 p. 8 refs. thin layer of ceramic and convection cooled by spanwise flow of Members, S2.00; nonmembers, S4.00. cooling air. The analysis was made to determine the feasibility of In-situ calibration offers a promising approach for economically using this concept for cooling very small turbines, primarily for short minimizing errors in surface heating rates obtained from subsurface, duration applications such as in missile engines. The analysis was transient, temperature measurements. Experience has shown that made for gas conditions of approximately 10 and 40 atm and 1644 K surface heat flux solutions are sensitive to inaccuracies in variables and with turbine vanes made of felt-type porous metals with relative such as thermocouple location, temperature measurements, model densities from 0.2 and 0.6 and ceramic coating thicknesses of 0.076 thermal properties and joint conductances. It is the purpose of in-situ to 0.254 mm. . (Author) calibration to determine the values of finite difference thermal model parameters which result in the least square error solution. A A82-10965 «, Fuel for future transport aircraft G. D. calibration heat flux is imposed on the surface surrounding a Brewer (Lockheed-California Co., Burbank, CA). American Society thermocouple installation and the thermal response is recorded. The of Mechanical Engineers and American Institute of Chemical temperature history is used in an inverse solution to obtain the Engineers, National Heat Transfer Conference, 20th, Milwaukee, Wl, surface heat flux which is then compared with the calibration pulse. Aug. 2-5, 1981, ASME Paper 81-HT-80. 8 p. 6 refs. Members, $2.00; Repetitive values of surface heat flux are obtained by systematically nonmembers, $4.00. varying model parameters until the calculated and calibration fluxes Despite attempts at conservation and the development of agree within a prescribed tolerance. The concept is illustrated with a synthetic aviation-grade kerosene from alternative fossil fuel materi- numerical example. (Author) als, it is widely recognized that alternatives to conventional petroleum-base aircraft fuels must become available in the near A82-10920 JJ Air-freon integrated environmental condition- future. The present paper discusses the prospects for liquid hydrogen ing system for trainer subsonic aircraft. M. Andriano, A. Mannini, as a future fuel for transport aircraft. Advantages of liquid hydrogen and V. Marchis (Microtecnica-Torino, Turin, Italy). American over synthetic fuels and liquid methane as alternative fuels in the Society of Mechanical Engineers, Intersociety Conference on En- areas of availability, safety, pollution, relative energy efficiency as a vironmental Systems, San Francisco, CA, July 13-15, 1981, Paper function of trip length and aircraft weight, overall costs and airport 81-ENAS-33. 7 p. Members, $2.00; nonmembers, $4.00. compatibility are considered. The possible requirements for a Development studies of a cabin environmental control system development program aimed at preparing liquid hydrogen for use in (ECS) for a new trainer subsonic aircraft are presented. The new operational aircraft are examined, and the probable time characteris- vapor cycle cooling system is energy efficient for engines sensitive to tics of fuel use during the transition to liquid hydrogen, which may bleed air extraction. The hybrid air-freon ECS is composed of four significantly replace synthetic fuels by the year 2000, are considered. subsystems: the recirculation loop, the bleed air line, the ram air line, A comprehensive plan for liquid hydrogen fuels R&D is then and the supplementary cooling assembly (SCA). The air system presented which is currently being considered for implementation on emergency control law and the SCA system emergency control law an international basis. A.L.W. are shown schematically in flow charts: if the sensor in the recirculating loop duct measures a temperature higher than 100 C, A82-10985 # Control laws for adaptive wind tunnels. E. H. the bypass valve is immediately closed; it is only opened if the duct Dowell (Princeton University, Princeton, NJ).AIAA Journal, vol. 19, temperature decreases below 70 C. The compressor in the SCA Nov. 1981, p. 1486-1488. 5 refs. Research supported by Princeton system is switched off in cases where the pressure is above 2.5 MPa University. and lower than 0.3 MPa. Performance tests correlated well with A control law is developed which will permit the systematic predicted ones, and the system overall weight was optimized at 30 modification of wind tunnel wall conditions, in order to minimize kg. The ECS was compared with the bootstrap air system and found the interference about a model. The approach is valid for both to have a substantially better bleed air flow rate (ECS = 1.20 kg/min; three-dimensional and lifting flows and, subject to the assumption of bootstrap = 7.0 kg/min). J.F. linearity, is not dependent on any particular theoretical description A82-10934 * H Multiple-scale turbulence modeling of free of the fluid. In addition, unlike previous control schemes, the present turbulent flows. G. Fabris and P. T. Harsha (Science Applications, method does not require an iterative approach. O.C. Inc., Combustion Dynamics and Propulsion Technology Div., Canoga Park, CA). American Society of Mechanical Engineers and American A82-10987 /} Wind tunnel tests on airfoils in tandem cas- Society of Civil Engineers, Joint Applied Mechanics, Fluids Engineer- cade. S. Raghunathan (Belfast, Queen's University, Belfast, Northern ing, and Bioengineering Conference, University of Colorado, Boulder, Ireland), C. P. Tan, and N. A. J. Wells. AIAA Journal, vol. 19, Nov. CO. June 22-27, 1981, ASME Paper 81-FE-20. 11 p. 28 refs. 1981.P.1490-1492. Members, $2.00; nonmembers, $4.00. Contract No. NAS1-15988. Wind tunnel tests on airfoils in tandem cascade, of the type As part of an investigation into the application of turbulence found on the Wells-type turbine, were conducted in a low-speed models to the computation of flows in advanced scramjet com- tunnel with a maximum air velocity of 35 m/sec. Airfoils tested had bustors, the multiple-scale turbulence model has been applied to a a chord of 85 mm and a span of 100 mm and included the NACA variety of flowfield predictions. The model appears to have a 0012, 0018 and 0021 profiles. The freestream dynamic pressure was potential for improved predictions in a variety of areas relevant to measured upstream of the cascade by a Pitot tube, as well as the combustor problems. This potential exists because of the partition of tangential and normal forces on the blades. Tests were performed for the turbulence energy spectrum that is the major feature of the several cascade solidities and at angles of incidence varying from zero model and which allows the turbulence energy dissipation rate to be to 90 deg, with Reynolds numbers of about 100,000. O.C. out of phase with turbulent energy production. To establish the general reliability of the approach, it has been tested through comparison of predictions with experimental data. An appreciable A82-11020 Tangential sensitivity of EW receivers. J. Tsui overall improvement in the generality of the predictions is observed, (USAF, Avionics Laboratory, Wright-Patterson AFB, OH). Micro- as compared to those of the basic two-equation turbulence model. A wave Journal, vol. 24, Oct. 1981, p. 99-102. 8 refs. Mach number-related correction is found to be necessary to A systematic approach to the determination of the tangential satisfactorily predict the spreading rate of the supersonic jet and sensitivity of a receiver is presented, and calculated results are mixing layer. (Author) compared with experimental data. Particular consideration is given to the following topics: the practical determination of the effective A82-10952 * H Thermal and flow analysis of a convection, noise bandwidth to be used in the sensitivity calculations of an EW air-cooled ceramic coated porous metal concept for turbine vanes. F. receiver; the influence of the RF gain in the receiver on the S. Stepka (NASA, Lewis Research Center, Cleveland, OH). American sensitivity; and the influence of the RF bandwidth and the video Society of Mechanical Engineers and American Institute of Chemical bandwidth on the sensitivity. B.J. Engineers, National Heat Transfer Conference, 20th, Milwaukee, Wl, Aug. 2-5. 1981, ASME Paper81-HT-48. 7 p. 9 refs. Members, $2.00; A82-11031 Relationships between naval aviation safety nonmembers, $4.00. and pilot flight experience. M. S. Borowsky (U.S. Naval Safety

12 A82-11317

Center, Norfolk, VA). Aviation, Space, and Environmental Medicine, stress relationships at fracture origins. The possibility that accelerat- vol. 52. Oct. 1981, p. 608-610. ed fatigue testing may sometime fail to reveal critical design Flight activity of all aviators flying naval aircraft and aircraft weaknesses or result in unrepresentative modes of fracture is accident data were analyzed to determine if statistical relationships explored, and simple ways of avoiding this problem are discussed. among lifetime and recent experience variables and accident liability (Author) exist. The results demonstrate that accident potential, though not A82-11225 On computing Floquet transition matrices of statistically related to flight hours in 30-d periods, is correlated with rotorcraft. G. H. Gaonkar, D. Sastry (Indian Institute of Science, lifetime flight experience with the higher liability associated with Bangalore, India), and 0. S. S. Prasad (National Aeronautical minimal amounts of flight hours and with transitioning into new Laboratory, Bangalore, India). American Helicopter Society, Journal, aircraft. (Author) vol. 26, July 1981, p. 56-61. 23 refs. A82-11149 Acoustic emission - An emerging technology There are conflicting claims concerning the efficiency of for assessing fatigue damage in aircraft structure. C. D. Bailey and W. different schemes of computing the Floquet transition matrices of M. Pless (Lockheed-Georgia Co., Marietta, GA). Materials Evaluation, rotorcraft. In this paper, computer-generated data are presented on vol.39, Oct. 1981, p. 1045-1050. 12refs. the comparative efficiency of four classes of methods: (1) Runge- Guidelines for the design of a dedicated acoustic emission (AE) Kutta one-step; (2) Hamming's predictor-corrector multistep; (3) system for aircraft fleet installations are discussed. It is shown that Bulirsch-Stoer extrapolation; and (4) hybrid or variable order. Data the successful development of an on-board AE crack detection pertain to single-pass and N-pass schemes for four flap-lag stability system depends on the existence of an integrated body of technology models. It is found that Hamming's fourth-order predictor-corrector combining AE detection technology, structural and crack growth method in single pass is the most economical with respect to characteristics, noise and EMI discrimination or rejection, and fleet three-significant-figure accuracy. The analytical formulation confirms maintenance practices. These technologies must be fully integrated the advantage of the single-pass approach over the N-pass, provides through the development and deployment of the system to achieve useful approximations to machine-time data, and is a feasible cost-effective results. V.L. economical approach to comparing different methods with respect to machine time. B.J.

A82-11177* Rheological behavior of progressively shear- A82-11300 Model helicopter rotor impulsive noise. J. E. thickening solutions. S. T. J. Peng and R. F. Landel (California Hubbard, Jr. and W. L. Harris (MIT, Cambridge, MA). Journal of Institute of Technology, Jet Propulsion Laboratory, Pasadena, CA). Sound and Vibration, vol. 78, Oct. 8, 1981, p. 425-437. 18 refs. Journal of Applied Physics, vol. 52, Oct. 1981, p. 5988-5993. 13 Contract No. DAAG29-C-027. refs. Contract No. NAS7-100. An investigation of helicopter rotor blade slap was performed on The Theological behavior of the recently developed polymer a 1.27 m diameter model rotor. The rotor blades were a NACA 0012 FM-9 in Jet A fuel and JP 8 fuel is reported. In aqueous solution, FM section with a -8 deg linear twist. The experiments were conducted in 9 is found to exhibit strong time-dependent shear thickening the MIT Anechoic Wind Tunnel. The effects of number of blades, behavior. Induction time necessary for the onset of thickening is blade pitch, advance ratio, and shaft angle on the generation and found to depend on shear rate, solvent, concentration, and molecular intensity of blade slap have been investigated. The effect of each weight. Altering the nature of the solvent results in effects similar to parameter was determined by varying the parameter of interest while those obtained by changing the concentration or molecular weight. A keeping the others constant. The rotor tip speeds of the tests critical shear rate is derived, and is inversely proportional to the zero performed in this study were limited to approximately Mach 0.4. shear rate viscosity of the solution for the temperature and The directivity associated with the blade slap signature was mea- concentrations observed. The onset of shear thickening behavior sured. The results of this investigation are based on a subjective appears to be related to the onset of viscoelastic response, and thus definition of blade slap. (Author) the time scale follows reduced variable behavior. D.L.G. A82-11302 H Ideal and simulated performance of an aircraft A82-11222 Development of the Triflex rotor head. A. in the terrain following mission. U. R. Prasad (Indian Institute of Gassier (Societe Nationale Industrielle Aerospatiale, Marignane, Science, Bangalore, India) and B. S. Subrahmanyam. Aeronautical Bouches-du-Rhone, France). American Helicopter Society, Journal, Society of India, Journal, vol. 31, Feb.-Nov. 1979, p. 13-19. 8 refs. vol.26, July 1981, p. 25-31. A new synthesis method of terrain following system design to This paper reviews the development of a new hingeless rotor hub realize closely the ideal performance obtainable from an aircraft in named Triflex. This hub is made of composite materials and features the mission is presented. Ideal performance'analysis and division of flexible arms that provide blade retention, flap/lag/pitch degrees of the mission into Avoid and Follow modes of flight leads to natural freedom through structural deflection, and lag damping. A large part template constructions imbedding the aircraft climb performance of the Triflex hub design effort has been devoted to determination of and human pilot tolerance limits to accelerations. Simulation of the flexible arm characteristics, since these strongly affect the aircraft flight in the mission complements the analysis in fixing the behavior of the rotor in flight. The Triflex hub dynamic characteris- configuration and parameters of the system. Step terrains are used in tics were carefully checked during laboratory and whirl stand tests the design iterations of the system because of their worst-case and found to be in agreement with theoretical predictions. Flight character. (Author) tests of the Triflex rotor on a Gazelle helicopter were successful in demonstrating the feasibility of the concept. Though rotor lag A82-11314 »' Dynamic response of aircraft structure to gun damping was found to be weak, no insurmountable stability shock loads. P. N. Raju and V. P. Rangaiah (Hindustan Aeronautics, problems were encountered, and the flying qualities of the Gazelle Ltd., Bangalore, India). Aeronautical Society of India, Journal, vol. helicopter fitted with the Triflex hub were good. The next phase of 31, Feb.-Nov. 1979, p. 103-105. 5 refs. the Triflex hub development will be aimed at improving the hub's The dynamic response of a fighter aircraft to gun firing is structural damping characteristics and at optimizing the manufactur- assessed, the vibration levels on the airframe being measured by flight ing process. (Author) tests of the aircraft in the development phase. The aircraft is instrumented for measuring the vibration levels at various points on A82-11224 Fatigue substantiation of non-linear structures. the aircraft structure, for example, the wing tip, fuselage, tail plane, B. P. W. Stocker (United Technologies Corp., Sikorsky Aircraft Div., and aileron and elevator. The flight vibration data thus obtained is Stratford, CT). (American Helicopter Society, Midwest Region analyzed using standard methods available in the literature. The Helicopter Fatigue Methodology Specialists Meeting, St. Louis, MO, analyzed data is plotted to ascertain whether the vibration levels fall Mar. 1980.1 American Helicopter Society, Journal, vol. 26, July below the upper bounds of the envelope drawn from the previous 1981, p. 51-55. flight-test data for the aircraft of the same class. C.R. Structures such as preloaded joints and lugs frequently exhibit non-linear load/stress relationships at critical locations. This paper A82-11317 H Development of aircraft production engineer- presents some examples of such structures, including typical attach- ing discipline at NT, Bombay. N. K. Naik (Indian Institute of ment lugs and preloaded threaded attachments, to illustrate the Technology, Bombay, India). Aeronautical Society of India, Journal, importance of test load level selection and determination of load vs vol.31, Feb.-Nov. 1979, p. 119-125.

13 A82-11359

The aircraft production engineering courses offered at the given to strain measurement using two beam interferometry, Fabry- Indian Institute of Technology, in Bombay, are discussed. To Perot interferometry displacement measurement, and strain induced demonstrate the value of the courses, the fundamentals of aircraft birefringence. G.R. production are outlined, the discussion being confined to airframe production. The loft-template method is described, and the principal A82-11434 End losses in turbine cascades with porous loft-template scheme used in aircraft production is shown. Also cooling. V. M. Epifanov and V. I. Gus'kov. (Aviatsionnaia Tekhnika, described are the theory and laboratory courses offered at the no. 3, 1980, p. 46-49.) Soviet Aeronautics, vol. 23, no. 3, 1980, p. institute. C.R. 38-41. 7 refs. Translation. Experimental results on poroub-cooled turbine blades are pre- A82-11359 Nonlinear prediction of subsonic aerodynamic sented and discussed. Exit losses in the blades are found to depend loads on wings and bodies at high angles of attack. P. Zhu, W. Shou on coolant flowrate and the degree of roughness of the porous (China Aeronautical Establishment, Institute of Computing Technol- surface. B.J. ogy, Xi'an, Shaanxi, People's Republic of China), and S. Luo (Northwestern Polytechnical University, Xi'an, Shaanxi, People's A82-11444 Study of reingestion of exhaust gases with Republic of China). Computer Methods in Applied Mechanics and different initial temperature in a reversed turbojet engine. Z. V. Engineering, vol. 26, June 1981, p. 305-319. 6 refs. Akhtiamov and M. Sh. Giliazov. lAviatsionnaia Tekhnika, no. 3, This paper predicts numerically the nonlinear aerodynamic loads 1980, p. 101-103.) Sower Aeronautics, vol. 23, no. 3, 1980, p. on wings and bodies at high angles of attack in subsonic flow 87-89. Translation. separating along certain known lines. It is assumed that the separation vortices are symmetric and unbursting. The wing mean A82-11446 Results of experimental study of heat transfer surfaces and body surfaces are simulated by bound vortex lattices, to turbine blades with porous cooling. S. G. Dezider'ev, A. G. and the separation vortex surfaces by free vortex lines. The vortex Karimova, and V. I. Lokai. lAviatsionnaia Tekhnika, no. 3, 1980, p. system satisfies boundary conditions on wing and body surfaces, 109-112.) Soviet Aeronautics, vol. 23, no. 3, 1980, p. 97-99. 8 refs. separation conditions, and the condition that free vortex lines are Translation. tangent to local velocity. The velocity induced by a vortex is A82-11448 One reason for the onset of high-frequency computed by the Biot-Savart law with Gothert transformation for self-excited oscillations. V. P. Pavlovskii. (Aviatsionnaia Tekhnika, subsonic small perturbation flows. The vortex strengths and the free no. 3, 1980,p. 116-118.) Soviet Aeronautics, vol. 23, no. 3, 1980, p. vortex locations are solved by relaxation method. Then the aero- 104-106. 5 refs. Translation. dynamic loads on wings and bodies are computed. They agree well Experiments have been.carried out to investigate generation with experimental tests. (Author) mechanisms of high-frequency auto-oscillations resulting from an increase in the pressure differential across the combustion chamber A82-11400 A note on fatal aircraft accidents involving injectors of a flight vehicle engine. It is found that a possible reason metal fatigue. G. S. Campbell (National Aeronautical Establishment, for the onset of the high-frequency auto-oscillations is breakdown of Ottawa, Canada). International Journal of Fatigue, vol. 3, Oct. 1981, the annular gas cavity in the oxidizer injector nozzle which initiates p. 181-185. 6 refs. unstable combustion due to the vapor phase removal. V.L. A world-wide survey of aircraft accidents was taken to deter- mine the extent to which metal fatigue is responsible for the A82-11459 Calculation of aerodynamic characteristics of incidents. A total of 306 fatal accidents since 1934 were found to be jet flapped airplane. V. G. Akent'ev and V. V. Guliaev. (Aviatsion- either wholly or partially due to metal fatigue; these accidents naia Tekhnika, no. 4, 1980, p. 3-6.) Soviet Aeronautics, vol. 23, no. resulted in 1803 deaths. Two-thirds of the accidents involved 4, 1980, p. 1-4. Translation. fixed-wing iarcraft, with wing failure (88 accidents) being the most A numerical method is developed for calculating the steady-state common cause, followed by engine failure (56 accidents). Of the 90 aerodynamic characteristics of an aircraft with jet flaps. The flow fatal helicopter accidents, about a third were due to failure of the past the aircraft and the jet are modeled as a system of oblique main-rotor system, and a quarter were due to tail-rotor failure. Over horseshoe-shaped vortices, and the problem is solved in the linear the last four years there has been an average of 18 fatal accidents per formulation for an incompressible medium. B.J. year resulting from metal fatigue; about 11 have been for fixed-wing aircraft and seven have been for helicopters. Thirteen accidents were A82-11462 On low-speed wind tunnels with deformable attributed to a failure to increase the inspection frequency required boundaries. A. A. Gruzdev. (Aviatsionnaia Tekhnika, no. 4, 1980, p. for aircraft used in a role for which they were not originally 23-26.) Soviet Aeronautics, vol. 23, no. 4, 1980, p. 18-20. 7 refs. designed. J.F. Translation. Attention is given to the development of self-streamlining or A82-11406 A mathematical model of an over-sea airborne self-correcting wind tunnels. Linear theory under the assumption of UHF radio link. T. Slator. Marconi Review, vol. 44, 2nd Quarter, potential flow is used to study the shape of streamline surfaces near a 1981, p. 101-118. 9 refs. wing of finite aspect ratio moving near a screen. The characteristics A mathematical model is described which enables the perfor- of flow macrostructure in the wake are analyzed; and it is shown mance of an over-the-sea airborne UHF radio link to be estimated as that, in contrast to the case of two-dimensional flow, it is not a function of terminal height and separation distance taking account possible to streamline the walls of the tunnel in the absence of a statistically of variations of signal level caused by such factors as vortex wake in the case of three-dimensional flow. B.J. irregular antenna radiation patterns and a rough sea surface. (Author) A82-11463 Basic problem of aircraft gasturbine engine A82-11407 Optical sensors for displacement measurement analytic design. II. lu. V. Kozhevnikov, V. O. Borovik, V. S. Ivanov, S. M. McGlade. Marconi Review, vol. 44, 2nd Quarter, 1981, p. V. A. Talyzin, I. N. Agliullin, and lu. V. Meluzov. (Aviatsionnaia 119-136.7 refs. Tekhnika, no. 4, 1980, p. 27-32.) Soviet Aeronautics, vol. 23, no. 4, A measurement system consists of sensors which are connected 1980, p. 21-24. Translation. to a control center. The use of fiber optics as the communications The paper presents results of the analytical optimization of the link has a number of advantages. Two of the most important are basic thermogasdynamic parameters of the cycle and the characteris- immunity from electromagnetic interference and the elimination of tic areas of the air path of a turbojet bypass engine; the optimization the danger of electrical sparking in explosive environments. These criterion is minimum engine-mass and minimum fuel required for a advantages are reduced by the necessity to use electrical devices in given flight distance. The multimode character of engine operation is the sensors. If the sensors were wholly optical then the advantages of analyzed. B.J. fiber optics would apply to the entire system outside the control center. Optical sensors will be difficult to develop. Initially, at least, they are only justified in applications where such methods are A82-11464 Formation of triangular-element stiffness becoming essential. One such area is in military aircraft. An optical matrix using sliding interpolation. P. D. Levashov. (Aviatsionnaia displacement transducer can be obtained by using the displacement Tekhnika, no. 4, 1980, p. 33-37.) Soviet Aeronautics, vol. 23, no. 4, to alter the transmission aperture of a light beam. Attention is also 1980, p. 25-28. Translation.

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The paper examines the use of sliding interpolation to construct shown to have some application for the prediction of the effect of the stiffness matrix of triangular elements of flat rib-stiffened panels. design load on the fatigue life of lugs with interference fit, but for This approach makes it possible to raise the order of the displace- the case of lugs without interference fit, predicted and test results ment field by employing computational parameters from adjacent disagreed completely. The disagreement is explained by the effect of elements without increasing the total number of unknowns. A fretting. J.F. computational example is discussed. B.J. A82-11715 H New separators for battery systems. J. Lee and V. D'Agostino (RAI Research Corp., Hauppauge, NY). In: Intersoci- A82-11465 On evaluating the influence of local disrup- ety Energy Conversion Engineering Conference, 16th, Atlanta, GA, tions of flow over trailing edge and leading edge flaps from the data August 9-14, 1981, Proceedings. Volume 1 New of wind tunnel tests of a rectangular wing segment. A. I. Matiazh, V. York, American Society of Mechanical Engineers, 1981, p. 111-116. A. Sterlin, A. B. Kuznetsov, V. V. Isaev, A. A. Shapiro, and E. M. The reported study takes into consideration separators for Ksenofontova. (Aviatsionnaia Tekhnika, no. 4, 1980, p. 38-42.) miniature cells, such as silver/zinc button cells, and separators for Soviet Aeronautics, vol. 23, no. 4, 1980, p. 29-32. 5 refs. aircraft nickel/cadmium batteries. It is pointed out that separators Translation. for energy systems having an aqueous electrolyte, either acid or Equipment for the suspension and control of leading and trailing basic, can be prepared by selective modification of radiation grafting flaps was tested in a low-speed wind tunnel. The influence of the parameters. A new family of separators, known as the 'SC' series, has control mechanisms, and, of their positions along the wing span and in the cross section, on the integral aerodynamic characteristics of a been developed. The SC separators have very uniform electrolytic rectangular wing was evaluated. It is found that local disturbances of resistance, excellent mechanical strength, and lower cost. General flow past leading and trailing flaps produce a significant reduction of improvements in battery service life could be observed as a result of lift and an increase of drag. B.J. the introduction of the grafted separators. The cycle life of vented aircraft Ni/Cd batteries could be extended three to four times. G.R. A82-11468 On the use of carbon composites in slat and stabilizer construction. B. N. Kornev, R. I. Guseva, and V. A. A82-11716 H Sealed lead-acid batteries for aircraft applica- Tikhomirov. (Aviatsionnaia Tekhnika, no. 4, 1980, p. 72-74.) Soviet tions. K. L. Senderak and A. W. Goodman (U.S. Navy, Naval Aeronautics, vol. 23, no. 4, 1980, p. 59, 60. Translation. Weapons Support Center, Crane, IN). In: Intersociety Energy Glass-graphite-plastic composite materials were used in the Conversion Engineering Conference, 16th, Atlanta, GA, August 9- construction of aircraft deflectors and stabilizers. This paper reviews 14, 1981, Proceedings. Volume 1. New York, the details of construction, and examines static-load testing results American Society of Mechanical Engineers, 1981, p. 117-122. for both deflector and stabilizer. B.J. In the 1970's, an important advance in lead-acid battery technology occurred with, the introduction of sealed, no- maintenance, lead-acid batteries. A description is given of a wide A82-11469 Synthesis of system for evaluating gyrostabi- variety of studies and tests conducted to evaluate the suitability of Hzer state with unknown disturbances. A. A. Leporskii. (Avia- the new batteries for employment in Navy aircraft. The results show tsionnaia Tekhnika, no. 4, 1980, p. 74-76.) Soviet Aeronautics, vol. that the sealed lead-acid (SLA) cells can be successfully used in a 23, no. 4, 1980. p. 61-63. Translation. potentially large number of aircraft applications, where very high- rate discharge performance is not required. The Navy is actively A82-11470 On the question of trailing airplane motion. A. pursuing the SLA battery for these applications to substantially A. Novad. lAviatsionnaia Tekhnika, no. 4, 1980, p. 79-81.) Soviet reduce the Navy's overall battery procurement and maintenance Aeronautics, vol. 23, no. 4, 1980, p. 67, 68. Translation. costs, and to improve reliability. G.R. Equations are derived for tne three-dimensional motion of an aircraft and are solved analytically for the initiation of banking A82-11717 if Applications of finite element method in flight. The solution describes the effect of the specific wing load on aerospace power systems design. E. U. A. Siddiqui. In: Intersociety the normal acceleration overloading of the aircraft. It is noted that Energy Conversion Engineering Conference, 16th, Atlanta. GA, the danger of a spin increases with increasing specific load. B.J. August 9-14, 1981, Proceedings. Volume 1. New York, American Society of Mechanical Engineers, 1981, p. 123-126. A82-11471 Experimental study of empennage snap- Complex power systems are needed to satisfy the exacting through vibrations. V. A. Pavlov, F. Sh. Khakimullin, A. la. power requirements of current avionic systems. A suitable tool for Gur'ianov, and M. I. Gershtein. (Aviatsionnaia Tekhnika, no. 4, the design of such power systems is finite element analysis, based on 1980, p. 81-84.) Soviet Aeronautics, vol. 23, no. 4, 1980, p. 69-71. 5 the principle of minimization of total potential energy. This refs. Translation. technique is being successfully used to eliminate excess weight and to The snap-through oscillations of a rectangular-planform empen- accurately predict stresses and resonant frequencies. The new nage model were studied in a subsonic wind tunnel. The aim of the method was used to conduct an analysis in connection with a study was to isolate the snap-through oscillations from all other problem related to the occurrence of severe vibrations in a 30,000 possible oscillations in the flow. An analysis of changes of the normal rpm generator. The analysis had the objective to determine the and frontal curvatures of the control surface demonstrate the effects of modifications made to the generator frame. It was found occurrence of snap-through oscillations. The frontal curvature falls to that the resonant frequency could be raised above the operational practically zero in the case of static snap-through. B.J. speed of the generator by introducing suitable modifications to the design of the frame. G.R. A82-11685 Fatigue life of lugs under service loading - Test results and predictions. A. Buch and A. Berkovits (Technion - Israel A82-11718 # Advanced aircraft electric power system. J. D. Institute of Technology, Haifa, Israel). Materialprijfung, vol. 23, Oct. Segrest (U.S. Naval Material Command, Naval Air Development 1981, p. 344-348. 27 refs. Center, Warminster, PA). In: Intersociety Energy Conversion Engi- Aircraft pin-lug joints with and without interference fit were neering Conference, 16th, Atlanta, GA, August 9-14, 1981, Proceed- tested in maneuver loading programs with random loading sequence ings. Volume 1. New York, American Society of in order to investigate the effect of design load, lug material and Mechanical Engineers, 1981, p. 127-129. interference fit on the spectrum fatigue life. An interference fit of The Advanced Aircraft Electric Power System is to increase fuel 0.3% had a strong beneficial effect on the fatigue life for all loading efficiency and reduce life cycle costs. The system includes 270 volt programs, even when local tensile stress peaks exceeded the material DC generators, solid state regulation, flat bus distribution, solid state yield stress. The spectrum fatigue life of 2024-T351 lug specimens switching, digital multiplex control and protection of power distribu- was longer than that of 7075-T7351 specimens, except under the tion through a system algorithm, and switching regulator power most severe loading program. Test results were compared with conditioning. A description is presented of the system concept, the predictions based on the Miner's rule, the relative Miner rule, and the hardware development, and the status of the Navy program. A high Neuber-Topper notch analysis method. The relative Miner rule was voltage DC power system development had been initiated by the Superior to the conventional rule in predicting the spectrum fatigue Navy to exploit the advantages of high-voltage DC operation for. life of aircraft lugs; the Neuber-Topper notch analysis method was future aircraft. G.R.

15 A82-11719

A82-11719 H Variable speed constant frequency A/SCF/ suggested. The effects produced by electrode additives are also electrical system cuts cost of ownership. R. V. Hildebrant and R. C. discussed. G.R. VanNocker (General Electric Co., Aircraft Equipment Div., Bingham- ton, NY). In: Intersociety Energy Conversion Engineering Confer- A82-11740 ff High voltage surge and partial discharge test to ence, 16th, Atlanta, GA, August 9-14, 1981, Proceedings. Volume 1. evaluate aerospace equipment parts. W. G. Dunbar (Boeing Aero- New York, American Society of Mechanical space Co., Seattle, WA) and D. Schweickart (USAF, Wright Aeronau- Engineers, 1981, p. 130-135. 5 refs. tical Laboratories, Wright-Patterson AFB, OH). In: Intersociety The methodology employed in the development of the electrical Energy Conversion Engineering Conference. 16th. Atlanta. GA, generating system for the F/A-18 aircraft is considered. This system August 9-14, 1981, Proceedings. Volume 1. New was the first production application in which the cycloconverter York, American Society of Mechanical Engineers, 1981, p. 250-254. electronics were packaged with the generator and mounted directly Eight test articles were selected for high voltage evaluation to to the accessory gearbox. Being the first production system of this verify the specifications. The test articles represent critical compo- type, a detailed and comprehensive analysis and evaluation program nents of a high-voltage, high-power airborne system. A description is was undertaken to provide assurance that the design could operate presented of the findings of these tests in the case of the capacitors. with a high degree of reliability in this generally hostile environment. Each capacitor was given preliminary tests to determine insulation A primary maintainability design objective was related to the design resistance at 100 volts dc, and the capacity using a standard ASTM and the selection of parts and materials which would last for the life capacitance bridge at low voltage. It was found that the insulation of the unit without scheduled maintenance. Attention is given to resistance and capacitance test methods and parameters are accept- maintenance cost experience and life cycle costs. G.R. able. The partial discharge and dielectric withstanding voltage and surge test methods are acceptable, but the test parameters for A82-11720 * A hidden advantage of permanent magnet airborne capacitors must be lower than those specified for commer- electrical generating systems. J. J. O'Neill (General Electric Co., cial capacitors. G.R. Binghamton, NY). In: Intersociety Energy Conversion Engineering Conference, 16th, Atlanta, GA, August 9-14, 1981, Proceedings. A82-11899 Increasing the lift:drag ratio of a flat delta Volume 1. New York, American Society of wing. A. A. Mattick and J. L. Stollery (Cranfield Institute of Mechanical Engineers, 1981, p. 136-139. 7 refs. USAF-supported Technology, Cranfield, Beds., England). Aeronautical Journal, vol. research. 85, Oct. 1981, p. 379-386. The development of permanent magnet aircraft electrical gener- Increases in the lift/drag (L/D) ratio attained by placing flaps on ating systems heralds the beginning of a new era. This technique the upper surface of a flat, 60 deg, small aspect ratio delta wing are brings many advantages to the user in terms of size, weight and reported. The flaps were positioned along a ray from the vertex of reliability. However, the most significant of these advantages is the the wing; their height, increasing from the vertex to the trailing edge, extremely high efficiency which is characteristic of these systems. was a percentage of the semispan, and they were hinged at the lower This paper examines the effect of the higher system efficiency on the edge. Position and heights were varied and lift and drag forces were user, specifically in the area of aircraft fuel consumption. Driven by measured over a range of angles of attack. The flaps were found to rising fuel costs, engine and aircraft manufacturers are striving for cause a lift force to act on themselves, up to a height of 6.1% of the more efficient performance to minimize life cycle costs. The results semispan, by causing air from the primary vortex core to separate of a study which examines the effect of several permanent magnet and form a vortex on the outboard side of the flaps. A maximum ratings on different aircraft sizes are presented. (Author) increase of 33% in the L/D was determined and it is noted that all the vertical flaps tested produced a positive thrust force. Graphs are provided of the derived aerodynamic ratios. M.S.K. A82-11721 # 60 KVA ADP permanent magnet VSCF starter generator system - Generator system performance characteristics. R. A82-11927 ff Fast and accurate gyrocompass using strap- C. Webb (General Electric Co., Binghamton, NY). In: Intersociety down tuned rotor gyros as a solution to combat helicopters Energy Conversion Engineering Conference, 16th, Atlanta, GA, navigation problems. P. Lloret, X. Lagarde, and G. Lavoipierre August 9-14, 1981, Proceedings. Volume 1. New (Societe d'Applications Generales d'Electricite et de Mecanique, York, American Society of Mechanical Engineers, 1981, p. 140-145. Paris, France). In: Symposium Gyro Technology 1980; Proceedings Contracts No. F33615-78-C-2200; No. F33615-74-C-2037. of the Symposium, Stuttgart, West Germany, September 24, 25, A description is presented of a Variable Speed Constant 1980. . Diisseldorf, Deutsche Gesellschaft fur Frequency (VSCF) system, which consists of a cycloconverter with a Ortung und Navigation, 1981, p. 1.0-1.25. synchronous generator that uses samarium cobalt magnets for its Results of verification tests to determine if gyrocompass excitation. As part of its normal operation, the converter regulates mechanization can be used to find true headings within 0.5 deg in each output wave in frequency and in voltage providing the necessary less than two minutes for helicopter navigation are presented. A voltage regulation for a permanent magnet (PM) generator. The strapdown inertial-Doppler navigation system which uses a pair of cycloconverter is capable of reverse power flow and the PM generator two-axis tuned rotor gyroscopes is described. The high accuracy of has the necessary excitation at standstill to make it possible to run mechancial gyroscopes is attributed to the repeatability of the the system as a brushless starter. Attention is given to the phases of thermal behavior of tuned rotor gyroscopes. The gyros were the development program, system operation, start mode operation, temperature measured externally and in the instrument block, and and test results. It is pointed out that the PM VSCF system offers a correlations were sought between temperatures and drift patterns. significant improvement in electrical generating system efficiency Although true correlations were necessarily synthetic, drift rates of over presently used systems. G.R. 15 deg/hr were reduced to 0.5 deg/hr peak residual drifts, confirming the potential use of 0.5 deg accuracy, two minute true heading A82-11725 ft Unsolved problems of nickel cadmium bat- mechanical gyroscopes as a complement to magnetic headings.M.S.K. teries. S. Gross (Boeing Aerospace Co., Seattle, WA). In: Intersociety Energy Conversion Engineering Conference, 16th, Atlanta, GA. A82-11932 s Design and development of a low cost servoed August 9-14, 1981, Proceedings. Volume 1. New rate gyro for unmanned aircraft. D. R. McKenzie (Smiths Industries York, American Society of Mechanical Engineers, 1981, p. 177-181. Aerospace and Defence Systems Co., Cheltenham, Glos., England). 8 refs. In: Symposium Gyro Technology 1980; Proceedings of the Sympo- A number of problems occurring with nickel cadmium battery sium, Stuttgart, West Germany, September 24, 25, 1980. systems are primarily important for aerospace applications, where Diisseldorf, Deutsche Gesellschaft fur Ortung und reliable, long'life is essential. Some of the problems are related to the Navigation, 1981, p. 14.0-14.56. design of plaques to obtain a large capacity and a long operational The development of a low cost rate gyro for use in unmanned life. Other subjects investigated are nickel electrode morphology vehicles is presented. The design parameters for the low weight gyro, changes, nickel electrode cycling degradation, and the effects of which has an input range of plus or minus 50 deg/sec and can operate cadmium migration. It is found that more work is needed for a better from a low voltage dc power source are outlined. A conventional understanding of the various factors involved. The development of a design, comprising a spinning rotor on a gimbal with torque restraint computerized mathematical model of the nickel cadmium cell is and dynamic damping, was chosen to minimize cost and time; a

16 A82-11999 feedback approach was adopted to maintain performance stability. A A82-11940 ti The certification of digital systems. D. J. rotational speed of 10,000 rpm with a polar moment of inertia of 20 Hawkes (Civil Aviation Authority, London, England). In: Digital g/sq cm was selected. The pick-off, torque motor, servoamplifier, and avionics - Promise and practice; Proceedings of the Joint Symposium, plastic molding are discussed and performance figures for 25 gyros London, England, March 20, 1980. London, are presented. A pulsed motor circuit was developed to maintain Royal Aeronautical Society, 1981. 12 p. 9 refs. motor speed within 7% of the set value over the operating The present situation in the field of airworthiness certification temperature range; elimination of a wheel speed control improved of digital systems is reviewed and the future certification task is nonlinearity and reduced costs. Circuitry diagrams and schematics examined with emphasis on safety-critical applications. It is shown are provided. M.S.K. that the existing certification requirements are adequate for the new generation of digital systems. For the foreseeable future, the A82-11933 ff Design considerations for the direct digital certification task will be very similar to that currently undertaken control of dry-tuned gyroscope. S. N. Puri (Indian Space Research and will involve performance verification, environmental testing, and Organization, Vikram Sarabhai Space Centre, Trivandrum, India). In: safety analyses. The certification task will be refined and judgement Symposium Gyro Technology 1980; Proceedings of the Symposium, will be improved as the weaknesses and peculiarities of digital Stuttgart, West Germany, September 24, 25, 1980. systems are exposed. V.L. Diisseldorf, Deutsche Gesellschaft fiir Ortung und Navigation, 1981, p. 15.0-15.25. A82-11941 H Digital avionics systems-The RAF experience. The use of direct digital processor control of dry-tuned gyros is B. J. Hunter (RAF, London, England). In: Digital avionics - Promise examined. Direct control is implemented because of a finite and practice; Proceedings of the Joint Symposium, London, England, processing time lag between input and output, and is aided by March 20, 1980. London, Royal Aeronautical minimizing the computation time by compensating for the effects of Society, 1981. 6 p. rounding coefficients in the control algorithm. The minimum settling The RAF's practical experience in operating digital avionic time is discussed analytically and a design is developed that reduces systems is reviewed with reference to a computer-based navigation complexity in the control function, offers lower torque demands, and attack system that forms part of a pilot/aircraft control loop for and has acceptably small steady state error. A retarded response is navigation, weapon aiming, and flight direction installed on Jaguar mentioned, and the use of a digital processor is found to add delays aircraft. The system has proved to be flexible and reliable; in the rebalance loops, requiring specific positioning of zeroes in the modifications of the system can now be accomplished by a software, determinant of the pulse transfer function. An example is given, rather than hardware, change; and the first and second line testing noting that pick-off noise at the spin frequency or its harmonics can has been reduced. The software maintenance practice and manage- be eliminated by use of a notch filter. Finally, a compromise is ment are discussed in detail. V.L. viewed as possible if slightly increased overshoot and settling time are found acceptable with a prescribed computing delay. M.S.K. A82-11942 ff Digital avionics: Promise and practice - An airlines experience in the field. J. E. Mills (British Airways, A82-11934 Digital avionics - Promise and practice; Pro- Hounslow, Middx., England). In: Digital avionics - Promise and ceedings of the Joint Symposium, London, England, March 20, practice; Proceedings of the Joint Symposium, London, England, 1980. Symposium sponsored by the Royal Aeronautical Society and March 20, 1980. London, Royal Aeronautical Institution of Electrical Engineers. London, Royal Aeronautical Society, 1981. 4 p. Society, 1981. 72 p. The British Airways experience with digital avionic systems is reviewed with regard to the initial expectations, achievements, and Papers presented at the symposium provide an overview of the maintenance and engineering problems encountered. It is shown that current status of digital avionic systems with emphasis on the the introduction of digital systems into civil aviation did not produce practical experience in operating these systems, achievements and the promised increase in reliability, the self test results being problems, and advanced technologies available. Topics discussed particularly disappointing. However, no maintenance problems of include: the influence of digital techniques on system architecture, any great significance have been encountered. It is expected that the certification of digital systems, the all digital military aircraft, and an use of custom LSI and microprocessors will diminish problems airline's experience in the field. V.L. previously associated with hardware and will provide improved reliability and more competent self test and monitoring, leading to A82-11937 ff The all digital military aircraft D. Roughton improved first line servicing. V.L. (British Aerospace Public, Ltd., Co., Brough, England). In: Digital avionics - Promise and practice; Proceedings of the Joint Symposium, London, England, March 20, 1980. London, A82-11997 H The CIVIC - A concept in vortex induced Royal Aeronautical Society, 1981. 14 p. combustion. II. J. R. Shekleton (Solar Turbines International, Developments in avionic systems over the past two decades are Turbomach Div., San Diego, CA). {American Society of Mechanical reviewed. The main factor that emerges is the conflict between the Engineers, International Gas Turbine Conference, Houston, TX, Mar. increasing complexity required to meet operational demands and the 8-12, 1981, Paper 81-GT-12.) ASME Transactions, Journal of need for simplicity of operation to ease the workload of the reduced Engineering for Power, vol. 103, Oct. 1981, p. 708-717. 34 refs. aircrew. In future aircraft, as the number and type of systems The development of vortex induced combustion is reviewed, continue to grow, system integration and system automation are noting that the modelling is based on convective processes in essential to ensure that the pilot workload is kept at an acceptable unequally heated adjacent air masses. The aerodynamics of vortex level. V.L. flow are analytically examined, and reaction criteria in gas turbine and reciprocating engine vortex combustors are presented. Buoyant A82-11938 K The digital civil aircraft J. F. Moore (British mixing to achieve fast, near constant volume combustion in diesel Aerospace Public, Ltd., Co., Aircraft Group Div., Bristol, England). engines is described for two cases. Use of a rotating cup fuel injector In: Digital avionics - Promise and practice; Proceedings of the Joint in a 10 kW gas turbine to provide good atomization with viscous Symposium, London, England, March 20, 1980. fluids, even in arctic conditions, is discussed, including a new design London, Royal Aeronautical Society, 1981. 16 p. feature which avoids injecting the fuel mist into the swirl air. Test The development of digital avionics is reviewed with particular results and schematics are presented of various applications, stressing reference to application in civil aircraft. Examples of in-service the ability of vortex induced combustion to display efficiencies with systems in which digital technology has been already implemented standard liquid fuels usually obtained only with natural gas. M.S.K. are examined, including inertial navigation systems, aircraft integrat- ed data systems/accident data recording, multiplexing systems, and A82-11999* j Thermal expansion accommodation in a jet the air intake control system of Concorde. Attention is given to the engine frame. M. H. Schneider (General Electric Co., Cincinnati, potential benefits of new applications, current developments, practi- OH). (American Society of Mechanical Engineers, Gas Turbine cal aspects, and implications of functional integration. Finally, future Conference and Products Show, Houston, TX, Mar. 9-12, 1981.1 applications are discussed such as full digital engine control and flight ASME Transactions, Journal of Engineering for Power, vol. 103, Oct. controls (fly-by-wire system). V.L. 1981, p. 776-780. Contract No. NAS3-20643.

17 A82-12021

Design advancements to enhance stress accommodation in gas structures, design, structural dynamics and materials; Proceedings of turbine engine frames are described. Consideration is given to the Aerospace Conference, San Francisco, CA, August 13-15, 1980. mechanical stiffness to maintain an adequate spring rate, and to New York, American Society of Mechanical thermal stresses in both ambient and transient modes. Noting that Engineers, 1980, p. 11-26. 10 refs. Grant No. NsG-1296. thermal stresses occur due to differing temperatures at different parts An experimental investigation was conducted to study the effect of the frame, the matching of the thermal expansion rates of of low velocjty projectile impact on the sandwich-type structural different structural materials is emphasized. Adequate stiffness is components. The materials used in the fabrication of the impact necessary to avoid dynamic reactions leading to case cracking as a surface were graphite-, Kevlar-, and boron-fibers with appropriate result of normal imbalances of moving parts. Stress and deflection epoxy matrices. The testing of the specimens was performed at analysis of a total frame concept using a three-dimensional finite moderately low- and high-temperatures as well as at room tempera- element stress analysis computer program, with modelling of all ture to assess the impact-initiated strength degradation of the frame components, is presented, and illustrations are provided. laminates. Eleven laminates with different stacking sequences, M.S.K. orientations, and thicknesses were tested. The low energy projectile impact is considered to simulate the damage caused by runway A82-12021 t Jet fuel from carbon (Reaktivnoe toplivo iz debris, dropping of the hand tools during servicing, etc., on the uglia). A. A. Krichko, M. K. lulin, A. C. Arifulin, T. C. Nikiforova, secondary aircraft structures fabricated with the composite materials. and V. A. Puchkov (Akademiia Nauk SSSR, Institut Goriuchikh The results show the preload and the impact energy combinations Iskopaemykh, Moscow, USSR). Khimiia i Tekhnologiia Topliv i necessary to cause catastrophic failures in the laminates tested. A set Masel, no. 9, 1981, p. 3-5. 8 refs. In Russian. of faired curves indicating the failure thresholds is shown separately A jet fuel of the T-8V type has been obtained by isomerization for the tension- and compression-loaded laminates. The specific- and hydrogenation at 4 MPa of the hydrorefined 180-320 C fraction strengths and -moduli for the various laminates tested are also given. of a liquid-phase carbon hydrogenation product. The flow scheme (Author) and the material balance of the process are presented. V.L. A82-12039 # Coupled fluid/structure response predictions A82-12022 t A protective additive for jet fuels (Zashchit- for soft body impact of airfoil configurations. J. J. Engblom (United naia prisadka k reaktivnym toplivam). 0. P. Lykov. G. I. Shor, V. P. Technologies Corp., Government Products Div., West Palm Beach, Lapin, V. V. Sashevskii, and L. I. Mosina (Moskovskii Institut FL). In: Emerging technologies in aerospace structures, design, Neftekhimicheskoi i Gazovoi Promyshlennosti, Moscow, USSR). structural dynamics and materials; Proceedings of the Aerospace Khimiia i Tekhnologiia Topliv i Masel, no. 10, 1981, p. 37-40. 6 refs. Conference, San Francisco, CA, August 13-15, 1980. In Russian. New York, American Society of Mechanical Engineers, A study has been carried out to investigate the protective action 1980, p. 209-223. 8 refs. Research supported by the United of an additive to jet fuels which consists of a mixture of dinners and Technologies Corp. trimers of synthetic fat acids. Results indicate that there exists a Jet engine overhaul costs related to foreign object damages correlation between changes in the protective properties of the fuel (FOD) are a significant concern in aircraft operations. Present FOD as a function of the additive content, on the one hand, and changes design systems, however, are not applicable to advanced airfoil in certain electrophysical characteristics of the fuel (e.g., conductiv- configurations. An analytical design tool has therefore been devel- ity, contact potential difference change, and electrifiability), on the oped to improve the FOD response prediction capability for the soft other hand. V.L. body impact of metal or composite fan blades, and is implemented by a finite element computer code. The basic approach involves A82-12025 * Design predictions for noise control in the coupling a fluid loading model with a structural model for the blade. cryogenic National Transonic Facility. W. S. Lassiter (NASA, Iterative effects are included in the solution, i.e., applied loads are a Langley Research Center, Hampton, VA). Noise Control Engineering, function of the structural response. Solutions include the effects of vol. 17, Sept.-Oct. 1981, p. 76-84. 6 refs. large displacement (geometric) and material (inelastic) nonlinearities. Noise control in the National Transonic Facility - a cryogenic The code is also modified to treat the response of hybrid composite wind tunnel - has been examined in terms of acoustical design materials, demonstrating its capability to meet impact response criteria, drive-fan noise and exhaust system noise. A duct lining with predictions for complex metal or composite airfoil configurations. It two layers of perforated sheeting and a gas-filled honeycomb core is concluded that the analysis can be used to support the design of was selected for attenuating drive-fan noise. With the exception of future high tip speed FOD-tolerant fan blades. J.F. attenuation peaks, attenuation of the lining was found to experimen- tally agree with predicted values at 20 C air temperatures. Exhaust A82-12041 it Response of nonlinear aircraft structural pan- system noise will be attenuated with a large muffler used in els to high intensity noise. C. Mei (Old Dominion University, conjunction with a 6.1-m high acoustical enclosure. Fan noise from Norfolk, VA). In: Emerging technologies in aerospace structures, the fan-ejector system will be attenuated by fan silencers and the design, structural dynamics and materials; Proceedings of the acoustic enclosure. S.C.S. Aerospace Conference, San Francisco, CA, August 13-15, 1980. New York, American Society of Mechanical A82-12026 Emerging technologies in aerospace structures, Engineers, 1980, p. 245-272. 17 refs. Contract No. design, structural dynamics and materials; Proceedings of the F49620-79-C-0169. Aerospace Conference, San Francisco, CA, August 13-15, 1980. Design methods and design criteria for sonic fatigue prevention Conference sponsored by the American Society of Mechanical have been developed based on analytical and experimental tech- Engineers. Edited by J. R. Vinson (Delaware, University, Newark, niques. This paper presents an analytical method for predicting the DE). New York, American Society of Mechanical Engineers, 1980. response of rectangular nonlinear structural panels subjected to 333 p. $20. broadband random acoustic excitation. The formulation is based on Topics discussed include the emerging technologies in composite the Karman-Herrmann large deflection plate equations, a single-mode materials structures, in materials, and in structural dynamics, shock Galerkin approximation, the equivalent linearization method, and an and impact. Particular attention is given to impact-initiated damage iterative procedure. Both simply-supported and clamped-support thresholds, adhesively bonded joints in composites, stress concentra- conditions with immovable or movable inplane edges are considered. tions in bonded multilayer stiffened strips and base plates, and the Panel mean-square deflection, maximum mean-square stress, and fatigue life of coldworked holes. Consideration is also given to the equivalent linear frequency at various acoustic loadings are deter- response of nonlinear aircraft structural panels to high intensity mined and presented in graphical form. The results obtained were noise, the dynamic numerical analysis of crack initiation, fast crack shown to agree well with experimental ones, and suggestions for propagation and crack arrest, and the energy release rate of a further research are given. J.F. penny-shaped crack at the fiber-end of a composite. J.F. A82-12043 # Crack growth evaluation of a method to A82-12028 * H Impact-initiated damage thresholds in compos- convert real-time loads history to a simplified engineering spectra. E. ites. A. V. Sharma (North Carolina Agricultural and Technical State J. Ferko (Lockheed-Georgia Co., Marietta, GA). In: Emerging University, Greensboro, NC). In: Emerging technologies in aerospace technologies in aerospace structures, design, structural dynamics and

18 A82-12120

materials; Proceedings of the Aerospace Conference. San Francisco, parameters which must be given due consideration by the fluidic CA, August 13-15, 1980. New York, American system designer. Included are the interfacing of the technology with Society of Mechanical Engineers, 1980, p. 285-294. 6 refs. other system components. Case histories of three fluidic control The random and independent nature of shear and axial stresses applications are cited. C.R. due to gust sources poses a complex problem for the structural analysis of cracks emanating from fastener holes in spanwise and A82-12100 Quantification of the thermal environment for beam-web splices of a transport aircraft wing. A practical engineering externally carried aircraft stores and ordnance. H. Schafer and I. solution to the shear/axial stress interaction problem was developed Barbe (U.S. Naval Weapons Center, China Lake, CA). Journal of for the C-5A wing, and a box beam test program was conducted to Environmental Sciences, vol. 24, Sept.-Oct. 1981, p. 23-26. evaluate the solution. The evaluation was accomplished by com- Thermal testing procedures for aircraft external stores and paring crack propagation rates generated by testing flight measured ordnance are discussed, noting the importance of considering the real time histories (RTH) with the engineering solution (referred to entire range of possible thermal environments for each tested as the Equivalent Analytical Representation spectra). The baseline component. A method is proposed in which necessary parameters of RTH spectra consisted of loads data recorded during dynamic environmental variables such as aircraft speed, altitude, air tempera- response flight testing. The EAR spectra was derived from the ture, and amount of fuel available are considered in terms of aforementioned RTH data and was analytically developed utilizing percentiles. A Gaussian distribution is assumed for each environmen- peak counting methods and the empirical shear/axial stress inter- tal range, enabling for example, the elimination of extreme high and action solution. Fractographic correlation of numerous cracks low flight speeds from average environment estimates. Use of the indicated that the EAR spectra adequately simulated the random Arnold Research and Development Center standard atmosphere was nature of shear and axial stresses in the RTH data. (Author) found to be preferrable for engineering considerations because of inherent biasing errors in the MIL-STD-210 hot and cold data A82-12045 # Numerical treatment of helicopter rotor stabil- atmosphere. Techniques of cross-correlating environmental percen- ity problems. R. Vepa and T. S. Balasubramanian (National tiles are defined, and it is emphasized that thermal gradients cause Aeronautical Laboratory, Bangalore, India). In: Emerging techno- the greatest hardware performance degradation. M.S.K. logies in aerospace structures, design, structural dynamics and A82-12107 H The dispersion of drop sizes in gas turbine fuel materials; Proceedings of the Aerospace Conference, San Francisco, nozzle sprays. D. L. Markham (Ex-Cell-O Corp.. Walled Lake, Ml). CA, August 13-15, 1980. New York, American In: Fluid mechanics of combustion systems; Proceedings of the Society of Mechanical Engineers, 1980, p. 307-319. 14 refs. Research Fluids Engineering Conference, Boulder, CO, June 22, 23, 1981. supported by the Ministry of Defence. New York. American Society of Mechanical The problem of calculating the Floquet transition matrix for Engineers, 1981, p. 95-100. 6 refs. parametric stability problems is considered. A new method of The dispersion of drop sizes in sprays as produced by gas turbine calculating the transition matrix with a minimum number of time fuel nozzles was studied by conducting a large number of tests on steps is described. The method is shown to be extremely efficient for several fuel nozzle sprays using a Malvern ST1800 Particle and a wide class of helicopter stability problems, including flapping Droplet Size Distribution Analyzer. It is found that the size stability of a helicopter rotor, helicopter ground resonance with a dispersion of a spray depends on the location where the spray cloud nonisotropic rotor and pitch-flap-bending stability of a helicopter is sampled, nozzle type, and nozzle operating condition. It is rotor in forward flight. The relationship of the method to the concluded that to fully specify the drop size characteristics of a gas classical method of averaging is pointed out. (Author) turbine fuel nozzle spray, not only must the mean drop size of the drop size distribution be reported, but also the drop size dispersion. A82-12048 ACMA - Fact or fantasy. W. T. Mikolowsky P.T.H. and W.-A. Garrett (Lockheed-Georgia Co., Marietta, GA). Lockheed Horizons, Fall 1981, p. 2-12. A82-12118 # Application of numerical modeling to gas The feasibility of the advanced civilian/military aircraft (ACMA) turbine combustor development problems. G. J. Sturgess, S. A. Syed, for use as both an advanced military airlift vehicle and a commercial and D. Sepulveda (United Technologies Corp., Commercial Products airfreighter is discussed. A partnership in development between Div., East Hartford, CT). In: Fluid mechanics of combustion government and industry is expressed as necessary to reduce costs systems; Proceedings of the Fluids Engineering Conference, Boulder, through larger production quantities, to increase emergency airlift CO, June 22, 23, 1981. New York, American capabilities in the Civil Reserve Air Fleet, and commercial mainte- Society of Mechanical Engineers, 1981, p. 2" i-250. 23 refs. nance of military aircraft. Design options and requirements are The effects of dome cooling air changes in an experimental presented along with timetables, showing production delivery to combustor for a large, turbofan gas turbine engine are investigated by commence in 1994. Topics such as commercial need, energy use, means of perturbation studies carried out with numerical modeling. engine design, and financial planning are examined, with emphasis on Two geometrical configurations are examined at high engine power system features that enhance the commercial attractiveness of the levels, and calculated changes in the flow fields are compared with vehicle. A preliminary configuration shows a payload capability of evidence obtained from experimental engines. Changes in dome and 390,000 Ibs with a fuel efficiency 50% better than that of the liner pressure drops are observed with severe dome distress in one of 747-200F. M.S.K. the configurations. It is concluded that the combustor simulations are qualitatively correct and have satisfactory quantitative agreement A82-12049 History of flight testing the L-1011 TriStar jet without requiring exact geometrical representations. D.L.G. transport. II • Testing highlights since initial certification of the L-1011-1. R. J. Gatineau (Lockheed-California Co., Palmdale, CA). A82-12120 • # On the prediction of swirling flowfields found Lockheed Horizons, Fall 1981, p. 14-29. in axisymmetric combustor geometries. D. L. Rhode, D. G. Lilley, and D. K. McLaughlin (Oklahoma State University, Stillwater, OK). A82-12087 H Considerations and applications for the use of In: Fluid mechanics of combustion systems; Proceedings of the fluidics in aerospace controls. T. G. Sutton (AiResearch Manufactur- Fluids Engineering Conference, Boulder, CO. June 22, 23, 1981. ing Company of Arizona, Phoenix, AZ). In: 20th Anniversary of • New York, American Society of Mechanical Fluidics Symposium, Chicago, IL, November 16-21, 1980, Proceed- Engineers, 1981, p. 257-266. 32 refs. Grant No. NAG3-74. ings. New York, American Society of Mechanical The paper reports research restricted to steady turbulence flow Engineers, 1980, p. 73-79. 6 refs. in axisymmetric geometries under low speed and nonreacting Fluidics technology has been considered for use in controls in conditions. Numerical computations are performed for a basic aerospace environments in order to obtain reliable and cost-effective two-dimensional axisymmetrical flow field similar to that found in a systems. White many applications involving fluidics have been in conventional gas turbine combustor. Calculations include a stairstep production for several years, there have been a number of failures boundary representation of the expansion flow, a conventional while attempting to apply fluidics technology to aerospace applica- k-epsilon turbulence model and realistic accomodation of swirl tions. Because of this, fluidic techniques must be very carefully effects. A preliminary evaluation of the accuracy of computed evaluated for any application before being considered as the most flowfields is accomplished by comparisons with flow visualizations desirable technology to be used. An overview is given of design using neutrally-buoyant helium-filled soap bubbles as tracer particles.

19 A82-12149

Comparisons of calculated results show good agreement, and it is reliability literature. Attention is given to the determination of the found that a problem in swirling flows is the accuracy with which the time-to-failure distribution of a component, the sources of com- sizes and shapes of the recirculation zones may be predicted, which ponent failure data, the real world of electronic component may be attributed to the quality of the turbulence model. D.L.G. procurement, the time to first failure for new systems, and system survivor functions for certain component distributions. Redundancy A82-12149 Determination of vertical profiles of aerosol and survivor functions of systems are considered along with size spectra from aircraft radiative flux measurements. II - The effect questions related to renewal theory and mean time between failures, of particle nonsphericity. R. M. Welch (Mainz, Universitat, Mainz, a Monte Carlo investigation of systems based on normal distribu- West Germany), S. K. Cox (Colorado State University, Fort Collins, tions, and subjects related to precision, confidence, and numbers CO), and K. la. Kondrat'ev (Glavnaia Geofizicheskaia Observatoriia, tested. G.R. Leningrad, USSR). Journal of Geophysical Research, vol. 86, Oct. A82-12323 Antenna theory and design. W. L. Stutzman 20, 1981, p. 9795-9800. 28 refs. NSF Grants No. ATM-78-05743; (Virginia Polytechnic Institute and State University, Blacksburg, VA) No. ATM-77-22384. and G. A. Thiele (Dayton, University, Dayton, OH). New York, John A82-12170 t Control of electromechanical actuator ele- Wiley and Sons, 1981. 608 p. 158 refs. $30.95. ments for flight vehicles (Upravlenie ispolnitel'nymi elementami Antenna fundamentals and definitions are examined, taking into slediashchikh elektroprivodov letatel'nykh apparatov). B. I. Petrov, account electromagnetic fundamentals, the solution of Maxwell's V. V. Bal'bukh, N. P. Pappe, V. P. Pappe, V. A. Serdiuk, and V. G. equations for radiation problems, the ideal dipole, the radiation Stebletsov. Moscow, Izdatel'stvo Mashinostroenie, 1981. 222 p. 40 pattern, directivity and gain, reciprocity and antenna pattern refs. In Russian. measurements, antenna impedance and radiation efficiency, antenna The control theory of electromechanical actuator elements is polarization, antennas in communication links and radar, and the developed with particular reference to application in electrical flight receiving properties of antennas. Some simple radiating systems are control systems (e.g., for tactical missiles). Attention is given to the considered along with arrays, line sources, wire antennas, broadband use of ac motors and dc motors in such systems, and to digital antennas, moment methods, and aperture antennas. High-frequency actuator systems. The limiting dynamic possibilities and energetic methods and aspects of antenna synthesis are discussed, giving characteristics of electromechanical actuators are considered. B.J. attention to geometrical optics, physical optics, wedge diffraction theory, the ray-fixed coordinate system, the cylindrical parabolic A82-12222 t The enhancement of heat exchange in chan- antenna, and linear array methods. G.R. nels /2nd revised and enlarged edition/ (Intensifikatsiia teploobmena v kanalakh /2nd revised and enlarged edition/1. E. K. Kalinin, G. A. A82-12449 Commercial EMS considerations for small gas Dreitser, and S. A. larkho. Moscow, Izdatel'stvo Mashinostroenie, turbine engines. R. Halliday (Pratt and Whitney of Canada, Ltd., 1981. 208 p. 199 refs. In Russian. Longueuil, Quebec, Canada). In: Aircraft gas turbine engine monitor- An analysis is presented of various means for the enhancement ing systems; Proceedings of the Aerospace Congress and Exposition, of heat exchange in the heat exchange channels of flight vehicles. Los Angeles, CA, October 13-16, 1980. Congress and Exposition The factors governing the selection of heat exchange enhancement sponsored by the Society of Automotive Engineers. Warrendale, PA, method are considered, and specific methods applicable to right Society of Automotive Engineers, Inc., 1981, p. 23-26. It is shown that electronic automated engine monitoring systems channels and longitudinal flow around a bundle of tubes, and curved (EMS) offer advantages over manual methods for power assurance, channels are indicated. Attention is then given to the methods and trend and limit exceedance monitoring, and low cycle fatigue and mechanisms of heat exchange enhancement in pipes, around pipe creep life recording. System cost, which is the main constraint on bundles and in circular channels, in two-dimensional and triangular EMS for small gas turbines, is proportional to the number of channels, taking into account the effects of hydraulic resistance and parameters measured. Although EMS cost may preclude a full the effectiveness of the various methods is evaluated. The enhance- diagnostic capability, it may be reduced by 'piggy backing' with ment of heat exchange in the presence of film boiling on the one other systems, such as those for fuel control or flight monitoring. hand and condensation on the other in channels is also examined. Future EMS are predicted to be part of modular, fully integrated A.L.W. systems employing multiplexing techniques. It is concluded that A82-12267 tt Validation studies of turbulence and combus- ARP 1587 is needed for that level of integration to be achieved. tion models for aircraft gas turbine combustors. S. A. Syed and G. J. Among the parameters monitored by an EMS are turbine tempera- Sturgess (United Technologies Corp., Commercial Products Div., East ture, gas generator speed, free turbine speed, output torque, pressure Hartford, CT). In: Momentum and heat transfer processes in altitude, and outside air temperature. O.C. recirculating flows; Proceedings of the Winter Annual Meeting, Chicago, IL, November 16-21, 1980. New York, A82-12450 Further application and development of an American Society of Mechanical Engineers, 1980, p. 71-89. 29 refs. engine usage/life monitoring system for military services. R. Holl. In: The paper describes work performed as part of a continuing Aircraft gas turbine engine monitoring systems; Proceedings of the program to explore computational fluid dynamics procedures and Aerospace Congress and Exposition, Los Angeles, CA, October related turbulence and combustion models for application to the 13-16, 1980. Congress and Exposition sponsored by the Society of design, understanding, and development of aircraft gas turbine Automotive Engineers. Warrendale, PA, Society of Automotive combustors. Validation studies were conducted using a finite Engineers, Inc., 1981, p. 27-30. difference procedure (TEACH) to solve the relevant steady, two- The Engine Usage Monitoring System (EUMS) which determines dimensional, elliptic transport equations for turbulent flow. The the rate and extent to which major and critical components of familiar two equation (k-epsilon) turbulence model was used. The military engines are being consumed. Rapid development and limited combustion model was based on the dissipation rate of oxidant, fuel, funding constraints led to the production of the Mk I EUMS, which and product containing eddies. It was concluded that for confined, incorporates a Phillips-type magnetic tape cassette as the recording nonreacting flows with reasonably well defined boundary conditions, medium and serial digital data formatting and has shown good the turbulence model predicts mean flow quantities to an accuracy performance point recording accuracy and reliability. The Mk II of about 85 percent in regions of parabolic flow. The size of the development of the EUMS incorporates a microprocessor, a solid recirculation zone is underpredicted by about 15-20 percent, and its state memory, and associated large scale electronics miniaturization strength is underpredicted by 20-25 percent. (Author) and integration. With the addition of a visual display unit, onboard computing/display facility requirements are also satisfied. A civil A82-12318 Extending the limits of reliability theory. H. aviation application of the EUMS is projected on the strength of its Goldberg. New York, Wiley-lnterscience, 1981. 275 p. 15 refs. basic simplicity and low cost. O.C. $32.50. Aspects of probability and statistics are examined, taking into account the objective view of probability, the binomial distribution, A82-12495 Powder metallurgy superalloys - Aerospace the use of probability for prediction, the meaning of the reliability materials for the 1980's; Proceedings of the Conference, Zurich, (survivor) function, questions of discrete and continuous distribu- Switzerland, November 18-20, 1980. Volume 1. Shrewsbury, Salop, tion, time-to-failure distributions, and distributions found in the England, MPR Publishing Services, Ltd., 1980. 237 p.

20 A82-12630

The conference focused on the latest advances in the powder A82-12563 Fuel conservation - DC-9 series 20/30/40. metallurgy of superalloys, including developments in powder produc- Society of Flight Test Engineers, Journal, vol. 3, Sept. 1981, p. 2-17. tion, consolidation, and shape-making techniques, and applications. Operational performance penalties and approximate fuel costs Papers are presented on the novel aspects for high-quality metal associated with the aerodynamics, flight operations, fuel gage system powder production equipment, oxide dispersion strengthened materi- and performance analysis aspects of the DC-9 Series 20, 30 and 40 als by mechanical alloying, potential for PM superalloys in aero aircraft are presented. Degradations in aerodynamic cleanness, caused engine application, HIP systems for superalloys, and electron-beam by the gradual deterioration of various seals, rigging adjustments and welding of PM nickel-base superalloys. V.L. skin surface smoothness, are shown to lead to drag increases of less than 0.5%, which, however, represents a significant cost in view of A82-12496 Superclean superalloy powders by the rotating the amount of fuel consumed. Flying off-optimum altitude or Mach electrode process. P. Loewenstein (Nuclear Metals, Inc., Concord, number may result in excess fuel expenditures greater than those due MA). In: Powder metallurgy superalloys - Aerospace materials for the to degraded aerodynamic cleanness. Other operational factors with 1980's; Proceedings of the Conference, Zurich, Switzerland, Novem- substantial influence on fuel use include fuel or aircraft weight, ber 18-20, 1980. Volume 1. Shrewsbury, Salop, center of gravity, flight time, the use of automatic flight control England, MPR Publishing Services, Ltd., 1980, p. 7, 7-1 to 7-28. 18 systems, APU operation, engine starting times, takeoff procedures, refs. climb speed, en route profile, descent profile, and approach A REP (rotating electrode process) powder system with inert gas maneuvers. The DC-9 fuel gage system has been designed to be as handling has been developed for the manufacture of 'superclean' accurate as possible in all phases, in order to minimize the necessity superalloy powders for fatigue-critical turbine applications. The of carrying excess fuel for a given flight. Finally, investigations of system employs a noncontaminating plasma arc source and input aircraft performance may be used to identify areas requiring electrodes in the form of precision ground bars that are free from correction through the comparison of the indicated performance nonmetallic inclusions. The production capability of the superalloy level against a reference, the assessment of engine and airframe powder facility is approximately 500,000 kg per year. V.L. contributions, and the investigation of the most likely areas for correction - the external control surfaces and internal systems. S.C.S.

A82-12497 Superalloy turbine components • Which is the A82-12564 Procedures and analysis techniques for deter- superior manufacturing process, as-HIP, HIP plus Isoforge, or mining static air minimum control speeds. E. N. Bradfield (USAF, 'gatorizing' of extrusion consolidated billet J. Coyne, W. H. Couts, Flight Test Center, Edwards AFB, CA). Society of Flight Test C. Chen, and R. P. Roehm (Wyman-Gordon Co., North Grafton and Engineers, Journal, vol. 3, Sept. 1981, p. 18-48. 6 refs. Worcester, MA). In: Powder metallurgy superalloys - Aerospace A method is presented which can be used to establish the materials for the 1980's; Proceedings of the Conference, Zurich, minimum air speed required for the static lateral and directional Switzerland, November 18-20, 1980. Volume 1. control of a multiengined aircraft following the failure of one or Shrewsbury, Salop, England, MPR Publishing Services, Ltd., 1980, p. more engines. Equations for the thrust moment and rudder pedal 11, 11-1 to 11-31. force coefficient in an asymmetrical force condition are derived from Identical parts of superalloys IN-100, Rene 95, MERL-76, minimum directional control speed theory, and applied to the AF-115, and Astroloy, which are being considered for turbine engine analysis of data obtained in climbs of the B-57 aircraft through a applications, have been produced by three different powder metallur- significant altitude band at minimum directional control speed with gy techniques: as-HIP, HIP plus Isoforge, and gatorizing of extrusion- wings level and banked at various angles, and with a rudder power consolidated billet. The mechanical properties of parts produced by assist system both operational and inoperative. An analysis procedure the different processes are found to be equivalent. Thus, the choice is also presented for aircraft for which minimum control is defined of a process should be based on factors other than the currently by the lack of lateral, rather than directional control, such as STOL expected mechanical properties; namely, materials utilization, and powered-lift aircraft. These methods allow minimum control inspectability. and economics. V.L. speed testing to be accomplished safely, without the necessity of flying at extreme low altitudes with an engine shut down, and permit A82-12499 Superalloy powder engine components; con- extrapolation to off-standard-day conditions and various gross trols employed to assure high quality hardware. J. E. Coyne, W. H. weights. S.C.S. Everett, and S. C. Jain (Wyman-Gordon Co., North Grafton and Worcester, MA). In: Powder metallurgy superalloys - Aerospace A82-12626 National Aerospace Meeting, Trevose, PA, materials for the 1980's; Proceedings of the Conference, Zurich, April 8-10, 1981, Proceedings. Meeting sponsored by the Institute of Switzerland, November 18-20, 1980. Volume 1. Navigation. Washington, DC, Institute of Navigation, 1981. 190 p. Shrewsbury, Salop, England, MPR Publishing Services, Ltd., 1980, p. 24, 24-1 to 24-27. Papers are presented on such topics as all-digital GPS receiver A program involving the production of several hundred turbine mechanization, worldwide coverage of the Phase II Navstar satellite engine components from Rene 95 alloy is reviewed. Consideration is constellation, real-time missile tracking with GPS, navigation task given to powder transportation and handling, development of stock partitioning in distributed-processing avionics systems, and memory acceptance tests and quality assurance program, precautions taken to requirements for future aerospace navigation systems. Consideration avoid powder contamination in the process of handling prior to is also given to the simulation study of a hybrid strapdown attitude HIP'ing, and final testing. Examples of crack initiating defects and and heading reference system, a comparative study of strapdown their effect on mechanical properties are included. V.L. algorithms, ring laser gyro navigator flight test results, and size effects in strapdown navigators. P.T.H. A82-12560 s Lineup of the IM-series aircraft-derivative gas turbines. Ishikawajima-Harima Engineering Review, vol. 21, July A82-12630 ff Satellite geometry considerations for low cost 1981, p. 279-285. 13 refs. In Japanese, with abstract in English. GPS user equipment Y. Rosenthal (Intermetrics, Inc., Cambridge, In order to establish the reliability of the power turbines to be MA). In: National Aerospace Meeting, Trevose, PA, April 8-10, 1981, developed by IHI, extensive investigations are carried out, in Proceedings. Washington, DC, Institute of Navi- particular, on the rotor assemblies. With engine test runs using actual gation, 1981. p. 30-32. FAA-supported research. IM5000 gas turbines, confirmation of the power turbine blade The paper evaluates the geometrical properties of various GPS vibratory stress is carried out through the whole operating range. The satellite configurations as seen by a low-cost user equipment designed measured stress levels reveal that they are far below the critical limits for use by general aviation (GA). The GA user is equipped with one and that no detrimental resonance is to be expected. The same antenna which covers an 85-deg cone perpendicular to the plane of procedure is used with the IM2500 power turbine. In addition to the aircraft. Therefore, when the aircraft banks, satellites which are analyses of the rotating parts, the various stationary parts are tested, above the horizon may be shadowed. Through a nominal turn at a especially the transient behavior of the casing for quick thermal bank angle of 25 deg, the identity of the visible satellites is changing response at the time of starting, stopping and emergency shutdown rapidly. Hence, preselection of the best four satellites is impossible. of the engine. C.R. Criteria for comparing 24 satellites from the GA user point of view is

21 A82-12634

presented, as well as some preliminary results which indicate the is obtained by using the maximum coverage boundary. The range and different results provided by different constellations. Results show bearing coordinates of minimum and maximum SNR boundaries for that as far as GA is concerned, the coverage provided by various 24 -20 dB and -30 dB are provided in tabular form for each Omega satellite constellations is not of equal value. P.T.H. station. P.T.H.

A82-12634 # A solution to the static geometry problem for A82-12639 # FAA acceptance tests on the NAVSTAR GPS JTIDS relative navigation. R. Weiss (Intermetrics, Inc., Cambridge, Z-Set receiver. R. J. Esposito (FAA, Technical Center, Atlantic City, MA) and P. Asher (USAF, Joint Program Office, Bedford, MA). In: NJ). In: National Aerospace Meeting, Trevose, PA, April 8-10, 1981, National Aerospace Meeting, Trevose, PA, April 8-10, 1981, Proceed- Proceedings. Washington, DC, Institute of Navi- ings. Washington, DC, Institute of Navigation, gation, 1981, p. 104-107. 1981, p. 62-64. This paper describes FAA acceptance tests on the NAVSTAR The current JTIDS (Joint Technical Information Distribution GPS Z-Set receiver which were conducted in a USAF System System) relative navigation algorithm restricts the use of relative Command C-141 aircraft over the instrumented range located at the position data in order to maintain stability. In a static geometry Yuma Proving Ground. The Yuma laser tracking system computed a situation, the position quality will be degraded. This paper proposes reference trajectory against which the GPS receiver solution was a solution to the static geometry problem which involves a second compared. Data from five flights, totalling over six hours, are source that maintains a high position quality by constraining its presented with the objective of assessing Z-Set capabilities to meet covariance matrix. There are several ways to implement this civil aviation requirements for non-precision approaches. (Author) situation, each of which must be evaluated in a simulation environment for scenarios involving transitions from static geometry A82-12640 # A navigation systems planning model. H. L. to normal mode. P.T.H. Solomon and A. R. Stephenson (Systems Control, Inc., Palo Alto, CA). In: National Aerospace Meeting, Trevose, PA, April 8-10, 1981, A82-12636 ," Hard limited approaches to correlation veloc- Proceedings. Washington, DC, Institute of Navi- ity sensing, T. J. Lund, R. E. Chapman, and G. A. Murdock gation, 1981, p. 108-119. (Teledyne, Inc., Teledyne Ryan Electronics, San Diego, CA). In: The advent of Navstar/GPS has directed the attention of National Aerospace Meeting, Trevose, PA, April 8-10, 1981, Proceed- government decision-makers to the possibility of ultimately replacing ings. Washington, DC, Institute of Navigation, or supplementing existing navigation systems with one or more 1981, p. 79-83. 6refs. alternative systems. To assist these decision-makers in evaluating Correlation velocity sensors determine velocity by measuring the these and other navigation policy alternatives, a navigation system time delay required for best correlation between signals gathered by cost/benefit model is being developed. A comprehensive data base is two downward looking radar receiver antennas having known also being developed from which the appropriate information can be separation along the velocity axis being measured. This paper extracted by the model in response to navigation system implementa- discusses a variation of this basic technique in which the received tion/decommissioning scenarios, as defined by the model users. The signals are hard limited such that correlation is only performed on model will predict the user's annualized response to a stipulated the phase of the signal. The hard limiting approach avoids the need scenario in terms of receiver purchases, thereby permitting navigation for AGC and allows the receiver outputs to be applied directly to a planners not only to consider operator costs but also the expected digital processor. Comparisons of correlation functions are presented costs and benefits on either an individual or combined user group for linear correlations on the total signal (phase and amplitude), basis. The model's outputs will also be useful to individual user amplitude only and phase only. It is shown that the correlation groups in assessing their position vis-a-vis navigation system policy properties of hard limited signals are well suited to correlation alternatives. P.T.H. velocity sensing. The results of simulations of the correlation velocity sensing process, which included a realistic terrain scattering model, A82-12641 tf Simulation study of a hybrid strapdown atti- are presented for various flight conditions and terrain types. The tude and heading reference system. D. B. Reid, B. N. McWilliam implementation of a hard limited correlation velocity sensor is (Philip A. Lapp, Ltd., Toronto, Canada), and D. F. Liang (Defence discussed. r (Author) Research Establishment, Ottawa, Canada). In: National Aerospace Meeting, Trevose, PA, April 8-10, 1981, Proceedings. A82-12637 /?' Memory requirements for future navigation Washington, DC, Institute of Navigation, 1981, p. systems. R. Fedorak (U.S. Naval Material Command, Naval Air 139-147. 13 refs. Development Center, Warminster, PA) and B. A. Zempolich (U.S. The aircraft attitude and heading reference system (AHRS) Navy. Naval Air Systems Command, Washington, DC). In: National considered in this paper comprises a low-accuracy strapdown inertial Aerospace Meeting, Trevose, PA, April 8-10, 1981, Proceedings. measurement unit (IMU), a strapdown magnetometer triad, which Washington, DC, Institute of Navigation, 1981, provides reference heading information, and air data sensors from p. 84-89. which barometric altitude and true airspeed measurements are The paper examines current problems concerning memories used derived. A variable-dimension U-D factorized Kalman filter is in aerospace navigation systems, identifies technical management employed to estimate the AHRS error state from the redundant concerns relative to various aspects of current use of specific memory sensor data. Estimated errors are fed back into the system using a technologies, and discusses memory requirements for future aero- combination of continuous and impulsive control methods to bound space navigation systems. Particular attention is given to such aspects the inertial attitude, heading, and velocity errors-and reduce the rate as nonvolatility, electrical reprogrammable memories, commonality of position error growth. A data compression algorithm is employed of memory hardware between platforms, packaging, and memory for smoothing of incoming measurement data to enable high-rate capacity. MNOS EEPROM, MNOS 8K BORAM, MNOS EAROM, and information to be incorporated into the filtering process at minimum bubble memories are considered. P.T.H. computational cost. The system operates in three modes: normal AHRS mode, alignment (erection) mode and magnetics calibration A82-12638 H Omega station 10.2 kHz signal selection made mode, in which the U-D filter is utilized to estimate systematic errors easy. R. R, Gupta and R. S. Warren (Analytic Sciences Corp., in the sensed magnetic field during a ground 'swing' procedure, Reading. MA). In: National Aerospace Meeting. Trevose, PA, April initial results obtained by full-scale simulation indicate that, with a 8-10, 1981, Proceedings. Washington, DC, Insti- low-accuracy strapdown IMU, the system can achieve roll and pitch tute of Navigation, 1981, p. 90-103. 7 refs. accuracies of about 5 arc minutes (RMS) and a heading accuracy of Recently developed Omega station signal coverage prediction approximately .75 degree (RMS). (Author) diagrams for 10.2 kHz at eight representative diurnal and seasonal global times of the year provide the most complete presentation of A82-12642 # The integrated inertial sensor assembly /MSA/ Omega station signal coverage ever available to Omega users. This - A redundant strapdown system for advanced aircraft navigation and paper presents minimum and maximum coverage extremes character- flight control functions. M. S. Dipasquo (U.S. Naval Material ized by the coverage diagrams for the eight representative coverage Command, Naval Air Development Center, Warminster, PA). In: times of the year for two signal selection criteria. A simplified National Aerospace Meeting, Trevose, PA, April 8-10, 1981, Proceed- algorithm which yields a conservative determination of the coverage ings. Washington, DC, Institute of Navigation,

22 A82-12697

1981, p. 153-162. fiberglass. Wing body sandwich fairings, undenting fillet panels, and In order to achieve the benefits of an integrated inertial sensor aft engine fairings were built, tested for aerodynamic loads, and assembly (MSA) for the next generation aircraft, the U.S. Navy has found acceptable in a NASA flight service program. The parts were embarked on an advanced development program to demonstrate the then mounted on Lockheed L-1011's for use in commercial airline USA concept. This paper examines the requirements definition, the service; after 50,000 flying hours wear was equivalent to the use of system concept formulation, and the design definition of the fiberglass. Interior and exterior applications in aircraft, such as for advanced development model (ADM) that will be used for concept rudder and trailing edge flaps, are discussed. D.H.K. validation in a later flight test program. P.T.H. A82-12694 Wings in the sun - The evolution of Solar A82-12643 # Integrated satellite navigation and strapdown Challenger. M. Cowley. Flight International, vol. 119, June 13, 1981, attitude and heading reference systems for civil air carriers. J. J. p. 1865-1868. Hopkins (Navigation Development Services, Inc., Northridge, CA). The design, development and testing of the Solar Challenger In: National Aerospace Meeting, Trevose, PA, April 8-10, 1981, aircraft are described, with attention to its lightweight structural Proceedings. Washington, DC, Institute of Navi- design and photovoltaic cell array-powered electric propulsion gation, 1981, p. 163-170. 17 refs. system. The configuration features a cantilever wing and horizontal The potential of the integrated GPS navigator and the strap- tail, whose upper surfaces support 236 sq ft of solar cells that are down AHRS as a replacement for several existing avionics systems is rated at 13% conversion efficiency. The main wing spar and fuselage investigated. Its application is discussed including the economic boom are constructed by wrapping a carbon fiber tube with impact with regard to acquisition and maintenance. The system 1/4-in.-thick Nomex honeycomb, followed by two layers of Kevlar components and integration approach are described, and the expecta- cloth. Flutter tests of the airframe have been conducted at speeds of tions for favorable performance comparisons with its competition are up to 65 mph by mounting the tail, fin and wing on a van. The presented. It is concluded that the economic and performance aircraft is designed for 100-mile flights at 5000-10,000 ft altitudes advantages are unmistakably outstanding. Consequently, to save and 25-35 mph, but the nearly horizontal mounting of the solar cells costs and to safely handle increased traffic there is a strong restricts flight conditions to those with high sun angles, at midday. likelihood that integrated GPS/AHRS will become the standard When the sun is low in the sky, as in winter, the Solar Challenger position, velocity, and attitude reference system for future civil must fly due north to maximize insolation. O.C. aircraft. P.T.H. A82-12696 § Helicopter icing spray system - Improvements A82-12644 H Ring Laser Gyro Navigator/RLGN/flight test and flight experience. D. Belte (U.S. Army, Edwards AFB, CA). results. K. L. Bachman (U.S. Naval Material Command, Naval Air (Canadian Aeronautics and Space Institute, Flight Test Symposium, Development Center, Warminster, PA). In: National Aerospace Medley, Alberta, Canada, Mar. 31, Apr. J, 1981.) Canadian Aero- Meeting, Trevose, PA, April 8-10, 1981, Proceedings. nautics and Space Journal, vol. 27, 2nd Quarter, 1981, p. 93-106. 6 Washington, DC, Institute of Navigation, 1981, p. refs. 171-178. In 1979 improvements were made to the helicopter icing spray This paper describes a flight test program and the resultant system used in icing qualification tests. The improvements were navigation performance achieved on an Advanced Development aimed at reducing drop diameter and eliminating ice formation on Model (ADM) Ring Laser Gyro Navigator (RLGN) in Navy A-7E and the spray boom. A Sonicore nozzle was selected to replace the P-3C aircraft. As the RLGN represents a significant departure from original atomizers and the number of atomizers on the spray boom conventional gimballed inertial system technology, a brief functional was tripled. The newly modified configuration was evaluated using a system description is given highlighting key hardware and software UH-1H helicopter. Measurements were made of drop size distribution design features. This is followed by a description of the A-7E flight and liquid water content. Spray cloud measurements showed great test program, its objective, flight profiles, method of data acquisi- improvement over earlier characteristics, and the median volumetric tion, and analysis of results. The P-3C flight test program is discussed diameter approached that of natural clouds. The types of ice including a description of the flight test recording instrumentation, formation also reflected the improvement in cloud quality. Since flight profiles, data reduction, and analysis of results. An indication in-flight spray simulation cannot duplicate the 100% relative humidi- of system reliability, maintenance, and calibration actions'versus ty of a natural icing cloud, a computer program was developed to system design goals is given. Effects of high latitude on system define the evaporation effect on liquid water content. An expanded alignment and navigation performance are also highlighted. (Author) airspeed range was used for 1980-1981 tests and results were compiled for the UH-60A, UH-1H ice phobics. Bell Model 412 and Grumman OV-1D. S.C.S. A82-12646 Kevlar composites; Proceedings of the Sympo- sium, El Segundo, CA, December 2, 1980. Symposium sponsored by the Technology Conferences. El Segundo, CA, Technology Confer- A82-12697 ff Fractographic determination of fatigue crack ences, 1980. 96 p. $24. growth rates in aircraft components. W. Wiebe and R. V. Dainty (National Aeronautical Establishment, Structures and Materials Papers presented cover Kevlar-49 properties and Kevlar/epoxy Laboratory, Ottawa, Canada). (Canadian Aeronautics and Space composite materials. Kevlar roles in the aerospace industry were Institute. Annual General Meeting, Montreal, Canada, May 11, 12, noted in the design of the L-1011 Tristar components, in the 1981.) Canadian Aeronautics and Space Journal, vol. 27, 2nd materials processing for commercial aircraft, and applications in Quarter, 1981, p. 107-117. commuter aircraft; additional papers describe Kevlar use in life-saving The application of electron fractography to the failure analysis equipment, for rocket motors, pressure vessels, and fuel tanks. of aircraft components is considered to be rewarding because it Finally, the methods and tools necessary for using Kevlar are frequently permits the precise identification of the causes of presented. D.H.K. component failure. Quantitatively, considerable effort has been devoted to the development of techniques specifically directed to the A82-12647 Seven years experience with Kevlar-49 in the evaluation of fatigue crack growth rate information, both from Lockheed L-1011 Tristar. R. H. Stone (Lockheed-California Co., service fatigue failures, and from components fractured during Burbank, CA). In: Kevlar composites; Proceedings of the Symposi- full-scale aircraft laboratory fatigue tests. Originally, the fracto- um, El Segundo, CA, December 2, 1980. El graphic determination of crack growth rate data in these laboratory Segundo, CA, Technology Conferences, 1980, p. 25-43. tests was relatively straightforward, since discrete numbers of load A history of the use of Kevlar-49 in aircraft structures is cycles were applied at each of the various load levels in the fatigue presented. The aramid fibers provide a 25-30% weight reduction over loading spectrum. However, recent use of computer-controlled fiberglass with 1.5 times the stiffness, in addition to comparable random fatigue loading equipment has produced new problems tensile strength; compressive strength is lower, though acceptable. associated with the identification and correlation of the randomly Aircraft parts were fabricated on fiberglass production equipment spaced fatigue striations on the fracture surface, and the derivation using epoxy resin prepregs and tested for durability, impact of crack growth rate data from them. The fractographic methods resistance, and flammability; all were found to be comparable to developed for the solution of these problems are described. (Author)

23 A82-12698

A82-12698 ff SARSAT applications. W. R. McPherson Warminster, PA). Astronautics and Aeronautics, vol. 19, Nov. 1981, (Defence Research Establishment, Ottawa, Canada). (Canadian Aero- p. 56-61. 22 refs. nautics and Space Institute, Canadian Conference on Astronautics, A description is presented of advances in specific areas of 1st, Ottawa, Canada, Oct. 20-22, 1980.) Canadian Aeronautics and parachute technology, taking into account developments occurring Space Journal, vol. 27, 2nd Quarter, 1981, p. 118-126. since 1975. It is pointed out that stress and parachute design analysis The SARSAT system is designed to utilize satellite technology continue to have the same needs as in 1975. Some analytic work has for the rapid detection and location of marine and air distress related nonlinear elasticity, energy dissipation and textile weave to incidents. The system consists of (1) emergency beacons for small the propagation of step strain pulses due to snatch or impact aircraft and boats operating at 406 MHz; (2) space components loadings. Sophisticated computer programs exist for stress analysis of including on-board receivers and processors; and (3) a ground parachutes and for calculating their opening load. Attention is given receiving station with related communication links. The system is to the improved performance of new textile materials, possibilities expected to detect an emergency beacon within six hours of its for improvements related to supersonic parachutes, aspects of activation with local accuracy to the order of 20 km at present, and parachute packing, and developments concerning ejection seats. G.R. 5 km or better for the 406 MHz test units. The first SAR instrumented spacecraft will be launched in mid-1982. Five countries are presently involved in the project, including the USSR COSPAS/- SARSAT project and the SARSAT Investigator in Norway. S.C.S.

A82-12775 F-5G Tigershark. D. Richardson. Flight Inter- national, vol. 120, Oct. 17, 1981, p. 1144-1150. Design features, production goals, and potential markets for the F-5G fighter are reviewed. The aircraft was developed as a counter to the MiG-23 and third generation MiG-21. A GE F404 turbofan engine was chosen, with space left in the redesigned fuselage to accommodate minor engine improvements. A Mach 2 top speed is noted, and an 8,000 hr service life with a 9 g limiting load is projected; fuel consumption is lower than in the F5-E, with more available thrust. Design changes affected the rear fuselage profile, added a carbon composite tailplane, spar, and vertical fin, thicker wing skins to withstand 9 g combat maneuvers, and a larger canopy for greater visibility, in addition to instrument console flexibility. Armament options are provided, with mounts capable of using non-US ordnance; performance characteristics, including the 16,400 Ib thrust are given, along with estimated selling price and production schedules. Over 90% of the ground support equipment of the F5-E is mentioned as being compatible with the F-5G. M.S.K.

A82-12801 ff The case for a defensive air-to-air fighter. W. Hill, Jr. (Rockwell International Corp., North American Aircraft Div., Los Angeles, CA). Astronautics and Aeronautics, vol. 19, Nov. 1981, p. 28-36. An investigation is conducted regarding the approaches available to compensate for the imbalance of tactical air power which favors the Soviets/Warsaw Pact over the U.S./NATO forces, taking into account the constraints of the U.S. Air Force budget. One approach can be to increase the fighter procurement monies, by reducing other budget items, to buy large quantities of the expensive multimission fighter. However, in connection with budgetary considerations related to the urgency of other requirements, it appears that new aircraft the size and capability of the F-15 and F-16 cannot be obtained in quantities sufficient to gain parity with Soviet air forces. It is, therefore, proposed to employ a single-mission aircraft which, because of its simple design and low cost, can be built in quantity. This proposal is based on the recognition that an effective NATO interceptor does not need all the capabilities of the F-15 and F-16. G.R.

A82-12803 * ff Solution to the hidden-line problem. D. R. Hedgley (NASA, Flight Research Center, Edwards AFB, CA). Astronautics and Aeronautics, vol. 19, Nov. 1981, p. 51. It is pointed out that realistic three-dimensional renderings of solid objects or surfaces by computers have long been needed. The NASA Dryden Flight Research Center will soon publish a report and the computer program on an algorithm that solves for hidden lines. The computer program is written in FORTRAN IV and its size is approximately 35N + 9500 words, where N is the number of elements. A number of pictures are presented which were drawn by a computer using the algorithm. G.R.

A82-12804 ft Parachute technology under pressure. E. A. Reed (U.S. Naval Material Command, Naval Air Development Center,

24 discussed and partly compared with results from a theoretical model. Author (ESA)

N82-10020# Advisory Group for Aerospace Research and Development. Neuilly-Sur-Seine (France). AIRCRAFT EXCRESCENCE DRAG STAR ENTRIES A. D. Young. J. H. Paterson. and J. Uoyd Jones, ed. Jul. 1981 172 p refs (AGARD-AG-264: ISBN-92-835-1392-4) Avail: NTIS HC A08/MF A01 A review was undertaken of the available data on the subject N82-10O02# Deutsche Forschungs- und Versuchsanstalt fuer of the drag of excrescences on aircraft surfaces. Information Luft- und Raumfahrt. Brunswick (West Germany). Abteilung from this review is summarized and presented in a way that is Festigkeit. readily usable for prediction and design purposes. The basic MATHEMATICAL MODEL FOR THE MAINTENANCE characteristics of boundary layers are discussed and, where PROGRAM OF MODERN JET AIRCRAFT possible, the drag of excrescences is related to those characteris- Rudolf Prinz, Hans-Christian Goetting. Karl-Heinz Galda (Deutsche tics. In particular, because the size of many types of surface . Lufthansa A.G.. Hamburg), and Juergen Kreth (Deutsche Lufthansa imperfection is small in comparison with boundary layer A.G.. Hamburg) Oct. 1980 44 p refs In GERMAN: ENGLISH thicknesses, the drag of such imperfections can be correlated in summary Report will also be announced as Translatation terms of the properties of inner regions of the boundary layer. (ESA-TT-724) Several previously published analyses of this type are highlight- (DFVLR-FB-81-14) Avail: NTIS HC A03/MF A01: DFVLR, ed and. where possible, extensions to other data sources or Cologne DM 10.40 other types of excrescence are presented. The practical problems Step-by-step escalation of structural inspection intervals of applying these data in the varying velocity gradients existing based on long-term experience with a fleet of transport aircraft on aircraft surface are treated and one section is devoted to is described by a mathematical model. Fundamental to the model the drag of auxiliary air inlet and exit openings. Gaps in existing are statistical distributions of load and detectable crack length data which offer opportunities for research effort are pointed in a fatigue loaded component. Knowing realistic probabilities of out. J.M.S. failure enables the calculation of appropriate inspection inter- vals. Calculation procedure yields increasing intervals up to a N82-10021*/j/ Kansas Univ. Center for Research. Inc.. Lawrence. maximum value and a decrease when approximating the mean Flight Research Lab. value of detectable crack length. As to usual interval steps, the ICING TUNNEL TEST OF A GLYCOL-EXUDING POROUS results show good agreement with practice. Restrictions and LEADING EDGE ICE PROTECTION SYSTEM ON A GENERAL possible applications of the model are discussed. Author (ESA) AVIATION AIRFOIL Final Report David L. Kohlman. William G. Schweikhard, and Alan E. Albright N82-10016# Messerschmitt-Boelkow-Blohm G.m.b.H.. Munich Sep. 1981 37 p refs (Grant NAG3-71) (West Germany). STANDARD TESTS OF A RESEARCH MODEL ROTOR IN (NASA-CR-165444: KU-FRL-464-1) Avail: NTIS A WIND TUNNEL. INCLUDING MODEL SIMILARITY HC A03/MF A01 CSCL01C [STANDARD ERPROBUNG DES FORSCHUNGS Test results show that the system is very effective in MODELLROTORS IM WINDKANAL. EINSCHLIESSLICH preventing ice accretion (anti-ice mode) or removing ice from MODELLVERGLEICHEN] an airfoil. Minimum glycol flow rates required for antiicing are a function of velocity, liquid water content in the air, ambient R. Strieker. V. Mikulla. and E. Allramseder Bonn Bundesminister- temperature, and droplet size. Large ice caps were removed in ium der Verteidigung 1979 93 p refs In GERMAN: ENGLISH only a few minutes using anti-ice flow rates, with the shed summary Sponsored by Bundesministerium der Verteidigung time being a function of the type of ice, size of the ice cap. (BMVg-FBWT-79-16) Avail: NTIS HC A05/MF A01: Dok- angle of attack, and glycol flow rate. Wake surveys measurements zentbw, Bonn DM 30 show that no significant drag penalty is associated with the A wind tunnel test program was developed, as a basis the installation or operation of the system tested. T.M. actual flight regime of the BO-105 helicopter. Operation of the test stand and calibration of measuring devices is described. The procedure for data reduction (digital programs) is given. N82-10022# Committee on Science and Technology (U. S. Results include the parameters: mean and fluctuating components House). of rotor forces and moments: blade bending moments (flapping, SPIN RECOVERY TRAINING lagging): and control forces. Control and static stability derivatives Washington GPO 1980 15 p Presented by the Subcomm. are also determined. The calculations done for comparison with on Invest, and Oversight of the Comm. on Sci. and Technol.. measurements, using aerodynamic/aeroelastic/flight mechanic 96th Congr., 2nd Sess.. Jul. 1980 digital programs, show in almost all cases very good agreement (GPO-66-020) Avail: Subcommittee on Investigations and with model test results. The correlation with flight test data of Oversight the BO-105 helicopter shows that model similarity according to The FAA policy of not requiring spin recovery training as a the most important scaling laws is fulfilled to a high degree prerequisite for a private pilot license was examined in an effort and that the results can be used for real comparison of various to determine if such a requirement would result in a net savings sizes of hingeless helicopter rotors. Author (ESA) of life. Only FAA remained adamant in defense of the no-spin training policy. All other witnesses, to varying degrees, expressed the need for spin and recovery training as a common sense N82-10017$ Deutsche Forschungs- und Versuchsanstalt fiier safety requirement. It can be concluded without equivocation Luft- und Raumfahrt. Goettingen (West Germany). Inst. fuer that experienced aviators overwhelmingly demand that aspiring Experimented Stroemungsmechanik. pilots be trained to protect themselves and be able to recover EXPERIMENTAL INVESTIGATIONS OF THE SEPARATED from post stall gyrations, incipient spins, and spins. The FLOW AROUND A RECTANGULAR WING subcommittee's recommendations that such training be required Hans Bippes. Michael Turk, and Klaus Jacob Oct. 1980 56 p for licensing is discussed with emphasis on the development of refs In GERMAN: ENGLISH summary a flight training manual and an implementation plan. A.R.H. (DFVLR-FB-81-12) Avail: NTIS HC A04/MF A01: DFVLR. Cologne DM 10 N82-10023$ Naval Postgraduate School. Monterey. Calif. Dept. For the aspect ratios lambda = 3.1 and 2.3. pressure of Operations Research. distributions over the whole span were measured at angles of A PROPOSED FLIGHT SAFETY PROGRAM FOR THE attack up to alpha approximately = 27 deg. For selected cases, KOREAN AIR FORCE M.S. Thesis oil flow patterns were produced and velocity profiles behind the Chong Kwan Lee Mar. 1981 136 p refs wing along with shear stresses at the surface were measured. (AD-A102373) Avail: NTIS HC A07/MF A01 CSCL 05/1 Most of the model and the experiments were carried out at Re Several methodologies relevant to the development of a safety approximately = 2.100.000 and M approximately = 0.17. The program for the Korean Air Force were reviewed. Methodologies model and the experiments are described. The results are considered included: Control charts: System safety analysis: and

25 N82-10024

Critical incident technique. Data collection methods applicable high speed, especially when the platforms with the direction to accident analysis were proposed. Recommendations for the finding equipment are also aircraft. Author (GRA) incorporation of these methods into a safety program for the KA.F. were developed. The safety program described in this thesis possesses the potential for reducing overall operational N82-10028*# Wyle Labs., Inc.. Huntsville, Ala. costs and maximizing aircraft availability. The end result of such EXPERIMENTAL MODAL ANALYSIS OF THE FUSELAGE a program can only serve to increase operational readiness and PANELS OF AN AERO COMMANDER AIRCRAFT Final thereby maximize overall efficiency and military capability of the Report K.A.F. GRA David Geisler Sep. 1981 164 p refs Prepared in cooperation with Structural Dynamics Res. Corp.. Cincinnati, Ohio (Contract NAS1-14693) N82-10024# Research Inst. of National Defence. Stockholm (NASA-CR-165750: Rept-10568) Avail: NTIS (Sweden). Huvudavdelning 2. HC A08/MF A01 CSCL 01C LIGHTNING EFFECTS ON AIRCRAFT AND COMPOSITES. The reduction of interior noise in light aircraft was investigated LITERATURE STUDY ON LIGHTNING STRIKES AND with emphasis the thin fuselage sidewall. The approach used is PROTECTION [VERKAN AV BLIXT I FLYGPLAN OCH theoretical and involves modeling of the sidewall panels and KOMPOSITER. UTTERATURSTUDIE OEVER SKADOR OCH stiffeners. Experimental data obtained from tests investigating SKYOD] the effects of mass and stiffness treatments to the sidewalls Anita Aim Nov. 1980 102 p refs In SWEDISH are presented. The dynamic characteristics of treated panels are (FOA-C-20388-F9) Avail: NTIS HC A06/MF A01 contrasted with the untreated sidewall panels using experimental The frequency and different types of lightning strike on modal analysis techniques. The results include the natural different parts of aircraft and several ways of protection against frequencies, modal dampling. and mode shapes of selected panels. direct and indirect lightning effects were reviewed. Fiber Frequency response functions, data relating to the global fuselage composites, lightning damage and testing of lightning protection response, and acoustic response are also presented. J.M.S. for modern aircraft material are studied by means of simulation techniques. Unshielded composite materials are damaged by N82-10029*# National Aeronautics and Space Administration. lightning. With a correctly shaped lightning shield damage can Ames Research Center. Moffett Field. Calif. be prevented. Author (ESA) V/STOL AIRCRAFT AND FLUID DYNAMICS Leonard Roberts (Stanford Univ., Calif.) and Seth B. Anderson N82-10025| Societe Nationale Industrielle Aerospatiale. Paris Oct. 1981 8 p refs (France). (NASA-TM-81328: A-8730) Avail: NTIS HC A02/MF A01 COST REDUCTION IN AIR TRANSPORTATION CSCL QIC P. Lebouc 1980 21 p Presented at French Aerospace Week. The impact of military applications on rotorcraft and V/STOL Indonesia. 8-12 Dec. 1980 aircraft design is summarized with respect to fixed-wing aircraft. (SNIAS-811-150-101) Avail: NTIS HC A02/MF A01 The influence of the mission needs on the configurational design Historical trends in costs are reviewed. By adopting fuel of V/STOL aircraft, the implications regarding some problems in conservation policies, such as renewal of the jet fleet, adaptation fluid dynamics relating to propulsive flows, and their interaction of flight operation, and modification of air traffic control with the aircraft and the ground plane, are also considered. procedures, the airlines can limit the effect of expected fuel Additional research in fluid dynamics that can contribute to an price increases. In parallel, productivity gains should keep at a improvement in performance of V/STOL aircraft is suggested. constant level all the other costs of airline operations. Under B.W. the above conditions, growth of the industry seems to be certain even if fuel prices increase at a rate of 2 to 4% per year above N82-10030*# National Aeronautics and Space Administration. inflation during the next 20 years. Author (ESA) Ames Research Center, Moffett Field. Calif. AN INVESTIGATION OF A STOPPABLE HELICOPTER N82-10026# Deutsche Forschungs- und Versuchsanstalt fuer ROTOR WITH CIRCULATION CONTROL Luft- und Raumfahrt. Bonn (West Germany). Inst. fuer John D. Ballard, John L. McCloud, III, and T. J. Forsyth Aug. Flugmedizin. 1980 372 p refs DEVELOPMENT AND CONSTRUCTION OF PILOT EJECTOR (NASA-TM-81218: A-8278) Avail: NTIS HC A16/MF A01 SEATS IN GERMANY FROM 1938-1945 CSCL 01C Siegfried Ruff Feb. 1981 110 p refs In GERMAN: ENGLISH A stoppable helicopter rotor with circulation control was summary investigated in the Ames 40 by 80 foot wind tunnel. The model (DFVLR-FB-81-04) Avail: NTIS HC A06/MF A01; DFVLR. was tested as a rotating wing, a fixed wing, and during transition Cologne DM 26 start/stop sequences. The capability of the model's control system Pioneering research, leading to the development of an ejector to maintain pitch and roll moment balance during the start/stop seat for the Junkers Ju 88, is reviewed. Fundamentals in sequence, the ability of the blades to withstand the start/stop establishing human acceleration tolerances are discussed. The loads, the adequacy of the control system to maintain balance experimental simulation of shock induced acceleration is described. in the helicopter mode, and the control system capabilities in and human resistance is quantified. Exploitation and follow-up the fixed-wind mode were assessed. Time-history data of several of accident related data are summarized, including investigations start/stop sequences of the X-wing rotor, and the steady-state of the accelerations experienced with an aircraft out of control, data relating to the model as both a rotor and as a fixed-wing e.g., shot down. The action of airspeed pressure on a person is aircraft are presented. In addition, stability data are presented considered, and experience gained with research aircraft is which were acquired during open-loop and closed-loop tests of recounted. Measuring methods for technical and physiological the hub moment feedback control system. J.M.S. parameters are indicated. The beginning of ejector seat develop- ment in England. Sweden, and the U.S. (1944-45) is also briefly N82-10031*# National Aeronautics and Space Administration. reviewed in comparison. Author (ESA) Washington, D. C. QUIET SHORT-HAUL RESEARCH AIRCRAFT FAMILIARIZA- TION DOCUMENT, REVISION 1 N82-10027# Applied Physics Lab.. Johns Hopkins Univ.. Laurel. Joseph C. Eppel Sep. 1981 81 p refs Md. (NASA-TM-81298: A-8601) Avail: NTIS HC A05/MF A01 THE STATISTICAL THEORY OF RADIO DIRECTION CSCL 01C FINDING The design features and general characteristics of the Quiet R. L Holland Jun. 1981 47 p refs Short Haul Research Aircraft are described. Aerodynamic (Contract N00024-81-C-5301) characteristics and performance are discussed based on predictions (AD-A104156: JHU/APL/TG-1330) Avail: NTIS and early flight test data. Principle airplane systems, including HC A03/MF A01 CSCL 17/3 the airborne data acquisition system, are also described. The The statistical theory of radio direction finding as it applied aircraft was designd and built to fulfill the need for a national to three-dimensional geometries is presented in this report. This research facility to explore the use of upper surface blowing, theory is an extension of the two-dimensional theory presented propulsive lift technology in providing short takeoff and landing by R. G. Stansfield in 1947. The theory has application in situations capability, and perform advanced experiments in various technical where airborne targets are maneuvering in three dimensions at disciplines such as aerodynamics, propulsion, stability and control.

26 N82-10039

handling qualities, avionics and flight control systems, trailing dynamic, and vibration testing of the structure are presented. A vortex phenomena, acoustics, structure and loads, operating series production method is then outlined, including inspection systems, human factors, and airworthiness/certification criteria. and certification procedures. Author (ESA) An unusually austere approach using experimental shop practices resulted in a low cost and high research capability. Author N82-10036# European Space Agency. Paris (France). THEORETICAL INVESTIGATION OF THE INFLUENCE OF N82-10032*# Old Dominion Univ.. Norfolk. Va. Dept. of SPOILER DYNAMICS ON THE HANDLING QUALITIES OF Mechanical Engineering and Mechanics. AN AIRCRAFT WITH DIRECT LIFT CONTROL COMPARATIVE STUDY OF FLARE CONTROL LAWS Final Dieter Schafranek Jul. 1981 66 p refs Transl. into ENGLISH Report, 16 Dec. 1979 - 16 Oct. 1981 of "Theoretische Untersuchung ueber den Einfluss der Spoilerd- A. A. Nadkarni Oct. 1981 52 p refs ynamik auf die Fliegbarkeit eines Flugzeugs mit direkter auftriebsst- (Grant NsG-1480) euerung" Rept. DFVLR-FB-80-07 DFVLR. Brunswick. 1980 (NASA-CR-164903) Avail: NTIS HC A04/MF A01 CSCL Original report in GERMAN previously announced as N81-13975 QIC The development of a digital, three dimensional, automatic (ESA-TT-681: DFVLR-FB-80-07) Avail: NTIS HC A04/MF A01: control law designed to achieve an optimal transition of a B-737 DFVLR, Cologne DM 14.70 aircraft between glide slope conditions and the desired final Theoretical parameters describing the pilot's workload during touchdown condition is presented. The digital control law is a aircraft control pitch tracking and flight path tracking tasks on a time invariant, state estimate feedback law. and the design is transport aircraft equipped with spoiler direct lift control (DLC) capable of using the microwave landing system. Major emphasis were studied. The determined parameters are the necessary phase is placed on the reduction of aircraft noise in communities compensation and gain adapation which the pilot must perform, surroundings airports, the reduction of fuel consumption, the and also the closed loop resonance. The influence of the DLC-gain reduction of the effects of adverse weather conditions on aircraft factor, spoiler actuator rate, and spoiler deflection washout time operations, and the efficient use of airspace in congested terminal constant on pilot workload is presented. Simulated time histories areas. Attention is also given to the development of the capability of pitch rate and normal acceleration response due to step type to perform automatic flares from steep glide slopes to precise control inputs show the corresponding reactions of the various touchdown locations. B.W. DLC-configurations which are essential for pitch control and flight path control. Direct lift control using spoilers is shown to be N82-10033# Aberdeen Univ. (Scotland). Dept. of Engineer- sensible for the aircraft in the test only if the pitching moment ing. of the spoiler is completely compensated, the time constant for the spoiler deflection washout is not too small (greater than APPLICATION OF NUMERICAL METHODS TO THE 5 seconds) and if the spoiler moves with more delay than the CALCULATION OF ELECTROSTATIC FIELDS IN AIRCRAFT elevator. Author (ESA) FUEL TANKS Final Scientific Report. 1 Jul. 1980 - 30 Jun. 1981 J. R. Smith. P. Lees, and D. McAllister Aug. 1981 65 p refs N82-10037*# Detroit Diesel Allison, Indianapolis. Ind. (Grant AF-AFOSR-0223-80: AF Proj. 2301: AF Proj. 3048) PROPULSION STUDY FOR SMALL TRANSPORT AIRCRAFT (AD-A103270; EOARD-TR-81-9) Avail: NTIS TECHNOLOGY (STAT) Contractor Final Report HC A04/MF A01 CSCL 01/3 J. C. Gill. R. V. Earle, D. V. Staton. P. C. Stolp. D. S. Huelster. The solution of electrostatic field problems occurring during and B. A. Zolezzi 16 Dec. 1980 186 p refs the refueling of aircraft fuel tanks containing explosion suppressant (Contract NAS3-21995) foams is discussed. A computational model of a fuel tank is set (NASA-CR-165499: DDA-EDR-10470) Avail: NTIS up, and the finite element method is used to calculate the HC A09/MF A01 CSCL 21E electrostatic potential distribution within the tank. Author (GRA) Propulsion requirements were determined for 0.5 and 0.7 Mach aircraft. Sensitivity studies were conducted on both N82-10034# Boeing Military Airplane Development, Seattle, these aircraft to determine parametrically the influence of Wash. propulsion characteristics on aircraft size and direct operating LOW MAINTENANCE HYDRAULIC ACCUMULATOR Final cost (DOC). Candidate technology elements and design features Report. Aug. 1976 • Dec. 1980 were identified and parametric studies conducted to select the E. C. Wagner and W. E. Willard Jun. 1981 65 p STAT advanced engine cycle. Trade off studies were conducted (Contract F33615-76-C-2088; AF Proj. 3145) to determine those advanced technologies and design features (AD-A103947: AFWAL-TR-81-2031) Avail: NTIS that would offer a reduction in DOC for operation of the STAT HC A04/MF A01 CSCL 13/7 engines. These features were incorporated in the two STAT This report presents the results of a program to develop a engines. A benefit assessment was conducted comparing the low maintenance accumulator, compatible with current MS STAT engines to current technology engines of the same power envelopes and competitive in cost with conventional accumulators. and to 1985 derivatives of the current technology engines. The purpose of the program was to select and develop a metal Research and development programs were recommended as part bellows configuration/concept to replace the conventional moving of an overall technology development plan to ensure that full piston and seal of conventional accumulators. The selected bellows commercial development of the STAT engines could be initiated are of welded construction and welded in place to allow bellows in 1988. T.M. movement identical to piston movement. The accumulator housing is of welded construction to eliminate all possible leak points. N82-10038*# Detroit Diesel Allison, Indianapolis. Ind. The program goal was to develop an accumulator to provide a PROPULSION STUDY FOR SMALL TRANSPORT AIRCRAFT ten year unservcced life. Test results, indicate an accumulator TECHNOLOGY (STAT). APPENDIX B Final Report design is possible to achieve a service life of 6 to 10 years [1980] 11 p refs based on installation on an F-16 aircraft. Author (GRA) (Contract NAS3-21995) (NASA-CR-165499-App-B: DDA-EDR-10470-App-B) Avail: NTIS HC A02/MF A01 CSCL 21E N82-10036| Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- Data are tabulated for two conceptual engines designed for brunn (West Germany). Unternehmensbereich Flugzeuge. small transport aircraft. These are the 1790 W (2400 shp) class A CFRP TAILERON FOR THE TORNADO: CONSTRUCTION engine and the 3579 kW (4800 shp) class engine for the 0.5 M AND PRODUCTION [CFK TAILERON FUER DEN TOR- sub N and 0.7 M sub N airplanes, respectively. All data points NADO: KONSTRUKTION UNO FERTI6UNG] L. Lernmer, W. Hartmann. and R. Guenther 1980 67 p In required to perform the STAT missions are provided including GERMAN Presented at Gastvortrag im KL 624. Mannheim. take-off, climb, cruise, loiter, and fuel allowances. The weight, West Germany. 10-14 Nov. 1980 dimensions, price, and maintenance costs are given as well as the installation criteria and equations used for adjusting horse- (MBB-FE-212/KFK/PUB/2) Avail: NTIS HC A04/MF A01 power for gearbox loss, and converting horsepower to thrust. A CFRP lightweight structure, i.e.. CFRP taileron, for the Scaling equations are included. A.R.H. Tornado aircraft was developed. The CFRP taileron is interchange- able with the currently used metal horizontal stabilizer as far as geometry, function and durability are concerned while a 30% N82-10039*/? United Technologies Research Center. East weight reduction is achieved with CFRP construction. The Hartford. Conn. assembly of the CFRP taileron is detailed and results from static. DEVELOPMENT OF LOW MODULUS MATERIAL FOR USE

27 N82-10040

IN CERAMIC GAS PATH SEAL APPLICATIONS Final N82-10043*# Lear Siegler. Inc., Santa Monica. Calif. Astronics Report Div. H. E. Eaton and R. C. Novak Oct. 1981 83 p refs DEVELOPMENT AND EVALUATION OF AUTOMATIC (Contract NAS3-22134) LANDING CONTROL LAWS FOR LIGHT WING LOADING (NASA-CR-165469; R81-915188-13) Avail: NTIS STOL AIRCRAFT HC A05/MF A01 CSCL 21E B. Feinreich, 0. Degani. and G. Gevaert Jul. 1981 371 p Three candidate materials were examined: Brunsbond (F refs Pad: plasma sprayed porous NiCrAlY: and plasma sprayed low (Contract NAS2-9410) modulus microcracked zirconia. Evaluation consisted of mechani- (NASA-CR-166160) Avail: NTIS HC A16/MF A01 CSCL cal, thermophysical. and oxidation resistance testing along with 01C optical microscopy and a feasibility demonstration of attaching Automatic flare and decrab control laws were developed for the material to a suitable substrate. The goals of the program NASA's experimental Twin Otter. This light wing loading STOL were the following: feasibility of fastening or depositing the low aircraft was equipped with direct lift control (OLC) wing spoilers modulus system onto a broad range of substrate alloys: feasibility to enhance flight path control. Automatic landing control laws of depositing or forming the low modulus system to a thickness that made use of the spoilers were developed, evaluated in a of 0.19 cm to 0.38 cm: potential to attain a modulus of elasticity simulation and the results compared with these obtained for in the range of 3.4 to 6.9 GPa (0.5 to 1.0 MSI), and an ultimate configurations that did not use DLC. The spoilers produced a strength of 17.2 MPa (2.5 ksi): suitable thermal conductivity: significant improvement in performance. A simulation that could and static oxidation life of at least 1000 hours at 1311 K. The be operated faster than real time in order to provide statistical results of the program indicate that all three systems offer landing data for a large number of landings over a wide spectrum attractive properties as a strain isolator material. T.M. of disturbances in a short time was constructed and used in the evaluation and refinement of control law configurations. A longitudinal control law that had been previously developed and N82-10040*# General Electric Co., St. Petersburg, Fla. evaluated in flight was also simulated and its performance THERMAL-BARRIER-COATED TURBINE BLADE STUDY compared with that of the control laws developed. Runway Final Report alignment control laws were also defined, evaluated, and refined P. A. Siemers and W, B. Hillig Aug. 1981 134 p refs to result in a final recommended configuration. Good hiding (Contract NAS3-21727) performance, compatible with Category 3 operation into STOL (NASA-CR-165351: SRD-81-083) Avail: NTIS runways, was obtained. Author HC A07/MF A01 CSCL 21E The effects of coating TBC on a CF6-50 stage 2 high-pressure N82-10044$ Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- turbine blade were analyzed with respect to changes in the brunn (West Germany). mean bulk temperature, cooling air requirements, and high-cycle ACTIVE CONTROL ELEMENTS ON THE TRANSONIC WING fatigue. Localized spallation was found to have a possible OF THE AIRBUS A 300 (ACTTA A). AIRBUS A-300 WITH deleterious effect on low-cycle fatigue life. New blade design REDUCED LONGITUDINAL STABILITY (ACTTA-C) [AKTIVE concepts were developed to take optimum advantage of TBCs STEUERELEMENTE AM TRANSSONISCHEN FLUEGEL DES Process and material development work and rig evaluations were AIRBUS A300 (ACTTA A). AIRBUS A300 MIT REDUZIER undertaken which identified the most promising combination as TER LAENGSSTABILITAET (ACTTA-C)] Zr02 containing 8 w/o Y203 applied by air plasma spray onto H. G. Klug 1980 34 p In GERMAN Presented at 2nd a Ni22Cr-10AI-1Y bond layer. The bond layer was applied by a Bundesministerium fuer Forschung und Technologic Statusseminar low-pressure, high-velocity plasma spray process onto the base Luftfahrtforsch. und Luftfahrtechnol., Garmisch-Partenkirchen. alloy. During the initial startup cycles the blades experienced West Germany. 8-9 Oct. 1980 localized leading edge spallation caused by foreign objects. T.M. Avail: NTIS HC A03/MF A01 Two projects concerned with the development and design optimization of the Airbus A-300 are reviewed. Studies related N82-10O41*# National Aeronautics and Space Administration. to active control are discussed. Investigations specific to gust Langley Research Center, Hampton, Va. loading and maneuver induced loading of the A-300 structure DETERMINATION OF AIRPLANE MODEL STRUCTURE are emphasized. Results influence design criteria, e.g.. open or FROM FLIGHT DATA BY USING MODIFIED STEPWISE closed loop control, sensor selection, etc. Reduced longitudinal REGRESSION stability of the A-300 is then considered as a tradeoff in favor Vladislav Klein (Joint Inst. for Advancement of Flight Sciences. of weight reduction through the use of lightweight materials. Hampton, Va.), James G. Batterson, and Patrick C. Murphy Oct. Wind tunnel and other simulation tests are described. 1981 48 p refs Author (ESA) (NASA-TP-1916; L-14613) Avail: NTIS HC A03/MF A01 CSCL 01C The linear and stepwise regressions are briefly introduced, N82-1O045# European Space Agency, Paris (France). then the problem of determining airplane model structure is SYSTEM IDENTIFICATION OF THE LONGITUDINAL addressed. The MSR was constructed to force a linear model MOTION OF THE DFVLR HFB 320 RESEARCH AIRCRAFT for the aerodynamic coefficient first, then add significant nonlinear WITH PARTICULAR CONSIDERATION OF CONTROL terms and delete nonsignificant terms from the model. In addition SURFACE EFFECTIVENESS to the statistical criteria in the stepwise regression, the prediction Ohad Rix Apr. 1981 55 p refs Transl. into ENGLISH of sum of squares (PRESS) criterion and the analysis of residuals "Systemidentifizierung des DFVLR-Forschungsflugzeugs HFB were examined for the selection of an adequate model. The 320 in der Laengsbewegung mit besonderer Beruecksichtigung procedure is used in examples with simulated and real flight der Steuerflaechenwirksamkeit" Rept. DFVLR-Mitt-79-66 data. It is shown that the MSR performs better than the ordinary DFVLR, Brunswick. Jul. 1979 Original report in GERMAN stepwise regression and that the technique can also be applied previously announced as N81-13971 to the large amplitude maneuvers. T.M. (ESA-TT-666; DFVLR-Mitt-79-16) Avail: NTIS HC A04/MF A01: DFVLR. Cologne DM 12 N82-10042*$ National Aeronautics and Space Administration. Analysis of the longitudinal motion of the DFVLR HFB-320 Langley Research Center, Hampton. Va. research aircraft by means of a maximum likelihood method is ESTIMATION OF AIRPLANE STABILITY AND CONTROL described. The control surface effectiveness of separately or DERIVATIVES FROM LARGE AMPLITUDE LONGITUDINAL simultaneously deflected DLC flaps and spoilers was deter- MANEUVERS mined. The flight test technique, and the influence of different James G. Batterson Oct. 1981 43 p refs mathematical models on the results obtained, are illustrated and (NASA-TM-83185: L-14524) Avail: NTIS HC A03/MF A01 discussed. Author (ESA) CSCL 01C The application of a modified stepwise regression algorithm N82-10046# European Space Agency. Paris (France). to both a complete data string and to that same data partitioned A CONTRIBUTION TO THE STABILIZATION OF FLIGHT into bins as a function of angle of attack was demonstrated. VEHICLE PARACHUTE SYSTEMS Results from the large-scale maneuver agree well with results Christos Saliaris and Dieter Muenscher Jun. 1981 30 p refs from 20 maneuvers in which small perturbation from trim at Transl. into ENGLISH of "Beitrag zur Stabilisierung von Flugkoerp- various angles of attack were induced. T.M. er-Fallschirm-Systemen" Rept. Mitt-80-05 DFVLR. Brunswick.

28 N82-10053

Apr. 1980 traditional design and analysis techniques. Stability and control design specification are inadequate in dealing with statistically (ESA-TT-679; DFVLR-Mitt-80-05) Avail: NTIS unstable vehicles, multiple control loops and high dynamic HC A03/MF A01; DFVLR. Cologne DM 8.30 coupling. Better control system design and analysis techniques The dynamic behavior of a parachute-load system moving are needed which address the multi-input closely coupled dynamic in a plane is analyzed. A mathematical model is adopted and a nature of today's and tomorrows aircraft weapon systems. system of nonlinear equations of motion is produced, which are A.R.H. then solved without linearization using a digital computer. Calculations au carried out using a modified g_ide surface N82-10050# Cambridge Univ. (England). Dept. of Engineer- parachute in order to investigate the effects of parachute size, ing. distance between attachment point and canopy, and distance CHARACTERISTIC AND PRINCIPAL GAINS AND PHASES between the attachment point and the center of gravity of the AND THEIR USE AS MULTIVARIABLE CONTROL DESIGN load on the oscillation of the missile. Parameters influencing the TOOLS variation of the pitch angle of the load with time are also studied. Alistair G. J. MacFarlane In AGARD Multi-Variable Analysis Increasing the canopy and moving the attachment point behind and Design Tech. Sep. 1981 34 p refs the center of gravity of the load results in better stabilization. The damping increases, i.e. the pitch angle of the load becomes Avail: NTIS HC A08/MF A01 smaller and the period of oscillation decreases. If the distance The key to the generalization of classical frequency-response between the attachment point on the load and the center of design techniques to the multivariable case lies in the development the canopy base is varied, there is scarcely any detectable change of ways of suitably extending the concepts of gain and phase. to the period of oscillation. However, the damping is influenced It is shown how algebraic function theory can be used to generalise by a change in this distance: it has a maximum when the distance Nyquist diagram and Root-Locus diagram techniques for use is approximately that which is customarily used. Author (ESA) with systems having many inputs and outputs. This is done in such a way that the main structural features of such diagrams N82-10047# Deutsche Forschungs- und Versuchsanstalt fuer can be related to state-space model parameters. The shortcomings Luft- und Raumfahrt. Goettingen (West Germany). Abteilung of characteristic gains and phases (used in a generalised Nyquist Elastomechanik und Aeroelastische Stabilitaet. approach) are then noted. An alternative way of introducing A METHOD FOR DETERMINATION OF THE AEROELASTIC amplitude and phase information, via the polar decomposition BEHAVIOR OF AIRCRAFT WITH ACTIVE CONTROL of an operator, leads to the introduction of principal gains and SYSTEMS Ph.D. Thesis - Tech. Univ. Carolo-Wilhelmina principal phases. Their properties are examined and. in particular, Raymond Freymann Feb. 1981 128 p refs In GERMAN; it is shown how they may be used to characterise robustness. ENGLISH summary Report will also be announced as translation The use of these techniques for design purposes is discussed. (ESA-TT-719) A.R.H. (DFVLR-FB-81-05) Avail: NTIS HC A07/MF A01: DFVLR. Cologne DM 26,30 N82-10051# Honeywell Systems and Research Center. An analytical method for the performance of dynamic Minneapolis, Minn. calculations on servocontrolled aircraft, based on an extended MULTIVARIABLE DESIGN TECHNIQUES BASED ON formulation of the generalized aeroelastic equations is presented. SINGULAR VALUE GENERALIZATIONS OF CLASSICAL The additional parameters introduced in the extended equations CONTROL of motion are determined experimentally in a ground vibration John C. Doyle In AGARD Multi-Variable Analysis and Design test performed on a real aircraft structure as well as with help Tech. Sep. 1981 15 p refs from an experimental-analytical method for determination of the transfer functions of the hydraulic actuators. The elaborated Avail: NTIS HC A08/MF A01 method is shown satisfactory by comparison of measured and Singular value analysis was used to generalize the fundamental calculated data resulting from investigations performed on a model feedback ideas from classical single loop'control theory to wing structure with a rudder driven by a hydraulic actuator. multiloop systems. The classical view of measuring the benefit Author (ESA) of feedback in terms of desensitizing the system to plant variations and disturbances is discussed. Uncertainty is shown to play a critical role in determining the way in which feedback may be N82-10048# Advisory Group for Aerospace Research and used. Certain singular value plots, called sigma-plots. are Development, Neuilly-Sur-Seine (France). introduced as natural and effective generalizations of Bode gain MULTI-VARIABLE ANALYSIS AND DESIGN TECHNIQUES plots and form the basic tools for analysis of multiloop feedback Sep. 1981 168 p refs Presented at a Lecture Series held at systems. These tools provide reliable means for assessing the Ankara. 28-29 Sep. 1981. Bolkesjo. Norway. 1-2 Oct. 1981. stability margins, bandwidth, and desensitizing effects of multiloop and Delft, The Netherlands. 5-6 Oct. 1981 feedback systems. Examples of a two input oscillator and (AGARD-LS-117) Avail: NTIS HC A08/MF A01 control of the rotors of the CH-47 helicopter are given to illustrate The basic theories and concepts involved in the design of the use of the sigma-plots and their interpretations. A.R.H. advanced guidance and control systems employing state-space and multi-variable design methods are explained. The main topics reviewed include: (1) analysis and synthesis techniques: N82-10052# Honeywell. Inc., Minneapolis, Minn. Systems (2) application of observer and estimation principles: (3) comput- and Research Center. er-aided design and analysis methods: (4) system simulation LIMITATIONS ON ACHIEVABLE PERFORMANCE OF techniques: and (5) tests evaluation and validation. MULTIVARIABLE FEEDBACK SYSTEMS John C. Doyle In AGARD Multi-Variable Analysis and Design Tech. Sep. 1981 9p refs N82-1O049# Honeywell. Inc.. Minneapolis. Minn. Systems and Research Center. Avail: NTIS HC A08/MF AO1 THE NEED FOR MULTIVARIABLE DESIGN AND ANALYSIS The design tradeoffs that are the focus of classical single-loop TECHNIQUES theory were generalized to multiloop systems using singular value Rhall E. Pope In AGARD Multi-Variable Analysis and Design analysis techniques. The first tradeoff is algebraic between large Tech. Sep. 1981 10 p loop gain for good sensitivity properties and small loop gain for stability margins. Another is the functional tradeoff improsed by Avail: NTIS HC A08/MF A01 the Bode gain/phase relations. These tradeoffs impose limitations Demand for higher accuracy, improved reliability/survivability, on the achievable performance of any feedback design. The and more automation are placing increased emphasis on the limitations caused by nonminimum phase zeros are also discussed. control function for successful operation of aircraft weapon The problem of directionality in multiloop systems has no analog systems. Modifications to airframe designs directed at increased in single loop feedback systems is presented and analyzed. maneuverability and reduced weight are placing stringent on A.R.H. flight control systems. Fly-by-wire systems, particularly digital systems, provide the flexibility to not only accommodate but N82-10053# Honeywell. Inc.. Minneapolis. Minn. Systems influence airframe design modifications and led to the control and Research Center. configured vehicle (CCV) concept. These advances in air. vehicle LOG-BASED MULTIVARIABLE DESIGN: FREQUENCY design and flight control system implementation are overwhelming DOMAIN INTERPRETATION

29 N82-10054

Gunter Stein In AGARD Multi-Variable Analysis and Design FEEDBACK AND MINIMAX SENSITIVITY Tech. Sep. 1981 9p refs George Zames and Bruce A. Francis (Waterloo Univ.) In AGARD Multi-Variable Analysis and Design Tech. Sep. 1981 8 p refs Avail: NTIS HC A08/MF A01 Sponsored in part by National Science and Engineering Research The use of the Linear-Quadratic-Gaussian (LOG) methodology Council of Canada in designing feedback compensators which meet multivarible (Grant NSF ECS-80-12-565) performance, stability, and stability robustness requirements Avail: NTIS HC A08/MF A01 expressed as singular value conditions in the frequency domain Feedbacks that minimize me sensitivity function of a linear, is demonstrated. A.R.H. single variable feedback system represented by its frequency responses were considered. Sensitivity is measured in a weighted H (infinity) norm. The single variable cases are studied. The N82-10054# Honeywell, Inc., Minneapolis, Minn. Systems results are extended to unstable plants, and explicit formulas and Research Center. for the general situation of a finite number of RHP plant zeros LOG MULTIVARIABLE DESIGN TOOLS or poles are provided. The Q or 'approximate-inverse' parameter- Gunter Stein and Stephen Pratt In AGARD Multi-Variable ization of feedbacks that maintain closed-loop stability is extended Analysis and Design Tech. Sep. 1981 16 p refs to the case of unstable plants. The H (infinity) and Wiener- Hopf approaches are compared. A.R.H. Avail: NTIS HC A08/MF A01 The basic design algorithms needed for frequency domain oriented Linear-Quadratic-Gaussian feedback design are described N82-10059*# Bolt, Beranek, and Newman, Inc.. Cambridge, and experimental interactive computer aided design package Mass. through which these algorithms can be effectively acessed is EVALUATION OF THE ACOUSTIC MEASUREMENT introduced. The algorithms and design package are illustrated CAPABILITY OF THE NASA LANG LEY V/STOL WIND with several flight control design examples for highly maneuverable TUNNEL OPEN TEST SECTION WITH ACOUSTICALLY aircraft. A.R.H. ABSORBENT CEILING AND FLOOR TREATMENTS Final Report N82-10055# Groningen Rijksuniversiteit (Netherlands). Math- Mark A. Theobald May 1978 46 p refs ematics Inst. (Contract NAS1-14611) DESIGN OF HIGH INTEGRITY MULTIVARIABLE CONTROL (NASA-CR-165796: Rept-3820) Avail: NTIS SYSTEMS HC A03/MF A01 CSCL 14B J. C. Williams In AGARD Multi-Variable Analysis and Design The single source location used for helicopter model studies Tech. Sep. 1981 10 p refs was utilized in a study to determine the distances and directions upstream of the model accurate at which measurements of the Avail: NTIS HC A08/MF A01 direct acoustic field could be obtained. The method used was The notions of (almost) controlled and conditionally invariant to measure the decrease of sound pressure levels with distance subspaces of linear systems are explained and their application from a noise source and thereby determine the Hall radius as a to the synthesis of feedback compensators for disturbance rejection function of frequency and direction. Test arrangements .and and to robust controller is outlined. The disturbance rejection procedures are described. Graphs show the normalized sound and the robust controller design problems are viewed as a pressure level versus distance curves for the glass fiber floor procedure for designing a high integrity feedback control treatment and for the foam floor treatment. A.R.H. system. A.R.H. N82-10062# Committee on Science and Technology (U/S. N82-10056# Toronto Univ. (Ontario). Systems Control House). Group. AIRPORT AND AIRWAY IMPROVEMENT ACT OF 1981. A GEOMETRIC APPROACH TO MULTIVARIABLE CONTROL PART 1 SYSTEM SYNTHESIS Washington GPO 1981 56 p Rept to accompany H. R. W. Murray Wonham In AGARD Multi-Variable Analysis and 2643 Presented by the Comm. on Sci. and Technol. at the Design Tech. Sep. 1981 21 p refs 97th Congr, 1st Sess., 19 Mar. 1981 (GPO-76-241-Pt-1) Avail: US Capitol. House Document Avail: NTIS HC A08/MF A01 Room Multivariable control is discussed with emphasis on Multivari- A bill authorizing appropriations to the FAA in the amount able Control: fundamentals, disturbance decoupling and output of $85,000,000 for air traffic control, navigation, aviation weather, stabilization, controllability subspaces, noninteracting control, and aviation medicine, and ATC computer modernization for FY-1981- regulation and tracking in linear systems and structurally stable 1982 is presented. The Committee directs that funds be nonlinear regulation with step inputs A version of the internal reprogrammed to permit completion of the Flight Level 290 and model principle for controlled sequential machines is included. to expedite development of the Doppler weather radar (Nexrad). A.R.H. The request for a trust fund to supports 19.81 million of regulatory support research and development was denied. A.R.H. N82-10O57# McGill Univ.. Montreal (Quebec). Dept. of Electrical Engineering. N82-10063# Advisory Group for Aerospace Research and MULTIVARIABLES DESIGN: THE OPTIMIZATION OF Development. Neuilly-Sur-Seine (France). APPROXIMATE INVERSES AIR-BREATHING ENGINE TEST FACILITIES REGISTER G. Zames In AGARD Multi-Variable Analysis and Design Tech. Joachim H. Krengel. comp. Jul. 1981 122 p Sep. 1981 6 p refs (AGARD-AG-269) Avail: NTIS HC A06/MF A01 A register was compiled, aimed at comprising the test facilities Avail: NTIS HC A08/MF A01 relevant for research and development in NATO countries. Included A mathematical framework for the analysis of sensitivity in are test facilities being in use or under construction at the various multi-input-multi-output linear feedback systems is proposed, research organizations, industrial firms, and universities. Test based on the concepts of a multiplicative seminorm and an facilities and their technical data are given as far as the approximate inverse. Many of the empirical results of classical response to a questionnaire was received or open literature was control theory pertaining to the use of lead-lag networks can be available. Test engineers will be able to find whether a test deduced in this framework as solutions to well-posed mathematical facility suiting their specific demands already exists or may be optimization problems. Moreover, new classes of optimal filters easily adapted to their purposes. T.M. for the reduction of sensitivity are introduced. A definition of optimal sensitivity to plant uncertainty is established. The multiplicative property of semmorms is used to obtain the following N82-10107# European Space Agency. Paris (France). principle: for any specified aposteriori accuracy, there is a FLIGHT TEST RESULTS OF THE MODEL SIMULATION maximum of apriori plant uncertainty that can be tolerated, and CONTROLLER FOR THE HFB 320 FOR IN-FLIGHT SIMULA- a minimum of identification that is required. Author TION OF THE A310 AIRBUS Hans-Heinz Lange Apr. 1981 72 p refs Transl. into ENGLISH N82-10058# McGill Univ.. Montreal (Quebec). Dept. of Electrical of 'Flugerprobung des modellfolgereglers fuer die HFB 320 zur Engineering. Simulation des Airbus A 310 in Fluge" Rept. DFVLR-Mitt-79-13

30 N82-10981

DFVLR. Brunswick. 1979 Original report in GERMAN previously ture, integrated, hierarchical, and non-integrated dedicated. The announced as N81-10078 three designs were evaluated for application to a two engine (ESA-TT-660: DFVLR-Mitt-79-13) Avail: NTIS tactical aircraft. Processor and data bus loading were examined HC A04/MF A01; DFVLR. Cologne DM 15.40 for each architecture. Based on the evaluation, the conceptual The onboard computer program which completes the model design based on the integrated architecture is recommended for simulating control system is presented and its fundamental preliminary design in Task 3, phase I. Author (GRA) operations explained. The effect of nonlinearities is demonstrated by means of the results of ground simulation of the test aircraft, N82-10421$ Shock and Vibration Information Center (Defense). the control system and the simulated aircraft. The flight test Washington. D. C. results show the achieved quality of in-flight simulation of the THE SHOCK AND VIBRATION DIGEST, VOLUME 13. modeled A310 aircraft. Examples of the ground simulation NO. 9 predictions of the overall aircraft and controller system behavior Judith Nagle-Eshleman. ed. Sep. 1981 123 p refs are cited. Author (ESA) (AD-A105062) Avail: SVIC. Code 5804. Naval Research Lab.. Washington. D.C. 20375; S15.00/set CSCL 20/11 N82-10254# KV6. Inc.. Irvine. Calif, Structural dynamic problems inherent to design, analysis, BASELINE DATA ON UTILIZATION OF LOW-GRADE FUELS and operation of rotating machinery were investigated. The IN GAS TURBINE APPLICATIONS. VOLUME 3: EMIS- following Space Shuttle related problems are discussed: analytical SIONS EVALUATION Final Report and experimental loads, and dynamics efforts: development of T. Sonnichsen Jun. 1981 108 p refs Sponsored in part by data systems and environmental testing programs: Space Shuttle Electric Power Research Inst. thermal protection system and the Space Shuttle main engine: (EPRI Proj. 1079-3) structural dynamics, dynamic testing, and vibration control. (DE81-903764: EPRI-AP-1882-Vol-3) Avail: NTIS HC A06/MF A01 A series of field tests was conducted on two residual-oil-fired N82-10452# Deutsche Forschungs- und Versuchsanstalt fuer gas turbine/heat recovery steam generators (HRSG) comprising Luft- und Raumfahrt. Goettingen (West Germany). Inst. fuer a Westinghouse PACE 260-MW combined-cycle unit. Base load Aeroelastic. emission levels were determined. A series of tests was also CALCULATION OF NATURAL MODES OF VIBRATION FOR made at reduced operating loads. Emission measurements ROTOR BLADES BY THE FINITE ELEMENT METHOD included: (1) gaseous constituents measured by continuous Fritz Kiessling and Dieter Ludwig Jan. 1981 66 p refs In monitoring instrumentation (02. C02. NO. NO sub x. and SO2) GERMAN: ENGLISH summary and by wet chemistry methods (S03, aldehydes, and chlorides): (DFVLR-FB-81-07) Avail: NTIS HCA04/MFA01: DFVLR, and (2) paniculate characteristics (mass loding. smoke spot Cologne DM 14.20 number: submicron particle size, and particle morphology). The mass and stiffness matrices for a rotating blade are Corrected NO sub x emissions at base load were 170 ppM and established by the finite element method. The formulation is 200 ppM with and without HRSG afterburners in service, based on the Lagrange function presented for combined flapwise respectively. The NO sub x emissions decreased with water bending, chordwise bending, and torsion of twisted nonuniform injection by 50% and were unchanged with the turbine wash. rotor blades. The element matrices were created by the nonnumeric The NO sub x increased with load. DOE computer program REDUCE by which it is possible to evaluate the formulas by symbolic manipulation. An ordering scheme was N82-10286*# National Aeronautics and Space Administration. introduced to demonstrate which terms were simplified or Pasadena Office, Calif. neglected. As examples, eigenanalyses are performed for a SYNTHETIC APERTURE RADAR TARGET SIMULATOR nonrotating homogeneous beam and for the rotor blade of a Patent Application wind energy converter. Author (ESA) Howard A. Zebker (JPL. California Inst. of Technology. Pasadena). Daniel N. Held (JPL. California Inst. of Technology. Pasadena). N82-10812# Hope Associates. Inc.. Washington. D.C. Richard M. Goldstein (JPL. California Inst. of Technology. A COMPREHENSIVE BIBLIOGRAPHY OF LITERATURE ON Pasadena), and Thomas C. Bickler. inventors (to NASA) (JPL, HELICOPTER NOISE TECHNOLOGY Final Report California Inst. of Technology. Pasadena) Filed 17 Jul. 1981 A. M. Carter, Jr. Jun. 1981 116 p 15 p (Contract DTFA01-80-Y-10597) (Contract NAS7-100) (AD-A103331: FAA-EE-81-4) Avail: NTIS HC A06/MF A01 (NASA-Case-NPO-15024-1: US-Patent-Appl-SN-284287) Avail: CSCL 20/1 NTIS HC A02/MF A01 CSCL 171 This bibliography, covering the period 1975 through calendar A simulator for simulating the radar return, or echo, from a 1980 also provides abstracts on literature that appear to make target seen by a SAR antenna mounted on a platform moving a significant contribution to the field of helicopter noise technology. with respect to the target is described. It includes a first-in The helicopter is recognized as a complex noise generator, with first-out memory which has digital information clocked in at a significant contributions from the rotors, the engine and the rate related to the frequency of a transmitted radar signal and gearbox. Progress continues to be made in the noise areas of: digital information clocked out with a fixed delay defining range (a) Formulations, math models and analytical procedures: between the SAR and the simulated target, and at a rate related (b) Noise prediction methodology: (c) Noise reduction techniques: to the frequency of the return signal. An RF input signal having and (d) Subjective response to helicopter noise. The body of a frequency similar to that utilized by a synthetic aperture array information, data and knowledge has use in many applications, radar is mixed with a local oscillator signal to provide a first including the reduction of helicopter noise in a cost effective baseband signal to provide a first baseband signal having a manner and in minimizing annoyance to the civil populace. GRA frequency considerably lower than that of the RF input signal. T.M. N82-10959# Committee on Science and Technology (U. S. House). N82-10326# Boeing Military Airplane Development. Seattle. NASA AUTHORIZATION. 1982: INDEX Wash. Mechanical/Electrical Systems Technology Dept. Washington GPO 1981 316 p Hearings on H.R. 1257 ADVANCED AIRCRAFT ELECTRICAL SYSTEM CONTROL before the Comm. on Sci. and Technol.. 97th Congr., 1st Sess.. TECHNOLOGY DEMONSTRATOR. PHASE 1: REQUIRE- No. 2. 1981 MENTS ANALYSIS AND CONCEPTUAL DESIGN Interim (GPO-84-713) Avail: Committee on Science and Technology Technical Report. 1 Sep. 1980 - 28 Feb. 1981 A subject and name index is presented to the testimony G. L. Dunn. P. J. Leong. and I. S. Mehdi Jul. 1981 103 p delivered, statements received, and questions raised in relation refs to NASA's budget requests, for program management, construc- (Contract F33615-80-C-2004: AF Proj. 3145) tion of facilities, and research and development. A.R.H. (AD-A103922: D180-25927-2: AFWAL-TR-81-2058) Avail: NTIS HC A06/MF A01 CSCL 09/3 In Task 1, the requirements for the electrical power system N82-10981| Air Force Systems Command. Wright-Patterson and the integrated power system control were defined. In Task AFB. Ohio. Foreign Technology Div. 2. three conceptual designs for the electrical power system were FINITE DIFFERENCE COMPUTATION OF THE STEADY prepared. Each design incorporated a different data bus architec- TRANSONIC POTENTIAL FLOW AROUND AIRPLANES

31 N82-10982

Luo Shijun.'Zheng Yuwen, Qian Hong, and Wang Dieqian In TIONS WITH GIVEN COMPUTER CAPACITY its Recent Selected Papers of NW Polytech. Univ.. pt. 1 Yang Qingxiong In its Recent Selected Papers of NW Polytech. (FTD-ID(RS)T-0259-81-Pt-1) 20 Aug. 1981 p 5-30 refs Transl. Univ.. pt. 1 (FTD-ID(RS)T-0259-81-Pt-1) 20 Aug. 1981 into ENGLISH from Recent Selected Papers of NW Polytech. p 338-358 refs Transl. into ENGLISH from Recent Selected Univ.. pt. 1 (Xian Shaanxi). 1979 Papers of NW Polytech. Univ.. pt. 1 (Xian Shaanxi). 1979

Avail: NTIS HC A17/MF A01 Avail: NTIS HC A17/MF A01 The velocity potential equation was approximated by assuming The history of using the method for structural computation that the perturbation velocity component in the transverse plane in domestic aeronautical engineering was reviewed. The develop- of the body is much smaller than the undistributed flow velocity, ment and application of the matrix method was examined. T.M. while the perturbation velocity component in the longitudinal direction may not be so. It was then solved with mixed schemes N82-10995jjf Air Force Systems Command. Wright-Patterson of finite differences. The boundary condition on wings (tails) AFB, Ohio. Foreign Technology Div. and its wake were approximated similarly. Two numerical examples STRUCTURAL ANALYSIS OF FUSELAGES WITH CUTOUTS are included and the results agree well with known wind tunnel BY FINITE ELEMENT METHOD test results. T.M. G. Shoulian. Sun Can, Tang Xuunchun, and Ye Tiangi In its Recent Selected Papers of NW Polytech. Univ.. pt. 1 (FTD-ID(RS) N82-10982# Air Force Systems Command. Wright-Patterson T-0259-81-Pt-1) 20 Aug. 1981 p 359-378 refs Transl. into AFB. Ohio. Foreign Technology Div. ENGLISH from Recent Selected Papers of NW Polytech. Univ.. SECOND ORDER APPROXIMATION THEORY OF AN pt. 1 (Xian Shaanxi). 1979 ARBITRARY AEROFOIL IN COMPRESSIBLE POTENTIAL FLOW Avail: NTIS HC A17/MF A01 Lin Chaoqiang In its Recent Selected Papers of NW Polytech. The rear part of a transport aircraft's fuselage was studied. Univ.. pt. 1 (FTD-ID(RS)T-0259-81-PM) 20 Aug. 1981 It consists of two sections, the front section being a closed p 31-50 refs Transl. into ENGLISH from Recent Selected cylinder with a floor and the other section containing a large Papers of NW Polytech. Univ., pt. 1 (Xian Shaanxi). 1979 cutout. An idealized structure is considered to have 1950 degrees of freedom. In this analysis, three kinds of finite element were Avail: NTIS HC A17/MF A01 adopted: a flange element with various cross sections: a The region outside an arbitrary airfoil is conformally trans- constant shear flow quadrilateral of arbitrary shape: and a beam formed into the region outside a unit circle. The transformation element of various cross sections taking account of eccentricity functions are expanded into ascending power series and then of the nodes from the axes of moment and inertia. A factorization only those terms up to and including the second order are retained. algorithm was adopted in the solution of the system of linear The resulting formulae are given analytically. The method is nearly algebraic equations. T.M. an exact solution from the engineering point of view, even for an airfoil with thickness as much as 30 percent of the chord N82-10998# Air Force Systems Command. Wright-Patterson and with maximum camber as much as 10 percent of the AFB. Ohio. Foreign Technology Div. chord. T.M. MATRIX ANALYSIS OF WINGS Xu Yuan, Zhu Runziang, Jiang Jinqiag. and Cai Yiuliu In its N82-10983# Air Force Systems Command. Wright-Patterson Recent Selected Papers of NW Polytech. Univ., pt. 2 (FTD-ID(RS) AFB. Ohio. Foreign Technology Div. T-0260-81-Pt-2) 28 Aug. 1981 p 76-111 refs Iransl. into AERODYNAMIC CALCULATIONS AND DESIGN OF ENGLISH from Recent Selected Papers of NW Polytech. Univ., SUBCRITICAL AEROFOILS pt. 2 (Xian Shaanxi). 1979 Lin Chaoqiang In its Recent Selected Papers of NW Polytech. Univ., pt. 1 (FTD-ID(RS)T-0259-81-Pt-1) 20 Aug. 1981 Avail: NTIS HC A18/MF A01 p 51-64 refs Transl. into ENGLISH from Recent Selected The plate-beam wing constructions are simplified either as Papers of NW Polytech. Univ.. pt. V (Xian Shaanxi). 1979 plane stress or plate bending models. The triangular element matrix of a laminated plate is introduced as well as the element Avail: NTIS HC A17/MF A01 stiffness matrix of the beam of axially variable rectangular cross A method of calculating the velocity and pressure distribution section. Two general computer calculation programs are also on an airfoil of given geometrical profile at a given angle of compiled. Calculations are shown for wings consisting of plates attack in subcritical potential flow is described. Inversely, designing and beams, honeycomb core and solid wings. Compared to the appropriate airfoil geometry and the corresponding angle of attack experimental results, the errors in the nodal deflections are for a given pressure distribution is discussed. T.M. generally less than 5%. It is clear that the method adopted has finite accuracy and generality. R.C.T. N82-10984# Air Force Systems Command. Wright-Patterson AFB. Ohio. Foreign Technology Div. N82-11006# Air Force Systems Command. Wright-Patterson AN AERODYNAMIC DESIGN METHOD FOR TRANSONIC AFB, Ohio. Foreign Technology Div. AXIAL FLOW COMPRESSOR STAGE INITIAL EXPERIMENTAL RESEARCH INTO THE RESPONSE Zhu Fangynan. Zhou Xinhai. Liu Songling. and Fan Feida In its OF TURBOJET ENGINE COMPRESSORS TO DISTORTION Recent Selected Papers of NW Polytech. Univ.. pt. 1 (FTD-ID(RS)T- OF INTAKE PRESSURE 0259-81-Pt-1) 20 Aug. 1981 p 65-86 refs Transl. into Chen Fu-qun. Tang Di-yi. Hu Zi-long. Id Wen-Ian. Yu Jin-di. Wu ENGLISH from Recent Selected Papers of NW Polytech. Univ.. Xin-yuan. Zhao Jue-liang. Lin Qi-xun. Wang Zong-yuan. Liu pt. 1 (Xian Shaanxi). 1979 Si-hong et al In its Recent Selected Papers of NW Polytech. Univ., pt. 2

32 N 82-11025

A PRELIMINARY EXPERIMENTAL INVESTIGATION OF THE THREE-DIMENSIONAL FLOW WITH THE S SUB 1-SUR- RESPONSE OF A TURBOJET ENGINE TO INLET PRESSURE FACE TWISTED DISTORTION Xin Xiao-Kang. Jiang Jin-Liang, and Zhu Shi-Can In its Acta Chen Fu-qun, Tang Di-yi. Hu Zi-long, Id Wen-Ian, Yu Jin-di, Wu Mech. Sinica (FTD-ID(RS)T-0704-81) 11 Sep. 1981 p 1-19 Xin-yuan. Zhao Jue-liang. Lin Qi-xun. Wang Zong-yuan. and Liu refs Transl. into ENGLISH from Acta Mech. Sinica (China), Si-hong In its Recent Selected Papers of NW Polytech. Univ., no. 1. 1979 pt. 2 (FTD-ID(RS)T-0260-81-Pt-2) 28 Aug. 1981 p 317-346 Avail: NTIS HCA03/MFA01 CSCL01/2 refs Transl. into ENGLISH from Recent Selected Papers of NW On the basis of the quasi-orthogonal surface method, a Polytech. Univ.. pt. 2 (Xian Shaanxi), 1979 three-dimensional flow field solution of inviscous fluids in turbine machinery is obtained. This method, under the condition allowed Avail. NTIS HC A18/MF A01 by the storage of the computer, can calculate any shapes of S Preliminary experimental results about the effect of inlet sub 1 and S sub 2 surfaces (including twisting S sub 1 surfaces) pressure distortion on the characteristics and instability of the and obtain the shapes of space streamlines and the three- axial compressor of a turbojet engine are presented. The dimensional distribution of parameters such as velocity. The experiments were conducted on the test bed on a turbojet engine calculations for the two conditions of a centrifugal compressor with a 9-stage compressor, whose first stage is transonic. The with a small impeller (phi 110) indicate the relative value of tests were run for each of the following cases: 11) at 99% the twist of the S sub 1 surface is about 3 to 10 percent. The design speed with 180 deg triple-deck 36 mesh screen in front S sub 1 surface shows a double twist like a twist drill from the of the engine inlet, i.e., 3x36 mesh: (2) at 90% design speed inlet to the outlet. M.G. with 180 deg single-deck 35 mesh screen, i.e.. 1x36 mesh: (3) at 90% design speed with clean inlet: and (4) at 87% design N82-11016# Air Force Systems Command, Wright-Patterson speed with a decrease of about 12% of the first stage turbine AFB. Ohio. Foreign Technology Div. nozzle exit area. R.C.T. THE PRINCIPLES AND METHODS FOR SHAPING THE WING ROOT REGIONS OF A WING-BODY COMBINATION N82-11008| Air Force Systems Command, Wright-Patterson AT TRANSONIC AND LOWER SUPERSONIC SPEEDS AFB. Ohio. Foreign Technology Oiv. AN EXPERIMENTAL INVESTIGATION OF THE ROTATING Yang Tso Sheng, Tai Chia Tsun. Chen Ching Sung, and Fan I. STALL. SURGE AND WAKE BEHIND THE ROTOR FOR A Chia In its Acta Mech. Sinica (FTD-ID(RS)T-0704-81) 11 Sep. SINGLE STAGE AXIAL COMPRESSOR 1981 p 20-35 refs Transl. into ENGLISH from Acta Mech. Zhang Weide. Zbang Changsheng. Liu Zhiwei. and Liu Jiafeng Sinica (China), no. 1, 1979 In its Recent Selected Papers of NW Polytech. Univ.. pt. 2 (FTD-ID(RS)T-0260-81-Pt-2) 28 Aug. 1981 p 347-370 refs Avail: NTIS HCA03/MFA01 CSCL01/2 Transl. into ENGLISH from Recent Selected Papers of NW The principles and methods for the combined shaping of Polytech. Univ.. pt. 2 (Xian Shaanxi). 1979 the wing root regions of a wing-body combination, in accordance with the requirements of area rule and shockless pressure field, Avail: NTIS HC A18/MF A01 are discussed. It is shown that the favorable non-midwing Dynamic tests were conducted in order to investigate the arrangement is able to reduce the amount of fuselage shaping rotating stall, surge, and wake behind the rotor of a single stage required for the reduction of the zero lift wave drag of a wing-body axial compressor. The relationship between the rotating stall and combination. The combined shaping so designed may thus be the total turbulence behind the rotor caused by the wake was realized more easily in structural arrangement. M.G. also studied. It was found that the waveform of the wake behind the rotor shows marked changes when rotating stall approach- N82-11024# Air Force Systems Command. Wright-Patterson es. The wake induced degree of total turbulence increases sharply, AFB, Ohio. Foreign Technology Div. and therefore may be used as a way to predict rotating stall. THEORETICAL INVESTIGATIONS AND EXPERIMENTAL The total process of rotating stall and surge as well as the RESEARCHES FOR HIGHER SUBSONIC TWO- differences between the two and their connection were also DIMENSIONAL COMPRESSOR CASCADE compared. R.C.T. Yan Ru-qun and Qian Zhao-yan In its J. of Eng. Thermophys. (Selected Articles) (FTD-ID(RS)T-0570-81) 16 Sep. 1981 N82-11013*# National Aeronautics and Space Administration. p 1-34 refs Transl. into ENGLISH from Gongcheng Rewuli Langley Research Center. Hampton, Va. Xuebao (China), v. 2. no. 1, Feb. 1981 Presented at the 3rd EFFECTS OF VORTEX FLAPS ON THE LOW-SPEED Ann. All-China Thermophys. Eng. Technol. Conf., Gui Lin. China, AERODYNAMIC CHARACTERISTICS OF AN ARROW Apr. 1980 WING Avail: NTIS HC A05/MF A01 CSCL 21/5 Long P. Yip and Daniel G. Murri Nov. 1981 64 p refs Compressible turbulence flow boundary layer theory and (NASA-TP-1914: L-14575) Avail: NTIS HC A04/MF A01 several characteristic boundary layer parameters (momentum CSCL 018 thickness, form factors, energy factors and other combinational Tests were conducted in the Langley 12-foot low-speed parameters) were combined with simplified gas flow speed wind-tunnel to determine the longitudinal and lateral-directional distributions in the boundary layers in the wake behind the aerodynamic effects of plain and tabbed vortex flaps on a flat-plate, blade cascade and used to deduce, on the basis of the research highly swept arrow-wing model. Flow-visualization studies were foundation accumulated in the past about the theory of blade made using a helium-bubble technique. Static forces and moments cascade losses, a simplified equation for the calculation of total were measured over an angle-of-attack range from 0 deg to two-dimensional blade cascade pressure losses for subsonic and 50 deg for sideslip angles of 0 deg and -f or - 4 deg. A.R.H. transonic speeds. With this equation, it is possible to calculate the two-dimensional blade cascade pressure losses in designed N82-11014# Air Force Systems Command. Wright-Patterson operational configurations and off-designed operational configura- AFB, Ohio. Foreign Technol. Div. tions. A graphical method for determining the corrected gas ACTA MECHANICA SINICA compressibility effect in the blade cascade of compressors under 11 Sep. 1981 47 p refs Transl. into ENGLISH from Acta operating conditions involving higher subsonic and transonic Mech. Sinica (China), no. 1, 1979 70-73 speeds is also introduced. A.R.H. (AD-A105184: FTD-ID(RS)T-0704-81) Avail: NTIS HC A03/MF A01 CSCL 01/2 Various fluid dynamics problems are discussed including the N82-11026# Air Force Systems Command. Wright-Patterson computation of three-dimensional flow in turbomachinery. the AFB, Ohio. Foreign Technology Div. design of wing root regions of aircraft wing-body combinations, A THEORETICAL ANALYSIS OF THE STREAM SURFACE and the diffraction and reflection of traveling shock waves. OF REVOLUTION WITH SUPERSONIC INLET FLOW IN A TRANSONIC AXIAL COMPRESSOR Xu Jian-zhong. Jiang Zuo-ren. Yang Jin-sheng. Zhang Ying, and N82-11015# Air Force Systems Command, Wright-Patterson Du Zhuan-she In its J. of Eng. Thermophys. (Selected Articles) AFB, Ohio. Foreign Technology Div. (FTD-ID(RS)T-0570-81) 16 Sep. 1981 p 35-50 refs Transl. THE ARBITRARY QUASI-ORTHOGONAL SURFACE into ENGLISH from Gongcheng Rewuli Xuebao (China), v. 2. METHOD FOR COMPUTING THREE-DIMENSIONAL FLOW no. 1. Feb. 1981 Presented at the 3rd Ann. All-China Eng. IN TURBINE MACHINERY. 2. CALCULATION OF THE Thermophys. and Technol. Conf.. Gui Lin. China. Apr. 1980

33 N82-11027

Avail: NTIS HC A05/MF A01 CSCL 21/5 N82-11036# National Aerospace Lab.. Tokyo (Japan). First Changes in the gas flow velocity triangle behind the shock Airframe Div. waves being considered were studied in an effort to analyze the A STUDY ON NUMERICAL METHOD FOR EVALUATING effect which shock waves have on gas flow. A planar oblique SPANWISE INTEGRAL IN SUBSONIC LIFTING-SURFACE relationship formula was used to deduce the corresponding values THEORY of changes in velocity moment, pressure losses, and total pressure Teruo Ichikawa Mar. 1981 22 p refs ratios. This explains the important phenomenon involved when (NAL-TR-661T; ISSN-3989-4010) Avail: NTIS the supersonic intake cross section shock waves of transonic HC A02/MF A01 compressors cause addition pressurization of gas flow (supercharg- Two disputable points are discussed. The first point is the ing). Aerodynamic and thermodynamic analyses and calculations coincidence of each collocation section with one of the spanwise were then carried out on the tip cross sections of the rotors. integration points. The second point is the relatively small, but The characteristic curve calculations for the shock waves in undesirable, sharp variation of the regularized influence functions front of the blade cascades and for the intake areas of these near the collocation sections. Two proposals for coping with cascades are examined. Passageway shock waves are also these difficulties are made. Their effects are examined by calculated. Results are discussed. A.R.H. computing the downwash at the surface of a steady rectangular wing subjected to a simple wing loading. It is shown that method 1. which avoids the coincidence, makes it possible, with no N82-11027# Air Force Systems Command. Wright-Patterson losses in accuracy, to greatly reduce the computing time in cases AFB, Ohio. Foreign Technology Div. of oscillating wings. Further, it is shown that remarkable A NEW METHOD OF COOLING TURBINE VANES improvement in convergence with respect to the number of Gu Wei-zao. Zhang Yu-ming, and Xu Hong-kun In its J. of spanwise integration points is obtained by method 2 which Eng. Thermophys. (Selected Articles) (FTD-ID(RS)T-0570-81) distributes the spanwise integration points densely only near the 16 Sep. 1981 p 65-71 refs Transl. into ENGLISH from collocation sections. T.M. Gongcheng Rewuli Xuebao (China), v. 2, no. 1. Feb. 1981 Presented at the 3rd Ann. All-China Eng. Thermophys. Technol. Conf.. Gui Zhoy. China. Apr. 1980 N82-11039*# North Carolina State Univ.. Raleigh. Center for Sound and Vibration. Avail: NTIS HC A05/MF A01 CSCL 21/5 AIRCRAFT WING TRAILING EDGE NOISE The combined use of an internal cooling process with Ronald L. Underwood and Thomas H. Hodgson 1981 145 p strengthened blades and of additives to lessen heat transfer to refs the blades from fuel gasses is proposed as a means of increasing (Grant NsG-1377) intake temperature in aircraft turbine engines. Topics covered (NASA-CR-164952) Avail: NTIS HC A07/MF A01 CSCL include coarseness-strengthened heat exchange in the inner 01A passageways of blades and the precipitation of silicon dioxide The mechanism and sound pressure level of the trailing-edge particles in fuel gases onto blade surfaces. Temperature noise for two-dimensional turbulent boundary layer flow was calculations made for the first stage guide vanes of the MK202 examined. Experiment is compared with current theory. A NACA engine are included. A.R.H. 0012 airfoil of 0.61 m chord and 0.46 m span was immersed in the laminar flow of a low turbulence open jet. A 2.54 cm width roughness strip was placed at 15 percent chord from the N82-11033*# National Aeronautics and Space Administration. leading edge on both sides of the airfoil as a boundary layer Langley Research Center. Hampton. Va. WIND-TUNNEL RESULTS FOR A MODIFIED 17-PERCENT trip so that two separate but statistically equivalent turbulent boundary layers were formed. Tests were performed with several THICK LOW-SPEED AIRFOIL SECTION trailing-edge geometries with the upstream velocity U sub infinity Robert J. McGhee and William D. Beasley Nov. 1981 87 p refs ranging from a value of 30.9 m/s up to 73.4 m/s. Properties (NASA-TP-1919: L-14666) Avail: NTIS HC A05/MF A01 of the boundary layer for the airfoil and pressure fluctuations in CSCL 01A the vicinity of the trailing-edge were examined. A scattered pressure field due to the presence of the trailing-edge was Wind-tunnel tests were conducted in the Langley low- observed and is suggested as a possible sound producing turbulence pressure tunnel to evaluate the effects on performance mechanism for the trailing-edge noise. T.M. of modifying a 17-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the pitching-moment coefficient by increasing the forward loading and to increase the climb N82-11042*# National Aeronautics and Space Administration. lift-drag ratio by decreasing the aft upper surface pressure gradient. Lewis Research Center. Cleveland. Ohio. The tests were conducted over a Mach number range from 0.07 LOW SPEED TESTING OF THE INLETS DESIGNED FOR A to 0.32. a chord Reynolds number range 1.0 x 10 to the 6th TAMDEN-FAN V/STOL NACELLE power to 12.0 x 10 to the 6th power, and an angle-of-attack Robert C. Williams and Andres H. Ybarra (Vough Corp.. Dallas) range from about -10 deg to 20 deg. Author 1981 13 p refs Presented at the V/STOL Conf.. Palo Alto. Calif.. 7-9 Dec. 1981 N82-11034# National Aerospace Lab.. Tokyo (Japan). (NASA-TM-82728: E-1031; AIAA-81-2627) Avail: NTIS NEW ESTIMATION METHOD FOR FLUTTER OR DIVER- HC A02/MF A01 CSCL 01A GENCE BOUNDARY FROM RANDOM RESPONSES AT An approximately 0.25 scale model of a tandem fan nacelle, SUBCRITICAL SPEEDS designed for a subsonic V/STOL aircraft, was tested in a Lewis Yuji Matsuzaki and Yasukatsu Ando Apr. 1981 15 p refs wind tunnel. Model variables included long and short aft inlet (NAL-TR-667T; ISSN-0389-4-10) Avail: NTIS cowls and the addition of exterior strakes to the short inlet HC A02/MF A01 cowl. Inlet pressure recoveries and distortion were measured at A new technique for estimating the flutter or divergence pitch angles to 40 deg and at combinations of pitch and yaw boundary from responses due to turbulence at subcritical speeds to 30 deg. Airspeeds covered a range to 135 knots (69 m/sec). is described. The boundary can be predicted without estimating The short aft inlet with added strakes had the best aerodynamic or measuring the dampings and frequencies of the aeroelastic performance and is considered suitable for the intended V/STOL modes. The sampled time response is modeled by the mixed application. T.M. autoregressive moving average process. The orders and coefficients of both autogressive and moving average parts of the process N82-11043*# National Aeronautics and Space Administration. are determined with the aid of Akaike's estimation procedure. Lewis Research Center. Cleveland. Ohio. The stability boundary is estimated by using Jury's stability A SUMMARY OF V/STOL INLET ANALYSIS METHODS determinants which are expressed in terms of the autogressive Danny P. Hwang 1981 12 p refs Presented at the V/STOL coefficients alone. The modal frequencies and dampings are Conf.. Palo Alto. Calif.. 7-9 Dec. 1981 also evaluated from the coefficients. The technique proposed (NASA-TM-82725: E-1027) Avail: NTIS HC A02/MF A01 has been applied with success to signals from a cantilever wing CSCL 01A model tested in a low supersonic flow. Comparison between Recent extensions and applications of the methods are the actual and estimated flutter boundaries shows that an accurate emphasized. They include the specification of the Kutta condition estimation can be made from data obtained in a narrow range for a slotted inlet, the calculation of suction and tangential blowing of the dynamic pressure which is sufficiently below the bound- for boundary layer control, and the analysis of auxiliary inlet ary. Author geometries at angles of attack. A comparison is made with

34 N82-11054

experiment for the slotted inlet. An optimum diffuser velocity FAA is not adequately surveying or evaluating air traffic distribution was developed. T.M. levels at 24 hour control towers to identify opportunities to reduce operating hours and save money. GRA

N82-11046*$ National Aeronautics and Space Administration. N82-11050*# National Aeronautics and Space Administration. Langley Research Center. Hampton. Va. Langley Research Center. Hampton. Va. COMPUTATION OF HIGH REYNOLDS NUMBER INTERNAL/ PARAMETRIC STUDY OF MICROWAVE-POWERED EXTERNAL FLOWS HIGH-ALTITUDE AIRPLANE PLATFORMS DESIGNED FOR Michael C. Cline and Richard G. Wilmoth 1981 12 p refs LINEAR FLIGHT Presented at the 5th AIAA Computational Fluid Dyn. Conf.. Palo Charles E. K. Morris. Jr. Nov. 1981 74 p rets Alto. Calif.. 22-23 Jun. 1981 (NASA-TP-1918: L-14606) Avail: NTIS HC A04/MF A01 (Contract W-7405-eng-36) CSCL 01C INASA-TM-84049: DE81-025343: LA-UR-81-1882; The performance of a class of remotely piloted, microwave CONF-810664-2) Avail: NTIS HC A02/MF A01 CSCL 01A powered, high altitude airplane platforms is studied. The first A general, user oriented computer program, called VNAP2. part of each cycle of the flight profile consists of climb while was developed to calculate high Reynolds number, internal/ the vehicle is tracked and powered by a microwave beam: this external flows. The VNAP2 program solves the two dimensional, is followed by gliding flight back to a minimum altitude above time dependent Navier-Stokes equations. The turbulence is a microwave station and initiation of another cycle. Parametric modeled with either a mixing-length, a one transport equation, variations were used to define the effects of changes in the or a two transport equation model. Interior grid points are characteristics of the airplane aerodynamics, the energy transmis- computed using me explicit MacCormack Scheme with special sion systems, the propulsion system, and winds. Results show procedures to speed up the calculation in the fine grid. All boundary that wind effects limit the reduction of wing loading and the conditions are calculated using a reference plane characteristic increase of lift coefficient, two effective ways to obtain longer scheme with the viscous terms treated as source terms. Several range and endurance for each flight cycle. Calculated climb internal, external, and internal/external flow calculations are performance showed strong sensitivity to some power and presented. DOE propulsion parameters. A simplified method of computing gliding endurance was developed. S.L. N82-11047# Federal Aviation Administration. Washington. D.C. Systems Research and Development Service. N82-11052*$ Kansas Univ. Center for Research. Inc., Lawrence. THREAT ALERT AND COLLISION AVOIDANCE SYSTEM Flight Research Lab. (TCAS) SYMPOSIUM ICING TUNNEL TESTS OF A COMPOSITE POROUS 22 Jul. 1981 177 p refs Symp. held at Washington. D.C.. LEADING EDGE FOR USE WITH A LIQUID ANTI-ICE 22 Jul. 1981 SYSTEM (AD-A104563: FAA-RD-81-76) Avail: NTIS David L Kohlman Sep. 1981 21 p refs HC A09/MF A01 CSCL 01/4 (Grant NAG3-71) The Federal Aviation Administration held a symposium on (NASA-CR-164966: KU-FRL-464-3) Avail: NTIS Threat Alert and Collision Avoidance System (TCAS) in Washing- HC A02/MF A01 CSCL01C ton. D.C.. July 22. 1981. which was attended by representatives The efficacy of liquid ice protection systems which distribute of 68 organizations and 21 airlines. This report contains the a glycol-water solution onto leading edge surfaces through a news release announcing the new approach to providing porous skin was demonstrated in tests conducted in the NASA protection against mid-air collisions. 10 presentations and the Lewis icing research tunnel using a composite porous leading transcript of the panel discussion. The TCAS will provide a range edge panels. The data obtained were compared with the of capabilities and costs which will meet the requirements of all performance of previously tested stainless steel leading edge airspace users. The least complex part of the system is designed with the same geometry. Results show: (1) anti-ice protection for private pilots and would cost about $2.500. The fully of a composite leading edge is possible for all the simulated capable, or airline, version would cost between $45,000 and conditions tested: (2) the glycol flow rates required to achieve $50.000. This new concept represents a new capability which anti-ice protection were generally much higher than those required draws on all FAA has learned about collision avoidance in its for a stainless steel panel: (3) the low reservoir pressures of past efforts, extends and simplifies FAA's efforts to date, provides the glycol during test runs indicates that more uniform distribu- new capabilities to all users, and is fully compatible with tion of glycol. and therefore lower glycol flow rates, can probably international standards and improvement activities on the be achieved by decreasing the porosity of the panel: and (4) Secondary Surveillance Radar (£SR). Author (GRA) significant weight savings can be achieved in fluid ice protection systems with composite porous leading edges. The resistance of composite panels to abrasion and erosion must yet be determined N82-11048# Lear Siegler. Inc.. Grand Rapids. Mich. Instrument before they can be incorporated in production systems. A.R.H. Div. FLIGHT TRAJECTORY CONTROL INVESTIGATION Final Report. 15 May 1978 - 30 Oct. 1980 N82-11053*# National Aeronautics and Space Administration. M. Bird and J. Karmarker Wright-Patterson AFB. Ohio AFWAL Lewis Research Center, Cleveland, Ohio. Mar. 1981 174 p refs SELECTED BIBLIOGRAPHY OF NACA-NASA AIRCRAFT (Contract F33615-78-C-3607. AF Proj. 2403) ICING PUBLICATIONS (AD-A104542; ID-05R-1180: AFWAL-TR-81-3012) Avail: John J. Reinmann, comp Aug. 1981 127 p NTIS HC A08/MF A01 CSCU 17/9 (NASA-TM-81651: E-668) Avail: NTIS HC E15/MF A01 CSCL Optimal control algorithms for four-dimensional guidance of 01C a transport aircraft were investigated for feasibility. Cost function A summary of NACA-NASA icing research from 1940 to constraints on the optimal reference path generator appeared 1962 is presented. It includes: the main results of the NACA icing program from 1940 to 1950: a selected bibliography of impossible to achieve and the optimal guidance algorithms do 132 NACA-NASA aircraft icing publications: a technical summary not achieve significant performance improvement without of each document cited in the selected bibliography: and a excessive increases in sophistication and cost of the onboard avionics computer. A modularized existing Mission Management microfiche copy of each document cited in the selected system allows a three-phase flight test plan to demonstrate the bibliography. T.M. operational capability of the existing classical integrated flight trajectory control algorithms. Author (GRA) N82-11054*$ National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. N82-11049$ General Accounting Office. Washington. D. C. A COMPARISON OF THEORETICAL AND EXPERIMENTAL Community and Economics Development Div. PRESSURE DISTRIBUTIONS FOR TWO ADVANCED FAA MISSES OPPORTUNITIES TO DISCONTINUE OR FIGHTER WINGS REDUCE OPERATING HOURS OF SOME AIRPORT TRAFFIC H. P. Hanev WougUt Cotp.. Dallas) and R. M. Hicks Oct. 1981 CONTROL TOWERS Report to the Congress 87 p refs 1 Jun. 1981 39 p (NASA-TM-81331: A-8741) Avail: NTIS HC A05/MF A01 (PB81-224214: CED-81-100) Avail: NTIS HC A03/MF A01 CSCL 01C CSCL 17G A comparison was made between experimental pressure

35 N82-11055

distributions measured during testing of the Vought A-7 fighter TECHNOLOGY BASE FOR ICING INSTRUMENTATION AND and the theoretical predictions of four transonic potential flow MATHEMATICAL MODELLING codes. Isolated wind and three wing-body codes were used for In its Rotorcraft Icing Aug. 1981 p 14-33 refs comparison. All comparisons are for transonic Mach numbers and include both attached and separate flows. In general, the Avail: NTIS HC A07/MF A01 wing-body codes gave better agreement with the experiment The fundamental mechanisms of ice accretion and shedding than did the isolated wing code but, because of the greater from rotor airfoils are considered. It is felt that an opportunity complexity of the geometry, were found to be considerably more exists to exploit a combination of two-dimensional model and expensive and less reliable. Author three-dimensional model scale testing, measurement of ice release mechanisms, inclusion of heat transfer models, and considera- tion of icing simulation. These efforts should be aimed at N82-11055/JI Computational Mechanics Consultants. Knoxville. development of analytical models verified by both laboratory and Tenn. A NUMERICAL THREE-DIMENSIONAL TURBULENT full-scale data which then can be used to better predict SIMULATION OF A SUBSONIC VSTOL JET IN A CROSS- performance of rotors in icing conditions. Only with the above FLOW USING A FINITE ELEMENT ALGORITHM Final analytical basis can ice accretion and shedding characteristics become sufficiently predictable to permit the determination of Report. Sep. 1979 . Sep. 1980 what type of ice protection is necessary or, conversely, what A. J. Baker, J. A. Orzechowski. and P. 0. Manhardt Jun. 1981 72 p refs degree of flight envelope release might be permitted with a given level of ice protection. Further improvement in research (Contract N62269-79-C-0295) and development of operational icing sensors is recommended. (AD-A104514; NADC-79021-60) Avail: NTIS J.D.H. HC A04/MF A01 CSCL 01/3 The purpose of this study, the results of which are reported herein, was to formulate a mathematical model of the basic N82-11059# Advisory Group for Aerospace Research and VSTOL jet, and to validate its appropriateness by performing a Development, Neuilly-Sur-Seine (France). series of computational experiments on the discrete analog FACILITIES FOR DEVELOPMENT AND CLEARANCE (numerical) approximation to the mathematical description. In its Rotorcraft Icing Aug. 1981 p 34-53 Since the VSTOL jet problem is essentially steady, turbulent and fully three-dimensional, the mathematical description must Avail: NTIS HC A07/MF A01 be quite comprehensive. The approach selected was to utilize a A catalog of all NATO icing test facilities was compiled. It continuity-constrained, finite element algorithm for solution of is recommended that the Canadian National Research Council's the parabolized form of the time-averaged, three-dimensional small high speed icing tunnel is a one-of-a-kind facility that Navier-Stokes equations (3DPNS). The essential ingredients of needs to be available to support analytical development recom- this algorithmic description are presented and discussed. A mended, and that the tunnel should be reactivated or replaced. production finite element computer code (COMOC:3DPNS) was A decision has been made to retain the Ottawa Spray Rig in utilized to conduct the computational experiments, and the operational status for the near future. Efforts underway at the description of problem definition and data deck preparation is NASA-Lewis Research Center regarding rehabilitation of the Icing contained at the end of the report. The key results of the Research Tunnel and considering a major new icing test facility computational experiments are discussed, regarding the basic are endorsed. The US Army Helicopter Icing Spray System causal mechanisms of the VSTOL jet, as well as results for Improvement Program is also supported by the Working Group confirmation test cases documenting viability of the constructed and. as a recommendation for future discussion, the need for computational model. Author (GRA) European airborne icing spray systems should be considered. A conclusion reached by the Working Group is that current full N82-11066# Advisory Group for Aerospace Research and scale development and qualification facilities and procedures are Development, Neuilly-Sur-Seine (France). extremely expensive and time consuming. J.D.H. ROTORCRAFT ICING: STATUS AND PROSPECTS Aug. 1981 136 p refs N82-11060# Advisory Group for Aerospace Research and (AGARD-AR-166; ISBN-92-835-1397-5) Avail: NTIS Development. Neuilly-Sur-Seine (France). HC A07/MF A01 ICE PROTECTION SYSTEM TECHNOLOGY The impact of icing meteorological conditions on helicopter In its Rotorcraft Icing Aug. 1981 p 54-99 refs operations was examined, and methods for improving ice protection investigated. Avail: NTIS HC A07/MF A01 Deicing systems technology concepts are discussed. The conclusion is that electrothermal deicing systems are the only N82-11067jfl Advisory Group for Aerospace Research and effective present system for broad application. However, it is Development. Neuilly-Sur-Seine (France). noted that the cost of electrothermal deicing in terms of weight, OPERATIONAL ENVIRONMENT. METEOROLOGICAL power and expense is high, and provides an incentive for CONDITIONS AND WEATHER FORECASTING examination of alternatives. Therefore, additional work is clearly In its Rotorcraft Icing Aug. 1981 p 1-13 refs warranted on options such as ice phobics. fluid ice suppressant systems, pneumatic boots, vibratory surface systems, microwave Avail: NTIS HC A07/MF A01 and other hybrid systems concepts. It is recommended that the Helicopter icing is a significant operational consideration for operational limitations of ice protected aircraft such as the Black helicopters operating throughout Europe. Existing weather Hawk and Puma, be explored with the ice protection systems statistics demonstrate significant operational limitations during deliberately turned off, so as to simulate an aircraft without (or the winter months, and for as much as five percent of the time with inoperative) ice protection. Only through such definition of on a year-around basis. Unfortunately the existing meteorological the actual icing environment can a better estimation be made data base is insufficient to describe the operating environment of the operational impact of icing conditions on helicopter flight in which NATO rotorcraft must conduct flight. At present for operations. J.D.H. design purposes, the United States Federal Air Regulation 25 Appendix C or the UK Icing Atmosphere are employed for N82-11061# Advisory Group for Aerospace Research and determination of airworthiness release of helicopters. However, Development, Neuilly-Sur-Seine (France). neither of these atmospheres adequately defines the operational PROPOSED STANDARD REQUIREMENTS AND PRO- environment. This condition is exacerbated by the fact that CEDURES FOR ICING CLEARANCE forecasting techniques are currently inadequate to allow unrestric- In its Rotorcraft Icing Aug. 1981 p 100-117 ted helicopter operations in icing conditions. Increased coordina- tion among cloud physicists, forecasters, and helicopter icing Avail: NTIS HC A07/MF A01 specialists is needed - and ultimately a new icing atmosphere is A set of proposed standard requirements and procedures required to better define the helicopter operational icing for icing clearance is presented. It is felt that this clearance requirements. J.D.H. procedure constitutes a basis for NATO-wide icing clearance and should be adopted by the NATO military community as an interim N82-11058jjl Advisory Group for Aerospace Research and approach. The opportunity also exists to consider this proposal Development. Neuilly-Sur-Seine (France). for civil icing clearance. J.D.H.

36 N82-11068

N82-11062# Hughes Aircraft Co.. El Segundo. Calif. Display in implementation and cost even for the same bus standard. Systems Lab. The materials represent a snapshot of the current state of the STUDY AND DEVELOPMENT OF AN INTEGRATED art technology. The use of optical fiber instead of conventional HEAD-UP DISPLAY Final Report. 1 Jul. 1976 - 31 Aug. electrical cable (such as coaxial) as the transmission medium is 1980 also investigated based on the current technical reports. The Michael N. Ernstoff Jun. 1981 112 p refs problems of electromagnetic interference (EMI), and rejection (Contract F33615-76-C-1243: AF Proj. 2003) techniques are mentioned. GRA (AD-A104337; HAC-D6210; AFWAL-TR-81-1042) Avail: NTIS HC A06/MF A01 CSCL 14/5 N82-11065# General Electric Co.. Binghamton. N.Y. Aircraft The purpose of the Integrated Head-Up Display (I-HUD) Equipment Div. program was to demonstrate the advantages associated with ELECTRONIC MASTER MONITOR AND ADVISORY using a Liquid Crystal Matrix Display and Diffraction Optics DISPLAY SYSTEM, HUMAN ENGINEERING SUMMARY combiner in the design and construction of a high brightness REPORT Interim Report. Jun. 1979 - Jun. 1981 head-up display system. The program resulted in the design and Jun. 1981 227 p refs fabrication of the I-HUD brassboard consisting of a pilot's display (Contract DAAK80-79-C-0270: DA Proj. 1L2-62202-AH-85) unit, built in a form factor similar to that of the production F16 (AD-A104244: ACS-12385: USAAVRADCOM-TR-79-0270-3: HUD. and test support equipment. The following devices and IR-3) Avail: NTIS HCA11/MFA01 CSCL 17/2 modules were developed: A 350-by-350 pixel Liquid Crystal Information requirements, information handling formats, and Matrix Display complete with custom LSI circuit drivers, a the necessary display/control design criteria are discussed for a diffraction optics combiner, a diffraction optics diffusing screen, system being developed to integrate and display nonmission a specular mode projector, and custom lamp with a narrow related information on the status of various subsystems on rotary band (green) spectral output. Although the completed I-HUD wing aircraft. GRA brassboard did not meet all of its design goals, it does demonstrate the feasibility of applying advanced technology to the designs N82-11O66# Los Alamos Scientific Lab.. N. Mex. Electronics of Head-Up Displays. The I-HUD program has succeeded in solving Div. many of the fundamental design problems associated with this OUTSIDER'S LOOK AT FLIGHT INSTRUMENTATION approach and stands as a milestone in the development of solid Arvid S. Lundy 1981 7 p refs Presented at the AIAA/SAE/ state display devices and the development of more highly ASME Joint Propulsion Conf.. Colorado Springs. Colo.. 27-29 Jul. reliable, cost effective Head-Up Displays. GRA 1981 (Contract W-7405-eng-36) N82 11063# Panametrics. Inc.. Waltham. Mass. (DE81-025409: LA-UR-81-1748: CONF-810724-1) Avail: ADVANCED FUEL FLOWMETER FOR FUTURE NAVAL NTIS HC A02/MF A01 AIRCRAFT Final Report. Doc. 1977 - Apr. 1981 Ideas and speculations on possible diagnostic instrumentation L. C. Lynnworth. N. E. Pedersen. J. E. Bradshaw. J. E. Matson. for use in missile flight testing are presented. Techniques for E. S. Johansson, and T. H. Nguyen 28 Jun. 1981 149 p use in the development of flight instrumentation are recom- refs mended. DOE (Contract N62269-78-C-0069) (AD-A104364: NADC-80254-60) Avail: NTIS HC A07/MF A01 CSCL 21/4 N82-11067$ National Aerospace Lab., Tokyo (Japan). A fuel mass flowmeter was developed with the objective of NEW MOLDING METHOD OF THREE-DIMENSIONAL accurately measuring the mass flow rate M-dot of various fuels HOLLOW PHOTOELASTIC MODEL AND CENTRIFUGAL and their mixtures, for flow rates from 91 to 11.364 kg/hr STRESS ANALYSIS OF AIR COOLED TURBINE BLADE (200 to 25.000 Ib/hr). The delivered system included: (1) an MODEL area averaging zigzag flow velocimeter cell, in which the fuel Toyoaki Yoshida. Katsutashi Matsusue, Kitao Takahara, and was interrogated in opposite directions by an alternating sequence Ryosaku Hashimoto May 1981 17 p refs In ENGLISH: of ultrasonic pulses, to determine the area averaged flow velocity. JAPANESE Summary V-bar: (2) a densitometer based on the Clausius-Mosotti law. in (NAL-TR-427T: ISSN-0389-4010) Avail: NTIS which the fuel density rho is determined: and (3) electronics HC A02/MF A01 which computed rho and V-bar separately, and then generated A new molding method for a three dimensional hollow a square wave output having a frequency proportional to the photoelastic model was invented and centrifugal stress analysis product of rho and V-bar. namely M-dot = rho(V-bar)A. where performed for air cooled turbine blade models to which the new A = velocimeter cell cross sectional area. The transducers can method was applied. A distinctive feature of the molding method operate beyond the temperature range -38 to +150 C, and the is the introduction of a copper coated wax core which forms a flow cell, with transducers, at pressures up to 1500 psig and in three dimensional hollow shape inside a model. The air cooled the 3-axis, 20 g, 5 to 2000 Hz vibration environment specified turbine photoelastic model with a coolant passage simulates the by MIL Std. 810-514.1, except for noise problems at a few first stage rotor blade in the high temperature turbine full scale discrete frequencies. GRA model HT-10H used at the NAL. The results of stress analysis cleared the critical regions and stress magnitude and thus they are of great aid to the successful development of a full scale N82-11064# General Electric Co.. Binghamton. N.Y. Aircraft turbine model. Author Equipment Div. ELECTRONIC MASTER MONITOR AND ADVISORY N82-11068*# Teledyne Continental Motors. .Muskegon. Mich. DISPLAY SYSTEM, DATA TRANSMISSION STUDY Interim General Products Div. Report. Jun. 1979 - Aug. 1980 LIGHTWEIGHT DIESEL ENGINE DESIGNS FOR COMMUT- Aug. 1980 57 p refs ER TYPE AIRCRAFT (Contract DAAK80-79-C-0270: DA Proj. 1L2-62202-AH-85) Alex P. Brouwers Jul. 1981 70 p refs (AD-A104243: ACS-12177: USAAVRADCOM-TR-79-0270-1: (Contract NAS3-22149) IR-1) Avail: NTIS HC A04/MF A01 CSCL 17/2 (NASA-CR-165470: Rept-995) Avail: NTIS HC A04/MF A01 The development of nonmission related status information is CSCL 21E one area of rotary wing instrumentation which has not kept Conceptual designs and performance of advanced technology pace with the state of art. This includes raw data, discrete and lightweight diesel engines, suitable for commuter type aircraft summary status information related to the engine, transmission, power plants are defined. Two engines are discussed, a 1491 kW rotor, fuel, hydraulic and electrical subsystems. The objective of (2000 SHP) eight-cylinder engine and a 895 kW (1200 SHP) this report is to define an efficient and cost effective data six-cylinder engine. High performance and related advanced transmission method for an electronic master monitor and technologies are proposed such as insulated cylinders, very high advisory display system (EMMADS). Several current standard injection pressures and high compressor and turbine efficiencies. and nonstandard data bus specifications which are applicable to The description of each engine includes concept drawings, a the EMMADS system are introduced. Their tradeoff in terms of performance analysis, and weight data. Fuel flow data are given hardware, software and system considerations are compared. It for full and partial power up to 7620m altitude. The performance should be noted that a typical standard bus specs addresses data are also extrapolated over a power range from only the protocol and message formats, not the mechanization 671 kW(900 SHP) to 1864 kW (2500 SHP). The specific fuel of the control algorithm. Hence there is a considerable variation consumption of the 1491 kW (2000 SHP) engine is 182

37 N82-11069 g/hWh (.299 Ib/HPh) at cruise altitude, its weight 620 kg 214 p refs (1365 Ib.) and specific weight .415 kg/kW (.683 Ib/HP). The (Contract F33615-77-C-2034: AF Pro). 3145) specific fuel consumption of the 895 kW (1200 SHP) engine is (AD-A104263: AFWAL-TR-81-2012) Avail: NTIS 187 g/hWh (.308 Ib/HPh) at cruise altitude, its weight 465 kg HC A10/MF A01 CSCL 09/2 (1025 Ib.) and specific weight .520 kg/kW (.854 Ib/HP). R.J.F. The development of an Incremental digitally-controlled electrohydraulic incremental digitally-controlled electrohydraulic N82-11069# Naval Postgraduate School. Monterey. Calif. Dept. actuation system (DEHA) is reported. An electronic digital of Aeronautics. controller and a prototype DEHA unit, with an electric-stepper- SUBSONIC CASCADE WIND TUNNEL TESTS USING A motor-driven rotary distributor valve, two hydraulic drive motors, COMPRESSOR CONFIGURATION OF DCA BLADES and a torque-summing gearbox, were assembled. Significant M.S. Thesis reductions in the hydraulic power normally required with a Frank S. Cina Jun. 1981 210 p refs conventional geared hydraulic motor system, and some degree (AD-A104597) Avail: NTIS HCA10/MFA01 CSCL 21/5 of hydraulic power recovery were obtained. Author (GRA) Tests are reported in which air incidence angle was varied to a cascade of 20 blades. 5 inches in chord with aspect ratio N82-11073# Advisory Group for Aerospace Research and of 2.0 and solidity of 1.67. Preliminary blade element performance Development. Neuilly-Sur-Seine (France). Guidance and Control data were obtained using pneumatic probe surveys and surface Panel. pressures were also measured. Results of preparatory tests of a THEORY AND APPLICATIONS OF OPTIMAL CONTROL IN similar cascade of 15 C-senes blades at a solidity of 1.28 are AEROSPACE SYSTEMS also included. Whereas the flow in the C-series blading cascade Pieter Kant. ed. (National Aerospace Lab.. Emmeloord. Nether- was always acceptable, the flow in the DCA blading cascade lands) London Jul. 1981 283 p refs was not acceptable at negative incidence angles. A modification (AGARD-AG-251: ISBN-92-835-1391-6) Copyright. Avail: of the cascade inlet guide vanes is recommended which will NTIS HC A13/MF A01 guarantee periodic conditions and serve to generate more nearly The basic concepts of control theory were reviewed. Pratical uniform inlet flow at all test conditions. Author (GRA) design techniques that were developed from the theory are presented. Design examples and practical applications in real N82-11070*# Analytical Mechanics Associates, Inc.. Hampton. systems are described. Major emphasis is on flight control of Va. distributed parameter systems. AN INFLUENCE COEFFICIENT METHOD FOR THE APPLI- CATION OF THE MODAL TECHNIQUE TO WING FLUTTER SUPPRESSION OF THE DAST ARW-1 WING Final Report N82-11074jjf Stanford Univ.. Calif. Dept. of Aeronautics and Samuel Pines Nov. 1981 49 p refs Astronautics. (Contract NAS1-15593) AN OVERVIEW OF OPTIMAL CONTROL IN AEROSPACE (NASA-CR-165772: AMA-81-25) Avail: NTIS SYSTEMS HC A03/MF A01 CSCL01C Arthur E. Bryson, Jr. In AGARD Theory and Appl. of Optimal The methods used to compute the mass, structural stiffness, Control in Aerospace Systems Jul. 1981 5 p refs and aerodynamic forces in the form of influence coefficient matrices as applied to a flutter analysis of the Drones for Avail: NTIS HC A13/MF A01 Aerodynamic and Structural Testing (DAST) Aeroelastic Research Optimal control started with the calculus of variations Wing. The DAST wing was chosen because wind tunnel flutter (COV) The digital computer made the calculus of variations a test data and zero speed vibration data of the modes and practical tool for synthesis of optimal control logic. Optimal control frequencies exist and are available for comparison. A derivation concepts and algorithms are used not only in the field of automatic of the equations of motion that can be used to apply the modal control but also in fields of structural optmization. econometrics, method for flutter suppression is included. A comparison of the and operations research. T.M. open loop flutter predictions with both wind tunnel data and other analytical methods is presented. S L. N82-11075# Universite Catholique de Louvain (Belgium). THEORY OF STOCHASTIC OPTIMAL CONTROL SOME N82-11071*# Massachusetts Inst. of Tech., Cambridge. Dept. BASIC NOTIONS of Aeronautics and Astronautics. In AGARD Theory and Appl. of Optimal Control in Aerospace AEROACOUSTfC THEORY FOR NONCOMPACT WING- Systems Jul. 1981 19 p refs GUST INTERACTION Rudolph Martinez and Sheila E. Widnall Oct. 1981 124 p Avail: NTIS HC A13/MF A01 refs The optimal control problem for stochastic systems is (Grant NsG-2142) described in details. Several classes of policy are defined and (FDRL-81-7) Avail: NTIS HC A06/MF A01 CSCL 01C compared The corresponding solutions are deduced from Three aeroacoustic models for noncompact wing-gust Bellman's principle and discussed in connection with the concept interaction were developed for subsonic flow The first is that of dual effect of the control. After the derivation of the optimal for a two dimensional (infinite span) wing passing through an closed-loop solution for the linear quadratic Gaussian problem, oblique gust. The unsteady pressure field was obtained by the several algorithms are proposed for the nonlinear problem and Wiener-Hopf technique: the airfoil loading and the associated discussed in the perspective of their implementation in aerospace acoustic field were calculated, respectively, by allowing the field applications. T.M. point down on the airfoil surface, or by letting it go to infinity. The second model is a simple spanwise superposition of two N82-11076# Princeton Univ.. N J. Flight Research Lab. dimensional solutions to accuunt for three dimensional acoustic AN INTRODUCTION TO STOCHASIC OPTIMAL CONTROL effects of wing rotation (for a helicopter blade, or some other THEORY rotating planform) and of finiteness of wing span. A three In AGARD Theory and Appl of Optimal Control in Aerospace dimensional theory for a single gust was applied to calculate Systems Jul. 1981 33 p refs the acoustic signature in closed form due to blade vortex interaction in helicopters The third model is that of a quarter Avail: NTIS HC A13/MF A01 infinite plate with side edge through a gust at high subsonic The design of control logic that commands a dynamic system speed. An approximate solution for the three dimensional loading to a desired output or that augments the system's stability is and the associated three dimensional acoustic field in closed facilitated if objectives are expressed in a quantitative criterion, form was obtained. The results reflected the acoustic effect of because the optimization of this criterion establishes a feasible satisfying the correct loading condition at the side edge. R.J.F. design point for control. If the information which the control logic must use is uncertain or if the dynamic system is forced N82-11072# Boeing Military Airplane Development, Seattle. by random disturbances, only the expected value can be optimized. Wash. Advanced Airplane Branch. The methodology for design is based upon stochastic optimal AIRCRAFT DIGITAL INPUT CONTROLLED HYDRAULIC control theory. After introducing the dynamic models of interest, ACTUATION AND CONTROL SYSTEM Final Report, Aug. optimal control and estimation are presented separately. 1977 - Dec. 1980 Limitations of this approach are addressed, and the unified design Eugene T. Raymond and Curtiss W. Robinson Mar. 1981 of linear stochastic optimal controllers for analog and digital

38 N82-11084

implementations is described. The principal benefit of stochastic other criteria. Aspects of the control law design and flight test optimal control theory is that it provides an engineering framework experience with the integrated digital flight control system are within which practical control design can be accomplished for described. DOE complex dynamic systems. T.M. N82-11081# Purdue Univ.. Lafayette. Ind. School of Aeronautics N82-11077# Royal Aircraft Establishment. Farnborough and Astronautics. (England). Flight Systems Dept. CONTROL DESIGN OF FLEXIBLE SPACECRAFT DESIGN CONSIDERATIONS FOR OPTIMAL FLIGHT Robert E. Skelton In AGARD Theory and Appl. of Optimal CONTROL SYSTEMS Control in Aerospace Systems Jul. 1981 28 p refs F. R. Gill In AGARD Theory and Appl. of Optimal Control in Aerospace Systems Jul. 1981 21 p refs Avail: NTIS HC A13/MF A01 When compared to other large scale systems, flexible Avail: NTIS HC A13/MF A01 spacecraft have some peculiarities which can make control more Following a review of the several interacting factors affecting difficult. Emphasis is placed upon the time domain and suboptimal the design of control laws for any kind of flight control system linear quadratic guassian (LOG) methods, with special attention (FCS). the modelling problem is discussed, including accuracy given to the effects of modeling errors. These effects are discussed requirements for computer models of the aircraft. FCS. external in light of the model reduction problem, stability, and control disturbances and sensor noise. The state-of-the-art in designing design. Stability, controllability and observability computations the control and scheduling laws is surveyed and the limits of are reduced to their simplest form possible to provide insight conventional control techniques are exposed. To overcome these and to facilitate the location of sensors and actuators. The limits, the use of selected nonlinear control techniques is discussed, techniques of modal cost analysis are used to identify the critical including the concept of redundant adaptation with safeguards. parameters and the critical models of the structure. In the final T.M. stage of design, component cost analysis reveals which states of the optimal dynamical controller should be deleted to produce N82-11078*# Honeywell Systems and Research Center. a reduced controller which is compatible with the on-line computer Minneapolis, Minn. Systems and Control Technology Sect. software limitations. T.M. DESIGN TECHNIQUES FOR MUTLIVARIABLE FLIGHT CONTROL SYSTEMS N82-11082*# National Aeronautics and Space Administration. In AGARD Theory and Appl. of Optimal Control in Aerospace Ames Research Center, Moffett Field, Calif. Systems Jul. 1981 33 p refs OPTIMUM CLIMB AND DESCENT TRAJECTORIES FOR AIRLINE MISSIONS (Contracts NAS4-2518: N00014-75-C-01444) Heinz Erzberger In AGARD Theory and Appl. of Optimal Control Avail: NTIS HC A13/MF A01 CSCL01C in Aerospace Systems Jul. 1981 15 p refs Techniques which address the multi-input closely coupled nature of advanced flight control applications and digital Avail: NTIS HC A13/MF A01 CSCL 01C implementation issues are described and illustrated through flight The characteristics of optimum fixed-range trajectories whose control examples. The techniques described seek to exploit the structure is constrained to climb, steady cruise, and descent advantages of traditional techniques in treating conventional segments are derived by application of optimal control theory. feedback control design specifications and the simplicity of modern The performance function consists of the sum of fuel and time approaches for multivariable control system design. T.M. costs, referred to as direct operating cost (DOC). The state variable is range to go and the independent variable is energy. In this formulation a cruise segment always occurs at the optimum N82-11079# Bodenseewerk Geraetetechnik GmbH, Ueberlin- cruise energy for sufficiently large range. At short ranges (400 n. gen (West Germany). mi. and less), a cruise segment may also occur below the optimum PRACTICAL DESIGN AND REALIZATION OF A DIGITAL cruise energy. The existence of such a cruise segment depends ADAPTIVE FLIGHT CONTROL SYSTEM primarily on the fuel flow vs thrust characteristics and on thrust V. Krebs and U. Hartmann In AGARD Theory and Appl. of constraints. If thrust is a free control variable along with Optimal Control in Aerospace Systems Jul. 1981 22 p refs airspeed, it is shown that such cruise segments will not generally Sponsored in part by the West German Ministry of Defense occur. If thrust is constrained to some maximum value in climb and to some minimum in descent, such cruise segments generally Avail: NTIS HC A13/MF A01 will occur. T.M. A new approach for the design and the practical realization of a digital adaptive command and stability system is proposed N82-11083"# National Aeronautics and Space Administration. The control law for the longitudinal motion of the aircraft is Ames Research Center. Moffett Field, Calif. obtained by state vector feedback using the MIL-F-8785 B handling qualities requirements. The design principle is based APPLICATION OF NONLINEAR SYSTEMS INVERSES TO on decoupling of the angle of attack and pitch rate on the one AUTOMATIC FLIGHT CONTROL DESIGN: SYSTEM CONCEPTS AND FLIGHT EVALUATIONS hand and tne pole allocation method for the eigenvalues of the George Meyer and Luigi Cicolani In AGARD Theory and Appl. control system on the other hand. Since the necessary gain of Optimal Control in Aerospace Systems Jul. 1981 29 p factors contain unknown and variable aircraft parameters, an refs on-line fading-memory least squares algorithm for the estimation Avail: NTIS HC A13/MF A01 CSCL 01C of these parameters is used. Only conventional aircraft sensors A practical method for the design of automatic flight control (rate gyros and accelerometers) and an airborne digital computer systems for aircraft with complex characteristics and operational are necessary. Hybrid simulations of the complete system as requirements, such as the powered lift STOL and V/STOL well as flight test results demonstrate the efficiency of the configurations, is presented. The method is effective for a large concept. T.M. class of dynamic systems requiring multi-axis control which have highly coupled nonlinearities. redundant controls, and complex N82-11080# Deutsche Forschungs- und Versuchsanstalt fuer multidimensional operational envelopes. It exploits the concept Luft- und Raumfahrt. Brunswick (West Germany). of inverse dynamic systems, and an algorithm for the construction CONTROL LAW DESIGN FOR TRANSPORT AIRCRAFT of inverse is given. A hierarchic structure for the total control FLIGHT TASKS logic with inverses is presented. The method is illustrated with Volkmar Adam and Hagen Leyendecker In AGARD Theory an application to the Augmentor Wing Jet STOL Research Aircraft and Appl. of Optimal Control in Aerospace Systems Jul. 1981 equipped with a digital flight control system. Results of flight 13 p refs evaluation of the control concept on this aircraft are presented. Avail: NTIS HC A13/MF A01 T.M. An integrated digital flight control system was developed. The primary objective of the program was. both to improve the N82-11084*# National Aeronautics and Space Administration. manual control of the aircraft assisted by control systems, and Langley Research Center. Hampton. Va. to develop new control and display systems. In addition, MANAGEMENT OF REDUNDANCY IN FLIGHT CONTROL automation is to be provided for loner flight phases which are SYSTEMS USING OPTIMAL DECISION THEORY to be optimized with respect to fuel consumption, flight time, or In AGARD Theory and Appl. of Optimal Control in Aerospace

39 N82-11087

Systems Jul. 1981 12 p refs N82-11224*# Lockheed-California Co.. Burbank. EXPERIMENTAL STUDY OF FUEL HEATING AT LOW Avail: NTIS HC A13/MF A01 CSCL QIC TEMPERATURES IN A WING TANK MODEL, VOLUME 1 The problem of using redundancy that exists between Final Report dissimilar systems in aircraft flight control is addressed. That is. Francis J. Stockemer Aug. 1981 75 p refs using the redundancy that exists between a rate gyro and an (Contract NAS3-21977) accelerometer—devices that have dissimilar outputs which are (NASA-CR-165391: LR-29935-Vol-1) Avail: NTIS related only through the dynamics of the aircraft motion. HC A04/MF A01 CSCL 21D Management of this type of redundancy requires advanced logic Scale model fuel heating systems for use with aviation so that the system can monitor failure status and can reconfigure hydrocarbon fuel at low temperatures were investigated. The itself in the event of one or more failures. An optimal decision effectiveness of the heating systems in providing flowability and theory was tutorially developed for the management of sensor pumpability at extreme low temperature when some freezing of redundancy and the theory is applied to two aircraft examples. the fuel would otherwise occur is evaluated. The test tank The first example is the space shuttle and the second is a simulated a section of an outer wing tank, and was chilled on highly maneuvering high performance aircraft--the F8-C. The the upper and lower surfaces. Turbine engine lubricating oil was examples illustrate the redundancy management design process heated, and recirculating fuel transferred the heat. Fuels included: and the performance of the algorithms presented in failure a commercial Jet A: an intermediate freeze point distillate: a detection and control law reconfiguration. T.M. higher freeze point distillate blended according to Experimental Referee Broadened Specification guidelines: and a higher freeze point paraffinic distillate used in a preceding investigation. Each fuel was chilled to selected temperature to evaluate unpumpable N82-11087$ Systems Control. Inc., Palo Alto. Calif. solid formation (holdup). Tests simulating extreme cold weather DEVELOPMENT OF MULTIVARIABLE CONTROLLERS FOR flight, without heating, provided baseline fuel holdup data. Heating AIRCRAFT TURBINE ENGINES and recirculating fuel increased bulk temperature significantly: it Ronald L. DeHoff. Stephen M. Rock, and Muhammed M. Akhter had a relativley small effect on temperature near the bottom of In AGARD Theory and Appl. of Optimal Control in Aerospace the tank. Methods which increased penetration of heated fuel Systems Jul. 1981 12 p refs into the lower boundary layer improved the capability for reducing holdup. S.L Avail: NTIS HC A13/MF A01 A model reference structure is discussed which is shown to be a flexible framework within which digital control programs of N82-11228# Air Force Wright Aeronautical Labs.. Wright- a wide variety of function and complexity can be formulated. Patterson AFB, Ohio. Fuels and Lubrication Div. The development of the plant reference model is discussed and JET FUEL LOCKS TO SHALE OIL: THE 1980 TECHNOLOGY trade-offs between accuracy and complexity presented. The REVIEW techniques used to produce optimized, feed-forward state, control Herbert R. Lander May 1981 156 p refs Proceedings of and output trajectories are presented. The well-known methods Conf. held at Cincmnatti, 19-20 Nov. 1980 of regulator synthesis using quadratic performance functions are (AF Proj. 2480) briefly reviewed and the results of several successful applications (AD-A104414: AFWAL-TR-81-2063) Avail: NTIS of this methodology are summarized. T.M. HC A08/MF A01 CSCL 11/4 The progress of several Air Force shale oil related programs is reported. Three shale oil processing studies evaluating the yield, cost, and quality of JP-4 and JP-8 turbine fuel produced N82-11089 Royal Aircraft Establishment, Bedford (England). from whole crude shale oil are discussed Details of a fourth Library. program that produced 11.300 gallons of specification JP-4 from ADAPTATION OF A TURBINE TEST FACILITY TO HIGH- Geokinetics shale oil are reported. Some of this jet fuel was TEMPERATURE RESEARCH tested in Air Force Fuel Mainburner/Turbine Effects Programs J. Francois. Y. LeBot, J. Michard. and P. Deguest Dec. 1980 and was shown to behave very similar to petroleum derived 30 p refs Transl. into ENGLISH from AGARD Conf. Proc. JP-4. An additional study concentrated on developing hydretreat- No. 229. Ankara, Sept. ing catalysts that would more efficiently convert shale oil into (RAE-Lib-Trans-2064: BR78650) Copyright. Avail: Issuing aviation turbine fuel. Author (GRA) Activity A facility for research on a high temperature (1800 K) and high pressure (4.5 bar) turbine stage is described. The turbine N82-11230*# Pratt and Whitney Aircraft Group. East Hartford. operates in a realistic engine environment and is comprehensively Conn. Commercial Products Div. instrumented to permit wide variation of mainstream and coolant AN ASSESSMENT OF THE USE OF ANTIMISTING FUEL flow parameters. The development of robust probes for the IN TURBOFAN ENGINES Final Report. Sep. 1979 - Nov. measurement of turbulence and temperature fluctuations and 1980 A. Fiorentino. R. DeSaro, and T. Franz Jun. 1981 53 p refs optical pyrometry techniques is described. Results of studies of (Contract NAS3-22045) nozzle guide vane heat transfer coefficients, metal temperatures (NASA-CR-165258: AD-A104673: PWA-5697-29: and film cooling efficiency are presented together with rotor FAA-CT-81-58) Avail: NTIS HC A04/MF A01 CSCL 21/4 blade surface temperature distributions. The MINOS rig confirmed An evaluation was made on the effects of using antimisting1 the validity of turbine design prediction methods by providing kerosene (AMK) on the performane of the components from the performance data to correlate theory, scale model testing and fuel system and the combustor of a current in-service JT8D gas turbine engine testing. T.M. aircraft engine. The objectives were to identify problems associated with using antimisting kerosene and to determine the extent of shearing or degradation required to allow the^engine components N82-11212# Naval Surface Weapons Center. White Oak. Md. to achieve satisfactory operation The program consisted of a Research and Technology Dept. literature survey and a test program which evaluated the antimisting kerosene fuel in laboratory and bench component POLYURETHANE FOAMS FOR AIRCRAFT SHOCK testing, and assessed the performance of the combustor in a MOUNTS. 3: VIBRATION DAMPING BY POLYETHER high pressure facility and in an atitude relight/cold ignition facility. FOAMS Progress Report, Sep. 1979 - Jun. 1980 James V. Duffy Jul. 1981 38 p refs Performance of the fuel pump and control system was evalu- ated in an open loop simulation. Thus far. results of the program (AD-A104496: NSWC/TR-80-343) Avail: NTIS HC A03/MF A01 CSCL 1 1/9 would not preclude the use of antimisting kerosene in a jet engine application. GRA The objective of this program was to develop flexible foam systems which would meet the specifications outlined in MIL-F-81334BIAS). The vibration damping and mechanical N82-11232# Naval Postgraduate School. Monterey. Calif. Dept. properties of a series of foams based on mixtures of poly of Aeronautics. (oxytetrarhethylene) glycol and poly(oxypropylene) polyol were AN INVESTIGATION OF THE COMBUSTION PROCESS IN determined. The effect of polyol ratio, foam density, surfactant SOLID FUEL RAMJETS M.S. Thesis type and unit loading on vibration output transmissibility for these William Vernon Goodwin Jun. 1981 58 p refs systems is reported. Author (GRA) (AD-A104603) Avail: NTIS HC A04/MF A01 CSCL 21/4

40 N82-11514

An experimental investigation was conducted into four areas crossflow disturbances are presented for 10 typical velocity profiles of the solid fuel ramjet .combustion process: (1) the effects of on a swept laminar flow control wing. The critical crossflow near wall turbulent mixing and equivalence ratio on combustion Reynolds number is shown to be a function of a boundary layer efficiency, (2) the effects of bypass air on combustion efficiency. shape factor. Amplification rates for crosslow disturbaces are (3) the combustion process in a cylindrically perforated fuel grain shown to be proportional to the maximum crossflow velocity. A with a twin side-dump/dome configuration, and (4) the comparison computer stability program called MARIA, employing the of experimental radial temperature profiles to computer generated amplification rate data for the 10 crossflow velocity profiles, is radial profiles. Polymethylmethacrylate fuel grains were burned constructed. This code is shown to adequately approximate more in a ramjet motor and a thrust stand. Combustion efficiencies involved computer stability codes using less than two percent were determined and compared for different configurations. It as much computer time while retaining the essential physical was found to be insensitive to variations in the mixture ratio disturbance growth model. Author and to near-wall mixing. Bypass air was found to adversely affect the combustion efficiency both in stable and unstable N82-11491*# National Aeronautics and Space Administration. combustion environments. The twin side-dump/dome configura- Lewis Research Center, Cleveland. Ohio. tion was unable to sustain combustion for all conditions INTEGRATED ANALYSIS OF ENGINE investigated. Theoretical radial temperature profiles were found Christos C. Chamis 1981 24 p refs Presented at the Ann. to have larger near wall gradients than were measured experiment- Meeting of the ASME. Washington. D.C.. 16-21 Nov. 1981 ally. Author (GRA) (NASA-TM-82713: E-9951 Avail: NTIS HC A02/MF A01 CSCL 20K N82-11313# New Mexico Univ., Albuquerque. Engineering The need for light, durable, fuel efficient, cost effective Research Inst. aircraft requires the development of engine structures which are DESIGN OF AIRPORT PAVEMENTS FOR EXPANSIVE SOILS flexible, made from advaced materials (including composites), Final Report resist higher temperatures, maintain tighter clearances and have R. Gordon McKeen Jan. 1981 198 p refs lower maintenance costs. The formal quantification of any or (Contract F29601-76-C-0051) several of these requires integrated computer programs (multi- (AD-A104660; NMERI-AP-37: FAA-RD-81-25) Avail: NTIS level and/or interdisciplinary analysis programs interconnected) HC A09/MF A01 CSCL 08/13 for engine structural analysis/design. Several integrated analysis Expansive soil subgrades exhibit volume changes with computer prorams are under development at Lewis Reseach variation in moisture condition. These changes result in differential Center. These programs include: (1) COBSTRAN-Composite Blade movement of airport pavements resting on these soils. Special Structural Analysis, (2) CODSTRAN-Composite Durability design procedures must be used to account for the. expansive Structural Analysis. 13) CISTRAN-Composite Impact Structural soil activity during equilibration. In addition, special precautions Analysis. (4) STAEB L-StruTailoring of Engine Blades, and are required to protect the subgrade from moisture variation (5) ESMOSS-Engine Structures Modeling Software System. Three with climate. Measurement of soil suction is a key step in other related programs, developed under Lewis sponsorship, are quantifying moisture-induced soil behavior. Procedures are outlined described. Author for suction characterization of the soil and for estimating the in situ differential movement likely to occur under the pavement. N82-11498# Army Engineer Waterways Experiment Station. Once the wavelength and amplitude characteristics of the Vicksburg. Miss. Geotechnical Lab. differential movement are obtained, design calculations to select STRUCTURAL ANALYSIS COMPUTER PROGRAMS FOR the thickness and materials for the pavement may proceed.GRA RIGID MULTICOMPONENT PAVEMENT STRUCTURES WITH DISCONTINUITIES, WESLIQID AND WESLAYER. N82-11339*# National Aeronautics and Space Administration. REPORT 1: PROGRAM DEVELOPMENT AND NUMERICAL Langley Research Center, Hampton. Va. PRESENTATIONS Technical Report. 1 Oct. 1978 - 30 Sep. GENERAL AVIATION AIRCRAFT ANTENNAS FOR THE 1979 GLOBAL POSITIONING SYSTEM Yu T. Chou May 1981 150 p refs Melvin C. Gilreath and J. S. Chatterjee Oct. 1981 37 p refs (DA Proj. 4A7-62719-AT-40) (NASA-TM-83212) Avail: NTIS HC A03/MF A01 CSCL (AD-A104545: WES/TR/GL-81-6-1) Avail: NTIS HC A07/MF A01 CSCL 13/13 17G Several antenna designs that utilize the NAVSTAR Global This study was conducted to develop finite element computer Positioning System in a low-cost system for general aviation programs to calculate stresses and deflections in rigid pavements aircraft were evaluated. Experimental investigations were made with cracks and joints subjected to loads and temperature warping, of crossed-dipoles. various types of crossed-slots, and microstrip as well as in the supporting subgrade soil. The joints are connected antennas with modifications to improve their coverage. Principal by dowel bars or other load transfer devices. The slabs can plane radiation patterns for several of these antennas were have full or partial loss of subgrade support over designed regions measured on a one-seventh scale model of a Gates Lear Jet. of the slabs. Multiple-wheel loads can be handled and the number R.J.F. of wheels is not limited. Two programs were developed, one called WESLIQID and the other WESLAYER. The former is for pavements on liquid foundations and the latter is for linear layered N82-11354# Edgerton. Germeshausen and Grier. Inc., Albuquer- elastic solids. Variable slab thicknesses and moduli of subgrade que. N. Mex. reaction are incorporated in the WESLIQID program, and any SYSTEM SAFETY PROGRAM PLAN Final Report. number of slabs arrayed in an arbitrary pattern can be handled. 31 Mar. - 8 Aug. 180 Because of larger computer storage requirement and computa- A. J. Bonham 8 Aug. 1980 79 p refs tional complexity, the WESLAYER program is limited to two (Contract DNA001-80-C-0177) slabs. GRA (AD-A104557; AG-1446: DNA-5467F) Avail: NTIS HC A05/MF A01 CSCL 12/12 This document. System Safety Program Plan, is the imple- N82-11614*# Jet Propulsion Lab.. California Inst. of Tech.. menting document covering the safety aspects of performing an Pasadena. EMP Test on the A7E aircraft in the HPO (Horizontally Polarized RADAR MAPPING. ARCHAEOLOGY. AND ANCIENT LAND Dipole). VPD (Vertically Polarized Dipole). and NWEF hangar USE IN THE MAYA LOWLANDS facilities at Kirtland AFB, New Mexico. GRA R. E. W. Adams (Cambridge Univ.). W. E. Brown, Jr.. and T. Patrick Culbert (Arizona Univ.) 31 Mar. 1981 27 p refs (Contract NAS7-100) N82-11391*# National Aeronautics and Space Administration. (NASA-CR-164931) Avail: NTIS HC A03/MF A01 CSCL Langley Research Center. Hampton. Va. 088 AMPLIFIED CROSSFLOW DISTURBANCES IN THE Data from the use of synthetic aperture radar in aerial survey LAMINAR BOUNDARY LAYER ON SWEPT WINGS WITH of the southern Maya lowlands suggest the presence of very SUCTION large areas drained by ancient canals for the purpose of intensive J. Ray Dagenhart Nov. 1981 90 p refs cultivation. Preliminary ground checks in several very limited areas (NASA-TP-1902; L-14423) Avail: NTIS HC A05/MF A01 confirm the existence of canals and raised fields. Excavations CSCL 20D and ground surveys by several scholars provide valuable Solution charts of the Orr-Sommerfeld equation for stationary comparative information. Taken together, the new data suggest

41 N82-11636

that Late Classic period Maya civilization was firmly grounded Avail: NTIS HCA05/MFA01 CSCL 20/4 in large-scale and intensive cultivation of swampy zones. A.R.H. The forms of the lift distribution function for wings with control surfaces in steady subsonic flow are analyzed. Methods for treating kernel singularities of linear integral equations and N82-11636*# National Aeronautics and Space Administration. singularities of the lift distribution function are discussed and Washington. D. C. the numerical solution to the integral equation is given. These EFFECTS OF AIRCRAFT NOISE ON THE EQUILIBRIUM OF methods may be used to calculate the lift distribution of the AIRPORT RESIDENTS: TESTING AND UTILIZATION OF wing by itself or of the wing with partial or full control surfaces A NEW METHODOLOGY on both the leading and trailing edges. The numerical values Jacques Francois Sep. 1981 34 p Transl. into ENGLISH of agree well with experimental data and have the same accuracy "Repercussion du Bruit des Avions sur I'Equilibre des Riverains as those given by other theories. As compared with the vortex des Aereports: Test et Mise au Point d'une Methodologie lattice method, the computational storage requirement for this Nouvelle" Paris, Aug. 1977 p 1-134 Transl. was announced method is smaller and the computational time is less. The as N81-27692 Transl. Scientific Translation Service. Santa numerical computation may be carried out on smaller comput- Barbara. Calif. Original doc. prep, by IFOP/ETMAR ers. (Contract NASw-3542) (NASA-TM-76628) Avail: NTIS HC A03/MF A01 CSCL 13B The focus of the investigation is centered around two main themes: an analysis of the effects of aircraft noise on the psychological and physiological equilibrium of airport residents: ana an analysis of the sources of variability of sensitivity to noise. The methodology used is presented. Nine statistical tables are included, along with a set of conclusions T.M

N82-11859*# United Technologies Research Center. East Hartford. Conn. HELICOPTER ROTOR TRAILING EDGE NOISE Final Report Robert H. Schlinker and Roy K. Amier Washington NASA Nov. 1981 150 p refs (Contract NAS1-15730) (NASA-CR-3470) Avail: NTIS HC A07/MF A01 CSCL 20A A two dimensional section of a helicopter main rotor blade was tested in an acoustic wind tunnel at close to full-scale Reynolds numbers to obtain boundary layer data and acoustic data for use in developing an acoustic scaling law and testing a first principles trailing edge noise theory. Results were extended to the rotating frame coordinate system to develop a helicopter rotor trailing edge noise prediction. Comparisons of the calculated noise levels with helicopter flyover spectra demonstrate that trailing edge noise contributes significantly to the total helicopter noise spectrum at high frequencies. This noise mechanism is expected to control the minimum rotor noise. In the case of noise radiation from a local blade segment, the acoustic directivity pattern is predicted by the first principles trailing edge noise theory. Acoustic spectra are predicted by a scaling law which includes Mach number, boundary layer thickness and observer position. Spectrum shape and sound pressure level are also predicted by the first principles theory but the analysis does not predict the Strouhal value identifying the spectrum peak. A.R.H.

N82-11860*# National Aeronautics and Space Administration. Langley Research Center. Hampton. Va. SEL AND EPNL NOISE DURATION COEFFICIENTS FOR THE 747 AND T-38 AIRCRAFT William L Wiltshire. Jr. Sep. 1981 12.p refs (NASA-TM-83214) Avail: NTIS HC A02/MF A01 CSCL 20A Duration coefficient were calculated for Boeing 747 and T-38 airplanes for sound exposure level (SEL) and effective perceived noise level (EPNL) scales. The measured SEL duration coefficients were 8.4 for the Boeing 747 and 5.5 for the T-38 result was in good agreement with a previous result for a similar F-5 airplane. In EPNL. the duration coefficients were 7.2 for the Boeing 747 and 5.7 for the T-38. The difference in the results between the two airplanes is believed to be due to their different engine noise source spectra. The difference in the Boeing 747 results in the two different metric was due to the different frequency weighting of A-weighted sound pressure level, used in SEL. and tone-corrected perceived noise level, used in EPNL. when applied to the 747 spectra. B.W.

N82-12023# Air Force Systems Command. Wright-Patterson AFB, Ohio. Foreign Technology Div. ON THE KERNEL FUNCTION COLLOCATION METHOD IN STEADY SUBSONIC FLOW FOR WING WITH CONTROL SURFACES Chen Jing Song In its Acta Mech. Sinica (Selected Articles) (FTD-ID(RS)T-0705-81) 15 Sep. 1981 p 35-50 refs Transl. into ENGLISH from Acta Mech. Sinica (China), no. 2. 1979

42 SUBJECT INDEX AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 145) FEBRUARY 1982

Typical Subject Index Listing

[SUBJECT HEADING| ACOUSTIC PBOPAGATIOB SEL and EPHL noise duration coefficients for the ABTIICIIG ADDITIVES 747 and T-38 aircraft -Icing tunnel tests of a composite porous leading [HASA-TH-83214] N82-11860 edge for use vith a liquid anti-ice system ACOUSTIC PBOPEBTIES -Lewis icing research tunnel Evaluation of the acoustic measurement capability [HASi-CB-164966] H82-11052 of the NASA Langley V/STOL wind tunnel open test section with acoustically absorbent ceiling and floor treatments [BASA-CB-165796] 882-10059 ACTIVE COHTBOL Active control elements on the transonic wing of the Airbus A-300 (ACTTA A) . Airbus A-300 with The title is used to provide a description of the subject matter. When the reduced longitudinal stability (ACTTA-C) title is insufficiently descriptive of the document content, a title extension advanced control transonic transport aircraft is added, separated from the title by hyphens. The NASA or AIAA accession (ACCTA); design considerations number is included in each entry to assist the user in locating the abstract B82-10044 in the abstract section of this supplement. If applicable, a report number A method for determination of the aeroelastic is also included as an aid in identifying the document. behavior of aircraft with active control systems [DFVLB-FB-81-05] 1182-10047 ACTOATOBS Control of electromechanical actuator elements for flight vehicles Bussian book A82-12170 »-7 AIHCBAFT Aircraft digital input controlled hydraulic A comparison of theoretical and experimental actuation and control system pressure distributions for two advanced fighter [AD-A104263] H82-11072 vings ADAPTIVE COHIBOL [HASA-TH-81331] H82-11054 Control laws for adaptive wind tunnels System safety progran plan electromagnetic A82-10985 pulse testing of the A-7E aircraft Practical design and realization of a digital [AD-A104557J H82-11354 adaptive flight control system A-300 AIBCBAFT H82-11079 Active control elements on the transonic sing of ADDITIVES the Airbus A-300 {ACTTA A). Airbus A-300 with Bheological behavior of'progressively reduced longitudinal stability (ACTTA-C) shear-thickening solutions aircraft fuel advanced control transonic transport aircraft polymer additives for fire protection in (ACCTA); design considerations snzvivable crashes H82-10044 A82-11177 ABSOBBE8S (MATERIALS) A protective additive for jet fuels Evaluation of the acoustic measurement capability A82-12022 of the BASA Lang ley VSTOL wind tunnel open test ABBIAL PBOT06BAPBI section vith acoustically absorbent ceiling and Three navigation systems and their costs of floor treataents acquiring remote sensing data [HASA-CB-165796] H82-10059 A82-10049 »C GBBEBATOBS AEBOiCODSIlCS 60 KVA ADP permanent magnet VSCF starter generator Helicopter rotor trailing edge noise system - Generator system performance [AIAA PAPEB 81-2001] A82-10455 characteristics Design predictions for noise control in the A82-11721 cryogenic national Transonic Facility ACCIDBII PBBVEiTIOH A82-12025 A proposed flight safety progran for the Korean Aeroacoustic theory for noncompact wing-gust Air Force interaction [AD-A102373] H82-10023 [FDBL-81-7] H82-11071 Lightning effects on aircraft and composites. AEBODTHAHIC BALAiCB Literature study on lightning strikes and Development of new lifting parachute designs with protection advanced composite materials increased trim angle £POA-C-20388-F9] H82-10024 [AI4A PAPEB 81-1921] A82-10407 ACCOaOLATOHS AEBODII1HIC BBAKES Low maintenance hydraulic accumulator Aeroballistic characteristics of sonobnoy [AD-A103947] B82-10034 parachute decelerators limited to a length of ACOUSTIC BH1SSIOB three feet Acoustic emission - An emerging technology for [AIAA PAPEB 81-1950] A82-10425 assessing fatigue damage in aircraft structure AEBODIHAHIC CHABACtBBIStlCS A82-11149 Experimental study of subsonic and transonic flows ACODSTIC FATIGOB past a wing Besponse of nonlinear aircraft structural panels A82-10363 to high intensity noise Aerodynamics and performance of cruciform A82-12041 parachute canopies iCOOSTIC HBASOBBHBHS [AIAA PAPEB 81-1919] A82-10405 Effects of vane/blade ratio and spacing on fan noise Development of new lifting parachute designs with [AIA1 PA PEE 81-2033] A82-10457 increased trim angle [AIAA PAPEB 81-1921] A82-10407

A-1 ABBODtBAHIC COEFFICIENTS SUBJECT IBDBX

Propfan installation aerodynamics of a The CIVIC - A concept in vortex induced supercritical svept wing transport configuration combustion. II [111* PAPBB 81-1563] A82-10466 CASHE PAPEB 81-01-12) A82-11997 Calculation of aerodynamic characteristics of jet Aerodynamic calculations and design of subcritical flapped airplane aerofoils A82-11459 H82-10983 Comparative study of flare control laws ABBOEIASTICITI [BAS4-CB-164903] N82-10032 A method for determination of the aeroelastic Effects of vortex flaps on the low-speed behavior of aircraft with active control systems aerodynamic characteristics of an arrow wing [DFVLB-FB-81-05] H82-10047 [NASA-TP-1914] H82-11013 AEBOBAOTICAL BBGIBEBBIB6 & numerical three-dimensional turbulent simulation HASA Authorization, 1982: Index of a subsonic VSTOL jet in a cross-flow using a [GPO-84-713] B82-10959 finite element algorithm The automatic matrix force method and techniques [AD-A104514] H82-11055 for handling more complex computations with ABRODYHAHIC COEFFICIBBIS given computer capacity The effects of flexibility on the steady-state B82-10994 performance of small ribbon parachute models AEBOSOLS [AIAA PAPER 81-1923] A82-10408 Determination of vertical profiles of aerosol size Determination of airplane model structure from spectra from aircraft radiative flux flight data by using modified stepvise regression measurements. II - The effect of particle [NASA-TP-1916] B82-10041 nonsphericity Hind-tunnel results for a modified A82-12149 17-percent-thick low-speed airfoil section AEBOSPACE EBGIBBEBISG [SAS4-TP-1919] H82-11033 Emerging technologies in aerospace structures, AEBODIBAHIC COHPI6DBATIOBS design, structural dynamics and materials; The principles and methods for shaping the wing Proceedings of the Aerospace Conference, San toot regions of a wing-body combination at Francisco, CA, August 13-15, 1980 transonic and lower supersonic speeds A82-12026 N82-11016 Powder metallurgy superalloys - Aerospace Aecoacoustic theory for noncompact wing-gust materials for the 1980's; Proceedings of the interaction Conference, Zurich, Switzerland, November 18-20, [FDBL-81-7] H82-11071 1980. Volume 1 AEBODIBAHIC OBAG A82-12495 Seductions in parachute drag due to forebody wake NASA Authorization, 1982: Index effects [GPO-84-713] H82-10959 [AIAA PAPEB 81-1939] 482-10417 Theory and applications of optimal control in Aircraft excrescence drag aerospace systems [4GABD-AG-264] B82-10020 [AGABD-AG-251] H82-11073 AEBODWAHIC FOBCBS An overview of optimal control in aerospace systems Increasing the lift:drag ratio of a flat delta wing B82-11074 482-11899 AEBOSPACE IBDOSIBI An influence coefficient method for the Kevlar composites; Proceedings of the Symposium, application of the modal technique to wing El Segundo, CA, December 2, 1980 flutter suppression of the DAST ABi-1 wing A82-12646 tNASA-CB-165772) H82-11070 AEBOSPACE HEDICIBB AEBODIBAHIC HEATIBG Airport and Airway Improvement Act of 1981, part 1 In-situ calibration of flight heat transfer [GPO-76-241-PT-1] H82-10062 instrumentation AEBOSPACE SISTEBS [ASHE PAPEB 81-EHAS-13] A82-10901 Theory and applications of optimal control in ABBODtHAHIC IHTEBFEBEBCB aerospace systems Effects of vane/blade ratio and spacing on fan noise [AGABD-AG-251] H82-11073 [AI4A PAPEB 81-2033] A82-10457 An overview of optimal control in aerospace systems ABBODK1AHIC LOADS H82-11074 Hoalinear prediction of subsonic aerodynamic loads ABBOSPACE TECBBOLOGX TBAHSFBB on wings and bodies at high angles of attack Considerations and applications for the use of A82-11359 flnidics in aerospace controls AERODfHAHIC HOISB 482-12087 Helicopter rotor trailing edge noise AEBOTHEBHODIBA8ICS [AIAA PAPEB 81-2001] A82-10455 Design analysis of high temperature transparent Aircraft wing trailing-edge noise windshields for high performance aircraft [HASA-CB-16<»952] H82-11039 [ASHE PAPEB 81-EHAS-5] A82-10893 AERODfHAHIC STABILITY Quantification of the thermal environment for Experimental determination of parachute apparent externally carried aircraft stores and ordnance Bass and its significance in predicting dynaiic A82-12100 stability AIB BAG BBSIBAIBT DEVICES [AIAA PAPEB 81-1920] A82-10406 Air bag impact attenuation system for the AQH-34V Numerical treatment of helicopter rotor stability remote piloted vehicle problems [AIAA PAPEB 81-1917] A82-10403 A82-12045 AIB BBE4THIHG EH6IHES An investigation of a stoppable helicopter rotor Air-breathing engine test facilities register with circulation control aaes 40 by 80 foot [AGABD-AG-269] H82-10063 wind tunnel AIB COBDITIOHIBG EQDIPHBHT [HASA-IH-81218] 1182-10030 Towards minimum power for environmental control in AERODYIAIIIC STALLIBG transport aircraft A aicroprocessor-based data acquisition system for [ASHE PAPBB 81-BHAS-4] A82-10892 stall/spin research AIB COOIIHG [AIAA 81-2177] A82-10126 Air-film cooling returns to ramjets Spin recovery training licensing requirement [ASHE PAPEB 81-BBAS-8] A82-10896 [SPO-66-020] H82-10022 Thermal and flow analysis of a convection, An experimental investigation of the rotating air-cooled ceramic coated porous metal concept stall, surge and wake behind the rotor for a for turbine vanes single stage axial compressor [ASHE PAPEB 81-HT-48] A82-10952 H82-11008 Application of numerical modeling to gas turbine ABBODIHAHICS combustor development problems Control laws for adaptive wind tunnels A82-12118 A82-10985

A-2 SUBJECT IBDBX AIBCBAFT COHSTBOCIIOH HATEBIALS

AIR FLO! The Space Shuttle vehicle checkout involving Application of numerical modeling to gas turbine flight avionics software conbustor development problems [AIAA 81-2111] A82-10100 A82-12118 Bridging the gap from aircraft to space computers AIB ISTAKES [AIAA 81-2142] A82-10101 Lou speed testing of the inlets designed for a Airborne associative processor /ASPBO/ for tamdea-fan V/STOL nacelle conducted in the early warning radar surveillance, command, and Lewis 10 by 10 foot wind tunnel control applications [HASA-TH-82728] H82-11042 [AIAA 81-2145] A82-10104 AIB IAVIGAXIOB Controlling the software/hardware interface for Three navigation systems and their costs of the validation of avionics systems in flight acquiring remote sensing data control systems A82-10049 [AIAA 81-2159] A82-10116 navigation task partitioning in A microprocessor-based data acquisition system for distributed-processing avionics systens stall/spin research A82-10646 [AIAA 81-2177] A82-10126 Discrete address beacon, navigation and landing Performance analysis of enroute air traffic system control computers in the National Airspace System A82-10650 [AIAA 81-2203] A82-10140 Fast and accurate gyrocompass using strapdoun Interoperability testing of decentralized command, tuned rotor gyros as a solution to combat control, communications and intelligence /C3I/ helicopters navigation problems systems A82-11927 [AIAA 81-2205] A82-10143 National Aerospace fleeting, Trevose, FA, April Navigation task partitioning in 8-10, 1981, Proceedings distributed-processing avionics systems A82-12626 A82-10646 Satellite geometry considerations for low cost GPS Hemory requirements for future navigation systems user equipnent A82-12637 A82-12630 Bing Laser Gyro navigator /BLGN/ flight test results A solution to the static geometry problem for A82-12644 JTIDS relative navigation AIBCBAFT ACCIDEH IHVESTIGATIOS A82-12634 Downbnrsts and microbursts - An aviation hazard Hemory requirements for future navigation systems downdrafts beneath thunderstorms A82-12637 A82-10214 A navigation systems planning model Airborne weather radar and severe weather 482-12610 penetration The integrated inertial sensor assembly /USA/ - A A82-10219 redundant strapdown system for advanced aircraft A note on fatal aircraft accidents involving metal navigation and flight control functions fatigue A82-12642 A82-11400 Integrated satellite navigation and strapdown AIBCBAFT ACCIDEHTS attitude and heading reference systems for civil Relationships between naval aviation safety and air carriers pilot flight experience 482-12643 A82-11031 Bing Laser Gyro Navigator /BLGH/ flight test results SABSAT applications A82-12644 A82-12698 AIB TBAFFIC COHIBOL AIBCBAFT 1BTEBB1S Performance analysis of enroute air traffic General aviation aircraft antennas for the global control computers in the Rational Airspace System positioning system [AIAA 81-2203] A82-10140 [HASA-TH-83212] N82-11339 FAA developing new collision avoidance, data AIBCBAFT COHBDHICATIOB acquisition and transmission systems A mathematical model of an over-sea airborne DHF 482-10396 radio link Discrete address beacon, navigation and landing A82-11406 system AIBCBAFT COHPABTHEHTS A82-10650 Experimental modal analysis of the fuselage panels Airport and Airway Improvement Act of 1981, part 1 of an Aero Commander aircraft [GPO-76-241-PT-1] H82-10062 [HASA-CB-165750] N82-10028 FAA misses opportunities to discontinue or reduce AIBCBAFT COBFIGOBATIOBS operating hours of some airport traffic control Analysis of augmented aircraft flying qualities towers through application of the Seal-Smith criterion [PB81-224214] H82-11049 [AIAA PAPEB 81-1776] - A82-10462 AIB TBABSPOBTATIOI V/STOL aircraft and fluid dynamics Cost reduction in air transportation energy [HASA-TH-81328] H82-10029 conservation AIBCBAFT COBSTBOCTIOB HMBBIALS [SHIAS-811-150-101] H82-10025 The application of improved aluminium alloys and AIBBOBHE EflOIPBBHI steels in aircraft structures Instrumented aircraft verification of clear-air A82-10305 radar detection of low-level wind shear Sophisticated aircraft structure developments - A82-10221 Combat aeroplanes A mathematical nodel of an over-sea airborne DBF A82-10309 radio link On the use of carbon composites in slat and A82-11406 stabilizer construction High voltage surge and partial discharge test to A82-11468 evaluate aerospace equipment parts Powder metallurgy snperalloys - Aerospace A82-11740 materials for the 1980's; Proceedings of the AIBBOHIE SOBVEILLAICE BADAB Conference, Zurich, Switzerland, November 18-20, Airborne weather radar and severe weather 1980. Volume 1 penetration A82-12495 A82-10219 Kevlar composites; Proceedings of the Symposium, AIBBOBBB/SPACBBOBBB COHC01BBS El Segundo, CA. December 2, 1980 KC-135 Avionics Modernization Hot Bench A82-12646 [AIAA 81-2105] A82-10081 Seven years experience with Kevlar-49 in the BiBAT onboard flight computer system architecture Lockheed L-1011 Tristar and qualification A82-12647 [AIAA 81-2107] A82-10082 Synchronous fault-tolerant flight control systems [AIAA 81-2109] A82-10083

A-3 AIHCBAPT COHIBOL SDBJECT IHDBX

AIHCBAFT COHTB01 Solution to the hidden-line problem Controlling the software/hardware interface for A82-12803 the validation of avionics systems in flight V/STOL aircraft and fluid dynamics control systems [HASA-TH-81328] H82-10029 [AIAA 81-2159] 482-10116 Quiet short-haul research aircraft familiarization Use of Space Shuttle technology in conventional document, revision 1 aircraft [HASA-3H-81298] N82-10031 [AIAA 81-2176] A82-10125 Active control elements on the transonic wing of Analysis of augmented aircraft flying qualities the Airbus A-300 (ACTTA A). Airbus A-300 with through application of the Meal-Smith criterion reduced longitudinal stability (ACTTA-C) [AIAA PAPEB 81-1776] A82-10462 advanced control transonic transport aircraft Improving the HLS through enhanced cockpit displays (ACCTA); design considerations 482-106<49 H82-10044 Procedures and analysis techniques for determining Acta mechanica sinica static air minimum control speeds [AD-A105184] N82-11014 A82-12564 The principles and methods for shaping the wing Simulation study of a hybrid strapdovn attitude root regions of a wing-body combination at and heading reference system transonic and lover supersonic speeds A82-12641 H82-11016 Theoretical investigation of the influence of Hew estimation method for flutter or divergence spoiler dynamics on the handling qualities of an boundary from random responses at subcritical aircraft with direct lift control speeds [ESA-TT-681] N82-10036 [HAI-TH-667T] B82-1103U Estimation of airplane stability and control Design techniques for mutlivariable flight control derivatives from large amplitude longitudinal systems maneuvers H82-11078 [HASA-TH-83185] N82-10042 AIBCBAFT EHGIHBS Control law design for transport aircraft flight Design considerations for duty cycle, life and tasks reliability of small limited life engines H82-11080 [AIAA PAPEB 81-1402] A82-10465 AIBCBiFT DESIGB lir-film cooling returns to ramjets Integration of computer graphics design vith [ASME PAPEB 81-EHAS-8] A82-10896 analytical models for aircraft design One reason for the onset of high-frequency [AIAA 81-2134] A82-10096 self-excited oscillations in combustion Use of Space Shuttle technology in conventional chambers of aircraft engines aircraft A82-11448 [AIAA 81-2176] A82-10125 Basic problem of aircraft gasturbine engine Design aspects of non rigid airship envelopes analytic design. II A82-10306 A82-11463 Some possibilities for composite light aircraft Coupled fluid/structure response predictions for construction soft body impact of airfoil configurations A82-10307 ice and bird impact on aircraft engines Light aircraft structural design in non-metallics A82-12039 - Use of composite honeycomb for light aircraft History of flight testing the L-1011 Tristar jet A82-10308 transport. II - Testing highlights since initial Analytical determination of undercarriage certification of the L-1011-1 retraction kinematics A82-12049 A82-10364 Considerations and applications for the use of The balloon and the airship technological heritage fluidics in aerospace controls [AIAA PAPEB 81-1912] A82-10401 A82-12087 Air bag impact attenuation system for the AQH-347 The enhancement of heat exchange in channels /2nd remote piloted vehicle revised and enlarged edition/ • Bnssian book [AIAA PAPEB 81-1917] A82-10403 A82-12222 Analysis of augmented aircraft flying qualities Validation studies of turbulence and combustion through application of the Deal-Smith criterion models for aircraft gas turbine combnstors [AIAA PAPEB 81-1776] A82-10462 A82-12267 How large should a commuter transport be Commercial ESS considerations for saall gas [AIAA PAPEB 81-1732] A82-10463 turbine engines automated engine monitoring Optimization of the principal design parameters of systems a passenger aircraft A82-124H9 A82-10816 Further application and development of an engine Towards minimum power for environmental control in usage/life monitoring system for military services transport aircraft A82-12450 [ASHE PAPEB 81-EHAS-4] A82-10892 Superclean snperalloy powders by the rotating Design analysis of high temperature transparent electrode process windshields for high performance aircraft A82-12496 (ASBE PAPEB 81-EHAS-5] A82-10893 Superalloy turbine components - Which is the Calculation of aerodynamic characteristics of jet superior manufacturing process, as-HIP, HIP plus flapped airplane Isoforge, or 'gatorizing' of extrusion A82-11459 consolidated billet Design and development of a low cost servoed rate A82-12497 gyro for unmanned aircraft Lineup of the ID-series aircraft-derivative gas A82-11932 turbines Bespouse of nonlinear aircraft structural panels A82-12560 to high intensity noise Propulsion study for Small Transport Aircraft A82-12041 Technology (SIAT), Appendix B Crack growth evaluation of a method to convert [HASA-CB-165499-APP-B] S82-10038 real-time loads history to a simplified A new method of cooling turbine vanes engineering spectra for aircraft structural H82-11027 analysis Lightweight diesel engine designs for commuter A82-12043 type aircraft ACHA - Fact or fantasy Advanced [NASA-CB-165470] H82-11068 Civilian/Hilitary Aircraft Development of multivariable controllers for A82-12048 aircraft turbine engines F-5G Tigershark H82-11087 A82-12775 Integrated analysis of engine The case for a defensive air-to-air fighter [BASA-TH-82713] 1182-11491 A82-12801

A-4 SUBJECT IBDBX ilBCBAFT PBODOCII01

AIBCBAFI BQOTPHEHT Optical sensors for displacement measurement A new APD for mediaa place aircraft environmental A82-11407 control systems Determination of vertical profiles of aerosol size [ASHE PAPEB 81-EH1S-1] A82-10889 spectra from aircraft radiative flux &ic-freon integrated environmental conditioning measurements. II - The effect of particle system for trainer' subsonic aircraft nonsphericity [ASHE PAPEB 81-EHAS-33] A82-10920 A82-12149 New separators for batter; systems Commercial EDS considerations for small gas A82-11715 turbine engines automated engine monitoring Sealed lead-acid batteries for aircraft applications systems A82-11716 A82-12449 4 bidden advantage of permanent magnet electrical Further application and development of an engine generating systems usage/life monitoring system for military services A82-11720 A82-12450 60 KVA aDP permanent magnet VSCP starter generator Hard limited approaches to correlation velocity system - Generator system performance sensing characteristics A82-12636 A82-11721 AIBCBAFT HAIHTEHAHCB Design and development of a low cost servoed rate Digital avionics: Promise and practice - An gyro for unmanned aircraft airlines experience in the field A82-11932 A82-11942 Digital avionics - Prooise and practice; Hathematical model for the maintenance program of Proceedings of tbe Joint Symposium, London, modern jet aircraft crack detection; England, Barch 20, 1980 inspection intervals A82-11934 [DF?LB-FB-81-14] N82-10002 The all digital military aircraft AIBCBAFT HAHBUTBBS 482-11937 Beal-tioe, on-line digital simulation of optianm The digital civil aircraft maneuvers of supersonic aircraft A82-11938 [AIAA 81-2178] A82-10127 tow maintenance hydraulic accumulator Estimation of airplane stability and control [AD-A103947] B82-10034 derivatives from large amplitude longitudinal Advanced aircraft electrical system control maneuvers technology demonstrator. Phase 1: Requirements [SASA-TB-83185] H82-10042 analysis and conceptual design AlfiCBAFT HODBLS [AD-A103922] H82-10326 Determination of airplane model structure from Threat Alert and Collision Avoidance System (ICAS) flight data by using modified stepwise regression Symposium [BASA-TP-1916] H82-10041 [AD-A104563] 1182-11017 AIBCBAFT 1OISE Polyurethane foams for aircraft shock mounts. 3: 'Quiet please1 aircraft hydraulic systems Vibration damping by polyether foams noise reduction [AD-A104496] H82-11212 A82-10854 AIBCBAFT FOBL SYSIEHS Model helicopter rotor impulsive noise Application of numerical methods to the A82-11300 calculation of electrostatic fields in aircraft Experimental modal analysis of the fuselage panels fuel tanks of an Aero Commander aircraft [AD-A103270] B82-10033 [SASA-CB-165750] H82-10028 Advanced fuel flowmeter for future naval aircraft Aeroacoustic theory for uoneompact wing-gust [AD-A104364] H82-11063 interaction Experimental study of fuel beating at low [FDBL-81-7] H82-11071 temperatures in a wing tank model, volume 1 Effects of aircraft noise on the equilibrium of [HASA-CB-165391] H82-11224 airport residents: Testing and utilization of a AIBCHAFT FUELS nev methodology Fuel for future transport aircraft [HASA-TH-76628] H82-11636 [ASHE PAPEB 81-HT-80] A82-10965 Helicopter rotor trailing edge noise noise Bheological behavior of progressively prediction shear-thickening solutions aircraft fuel [HASA-CB-3470] H82-11859 polymer additives for fire protection in AIBCBAFT PABTS snrvivable crashes Implementation of AVBADCOH HH6T for military A82-11177 aircraft parts production engineering Fuel conservation - DC-9 series 20/30/40 A82-10545 A82-12563 Fatigue life of lugs under service loading - Test Experimental study of fuel heating at low results and predictions temperatures in a wing tank model, volume 1 A82-11685 [HASA-CB-165391] H82-11224 AIBCBAFT PEBFOBHABCE AIBCHAFT HA2ABDS An airport wind shear detection and warning system Detection and display of wind shear and turbulence using Doppler radar A82-10222 A82-10220 Selected bibliography of HACA-BASA aircraft icing Design challenges of high performance aircraft POD publications EOCfl cooling systems [BASA-TM-81651] B82-11053 Electro-Optical/Countermeasnre System safety program plan electromagnetic [ASBE PAPEB 81-EHAS-6] A82-10894 pulse testing of the A-7E aircraft Ideal and simulated performance of an aircraft in [AD-A104557] B82-11354 the terrain following mission AIBCBAFT HTDBAULIC SISTEHS A82-11302 Fluid power technology for the '80s Book On the question of trailing airplane motion A82-10851 A82-11470 High-efficiency hydraulic power transfer units for Fnel conservation - DC-9 series 20/30/40 multisystem aircraft A82-12563 A82-10853 Quiet short-haul research aircraft familiarization •Quiet please1 aircraft hydraulic systems document, revision 1 noise redaction [HASA-TH-81298] 882-10031 A82-10854 AIBCBAFT PILOTS AIBCBAFT IBSTH0BE1TS Belationships between naval aviation safety and The evolution of airborne weather avoidance radar pilot flight experience toward a calibrated remote rain gauge using BEACT A82-11031 Bain Echo Attenuation Compensation Hardware AIBCBAFT PBODOCTIOI A82-10225 Automated Paint and Process Line /APPL/ for Problems relating to the classical rate-gyro aircraft production A82-10497 [AIAA 81-2166] A82-10120

A-5 ilBCBiPT BE1IABILITI SOBJEC1 IHDKX

Development of aircraft production engineering AIBCBAFT BAKES discipline at IIT, Bombay Strong matching method for computing transonic A82-11317 viscous flovs including wakes and separations - 1IBCBAFT BELI1BILIII Lifting airfoils The certification of digital systems 482-10821 A82-11940 AIBFOIL PBOPIIBS AIBCHAFT SAFEST The use of the ieber method for FAA developing new collision avoidance, data minicomputer-assisted numerical analysis of acquisition and transmission systeas airfoils A82-10396 A82-10362 Test Pilots' Aviation Safety Workshop, U.S. Haval Strong matching method for computing transonic Postgraduate School, aonterey, CA, February viscous flows including wakes and separations - 25-28, 1981, Proceedings Lifting airfoils A82-10500 A82-10821 Electrical ground testing of aircraft antistatic Bind tunnel tests on airfoils in tandem cascade protection A82-10987 A82-10822 Coupled fluid/structure response predictions for AIBCBAFT SPIH soft body impact of airfoil configurations Spin recovery training licensing reguirement ice and bird impact on aircraft engines [GPO-66-020] N82-10022 A82-12039 AIBCBAFT STABILITY. lind-tnnnel results for a modified On computing Flognet transition matrices of 17-percent-thick low-speed airfoil section rotorcraft [HASA-TP-1919] H82-11033 A82-11225 Aeroacoustic theory foe noncompact wing-gust A note on fatal aircraft accidents involving metal interaction fatigue [FDBL-81-7] N82-11071 A82-11400 AIEFOILS numerical treatment of helicopter rotor stability Icing tunnel test of a glycol-exuding porous problems leading edge ice protection system on a general A82-12045 aviation airfoil -:— conducted in the Lewis Estimation of airplane stability and control Besearch Center icing research tunnel derivatives from large amplitude longitudinal [HASA-CB-165444] H82-10021 maneuvers Second order approximation theory of an arbitrary [NASA-TH-83185] H82-10042 aerofoil in compressible potential flow AIBCBAFT STBDCTOBES N82-10982 The application of improved aluminium alloys and Aerodynamic calculations and design of snbcritical steels in aircraft structures aerofoils A82-10305 H82-10983 Some possibilities for composite light aircraft Matrix analysis of wings construction H82-10998 A82-10307 AIBFBAHE HAIEBIALS Sophisticated aircraft structure developments - Lightning effects on aircraft and composites, Combat aeroplanes literature study on lightning strikes and A82-10309 protection advanced composite materials Analytical determination of undercarriage [FOA-C-20388-F9] N82-10024 retraction kinematics AIBFBAHES A82-10364 Development of aircraft production engineering The balloon and the airship technological heritage discipline at IIT, Bonbay [AIAA PAPEB 81-1912] A82-10401 A82-11317 Design analysis of high temperature transparent Design techniques for motlivariable flight control windshields for high performance aircraft systems [ASHE PAPEB 81-EHAS-5] A82-10893 H82-11078 Acoustic emission - An emerging technology for AIELIIE OPER4TIOSS assessing fatigue damage in aircraft structure flow large should a commuter transport be A82-11149 [AIAA PAPEB 81-1732] A82-10463 Fatigue substantiation of non-linear structures Optimum climb and descent trajectories for airline A82-11224 missions Dynamic response of aircraft structure to gun H82-11082 shock loads AIBPOBf TOiEBS A82-11314 FAS misses opportunities to discontinue or reduce Emerging technologies in aerospace structures, operating hours of some airport traffic control design, structural dynamics and materials; towers Proceedings of the Aerospace Conference, San [PB81-224214] H82-11049 Francisco, CA, August 13-15, 1980 AIBPOBTS A82-12026 An airport wind shear detection and warning system Impact-initiated damage thresholds in composites using Doppler radar A82-12028 A82-10220 Response of nonlinear aircraft structural panels Airport and Airway Improvement Act of 1981, part 1 to high intensity noise [GPO-76-241-PT-1] H82-10062 A82-12041 Design of airport pavements for expansive soils Quantification of the thermal environment for [4D-A104660] H82-11313 externally carried aircraft stores and ordnance Effects of aircraft noise on the equilibrium of A82-12100 airport residents: Testing and utilization of a Fractographic determination of fatigue crack new methodology growth rates in aircraft components [BASA-TH-76628] H82-11636 A82-12697 4IBSHIPS Aircraft excrescence drag Design aspects of non rigid airship envelopes [AGABD-AG-264] N82-10020 A82-10306 A method for determination of the aeroelastic The balloon and the airship technological heritage behavior of aircraft vitb active control systems [4IAA PAPEB 81-1912] A82-10401 [DFVLB-FB-81-05] H82-10047 AIRSPEED Finite difference computation of the stead; Cooparison of simulation and experimental data for transonic potential flow around airplanes a. gliding parachute in dynamic flight H82-10981 [AIAA PAPEIt 81-1924] A82-10409 AIBCBAFT SDBflVABILITI Procedures and analysis techniques for determining Lightning effects on aircraft and composites, static air minimum control speeds literature stud; on lightning strikes and A82-12564 protection advanced composite materials [FOA-C-20388-F9] 882-10024

A-6 SOBJECS IHDBI AVIOHICS

ALOHIHOB ALLOTS ATBOSPHBBIC SCATTBBIBG The application of improved aluminium alloys and Determination of vertical profiles of aerosol size steels in aircraft structures spectra from aircraft radiative flux A82-10305 measurements. II - The effect of particle AHPLIFICATIOB nonsphericity Characteristic and principal gains and phases and A82-12149 their ose as mnltivariable control design tools ATHOSPHBHIC SOOBDIBG generalizing Hygnist and root-locus diagram Limiting payload deceleration during ground impact techniques [AIAA PAPER 81-1918] A82-10404 H82-10050 ATBOSPBEBIC TOBBULEHCB ABALYSIS (BATHBBATICS) Downbnrsts and microbursts.- An aviation hazard Bulti-variable analysis and design technigues downdrafts beneath thunderstorms [AGABD-LS-117] B82-10048 A82-10214 ABSLB OF ATTACK Detection and display of uind shear and turbulence Nonlinear prediction of subsonic aerodynamic loads A82-10222 on wings and bodies at high angles of attack ATTITUDE COBTBOL A82-11359 Simulation study of a hybrid strapdown attitude Estimation of airplane stability and control and heading reference system derivatives froa large amplitude longitudinal A82-12641 maneuvers ADTOMATIC COBTBOL [NASA-TH-83185] H82-10042 Problens relating to the classical rate-gyro Aerodynamic calculations and design of snbcritical A82-10497 aerofoils Application of nonlinear systems inverses to H82-10983 automatic flight control design: System AIXBBBA DESIGH concepts and flight evaluations Antenna theory and design Book B82-11083 A82-12323 AUTOMATIC FLIGHT COBTBOL General aviation aircraft antennas for the global HiBAT onboard flight computer system architecture positioning system and qualification [HASA-TB-83212] H82-11339 [AIAA 81-2107] A82-10082 AHIBHBA BADIATZOH PATTEBBS Controlling the software/hardware interface for Antenna theory and design Book the validation of avionics systems in flight A82-12323 control systems AHTIICIHG ADDITIVES [AIAA 81-2159] A82-10116 Icing tunnel tests of a composite porous leading Ideal and simulated performance of an aircraft in edge for use vith a liquid anti-ice system the terrain following mission Lewis icing research tunnel A82-11302 [HASA-CR-164966] N82-11052 The digital civil aircraft AHIIHISTIIG POELS A82-11938 An assessment of the ose of antimisting fuel in ADTOBATIC LABDIBG COBTBOL turbofan engines Development and evaluation of automatic landing [HASA-CB-165258] N82-11230 control laws for light wing loading STOL aircraft AHtlSHIP MISSILES [HASA-CB-166160] B82-10043 Air-film cooling returns to ramjets AOTOBATIC TEST BQOIPBEHT [ASBE PiPEE 81-EHAS-8] A82-10896 Air supply system bite for Boeing 767 airplane APPBOXIBATIOB Built-in-Test-Equipment Haitivariables design: The optimization of [ASHE PAPEB 81-EHAS-7] A82-10895 approximate inverses Commercial EBS considerations for small gas H82-10057 turbine engines automated engine monitoring Second order approximation theory of an arbitrary systems aerofoil in compressible potential flow A82-12449 H82-10982 AOTOBATIOI ARCHAEOLOGY Automated Paint and Process Line /APPL/ for Badar napping, archaeology, and ancient land use aircraft production in the Maya lowlands [AIAA 81-2166] A82-10120 [BASA-CR-164931] 882-11514 AOZILIABI POiEB SOOBCBS ABCHITBCTOBE (COHPOTBBS) A new APO for medium place aircraft environmental HiHAT onboard flight computer system architecture control systems and qualification [ASBE PAPEB 81-EHAS-1] A82-10889 [AIAA 81-2107] A82-10082 A7IOHICS Airborne associative processor /ASPBO/ for KC-135 Avionics Hodernization Hot Bench early warning radar surveillance, command, and [AIAA 81-2105] A82-10081 control applications Bridging the gap from aircraft to space computers [AIAA 81-2145] A82-10104 [AIAA 81-2142] A82-10101 ABBA BAVIGAIIOM Controlling the software/hardware interface for Ose of Space Shuttle technology in conventional the validation of avionics systems in flight aircraft control systems [AIAA 81-2176] A82-10125 [AIAA 81-2159] A82-10116 Discrete address beacon, navigation and landing Closed loop environmental control systems for system fighter aircraft A82-10650 [ASHE PAPEB 81-EBAS-2] A82-10890 ABBBD FORCES (FOBEIGB) Design challenges of high performance aircraft POD A proposed flight safety program for the Korean EOCH cooling systems Air Force Electro-Optical/Conntermeasnre [AD-A102373] H82-10023 [ASHE PAPER 81-EBAS-6] A82-10894 ABSDI BIBGS Sealed lead-acid batteries for aircraft applications Effects of vortex flaps on the low-speed A82-11716 aerodynamic characteristics of an arrow wing Applications of finite element method in aerospace [BASA-TP-1914] B82-11013 power systems design ASTBIOBICS A82-11717 Memory requirements for future navigation systems Advanced aircraft electric power system A82-12637 A82-11718 ATMOSPHERIC CIBCOLATIOB Variable speed constant frequency /VSCP/ Multiple Doppler radar observations of FBL structure electrical system cats cost of ownership A82-10292 A82-11719 ATHOSPBEBIC ELECTRICITY Digital avionics - Proaise and practice; Electrical ground testing of aircraft antistatic Proceedings of the Joint Symposium, London, protection England, Harch 20, 1980 A82-10822 482-11934

A-7 ABACS AIBCBAFT SUBJECT IBDBZ

The all digital military aircraft BOEIBG 767 AIBCBAFT A82-11937 Air supply system bite for Boeing 767 airplane The digital civil aircraft Built-in-Test-Equipment A82-11938 [ASBE PAPEB 81-EHAS-7] A82-10895 Digital avionics systems - The BAF experience BOdBDARI LAZEB COBTBOL A82-11941 Developments in boundary layer Thrust vector control Digital avionics: Premise and practice - An A82-10855 airlines experience in the field New estimation method for flutter or divergence A82-11942 boundary from random responses at subcritical Memory requirements for future navigation systems speeds 482-12637 [BAL-TB-667T] H82-11034 The integrated inertial sensor assembly /USA/ - A Amplified crossflow disturbances in the laminar redundant strapdown system for advanced aircraft boundary layer on swept wings with suction navigation and flight control functions [HASA-TP-1902] B82-11391 A82-12642 BOOHDABI LAIEB FLOi P-5G Tigershark Hnltiple-scale turbulence modeling of free A82-12775 turbulent flows Electronic master monitor and advisory display [ASBE PAPEB 81-FE-20] A82-10934 system, data transmission study BOOHDABI LAYBB SEPABATIOB [AD-A104243] B82-11064 A summary of V/STOL inlet analysis methods ABACS AIBCBAFT [HASA-TB-82725] ' B82-11043 Airborne associative processor /ASPBO/ for BOOBDABI LAIBBS early warning radar surveillance, command, and Aircraft excrescence drag control applications [AGABD-AG-264] N82-10020 [AIAA 81-2145] A82-10104 Aircraft wing trailing-edge noise AXIAL STBESS [HASA-CB-164952] S82-11039 Crack growth evaluation of a method to convert BBAKES {FOB ABBESTI8G BOTIOB) real-time loads history to a simplified Aeroballistic characteristics of sonobuoy engineering spectra for aircraft structural parachute decelerators limited to a length of analysis three feet A82-120U3 [AIAA PAPEB 81-1950] A82-10425 AXISfflflBXBIC FLOS On the prediction of swirling flowfields found in axisymmetric combustor geometries A82-12120 C-135 AIBCBAFI KC-135 Avionics Nodernization Hot Bench [AIAA 81-2105] A82-10081 B CALIBBATIBG BALLISTICS In-situ calibration of flight heat transfer Aeroballistic characteristics of sonobuoy instrumentation parachute decelerators limited to a length of [ASHE PAPEB 81-EBAS-13] A82-10901 three feet CABOPIES [AIAA PAPER 81-1950] A82-10425 Aerodynaoics and performance of cruciform BALLOOB PLIGHT parachute canopies A new thermal and trajectory model for high [AIAA PAPEB 81-1919] A82-10405 altitude balloons Experimental determination of parachute apparent [AIAA PAPEH 81-1926] A82-10411 mass and its significance in predicting dynamic BALLOOH-BOBBB IBSTBOBBBTS stability Limiting payload deceleration daring ground impact [AIAA PAPEB 81-1920] A82-10406 [AIAA PAPEB 81-1918] A82-10404 Theoretical analysis of parachute inflation BALLOOBS including fluid kinetics The balloon and the airship technological heritage [AIAA PAPEB 81-1925] A82-10410 [AIAA PAPEE 81-1912] A82-10401 The net-skirt to a parachute canopy as a device to BEABS (SOPPOBTS) prevent inversion Hatrix analysis of wings [AIAA PAPEB 81-1927] A82-10412 N82-10998 Stress measurements in a ribbon parachute canopy BELLOIS during inflation and at steady state Low maintenance hydraulic accumulator [AIAA PAPEB 81-1944] A82-10420 [AD-A103947] H82-10034 Stress measurements in bias constructed parachute BBBDIBG FATIGUE canopies during inflation and at steady-state Hatrix analysis of wings [AIAA PAPEB 81-1945] A82-10421 H82-10998 CAPACITOBS BIBLIOGBAPHIBS High voltage surge and partial discharge test to Selected bibliography of NACA-NASA aircraft icing evaluate aerospace equipment parts publications A82-11740 [NASA-TH-81651 ] N82-11053 CABBOB FIBEB BEIHFOBCED PLASTICS BIT SIBCHBOBIZAIIOH Sophisticated aircraft structure developments - Synchronous fault-tolerant flight control systems Combat aeroplanes [AIAA 81-2109] A82-10083 A82-10309 BLADE SLAP BOISE On the use of carbon composites in slat and Model helicopter rotor impulsive noise stabilizer construction A82-11300 A82-11468 BODI-BIHG ABD TAIL COHFIGOBATIOBS A CFBP taileron for the Tornado: Construction and Experimental study of empennage snap-through production -:— horizontal stabilizer vibrations CBBB-FE-212/KFK/PDB/2] H82-10035 A82-11471 CARGO AIBCBAFT BODY-8IBG COHFIGOBATIOBS ACBA - Fact or fantasy Advanced Acta mechanica sinica Civilian/Hilitary Aircraft [AD-A105184] H82-11014 A82-12048 The principles and methods for shaping the wing CASCADE FLOi root regions of a wing-body combination at Hind tunnel tests on airfoils in tandem cascade transonic and lower supersonic speeds A82-10987 882-11016 End losses in turbine cascades with porous cooling BOEIBG 747 AIECHAFT A82-11434 SEL and EPNL noise duration coefficients for the Theoretical investigations and experimental 747 and T-38 aircraft researches for higher subsonic two-diaensional [ NASA-TH-83214] N82-11860 compressor cascade H82-11024

A-8 SUBJECT IBDBX COBPOTATIOBAL FLOID DYBABICS

Subsonic cascade wind tunnel tests using a COBBOBICAIIOB HETiOBKS coapressor configuration of DCi blades Interoperability testing of decentralized command, [AD-A104597] H82-11069 control, communications and intelligence /C3I/ CBILIHGS (ABCHITECTQBB) systems Evaluation of the acoustic measarenent capability [AIAA 81-2205] A82-10143 of the NASA Langley V/STOL vind tunnel open test A solution to the static geonetry problem for section with acoustically absorbent ceiling and JTIOS relative navigation floor treatments A82-12634 [HASA-CB-165796] 882-10059 Omega station 10.2 kHz signal selection made easy CENTBAL ABBBICA A82-12638 Badar napping, archaeology, and ancient land use COBPOIBR RELIABILITY in the Maya lowlands Extending the limits of reliability theory Book [H4S4-CB-164931] H82-11514 A82-12318 CBB1HICS COBFOSITE BATEBIALS Development of low Modulus material for use in Some possibilities for composite light aircraft ceramic gas path seal applications construction [H4S4-CB-165469] H82-10039 A82-10307 CBBTIPICATIOH Light aircraft structural design in non-metallics The certification of digital systems - Ose of composite honeycomb for light aircraft A82-11940 A82-10308 CHABHEL iOISB Emerging technologies in aerospace structures, Tangential sensitivity of EB receivers design, structural dynamics and materials; 482-11020 Proceedings of the Aerospace Conference, San CIRCUUTIOH COITBOL BOTOBS Francisco, CA, August 13-15, 1980 An investigation of a stoppable helicopter rotor 482-12026 nith circulation control aaes 40 by 80 foot Impact-initiated damage thresholds in composites vind tunnel A82-12028 [HASA-TB-81218] H82-10030 Lightning effects on aircraft and composites. CIVIL AVIATIOH Literature study on lightning strikes and The digital civil aircraft protection advanced composite materials A82-11938 [FOA-C^20388-F9] H82-10024 Digital avionics: Promise and practice - An COBPOSIIE STBOCTOBES airlines experience in the field Composite main rotor tubular braided A82-11942 482-10547 CLEAR AIB TDRBULEHCB Development of the Triflex rotor head Instrumented aircraft verification of clear-air 482-11222 radar detection of low-level Hind shear Icing tunnel tests of a composite porous leading A82-10221 edge for use with a liquid anti-ice system COAL LIO.OBFACTIOB Lewis icing research tunnel Jet fuel from carbon [HASA-CB-164966] H82-11052 A82-12021 COBPBESSIBIUTI EFFECTS COAL UTILIZATION Theoretical investigations and experimental Jet fuel froa carbon researches for higher subsonic two-dimensional A82-12021 compressor cascade COLLISIOB AVOIDABCB H82-11024 FAA developing nev collision avoidance, data COHPBESSIVE STBEIGTB acquisition and transnission systems Seven years experience with Kevlar-49 in the A82-10396 Lockheed L-1011 Tristar Threat Alert and Collision Avoidance System (TCAS) 482-12647 Symposium COHPBBSSOB BLADES (AD-4104563] 1182-11047 An aerodynamic design method for transonic axial COHBOSTIOH CHAHBBBS flow compressor stage One reason for the onset of high-frequency H82-10984 self-excited oscillations in combustion Subsonic cascade wind tunnel tests using a chambers of aircraft engines compressor configuration of DCA blades 482-11448 [AD-A104597] 1182-11069 The CIVIC - A concept in vortex induced COHPOTATIOH4L FLDID DIHABICS combustion. II The use of the Keber method for [ASBB PAPEB 81-61-12] A82-11997 minicomputer-assisted numerical analysis of Application of numerical modeling to gas turbine airfoils combnstor development problems A82-10362 A82-12118 Theoretical analysis of parachute inflation On the prediction of swirling flowfields found in including fluid kinetics axisymmetric combnstor geometries [4144 PAPEB 81-1925] 482-10410 A82-12120 Strong matching method for computing transonic Validation studies of turbulence and combustion viscous flows including wakes and separations - models for aircraft gas turbine coobustors Lifting airfoils A82-12267 482-10821 COHBOSTIOH PHISICS Multiple-scale turbulence modeling of free An investigation of the combustion process in turbulent flows solid fuel ramjets [4SBE PAPEB 81-FE-20] 482-10934 [AD-A104603] 1182-11232 Control laws for adaptive wind tunnels COBBUSTIOB STABILITY 482-10985 One reason for the onset of high-fregnency Calculation of aerodynamic characteristics of jet self-excited oscillations --- in combustion flapped airplane chambers of aircraft engines A82-11459 A82-11448 Validation studies of turbulence and combustion COHHA8D AHD COHTBOL models for aircraft gas turbine combustors Interoperability testing of decentralized command, A82-12267 control, communications and intelligence /C3I/ Acta mechanica sinica systems [AD-4105184] H82-11014 [AIAA 81-2205] A82-10143 The arbitrary quasi-orthogonal surface method for COHHE8CIAL AIBCBAFT computing three-dimensional flow in turbine ACHA - Fact or fantasy --- Advanced machinery. 2. Calculation of the Civilian/Bilitary Aircraft three-dimensional flow with the S sub 1-surface A82-12048 twisted Lightweight diesel engine designs for commuter H82-11015 type aircraft [HASA-CB-165470] 1182-11068

A-9 COHPOTEB DESIGS SUBJECT IBDBZ

Computation of high Reynolds number COHCEETE STBOCTUBES internal/external flows Structural analysis computer programs for rigid [NASA-TB-84049] H82-11046 multicomponent pavement structures with COHPOIBB DESIGB discontinuities, KESLIQID and HESLAIEB. Beport Bridging the gap from aircraft to space computers 1: Program development and numerical presentations [AIAA 81-2142] 482-10101 [4D-4104545] H82-11498 Airborne associative processor /ASPBO/ for COBFBBBBCES early warning radar surveillance, coamand, and Test Pilots' Aviation Safety Workshop, 0.S. Haval control applications Postgraduate School, Monterey, CA, February [AIAi 81-2145] 482-10104 25-28, 1981, Proceedings COHPOTEB 6BAPEICS 482-10500 Integration of computer graphics design with Digital avionics - Promise and practice; analytical models for aircraft design Proceedings of the Joint Symposium, London, [AIAA 81-2134] 482-10096 England, March 20, 1980 Improving the MLS through enhanced cockpit displays 482-11934 A82-10649 Emerging technologies in aerospace structures, Solution to the hidden-line problem design, structural dynamics and materials; 482-12803 Proceedings of the Aerospace Conference, San COHPOTEB FROGBAflS Francisco, CA, August 13-15, 1980 The Space Shuttle vehicle checkout involving 482-12026 flight avionics software Powder metallurgy superalloys - Aerospace [AIAA 81-2141] 482-10100 materials for the 1980's; Proceedings of the Controlling the software/hardware interface for Conference, Zurich, Switzerland, November 18-20, the validation of avionics systems in flight 1980. Volume 1 control systems A82-12495 [4IAA 81-2159] A82-10116 national Aerospace Meeting, Trevose, PA, April The certification of digital systems 8-10, 1981, Proceedings A82-11940 482-12626 Digital avionics systems - The EAF experience Kevlar composites; Proceedings of the Symposium, A82-11941 El Segundo, CA, December 2, 1980 Flight test results of the model simulation 482-12646 controller for the HPB 320 for in-flight The Shock and Vibration Digest, volume 13, no. 9 simulation of the 4310 airbus [AD-A105062] S82-10421 [ESA-TT-660] H82-10107 COH6BESSIOH4I BEPOBtS Computation of high Beynolds number Spin recovery training licensing requirement internal/external flows [GPO-66-020] H82-10022 [NASA-TH-84049] H82-11046 Airport and Airway Improvement Act of 1981, part 1 Integrated analysis of engine [GPO-76-241-PT-1] H82-10062 [HASA-Tfl-82713] H82-11491 COHSTHOCTIOB Structural analysis computer programs for rigid Development and construction of pilot ejector multicomponent pavement structures with seats in Germany from 1938-1945 discontinuities, HESLIQIO and BESLAYEB. Eeport [DFTLB-FB-81-04] N82-10026 1: Program development and numerical presentations A CFBP taileron for the Tornado: Construction and [4D-A104545] H82-11498 production horizontal stabilizer COHPOTEB SIOBA6E DEVICES [BBB-FE-212/KFK/POB/2] M82-10035 Hemory requirements for future navigation systems COBTBOl BOABDS 482-12637 Electronic master nonitor and advisory display COHPUTEB SISTEBS DESIGB system, human engineering summary report KC-135 Avionics Modernization Hot Bench [4D-4104244] H82-11065 [AIAA 81-2105] A82-10081 COHTBOL EQOIPBBHT Synchronous fault-tolerant flight control systems Considerations and applications for the use of [AI4A 81-2109] 482-10083 fluidics in aerospace controls Havigation task partitioning in 482-12087 distributed-processing avionics systems Management of redundancy in flight control systems 482-10646 using optimal decision theory COHPDIEB SISTEHS SIBDLAIIOH N82-11084 Performance analysis of enroute air traffic COBTBOL SIABILITY control computers in the national Airspace System Characteristic and principal gains and phases and [AIAA 81-2203] A82-10140 their use as multivariable control design tools COHPOIEBIZED DESIGB generalizing Nyguist and root-locus diagram Integration of computer graphics design with techniques analytical models for aircraft design H82-10050 [AI4A 81-2134] A82-10096 Design of high integrity mnltivariable control Solution to the hidden-line problem systems A82-12803 N82-10055 Multi-variable analysis and design technigues COBTBOl SOBF4CES [AGABD-LS-117] N82-10048 On the kernel function collocation method in Characteristic and principal gains and phases and steady subsonic flow for wing with control their use as multivariable control design tools surfaces generalizing Hyquist and root-locos diagram H82-12023 technigues COHTBOL fHEOBI H82-10050 Design considerations for the direct digital LQG multivariable design tools control of dry-tuned gyroscope H82-10054 A82-11933 The automatic matrix force method and techniques Control of electromechanical actuator elements for for handling more complex computations with flight vehicles Bussian book given computer capacity 482-12170 H82-10994 Theory and applications of optimal control in COHPD7BBXZBD SIBOLATIOB aerospace systems 4 new thermal and trajectory model for high [4G4BD-4G-251] H82-11073 altitude balloons An introduction to stochasic optimal control theory [AIA4 PAPEB 81-1926] A82-10411 H82-11076 Ideal and simulated performance of an aircraft in COHTBOLLABILITY the terrain following mission Theoretical investigation of the influence of A82-11302 spoiler dynamics on the handling qualities of an Application of numerical modeling to gas turbine aircraft with direct lift control combustor development problems [ESA-TT-681] II82-10036 482-12118

4-10 SUBJECT IHDBI DIGITAL SIBDLiTIOH

COBTBOLLEBS Haiti-variable analysis and design techniques [AGABD-LS-117] H82-10048 The need for nultivariable design and analysis DAHAGE ASSESSHBBT techniques Acoustic emission - An emerging technology for H82-10049 assessing fatigue damage in aircraft structure Feedback and minimal sensitivity A82-11149 H82-10058 DAHPIHG Development of oaltivariable controllers for New estimation method for flutter or divergence aircraft turbine engines boundary from random responses at subcritical H82-11087 speeds COOLIHG [BAL-TB-667T] H82-11034 End losses in turbine cascades with porous cooling DATA ACQDISITIOB 182-11434 A microprocessor-based data acquisition system for COOLIHG SYSIEHS stall/spin research Design challenges of high performance aircraft POD [AIAA 81-2177] A82-10126 EOCH cooling systems FAA developing new collision avoidance, data Electro-Optical/Countermeasure acquisition and transmission systems [ASHE PAPEB 81-EHAS-6] A82-1Q894 A82-10396 CORES DATA TBABSBISSIOI Hew molding method of three-dimensional hollow FAA developing new collision avoidance, data photoelastic model and centrifugal stress acquisition and transmission systems analysis of air cooled turbine blade model A82-10396 [HAL-TB-427T] H82-11067 Electronic master monitor and advisory display CQBBBLATIOH system, data transmission study Hard limited approaches to correlation velocity CAD-A104243] 1182-11064 sensing DC 9 AIBCBAFI A82-12636 Fuel conservation - DC-9 series 20/30/40 COBROSIOB PBBVEBIIOH A82-12563 A protective additive for jet fuels DBCELEBATIOB A82-12022 Limiting payload deceleration during ground impact COST REDOCTIOB [AIAA PAPER 81-1918] A82-10404 Variable speed constant fregnency /VSCF/ DBCISIOB HAKIIG electrical system cuts cost of ownership Hanagement of redundancy in flight control systems A82-11719 using optimal decision theory ACHA - Pact or fantasy Advanced H82-11084 Civilian/Hilitary Aircraft DEICEBS A82-12048 Botorcraft icing: Status and prospects Cost reduction in air transportation energy [AGABD-AB-166] B82-11056 conservation Ice protection system technology [SHIAS-811-150-101] 1182-10025 If 82-11060. FAA misses opportunities to discontinue or reduce DEICIBG operating hours of some airport traffic control Icing tunnel test of a glycol-exuding porous towers leading edge ice protection system on a general [PBS 1-224214] H82-11049 aviation airfoil conducted in the Lewis COBLIHGS Research Center icing research tunnel Low speed testing of the inlets designed for a [NASA-CB-165444] H82-10021 tamden-fan V/STOL nacelle conducted in the DELTA BIHGS Lewis 10 by 10 foot wind tunnel Formation of triangular-element stiffness matrix [HASA-TH-82728] H82-11042 using sliding interpolation CBACK PBOPAGATIOH A82-11464 Acoustic emission - An emerging technology for Increasing the lift:drag ratio of a flat delta wing assessing fatigue damage in aircraft structure A82-11899 A82-11149 DESIGN AIALISIS Crack growth evaluation of a method to convert Development of new lifting parachute designs with real-time loads history to a simplified increased trim angle engineering spectra for aircraft structural [AIAA PAPEB 81-1921] A82-10407 analysis Optimization of the principal design parameters of A82-12043 a passenger aircraft Fractographic determination of fatigue crack A82-10816 growth rates in aircraft components Design analysis of high temperature transparent A82-12697 windshields for high performance aircraft CBITICAL FLO! [ASHE PAPEB 81-EBAS-5] 482-10893 Aerodynamic calculations and design of subcritical Parachute technology under pressure aerofoils A82-12804 H82-10983 DIESEL EBSIIES CBITICIL LOADIHG Lightweight diesel engine designs for commuter Impact-initiated damage thresholds in composites type aircraft A82-12028 [HASA-CB-165470] H82-11068 CBOSS FLOB DIFFOSIOB ELECTBODBS A numerical three-dimensional turbulent simulation Unsolved problems of nickel cadmium batteries of a subsonic VS10L jet in a cross-flow using a A82-11725 finite element algorithm DIGITAL COBPOTEBS [AD-A104514] H82-11055 Aircraft digital input controlled hydraulic Amplified crossflow disturbances in the laminar actuation and control system boundary layer on swept wings with suction [AD-A104263] 882-11072 [HASA-TP-1902] H82-11391 DIGITAL BADAB SISTE8S CBTOGBHIC BIID TOBBELS The evolution of airborne weather avoidance radar Design predictions for noise control in the toward a calibrated remote rain gauge using BEACT cryogenic Hational Transonic Facility Bain Echo Attenuation Compensation Hardware A82-12025 A82-10225 CICLIC LOADS DIGITAL SIBOLATIOB Fatigue substantiation of non-linear structures Seal-time, on-line digital simulation of optimum A82-11224 maneuvers of supersonic aircraft [AIAA 81-2178] A82-10127

A-11 DIGITAL SXSTEBS SUBJECT IHDBZ

DIGITAL SISIEHS DBOBE AIBCBAFT Digital avionics - Promise and practice; Development of a nylon-Kevlar recovery system for Proceedings of the Joint Symposium, London, the Ct-289 /AH/DSD 502/ surveillance drone England, March 20, 1980 [AIAA PAPEB 81-1952] A82-10427 A82-11934 DROP SIZE The all digital military aircraft The dispersion of drop sizes in gas turbine fuel A82-11937 nozzle sprays The digital civil aircraft A82-12107 A82-11938 DBOP TESTS The certification of digital systems The constricted rigging line trials technique for A82-11940 assessing the opening characteristics of Digital avionics systems - the RAF experience parachutes A82-11941 [AIAA PAPEB 81-1932] A82-10113 Digital avionics: Promise and practice - AD DIBiHIC COHTBOL airlines experience in the field The need for multi-variable design and analysis A82-11942 techniques Practical design and realization of a digital H82-10049 adaptive flight control system AD introduction to stochasic optimal control theory N82-11079 H82-11076 Control lav design for transport aircraft flight DTHAHIC BODELS tasks Nev molding method of three-dimensional hollow H82-11080 photoelastic model and centrifugal stress Application of nonlinear systems inverses to analysis of air cooled turbine blade model automatic flight control design: system [HAL-TB-1127T] 882-11067 concepts and flight evaluations DIBASIC BESP01SB •82-11083 Dynamic response of aircraft structure to gun DIGITAL TBCBHIQOES shock loads Ose of Space Shuttle technology in conventional A82-11314 aircraft A method for determination of the aeroelastic [AIAA 81-2176] A82-10125 behavior of aircraft with active control systems Air supply system bite for Boeing 767 airplane [DFVLB-FB-81-05] 882-10047 Built-in-Test-Equipment A preliminary experimental investigation of the [ASBE PAPER 81-ENAS-7] A82-10895 response of a turbojet engine to inlet pressure Design considerations for the direct digital distortion control of dry-tuned gyroscope H82-11007 A82-11933 DIHAHIC STABILITI DIBBCT LIFT COBIBOLS A contribution to the stabilization of flight Theoretical investigation of the influence of vehicle parachute systems mathematical models spoiler dynamics on the handling qualities of an [ESA-TT-679] H82-10046 aircraft with direct lift control DIBASIC STBOCTOBAL ABM.ISIS CESA-TT-681] B82-10036 Fatigue substantiation of non-linear structures Development and evaluation of automatic landing A82-11224 control laws for light ving loading STOL aircraft Emerging technologies in aerospace structures, [HASA-CB-166160] H82-10043 design, structural dynamics and materials; DISCRETE ADDBESS BEACOI SISTEB Proceedings of the Aerospace Conference, San Discrete address beacon, navigation and landing Francisco, CA, August 13-15, 1980 system A82-12026 A82-10650 The Shock and Tibration Digest, volume 13, no. 9 DISPEBSIOBS [AD-A105062] H82-10421 The dispersion of drop sizes in gas turbine fuel nozzle sprays A82-12107 DISPLACBBEBT BEASDBEHEHT EABLI IARBIHG SISTEBS Optical sensors for displacement measurement Airborne associative processor /ASPBO/ for A82-11407 early warning radar surveillance, command, and DISPLAY DEVICES control applications Improving the HLS through enhanced cockpit displays £AIAA 81-2145] A82-10104 A82-10649 EARTH OBSERVATION (FROB SPACE) Electronic master monitor and advisory display SABSAT applications system, data transmission study A82-12698 [AD-A104243] S82-11064 EDGE LOADIBG Electronic master monitor and advisory display Aeroaconstic theory for noneOBpact wing-gast system, human engineering summary report interaction [AD-A104244] H82-11065 [FDBI-81-7] S82-11071 DOPPLEB BADAB EDOCATIOI Applications of conventional and Doppler radars Development of aircraft production engineering for aviation safety discipline at III, Bombay A82-10215 A82-11317 An airport wind shear detection and warning system EFFECTIVE PERCEIVED BOISE LEVELS using Doppler radar SEL and EFBL noise duration coefficients for the A82-10220 7U7 and T-38 aircraft Instrumented aircraft verification of clear-air [HASA-Tfl-83214] H82-11860 radar detection of low-level wind shear BIGEHViLOES A82-10221 Bultivariable design techniques based on singular Detection and display of wind shear and turbulence value generalizations of classical control A82-10222 B82-10051 Gust front structure observed by Doppler radar BJECTIOH IBJDBIES A82-10223 Development and construction of pilot ejector Bultiple Doppler radar observations of PEL structure seats in Germany from 1938-1945 A82-10292 [BFVLB-FB-81-04] B82-10026 DBAG BEDOCTIOB EJBCTIOB SEATS Beductions in parachute drag due to forebody wake Development and construction of pilot ejector effects seats in Germany from 1938-1945 [AIAA PAPEB 81-19393 &82-10417 [DF?LB-FB-81-04] H82-10026 The principles and methods for shaping the wing ELASTIC DEPOBBATIOB root regions of a wing-body combination at On low-speed wind tunnels with defornable boundaries transonic and lower supersonic speeds A82-11462 H82-11016

A-12 SUBJECT I1DEI EHGIiB TESTS

BLBCTBIC CH1BSB Cost reduction in aic transportation energy Electrical ground testing of aircraft antistatic conservation protection ISHIAS-811-150-101] H82-10025 482-10822 BBBBGT COHSOflPTIOS BLECTBIC COITBOL Characteristics and trends of energy consumption Control of electromechanical actuator eleaents for in transport missions vith aircraft and surface flight vehicles Bnssian book vehicles A82-12170 A82-10495 BLECTBIC BQOIPBE1T TESTS Towards minimua pover for environmental control in High voltage surge and partial discharge test to transport aircraft evaluate aerospace equipment parts fASHE PAPEB 81-EHAS-4] A82-10692 A82-11740 EBBBGI COB?BBSIOB BFFICIEBCT BLECTBIC FIELDS A hidden advantage of permanent magnet electrical Application of numerical methods to the generating systems calculation of electrostatic fields in aircraft A82-11720 fuel tanks EHGIHE COBTBOL [AD-A103270] H82-10033 Helicopter engine technology - Hith particular BLECTBIC GBBEBATOBS reference to the Bolls-Boyce Gem engine A hidden advantage of permanent aagnet electrical A82-10304 generating systens The digital civil aircraft A82-11720 A82-11938 BLECTBIC POIEB SUPPLIES EHGIHE COOLAITS Applications of finite element method in aerospace Air-film cooling returns to ramjets power systems design [ASBE PAPEB 81-EBAS-8] A82-10896 A82-11717 End losses in turbine cascades vith porous cooling Advanced aircraft electric pover system A82-11434 A82-11718 The enhancement of heat exchange in channels /2nd Variable speed constant frequency /VSCF/ revised and enlarged edition/ Bnssian book electrical system cuts cost of ovnership A82-12222 A82-11719 EH6IME DESIGB High voltage surge and partial discharge test to Helicopter engine technology - lith particular evaluate aerospace egnipaent parts reference to the Bolls-Boyce Gem engine A82-11740 A82-10304 KLBCTBICAL BESISTITITY Design considerations for duty cycle, life and Electrical ground testing of aircraft antistatic reliability of small limited life engines protection [AIAA PAPEB 81-1402] A82-10465 A82-10822 Basic problem of aircraft gastnrbine engine ELECTBO-OPTICS analytic design. II Design challenges of high performance aircraft POD A 82-11463 EOCH cooling systems Thermal expansion accommodation in a jet engine Electr o-optical/Conntermeasure frame [ASBE PAPEE 81-ENAS-6] A82-10894 A82-11999 Optical sensors for displacement measurement Propulsion study for Small Transport Aircraft A82-11107 Technology (STAT) ELECTBOHA6SBTIC FIELDS IHASA-CB-165499] H82-10037 Antenna theory and design Book Propulsion study for Snail Transport Aircraft A82-12323 Technology (STAT), Appendix B ELECTBOBAGIIETIC BOISE [HASA-CB-165499-APP-B] H82-10038 Tangential sensitivity of Ei receivers Lightweight diesel engine designs for commuter A82-11020 type aircraft BLECTBOBAGIBTIC POLSES [HASA-CB-165470] H82-11068 System safety program plan electromagnetic Development of mnltivariable controllers for pulse testing of the A-7E aircraft aircraft turbine engines [AD-A104557] 882-11354 H82-11087 BLECTBOBECH&BICAL DEVICES Integrated analysis of engine Control of electromechanical actuator elements for [HASA-TH-82713] H82-11491 flight vehicles Russian book EBGIBE I8LBTS A82-12170 A summary of V/STOL inlet analysis methods ELECTBOBIC AIBCBAFT [HASA-TH-82725] H82-11043 Design challenges of high performance aircraft POD EBGIBE flOBITOBIBG IBSIBOBEBTS EOCH cooling systems Commercial EHS considerations for small gas Electro-Optical/Conntermeasnre turbine engines -— automated engine monitoring [1SBE PAPES 81-EHAS-6] A82-10894 systems ELECTBOHIC COBTBOL A82-12449 Advanced aircraft electrical system control Further application and development of an engine technology demonstrator. Phase 1: Requirements usage/life monitoring system for military services analysis and conceptual design A82-12450 [AD-A103922] H82-10326 EBGIBE IOISB ELECTBOHIC COOBTEBHEASDBES Botor vake characteristics relevant to Design challenges of high performance aircraft POD rotor-stator interaction noise generation EOCB cooling systems [AIAA PAPEB 81-2031] A82-10456 Electro-Optical/Conn termeasnre EBGIBB PABSS [ASHE PAPER 81-EB4S-6] A82-1089a Snperalloy powder engine components; controls ELBCTBOBIC TB1BSDOCBBS employed to assure high quality hardware Outsider*s look at flight instrumentation A 82-12499 [DE81-025409] H82-11066 Initial experimental research into the response of ELECIBOBIC UABPABB turbojet engine compressors to distortion of Digital avionics systems - The BAP experience intake pressure A82-11941 B82-11006 ELECTROSTATICS EBGIBE STABTBBS Application of numerical aethods to the 60 KVA ADP permanent magnet VSCF starter generator calculation of electrostatic fields in aircraft system - Generator system performance fuel tanks characteristics [AD-A103270] H82-10033 A82-11721 BHBB6I COiSEBfATIOB EBGIBB TESTS Fuel conservation - DC-9 series 20/30/40 History of flight testing the L-1011 Tristar jet A82-12563 transport. II - Testing highlights since initial certification of the L-1011-1 A82-12049

A-13 BHVIBOHBBBTAL COHTBOL SUBJECT IBDBX

Propulsion stud; for Snail Transport aircraft Fractographic determination of fatigue crack Technology (ST4T). Appendix B growth rates in aircraft components [NASA-CB-165499-APP-B] N82-10038 A82-12697 Adaptation of a turbine test facility to FAB BLADES high-temperature research Effects of vane/blade ratio and spacing on fan noise [BAE-LIB-TBABS-2064] B82-11089 [AIAA PAPEB 81-2033] A82-10457 BBVIB08HEBTAL COBTBOl FATIGDB (BATBBIALS) A nev APO for medium place aircraft environmental Sophisticated aircraft structure developments - control systems Combat aeroplanes [ASBE PAPEB 81-EHAS-1] A82-10889 A82-10309 closed loop environmental control systems for Fractographic determination of fatigue crack fighter aircraft growth rates in aircraft components [ASflE PAPEB 81-EHAS-2] A82-10890 A82-12697 Towards minimum power for environmental control in FATIGUE LIFE transport aircraft Acoustic emission - An emerging technology for [ASBB PAPEB 81-EHAS-4] A82-10892 assessing fatigue damage in aircraft structure Air-freon integrated environmental conditioning 482-11149 system for trainer subsonic aircraft Fatigue life of lags under service loading - Test [ASHE PAPEB 81-ENAS-33] A82-10920 results and predictions BBTIBOBBEBTAL TESTS A82-11685 Quantification of the thermal environment for FATIGUE TESTS externally carried aircraft stores and ordnance Superclean snperalloy powders by the rotating 482-12100 electrode process The Shock and fibration Digest, volume 13, no. 9 A82-12496 [AD-A105062] B82-10421 Batrix analysis of wings BPOXT BAIBXX COBPOSITE HATBBIA1S B82-10998 Kevlar composites; Proceedings of the Syoposium, FATT! ACIDS El Segundo, CA, December 2, 1980 A protective additive for jet fuels A82-12646 A82-12022 EQOATIOBS OF BOTIOB FADLT TOLBBAICB Optimal flight paths for winged, supersonic flight Synchronous fault-tolerant flight control systems vehicles - Extension to the case where thrust [AIAA 81-2109] A82-10083 can be vectored FEDBBAL BUDGETS A82-10310 Airport and Airway Improvement Act of 1981, part 1 On the question of trailing airplane motion [GPO-76-241-PT-1] N82-10062 A82-11470 NASA Authorization, 1982: Index EQUATIOBS OF STATE [GPO-84-713] H82-10959 On computing Flognet transition matrices of FEEDBACK COBTBOL rotorcraft closed loop environmental control systems for A82-11225 fighter aircraft BSTIBATIBG £ASHE PAPEB 81-EBAS-2] A82-10890 New estimation method for flutter or divergence Comparative study of flare control laws boundary from random responses at snbcritical [BASA-CB-164903] B82-10032 speeds Haiti-variable analysis and design technigues [NAL-TB-667T] B82-11034 [AGABD-lS-117] H82-10048 EXHAUST EBISSIOB The need for multivariable design and analysis Baseline data on utilization of low-grade fuels in technigues gas turbine applications. Volume 3: Emissions H82-10049 evaluation Characteristic and principal gains and phases and [DE81-903764] H82-1025U their use as multivariable control design tools EXHAUST GASES generalizing Hyguist and root-locus diagram Study of reingestion of exhaust gases with technigues different initial temperature in a reversed H82-10050 turbojet engine Multivariable design technigues based on singular A82-11444 value generalizations of classical control EXPABS1OB H82-10051 Design of airport pavements for expansive soils Limitations on achievable performance of [AD-A104660J 1182-11313 multivariable feedback systems EXPEBJBHCE N82-10052 Belationships between naval aviation safety and IQG-based mnltivariable design: Freguency domain pilot flight experience interpretation A82-11031 H82-10053 EXTEHMAl SIOBES LQG multivariable design tools Quantification of the thermal environment for H82-10051 externally carried aircraft stores and ordnance Design of high integrity mnltivariable control 482-12100 systems EXTBODIHG B82-10055 Superalloy turbine components - Which is the A geometric approach to maltivariable control superior manufacturing process, as-HIP, HIP plus system synthesis Isoforge, or 'gatorizing' of extrusion B82-10056 consolidated billet Hultivariables design: The optimization of A82-12497 approximate inverses H82-10057 Feedback and minimal sensitivity H82-10058 F-5 AIBCBAFT Design techniques for mntlivariable flight control F-5G Tigershark systems A82-12775 B82-11078 P-18 AIBCBAFT Practical design and realization of a digital Variable speed constant freguency /VSCF/ adaptive flight control system electrical system cuts cost of ownership 882-11079 A82-11719 FIBEB OPTICS FAILURE &BALISIS Optical sensors for displacement measurement Synchronous fault-tolerant flight control systems 482-11407 £AIAA 81-2109] A82-10083 Electronic master monitor and advisory display Unsolved problems of nickel cadmium batteries system, data transmission study A82-11725 [4D-A104243] H82-11064 Extending the limits of reliability theory • Book A82-12318

A-14 SUBJECT IHDEX FLIGHT TESTS

FIELD TBEOBI (PHIS1CS) Design considerations for optimal flight control Antenna theory and design Book systems A82-12323 H82-11077 FIGHTER JUBCRIFT Design techniques for mutlivariable flight control Analysis of augmented aircraft flying qualities systems through application of the Seal-Smith criterion H82-11078 [AIAA PAPEB 81-1776] A82-10462 Practical design and realization of a digital Closed loop environmental control systems for adaptive flight control system fighter aircraft H82-11079 [ASHE PAPEB 81-EHAS-2] A82-10890 Control law design for transport aircraft flight Dynamic response of aircraft structure to gun tasks shock loads H82-11080 A82-11314 Hanagement of redundancy in flight control systems The case for a defensive air-to-air fighter using optimal decision theory A82-12801 N82-11084 FILH COOLIHG FLIGHT CBEWS Air-film cooling returns to ramjets The all digital military aircraft [ASHE PAPEE 81-EBAS-8] A82-10896 A82-11937 FIHITE DIFFEBBBCE TBBOBI FLIGHT HAZABDS Finite difference computation of the steady Dovnbursts and microbursts - An aviation hazard transonic potential flow around airplanes downdrafts beneath thunderstorms H82-10981 482-10211 FIBITB BLEHEBT 8ETHOD Airborne if eat her radar and severe veather Applications of finite element method in aerospace penetration pover systems design A82-10219 A82-11717 FLIGHT IBSTBDHBBTS Application of numerical methods to the In-sitn calibration of flight heat transfer calculation of electrostatic fields in aircraft instrumentation fuel tanks [ASHE PAPEB 81-EBAS-13] A82-10901 [AD-A103270] H82-10033 FLIGBT BECHABICS Calculation of natural modes of vibration for On the question of trailinq airplane motion rotor blades by the finite element method A82-11470 [DFVLB-FB-81-07] B82-10452 FLIGHT OP1IBIZATIOB Structural analysis of fuselages with cutouts by Beal-time, on-line digital simulation of optimum finite element method maneuvers of supersonic aircraft H82-10995 [AIAA 81-2178] A82-10127 Structural analysis computer programs for rigid Helicopter icing spray system - Improvements and multicomponent pavement structures with flight experience discontinuities. IES1IQID and iESLAIEB. Beport A82-12696 1: Program development and numerical presentations Optimum climb and descent trajectories for airline [AD-A104545] B82-11498 missions FIBB PBEVBRIOH B82-11082 Bheological behavior of progressively FLIGHT PATHS shear-thickening solutions aircraft fuel Optimal flight paths for winged, supersonic flight polymer additives for fire protection in vehicles - Extension to the case where thrust survivable crashes can be vectored A82-11177 A82-10310 FLEXIBILITY FLIGHT SAFETY The effects of flexibility on the steady-state Applications of conventional and Doppler radars performance of small ribbon parachute models for aviation safety [AIAA PAPEB 81-1923] 482-10408 A82-10215 FLEXIBLE SPACECBAFT Detection and display of wind shear and turbulence Control design of flexible spacecraft A82-10222 H82-11081 Test Pilots' Aviation Safety Rorkshop, O.S. Baval FLIGHT CHABACTEBISTICS Postgraduate School, Monterey, C4, February Analysis of augmented aircraft flying qualities 25-28, 1981, Proceedings through application of the Heal-Smith criterion A82-10500 [AIAA PAPEB 81-1776] 482-10162 Belationships between naval aviation safety and Binqs in the sun - The evolution of Solar Challenger pilot flight experience A82-12694 A82-11031 FLIGHT COBTBOL A proposed flight safety program for the Korean KC-135 Avionics Bodernization Bot Bench Air Force [AIAA 81-2105] A82-10081 [AD-A102373] B82-10023 Synchronous fault-tolerant flight control systems FLIGHT SIHULATIOB [AIAA 81-2109] A82-10083 Beal-time, on-line digital simulation of optimum The Space Shuttle vehicle checkout involving maneuvers of supersonic aircraft flight avionics software [AIAA 81-2178] A82-10127 [AIAA 81-2111] A82-10100 Comparison of simulation and experimental data for High-efficiency hydraulic pover transfer units for a gliding parachute in dynamic flight multisystem aircraft [AIAA PAPEB 81-1924] A82-10409 A82-10853 Ideal and simulated performance of an aircraft in Developments in boundary layer Thrust Vector Control the terrain following mission A82-10855 482-11302 Control of electromechanical actuator elements for Fatigue life of lugs under service loading - Test flight vehicles Bnssian book results and predictions A82-12170 482-11685 The integrated inertial sensor assembly /USA/ - A FLIGBT TEST IBSTBOflBHTS redundant strapdovn system for advanced aircraft Outsider's look at flight instrumentation navigation and flight control functions [DE81-025409] B82-11066 A82-12642 FLIGHT TESTS Development and evaluation of automatic landing HiBAT onboard flight computer system architecture control laws for light winq loading STOL 'aircraft and qualification [HASA-CB-166160] H82-10043 [AIAA 81-2107] A82-10082 Flight trajectory control investigation A microprocessor-based data acquisition system for [AD-A104542] B82-110a8 stall/spin research Electronic master monitor and advisory display [AIAA 81-2177] A82-10126 .system, human engineering summary report [AD-A104244] B82-11065

A-15 FLIGHT TBAIHIHG SUBJECT IHDEI

The constricted rigging line trials technique for FLDIDIC CIRCUITS assessing the opening characteristics of Considerations and applications for the use of parachutes fluidics in aerospace controls [ilAA PAPEB 81-1932) A82-10413 A82-12087 Inflatable system for fast deployment of FLOTTEB parachutes at lov altitudes from slow moving Hew estimation method for flutter or divergence aircraft or stationary supports boundary from random responses at sabcritical [AIAA PAPEE 81-1953] A82-10428 speeds Dynamic response of aircraft structure to gun [HAL-TB-667T] B82-11034 shock loads FLOTTEB AiALISIS A82-11314 Experimental study of empennage snap-through History of flight testing the 1-1011 Tristar jet vibrations transport. II - Testing highlights since initial A82-11471 certification of the L-1011-1 An influence coefficient method for the A82-12049 application of the modal technique to wing FAA acceptance tests on the HAVSTAB GPS Z-Set flutter suppression of the DAST ABB-1 wing receiver [HASA-CB-165772] H82-11070 A82-12639 FLY BI BIBB COHTBOL Bing Laser Gyro Navigator /HLGB/ flight test results Flight test results of the model simulation 482-12614 controller for the HFB 320 for in-flight Flight test results of the model simulation simulation of the A310 airbus controller for the HFB 320 for in-flight [ESA-TT-660] 1182-10107 simulation of the 4310 airbus FLIIHG PLATFOBHS [ESA-TT-660] N82-10107 Parametric study of microwave-powered FLI6HI TBAIIIBG high-altitude airplane platforms designed for Spin recovery training licensing requirement linear flight [GPO-66-020] B82-10022 [HASA-TP-1918] H82-11050 FLOOBS FLIBBBBLS Evaluation of the acoustic measurement capability Low maintenance hydraulic accumulator of the HASA langley V/ST01 wind tunnel open test [AD-A103947] 1182-10034 section with acoustically absorbent ceiling and FOBEBODIBS floor treatments Reductions in parachute drag due to forebody wake [NASA-CB-165796] H82-10059 effects FLOODS! THBOBBH [AIAA PAPEB 81-1939] A82-10417 On computing Floquet transition matrices of FOBEIGH BODIES 'rotorcraft Coupled fluid/structure response predictions for A82-11225 soft body impact of airfoil configurations Numerical treatment of helicopter rotor stability ice and bird impact on aircraft engines problems A82-12039 A82-12045 FOSSIL FUELS FLOS DIStOBTIOB Baseline data on utilization of low-grade fuels in On evaluating the influence of local disruptions gas turbine applications. Volume 3: Emissions of flow over trailing edge and leading edge evaluation flaps from the data of wind tunnel tests of a [DE81-90376U] 882-10254 rectangular wing segment FOOBDATIOHS A82-11465 Design of airport pavements for expansive soils Amplified crossflow disturbances in the laminar [AD-4104660] H82-11313 boundary layec on swept wings with suction FBACTOGBAPHI [BASA-TP-1902] B82-11391 Fractographic determination of fatigue crack FLOS DISCBIBOTIOM growth rates in aircraft components On the prediction of swirling flowfields found in A82-12697 axisymmetric combustor geometries FBACTUBB STBB1GTH A82-12120 The application of improved aluminium alloys and Second order approximation theory of an arbitrary steels in aircraft structures aerofoil in compressible potential flow A82-10305 N82-10982 FBAHES An aerodynamic design method for transonic axial Thermal expansion accommodation in a jet engine flow compressor stage frame B82-10984 A82-11999 A comparison of theoretical and experimental FBEE FLOB pressure distributions for two advanced fighter Hultiple-scale turbulence modeling of free wings turbulent flows [BASA-TH-81331] N82-11054 [ASHE PAPEB 81-FE-20] A82-10934 PLOB EQOAXIOHS FBEOH Computation of high Reynolds number Air-freon integrated environmental conditioning internal/external flows system for trainer subsonic aircraft [HASA-TH-84049] 882-11046 [ASHE PAPEB 81-EHAS-33] A82-10920 FLO! GEOHBTBI FBEQOEHCI STABILITY. Thermal and flow analysis of a convection, 60 KVA 4DP permanent magnet TSCF starter generator air-cooled ceramic coated porous metal concept system - Generator system performance for turbine vanes characteristics [ASHE PAPEB 81-HT-48] A82-10952 A82-11721 FLOW VISOALIZATIOB FROHIS (HETEOBOLOGI) Experimental study of subsonic and transonic flows Gust front structure observed by Doppler radar past a wing A82-10223 A82-10363 FDEL COHSOHPTIOB Effects of vortex flaps on the low-speed Belicopter engine technology - Bith particular aerodynamic characteristics of an arrow wing reference to the Bolls-Boyce Gem engine [BASA-TP-1914] B82-11013 A82-10304 FLOBHETEBS Characteristics and trends of energy consumption Advanced fuel flowineter for future naval aircraft in transport missions with aircraft and surface [AD-A104364] H82-11063 vehicles FLUID DIHAHICS 482-101495 V/STOL aircraft and fluid dynamics A hidden advantage of permanent magnet electrical [NASA-TH-81328] H82-10029 generating systems FLUID POBEB A82-11720 Fluid power technology for the '80s Book Fuel conservation - DC-9 series 20/30/40 A82-10851 A82-12563

A-16 SUBJECT IIDEZ GUST LOADS

FUEL COHBOSIOI A new method of cooling turbine vanes 4 protective additive .for jet fuels H82-11027 482-12022 6AOSS BQUAHOI FOEL 646BS LQG-based multivariable design: Frequency domain Advanced fuel flowmeter for future .naval aircraft interpretation [4D-4104364] H82-11063 H82-10053 FOBL PBODUCTIOB LQG multivariable design tools Fuel foe future transport aircraft H82-10054 [4SBE P4PEB 81-HT-80] 482-10965 6EHEBAL AVIATIOB AIBCBAFT FOEL SPBATS A new APU for medium place aircraft environmental The dispersion of drop sizes in gas turbine fuel control systems nozzle; sprajs [ASHE PAPBB 81-EHAS-1] 482-10889 482-12107 Icing tunnel test of a glycol-exnding porous FOBL TASKS leading edge ice protection system on a general Application of numerical Methods to the aviation airfoil conducted in the Lewis calculation of electrostatic fields in aircraft Besearch .Center icing research tunnel fuel tanks [H4S4-CB-165444] H82-10021 [AD-A103270] H82-10033 General aviation aircraft antennas for the global FUSELAGES positioning system Experimental aodal analysis of the fuselage panels [HASA-TH-83212] H82-1 1339 of an Aero Commander aircraft GEOBEIBI [BASA-CB-165750] H82-10028 A solution to the static geometry problem for Structural analysis of fuselages with cutouts by JTIDS relative navigation finite element aethod 482-12634 H82-10995 The statistical theory of radio direction finding [AD-A104156] H82-10027 A geometric approach to umltivariable control system synthesis GAS COOLI8C B82-10056 A new nethod of cooling turbine vanes Aerodynamic calculations and design of subcritical H82-11027 aerofoils GAS FLO! H82-10983 Theoretical investigations and experimental GLASS FIBEB BEIIFOBCED PLASTICS researches for higher subsonic tvo-diaensional On the use of carbon composites in slat and compressor cascade stabilizer construction H82-11024 A82-11468 GAS TEHPEBATUBB GLIDIBG Study of reingestion of exhaust gases vith Comparison of simulation and experimental data for different initial temperature in a reversed a gliding parachute in dynamic flight turbojet engine [4144 PAPEB 81-1924] 482-10409 A82-11444 GLOBAL POSITIOIIiG SISTEB GAS TOBBIBE BBGIBBS National Aerospace fleeting, Trevose, PA, April Design considerations for duty cycle, life and 8-10, 1981, Proceedings reliability of small limited life engines A82-12626 [AI44 PAPEB 81-1402] A82-10465 Satellite geometry considerations for low cost GPS A new Apt) for medium place aircraft environmental user equipment control systeas A82-12630 [ASHE PAPEB 81-EBAS-1] 482-10889 FAA acceptance tests on the NATSTAB GPS Z-Set End losses in turbine cascades with porous cooling receiver A82-11434 482-12639 Basic problem of aircraft gastnrbine engine A navigation systems planning model analytic design. II 482-12640 482-11463 Integrated satellite navigation and strapdown The Civic.- 4 concept in vortex induced attitude and heading reference systems for civil combustion. II air carriers [ASBE P4PEB 81-GT-12] 482-11997 482-12643 Thermal expansion accommodation in a jet engine General aviation aircraft antennas for the global frame positioning system 482-11999 [BASA-TH-83212] H82-11339 The dispersion of drop sizes in gas turbine fuel GBOOHD BASED COHTHOL nozzle sprays HiHAT onboard flight computer system architecture 482-12107 and qualification Application of numerical modeling to gas turbine [4144 81-2107] 482-10082 coobnstor development problems GBOUBD TESIS 482-12118 Electrical ground testing of aircraft antistatic Validation studies of turbulence and combustion protection lodels for aircraft gas turbine combustors 482-10822 482-12267 GUATEMALA Commercial EDS considerations for snail gas Badar mapping, archaeology, and ancient land use turbine engines automated engine monitoring in the Baya lowlands systems [HASA-CB-164931] B82-11514 A82-12449 GUIDABCE SEHSOBS Further application and development of an engine The integrated inertial sensor assembly /USA/ - A usage/life monitoring system for military services redundant strapdown system for advanced aircraft A82-12450 navigation and flight control functions Superclean superalloy powders by the rotating A82-12642 electrode process GUBFIBE A82-12496 Dynamic response of aircraft structure to gun Lineup of the IB-series aircraft-derivative gas shock loads turbines A82-11314 A82-12560 COST LOADS Development of low modulus material for use in Crack growth evaluation of a method to convert ceramic gas path seal applications real-time loads history to a simplified [HASA-CB-165469] H82-10039 engineering spectra for aircraft structural Baseline data on utilization of low-grade fuels in analysis gas turbine applications. ?oluoe 3: Emissions A82-12043 evaluation Aeroacoustic theory for noncompact wing-gust [DB81-903764] H82-10254 interaction [FDBL-81-7] B82-11071

A-17 COSTS SUBJECT IHDBI

COSTS BELICOPTEB BHGIHES Gust front structure observed by Doppler radar Helicopter engine technology - with particular 182-10223 reference to the Bolls-Boyce Gen engine GTBOCOBPASSES A82-10304 Fast and accurate gyrocompass using strapdown HELICOPTEB PBBPOBHAHCE tuned rotor gyros as a solution to combat Helicopter rotor trailing edge noise helicopters navigation probleas [AIAA PAPEB 81-2001] A82-10455 A82-11927 numerical treatment of helicopter rotor stability GIBOSCOPES problems Problems relating to the classical rate-gyro A82-12045 A82-10497 Helicopter icing spray system - Improvements and Design and development of a low cost servoed rate flight experience gyro for unmanned aircraft A82-12696 A82-11932 HELICOPTEBS GTROSXABILIZEBS Hodel helicopter rotor impulsive noise Synthesis of system for evaluating gyrostabilizer A82-11300 state with unknown disturbances A comprehensive bibliography of literature on A82-11469 helicopter noise technology [AD-A103331] B82-10812 Botorcraft icing: status and prospects H [AGABD-AB-166] H82-11056 HABDSABE Helicopter rotor trailing edge noise noise Controlling the software/hardware interface for prediction the validation of avionics systems -•— in flight [HASA-CB-3470] H82-11859 control systems HFB-320 AIBCBAFT [AIAA 81-2159] A82-10116 System identification of the longitudinal motion HEAD-OP DISPLAYS of the DFVLB HFB 320 research aircraft with Study and development of an integrated head-up particular consideration of control surface display effectiveness [AD-A104337] 1182-11062 [ESA-TT-666J H82-10045 BEAT BICBAHGBBS Flight test results of the model simulation The enhancement of heat exchange in channels /2nd controller for the HFB 320 for in-flight revised and enlarged edition/ Bnssian book simulation of the A310 airbus A82-12222 [ESA-IT-660] H82-10107 A nev method of coding turbine vanes BI6H ALTITUDE BALLOOHS 1182-11027 A new thermal and trajectory model for high HEAT BESISTASI ALLOYS altitude balloons Powder metallurgy snperalloys - Aerospace [AIAA PAPEB 81-1926] A82-10411 materials for the 1980's; Proceedings of the BIGB POLIHEBS Conference, Zurich, Switzerland, November 18-20, Bheological behavior of progressively 1980. Volume 1 shear-thickening solutions aircraft fuel A82-12495 polymer additives for fire protection in Superclean snperalloy powders by the rotating survivable crashes electrode process A82-11177 A82-12496 HIGH STBBB6TB SSEELS Superalloy turbine components - Bhich is the The application of improved aluminium alloys and superior manufacturing process, as-HIP, HIP plus steels in aircraft structures Isoforge, or 'gatorizing' of extrusion A82-10305 consolidated billet BIGB TBHPEBATOBB BESSABCB A82-12497 Adaptation of a turbine test facility to Superalloy powder engine components; controls high-temperature research employed to assure high guality hardware [BAE-LIB-IBANS-2064] B82-11089 A82-12499 BIGB VOLTAGES HEAT TBA8SFEB High voltage surge and partial discharge test to In-situ calibration of flight heat transfer evaluate aerospace equipment parts instrument ation A82-11740 [ASHE PAPEB 81-EBAS-13] A82-10901 HOHEICOHB STBOCTOBES Thermal and flow analysis of a convection, Light aircraft structural design in non-metallics air-cooled ceramic coated porous metal concept - Ose of composite honeycomb for light aircraft for turbine vanes A82-10308 [ASHE PAPEB 81-HT-48] A82-10952 BOBIZOHTAL FLIGHT Results of experimental study of heat transfer to Analysis of augmented aircraft flying qualities turbine blades with porous cooling through application of the Seal-Smith criterion A82-11446 [AIAA PAPEB 81-1776] A82-10U62 HEAT TBAHSHISSIOH Parametric study of microwave-powered The enhancement of heat exchange in channels /2nd high-altitude airplane platforms designed for revised and enlarged edition/ Bnssian book linear flight A82-12222 [HASA-TP-1918] H82-11050 HEATIHG EQOIPHER HOBIZOHTAL TAIL SDBFACES Ice protection system technology A CFBP taileron for the Tornado: Construction and H82-11060 production -:— horizontal stabilizer Experimental study of fnel heating at low [BBB-FB-212/KFK/POB/2] 882-10035 temperatures in a wing tank model, volume 1 HOBS [HASA-CB-165391] H82-11224 Development of the Triflex rotor head HELICOPTEB COHTBOL A82-11222 Electronic master monitor and advisory display BOHAB PACTOBS EHGIHBBBI1G system, data transmission study Electronic master monitor and advisory display [AD-A104243] H82-11064 system, human engineering summary report Electronic master monitor and advisory display [AD-A104244] H82-11065 system, human engineering summary report HOHAI PEBFOBHAICB [AD-A104244] H82-11065 Relationships between naval aviation safety and BELICOPTEB DESIGB pilot flight experience An investigation of a stoppable helicopter rotor A82-11031 with circulation control ames 40 by 80 foot BDHAH BEACTIOIS wind tunnel Effects of aircraft noise on the equilibrium of [HASA-M-81218] H82-10030 airport residents: Testing and utilization of a new methodology [HASA-Tfl-76628] H82-11636

A-18 SUBJECT IBDBX IHTAKB SISTEBS

BTDBAOLIC COHIBOL Commercial EHS considerations for small gas High-efficiency hydraulic power transfer units for turbine engines automated engine monitoring multisystem aircraft systems A82-10853 A82-12449 HIDBADLIC EQOIPBEBT Further application and development of an engine Fluid pover technology for the '80s Book usage/life monitoring system for military services 482-10851 482-12450 Low maintenance hydraulic accumulator Electronic master monitor and advisory display [AD-A103947] N82-10034 system, data transmission study Aircraft digital input controlled hydraulic [AD-A104243] H82-11064 actuation and control system Electronic master monitor and advisory display [AD-4104263] H82-11072 system, human engineering summary report flIDBOCABBCS FOB! PBODCCTIOS [AD-A104244] 882-11065 Jet fuel from carbon IHCOBPBESSIBLE FLOH A82-12021 Theoretical analysis of parachute inflation Jet fuel locks to shale oil: The 1980 technology including fluid kinetics review [AIAA PAPEB 81-1925] A82-10410 [4D-A104414] H82-11228 Second order approximation theory of an arbitrary HIDBOGEH FUELS aerofoil in compressible potential flow Fuel for future transport aircraft 582-10982 [ASBE PAPEB 81-HT-80] A82-10965 IHCOHPBBSSIBLB FLUIDS HYDB06EBATIOB Calculation of aerodynamic characteristics of jet Jet fuel fron carbon flapped airplane 482-12021 A82-11459 INDEXES (DOCDBEBTATIOH) NASA Authorization, 1982: Index [GPO-84-713] N82-10959 ICE FOBHATIOH IHEHTIAL HAflGATION Helicopter icing spray systen - Improvements and Synthesis of system for evaluating gyrostabilizer flight experience state with unknown disturbances A82-12696 482-11469 Selected bibliography of NACA-HASA aircraft icing Ring Laser Gyro Navigator /BLGH/ flight test results publications 482-12644 [NASA-TB-81651] H82-11053 IHEBTIAl BEFEBENCB STSTEBS Botorcraft icing: Status and prospects Integrated satellite navigation and strapdown [A6ABD-AB-166] H82-11056 attitude and heading reference systems for civil Operational environment, neteorological conditions air carriers and weather forecasting 482-12643 H82-11057 INFLATABLE STBOCTOBES Technology base for icing instrumentation and Inflatable system for fast deployment of mathematical modelling parachutes at low altitudes from slow moving N82-11058 aircraft or stationary supports Facilities for development and clearance [4144 P4PEB 81-1953] 482-10428 H82-11059 INFLATING Ice protection system technology Theoretical analysis of parachute inflation 1182-11060 including fluid kinetics Proposed standard requirements and procedures for [4144 PAPEB 81-1925] A82-10410 icing clearance The constricted rigging line trials technique for N82-11061 assessing the opening characteristics of ICE PBEVERI01 parachutes Icing tunnel test of a glycol-exuding porous [AIAA PAPEB 81-1932] A82-10413 leading edge ice protection system on a general Stress measurements in a ribbon parachute canopy aviation airfoil conducted in the Lewis during inflation and at steady state Besearch Center icing research tunnel [AIA4 P4PEB 81-1944] 482-10420 [N4S4-CB-165444] H82-10021 INJECTOBS Icing tunnel tests of a composite porous leading One reason for the onset of high-frequency edge for use with a liquid anti-ice system self-excited oscillations in combustion Lewis icing research tunnel chambers of aircraft engines [NASA-CB-164966] 882-11052 A82-11448 Selected bibliography of HACA-MASA aircraft icing INLET FLOB publications A theoretical analysis of the stream surface of [NASA-TH-81651] H82-11053 revolution with supersonic inlet flow in a IBASE EHHAHCBHBHT transonic axial compressor Solution to the hidden-line problem N82-11025 A82-12803 A summary of V/STOL inlet analysis methods IBP4CT ACCELEBATIOB [H4S4-TH-82725] B82-11043 Limiting payload deceleration during ground impact INLET PBESSDBE [AIAA PAPEB 81-1918] 482-10404 Initial experimental research into the response of IHPACT DABAGE turbojet engine compressors to distortion of Impact-initiated damage thresholds in composites intake pressure 482-12028 H82-11006 IHPACT LOADS 4 preliminary experimental investigation of the Coupled fluid/structure response predictions for response of a turbojet engine to inlet pressure soft body impact of airfoil configurations distortion ice and bird impact on aircraft engines N82-11007 482-12039 INSPECTION IBPACT BESISTAICE Hathematical model for the maintenance program of Seven years experience vith Kevlar-49 in the modern jet aircraft crack detection; Lockheed L-1011 Tristar inspection intervals A82-12647 [DFVLB-FB-81-14] N82-10002 IHPACI TESTS IHSTBOBEHT LANDING SISTEBS Air bag impact attenuation system for the AQH-34V Discrete address beacon, navigation and landing remote piloted vehicle system [AI4A PAPEB 81-1917] 482-10403 482-10650 IH-M.I6HT BOHITOBIH6 IBTAEE SISTEBS Performance analysis of enroute air traffic Initial experimental research into the response of control computers in the Rational Airspace System turbojet engine compressors to distortion of •[4144 81-2203] 482-10140 intake pressure N82-11006

A-19 IBTBGHiL EQOATIOBS SDBJECT IBDBZ

IBTBGBAL EQOATIOBS KEVLAB (TB4BEHABK) A study on numerical method foe evaluating Kevlar composites; Proceedings of the Symposium, spanvise integral in subsonic lifting-surface Bl Segundo, C4, December 2, 1980 theory 482-12646 [BAL-TB-661T] H82-11035 Seven years experience with Kevlar-49 in the IHTB1LIGBHCB Lockheed 1-1011 Tristar interoperability testing of decentralized command, 482-12647 control, communications and intelligence /C3I/ KIBEH1TICS systems Analytical determination of undercarriage £4114 81-2205] 482-10143 retraction kinematics IHTEBPOL1TIOH 482-10364 Feedback and minimal sensitivity KOBEA H82-10058 4 proposed flight safety program for the Korean IHVEBSIOBS iir Force The net-skirt to a parachute canopy as a device to [4D-4102373] H82-10023 prevent inversion [AI44 PAPEB 81-1927] 482-10412 IHVISCID FLO! Theoretical analysis of parachute inflation L-1011 AIBCBAFT including fluid kinetics History of flight testing the L-1011 Tristar jet [AI&A P4PEE 81-1925] 482-10410 transport. II - Testing highlights since initial The arbitrary quasi-orthogonal surface method for certification of the L-1011-1 computing three-dimensional flou in turbine 482-12049 machinery. 2. Calculation of the Seven years experience with Kevlar-49 in the three-dimensional flow vith the S sub 1-surface Lockheed L-1011 Tristar twisted 482-12647 H82-11015 LABIB1B BOOBD&BI LAIEB Amplified crossflow disturbances in the lauinar boundary layer on swept wings with suction [HASA-TP-1902] B82-11391 JAGOUE AIBCB&FT LAHIBAB FLO! Digital avionics systems - The B4F experience On low-speed wind tunnels with deferrable boundaries A82-11941 482-11462 JET AIBCBAFT LABIB1TES Calculation of aerodynamic characteristics of jet Impact-initiated damage thresholds in composites flapped airplane 482-12028 482-11459 LABD OSB History of flight testing the 1-1011 Tristar jet Badar mapping, archaeology, and ancient land use transport. II - Testing highlights since initial in the Haya lowlands certification of the 1-1011-'! [BAS4-CH-164931] N82-11514 482-12049 LABDIBG AIDS JET AIBCBAFT HOISB Comparative study of flare control laws SEL and EPNL noise duration coefficients for the [BASA-CB-164903] H82-10032 747 and T-38 aircraft LABDIH6 GBAB [H4S4-TH-83214] H82-11860 The possibility of using deformable rubber JET EBGISE FDELS components in landing gear Fuel for future transport aircraft A82-10496 [ASHE P4PEB 81-HT-80] . 482-10965 LASEB GIBOSCOPES Jet fuel from carbon Bing Laser Gyro Bavigator /BLGB/ flight test results 482-12021 482-12644 A protective additive for jet fuels LATEBAL COHTBOL 482-12022 Procedures and analysis technigues for determining Experimental study of fuel heating at low static air minimum control speeds temperatures in a wing tank nodel, volume 1 482-12564 [BASA-CB-165391] B82-11224 LEAD ACID BATTERIES Jet fuel locks to shale oil: The 1980 technology Sealed lead-acid batteries for aircraft applications review A82-11716 [4D-4104414] B82-11228 LEADIBG EDGE SLATS in assessment of the use of antimisting fuel in On evaluating the influence of local disruptions turbofan engines of flow over trailing edge and leading edge [NASA-CB-165258] • B82-11230 flaps from the data of wind tunnel tests of a JET BBGIBES rectangular wing segment Thermal expansion accommodation in a jet engine A82-11465 frame On the use of carbon composites in slat and A82-11999 stabilizer construction Coupled fluid/structure response predictions for A82-11468 soft body impact of airfoil configurations LBADIIG EDGES ice and bird impact on aircraft engines Icing tunnel test of a glycol-exnding porous 482-12039 leading edge ice protection system on a general JET FLIPS aviation airfoil conducted in the Lewis Calculation of aerodynamic characteristics of jet Besearch Center icing research tunnel flapped airplane [HASA-CB-165444) . H82-10021 482-11459 Icing tunnel tests of a composite porous leading JET 1BPIBGBHEBT edge for use with a liquid anti-ice system Study of reingestion of exhaust gases with Lewis icing research tunnel different initial temperature in a reversed [HASA-CB-164966] B82-11052 turbojet engine LICEBSIBG 482-11444 Spin recovery training licensing regnirement JET VABBS [GPO-66-020] B82-10022 Effects of vane/blade ratio and spacing on fan noise LIFE CTCLE COSTS [AIA4 P4PEB 81-2033] 482-10457 Closed loop environmental control systems for fighter aircraft [ASHE PAPEB 81-EBAS-2] A82-10890 K Variable speed constant frequency /VSCF/ KEBBEL FDBCTIOBS electrical system cuts cost of ownership On the kernel function collocation method in A82-11719 steady subsonic flow for ving with control A hidden advantage of permanent magnet electrical surfaces generating systems B82-12023 A82-11720

4-20 SUBJECT IBDEX BATHBBATICAL BOO ELS

LIFE SUPPORT SISTBHS LOOPS Air supply system bite for Boeing 767 airplane The need for mnltivariable design and analysis Built-In-Test-Bguipment technignes [ASBE PAPEB 81-EHAS-7] A82-10895 B82-10049 LIFT Bultivariable design techniques based on singular A stud; on numerical method for evalaating value generalizations of classical control spanwise integral in subsonic lifting-surface B82-10051 theory Limitations on achievable performance of [HAL-TB-661T] H82-11035 multivariable feedback systems LIFT AOGBEBTATIOB B82-10052 An investigation of a stoppable helicopter rotor LQG-based multivariable design: Frequency domain with circulation control ames 40 by 80 foot interpretation wind tunnel H82-10053 .[BASA-TB-81218] H82-10030 LQG mnltivariable design tools LIFT DBAG RATIO H82-10054 A nodular asymmetric parachute for wind tunnel Design of high integrity multivariable control testing systems [AIAA PAPBB 81-1933] A82-10414 B82-10055 Increasing the lift:drag ratio of a flat delta wing LOB ALTITUDE 482-11899 Inflatable system for fast deployment of LIFTIIG BODIES parachutes at low .altitudes from slow moving Development of new lifting parachute designs with aircraft or stationary supports increased tria angle [AIAA PAPEB 81-1953] A82-10428 [AIAA PAPEB 81-1921] A82-10407 LOB SPEED STABILITY A Modular asymmetric parachute for wind tunnel Effects of vortex flaps on the low-speed testing aerodynamic characteristics of an arrow wing [AIAA PAPEB 81-1933] A82-10414 [BASA-TP-1914] H82-11013 LIGHT AIBCBAFI wind-tunnel results for a modified Soae possibilities for composite light aircraft 17-percent-thick low-speed airfoil section construction [BASA-TP-1919] B82-11033 A82-10307 LOB SPEED USD TOBBELS Light aircraft structural design in non-metallics On low-speed wind tunnels with deformable boundaries - Ose of composite honeycomb for light aircraft A82-11462 A82-10308 On evaluating the influence of local disruptions The possibility of using deformable rubber of flow over trailing edge and leading edge components in landing gear flaps from the data of wind tunnel tests of a A82-10496 rectangular wing segment Ezperinental modal analysis of the fuselage panels A82-11465 of an Aero Commander aircraft LOB TBHPEBATOBB EB7IBOBBBBTS [HASA-CH-165750] H82-10028 Experimental study of fuel heating at low LIGBTIIBG temperatures in a wing tank model, volume 1 Lightning effects on aircraft and composites. [BASA-CB-165391] B82-11224 Literature study on lightning strikes and LOGS protection advanced composite materials Fatigue life of lugs under service loading - Test [FOA-C-20388-F9] H82-10024 results and predictions LIBEAB EQOAIIOIS A82-11685 LQG-based nultivariable design: Frequency domain interpretation H82-10053 M LQG mnltivariable design tools BAGBBTS H82-10054 A hidden advantage of permanent magnet electrical LIHEAB SISTEBS generating systems Limitations on achievable performance of A82-11720 multivariable feedback systems 60 KV4 ADP permanent magnet VSCF starter generator H82-10052 system - Generator system performance Design of high integrity mnltivariable control characteristics systems A82-11721 H82-10055 BAH BACHIIB SISTEBS A geometric approach to multivariable control Improving the BLS through enhanced cockpit displays system synthesis A82-10649 H82-10056 BABOAL COBTEOL Bultivariables design: The optimization of Improving the BLS through enhanced cockpit displays approximate inverses A82-10649 B82-10057 Control law design for transport aircraft flight Feedback and minimal sensitivity tasks B82-10058 B82-11080 Theory of stochastic optimal control some basic BASS DISTRIBOIIOB notions Experimental determination of parachute apparent H82-11075 mass and its significance in predicting dynamic LIQUID HIDBOGEB stability Fuel for future transport aircraft [AIAA PAPEB 81-1920] A82-10406 [ASBE PAPEB 81-HT-80] A82-10965 BATCHIBG LOAD TESTS Strong matching method for computing transonic Fatigue life of lugs under service loading - Test viscous flows including wakes and separations - results and predictions Lifting airfoils 482-11685 A82-10821 LOBGIIODIBAL COBTBOL HATEBIALS TESTS Systea identification of the longitudinal motion The possibility of using deformable rubber of the DFVLB BFB 320 research aircraft vith components in landing gear particular consideration of control surface A82-10496 effectiveness BATBEBATICAL BODELS [ESA-TT-666] B82-10045 A mathematical model of an over-sea airborne DBF LOBGITDDI1AL STABILITY radio link Active control elements on the transonic wing of A82-11406 the Airbus A-300 (ACTTA A). Airbus A-300 with Validation studies of turbulence and combustion reduced longitudinal stability (ACTTA-C) models for aircraft gas turbine coabnstors advanced control transonic transport aircraft A82-12267 (ACCTA); design considerations B82-10044

A-21 BATBICBS (BATHEBATICS) SUBJECT IHDBZ

Hatfaeaatical model for the maintenance program of The evolution of airborne weather avoidance radar modern jet aircraft crack detection; toward a calibrated remote rain gauge using BEACT inspection intervals Bain Echo Attenuation Compensation Hardware [DF7LB-FB-81-14] H82-10002 A82-10225 A contribution to the stabilization of flight BETEOBOLOGICAL BESBABCH AIBCBAFT vehicle parachute systems mathematical models Description of the meteorological research radar [ESA-TT-679] B82-10046 system aboard HOAA/Besearch Facilities Center Technology base for icing instrumentation and BP-3D aircraft mathematical modelling A82-10217 N82-11058 HEXICO Aeroacoustic theory for noncompact wing-gust Badar mapping, archaeology, and ancient land use interaction in the Haya lowlands [FDBL-81-7] N82-11071 [8ASA-CB-164931] H82-11514 Integrated analysis of engine BICBOBETBOBOLOGY [NASA-TH-82713] B82-11491 Downbursts and microbursts - An aviation hazard Structural analysis computer programs for rigid downdrafts beneath thunderstorms mnlticomponent pavement structures with A82-10214 discontinuities, WESLIQID and iESLAYEB. Report BICBOPBOCESSOBS 1: Program development and numerical presentations A microprocessor-based data acquisition system for [AD-A104545] H82-11498 stall/spin research BATBICES (BATHBBATICS) [AIAA 81-2177] A82-10126 On computing Floguet transition matrices of Navigation task partitioning in rotorcraft distribnted-processing avionics systems A82-11225 A82-10646 HAXBIZ BBTHODS HICB01AVE LAHDIBG SISTEBS The automatic matrix force method and techniques Improving the BLS through enhanced cockpit displays for handling more complex computations with A82-10649 given computer capacity BICBOiAVE TBABSBISSIOH 882-10994 Parametric study of microwave-powered BAIiElL EOOATIOH high-altitude airplane platforms designed for Antenna theory and design Book linear flight A82-12323 [NASA-TP-1918] B82-11050 HEASOR1BG IBSTBDBEHTS BILITABI AIBCBAFT Technology base for icing instrumentation and Automated Paint and Process Line /APPL/ for mathenatical modelling aircraft production N82-11058 [AIAA 81-2166] 482-10120 BECHABICAL DEVICES Sophisticated aircraft structure developments - A comprehensive bibliography of literature on Combat aeroplanes helicopter noise technology A82-10309 [AD-A103331] H82-10812 Sealed lead-acid batteries for aircraft applications BECBABICAL PBOPBBTIES A82-11716 Snperalloy turbine components - ihich is the Advanced aircraft electric power system superior manufacturing process, as-HIP, HIP plus A82-11718 Isoforge, or 'gatorizing1 of extrusion The all digital military aircraft consolidated billet A82-11937 A82-12497 ACHi - Fact or fantasy Advanced Snperalloy ponder engine components; controls Civilian/Military Aircraft employed to assure high gnality hardware 482-12048 A82-12499 Further application and development of an engine BETA! FATIGUE usage/life monitoring system for military services Fatigue substantiation of non-linear structures A82-12450 A82-11224 BILITABY AVIATION A note on fatal aircraft accidents involving metal Relationships between naval aviation safety and fat igue pilot flight experience A82-11400 A82-11031 BETAL POSDEB HILITAHY HELICOPTERS Superclean snperalloy powders by the rotating Fast and accurate gyrocompass using strapdown electrode process tuned rotor gyros as a solution to combat A82-12496 helicopters navigation problems BBTALLIZIHG A82-11927 Electrical ground testing of aircraft antistatic BILITABI OPEBATIOBS protection The case for a defensive air-to-air fighter A82-10822 A82-12801 BETEOBOLOGICAL EAEABETEBS BILITABY TECHBOLOGI Botorcraft icing: Status and prospects Implementation of AVBADCOB HHST for military [AGABD-AB-166] H82-11056 aircraft parts production engineering Operational environment, meteorological conditions A82-10545 and weather forecasting The all digital military aircraft 1182-11057 A82-11937 BETEOBOLOGICAL BADAB Digital avionics systems - The BAF experience Applications of conventional and Doppler radars A82-11941 for aviation safety Parachute technology under pressure A82-10215 A82-12804 Description of the meteorological research radar BIHICOHPDTBBS system aboard NOAA/Besearch Facilities Center The use of the Reber method for HP-3D aircraft minicomputer-assisted numerical analysis of A82-10217 airfoils Airborne weather radar and severe weather A82-10362 penetration BIBIBAI TECHBIQOE A82-10219 Feedback and minimax sensitivity An airport wind shear detection and warning system H82-10058 using Doppler radar BISSILB BODIES A82-10220 Nonlinear prediction of subsonic aerodynamic loads Instrumented aircraft verification of clear-air on wings and bodies at high angles of attack radar detection of low-level wind shear A 82-11359 A82-10221 HISSILB DESIGH Design considerations for doty cycle, life and reliability of small limited life engines [AIAA PAPEB 81-1402] A82-10465

A-22 SDBJBCT IBDEX OHEGA BAVIGATIOB SISTEB

Outsider's look at flight Instrumentation BOISE POLLOTIOS [DE81-025109] N82-11066 A comprehensive bibliography of literature on HOLDS helicopter noise technology Hew molding oethod of three-dimensional hollow [AD-A103331] H82-10812 photoelastic model and centrifugal stress Effects of aircraft noise on the equilibrium of analysis of air cooled turbine blade model airport residents: Testing and utilization of a [HAL-IB-127T] H82-11067 new methodology HOBOPLAHBS [HASA-TH-76628] H82-11636 Analytical determination of undercarriage BOISE PBEDICTIOB (AIRCBAPT) retraction kinematics Helicopter rotor trailing edge noise 482-10364 [AIAA PAPEB 81-2001] 182-10155 HBCi AIBCBAF1 Botor wake characteristics relevant to A CFBP taileron for the Tornado: Construction and rotor-stator interaction noise generation production horizontal stabilizer [AIAA PAPEB 81-2031] A82-10156 [HBB-FE-212/KFK/POB/2] 1182-10035 Effects of vane/blade ratio and spacing on fan noise HDLTIEBGIBE VEHICLES [AIAA PAPEB 81-2033] A82-10157 Procedures and analysis techniques for determining Helicopter rotor trailing edge noise noise static air minimum control speeds prediction A82-12561 [NASA-CB-3170] N82-11859 HOLTIPBOCESSIHG (COBPOTEBS) BOISE BBDOCTIOH Airborne associative processor /SSEBO/ for 'Quiet please1 aircraft hydraulic systems early warning radar surveillance, command, and noise reduction control applications A82-10851 [AI4A 81-2115] A82-10101 Design predictions foe noise control in the navigation task partitioning in cryogenic National Transonic Facility distribnted-processing avionics systems A82-12025 A82-10616 Experimental modal analysis of the fuselage panels of an Aero Commander aircraft CHASA-CB-165750} N82-10028 N Comparative study of flare control laws BACEL1ES [NASA-CB-161903] N82-10032 Low speed testing of the inlets designed for a A comprehensive bibliography of literature on tamden-fan V/STOL nacelle conducted in the helicopter noise technology Lewis 10 by 10 foot wind tunnel [AD-A103331] H82-10812 [NASA-TH-82728] H82-11012 BOISE SPECTBA HASA PBOGHiBS SEL and EPBL noise duration coefficients for the HASA Authorization, 1982: Index 717 and T-38 aircraft [GPO-81-713] H82-10959 [NASA-TH-83211] 1182-11860 BATIOBAL AIBSPACE UTILIZATION SISTEH BOBLIBEAB SISTEHS Performance analysis of enroute air traffic Fatigue substantiation of non-linear structures control computers in the National Airspace System A82-11221 [AIAA 81-2203] A82-10110 A geometric approach to multivariable control BATIOBAL AVIATION SISTEH system synthesis Airport and Airway Improvement Act of 1981, part 1 1182-10056 [GPO-76-211-PT-1] H82-10062 Theory of stochastic optimal.control some basic HAVIER-STOKES EQOATIOH notions Computation of high Reynolds nnnber 882-11075 internal/external flows Application of nonlinear systems inverses to [HASA-TH-81019] N82-11016 automatic flight control design: System BAVIGATIOB concepts and flight evaluations Flight trajectory control investigation N82-11083 [AD-A101512] H82-11018 HOZZLE DBSIGB An overview of optimal control in aerospace systems Developments in boundary layer Thrust Vector Control H82-11071 A82-10855 HAVIGATIOH AIDS BOHEBICAL ABALISIS Three navigation systems and their costs of The use of the Heber method for acquiring remote sensing data minicomputer-assisted numerical analysis of A82-10019 airfoils BAVSTAB SATELLITES A82-10362 FAA acceptance tests on the NAVSTAB GPS Z-Set Numerical treatment of helicopter rotor stability receiver problems A82-12639 A82-12015 BETS Procedures and analysis techniques for determining The net-skirt to a parachute canopy as a device to static air minimum control speeds prevent inversion A82-12561 [AIAA PAPEE 81-1927] A82-10112 The need for multivariable design and analysis BETBOBK COBTBOL techniques A solution to the static geometry problem for N82-10019 JTIDS relative navigation HOHEBICAL FLOi fISOALIZATIOI A82-12631 A numerical three-dimensional turbulent simulation BICKEL CADHIOB BATTBBIES of a subsonic VSTOL jet in a cross-flow using a Unsolved problems of nickel cadmium batteries finite element algorithm A82-11725 [AD-A101511] H82-11055 BOISE GEHEBATOBS BICOIST DIA6BAH Botor wake characteristics relevant to Characteristic and principal gains and phases and rotor-stator interaction noise generation their use as maltivariable control design tools [AIAA PAPEE 81-2031] A82-10456 generalizing Nyquist and root-locus diagram A comprehensive bibliography of literature on techniques helicopter noise technology H82-10050 [AD-A103331] H82-10812 BOISE HEASOBBHBBT Hodel helicopter rotor impulsive noise 482-11300 OH-58 HELICOPTEB SEL and EPBL noise duration coefficients for the Composite main rotor tubular braided 717 and T-38 aircraft A82-10517 [HASA-Tfl-83211] B82-11860 OHEGA HAVIGATIOH SISTBB Omega station 10.2 kHz signal selection made easy A82-12638

A-23 OBBOABD DAIA PBOCBSSIBG SUBJECT IBDBX

OBBOABD DATA PBOCBSSIBG Comparison of simulation and experimental data for Description of the meteorological research radar a gliding parachute in dynamic flight system aboard NOAA/Besearch Facilities Center [AIAA PAPEB 81-1924] A82-10409 HP-3D aircraft Theoretical analysis of parachute inflation A82-10217 including fluid kinetics navigation task partitioning in [AIAA PAPEB 81-1925] A82-10V10 distributed-processing avionics systems The constricted rigging line trials technique for 482-10646 assessing the opening characteristics of OPEBIBGS parachutes Structural analysis of fuselages with cutouts by [AIAA PAPEB 81-1932] A82-10413 finite element method Seductions in parachute drag due to forebody wake N82-10995 effects OPTICAL BEiSOEIHG IHSTEOHBIIS [AIAA PAPEB 81-1939] A82-10417 Optical sensors for displacement measurement Aeroballistic characteristics of sonobuoy A82-11407 parachute decelerators limited to a length of OPTIMAL COHTBOL three feet Design of high integrity naltivariable control IAIAA PAPEB 81-1950] A82-10425 systems Inflatable system for fast deployment of H82-10055 parachutes at low altitudes from slow moving Haitivariables design: The optinization of aircraft or stationary supports approximate inverses [AIAA PAPEB 81-1953] A82-10H28 N82-10057 A contribution to the stabilization of flight Flight trajectory control investigation vehicle parachute systems mathematical models [AD-A104542] H82-11048 [ESA-TT-679] H82-10046 Theory and applications oJ optimal control in PABACHOTE EABBICS aerospace systems Stress measurements in bias constructed parachute [AGABD-AG-251] H82-11073 canopies daring inflation and at steady-state An overview of optimal control in aerospace systems [AIAA PAPEB 81-1945] A82-10421 H82-11074 Development of a nylon-Kevlar recovery system for Theory of stochastic optimal control some basic the CL-289 /AH/OSD 502/ surveillance drone notions [AIAA PAPEB 81-1952] A82-10427 H82-11075 PABACBOTBS An introduction to stochasic optimal control theory Experimental determination of parachute apparent N82-11076 mass and its significance in predicting dynamic Design considerations for optimal flight control stability systems [AIAA PAPEB 81-1920] A82-10406 H82-11077 Development of new lifting parachute designs with Design technigues for mutlivariable flight control increased trim angle systems [AIAA PAPEB 81-1921] A82-10407 H82-11078 The net-skirt to a parachute canopy as a device to Control lav design for transport aircraft flight prevent inversion tasks [AIAA PAPEB 81-1927] A82-10412 H82-11080 A modular asymmetric parachute for wind tunnel Control design of flexible spacecraft testing H82-11081 [AIAA PAPEB 81-1933] A82-10414 Optimum climb and descent trajectories for airline Parachute technology under pressure missions A82-12804 N82-11082 PABABBTBB IDEBTIFICATIOg Hanagement of redundancy in flight control systems Parametric study of microwave-powered using optimal decision theory high-altitude airplane platforms designed for 1182-11084 linear flight OPTIBIZATIOB [NASA-TP-1918] H82-11050 Optimization of the principal design parameters of PABAHETEBIZATIOH a passenger aircraft Estimation of airplane stability and control A82-10816 derivatives from large amplitude longitudinal OBGABIC LIQUIDS maneuvers Bheological behavior of progressively [HASA-TH-83185] S82-10042 shear-thickening solutions aircraft fuel PABTIC1E SIZE DISTBIBOTIOI polymer additives for fire protection in Determination of vertical profiles of aerosol size survivable crashes spectra from aircraft radiative flux A82-11177 measurements. II - The effect of particle OBTHOGOBALIIZ nonsphericity The arbitrary guasi-orthogonal surface method for A82-12149 computing three-dimensional flov in turbine PASSEBGEB AIBCBAFT machinery. 2. Calculation of the How large should a commuter transport be three-dimensional flow with the S sub 1-surface [AIAA PAPEB 81-1732] A82-10463 twisted Optimization of the principal design parameters of H82-11015 a passenger aircraft A82-10816 Lightweight diesel engine designs for commuter type aircraft PAIBIS [HASA-CB-165470] H82-11068 Automated Paint and Process Line /APPL/ for PA7EBEBIS aircraft production Design of airport pavements for expansive soils [AIAA 81-2166] A82-10120 [AD-A104660] H82-11313 PAHELS Structural analysis computer programs for rigid aesponse of nonlinear aircraft structural panels •ulticomponent pavement structures with to high intensity noise discontinuities, iESLIQID and BESLAIEB. Report A82-12041 1: Program development and numerical presentations PABACBOTE DESCENT [AD-A104545] B82-11498 Aerodynamics and performance of cruciforn PAILOADS parachute canopies Limiting payload deceleration during ground impact CAIAA PAPEB 81-1919] A82-10105 [AIAA PAPEB 81*1918] A82-10404 Experimental determination of parachute apparent PEBFOBHAHCE PBEDICTIOB nass and its significance in predicting dynamic Ideal and simulated performance of an aircraft in stability the terrain following mission [AIAA PAPEE 81-1920] 482-10106 A82-11302

A-24 SOBJECT IBDEI FBESSOBE DISTBIBOTIOI

On the prediction of swirling flowfields found in POLIOBBTHAHB FOAB axisymmetric conbustor geometries Polyurethane foams for aircraft shock mounts. 3: A82-12120 Vibration damping by polyether foams Parametric stadj of microwave-powered [AD-AKW96] H82-11212 high-altitude airplane platforms designed for POBODS BATEBIALS linear flight Development of- low modulus material for use in [HASA-TP-1918J H82-11050 ceramic gas path seal applications PBBFOBBAICB TESTS [HASA-CB-165469J H82-10039 Interoperability testing of decentralized command, Icing tunnel tests of a composite porous leading control, communications and intelligence /C3I/ edge for use with a liguid anti-ice system syste»s Lewis icing research tunnel [AIAA 81-2205] A82-10143 [HASA-CB-164966] 882-11052 Air bag impact attenuation system for the AQH-34V POBOOS HALLS remote piloted vehicle Thermal and flow analysis of a convection, [AIAA PAPEB 81-1917] i82-10403 air-cooled ceramic coated porous metal concept Aerodynamics and performance of cruciform for turbine vanes parachute canopies [ASHE PAPEB 81-HT-48] A82-10952 [AIAA PAPBB 81-1919] 482-10405 End losses in turbine cascades with porous cooling The constricted rigging.line trials technique for A82-11434 assessing the opening characteristics of Besults of experimental study of heat transfer to parachutes turbine blades with porous cooling [AIAA PAPEB 81-1932] 482-10413 A82-114U6 High-efficiency hydraulic power transfer units for POSIIIOH (LOCATIOB) multisystem aircraft A solution to the static geometry problem for A82-10853 JTIDS relative navigation The certification of digital systems A82-12634 A82-11940 The statistical theory of radio direction finding FAA acceptance tests on the HAVSIAB GPS z-Set [AD-A104156] H82-10027 receiver POTEBTIAL FLOH A82-12639 Finite difference computation of the steady PEBTOBBATIOB IHEOBI transonic potential flow around airplanes Synthesis of system for evaluating gyrostabilizer H82-10981 state with unknown disturbances Second order approximation theory of an arbitrary 482-11469 aerofoil in compressible potential flow PHOXOELASIICIII 1182-10982 Hen molding method of three-dimensional hollow Aerodynamic calculations and design of subcritical photoelastic model and centrifugal stress aerofoils analysis of air cooled turbine blade model H82-10983 [HAL-TB-U27T] H82-11067 POBDEB HB1ALLOBGI PILOT TBAIIIHG Powder metallurgy superalloys - Aerospace Spin recovery training licensing requirement materials for the 1980's; Proceedings of the [GPO-66-020] H82-10022 Conference, Zurich, Switzerland, November 18-20, PILOTS (PBHSOHSBL) 1980. Volume 1 Development and construction of pilot ejector A 82-12195 seats in Germany from 1938-1945 Snperclean snperalloy powders by the rotating [DFVLB-FB-81-04] H82-10026 electrode process PISTOH BHGIHBS A82-12496 The CIVIC - A concept in vortex induced Superalloy turbine components - Hhich is the combustion. II superior manufacturing process, as-HIP, HIP plus [ASHE PAPEB 81-GT-12] A82-11997 Isoforge, or 'gatorizing' of extrusion PLAIBTART BOOBDABI 1ATEB consolidated billet. Multiple Doppler radar observations of PEL structure A82-12197 A82-10292 Superalloy powder engine components; controls PLAIIHG employed to assure high quality hardware A navigation systems planning model A82-12499 482-12640 POIBB EFFICIEBCI PLASHA SPBATIHG Helicopter engine technology - Hith particular Thermal-barrier-coated turbine blade study reference to the Bolls-Bpyce Gem engine [HASA-CB-165351] H82-10010 A82-10304 PLASTIC AIBCBAFI STBOCTOBES 60 RVA ADP permanent magnet VSCF starter generator On the use of carbon composites in slat and system - Generator system performance stabilizer construction characteristics 482-11468 A82-11721 Seven years experience with Kevlar-49 in the PBECIPITAIIOB (HBTBOBOLOGI) Lockheed L-1011 Iristar The evolution of airborne weather avoidance radar A82-12647 toward a calibrated remote rain gauge using BEACT PLOTTIBG Bain Echo Attenuation Compensation Hardware Bultivariable design techniques based on singular A 82-1022 5 value generalizations of classical control PBEOICIIOB ABALISIS TECBBIQOBS B82-10051 A new thermal and trajectory model for high PBBOHiTIC EQOIPDEHT altitude balloons A new APO for medium place aircraft environmental [AIAA PAPEB 81-1926] A82-10411 control systems PBESSOBB DISTBIBOTIOB [ASHE PAPEB 81-EHAS-1] A82-10889 The use of the ieber method for Towards minianm power for environmental control in minicomputer-assisted numerical analysis of transport aircraft airfoils [4SHE PAPEB 81-EB4S-4] A82-10892 A82-10362 Air supply system bite for Boeing 767 airplane Aerodynamic calculations and design of subcritical Built-in-Test-Equipment aerofoils [ASHE PAPEB 81-EBAS-7] A82-10895 H82-10983 POLLOTIOB COBTBOL Initial experimental research into the response of Baseline data on utilization of low-grade fuels in turbojet engine compressors to distortion of gas turbine applications. Volume 3: Emissions intake pressure evaluation H82-11006 [DE81-903764] 882-10254 A preliminary experimental investigation of the POLTBTHEB BESIHS response of a turbojet engine to inlet pressure Polyurethane foams for aircraft shock mounts. 3: distortion Vibration damping by polyether foams H82-11007 [AD-A10U496] 882-11212

A-25 PBESSDBE OSCI1LATIOBS SUBJECT IHDBI

A comparison of theoretical and experimental pressure distributions for two advanced fighter wings R [NASA-TH-81331 ] B82-11054 B&DAB AfTEHOATIOH PBESSDBE OSCILL1TIOBS The evolution of airborne weather avoidance radar One reason for the onset of high-frequency tovard a calibrated remote rain gauge using REACT self-excited oscillations in conbustion Bain Echo Attenuation Compensation Hardware chambers of aircraft engines A82-10225 A82-11UH8 BADAB DATA PBESSOBB BBDOCTIOB Description of the meteorological research radar Thermal and flow analysis of a convection, system aboard HOAA/Besearch Facilities Center air-cooled ceramic coated porons metal concept BP-3D aircraft for turbine vanes A82-10217 [ASME PAPEB 81-HT-48] A82-10952 BADAB DETECTION PRESSDBIZBD CABIBS Instrumented aircraft verification of clear-air Air supply system bite for Boeing 767 airplane radar detection of low-level wind shear Built-In-Test-Equipment A82-10221 [ASHE PAPEB 81-ENAS-7] A82-10895 BADAB HAPS PBOBABILITI TBBOBI Badar mapping, archaeology, and ancient land use Extending the limits of reliability theory Book in the Haya lowlands A82-12318 [HASA-CB-164931] H82-11514 PBOCBDDBBS BADAB HEASOBBBEBT Proposed standard requirements and procedures for Baltiple Doppler radar observations of PBL structure icing clearance A82-10292 H82-11061 BADAB TAB6E1S PBODOCT DE?BLOPBBBT Synthetic aperture radar target simulator Study and development of an integrated head-up [ HASA-CASB-HPO-1502U-1] H82-10286 display BADAB TBACKIBG [AD-A104337] B82-11062 Bard limited approaches to correlation velocity Integrated analysis of engine sensing [SASA-TH-82713] H82-11491 A82-12636 PBOOOCIIOB EHGIBEEBIHG BADIAHT FLUX DEBSITY Automated Paint and Process Line /APPI/ for Determination of vertical profiles of aerosol size aircraft production spectra from aircraft radiative flux [AIAA 81-2166] S82-10120 measurements. II - The effect of particle Development of aircraft production engineering nonsphericity discipline at IIT, Bombay A82-12149 482-11317 BADIO DIBBCTIOB FIBDBBS A CFBP taileron for the Tornado: Construction and The statistical theory of radio direction finding production horizontal stabilizer [AD-A104156] 882-10027 [HBB-FE-212/KFK/POB/2] H82-10035 BADIO BA?I6ATIOB PBOGBAH YBBXFICailOB (COHPDTEBS) Omega station 10.2 kHz signal selection made easy The Space Shuttle vehicle checkout involving A82-12638 flight avionics software FAA acceptance tests on the BAVSTAB GPS Z-Set [AlfiA 81-2141] A82-10100 receiver PBOJECT HABAGBBBBI A82-12639 Implementation of AVBADCOH MH6T for military BADIO BECBIVBBS aircraft parts production engineering Tangential sensitivity of El receivers A82-10545 A82-11020 PBOPBUEB FAHS FAA acceptance tests on the HAVSTAB GPS Z-Set Propfan installation aerodynamics of a receiver supercritical swept wing transport configuration A82-12639 [AIAA PAPEB 81-1563] A82-10466 BADIO BEIAI SISIEHS PBOPULSIYE BFFICIEBCI A mathematical model of an over-sea airborne OHF Quiet short-haul research aircraft familiarization radio link document, revision 1 A82-1U06 [HASA-TH-81298] 882-10031 BADIO TBACKIBG Propulsion study for Small Transport Aircraft The statistical theory of radio direction finding Technology (STAT), Appendix B [AD-A10K156] H82-10027 [HASA-CB-165499-APP-B] 882-10038 BAIB PROTECTIVE COATIH6S Airborne weather radar and severe weather Thermal-barrier-coated turbine blade study penetration [MASA-CB-1 65351] M82-10040 A82-10219 PBOTOBEBAHCES BAIB GAGES Aircraft excrescence drag The evolution of airborne weather avoidance radar [AGABD-AG-264J H82-10020 toward a calibrated remote rain gauge using BEACT PDHPS Bain Echo Attenuation Compensation Hardware High-efficiency hydraulic power transfer units for A82-10225 multisystem aircraft BABJBT EBGIBBS A82-10853 Air-film cooling returns to ramjets [ASHE PAPEB 81-BHAS-8] A82-10896 An investigation of the combustion process in solid fuel ramjets QOADBMIC EQOATIOHS [AD-A104603] H82-11232 LQG-based multivariable design: Frequency domain BEA1 IIBB OPEBATIOH interpretation Seal-tine, on-line digital simulation of optimum H82-10053 maneuvers of supersonic aircraft LQS multivariable design tools [AIAA 81-2178] A82-10127 B82-10054 BECIBCOLATIVE FLOID FLOi QOIBT EHGIBE PBOGBAB On the prediction of swirling flovfields found in Quiet short-haul research aircraft familiarization axisymnetric combustor geometries document, revision 1 A82-12120 [HASA-TH-81298] H82-10031 BBCOTBBZ PABACHOSBS Development of a uylon-Kevlar recovery system for the CL-289 /AH/USD 502/ surveillance drone [AIAA PAPEB 81-1952] A82-10U27

A-26 SUBJECT I1DBI BOTATIBG FIDIDS

BBCTASGOLAB FUSES BBEOLOGI Response of nonlinear aircraft structural panels Bheological behavior of progressively to high intensity noise shear-thickening solutions aircraft fuel A82-12041 polymer additives for fire protection in BBCTABGOLAB 1I8SS snrvivable crashes On evaluating the influence of local disruptions A82-11177 of flov over trailing edge and leading edge BIBBOI PABACHOTBS flaps from the data of wind tunnel tests of a The effects of flexibility on the steady-state rectangular wing segment performance of saall ribbon parachute models A82-11465 [AIAA PAPEB 81-1923] A82-10408 Experimental investigations of the separated flow Stress measurements in a ribbon parachute canopy around a rectangular wing in a wind tunnel during inflation and at steady state [DF7LB-FB-81-12] 1182-10017 [AIAA PAPEB 81-1944] A82-10420 BEDOIDAHCY BI6ID BOIOBS Banagement of redundancy in flight control systems Development of the Triflex rotor head using optimal decision theory A82-11222 B82-11084 BIHG LASEBS BEGISIEBS Bing Laser Gyro Bavigator /BLGH/ flight test results Air-breathing engine test facilities register. A82-12644 [AGABD-&G-269J N82-10063 BOBOSTBESS (HATBBHAIICS) BEGBBSSIOB AI4LYSIS Limitations on achievable performance of Determination of airplane model structure from multivariable feedback systems flight data by using modified stepwise regression H82-10052 [HASA-TP-1916] H82-10041 SOCKET EBGIBES Estimation of airplane stability and control The enhancement of heat exchange in channels /2nd derivatives from large amplitude longitudinal revised and enlarged edition/ Bussian book maneuvers A82-12222 [HASA-Tfl-83185] 882-10042 SOCKET 1OZZLES BBLIABILITY ABALYSIS Developments in boundary layer Thrust Vector Control Extending the limits of reliability theory Book A82-10855 A82-12318 BOCKBI-BpBBE IBSIBOBEHIS BEBOTB SEHSIHG Limiting payload deceleration during ground impact Three navigation systems and their costs of [AIAA PAPEB 81-1918] A82-10404 acquiring remote sensing data BOTABY GIBOSCOPBS A82-10049 Fast and accurate gyrocompass using strapdown BEHOTBLY PILOTED VEHICLES tuned rotor gyros as a solution to combat BiHAT onboard flight computer system architecture helicopters navigation problems and qualification A82-11927 [AIAA 81-2107] 482-10082 Design considerations for the direct digital Air bag impact attenuation system for the AQH-34V control of dry-toned gyroscope remote piloted vehicle A82-11933 [AIAA PAFEB 81-1917] A82-10403 BOTABI BIHG AIBCBAFT Design and development of a low cost servoed rate On computing Floguet transition matrices of gyro for unmanned aircraft rotorcraft A82-11932 A82-11225 Parametric study of microwave-powered BOIABI BIBGS high-altitude airplane platforms designed for Helicopter rotor trailing edge noise linear flight [AIAA FAPEB 81-2001] A82-10455 [B1SA-TP-1918] H82-11050 Composite main rotor tubular braided BEHE 95 A82-10547 Superalloy powder engine components; controls Model helicopter rotor impulsive noise employed to assure high quality hardware A82-11300 A82-12499 Numerical treatment of helicopter rotor stability BESCOB OEEBATIOSS problems SABSAT applications A82-12045 482-12698 Standard tests of a research model rotor in a wind BESEABCB AID DEVELOPHEBT tunnel, including model similarity Development and construction of pilot ejector calculations compared with measurements seats in Germany from 1938-1945 [BBVG-FBHT-79-16] 1182-10016 [DFVLB-FB-81-04] H82-10026 Botorcraft icing: Status and prospects BESBABCB FACILITIES [AGABD-AB-166] B82-11056 Description of the meteorological research radar, Operational environment, meteorological conditions system aboard HOAA/Besearch Facilities Center and weather forecasting HP-3D aircraft H82-11057 A82-10217 Technology base for icing instrumentation and BESIDEHIIAL ABEAS mathematical modelling Effects of aircraft noise on the equilibrium of H82-11058 airport residents: Testing and utilization of a Facilities for developnent and clearance new nethodology 1182-11059 [HASA-TB-76628] 1182-11636 Ice protection system technology BESOLOTIOB 1182-11060 Study and developnent of an integrated head-up Proposed standard requirements and procedures for display icing clearance [AD-A104337] 882-11062 882-11061 BESOIAHI FBBOOEBCIES Aeroacoustic theory for noncompact wing-gust Calculation of natural modes of vibration for interaction rotor blades by the finite element method [FDBL-81-7] 882-11071 [DF7LB-FB-81-07] B82-10452 Helicopter rot<<£ trailing edge noise noise BETBACTABLE EQOIPHBBT prediction Analytical determination of undercarriage [SASA-CB-3470] H82-11859 retraction kinematics BOTATIBG BODIES A82-10364 The Shock and Vibration Digest, volume 13, no. 9 BEIHOLDS HOHBEB [AD-A105062] ' H82-10421 Computation of high Eeynolds number BOTATIBG FLUIDS internal/external flows A theoretical analysis of the stream surface of [BASA-TH-84049] 882-11046 revolution with supersonic inlet flow in a transonic axial compressor H82-11025

A-27 BOTOB 4EBODTHAHICS SUBJECT IBDBZ

BOTOB AEBODIHAHICS SBP4BATOBS Botor wake characteristics relevant to New separators for battery systems rotor-stator interaction noise generation 482-11715 [4144 PAPEB 81-2031] 482-10456 SERVICE LIFE Hind tunnel tests on airfoils in tandem cascade Design considerations for duty cycle, life and 482-10987 reliability of small limited life engines Hunerical treatment of helicopter rotor stability [4144 P4PEB 81-1402] 482-10465 problems Unsolved problems of nickel cadmium batteries 482-12045 482-11725 BOTOB BLADES (TOBBOHACHIBBBI) SEBVOCONTBOL Effects of vane/blade ratio and spacing on fan noise 4 method for determination of the aeroelastic [4144 PAPEB 81-2033] 482-10157 behavior of aircraft with active control systems BOTOB SPEED [DFVLB-FB-81-05] N82-10047 60 KV4 4DF permanent magnet VSCF starter generator SBALE OIL system - Generator system performance Jet fuel locks to shale oil: The 1980 technology characteristics review 482-11721 [AD-A104414] N82-11228 BOBBSB SBEAB STBBSS The possibility of using deformable rubber Crack growth evaluation of a method to convert components in landing gear real-time loads history to a simplified 482-10*96 engineering spectra for aircraft structural BDNBAYS analysis Design of airport pavements for expansive soils 482-12043 [AD-A104660] H82-11313 SHIP TEBHIHALS 4 mathematical model of an over-sea airborne DBF radio link 482-11406 SAFETY HABAGE8BBT SHOCK ABSOBBBBS 4 proposed flight safety program for the Korean Polyurethane foams for aircraft shock mounts. 3: Air Force Vibration damping by polyether foams [4D-A102373] H82-10023 [AD-A104496] N82-11212 System safety program plan electromagnetic SHOCK L04DS pulse testing of the 4-7E aircraft Dynamic response of aircraft structure to gun [AD-4104S57] H82-1135U shock Loads SAHDilCH STBUCTOBBS 482-11314 Impact-initiated damage thresholds in composites The Shock and Vibration Digest, volume 13, no. 9 482-12028 [4D-4105062] H82-10421 S4BS4I SHOCE B4VE PBOPAGATIOH SABS4T applications 4cta mechanica sinica 482-12698 [4D-4105184] N82-11014 SATELLITE NAVIGATION SYSTEHS SBOBT HAUL AIBCBAFT National Aerospace Meeting, Trevose, FA, April Quiet short-haul research aircraft familiarization 8-10, 1981, Proceedings document, revision 1 A82-12626 [NASA-TM-81298] N82-10031 Satellite geometry considerations for lov cost GPS Propulsion study for Small Transport Aircraft user equipment Technology (STAT) 482-12630 [NAS4-CB-165499] N82-10037 A navigation systems planning model SHOBT TAKEOFF AIBCBAFT 482-12640 Quiet short-haul research aircraft familiarization Integrated satellite navigation and strapdown document, revision 1 attitude and heading reference systems for civil [N4S4-TH-81298] N82-10031 air carriers Development and evaluation of automatic landing 482-12643 control laws for light wing loading STOL aircraft SATELLITE BBTIOBKS [N4S4-CB-166160] H82-10043 Satellite geometry considerations for lo¥ cost GPS SIGHAL PBOCESSIBG user equipment Oeega station 10.2 kHz signal selection made easy 482-12630 482-12638 SC4LE MODELS SIGHAL TO BOISE BATIOS Standard tests of a research model rotor in a vind Tangential sensitivity of El receivers tunnel, including model similarity 482-11020 calculations compared with measurements SIHILABITZ THBOBEfl [BMVG-FBBT-79-16] N82-10016 Standard tests of a research model rotor in a wind SEALS (STOPPEBS) tunnel, including model similarity Development of lov modulus material for use in calculations compared with measurements ceramic gas path seal applications [BHVG-FB1T-79-16] N82-10016 [N4S4-CB-165469] 1182-10039 SIZE DISTBIBOTIOH SEABCB BAOAB The dispersion of drop sizes in gas turbine fuel Threat Alert and Collision Avoidance System (TCAS) nozzle sprays Symposium 482-12107 [AD-A104563] N82-11047 SKIBTS SELF OSCILLATIOB The net-skirt to a parachute canopy as a device to One reason for the onset of high-frequency prevent inversion self-excited oscillations in combustion [4144 P4PEB 81-1927] 482-10412 chambers of aircraft engines SLABS 482-11448 Structural analysis computer programs for rigid SEHSITIVITT. multicomponent pavement structures with Feedback and minimal sensitivity discontinuities, iESLIQID and SESL4IEB. Be port • N82-10058 1: Program development and numerical presentations SEP4BATED FLOS [4D-A104545] N82-11498 Strong matching method for computing transonic SIAP viscous flovs including wakes and separations - Experimental study of empennage snap-through Lifting airfoils vibrations 482-10821 A82-11471 Nonlinear prediction of subsonic aerodynamic loads SOIL MECHANICS on wings and bodies at high angles of attack Design of airport pavements for expansive soils 482-11359 [AD-A104660] N82-11313 Experimental investigations of the separated flow SOILS around a rectangular wing in a wind tunnel Design of airport pavements for expansive soils [DPVLB-FB-81-12] H82-10017 [40-4104660] N82-11313

4-28 SUBJECT IBDBX STRESS COBBOSIOH CBACKIBG

SOLAS POBBBBD AIBCBAFT SPBAI BOZZLES lings in the son - The evolution of Solar Challenger The dispersion of drop sizes in gas turbine fuel A82-12694 nozzle sprays SOLID ELECTRODES 482-12107 Unsolved problems of nickel cadmium batteries Belicopter icing spray system - Improvements and 482-11725 flight experience SOLID PBOPELLABT COHBOSTIOB A82-12696 An investigation of the combustion process in STABILIZERS (AGBBTS) solid fuel ramjets On the use of carbon composites in slat and [AD-4104603] H82-11232 stabilizer construction SOLID PBOPBLLABTS 482-11168 An investigation of the conbustion process in STAB04BDS solid fuel ran jets Botorcraft icing: status and prospects [AD-A104603] H82-11232 [AGABD-Afi-166] 882-11056 SOSOBOOIS Proposed standard requirements and procedures for Aeroballistic characteristics of sonobnoy icing clearance parachute decelecators limited to a length of H82-11061 three feet STATE VEC1OBS [AIM PAFEB 81-1950] A82-10425 Synthesis of system for evaluating gyrostabilizer SODBD PBESSDBE state with unknown disturbances Evaluation of the acoustic measurement capability A82-11469 of the HASA Langley V/S10L wind tunnel open test STEADI FLOB section with acoustically absorbent ceiling and Finite difference computation of the steady floor treatments transonic potential flow around airplanes [BASA-CB-165796] H82-10059 H82-10981 SODHD TBAHSHISSIO8 STEADI STATE Experimental modal analysis of the fuselage panels The effects of flexibility on the steady-state of an Aero Commander aircraft performance of small ribbon parachute models [HASA-CB-165750] H82-10028 [AIAA PAPEB 81-1923] A82-10108 SPACE HAVIGATIOB STIFFBESS BATBIX national Aerospace Meeting, Trevose, PA, April Formation of triangular-element stiffness matrix 8-10, 1981, Proceedings using sliding interpolation A82-12626 A82-11164 Hemory requirements for future navigation systems An influence coefficient method for the A82-12637 application of the modal technique to wing SPACE SHUTTLES flutter suppression of the DAST ABB-1 wing Che Space Shuttle vehicle checkout involving [HASA-CB-165772] H82-11070 flight avionics software STOCHASTIC PBOCESSES [AIAA 81-2HI1] A82-10100 Synthesis of system for evaluating gyrostabilizer Use of Space Shuttle technology in conventional stat. with unknown disturbances aircraft A82-11169 [AIAA 81-2176) A82-10125 Theory of stochastic optimal control some basic SPACE VEHICLE CBECKODI PBOGBAB notions Che Space Shuttle vehicle checkout involving 1182-11075 flight avionics software An introduction to stochasic optimal control theory [AIAA 81-2111] A82-10100 H82-11076 SPACECBAPT COHSTBOCTIOB HATEBIALS STORAGE BATTEBIES Powder metallurgy snperalloys - Aerospace Bew separators for battery systems materials for the 1980's; Proceedings of the A82-11715 Conference, Zurich, Switzerland, Hoveober 18-20, STOBBS (HETSOBOLOGI) 1980. Volume 1 Applications of conventional and Doppler radars A82-12495 for aviation safety SPACECBAFT COBTBOL A82-10215 Synthesis of system for evaluating gyrostabilizer STRAPDOIB IBEBTIAL GOIDA8CE state with unknown disturbances Fast and accurate gyrocompass using strapdown A82-11469 tuned rotor gyros as a solution to combat SPACECBAPf DBSIGB helicopters navigation problems Control design of flexible spacecraft A82-11927 H82-11081 Design considerations for the direct digital SPACECBAFT ELECTBOBIC BQOIPBBBI control of dry-tuned gyroscope Bridging the gap from aircraft to space computers A82-11933 [AIAA 81-2112] A82-10101 Simulation study of a hybrid strapdown attitude SPABIISE BLOBIB6 and heading reference system A study on numerical method for evaluating A82-12641 spanwise integral in subsonic lifting-surface The integrated inertial sensor assembly /list/ - A theory redundant strapdown system for advanced aircraft [BAL-TB-661T] B82-11035 navigation and flight control functions SPEED COBTBOL A82-12642 Procedures and analysis technigues for determining Integrated satellite navigation and strapdown static air minimum control speeds attitude and heading reference systems for civil A82-12561 air carriers SPIB DIBASICS A82-12643 A microprocessor-based data acguisition system for STBEAB FDBCTIOBS (FLUIDS) stall/spin research An aerodynamic design method for transonic axial [AIAA 81-2177] 482-10126 flow compressor stage SPOILEBS H82-10984 Theoretical investigation of the influence of STBBSS ABALISIS spoiler dynamics on the handling gualities of an Lineup of the IB-series aircraft-derivative gas aircraft with direct lift control turbines [ESA-TT-681] B82-10036 482-12560 Development and evaluation of automatic landing Hew molding method of three-dimensional hollow control lavs for light wing loading STOL aircraft photoelastic model and centrifugal stress [BASA-CB-166160] H82-10043 analysis of air cooled turbine blade model System identification of the longitudinal motion [BAL-TB-427T] H82-11067 of the DFVLB HFB 320 research aircraft with STBBSS COBBOSIOB CBACKIBG particular consideration of control surface The application of improved aluminium alloys and effectiveness steels in aircraft structures [ESA-TT-666] 882-10045 A82-10305

A-29 STBESS HEASOBBHBNT SUBJECT IHDBZ

STRESS HEASOBEHEBT Experimental study of subsonic and transonic flows Stress measurements in a ribbon parachute canopy past a wing daring inflation and at stead; state A82-10363 [JIAA PAPBB 81-19111] 482-10420 Nonlinear prediction of subsonic aerodynamic loads Stress measurements in bias constructed parachute on wings and bodies at high angles of attack canopies during inflation and at steady-state A82-11359 [8141 P4PBB 81-1945] 482-10421 Theoretical investigations and experimental STBOCTUHil ANALYSIS researches for higher subsonic two-dimensional Formation of triangular-element stiffness matrix compressor cascade using sliding interpolation N82-11024 482-11464 Aeroacoustic theory for noncompact wing-gust Crack growth evaluation of a method to convert interaction real-time loads history to a simplified [FDB1-81-7] H82-11071 engineering spectra for aircraft structural On the kernel function collocation method in analysis steady subsonic flow for wing with control 482-12043 surfaces Mathematical model for the maintenance program of H82-12023 modern jet aircraft crack detection; SUBSONIC BIND TOHNELS inspection intervals Subsonic cascade wind tunnel tests using a [DFVLB-FB-81-14] N82-10002 compressor configuration of DCA blades Structural analysis of fuselages with cutouts ty [AD-4104597] H82-11069 finite element method SUCTI01 1182-10995 Amplified crossflow disturbances in the laminar Hatrix analysis of wings boundary layer on swept wings with suction 1182-10998 [N4SA-TP-1902] H82-11391 Integrated analysis of engine SOPEBCBITICAL ilNGS [SASA-TH-82713] 1182-11491 Fropfan installation aerodynamics of a Structural analysis computer programs for rigid supercritical swept wing transport configuration multicomponent pavement structures with [AIAA PAPEB 81-1563] 482-10466 discontinuities, HESLIQID and WESLAIEB. Beport A comparison of theoretical and experimental 1: Program development and numerical presentations pressure distributions for two advanced fighter [AD-A104545] 1182-11498 wings SIBOCIOBA1 DESIGB [NASA-Tfl-81331] B82-11054 light aircraft structural design in non-metallics SOPEBSOBIC AIBCBAFT - Use of composite honeycomb for light aircraft Deal-tine, on-line digital simulation of optimum 482-10308 maneuvers of supersonic aircraft Emerging technologies in aerospace structures, [AIAA 81-2178] A82-10127 design, structural dynamics and materials; SOPEBSOBIC COBBOSTION BAHJEI ENGINES Proceedings of the Aerospace Conference, San Multiple-scale turbulence modeling of free Francisco, C4, August 13-15, 1980 turbulent flows 482-12026 [ASUE PAPEB 81-FE-20] 482-10934 Determination of airplane model structure from SOPEBSONIC FLIGHT flight data by using modified stepwise regression Optimal flight paths for winged, supersonic flight [NASA-TP-1916] N82-10041 vehicles - Extension to the case where thrust " Control design of flexible spacecraft can be vectored H82-11081 A82-10310 Design of airport pavements for expansive soils SOPEESOBIC INLETS [AD-A104660] 1182-11313 A theoretical analysis of the stream surface of STBOCTOBAL FAILOBE revolution with supersonic inlet flow in a A note on fatal aircraft accidents involving metal transonic axial compressor fatigue 1182-11025 A82-11400 SDPEBSOHIC JET FLOW STBOCTOBAL IHFLOBHCE COEFFICIENTS Multiple-scale turbulence modeling of free An influence coefficient method for the turbulent flows application of the modal technique to wing [ASBE PAPEB 81-FE-20] A82-10934 flutter suppression of the DAST ABI-1 wing SOPEBSONIC SPEEDS [HASA-CB-165772] N82-11070 The principles and methods for shaping the wing STBOCTOBAL BEIIABILIII root regions of a wing-body combination at Lineup of the IH-series aircraft-derivative gas transonic and lower supersonic speeds turbines N82-11016 A82-12560 SOBFACE LAIBBS STBOCTOBAL STABILITY Besnlts of experimental study of heat transfer to An influence coefficient method for the turbine blades with porous cooling application of the modal technique to wing 482-11446 flutter suppression of the DAST ABi-1 wing SOBFACE PBOPEBTIBS [HASA-CB-165772] H82-11070 Design of airport pavements for expansive soils STBOCTOBAL STRAIN [AD-A104660] H82-11313 Optical sensors for displacement measurement SOBFACE VESICLES A82-11407 Characteristics and trends of energy consumption STBOCTOBAL VIBBAtlOB in transport missions with aircraft and surface Helicopter engine technology - With particular vehicles reference to the Bolls-Boyce Gem engine A82-10495 A82-10304 SOBFACES Lineup of the IH-series aircraft-derivative gas A study on numerical method for evaluating turbines spanwise integral in subsonic lifting-surface 482-12560 theory New estimation method for flutter or divergence [HAL-TB-661T] B82-11035 boundary from random responses at subcritical SOBGBS speeds High voltage surge and partial discharge test to [BAL-TB-667I] N82-11034 evaluate aerospace equipment parts SOBSOBIC.AIBCBAFT A82-11740 Air-freon integrated environmental conditioning SOBfBILLANCB BADAB system for trainer subsonic aircraft Airborne associative processor /ASPBO/ for [ASHE PAPEB 81-EHAS-33] A82-10920 early warning radar surveillance, command, and SOBSOBIC FLOB control applications The use of the Weber method for [AHA 81-2145] 482-10104 minicomputer-assisted numerical analysis of airfoils A82-10362

A-30 SUBJECT IBDBX THEBBAL FATIGUE

SWEAT COOLIHG Results of experimental study of heat transfer to turbine blades with porous cooling A82-11446 T-38 AIBCBAFT SBBPT 1IBGS SEL and EPHL noise duration coefficients for the Propfan installation aerodynamics of a 747 and T-38 aircraft supercritical swept ving transport configuration [BASA-TH-83214] H82-11860 [AIA4 P4PEE 81-1563] 482-10466 TACAB Amplified crossflow distarbances in the laminar Interoperability testing of decentralized command, boundary layer on swept wings with suction control, communications and intelligence /C3I/ [H4S4-TP-1902] H82-11391 systems SBITCHISG CIBCOITS [AIAA 81-2205] A82-10143 Advanced aircraft electrical system control TAIL ASSEBB1IES technology demonstrator. Phase 1: Eeqairements Experimental study of empennage snap-through analysis and conceptual design vibrations [4D-4103922] H82-10326 A82-11471 SIBTHETIC APEBTOBB BAIAB TABGET SIHDLATOHS Synthetic aperture radar target simulator Synthetic aperture radar target simulator [BASA-CASE-BPO-15024-1] H82-10286 [HASA-CASE-HPO-15024-1] N82-10286 SISTEB FAILOBBS TECHHOLOGICAL FOBECASTIHG Extending the limits of reliability theory Book Propulsion study for Small Transport Aircraft 482-12318 Technology (STAT) SISTEHS AHALYSIS [HASA-CB-165499] N82-10037 Haiti-variable analysis and design techniques TECHNOLOGY ASSESSHBHT [AGABD-LS-117] B82-10048 Fluid power technology for the •80s Book Multivariable design techniques based on singular A82-10851 value generalizations of classical control Jet fuel locks to shale oil: The 1980 technology H82-10051 review SISTERS EHGIHEERIBG [4D-A104414] H82-11228 Acoustic emission - An emerging technology for TECBHOLOGY TBABSFBB assessing fatigue damage in aircraft structure Bridging the gap from aircraft to space computers A82-11149 [AIAA 81-2142] A82-10101 The certification of digital systems TECHIOLOGY OTILIZATIOH 482-11940 Use of Space Shuttle technology in conventional Digital avionics: Promise and practice - An aircraft airlines experience in the field [AIAA 81-2176] 482-10125 482-11942 The balloon and the airship technological heritage Haiti-variable analysis and design techniques [AIAA PAPEB 81-1912] A82-10401 [4G4BD-LS-117] N82-10048 SABSAT applications The need for multivariable design and analysis 482-12698 techniques TE1EBETBI H82-10049 Outsider's look at flight instrumentation Design of high integrity multivariable control [DE81-025409] B82-11066 systems TEHPEBATOBE HEASOBEHENT B82-10055 In-situ calibration of flight heat transfer A geometric approach to multivariable control instrumentation system synthesis [ASHE PAPEB 81-E8AS-13] 482-10901 H82-10056 Adaptation of a turbine test facility to Hultivariables design: The optimization of high-temperature research approximate inverses [B4E-LIB-TBAHS-2064] H82-11089 H82-10057 TEEB4IB FOLLOBIBG AIBCBAFT Design considerations for optimal flight control ; Ideal and simulated performance of an aircraft in systems the terrain following mission H82-11077 A82-11302 Design techniques for mntlivariable flight control TEST FACILITIES systems Air-breathing engine test facilities register H82-11078 [4GABD-AG-269] B82-10063 Application of nonlinear systems inverses to Botorcraft icing: status and prospects automatic flight control design: System [AGABD-AB-166] B82-11056 concepts and flight evaluations Facilities for development and clearance H82-11083 B82-11059 SISTEHS IH1EGBATIOH Adaptation of a turbine test facility to KC-135 Avionics Modernization Hot Bench high-temperature research [AIAA 81-2105] 482-10081 [BAE-LIB-TBANS-2064] H82-11089 Discrete address beacon, navigation and landing System safety program plan electromagnetic system pulse testing of the A-7E aircraft A82-10650 [AD-4104557] H82-11354 The integrated inertial sensor assembly /USA/ - 4 TEST PILOTS redundant strapdown system for advanced aircraft Test Pilots' Aviation Safety Workshop, U.S. Haval navigation and flight control functions Postgraduate School, Honterey, CA, February 482-12642 25-28, 1981, Proceedings Integrated satellite navigation and strapdown 482-10500 attitude and heading reference systems for civil TBEBBA1 EIVIBOBBEBTS air carriers Closed loop environmental control systems for 482-12643 fighter aircraft SISTEHS S1BDL4TIOH [ASHE PAPBB 81-EBAS-2] 482-10890 Interoperability testing of decentralized command, Quantification of the thermal environment for control, communications and intelligence /C3I/ externally carried aircraft stores and ordnance systems A82-12100 [4144 81-2205] 482-10143 TBEBBAL EIPABSIOH Simulation study of a hybrid strapdown attitude Thermal expansion accommodation in a jet engine and heading reference system frame 482-12641 482-11999 THEBBAL FATIGOE Thermal expansion accommodation in a jet engine frame 482-11999

A-31 THEEHAL PBOTECIIOH SUBJECT IHDBI

IBEBH1L EBOTECTIOB TBAILIHG EDGES The Shock and Vibration Digest, volume 13, no. 9 Helicopter rotor trailing edge noise [AD-A105062] N82-10421 [AIAA PAPEB 81-2001] A82-10455 THEBH4L BBSISXABCB Aircraft wing trailing-edge noise Design analysis of high temperature transparent [NASA-CB-164952] H82-11039 windshields for high performance aircraft Helicopter rotor trailing edge noise noise [ASHE PAPEB 81-EHAS-5] A82-10893 prediction Theroal-barrier-coated turbine blade study [UASA-CB-3470] H82-11859 [HASA-CB-165351 ] H82-10040 IBAILIH6-BDGB FLAPS THEBUL SIHDLKIOB On evaluating the influence of local disruptions A new thermal and trajectory model for high of flow over trailing edge and leading edge altitude balloons flaps from the data of wind tunnel tests of a [AIAA PAPEB 81-1926] A82-10411 rectangular wing segment THEBHOCOOPLES A82-11465 In-situ calibration of flight heat transfer System identification of the longitudinal motion instrumentation of the DFTLB HFB 320 research aircraft with [ASHE PAPEB 81-BHAS-13] A82-10901 particular consideration of control surface THEBBODIHAHIC PBOPEBTIBS effectiveness Basic problem of aircraft gastnrbine engine [ESA-TT-666] N82-10045 analytic design. II TBAIHIBG AIBCBAFI 482-11463 Air-freon integrated environmental conditioning CHBEE DIHEHSIOHAL FLO! system for trainer subsonic aircraft Acta mechanica sinica [ASHE PAPEB 81-EHAS-33] A82-10920 [AD-A105184] 082-11011 TBAJBCIOBI ABALTSIS The arbitrary guasi-orthogonal surface method for A new thermal and trajectory model for high computing three-dimensional flow in turbine altitude balloons machinery. 2. Calculation of the [AIAA PAPEB 81-1926] A82-10411 three-dimensional flow with the S sub 1-surface THAJECTOBY COHTBOL twisted Flight trajectory control investigation H82-11015 [4D-4104542] N82-11048 A theoretical analysis of the stream surface of Optimum climb and descent trajectories for airline revolution with supersonic inlet flow in a missions transonic axial compressor H82-11082 H82-11025 TSAJECTOBI OPTIHIZATIOH A numerical three-dimensional turbulent simulation Optimal flight paths for winged, supersonic flight of a subsonic VSTOL jet in a cross-flow using a vehicles - Extension to the case where thrust finite element algorithm can be vectored [AD-A104514] N82-11055 A82-10310 Aeroacoustic theory for noncompact wing-gust TBAHSFBB FDBCTIOHS interaction Limitations on achievable performance of [FDBL-81-7] H82-11071 multivariable feedback systems THREE DIHEHSIOHAL HOIIOH H82-10052 On the question of trailing airplane motion 1BAHS01IC COHPBBSSOBS 482-11470 A theoretical analysis of the stream surface of THBDST COHZBOL revolution with supersonic inlet flow in a V/STOL aircraft and fluid dynamics transonic axial compressor [HASA-TH-81328] H82-10029 H82-11025 THBOST BETEBSAL TBAHSOHIC FLOB Study of reingestion of exhaust gases with Experimental study of subsonic and transonic flows different initial temperature in a reversed past a wing turbojet engine A82-10363 482-11444 Strong matching method for computing transonic THBDST TBC3OB COHTBOL viscous flows including wakes and separations - Optinal flight paths for winged, supersonic flight Lifting airfoils vehicles - Extension to the case where thrust 482-10821 can be vectored Finite difference computation of the steady A82-10310 transonic potential flow around airplanes Developments in boundary layer Thrust Vector Control N82-10981 A82-10855 A comparison of theoretical and experimental TIME pressure distributions for two advanced fighter SE1 and EPHL noise duration coefficients"for the wings 747 and T-38 aircraft [HASA-TH-81331] H82-11054 [HASA-TH-83214] H82-11860 TBAHSOHIC SPEED TIDE LAG The principles and methods for shaping the wing Hard limited approaches to correlation velocity root regions of a wing-body combination at sensing transonic and lower supersonic speeds A82-12636 H82-11016 TIBE OPTIBAL COHTBOL TBAHSOHIC HIHO TUBBELS LQG-based mnltivariable design: Frequency domain Design predictions for noise control in the interpretation cryogenic National Transonic Facility 882-10053 A82-12025 TIUHIDB ALLOTS TBAHSPOHDEBS Sophisticated aircraft structure developments - Threat Alert and Collision Avoidance System (TCAS) Combat aeroplanes Symposium 482-10309 [AD-A104563] H82-11047 TODCBDOBH THASSPOBT AIBCBAFT Comparative study of flare control laws Propfan installation aerodynamics of a (NASA-CB-164903] H82-10032 supercritical swept wing transport configuration TBACKIHG BADAB [AIAA PAPEB 81-1563] A82-10466 Synthetic aperture radar target simulator Characteristics and trends of energy consumption [HASA-CASE-NPO-15024-1] H82-10286 in transport missions with aircraft and surface TBADEOFFS vehicles Active control elements on the transonic wing of A82-10495 the Airbus A-300 (ACTTA A). Airbus A-300 with Towards minimum power for environmental control in reduced longitudinal stability (ACTTA-C) transport aircraft advanced control transonic transport aircraft [ASHE PAPEB 81-EHAS-4] A82-10892 (ACCTA); design considerations Fuel for future transport aircraft N82-10044 [ASHE PAPEB 81-HT-80] 482-10965

4-32 SUBJECT IBDEI OBSTBADX FLO!

History of flight testing the L-1011 Tristar jet Initial experimental research into the response of transport. II - Testing highlights since initial turbojet engine compressors to distortion of certification of the L-1011-1 intake pressure A82-12049 B82-11006 Theoretical investigation of the influence of A preliminary experimental investigation of the spoiler dynamics on the handling qualities of an response of a turbojet engine to inlet pressure aircraft with direct lift control distortion [ESi-TT-681] 882-10036 B82-11007 Propulsion study for Snail Transport Aircraft TDBBOBACHIBE BLADES Technology (STAT) Calculation of natural modes of vibration for [BASA-CB-165499] H82-10037 rotor blades by the finite element method Propulsion study for Small Transport Aircraft [DF7LB-FB-81-07] B82-10452 Technology (STAT), Appendix B TOBBOHACBIIEBI [BASA-CB-165499-APP-B] 1182-10038 Acta mechanica sinica Control lav design for transport aircraft flight [AD-A105184] B82-11014 tasks The arbitrary quasi-orthogonal surface method for H82-11080 computing three-dimensional flow in turbine TRAPEZOIDAL iIHGS machinery. 2. Calculation of the Experimental study of subsonic and transonic flows three-dimensional flow with the S sub 1-surface past a wing twisted A82-10363 B82-11015 CUBE BEAT BICHABGEBS TOBBOPBOP EBGIBBS The enhancement of heat exchange in channels /2nd Propulsion study for Small Transport Aircraft revised and enlarged edition/ -•— Bussian book Technology (STAT) A82-12222 [HASA-CB-165499] H82-10037 TOBBIBE BLADES TUBBOLBBT BOOBDABT LAIEB Thermal and flow analysis of a convection, Theoretical investigations and experimental air-cooled ceranic coated porous metal concept researches for higher subsonic two-dimensional for turbine vanes compressor cascade [ASHE PAPEB 81-BT-48] A82-10952 H82-11024 End losses in turbine cascades with porous cooling TDBBOLEBT FLOB A82-11434 Multiple-scale turbulence modeling of free Results of experimental study of heat transfer to turbulent flows turbine blades with porous cooling [ASHE PAPEB 81-FE-20] A82-10934 A82-11446 On the prediction of swirling flowfields found in Thermal-barrier-coated turbine blade study axisymaetric combastor geometries [BASA-CB-165351] B82-10040 A82-12120 A new method of cooling turbine vanes Validation studies of turbulence and combustion H82-11027 models for aircraft gas turbine combustors Hew molding method of three-dimensional hollow A82-12267 photoelastic model and centrifugal stress A new method of cooling turbine vanes analysis of air cooled turbine blade model 1182-11027 [BAL-TB-427T] H82-11067 Hind-tunnel results for a modified TOBBIIE EHGIBBS 17-percent-thick low-speed airfoil section Superalloy turbine components - Which is the [BASA-TP-1919] 1182-11033 superior manufacturing process, as-BIP, HIP plus A numerical three-dimensional turbulent simulation Isoforge, or 'gatorizing1 of extrusion of a subsonic VSTOL jet in a cross-flow using a consolidated billet finite element algorithm A82-12497 [AD-A104514] 1182-11055 Superalloy powder engine components; controls TOBBOLEBx BAKES employed to assure high guality hardware Seductions in parachute drag due to forebody wake A82-12499 effects Development of multivariable controllers for [AIAA PAPEB 81-1939] A82-10417 aircraft turbine engines Botor vake characteristics relevant to B82-11087 rotor-stator interaction noise generation TOBBOCOHPBBSSOBS [AIAA PAPEB 81-2031] A82-10456 •ind tunnel tests on airfoils in tandem cascade TBO DIHEBSIOBAL FLOB A82-10987 Control laws for adaptive wind tunnels An aerodynamic design method for transonic axial A82-10985 flow compressor stage An aerodynamic design method for transonic axial H82-10984 flow compressor stage Initial experimental research into the response of B82-10984 turbojet engine compressors to distortion of Theoretical investigations and experimental intake pressure researches for higher subsonic two-dimensional H82-11006 compressor cascade An experimental investigation of the rotating B82-11024 stall, surge and wake behind the rotor for a single stage axial compressor N82-11008 u A theoretical analysis of the stream surface of OB-1 BEUCOPTEB revolution with supersonic inlet flow in a Belicopter icing spray system - Improvements and transonic axial compressor flight experience H82-11025 A82-12696 TOBBOFAB EBGI1ES OLTBAHIGH FBEQOBBCIES Botor wake characteristics relevant to A mathematical model of an over-sea airborne DBF rotor-stator interaction noise generation radio link [AIAA PAPEB 81-2031] A82-10456 182-11106 Application of numerical modeling to gas turbine OBDEBCiBBIAGBS combnstor development problems Analytical determination of undercarriage A82-12118 retraction kinematics An assessment of the use of antimisting fuel in A82-10364 tnrbofan engines OBSTBADI FLOB [BASA-CB-165258] B82-11230 An experimental investigation of the rotating TOBBOJET EBGIBES stall, surge and wake behind the rotor for a Study of reingestion of exhaust gases with single stage axial compressor different initial temperature in a reversed B82-11008 turbojet engine A82-11444

A-33 DPPBH SURFACE BLOBIHG SUBJECT IHDBX

OPPEB SURFACE BLOBIHG VORTEX FLAPS Quiet short-haul research aircraft familiarization Effects of vortex flaps on the low-speed document, revision 1 aerodynamic characteristics of an arrow wing [NASA-TH-81298] H82-10031 [BASA-TP-1914] 882-11013 VORTICES Increasing the lift:drag ratio of a flat delta wing A82-11899 V/STOL AIRCRAFT The CIVIC - A concept in vortex induced V/STOL aircraft and fluid dynamics combustion. II [HASA-TB-81328] H82-10029 [ASHE PAPER 81-6T-12] A82-11997 Lou speed testing of the inlets designed for a tamden-fan V/STOI nacelle conducted in the Lewis 10 by 10 foot wind tunnel w [HASA-TH-82728] H82-11042 BALL FLOI A summary of V/STOL inlet analysis methods Control laws for adaptive wind tunnels [HASA-TH-82725] N82-11043 A82-10985 A numerical three-dimensional turbulent simulation BARHIHG SISTEBS of a subsonic VSTOL jet in a cross-flow using a An airport wind shear detection and warning system finite element algorithm using Doppler radar [AD-A104514] H82-11055 A82-10220 VABI ABILITY Threat Alert and Collision Avoidance System (TCAS) Characteristic and principal gains and phases and Symposium their use as oultivariable control design tools [AD-A104563] H82-11047 generalizing Hyguist and root-locus diagram BAVE DIFFBACTIOH techniques Acta mechanica sinica H82-10050 [AD-A105184] N82-11014 Multivariable design techniques based on sinqular BAVE REFLECTIOH value generalizations of classical control Acta mechanica sinica H82-10051 CAD-A10518H] H82-1101U VELOCITY DISTHIBUTIOB BEAPOH STSTEBS Aerodynamic calculations and design of snbcritical Quantification of the thermal environment for aerofoils externally carried aircraft stores and ordnance N82-10983 A82-12100 VELOCITY HBASOBBBBHT iEATBEH FOBECASTIBG Hard limited approaches to correlation velocity Operational environment, meteorological conditions sensing and weather forecasting 482-12636 H82-11057 VERTICAL AIR COBBESTS BIRD DIBBCTIOH Oovnbursts and microbursts - An aviation hazard Gust front structure observed by Doppler radar -•— dovndrafts beneath thunderstorms A82-10223 A82-10214 BIHD HEASOREHEHT VERTICAL DISTRIBUTION Detection and display of wind shear and turbulence Determination of vertical profiles of aerosol size A82-10222 spectra from aircraft radiative flux BIHD SHEAR measurements. II - The effect of particle An airport wind shear detection and warning system nonsphericity using Doppler radar A82-12149 A82-10220 TEBY LOi FBEQDEHCIES Instrumented aircraft verification of clear-air Onega station 10.2 kHz signal selection made easy radar detection of low-level wind shear A82-12638 A82-10221 VIBBATIOH DAHPIHG Detection and display of wind shear and turbulence 1 Quiet please' aircraft hydraulic systems A82-10222 noise redaction Comparative study of flare control laws A82-10854 [NASA-CB-164903] N82-10032 Polyarethane foams for aircraft shock mounts. 3: BIHD TUHHBL DRIVES Vibration damping by polyether foams Design predictions for noise control in the [AD-A104496] H82-11212 cryogenic Rational Transonic Facility VIBBATIOH EFFECTS A82-12025 The Shock and Vibration Digest, volume 13, no. 9 BIHD TOHBBL TESTS [AD-A105062] B82-10421 A modular asymmetric parachute for wind tunnel VIBBATIOH ISOLATORS testing The possibility of using deformable rubber [AIAA PAPEB 81-1933] A82-10414 components in landing gear Stress measurements in a ribbon parachute canopy 482-10196 during inflation and at steady state Polyurethaue foams for aircraft shock mounts. 3: CAIAA PAPEB 81-19«4] A82-10420 Vibration damping by polyether foams Hind tunnel tests on airfoils in tandem cascade [AD-A104496] H82-11212 A82-10987 VIBBATIOH BODE Standard tests of a research model rotor in a wind Applications of finite element method in aerospace tunnel, including model similarity power systems design calculations compared with measurements A82-11717 [BHVG-FBWT-79-16] B82-10016 Calculation of natural modes of vibration for Experimental investigations of the separated flow rotor blades by the finite element method around a rectangular wing in a wind tunnel [DFVLB-FB-81-07] H82-10452 [DFVLR-FB-81-12] N82-10017 VIBBATIOH TESTS Effects of vortex flaps on the low-speed The Shock and Vibration Digest, volume 13, no. 9 aerodynamic characteristics of an arrow wing [AD-A105062] H82-10421 [HASA-TP-1914] N82-11013 VIBRATORY LOADS lind-tnnnel results for a modified Lineup of the IH-series aircraft-derivative gas 17-percent-thick low-speed airfoil section turbines [HASA-TP-1919] H82-11033 A82-12560 Icing tunnel tests of a composite porous leading VIDEO EQOIPHEHt edge for use with a liquid anti-ice system Tangential sensitivity of BB receivers Lewis icing research tunnel A82-11020 [HASA-CB-164966] H82-11052 VISCOUS FLOW Subsonic cascade wind tunnel tests using a Strong matching method for computing transonic compressor configuration of DCA blades viscous flows including wakes and separations - IAD-A104597] H82-11069 Lifting airfoils A82-10821

A-3Q SOBJECT IBDEI Z WIBG BOTOBS

Helicopter rotor trailing edge noise noise prediction [HASA-CB-3470] B82-11859 IIHD TOHHEL BALLS Control laws for adaptive wind tunnels A82-10985 On low-speed «ind tunnels with defomable boundaries A82-11462 BIBD TOBHELS Evaluation of the acoustic measurement capability of the NASA Langley V/STOL wind tunnel open test section with acoustically absorbent ceiling and floor treatments [HASA-CB-165796] H82-10059 HID VELOCITY Gust front structure observed by Doppler radar 482-10223 BIHDSHIELDS Design analysis of high tenperature transparent windshields for high performance aircraft [ASHE PAPEB 81-EBAS-5] A82-10893 •IBG FLAPS Increasing the lift:drag ratio of a flat delta wing A82-11899 IIHG FLO! HETHOD TESfS Experimental stud; of subsonic and transonic flows past a wing A82-10363 BIBG LOADIBG Nonlinear prediction of subsonic aerodynamic.leads on wings and bodies at high angles of attack A82-11359 On the question of trailing airplane notion A82-11470 A study on numerical method for evaluating spanwise integral in subsonic lifting-surface theory [HiL-TB-661T] H82-11035 Aeroacoustic theory for noncompact wing-gust interaction [FDBL-81-7] B82-11071 ilBG OSCILLAIIOHS Experimental study of empennage snap-through vibrations A82-11471 IIHG PANELS Formation of triangular-element stiffness matrix using sliding interpolation A82-11464 IIB6 PROFILES An influence coefficient method for the application of the nodal technique to wing flutter suppression of the DAST ABS-1 wing [HASA-CB-165772] B82-11070 BIHG BOOTS Acta aechanica sioica [AD-A105184] H82-11014 The principles and methods for shaping the wing root regions of a wing-body combination at transonic and lower supersonic speeds B82-11016 BIBG TASKS Experimental study of fuel heating at low temperatures in a wing tank model, volume 1 [HASA-CB-165391] B82-11224 BIBGS Aircraft wing trailing-edge noise [BASA-CB-164952] B82-11039 On the kernel function collocation method in steady subsonic flow for wing with control surfaces B82-12023 X Z BIBG BOTOBS An investigation of a stoppable helicopter rotor with circulation control ames 40 by 80 foot wind tunnel [BASA-TB-81218] H82-10030

A-35 PERSONAL AUTHOR INDEX AERONAUTICAL ENGINEERING/^ Continuing Bibliography (Suppl. 145) FEBRUARY 1982

Typical Personal Author Index Listing

[PERSONAL AUTHOR| ABOO, X. Hen estimation method for flutter or divergence boundary from random responses at snbcritical ADABS, B. E. I. speeds I—Badar napping, archaeology, and ancient land use [BAL-TB-667T] B82-11034 in the Baya lowlands ASDBIAHO, H. [HiSA-CB-164931] H82-11514 Air-freon integrated environmental conditioning system for trainer subsonic aircraft [ASBE PAPEB 81-EBAS-33] A82-10920 REPORT TITLE ABCHDBACOI, J. I_ NUMBER KC-135 Avionics Modernization Bot Bench [AIAA 81-2105] A82-10081 Listings in this index are arranged alphabetically by personal author. The ABIFOLII. A. C. title of the document provides the user with a brief description of the subject Jet fuel from carbon matter. The report number helps to indicate the type of document cited (e.g., A82-12021 NASA report, translation, NASA contractor report). The accession number ASHEB, P. is located beneath and to the right of the title, e.g., N82-11514. Under any A solution to the static geometry problem for one author's name the accession numbers are arranged in sequence with JIIDS relative navigation the IAA accession numbers appearing first. A82-12634 ATKIHSOI, G. P. Air supply system bite for Boeing 767 airplane [ASBE FAPEB 81-EBAS-7] A82-10895

ADAH, V. B Control lav design for transport aircraft flight BABISB. C. A., Ill tasks Design analysis of high temperature transparent N82-11080 windshields for high performance aircraft ADAHS, B. E. i. [ASBE PAPEB 81-EBAS-5] A82-10893 Badar napping, archaeology, and ancient land use BACBHAB, K. L. in the Haya lowlands Bing Laser Gyro Navigator /ELGH/ flight test results [NASA-CB-164931] H82-11514 A82-12644 &GLIOLLIB, I. H. BAILBI. C. D. Basic problem of aircraft gasturbine engine Acoustic emission - An emerging technology for analytic design. II assessing fatigue damage in aircraft structure A82-11463 A82-11149 AKBHSEV. V. G. BAILEI, B. B. Calculation of aerodynamic characteristics of jet Analysis of augmented aircraft flying qualities flapped airplane through application of the Deal-Smith criterion A82-11459 [AIAA PAPEB 81-1776] A82-10462 AKBIEB, H. B. BAKEB. A. J. Development of multivariable controllers for A numerical three-dimensional turbulent simulation aircraft turbine engines of a subsonic VSTOL jet in a cross-flow using a H82-11087 finite element algorithm AKHTIAflOV, Z. ?. [AD-A104514] H82-11055 Study of reingestion of exhaust gases with BALASOBBAHAHIAB, X. S. different initial temperature in a reversed Numerical treatment of helicopter rotor stability turbojet engine problems A82-11444 A82-12045 ALBBIGfll, A. B. BALBOKB, V. V. Icing tunnel test of a glycol-exuding porous Control of electromechanical actuator elements for leading edge ice protection system on a general flight vehicles aviation airfoil A82-12170 [HASA-CB-165144] B82-10021 B&LLABD, J. D. ALLBABSBDBB. B. An investigation of a stoppable helicopter rotor Standard tests of a research model rotor in a wind with circulation control tunnel, including model similarity [BASA-TB-81218] B82-10030 [BHVG-FBBT-79-16] B82-10016 BALOHBIB, J. B. ALB, A. Botor wake characteristics relevant to Lightning effects on aircraft and composites. rotor-stator interaction noise generation Literature study on lightning strikes and [AIAA PAPEB 81-2031] A82-10456 protection BABBE, I. [FOA-C-20388-F9] 082-10024 Quantification of the thermal environment for AHIBB, B. K. externally carried aircraft stores and ordnance Helicopter rotor trailing edge noise A82-12100 [HASA-CB-3470] H82-11859 BAITEBSOI. J. G. 4BIBI, B. K. Determination of airplane model structure from Helicopter rotor trailing edge noise flight data by using modified stepwise regression [AIAA PiPEE 81-2001] A82-10455 [HASA-TP-1916] 1182-10041 ABDBBSOB, S. B. Estimation of airplane stability and control V/STOL aircraft and fluid dynamics derivatives from large amplitude longitudinal [HASA-TH-81328] H82-10029 maneuvers [HASA-TB-83185] B82-10042

B-1 BEASLEI, R. D. PEBSOHAL ADTHOH III DEI

BEASLEI, 8. 0. BBTSOH. A. B., JB. Hind-tunnel results for a modified An overview of optimal control in aerospace systems 17-percent-thick low-speed airfoil section H82-11074 [HASA-TP-1919] H82-11033 BOCB, A. BELTS, P. Fatigue life of lugs under service loading - Test Helicopter icing spray system - Improvements and results and predictions flight experience A82-11685 482-12696 BOCKBB, B. 0. BBBKOfUS, A. Inflatable system for fast deployment of Fatigue life of lugs under service loading - lest parachutes at low altitudes from slow moving results and predictions aircraft or stationary supports A82-11685 [AIAA PAPEB 81-1953] A82-10428 BICKLBB, T. C. BOCKIHGBAH. B. D. Synthetic aperture radar target simulator Design challenges of high performance aircraft POD [ HASi-CASE-HPO-15021-1] H82-10286 EOCH cooling systems BIPPES. B. [ASHE PAPEB 81-EHAS-6] A82-10894 Experimental investigations of the separated flow around a rectangular wing [DF7LB-FB-81-12] H82-10017 BIRCH, S. A. CALIABBO, C. I. The constricted rigging line trials technique for Aeroballistic characteristics of sonobuoy assessing the opening characteristics of parachute decelerators limited to a length of parachutes three feet [AIAA PAPEE 81-1932] A82-10413 [AIAA PAPEH 81-1950] A82-10425 BIRD, 8. CALLIZO, L. A. Flight trajectory control investigation HiHAT onboard flight computer system architecture [AD-A104542] B82-11048 and qualification BJEBKAAS, C. L. [AIAA 81-2107] A82-10082 Gust front structure observed by Ooppler radar CAHP, D. H. A82-10223 An airport wind shear detection and warning system BJOBKLUHD, B. C. using Doppler radar Interoperability testing of decentralized command, A82-10220 control, communications and intelligence /C3I/ CABPBBLL, 6. S. systems A note on fatal aircraft accidents involving metal [AIAA 81-2205] A82-10143 fatigue BUCK, B. F. A82-11400 An airport wind shear detection and warning system CAB. S. using Doppler radar Structural analysis of fuselages with cutouts by A82-10220 finite element method BOCKSTAHLBB, A.M. 882-10995 Design analysis of high temperature transparent CAPBIiB, C. windshields for high performance aircraft The possibility of using deformable rubber [ASHE PAPBB 81-EHAS-5] A82-10893 components in landing gear BOBBBIHGEB, i. B. A82-10496 High-efficiency hydraulic power transfer units for CABBOIB, B. multisystem aircraft Detection and display of wind shear and turbulence A82-10853 A82-10222 BOLTOH, R. B. CABLSOH, L. A. Development of new lifting parachute designs with A new thermal and trajectory model for high increased trio angle altitude balloons [AIAA PAPEB 81-1921] A82-10407 [AIAA PAPEB 81-1926] A82-10411 BOHBAH, A. J. CABTBB, A. H., JB, system safety program plan A comprehensive bibliography of literature on [AD-A104557] H82-11354 helicopter noise technology BOBELLO, L. [AD-A103331] B82-10812 problems relating to the classical rate-gyro CASSIBB, A. A82-10497 Development of the Iriflex rotor head BOBOVIK, T. 0. A82-11222 Basic problem of aircraft gasturbine engine CEHTEB. J. L. analytic design. II Navigation task partitioning in A82-11463 distributed-processing avionics systems BOBORSK!, B. S. A82-10646 Relationships between naval aviation safety and CBAHIS, C. C. pilot flight experience Integrated analysis of engine A82-11031 [MASA-TM-82713] 882-11491 BBADFIBLD, B. 8. CHABSSBE1G, Z, procedures and analysis technigues for determining An experimental investigation of the rotating static air minimum control speeds stall, surge and wake behind the rotor for a A82-12564 single stage axial compressor BHADSHAB, J. B. 882-11008 Advanced fuel flowmeter for future naval aircraft CHAOQIAHG. L. [AD-A104364] 1182-11063 Second order approximation theory of an arbitrary BBEREB, 6. D. aerofoil in compressible potential flow Fuel for future transport aircraft 882-10982 [ASBE PAPEB 81-H1-80] A82-10965 Aerodynamic calculations and design of subcritical BBOdRBBS. A. P. aerofoils Lightweight diesel engine designs for commuter H82-10983 type aircraft CHAPBAB, B. B. [HASA-CB-165470] H82-11068 Hard limited approaches to correlation velocity BBOBH, R. E.. JB. sensing Radar mapping, archaeology, and ancient land use A82-12636 in the Haya lowlands CHATTBBJBB. J. S. [BASA-CB-164931] 882-11514 General aviation aircraft antennas for the global BBDEBB, A. positioning system Electrical ground testing of aircraft antistatic [NASA-TH-83212] 882-11339 protection A82-10822

B-2 PBBSOHAL AUTHOR IBDEI 00GBABBOT, J. D.

CHB1. C. Superalloy turbine components - Which is the superior manufacturing process, as-HIP, HIP plus Isoforge, or 'gatorizing' of extrusion DAGESHABT, J. B. consolidated billet Amplified crossflow disturbances in the laminar 482-12497 boundary layer on swept wings with suction CHIA, F. I. [HASA-TP-1902] B82-11391 The principles and methods for shaping the wing DAGOSIIIO, T. root regions of a wing-body combination at Hew separators for battery systems transonic and lower supersonic speeds A82-11715 H82-11016 DAIHTI, B. ?. CBOO. I. I. Fractographic determination of fatigue crack Structural analysis computer programs for rigid growth rates in aircraft components multicomponent pavement structures with A82-12697 discontinuities, iESLIQID and IESLAIEB. Report DEG4BI, 0. 1: Program developnent and numerical presentations Development and evaluation of automatic landing [4D-A104545] 882-11498 control laws for light wing loading STOL aircraft CICOLASI, L. [N4S4-CB-166160] S82-10043 Application of nonlinear systems inverses to DEGOEST, P. automatic flight control design: System Adaptation of a turbine test facility to concepts and flight evaluations high-temperature research H82-11083 [BAE-LIB-TBAHS-2064] H82-11089 CIHA, F. S. DEHOPF, Bo L. Subsonic cascade wind tunnel tests using a Development of multivariable controllers for compressor configuration of DCA blades aircraft turbine engines [4D-4104597] 1182-11069 H82-11087 CLARK, J. F. DESABO, B. The evolution of airborne weather avoidance radar An assessment of the use of antimisting fuel in toward a. calibrated remote rain gauge using BEACT turbofan engines A82-10225 [HASA-CB-165258] H82-11230 CLIHE, H. C. DEZIDEBE?, S. G. Computation of high Beynolds number Besults of experimental study of heat transfer to internal/external flows turbine blades with porous cooling [HASA-TH-84049] N82-110U6 A82-11446 COCKBE1L, D. J. DI-II, 1. Aerodynamics and performance of cruciform Initial experimental research into the response of parachute canopies turbojet engine compressors to distortion of [AIAA PAPEB 81-1919] 482-10105 intake pressure Experimental determination of parachute apparent H82-11006 mass and its significance in predicting dynamic A preliminary experimental investigation of the stability response of a turbojet engine to inlet pressure [AIAA PAPEB 81-1920] 482-10406 distortion COOTS, I. H. H82-11007 Superalloy turbine components - ihich is the DIEQIAI, B. superior manufacturing process, as-HIP, RIP plus Finite difference computation of the steady Isoforge, or 'gatorizing1 of extrusion transonic potential flow around airplanes consolidated billet H82-10981 482-12497 OieiACIHXO, I. COBLE!, H. Airborne associative processor /ASPBO/ Rings in the sun - The evolution of Solar Challenger [AIAA 81-2145] A82-10104 A82-12694 DIPASflOO, H. S, COX, S. B. The integrated inertial sensor assembly /USA/ - A Determination of vertical profiles of aerosol size redundant strapdown system for advanced aircraft spectra from aircraft radiative flux navigation and flight control functions measurenents. II - The effect of particle A82-12642 nonsphericity DOBALDSOB, B. J.. JB. A82-12149 Gust front structure observed by Doppler radar COIBE, J. A82-10223 Snperalloy turbine components - Which is the DOVIAI, B. J. superior manufacturing process, as-HIP, HIP plus An airport wind shear detection and warning system Isoforge, or •gatorizing1 of extrusion using Doppler radar consolidated billet 482-10220 A82-12497 Instrumented aircraft verification of clear-air COIBE, J. E. radar detection of low-level wind shear Snperalloy powder engine components; controls A82-10221 employed to assure high guality hardware DOiELL, B. fl. 482-12499 Control laws for adaptive wind tunnels CBOLL, B. H. A82-10985 A modular asymmetric parachute for wind tunnel DOYLE, J. C. testing Hultivariable design techniques based on singular [AIAA PAPEB 81-1933] A82-10414 value generalizations of classical control CBOB, B. P. H82-10051 Discrete address beacon, navigation and landing Limitations on achievable performance of system nultivariable feedback systems A82-10650 882-10052 COLBEBT, I. F. DBEITSEB, G. A. Badar mapping, archaeology, and ancient land use The enhancement of heat exchange in channels /2nd in the Maya lowlands revised and enlarged edition/ [HASA-CB-164931] H82-11514 A82-12222 CZTZEiSKI, K. DUFFI. J. V. The use of the Heber uethod for Polynrethane foams for aircraft shock mounts. 3: minicomputer-assisted numerical analysis of Vibration damping by polyether foams airfoils [AD-A104496] 882-11212 A82-10362 DOGBAIBDI, J. D. Description of the meteorological research radar system aboard H044/Besearch Facilities Center IP-3D aircraft 482-10217

B-3 DOHBAB, i. 6. PEBSOBAL AUTHOB IHOBZ

OOHBAB. 1. 6. FIOHEBIISO, A. High voltage surge and partial discharge test to An assessment of the use of antimisting fuel in evaluate aerospace equipment parts turbofan engines A82-11740 [SASA-CB-165258] B82-11230 DDMH, G. L. FITZ6BHAID, B. B. Advanced aircraft electrical system control Developments in boundary layer Thrust Vector Control technology demonstrator. Phase 1: Requirements A82-10855 analysis and conceptual design FITZSIBBOIS, B. D. [AD-A103922] B82-10326 Bow large should a commuter transport be [AIAA PAPEB 81-1732] A82-10463 FOBSITH, t. J. An investigation of a stoppable helicopter rotor BULB. B. V. with circulation control Propulsion study for Snail Transport Aircraft [HASA-TH-81218] H82-10030 Technology (STAT) FEASCIS, B. A. [BASA-CB-165499] H82-10037 Feedback and minimax sensitivity BABLS, H. B. N82-10058 HiHAT onboard flight computer system architecture FBAHCOIS. J. and qualification Adaptation of a turbine test facility to [AIAA 81-2107] A82-10082 high-temperature research EiTOB, B. E. [BAE-LIB-TBANS-2064] H82-11089 Development of lov modulus material for use in Effects of aircraft noise on the equilibrium of ceramic gas path seal applications airport residents: Testing and utilization of a [BASA-CR-165469] N82-10039 new methodology BISBIBTB, E. A. [HASA-3H-76628] H82-11636 In-sitn calibration of flight heat transfer FBAHZ, I. instrumentation An assessment of the use of antimistiug fuel in [ASBE PAPBB 81-EHAS-13] A82-10901 turbofan engines ELHOHB, K. L. [HASA-CB-165258] H82-11230 An airport wind shear detection and warning system FEEIHABI, B. using Doppler radar A method for determination of the aeroelastic A82-10220 behavior of aircraft with active control systems Instrumented aircraft verification of clear-air [DFV1B-FB-81-05] B82-10047 radar detection of low-level wind shear FBOST. B. A82-10221 An airport wind shear detection and warning systen EH6BLOB. J. J. using Doppler radar Coupled fluid/structure response predictions for A82-10220 soft body impact of airfoil configurations FO-QOI, C. A82-12039 Initial experimental research into the response of EPIFAHO7, V. 0. turbojet engine compressors to distortion of End losses in turbine cascades with porous cooling intake pressure A82-11434 B82-11006 EPPEL. J. C. A preliminary experimental investigation of the Quiet short-haul research aircraft familiarization response of a turbojet engine to inlet pressure document, revision 1 distortion [BASA-TH-81298] N82-10031 1182-11007 BBBSXOFF, fl. H. FOJITA, I. I. Study and development of an integrated head-up Downbursts and microbursts - An aviation hazard display A82-10214 [AD-A104337] H82-11062 BBZBEBGEB, H. Optimum climb and descent trajectories for airline missions 6ABBIBL1I. G. H82-11082 Characteristics and trends of energy consumption BSPOSITO, B. J. in transport missions with aircraft and surface FAA acceptance tests on the HAVSTAB GPS Z-Set vehicles receiver A82-10495 A82-12639 G1LDA. K. fl= BVBBBTT. •- B. flathematical model for the maintenance program of Superalloy powder engine components; controls modern jet aircraft employed to assure high quality hardware [DF¥LB-FB-81-14] H82-10002 A82-12499 GAOBKAB, G. H, On computing Floquet transition matrices of rotorcraft A82-11225 FABBIS, G. GABBABO. B. 1. Hnitipie-scale turbulence modeling of free The effects of flexibility on the steady-state turbulent flows performance of small ribbon parachute models [ASHE PAPEB 81-FE-20] A82-10934 [AIAA EAFEB 81-1923] A82-10408 FAIGIHAB, Z. Stress measurements in a ribbon, parachute canopy An aerodynamic design method for transonic axial during inflation and at steady state flow compressor stage [AIAA PAPEB 81-1944] A82-10420 H82-10984 Stress measurements in bias constructed parachute FEDOBAK, B. canopies during inflation and at steady-state Hemory requirements for future navigation systems [AIA8 PAPEB 81-1945] A82-10421 A82-12637 GABBBIT. B. A. FBIOA, F. ACHA - Fact or fantasy An aerodynamic design method for transonic axial A82-12048 flow compressor stage GATIBBAO, B. J. 882-10984 History of flight testing the L-1011 Tristar jet FEIBHBICH, B. transport. II - Testing highlights since initial Development and evaluation of automatic lauding certification of the L-1011-1 control laws for light wing loading STOL aircraft A82-12049 [HASA-CB-166160] N82-10043 GBISLEB. 0. FBBKO, B. J. Experimental modal analysis of the fuselage panels Crack growth evaluation of a method to convert of an Aero Commander aircraft real-time loads history to a simplified [HASA-CB-165750] H82-10028 engineering spectra A82-12043

B-4 PBBSOBAL AOIHOB IBDEX HOPKI8S. J. J.

GBBSHTEIB, a. I. Experimental study of empennage soap-through vibrations H A82-11U71 BALLIDAI, B. GEVABBT, 6. Commercial EBS considerations for small gas Development and evaluation of automatic landing turbine engines control lavs for light wing loading STOL aircraft A82-12449 [BASA-CB-166160] 882-10043 BABBZ. B. P. GILIAZOT, B. SB. A comparison of theoretical and experimental Study of reingestion of exhaust gases Kith pressure distributions for two advanced fighter different initial temperature in a reversed Mings turbojet engine [BASA-TH-81331] H82-11054 A82-11444 BABBIS, B. L. GILL, F. B. Bodel helicopter rotor impulsive noise Design considerations for optimal flight control A82-11300 systems HAHSHA, P. I. H82-11077 Hultiple-scale turbulence modeling of free GILL, J. C. turbulent flows Propulsion study for Small Transport Aircraft [ASBE PAPEB 81-FE-20] A82-10934 Technology (STAT) BABTBABB, 0. [HASA-CH-165499] H82-10037 Practical design and realization of a digital GILBBATB, H. C. adaptive flight control system General aviation aircraft antennas for the global H82-11079 positioning system BABTBABB, I, [HASA-IB-83212] N82-11339 A CFBP taileron for the Tornado: Construction and GIBABD, L. A., JB. production Air bag impact attenuation system for the AQH-34V [BBB-FE-212/KFK/POB/2] B82-10035 remote piloted vehicle BASBIBOXO. B. [AIAA PAPBB 81-1917] A82-10403 Hew molding method of three-dimensional hollos GLIEBE, P. B. photoelastic model and centrifugal stress Effects of vane/blade ratio and spacing on fan noise analysis of air cooled turbine blade model [AIAA PAPEB 81-2033] A82-10457 [SAI-TB-427T] H82-11067 GOETTIHG. B. C. HABKBS, D. J. Mathematical model for the maintenance program of The certification of digital systems modern jet aircraft 182-11910 [DFVLB-FB-81-14] N82-10002 BAHLBI. D. L. 6OLDBEBG, B. Three navigation systems and their costs of Extending the limits of reliability theory acguiring remote sensing data A82-12318 A82-10049 GOLDSTEIS. B. B. BEDGLEI, D. B. Synthetic aperture radar target simulator Solution to the hidden-line problem [HASA-CASB-HPO-15024-1] N82-10286 A 82-12803 GOODBAB, A. B. HELD, D. B. Sealed lead-acid batteries for aircraft applications Synthetic aperture radar target simulator A82-11716 [JIASA-CASE-HPO-15024-1 ] H82-10286 GOCDBICK, X. F. HICKS, B. B. Comparison of simulation and experimental data for A comparison of theoretical and experimental a gliding parachute in dynamic flight pressure distributions for tvo advanced fighter [AIAA PAPEB 81-1924] A82-10409 vings GOODilB, B. V. [HASA-TH-81331] H82-11054 An investigation of the combustion process in BILOBBBABD, P. B. solid fuel ramjets Multiple Doppler radar observations of PEL structure [AD-A104603] H82-11232 A82-10292 GOBLIBB, G. A. HILDEBBABT, B. V. Implementation of AVBADCOH BBST Variable speed constant freguency /VSCF/ A82-10545 electrical system cuts cost of ownership GBIES, D. A. A 82-11719 Design considerations for duty cycle, life and HILL, B.. JB. reliability of snail limited life engines The case for a defensive air-to-air fighter [AIAA PAPEB 81-1402] A82-1046S A82-12801 GBOSS, S. HILLIG. B. B. Unsolved problems of nickel cadmium batteries Theroal-barrier-coated turbine blade study . A82-11725 [HASA-CB-165351] 882-10040 GBOZDEV, A. A. HODGSOI. *.. B. On low-speed wind tunnels Kith deforoable boundaries Aircraft wing trailing-edge noise A82-11462 CHASA-CB-164952] 882-11039 GOBBTflBB. B. BOLL, B. A CFBP taileron for the Tornado: Construction and Further application and development of an engine production usage/life monitoring system for military services [B BB-FE-212/KFK/PDB/2] 882-10035 A82-12450 GOLIABV, V. V. HOLLAHD, B. L. Calculation of aerodynamic characteristics of jet The statistical theory of radio direction finding flapped airplane [AD-A104156] 882-10027 A82-11459 BOLT. I. 1. GOPTA, B. B. Development of new lifting parachute designs with Omega station 10.2 kHz signal selection made easy increased trim angle A82-12638 [AIAA PAPEB 81-1921] A82-10407 GOBIABOV, A. IA. HOHG-KDI. X. Experimental study of empennage snap-through A new method of cooling turbine vanes vibrations 882-11027 A82-11471 BOBG, Q. GOSE7A, B. I. Finite difference computation of the steady On the use of carbon composites in slat and transonic potential flow around airplanes stabilizer construction 882-10981 A82-11468 BOPKIBS. J. J. GDSKOV, ?. I. Integrated satellite navigation and strapdown End losses io turbine cascades with porous cooling attitude and heading reference systems for civil A82-11434 air carriers A82-12643

B-5 HOBB, B. J. PEBSOBAL AOTBOB IHOEZ

HOHH, B. J. JIB-SBBBG, I. A nev thermal and trajectory model for high A theoretical analysis of the stream surface of altitude balloons revolution with supersonic inlet flow in a [AIAA PAPER 81-1926] A82-10411 transonic axial compressor BDBBABO, J. B., JB. H82-11025 Hodel helicopter rotor impulsive noise JIBQIAG, J. A82-11300 Matrix analysis of wings HUELSTBB. 0. S. B82-10998 Propulsion study for Snail Transport Aircraft JOHABSSOB. B. S, Technology (STAT) Advanced fuel flowmeter for future naval aircraft [HASA-CB-165499] H82-10037 [AD-A104364] N82-11063 HOBTBB, B. J. JOBHSOS. D. B. Digital avionics systems - The BAF experience Seductions in parachute drag due to forebody wake A82-11941 effects HBABG, D. P. [AIAA PAPEB 81-1939] A82-10417 A summary of V/STOL inlet analysis methods JOBBS, J. I. [BASA-TS-82725] H82-11043 Aircraft excrescence drag [AGABD-AG-26U] H82-10020 JOBGBSSEB, 0. S. Aerodynamics and performance of cruciform ZABEHO, S. A. parachute canopies The enhancement of heat exchange in channels /2nd (AIAA PAPEB 81-1919] A82-10U05 revised and enlarged edition/ JUB-LIABG, Z. A82-12222 Initial experimental research into the response of ICHIKABA. T. turbojet engine compressors to distortion of A study on numerical method for evaluating intake pressure spanvise integral in subsonic lifting-surface B82-11006 theory A preliminary experimental investigation of the [BAL-TB-661T] B82-11035 response of a turbojet engine to inlet pressure ISAEV, V. 7. distortion On evaluating the influence of local disruptions S82-11007 of flow over trailing edge and leading edge flaps from the data.of wind tunnel tests of a rectangular wing segment K A82-11465 KALIBIB, E. K. IULIB, B. K. The enhancement of heat exchange in channels /2nd Jet fuel from carbon revised and enlarged edition/ A82-12021 A82-12222 IOB, G. B. KAHPE, B. F. Optimization of the principal design parameters of Developments in boundary layer Thrust Vector Control a passenger aircraft A82-10855 A82-10816 KABIA, B. IVABOV, T. S. Experimental study of subsonic and transonic flows Basic problem of aircraft gasturbine engine past a wing analytic design. II A82-10363 A82-11463 KANT. P. Theory and applications of optimal control in aerospace systems [AGABD-AG-251] B82-11073 JACOB. K. KABTOLA. B. A. Experimental investigations of the separated flow Effects of vane/blade ratio and spacing on fan noise around a rectangular wing [AIAA PAPEB 81-2033] A82-10457 [DFVLB-FB-81-12] H82-10017 KABIBOVA, A. G. JAIB. S. C. Besults of experimental study of heat transfer to Snperalloy powder engine components; controls turbine blades with porous cooling employed to assure high quality hardware A82-11446 A82-12199 KABBABKEB. J. JBBSEB, B. S. Flight trajectory control investigation Improving the HLS through enhanced cockpit displays [AD-A104542] 1182-11048 A82-10649 KBAKIBOLUB, F. SB. JIAFBHG, L. Experimental study of empennage snap-through An experimental investigation of the rotating vibrations stall, surge and wake behind the rotor for a A82-11471 single stage axial compressor KIESSLIBG. t, 082-11008 Calculation of natural modes of vibration for JIAH-ZHOBS, I. rotor blades by the finite element method A theoretical analysis of the stream surface of IDFVLH-FB-81-07] B82-10452 revolution with supersonic inlet flow in a KIPP, B. B. transonic axial compressor In-situ calibration of flight heat transfer B82-11025 instrumentation JIB-DI, I. [ASSE PAPEB 81-EHAS-13] A82-10901 Initial experimental research into the response of KLEIB. V. turbojet engine compressors to distortion of Determination of airplane model structure from intake pressure flight data by using modified stepwise regression N82-11006 [HASA-TP-1916] H82-10041 A preliminary experimental investigation of the KLIBAS, P. C. response of a turbojet engine to inlet pressure A modular asymmetric parachute for wind tunnel distortion testing B82-11007 [AIAA PAPEB 81-1933] A82-10414 JIK-LIABG, J. KXOG, B. G. The arbitrary quasi-orthogonal surface method for Active control elements on the transonic wing of computing three-dimensional flow in turbine the Airbus A-300 (ACTTA A). Airbus A-300 with machinery. 2. Calculation of the reduced longitudinal stability (ACTTA-C) three-dimensional flow with the S sab 1-surface B82-10044 twisted KOB1HAH, D. L. B82-11015 Icing tunnel test of a glycol-exuding porous leading edge ice protection system on a general aviation airfoil [HASA-CB-165444] 882-10021

B-6 PBBSOIAL AOTHOB IBDEI LLOBET, P.

Icing tunnel tests of a conposite porous leading LABGB, E. edge for use with a liquid anti-ice system Optimal flight paths for winged, supersonic flight [HASA-CB-164966] H82-11052 vehicles - Extension to the case where thrust KOBDBATB?. K. II. can be vectored Determination of vertical profiles of aerosol size A82-10310 spectra from aircraft radiative flux LASSITBB, B. S. measurements. II - The effect of particle Design predictions for noise control in the nonsphericity cryogenic Rational Transonic Facility 482-12149 A82-12025 KOBICKB, I. A. LAVOIPIEBBE, G. Stress measurements in a ribbon parachute canopy Fast and accurate gyrocompass using strapdown during inflation and at steady state tuned rotor gyros as a solution to combat [AIAA PAPEB 81-1944] A82-10420 helicopters navigation problems Stress measurements in bias constructed' parachute A82-11927 canopies during inflation and at steady-state LE BA1LEOB, J. C. [AIAA PAPEB 81-1945] A82-10421 Strong matching method for computing transonic KOBHBV, B. B. viscous flows including wakes and separations - On the use of carbon composites in slat and lifting airfoils stabilizer construction A82-10821 A82-11468 LEBOI, I. KOZHE?IIKOV. 10. f. Adaptation of a turbine test facility to Basic problem of aircraft gastnrbine engine high-temperature research analytic design. II [BAE-1IB-TBAHS-2064] H82-11089 A82-11463 LBBODC. C. KBEBS, ?. Cost reduction in air transportation Practical design and realization of a digital [SBIAS-811-150-101] H82-10025 adaptive flight control system LEE, C. K. H82-11079 A proposed flight safety program for the Korean KBEHGEL, J. H. Air Force Air-breathing engine test facilities register [AD-A102373] H82-10023 [AGABD-AG-269] H82-10063 LEE, J. KBEIH, J. New separators for battery systems Hathematical model for the maintenance program of A82-11715 modern jet aircraft LEE. J. T. [DPVLB-FB-81-14] H82-10002 Applications of conventional and Doppler radars KBICHKO, A. A. for aviation safety Jet fuel from carbon 482-10215 A82-12021 LEES, P. EBZISIAK. A. Application of numerical methods to the Experimental study of subsonic and transonic flows calculation of electrostatic fields in aircraft past a wing fuel tanks A82-10363 [AD-4103270] H82-10033 KSEHOFOHTOVA, E. H. LEHHEH, L. On evaluating the influence of local disruptions A CFRP taileron for the Tornado: Construction and of flo« over trailing edge and leading edge production flaps from the data of wind tunnel tests of a [HBB-FE-212/KFK/POB/2] H82-10035 rectangular ving segment LEOBG, P. J. A82-11465 Advanced aircraft electrical system control KffZHEBKO, V. M. technology demonstrator. Phase 1: Requirements Optimization of the principal design parameters of analysis and conceptual design a passenger aircraft [4D-A103922] H82-10326 482-10816 LEPOBSKII, A. A. KDZBETSOf, A. B. Synthesis of system for evaluating gyrostabilizer On evaluating the influence of local disruptions state with unknown disturbances of flov over trailing edge and leading edge A82-11469 flaps from the data of Bind tunnel tests of a LE7ASHOV, P. D. rectangular wing segment Formation of triangular-element stiffness matrix A82-11465 using sliding interpolation 482-11464 LEVIB. A. D. Propfan installation aerodynamics of a LAGABDB, X. supercritical swept wing transport configuration Fast and accurate gyrocompass using strapdown [AI44 PAPEB 81-1563] A82-10466 tuned rotor gyros as a solution to combat LEWIS, D. helicopters navigation problems Helicopter engine technology - With particular A82-11927 reference to the Bolls-Boyce Gem engine LAHB, I. G. A82-10304 Controlling the software/hardware interface for LEXEHDECKBB, H. the validation of avionics systems Control law design for transport aircraft flight [AIAA 81-2159] A82-10116 tasks LABDBL, B. F. B82-11080 Bheological behavior of progressively LIAHG, D. F. shear-thickening solutions Simulation study of a hybrid strapdown attitude A82-11177 and heading reference system LABDEB, H. B. 482-12641 Jet fuel locks to shale oil: The 1980 technology LILLET. D. 6. review On the prediction of swirling flowfields found in [AD-A104414] 1182-11228 axisynaetric coobnstor geometries LABGB, B. H. 482-12120 Flight test results of the model simulation LIB, C.-F. controller for the HFB 320 for in-flight Beal-time, on-line digital simulation of optimum simulation of the A310 airbus maneuvers of supersonic aircraft [ESA-TT-660] B82-10107 [4144 81-2178] 482-10127 LiPIH, 7. P. LLOBET, P. A protective additive for jet fuels Fast and accurate gyrocompass using strapdown A82-12022 tuned rotor gyros as a solution to combat helicopters navigation problems 482-11927

B-7 LOB1EBSTEIB. P. PBBSOHAL AOTHOB IBDEI

LOEBBBSTBIH, P. HAIEB, J. I. B. Superclean superalloy powders by the rotating The Space Shuttle vehicle checkout.involving electrode process flight avionics software £82-12496 [4IAA 81-2141] A82-10100 LOK1I, V. I. BAIEB. B. J. Results of experimental study of heat transfer to The balloon and the airship technological heritage tarbine blades with porous cooling [AI4A PAPEB 81-1912] A82-10401 482-11446 BCALLISTEB, D. LODHIG, D. Application of numerical methods to the Calculation of natural nodes of vibration for calculation of electrostatic fields in aircraft rotor blades by the finite'element method fuel tanks [DFVLB-FB-81-07] H82-10452 [AD-A103270] B82-10033 LOKASZBiICZ, M. BCCABTBI, J. The use of the leber method for An airport wind shear detection and warning system minicomputer-assisted nuaerical analysis of 'using Doppler radar airfoils 482-10220 482-10362 Instrumented aircraft verification of clear-air LOHD. I. J. radar detection of low-level wind shear Hard limited approaches to correlation velocity 482-10221 sensing BCCLODD. J. L., Ill 482-12636 An investigation of a stoppable helicopter rotor LOHDI, 4. S. with circulation control Outsider's look at flight instrumentation [BASA-TH-81218] 882-10030 [DE81-025409] H82-11066 HCD4BBAID, 0. S. LOO, S. The application of improved aluminium alloys and Nonlinear prediction of subsonic aerodynamic loads steels in aircraft structures on wings and bodies at high angles of attack 462-10305 482-11359 BCGHEE, B. J. LT.KOV, O. P. Hind-tunnel results for a modified A protective additive for jet fuels 17-percent-thick .low-speed airfoil section 482-12022 [BASA-TP-1919] H82-11033 LTMBOBTH, L. C. BCGLADB, S. ft. Advanced fuel flowmeter for future naval aircraft Optical sensors for displacement measurement [AO-4104364] H82-11063 482-11407 BCKEEB. B. G. Design of airport pavements for expansive soils M [AD-4104660] S82-11313 HACFABLAHB. A. G. J. HCKEHZIE, D. B. Characteristic and principal gains and phases and Design and development of a low cost servoed rate their use as nultivariable control design tools gyro for unmanned aircraft H82-10050 A82-11932 BAHHABDT. P. D. BCLAUGHLIB, D. E. A numerical three-dimensional turbulent simulation On the prediction of swirling flowfields found in of a subsonic VSTOL jet in' a cross-flow using a axisymmetric combustor geometries finite element algorithm 482-12120 [AD-A104514] H82-11055 BCPBEBSOB, I. B. HAHIOB. B. E. SABS4T applications Automated Paint and Process Line /APPL/ 482-12698 [4144 81-2166] 482-10120 BCHILLIAH, B. H. BABBIBI, 4. Simulation study of a hybrid strapdown attitude 4ir-freon integrated environnental conditioning and heading reference system systen for trainer subsonic aircraft A82-12641 [ASBE P4PEB 81-EH4S-33] 482-10920 BEHDI, I. S. BIBCHIS, 7. Advanced aircraft electrical system control Air-freon integrated environmental conditioning technology demonstrator. Phase 1: Beguirements system for trainer subsonic aircraft analysis and conceptual design [ASHE PAPEB 81-EB4S-33] 482-10920 [4D-4103922] B82-10326 BABKHAH, D. L. HEX, C. The dispersion of drop sizes in gas turbine fuel Besponse of nonlinear aircraft structural panels nozzle sprays to high intensity noise 482-12107 482-12041 BABTIBEZ. B. HELOiOV, ID. V. Aeroaconstic theory for noncompact wing-gust Basic problem of aircraft gasturbine engine interaction analytic design. II [FDBL-81-7] H82-11071 482-11463 BAIIAZH, 4. I. BETCALP, J. I. On evaluating the influence of local disruptions Airborne weather radar and severe weather of flow over trailing edge and leading edge penetration flaps from the data of wind tunnel tests of a 482-10219 rectangular wing segment BEIEB. G. 482-11465 Application of nonlinear systems inverses to BATSOH, J. E. automatic flight control design: System Advanced fuel flowmeter for future naval aircraft concepts and flight evaluations [40-4104364] 1182-11063 N82-11083 HATSDSOE, K. HICHABD. 3. Bew molding method of three-dimensional hollow Adaptation of a turbine test facility to photoelastic Bodel and centrifugal stress high-temperature research analysis of air cooled turbine blade model [B4E-LIB-TB4BS-2064] H82-11089 [H4L-TB-427T] ' H82-11067 BIKALBVICH, V. S. H4TSOZAKI, I. Optimization of the principal design parameters of Sew estimation method for flutter or divergence a passenger aircraft boundary from random responses at saberitical 482-10816 speeds BIEOLOBSKI, B. I. [HAL-TB-667T] B82-11034 ACB.A - Fact or fantasy BATTICK, 4. A. 482-12048 Increasing the lift:drag ratio of a flat delta wing BIKOLL4. f. A82-11899 Standard tests of a research model rotor in a wind tunnel, including model similarity [BBVG-FBBT-79-16] 882-10016

B-8 PEBSOHAL AOTHOB IBDEX PDBVIS, J. i.

HILLS, J. E. PAPPE, B. P. Digital avionics: Promise and practice - An Control of electromechanical actuator elements for airlines experience in the field flight vehicles A82-11942 A82-12170 HIBOHEB. A. PAPPE. V. P. Limiting payload deceleration daring ground impact Control of electromechanical actuator elements for [AIAA PAPEB 81-1918] A82-10404 flight vehicles BITCHELL, P. A82-12170 Bridging the gap from aircraft to space computers PAIEBSOB, J. H. [AIAA 81-2142] A82-10101 Aircraft excrescence drag HOOBE, J. P. [AGABD-AG-264] N82-10020 The digital civil aircraft PATBICK, J. f, A82-11938 Air supply system bite for Boeing 767 airplane BOBBIS, C. E. K.. JB. [ASHB PAPEB 81-EHAS-7] A82-10895 Parametric study of microwave-powered PAVLOV. V. A. high-altitude airplane platforms designed for Experimental study of empennage snap-through linear flight vibrations [HASA-TP-1918] H82-11050 A82-11471 HOSIBA, L. I. PAVLOTSEII. V. P. A protective additive for jet fuels One reason for the onset of high-frequency A82-12022 self-excited oscillations IOEBSCHBB, D. A82-11448 A contribution to the stabilization of flight PEOEBSEB, B. E. vehicle parachute systems Advanced fuel flowmeter for future naval aircraft [ESA-TT-679] H82-10046 [AD-A104364] H82-11063 HUBDOCK, 6. A. PEEL, C. J. Hard limited approaches to correlation velocity The application of improved aluminium alloys and sensing steels in aircraft structures A82-12636 A82-10305 HOBPHT. E. C. PEBG, S. I. J. Determination of airplane model structure from Bheological behavior of progressively flight data by using modified stepwise regression shear-thickening solutions [HASA-TP-1916] H82-10041 A82-11177 HOBBI, D. G. PEXEBSOB, C. B. Effects of vortex flaps on the low-speed Reductions in parachute drag due to forebody wake aerodynamic characteristics of an arrov ving effects [HASA-TP-1914] H82-11013 [AIAA PAPEB 81-1939] A82-10417 HIEBS, A. F. PETBOV, B. I. HiHAT onboard flight computer system architecture Control of electromechanical actuator elements for and qualification flight vehicles [AIAA 81-2107] A82-10082 A82-12170 PIEBBBPOBT, D. Towards minimum power for environmental control in N transport aircraft HADKABMI, A. A. [ASBE PAPEB 81-EHAS-4] A82-10892 Comparative study of flare control laws PIBES, S. [NASA-CB-164903] N82-10032 An influence coefficient method for the BAGLE-BSHLBflAB, J. application of the modal technique to wing The Shock and Vibration Digest, volume 13, no. 9 flutter suppression of the DAST ARi-1 wing [AD-A105062] N82-10421 [HASA-CB-165772] 1182-11070 HAIK, H. K. PLESS, R. B. Development of aircraft production engineering Acoustic emission - An emerging technology for discipline at III, Bombay assessing fatigue damage in aircraft structure A82-11317 A82-11149 HELSOS, S. C. POPE, B. E. How large should a commuter transport be The need for multivariable design and analysis [AIAA PAPEB 81-1732] A82-10463 techniques •GOIBH, T. H. H82-10049 Advanced fuel flowmeter for future naval aircraft PBASAD, 0. S. S. [AD-A104364] N82-11063 On computing Floquet transition matrices of NIKIFOBOVA. I. C. rotorcraft Jet fuel from carbon A82-11225 A82-12021 PBASAD, D. B. HOVAD, A. A. Ideal and simulated performance of an aircraft in On the question of trailing airplane motion the terrain following mission A82-11470 A82-11302 BOVAE, B. C. PBATI, S. Development of low modulus material for use in LQG mnltivariable design tools ceramic gas path seal applications 1182-10054 [HASA-CB-165469] H82-10039 PBBSS, J. Performance analysis of enroute air traffic control computers in the Rational Airspace System [AIAA 81-2203) A82-10140 OIEILL, J. J. PBIHZ, B. A hidden advantage of permanent magnet electrical Batheoatical model for the maintenance program of generating systems modern jet aircraft A82-11720 [DFVLB-FB-81-14] H82-10002 OBZECHOBSKI, J. A. POCHKOV, T. A. A numerical three-dimensional turbulent simulation Jet fuel from carbon of a subsonic VSTOL jet in a cross-flow using a A82-12021 finite element algorithm POBI. S. H. [AD-A104514] H82-11055 Design considerations for the direct digital control of dry-tuned gyroscope A82-11933 PDBVIS, J. B. PALB, L. Theoretical analysis of parachute inflation Development of a nylon-Kevlar recovery system for including fluid kinetics the CL-289 /AM/DSD 502/ surveillance drone- [AIAA PAPEB 81-1925] A82-10410 [AIAA PAPEB 81-1952] A82-10427

B-9 QI-XUB, I. PEBSOIAL AOTHOB IBDEI

BOBIHSOB. C. I. Aircraft digital input controlled hydraulic Q actuation and control system QI-XOH, I. [40-4104263] H82-11072 Initial experimental research into the response of BOCK. S. fl. turbojet engine compressors to distortion of Development of mnltivariable controllers for intake pressure aircraft turbine engines H82-11006 H82-11087 & preliminary experimental investigation of the BODGEBS, C. response of a turbojet engine to inlet pressure A new APO for medium place aircraft environmental distortion control systems H82-11007 [ASHB P4PEB 81-EH4S-1] 482-10889 QIBGIIOBG, I. BOEBfl. B. P. The automatic natrix force method and techniques Superalloy turbine components - Which is the for handling more complex computations with superior manufacturing process, as-HIP, HIP plus given computer capacity Isoforge, or 'gatorizing' of extrusion H82-10994 consolidated billet 482-12497 BOSBHTHAI, T. Satellite geometry considerations for low cost GPS BAGHOHATHAB, S. user eguipment Hind tunnel tests on airfoils in tandem cascade 482-12630 A82-1D987 BODGHTOB, D. RAGSDUE, i. A. The all digital military aircraft Use of Space Shuttle technology in conventional A82-11937 aircraft BO-(JOB, T. QMAA 81-2176] 482-10125 Theoretical investigations and experimental SAJPAOL, V. K. researches for higher subsonic two-dimensional Closed loop environmental control systems for compressor cascade fighter aircraft N82-11024 [&SHE PA PEE 81-EHAS-2] A82-10890 BUFF, S. BAJO. S, H. Development and construction of pilot ejector Dynamic response of aircraft structure to gun seats in Germany from 1938-1945 shock loads [DFVLB-FB-81-04] H82-10026 482-11311 BOHZIAHG, Z. BAHG, E. B. Hatrix analysis of wings Controlling the software/hardware interface for H82-10998 the validation of avionics systems [4144 81-2159] 482-10116 BABGAIAH, V. P. Dynamic response of aircraft structure to gun SALIABIS, C. shock loads A contribution to the stabilization of flight 482-11314 vehicle parachute systems BAIHOHD, E. T. [ES4-TT-679] H82-10046 Aircraft digital input controlled hydraulic SALVIOBI, L. actuation and control system The possibility of using deformable rubber [AD-4104263] N82-11072 components in landing gear REED, B. 4. 482-10496 Parachute technology under pressure SASHEVSKII. T. T. 482-12801 4 protective additive for jet fuels 8BID, D. B. 482-12022 Simulation study of a hybrid strapdovn attitude S4SIBI, D. and heading reference system On computing Floguet transition matrices of 482-12641 rotorcraft 8BID, J. A. I. A82-11225 Design aspects of non rigid airship envelopes SCBAFBB, B. 482-10306 Quantification of the thermal environment for REIHHAIH. J. J. externally carried aircraft stores and ordnance Selected bibliography, of BACfi-NASA aircraft icing A82-12100 publications SCBAFBAIBK, D. [HAS4-TH-81651] H82-11053 Theoretical investigation of the influence of RHODE, D. L. spoiler dynamics on the handling qualities of an On the prediction of stiicling flovfields found in aircraft with direct lift control axisymmetric combustor geometries [ESA-TT-681] H82-10036 482-12120 SCB1IIKEB, B. B, BICCI, B. J. Helicopter rotor trailing edge noise Integration of computer graphics design with [4144 P4PEB 81-2001] 482-10455 analytical models Helicopter rotor trailing edge noise [4144 81-2134] 482-10096 [B4S4-CB-3470] B82-11859 8ICHABDSOI, 0. SCHBEIDEB. H. H. F-56 ligershark Thermal expansion accommodation in a jet engine 482-12775 frame BIBS, E. G. 482-11999 Interoperability testing of decentralized command, SCHiABTZ, A. C. control, communications and intelligence /C3I/ F44 developing new collision avoidance, data systems acquisition and transmission systems [4IA4 81-2205] 482-10143 482-10396 BIX, 0. SCBHEICKABI. D. System identification of the longitudinal motion High voltage surge and partial discharge test to of the DFVLE HFB 320 research aircraft with evaluate aerospace equipment parts particular consideration of control surface 482-11740 effectiveness SCBIEIEHABD. B. 6. [ESA-TT-666] H82-10045 Icing tunnel test of a glycol-exuding porous BOBEBIS, L. leading edge ice protection system on a general V/STOL aircraft and fluid dynamics aviation airfoil [HAS4-TH-81328] H82-10029 (HASA-CB-165444] B82-10021 BOBEBIS, B. E. SB6BEST, J. D. Air-film cooling returns to ramjets Advanced aircraft electric power system [ASHE P4PEB 81-EB4S-8] 482-10896 482-11718

B-10 PBBSOBAL AOIHOB IIDEX STOCKBB, B. P. 1.

SBIF, J. SLATOB, T. Hov large should a commuter transport be A mathenatical model of an over-sea airborne DBF [4I4A PAPEB 81-1732] A82-10463 radio link SBLLABS. B. J. A82-11406 Sophisticated aircraft structure developments - SBIIfl, J. B. Combat aeroplanes Application of numerical methods to the &82-10309 calculation of electrostatic fields in aircraft SEBDBBAK, K. L. fuel tanks Sealed lead-acid batteries for aircraft applications [AD-A103270] H82-10033 482-11716 SHIXB, B. C. SBPOL7BDA, D. Propfan installation aerodynamics of a Application of numerical modeling to gas turbine supercritical swept wing transport configuration combnstor development problems [AIAA PAPBB 81-1563] A82-10466 A82-12118 SHITB. B. E. SBBAFII, B. Analysis of augmented aircraft flying qualities Detection and display of Hind shear and turbulence through application of the Seal-Smith criterion A82-10222 [AIAA PAPBB 81-1776] A82-10462 SBHDIUK, V. A. SHITB, T. B. Control of electromechanical actuator elements for Synchronous fault-tolerant flight control systems flight vehicles [AIAA 81-2109] A82-10083 A82-12170 SOLOBOB, H. L. SHAPIHO. A. A. A navigation systems planning model On evaluating the influence of local disruptions A82-12640 of flow over trailing edge and leading edge SOBG. C. J. flaps from the data of wind tunnel tests of a On the kernel function collocation method in rectangular wing segment steady subsonic flow for wing with control A82-11465 surfaces SBABBA, A. V. H82-12023 Impact-initiated damage thresholds in composites SOH6LIHG. L. 482-12028 An aerodynamic design method for transonic axial SHAB, L. H. flow compressor stage Botor wake characteristics relevant to B82-10984 rotor-stator interaction noise generation SOBBICHSEB, T. [AIA4 PAPEB 81-2031] A82-10456 Baseline data on utilization of low-grade fuels in SHEKLETO8. J. B. gas turbine applications. Volume 3: Emissions The CIVIC - A concept in vortex induced evaluation combustion. II [DE81-903764] B82-10254 [ASBE PAPEB 81-6T-12] 482-11997 SBI-JAIABIBA. B. SBBHG, I, X. A microprocessor-based data acquisition system for The principles and methods for shaping the wing stall/spin research root regions of a wing-bod; combination at [AIAA 81-2177] A82-10126 transonic and loner supersonic speeds STAHCZAK. B. H82-11016 Analytical determination of undercarriage SBI-CAB, Z. retraction kinematics The arbitrary quasi-orthogonal surface method for A82-10364 computing three-dimensional flow in turbine STATOB. 0. 7. machinery. 2. Calculation of the Propulsion study for Small Transport Aircraft three-dimensional flow with the S sab 1-surface Technology (STAT) twisted [HASA-CH-165499] H82-10037 H82-11015 SIBBLBTSOV, 7. G. SHIJDI. 1. Control of electromechanical actuator elements for Finite difference computation of the steady flight vehicles transonic potential flow around airplanes 482-12170 882-10981 STEIB, G. SBOB. G. I. LQG-based mnltivariable design: Frequency domain A protective additive for jet fuels interpretation 482-12022 H82-10053 SHOO, B. LQG mnltivariable design tools Nonlinear prediction of subsonic aerodynamic loads H82-10054 on wings and bodies at high angles of attack STEH6EI. B. F. A82-11359 A microprocessor-based data acquisition system for SHOOLIAB, 6. stall/spin research Structural analysis of fuselages with cutouts by [4144 81-2177] 482-10126 finite element method STEPHEBSOI, A. B. H82-10995 A navigation systems planning model SI-BOH6, L. A82-12640 Initial experimental research into the response of STEPKA, P. S. turbojet engine compressors to distortion of Thermal and flow analysis of a convection, intake pressure air-cooled ceramic coated porous metal concept N82-11006 for turbine vanes A preliminary experimental investigation of the [ASHE PAPBB 81-BT-48] A82-10952 response of a turbojet engine to inlet pressure STEB1II, 7. A. distortion On evaluating the influence of local disruptions H82-11007 of flow over trailing edge and leading edge SIDDIQDI. B. 0. A. flaps from the data of wind tunnel tests of a Applications of finite element method in aerospace rectangular wing segment power systems design A82-11465 A82-11717 SXB7BBS, G. B. B. SIEBEBS, P. A. The net-skirt to a parachute canopy as a device to Theroal-barrier-coated turbine blade study prevent inversion [H4S4-CB-165351] B82-10040 [AIAA PAPBB 81-1927] 482-10412 STOCKBBBB, F. J. SKAISXES, S. J. 1 'Quiet please Experimental study of fuel heating at low A82-10854 temperatures in a wing tank model, volume 1 SKELTOB. B. E. [B4S4-CB-165391] H82-11224 Control design of flexible spacecraft STOCKS. B. P. B. B82-11081 Fatigue substantiation of non-linear structures 482-11224

B-11 SXOLLBBI, J. I. PEBSOBAL AUTHOB IBDEI

STOLLEBI, J. I. TSUJIKABA, G. S. Increasing the lift:drag ratio of a flat delta wing Closed loop environmental control systems for A82-11899 fighter aircraft STOLP, P. C. [ASHE PAPEB 81-ENAS-2] A82-10890 Propulsion study for Small Transport Aircraft TSOB, I. C. Technology (STATJ The principles and methods for shaping the wing [NASA-CB-165499] 1182-10037 root regions of a wing-body combination at STOHE, B. H. transonic and lower supersonic speeds Seven years experience with Kevlar-49 in the 1182-11016 Lockheed L-1011 Tristar IOOHELA, C. A82-12647 Test Pilots' Aviation Safety Horkshop, D.S. Naval STBICKBB, B. Postgraduate School, Honterey, CA, February Standard tests of a research model rotor in a wind 25-28, 1981, Proceedings tunnel, including model similarity A82-10500 [BHVG-FBBT-79-16] H82-10016 TOBK. B. STOKGBSS, G. J. Experimental investigations of the separated flow Application of numerical modeling to gas turbine around a rectangular wing combustor development problems [DFVLB-FB-81-12] H82-10017 A82-12118 TOBHEB, C. I. Validation studies of turbulence and combustion Air bag impact attenuation system for the AQH-31V models for aircraft gas turbine combustors remote piloted vehicle A82-12267 [AIAA PAPEE 81-1917] A82-10403 STOTZflAH, I. L. Antenna theory and design A82-12323 u SOBBAHRAHYAH. B. S. OHDEBiOOD, B. L. Ideal and simulated performance of an aircraft in Aircraft wing trailing-edge noise the terrain following mission [BASA-CB-164952] H82-11039 A82-11302 OBQOHABT, B. SUHG, C. C. Limiting payload deceleration during ground impact The principles and methods for shaping the wing [AIAA PAPEB 81-1918) A82-10101 root regions of a wing-body combination at transonic and lower supersonic speeds H82-11016 V SOTTOB, I. G. VABBOCKEB, B. C. Considerations and applications for the use of Variable speed constant frequency /VSCF/ fluidics in aerospace controls electrical system cuts cost of ownership A82-12087 A82-11719 SIBO, S. A. VEPA, B. Application of numerical modeling to gas turbine Numerical treatment of helicopter rotor stability combustor development problems problems A82-12118 A82-12045 Validation studies of turbulence and combustion TIBSOB, J. B. models for aircraft gas turbine combustors Emerging technologies in aerospace structures, A82-12267 design, structural dynamics and materials; Proceedings of the Aerospace Conference, San Francisco, CA, August 13-15, 1980 A82-12026 TkKftBAU, K. VLCEK, C. Hew molding method of three-dimensional hollow Bridging the gap from aircraft to space computers photoelastic model and centrifugal stress [AIAA 81-2142] ' A82-10101 analysis of air cooled turbine blade model [HAL-TB-427T] H82-11067 TALYZIH, V. ». w Basic problem of aircraft gastnrbine engine IAGHEB, B. C. analytic design. II . Low maintenance hydraulic accumulator A82-11463 [AD-A103947] H82-10034 TAB, C. P. liLIEBS, B. iind tunnel tests on airfoils in tandem cascade Limiting payload deceleration during ground impact A82-10987 [AIAA PAPEB 81-1918] A82-10404 TEHKE1, B. BABBEB, B- S. An airport wind shear detection and warning system Omega station 10.2 kBz signal selection made easy using Doppler radar A82-12638 A82-10220 BASSEBBEBG, S. TEBBY, 6. Air-film cooling returns to ramjets Sophisticated aircraft structure developments - [ASSE PAPEB 81-EHAS-8] A82-10896 Coabat aeroplanes BEBB. 0. B. A82-10309 Development of a nylon-Kevlar recovery system for THEOBALD, B. A. the CL-289 /AH/DSD 502/ surveillance drone Evaluation of the acoustic measurement capability [AIAA PAPEB 81-1952] &82-10427 of the RASA Langley V/STOL wind tunnel open test BEBB. J. fl. section with acoustically absorbent ceiling and Some possibilities for composite light aircraft floor treatments construction [NASA-CB-165796] N82-10059 A 82-10307 THIELE, 6. A. BEBB, B. C. Antenna theory and design 60 KVA 4DP permanent magnet VSCF starter generator A82-12323 system - Generator system performance TIAHGI, I. characteristics Structural analysis of fuselages with cutouts by A82-11721 finite element method BEBEB. T. H82-10995 The effects of flexibility on the steady-state TIKHOHIROT, V. A. performance of small ribbon parachute models On the use of carbon composites in slat and [4IAA PAPEB 81-1923] A82-10408 stabilizer construction BEI-ZAO, G. A82-11468 A new method of cooling turbine vanes TSDI, J. N82-11027 Tangential sensitivity of EH receivers A82-11020

B-12 PBBSOBAL 10IHOB IHDEX ZHAO-TAB, Q.

BEIDB. Z. An experimental investigation of toe rotating stall, surge and wake behind the rotor for a single stage axial compressor ZIAO-KABG. X. H82-11008 The arbitrary guasi-orthogonal surface method for WEISS. B. computing three-dimensional flow in turbine A solution to the static geometry problem for machinery. 2. Calculation of the JIIDS relative navigation three-dimensional flow .with the S sub 1-snrface A82-12631 twisted BELCH, B. B. H82-11015 Determination of vertical profiles of aerosol size ZIB-TOAB, B. spectra from aircraft radiative flux Initial experimental research into the response of measurements. II - The effect of particle turbojet engine compressors to distortion of nonsphericity intake pressure A82-12149 N82-11006 BELLS, H. 1. J. A preliminary experimental investigation of the Bind tunnel tests on airfoils in tandem cascade response of a turbojet engine to inlet pressure A82-10987 distortion BEB-LAB, I. 882-11007 Initial experimental research into the response of IIHHAI, Z. turbojet engine compressors to distortion of An aerodynamic design method for transonic axial intake pressure flow compressor stage N82-11006 H82-1098U A preliminary experimental investigation of the IODBCBOB, I. response of a turbojet engine to inlet pressure Structural analysis of fuselages with cutouts by distortion finite element method H82-11007 H82-10995 BHIIE. H. Composite main rotor tabular braided A82-105U7 UDDOiS, B. E. YA70Z, T. A modular asymmetric parachute for wind tunnel Experimental determination of parachute apparent testing mass and its significance in predicting dynamic [AIAA PAPEB 81-1933] A82-10U14 stability ilDIALL, S. E. [AIAA PAPEB 81-1920] A82-10406 Aeroacoustic theory for noncompact wing-gust IBABBA, A. H. interaction Low speed testing of the inlets designed for a [FDB1-81-7] H82-11071 tamden-fan V/STOL nacelle BIEBB, B. [HASA-TH-82728] H82-11042 Fractographic determination of fatigue crack TIBG, Z. growth rates in aircraft components A theoretical analysis of the stream surface of A82-12697 revolution with supersonic inlet flow in a BILBBT. C. B. transonic axial compressor KC-135 Avionics Modernization Hot Bench H82-11025 [AIAA 81-2105] A82-10081 YIP, L. P. BILK, K. B. Effects of vortex flaps on the low-speed Applications of conventional and Doppler radars aerodynamic characteristics of an arrow wing for aviation safety [HASA-TP-1914] N82-11013 A82-10215 IIOLIO. C. 1ILLABD, B. B. Hatrix analysis of wings Low maintenance hydraulic accumulator H82-10998 [AD-A1039K7] H82-10031 IOSHID4, I. IILLIAHS. J. C. Hew molding method of three-dimensional hollow Design of high integrity multivariable control pbotoelastic model and centrifugal stress systems analysis of air cooled turbine blade model H82-10055 [HAL-TB-U27T] H82-11067 IILLIAHS. B. C. IOOBG, A. D. Low speed testing of the inlets designed for a Aircraft excrescence drag tamden-fan V/STOL nacelle [AGABD-AG-26U] B82-10020 [NASA-TH-82728] 882-11012 IO-HIHG, Z.. ilLLSHIBE. B. L., JB. A new method of cooling turbine vanes SEL and EPNL noise duration coefficients for the 882-11027 7U7 and T-38 aircraft IDAS, Z. [SASA-TH-8321U] , H82-11860 Hatrix analysis of wings IILHOTB, B. 6. N82-10998 Computation of high Reynolds number TUBES, Z. internal/external flows Finite difference computation of the steady [HASA-TH-81049] B82-110U6 transonic potential flow around airplanes BILSOB, J. H82-10981 Detection and display of wind shear and turbulence A82-10222 BILSOB, f. B. Design analysis of high temperature transparent ZABES, G. windshields for high performance aircraft Hnltivariables design: The optimization of [ASBE PAPEB 81-EHAS-5] A82-10893 approximate inverses BOBHAB, B. B. H82-10057 A geometric approach to mnltivariable control Feedback and minimal sensitivity system synthesis H82-10058 H82-10056 ZEBKEB, B. A. BOODLBT, 6. B. Synthetic aperture radar target simulator Light aircraft structural design in non-metallics [HASA-CASE-HPO-1502U-1] B82-10286 - Dse of composite honeycomb for light aircraft ZEBPOLICB, B. A. A82-10308 Heoory regnirements for future navigation systems A82-12637 ZBAO-IAB, Q. Theoretical investigations and experimental researches for higher subsonic two-dimensional compressor cascade H82-11024

B-13 ZHIBEI, L. PEBSOHA1 AUTHOB IBDEI

ZHJWBI, L. An experimental investigation of the rotating stall, surge and vake behind the rotor for a single stage axial compressor 1182-11008 2H0, P. Honlinear prediction of subsonic aerodynamic loads on wings and bodies at high angles of attack 482-11359 ZHUAH-SHB, D. A theoretical analysis of the stream surface of revolution with supersonic inlet flow in a transonic axial compressor 882-11025 ZI-LOBG, H. Initial experimental research into the response of turbojet engine compressors to distortion of intake pressure N82-11006 A preliminary experimental investigation of the response of a turbojet engine to inlet pressure distortion H82-11007 ZOLEZZI, B. A. Propulsion study for Small Transport Aircraft Technology (STAT) [NASA-CB-165199] H82-10037 ZOSG-IOAN, B. Initial experimental research into the response of turbojet engine compressors to distortion of intake pressure H82-11006 & preliminary experimental investigation of the response of a turbojet engine to inlet pressure distortion B82-11007 ZBSIC, D. S. Instrumented aircraft verification of clear-air radar detection of low-level wind shear A82-10221 ZOO-BED, J. A theoretical analysis of the stream surface of revolution with supersonic inlet flow in a transonic axial compressor H82-11025

B-11 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 145) FEBRUARY 1982 Typical Contract Number Index Listing

530-01-13-02 882-11050 CONTRACT 532-02-11 882-10031 I NUMBER 534-01-13-14 B82-11391

BAS1-14693 N82-10028

NASA ACCESSION I NUMBER | Listings in this index are arranged alphanumerically by contract number. Under each contract number, the accession numbers denoting documents that have been produced as a result of research done under that contract are arranged in ascending order with the IAA accession numbers appearing first. The accession number denotes the number by which the citation is identified in either the IAA or STAR section. iF PBOJ. 2003 BAS3-20643 A82-11999 N82-11062 BAS3-21727 882-10040 AF PBOJ. 2301 BAS3-21977 882-11224 882-10033 BAS3-21995 882-10037 AF PBOJ. 2403 882-10038 1182-11048 HAS3-22045 882-11230 AF PBOJ. 2480 BAS3-22062 A82-10457 882-11228 BAS3-22134 882-10039 IF PBOJ. 3048 BAS3-22149 882-11068 882-10033 BAS4-2518 H82-11078 AF PBOJ. 3145 8AS6-3072 A82-10411 882-10034 BAS7-100 A82-11177 882-10326 882-10286 H82-11072 B82-11514 AF-AFOSB-0223-80 BAS8-31377 A82-10220 882-10033 A82-10221 DA PfiOJ. 1L2-62202-AH-85 BAS8-33458 A82-10220 882-11064 A82-10221 882-11065 BGB-14-001-008 DA PBOJ. 4A7-62719-AT-40 A82-10214 882-11498 B01A-04-4-158-1 DAAG29-C-027 A82-11300 A82-10214 DAAK80-79-C-0270 BSF A1H-74-03406-A02 882-11064 A82-10220 882-11065 A82-10221 DE-AC04-76DP-00789 BSF AIH-76-24236 A82-10414 A82-10292 DBA001-80-C-0177 BSF ATH-77-22384 882-11354 A82-12149 DTFA01-80-Y-10597 BSF A1H-78-01074 882-10812 A82-10214 EPBI PBOJ. 1079-3 BSF ATH-78-05743 882-10254 A82-12149 F29601-76-C-0051 BSF ATH-78-12401 882-11313 A82-10220 F33600-80-C-0473 A82-10221 A82-10081 BSF ECS-80-12-565 F33615-68-C-3421 B82-10058 A82-10893 BSG-1296 A82-12028 F33615-74-C-2037 BSG-1377 B82-11039 A82-11721 BSG-1480 882-10032 F33615-76-C-1243 BSG-2142 B82-11071 882-11062 B00014-75-C-01444 F33615-76-C-2088 882-11078 882-10034 B00024-81-C-5301 F33615-77-C-2034 B82-10027 882-11072 B62269-78-C-0069 F33615-78-C-2200 B82-11063 A82-11721 B62269-79-C-0295 F33615-78-C-3607 B82-11055 882-11048 B62269-80-C-0146 F33615-80-C-2004 A82-10646 882-10326 B-7405-EBG-36 F49620-79-C-0169 882-11046 A82-12041 882-11066 BAG3-71 882-10021 500-42-62 882-11043 882-11052 505-31-33-05 B82-11033 BAG3-74 A82-12120 505-31-41 B82-11054 BASB-3542 882-11636 505-32-03-01 B82-11860 BAS1-14611 882-10059 505-32-12 B82-10039 BAS1-14693 882-10028 505-34-13-02 882-11339 BAS1-15593 882-11070 505-34-33-06 B82-10041 BAS1-15730 A82-10455 882-10042 882-11859 505-42-71 B82-10029 BAS1-15988 A82-10934 505-43-13-01 882-11013 8AS2-9410 882-10043 505-44-12 B82-10021

C-1 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037(l45) 4. Title and Subtitle 5. Report Date February 1982 AERONAUTICAL ENGINEERING 6. Performing Organization Code A Continuing Bibliography (Supplement 1^5)

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

10. Work Unit No. 9. Performing Organization Name and Address ... National Aeronautics and Space Administration Washington, D.C. 205^6 11. Contract or Grant No.

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

14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract

Th is B ibl iography 1 ists 326 reports, articles, and other documents introduced into the NASA scientific and technical information system in January 1982.

17. Key Words (Suggested by Author(s)) 18. Distribution Statement Aerodynamics Aeronautical Engineering Aeronautics Unclassified - Unlimited Bibl iographies

1 9. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price* Uncl assi f led Unclassified 1 04 $5-00 HC

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

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