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k^B* 4% Aeronautical NASA SP-7037 (103) Engineering December 1978 A Continuing SA Bibliography with Indexes

National Aeronautics and Space Administration

• L- I Aeronautical EngineerfrljAer 3 i. • erjng Aeronautical Engineerjn igineering Aeronautical Engim cal Engineering Aeronautical E nautical Engineering Aeronaut Aeronautical Engineering Aen sring Aeronautical Engineerinc . gineering Aeronautical Engine ;al Engineering Aeronautical E lautical Engineering Aeronaut Aeronautical Engineering Aerc ring Aeronautical Engineering ACCESSION NUMBER RANGES

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

STAR(N-10000 Series) N78-30038—N78-32035

IAA (A-10000 Series) A78-46603—A78-50238

This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by Informatics Information Systems Company. NASA SP-7037(103)

AERONAUTICAL ENGINEERING

A Continuing Bibliography

Supplement 103

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in November 1978 m • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA)

Scientific and Technical Information Branch 1978 National Aeronautics and Space Administration Washington, DC This Supplement is available from the National Technical Information Service (NTIS). Springfield. Virginia 22161. at the price code E02 ($475 domestic. $9.50 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 Since that time, monthly supplements have been issued. This supplement to Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 457 reports, journal articles, and other documents originally announced in November 1978 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, IA A 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 (A78 10OOO Series)

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VIM TABLE OF CONTENTS

IAA Entries 507 STAR Entries 543

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 -»-N78-10020*jjf Boeing Vertol Co Philadelphia Pa — -•-WIND TUNNEL INVESTIGATION OF ROTOR LIFT AND NASA ACCESSION PROPULSIVE FORCE AT HIGH SPEED DATA ANALYSIS -CORPORATE NUMBER -^•Frank McHugh Ross Clark and Mary Soloman Oct 1977 -• SOURCE 211 p 3 Vol -..(Contract NAS1-14317) TITLE . pMNASA-CR-145217-App-l D210-1M351) Avail NTIS-*- HC A10/MF A01 CSCL 01A .PUBLICATION The basic test data obtained during the lift-propulsive force DATE AUTHORS. limit wind tunnel test conducted on a scale model CH 47b rotor are analyzed Included are the rotor control positions blade loads and six components of rotor force and moment corrected for -AVAILABILITY CONTRACT hub tares Performance and blade loads are presented as the SOURCE OR GRANT. rotor lift limit is approached at fixed levels of rotor propulsive force coefficients and rotor tip speeds Performance and blade load trends are documented for fixed levels of rotor lift coefficient REPORT as propulsive force is increased to the maximum obtainable by • COSATI NUMBERS. the model rotor Test data is also included that defines the CODE effect of stall proximity on rotor control power The basic test data plots are presented in volumes 2 and 3 Author

TYPICAL CITATION AND ABSTRACT FROM IAA

NASA SPONSORED. AVAILABLE ON H MICROFICHE [-*• A78-13071 * H ^^ Toward a new V/STOL generation L Roberts-w- AIAA ACCESSION NUMBER I I and S B Anderson (NASA, Ames Research Center, Moffett Field. •»- Calif^Astronautics and Aeronautics, vol 15, Nov 1977;*f) 22-27 AUTHORS While many V/STOL problems are now better understood and TITLE. technology has progressed to the point where higher thrust/weight ratios and greater stability augmentation are achievable, a number of AUTHOR'S TITLE OF still existing insufficiencies provide a sobering reminder that learning AFFILIATION PERIODICAL- in ground testing and simulation, and careful methodical planning, are a prerequisite for any research and development program The -PUBLICATION present paper is centered on the major technical problems for the DATE Navy Type multimission V/STOL aircraft The aircraft's configurations with and without forward lift fan are discussed, along with the propulsion systems, testing techniques, controls, displays, flight dynamics, and ground/flow field interactions V P AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 103)

DECEMBER 1978 IAA ENTRIES A78-46965 ff Stability augmentation by eigenvalues control and model matching M N Wagdi (Cairo, University, Cairo, Egypt) Journal of Guidance and Control, vol 1, Sept -Oct 1978, p 381-383 Generally, when performing certain maneuvers, the aircraft stability is considerably degraded, thus limiting its performance A78-46915 Methods available to ONERA for analysis of capabilities The utilization of a stability augmentation system combustion chambers (Methodes dispombles a I'ONERA pour le permits the aircraft to perform the required maneuver with the calcul des chambres de combustion) R Borghi, F Hirsmger, and H desired stability requirements A description is provided of a stability Tichtmsky (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seme, augmentation system which could be considered as a version of a France) Entropie. vol '4, May June 1978, p 3-14 23 refs In digital fly by-wire control system The considered scheme differs French fundamentally from the conventional model-following techniques It The approaches described treat in a detailed manner not the requires knowledge of the model eigenvalues rather than the model global problem of combustion in a combustion chamber but rather coefficient matrix A new approach for eigenvalues assignment is the processes taking place in different regions of the chamber The presented It is valid for distinct as well as repeated eigenvalues, discussion covers the principle of decomposition of the combustors complex or real The control vector is linearly related to the system into different subsets to which the various methods apply, the state and to the command input through two gam matrices G R different physical and chemical processes to be schematized under the dual requirements of accuracy and economy of calculation, two-dimensional steady analyses without recirculation, and an A78-47124 Neutralization problem for a Space Shuttle H unsteady two-dimensional analysis with recirculation applied to Kikuchi (Nihon University, Tokyo, Nagoya University, Nagoya, ignition in a recirculation core PTH Japan) In International Symposium on Space Technology and Science, 12th, Tokyo, Japan, May 16-20, 1977, Proceedings Chofu, Tokyo, National Aerospace Laboratory, A78-46961 ff Constant-control rolling maneuver T Hacker 1977,p 893-899 12refs (Institute for Fluid Mechanics and Aerospace Design, Bucharest, An attempt is made to gain insight into the mechanism of Rumania) Journal of Guidance and Control, vol 1, Sept-Oct 1978, Shuttle Orbiter charging and discharging during the operation of the p. 313-318 10 refs electron gun.^as well as to find some effective methods for charge Practical interest for supplementing stability analysis by domain- neutralization, particularly for pulsed electron beams If a pulsed or of-attraction considerations in studying constant-control maneuvers bunched electron beam rather than a pure continuous dc beam is is pointed out Implications in cost of computing work of the free used, the vehicle charge neutralization problem can be alleviated by parameter choice are estimated A technique is presented for defining increasing amplitude and decreasing duty cycle in beam pulses, the entire safe range of maneuver in terms of regions of allowable because a high positive potential of the vehicle can be discharged or and actually attainable roll rate values and the corresponding aileron shorted through a distributed capacitance between the beam and inputs Gravity effects are considered to define peak-value correc- conducting areas in the form of ac displacement current rather than tions of limits on the steady-state values of system variables and to dc current The thermal insulator skin offers an ac short-circuit effect estimate the maximum allowable duration of a rolling maneuver An acting as a dielectric capacitor to facilitate ac neutralization S 0 illustration of how a Lyapunov function provides estimate of the domain of attraction is given (Author) A78-47172 H Trailing vortices II (Problem wirow zaskrzyd- lowych II) J Staszek Technika Lotnicza i Astronautyczna, vol 33, A78-46962 ft Digital control law synthesis in the w prime July 1978, p 1215 In Polish domain R F Whitbeck and L G Hofmann (Systems Technology, The paper deals with the mechanisms of trailing vortex Inc. Hawthorne, Calif) Journal of Guidance and Control, vol 1, generation, and with vortex development and decay The influence Sept-Oct 1978, p 319-326 11 refs Contract No of the turbulence induced by wide-body airliners on smaller'aircraft F33615-77-C-3026 flying in their wake is examined, and a scheme for establishing safe Utility of w prime transform domain analysis/synthesis proce- separations between aircraft of various weight, in flight and in dures for linear, constant, single-rate sampled-data systems is approaches to landing, is proposed Means of suppressing the explored Basic properties of the w prime domain are reviewed and development of trailing vortices by modifying their structure are compared with corresponding z-, w-, and s-domam properties The discussed V P main contribution of the paper is recognition that sampling and data-hold operations are modeled exactly in the w prime domain, A78-47173 H Progress in propeller aerodynamics (Wspolczes- regardless of the sampling rate employed, and that the w prime ny rozwoj aerodynamiki smigla) Z Brodzki Technika Lotnicza i variable is analogous to the s variable in the sense that all familiar Astronautyczna, vol 33, July 1978, p 25-29 11 refs In Polish frequency domain design concepts, procedures, and interpretations The paper is a review of the results of present studies concerning can be carried over directly Moreover, the imaginary part of w prime the thrust characteristics and aerodynamics of turbofans, ducted approximates angular frequency for absolute values less than Pi/2T, propellers, proprotors, and propfans (the latter operating in a which further facilitates interpretation Two example applications cross-wind) The structure of vortices trailing off propeller blades of illustrate the procedure and make dear (by means of transfer various design is analyzed Particular attention is given to the functions and Bode plots) the nonminimum phase effects of characteristics of an eight-blade propfan with sword shaped blades sampling and data-hold operations and of sampling rate It is The underestimation of the actual thrust of these advanced propeller demonstrated that acceptable closed-loop performance can be designs is noted, and corrections to classical theory, based on the achieved at sampling rates that are an order of magnitude less than consideration of such factors as the Conolis force, the complex those employed when an emulation design approach is used structure of the trailing vortex, the scale factor, etc is discussed (Author) VP 507 A78-47175

A78-47175 # Operation of oil seales of aircraft piston Specific range comparisons are then presented for a mission of 500 engines under conditions of cavitation I (Praca olejowych uszczel- nautical miles along with a range factor analysis for missions of the nien silnikow pierscieniowych lotniczych w warunkach kawitacji I) same distance B J M Ostapkowicz (Instytut Techniczny Wojsk Lotniczych, Warsaw, Poland) Technika Lotn/cza i Astronautyczna, vol 33, July 1978, p A78-47346 # Flutter suppressor for transonic flight (Sup- 33-35 In Polish presseur de flottement en transsomque) R Destuynder (ONERA, Division de Recherche, Chatillon sous Bagneux, Hauts de-Seme, A78-47242 * An acoustic range for the measurement of the France) La Recherche Aerospatiale, May June 1978, p 117-123 In noise signature of aircraft during flyby operations D A Hilton and French H R Henderson (NASA, Langley Research Center, Hampton, Va ) A dynamically similar model of the half-wing of a modern Noise Control Engineering, vol 10, May-June 1978, P 120-128 6 aircraft was equipped with weighted external tank in order to obtain refs flutter at transonic velocity Flutter control is achieved by a classical The remotely operated multiple array acoustic range aileron that produces a reduction in frequency of the lowest flutter (ROMAAR), which has been developed to give direct measurement mode through the effect of 'negative stiffness' Significant gam in the and display of aircraft noise in several measurement units during critical dynamic pressure and Mach number have been achieved takeoff, landing, and flyby operations, is described The ROMAAR, Different values of the feedback phase were employed in order to which provides information on the ground noise signature of aircraft, determine the stability range as a function of feedback phase P T H represents a unique combination of state-of the-art digital and analog noise-recording methods, computer-controlled digital communication methods, radar tracking facilities, quick-look weather (profile) A78-47347 * Linearized theory of plane, unsteady, super- capabilities, and sophisticated data handling routines and facilities sonic flow through a cascade - Subsonic part of the leading edge The ROMAAR, which is operated by NASA, allows direct data (Theorie lineansee de I'ecoulement plan supersomque instationnaire feedback to the NASA Aircraft Noise Prediction Office As many as a travers une grille - Lieu des bords d'attaque subsomque) P Salaun 38 simultaneous noise measurements can be made for each aircraft (ONERA, Chatillon-sous-Bagneux, Hauts de-Seme, France) La overflight M L Recherche Aerospatiale, May-June 1978, p 125-132 11 refs In French Perturbation pressures are computed by a linearized theory from A78-47266 # The promise of tilt rotor T H Thomason (Bell Helicopter Textron, Fort Worth, Tex ) Aircraft Engineering, the starting point of an integral equation in which the unknown function is the pressure difference between two sides of a reference vol 50, July 1978, P 11-13 blade and the right-hand side is a known function of the motion The After a brief description of the principles of tilt rotor aircraft, integral equation is obtained from the boundary condition for the the paper emphasizes its prospective applications Such applications reference blade by setting up a pressure doublet distribution on the as pomt-to-pomt executive transportation, off-shore exploration, and blades Approximations made in a three-dimensional calculation are short haul commercial air transportation are briefly discussed tested by this theory for the case of two-dimensional flow P T H Consideration is given to the noise-pollution and safety aspects of tilt rotor as well as to its principles of flight and historical development A78-47348 # Calculation of exchange coefficients for high- The question of when tilt rotor will become available is discussed temperature turbine blades (Calcul des coefficients d'echange sur les BJ aubes de turbines a haute temperature) P Michard and D Dutoya A78-47267 ff Large electroformed nickel moulds for aircraft (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seme, France) La parts P Spiro Aircraft Engineering, vol 50, July 1978, p 14-16 Recherche Aerospatiale, May-June 1978, p 133-137 6 refs In After a brief discussion of traditional tooling, the paper French considers the use of electroformed nickel molds for glass-fiber- The paper gives the results of a finite element calculation of the remforced-plastic aircraft components (e g, radomes) Attention is velocity and temperature profiles, momentum thickness, wall fluxes, given to the electroformmg process, the maximum size of the mold, and the exchange coefficient from the equations of mass, momentum the formation of masters, and the formation of molds Several and energy conservation in parabolic form for high-temperature photographs of the nickel molds are presented B J turbulent flow past a turbine blade The exchange coefficient calculated is defined as the wall flux divided by the difference A78-47268 # COMED - The cockpit display of the future E between the adiabatic wall temperature and the wall temperature W Hare (Ferranti, Ltd, Inertial Systems Dept, Edinburgh, Scot- Experimental results for a distributor blade were compared with land) Aircraft Engineering, vol 50, July 1978, p 17-19 calculations, and the agreement is satisfactory P T H COMED (Combined Map and Electronic Display) is suitable for displaying both phototopographical and electronically generated A78-47349 # Flight application of optical fiber transmission graphical information, either separately or together A moving map on a Falcon 10 aircraft (Utilisation en vol d'une transmission par indicating the aircraft's present position can be shown on COMED fibre optique a bord d'un Falcon 10) J Taillet (ONERA, Chatillon- with superimposed waypomts, command tracks, and any other data - sous-Bagneux, Hauts-de-Seme, France) and J Reibaud (Avions either graphical or alphanumeric - that may be relevant Battle Marcel-Dassault-Breguet Aviation, Vaucresson, Hauts de-Seme, intelligence could also be displayed electronically by superimposing France) La Recherche Aerospatiale, May-June 1978, p 139-141 In on the COMED projected map such details as enemy SAM sites, French defended areas, etc The paper gives a detailed description of A device for measuring the current from a potential discharger COMED and presents a close-up photograph of the COMED uses optical fiber for digital transmission The operation of the device prototype as well as a picture of the COMED optical arrangement mounted on an aircraft has been tested in flight The first tests show BJ that the signal-to-noise ratio is greatly improved over that of the conventional transmission system P T H A78-47269 # Let's put fuel efficiency into perspective J P Dow (Grumman American Aviation Corp , Savannah, Ga ) Aircraft A78-47402 ft Solution of an adjoint problem of steady-state Engineering, vol 50, July 1978, p 24 27 heat transfer associated with the cooling of gas-turbine blades, by The paper discusses several measures of fuel efficiency and means of a quasi-analog/digital system (Resheme sopriazhennoi examines the advantages of each as it applies to business aircraft The zadachi statsionarnogo teploobmena primenitel'no k oklazhdaemym measures of efficiency discussed are passenger miles, fuel consump- lopatkam gazovykh turbin s pomoshch'iu kompleksa - kvaziana- tion per mile or specific range, range factor (a measure of design logovaia AVM-ETsVM) A V Temmkov, V I Igonm, and lu S efficiency), and specific fuel consumption la measure of engine Vytchikov In Simulation of nonstationary processes efficiency) Figures are presented illustrating changes of specific fuel Kiev, Institut Matematiki AN USSR, 1977, p 22-27 6 consumption for four different conditions of net thrust definition refs In Russian

508 A78 47490

A78-47404 § Application of electrical analogy to the sub- available, weight, cost, knowledge of material behavior, and the stantiation and comparison of some analytical methods of deter- mechanical properties Attention is given to the evaluation of new mining temperature fields in gas-turbine blades (Pnmenenie elektri- materials, questions of material characterization, the design of cheskogo modelirovaniia dha obosnovanua i sravneniia s nekotorymi components which are subjected to high stresses, an assessment of analiticheskimi metodami opredelenna teplovykh polei v lopatkakh the disk, objectives and implementation of quality control, and the gazovykh turbin). V I Igonin, A V Temnikov, and V M conduction of tests to verify that design requirements have been met Khorol'skn In Simulation of nonstationary processes Forgmgs are chosen where the property and quality levels and 47401 21 59) Kiev, Institut Matematiki AN USSR, 1977, p 71-76 5 consistency are the controlling factors in the use G R refs In Russian

A78-47407 # Probabilistic model of an instrument landing A78-47453 Design philosophy for airframes I L G system (Veroiatnostnaia model' mstrumental'noi posadki samoletov) Baillie and W P C Soper (British Aircraft Corp Ltd , Commercial L la ll'nitskii, A G Revuk and M I Fuzik In Simulation of Aircraft Div , Filton, Bristol, England) In Forging and properties of nonstationary processes (' Kiev, Institut Mate- aerospace materials. Proceedings of the International Conference, matiki AN USSR, 1977, p 124-127 In Russian Leeds, England, January 5-7, 1977 London, In the present paper, the model of an instrument landing system Metals Society, 1978, p 8-23 is treated as the guidance process involved in a rendezvous maneuver, The technical requirements for modern civil and military aircraft complicated by a variable electromagnetic environment In this entail a continual improvement in materials and their application approach, there arises the problem of determining the probability The structural loading and airworthiness requirements background is that at a certain moment of time the aircraft will be situated either in explained in terms of aerodynamic loads and aircraft use with special a region corresponding to the zero-reading of the onboard indicator, reference to modern 'fail safe' airframe design concepts, leading to a or in a radio range of plus or minus 10 degrees (or between 10 and defined range of properties which must be checked to be acceptable 35 degrees) from the specified track The problem is solved by using Suitable applications for forgings are detailed for the range of a model in the form of a sequence of random events characterized by aluminum, titanium, steel and nickel alloy systems of interest, and five possible states V P the need for application of new techniques explored for airframe exploitation Emphasis is also placed on batch quality control aspects via national UK specifications (Author) A78-47423 The second generation of high-bypass turbofans-A market clouded by uncertainly J F Bnndley Interavia, vol 33, Aug 1978, p 711 714 Second generation high bypass turbofan concepts for commer- A78-47481 Advances in mertial navigation P R Foggie cial aviation are reviewed in terms of performance and fuel economy (RAF, London, England) Electronics and Power, vol 24, Aug 1978, The General Electric/SNECMA CFM56 is considered the most p 582-584 advanced, offering fuel savings on the order of 30% per passenger Inertial navigation systems in use and under development are over older engines The CFM56 will be rated at 10,885 kp and could discussed Navattack systems used in modern military aircraft rely on enter service by 1981 Other engines are also reviewed, including the stabilized platform systems which are costly and, as a result of their RB 211 535, the JT10D, rated at 14,515 kp, to be used in a new complexity, not totally reliable The performance capabilities of Boeing trijet, and the CF6-32, which maintains the core of the Navattack systems, which are examples of integrated systems, are Dash-6D2 while incorporating a new LP turbine and turbine indicated Strap-down mertial systems, still in the developmental mid-frame D M W stage, are described, in these systems, both gyros and accelerometers are mounted rigidly on the aircraft structure One approach involves the electrostatic suspended gyro which has a ball spun within a A78-47424 RNAV Corporate operators set the pace E closely surrognding spherical case without there being any mechani- Wooten Interavia, vol 33, Aug 1978, p 722727 cal connection between ball and case The laser gyro represents Area navigation (RNAV) systems are discussed in terms of their another approach, this gyro, which has no moving parts, is cheap, but suitability for the commercial aircraft market, and with attention to its use is complicated by basic sources of errors, including frequency their capabilities in the vertical dimension Four RNAV categories synchronization (lockin) M L are outlined course line, whereby a number of way-points (determined in advance) are entered into a computer, and steering and other guidance parameters are calculated to provide navigation from way-point to way-point, great circle, which provides point to-pomt navigation along great circle routes, inertia!, using updated but A78-47490 * Ride quality evaluation IV-Models of subjec- self-contained mertial guidance, and VLF/Omega systems, which tive reaction to aircraft motion I D Jacobson and L G Richards permit manual or automatic updating of Omega signals to an (Virginia. University, Charlottesville, Va ) Ergonomics, vol 21, July accuracy of 2 8 km along track D M W 1978, p 521-529 Grant No NCR 47-005-181 The paper examines models of human reaction to the motions typically experienced on short-haul aircraft flights Data are taken on the regularly scheduled flights of four commercial airlines three airplanes and one helicopter The data base consists of (1) a series of A78-47452 Design philosophy for engine forgings J D motion recordings distributed over each flight, each including all six Alexander (Rolls-Royce, Ltd , London, England) In Forging and degrees of freedom of motion, temperature, pressure, and noise are properties of aerospace materials. Proceedings of the International also recorded, (2) ratings of perceived comfort and satisfaction from Conference, Leeds, England, January 5-7, 1977 the passengers on each flight, (3) moment-by-moment comfort London, Metals Society. 1978, p 1-7 ratings from a test subject assigned tp each airplane, and (4) overall Design and control considerations in connection with the comfort ratings for each flight from the test subjects Regression manufacture of engine components for jet engines are discussed It is models are obtained for prediction of rated comfort from rms values pointed out that the design and control of these parts requires a for six degrees of freedom of motion It is shown that the model C = detailed understanding of both the use and the material behavior of 21 + 171 T+ 172V (T = transverse acceleration, V = vertical the involved component The design of a component is based on the acceleration) gives a good fit to the airplane data but is less required performance, the guaranteed life required, the space acceptable for the helicopter data S D

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A78-47570 From Challenger to winner Air International, Recent developments in air-to-air combat simulation are review- vol 15, Sept 1978, p 111-116,129,130 ed, and particular emphasis is placed on the Maneuver and Attack The development and characteristics of the Canadair Challenger Simulator and the BACTAC model The design of a single dome business jet are described, with the aircraft utilizing a modification of combat configuration with a human pilot versus a computer the LearStar 600 The aircraft will provide a range of 4,450 naut mis opponent is described The uses of BACTAC for aircraft develop- with a tolerance of 450 naut mis, a maximum speed of 505 kt with a ment and pilot training are considered B J 20-kt tolerance, and a cruising speed of Mach 086 (490 kt/hr) The fuselage diameter is 106 in, the wing area is 420 sq ft, and the gross weight is 32,500 Ib The engines, (modified ALF 502), give 7500 Ib A78-47869 On the linear superposition of aerodynamic st for take-off and a thrust-to-weight ratio of 0 46 1 The wing is a forces on wings in periodic gusts M H Patel (University College, highly complex design with a deeply scalloped undersurface, a London, England) Aeronautical Journal, vol 82, June 1978, p built-in twist from root to tip, and changes of aerofoil along the 267 272 Research supported by the Ministry of Defence (Procure- wing The first Challenger was completed in May 1978 Sales ment Executive) prospects and negotiations between Lear and Canadair are discussed An experimental study has been made in a low speed gust tunnel M L of the lift forces and pitching moments on two wings immersed in periodic vertical gusts which consist of two frequency components A78-47599 ft The influence of high twist on the dynamics of Systematic variations of the frequency pairs making up the incident rotating blades W F White, Jr (US Army, Structures Laboratory, gust, the 'phase' difference between the two components, and the Hampton, Va ) Associations Italiana di Aeronautica ed Astronautics amplitude components of each frequency for both wings at two test and Associazione Industrie Aerospaziah, European Rotorcraft and incidences show that the ability to build up aerodynamic load by Powered Lift Aircraft Forum, 4th, Stresa, Italy, Sept 13-15, 1978, superposition applies generally for any gust composed of the sum of Paper 14 p 6 refs two frequency components This demonstration of the validity of A method is presented for determining the free vibration superposition depends on the exclusion of any major changes in the characteristics of a rotating blade having high twist and nonuniform state of the wing boundary layers during a cycle of the imposed spanwise properties The equations which govern the bending and oscillatory flow B J torsional motion of such a blade are solved using a generalized integration matrix as the basis of the method of solution By using A78-47887 On the theory of drag calculation and profile this matrix as an operator on the equations expressed in matrix optimization in shockless near free molecular flow R Monaco notation, the differential equations are numerically integrated to (Torino, Politecnico, Turin, Italy) Acta Mechanics, vol 29, no 1-4, eliminate the spatial dependence and reduced to familiar matrix 1978, p 275-282 13 refs eigenvalue form from which the dynamics of the blade are A mathematical model is developed for the calculation of drag determined using standard eigenvalue extraction techniques The of axisymmetric bodies in quasi-free-molecular flow In particular, application of this technique to problems of this type offers several the model is used to evaluate the ratio of the drag coefficient in computational advantages over other methods of solution Numerical quasi-free-molecular flow to that in free molecular flow for convex results using the present method of solution are in good agreement bodies Numerical results agree well with experimental results for with experimental results (Author) sharp as well as blunt bodies The proposed model is improved over other models in that it takes correct account of gas-solid interface conditions and the effects of 'first and second collisions' between A78-47865 AIDS in engine management programmes A impinging and reemitted molecules The model is very promising for E Davies (Rolls-Royce, Ltd , Derby, England) Aeronautical Journal, axisymmetric profile optimization B J vol 82, June 1978, p 235-242 5 refs The paper examines the role of AIDS (airborne integrated data systems) in the total management program of an aircraft propulsion A78-47899 # Flight deck display trends W R Denton system As a particular example, attention is given to the application Aviation Review, June 1978, p 5-8 of AIDS to the control system monitoring and low cycle fatigue Potential innovations in flight deck display equipment, which monitoring of the Concorde engine The applications of AIDS to range from cathode ray tube and other forms of solid-state display to helicopter engines and military aircraft engines are also discussed new state-of-the-art electromechanical and purely mechanical in- along with the future development of AIDS B J struments, are discussed with attention to attitude director and horizontal situation display, air data displays, and engine management displays It is concluded that, while advanced display technology is available, improvements in current display equipment will A78-47866 AIDS in military aircraft E Daley and A prolong the life expectancy of many of the instruments in service at Delahunty (British Aerospace, Aircraft Group, Preston, Lanes, present The comparative advantages of modification and totally new England) Aeronautical Journal, vo\ 82, June 1978, p 243-246 design are considered, and the requirements of corporate aviation The paper reviews the development of AIDS (airborne integrat- and feeder line aircraft are examined M L ed data systems) in the past 10 12 years with reference to military aircraft Consideration is given to the operational requirements of A78-47900 # Solid-state displays for fuel management sys- AIDS, and to the use of AIDS, particularly BITE (built in test tems J W Aspmall Aviation Review, June 1978, p 11, 12 equipment) in three generations of aircraft the in-service generation, The design of several fuel management displays for aircraft is aircraft presently under development, and the next generation For described Examples discussed include a combined aircraft weight- aircraft now under development, emphasis is placed on continuous total fuel indicator, a solid-state combined amplifier-indicator, a monitoring, interruptive testing, and test software, for the next fuel-management display using fiber optics, and a LED fuel man- generation, emphasis is placed on the computing system, display agement display selector Components, requirements, and future systems, and sensors B J technology are considered M L

A78-47901 ft Gates Learjet Model 28/29, the first 'Long- horn' Learjet P T Reynolds, W M Gertsen, and C G Voorhees A78-47868 Air-to-air combat simulation A G Barnes and (Gates Learjet Corp , Wichita, Kan ) American Institute of Aeronau- D E A Houghton (British Aerospace, Warton Div , Preston, Lanes, tics and Astronautics, Aircraft Systems and Technology Conference, England) Aeronautical Journal, vol 82, June 1978, p 255-260 Los Angeles, Calif ,Aug 21-23, 1978, Paper 78-1445 6p

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In August 1977 the Gates Learget Model 28 prototype became other kind in a chronological chain The need to include design the first jet to fly with winglets The paper discusses the theory and courses at the baccalaureate level is emphasized V P history of winglets and considers performance improvements, and stability and control characteristics of the wmglet configuration It is noted that the Model 28/29 test program is progressing rapidly and A78-47907 * ft Some observations on the mechanism of air- FAA certification is expected in late 1978 The winglets have craft wing rock C Hwang and W S Pi (Northrop Corp , Aircraft contributed a great deal of drag reduction and have presented no Div , Hawthorne, Calif) American Institute of Aeronautics and significant problems BJ Astronautics, Aircraft Systems and Technology Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1456 11 p 6 refs A78-47903 # B-1 flight test progress report R N Contract No NAS2-8734 Broughton (Rockwell International Corp, Los Angeles, Calif) A pressure scale model of Northrop F-5A was tested in NASA American Institute of Aeronautics and Astronautics, Aircraft Sys- Ames Research Center Eleven-Foot Transonic Tunnel to simulate the tems and Technology Conference, Los Angeles, Calif, Aug 21-23, wing rock oscillations in a transonic maneuver For this purpose, a 1978, Paper 78 1448 6 p flexible model support device was designed and fabricated which The B 1 flight test program, since first flight in December 1974, allowed the model to oscillate in roll at the scaled wing rock has been carefully organized to supply engineering development frequency Two tunnel entries were performed to acquire the information and provide for an evaluation of the weapon systems pressure (steady state and fluctuating) and response data when the operational capability This paper provides a resume of B-1 flight test activities over the past three and one-half years It is intended to model was held fixed and when it was excited by flow to oscillate in roll Based on these data, a limit cycle mechanism was identified highlight some innovative approaches to technical and managerial applications that have produced a highly successful large-aircraft test which supplied energy to the aircraft model and caused the Dutch program, and to show that the data generated to date are conclusive roll type oscillations, commonly called wing rock The major origin evidence that the aircraft can perform its design mission (Author) of the fluctuating pressures which contributed to the limit cycle was traced to the wing surface leading edge stall and the subsequent lift A78-47904 * ff Canard configured aircraft with 2-D nozzle R recovery For typical wing rock oscillations, the energy balance D Child (Rockwell International Corp, Los Angeles, Calif) and W between the pressure work input and the energy consumed by the P Henderson (NASA, Langley Research Center, Propulsion Aero model aerodynamic and mechanical damping was formulated and dynamics Branch, Hampton, Va ) American Institute of Aeronautics numerical data presented (Author) and Astronautics, Aircraft Systems and Technology Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78 1450 12 p 10refs A closely-coupled canard fighter with vectorable two A78-47908 ff The HiMAT RPRV system L E Brown, Jr, dimensional nozzle was designed for enhanced transonic maneu M H Roe, and C D Wiler (Rockwell International Corp, Los vermg The HiMAT maneuver goal of a sustained 8g turn at a Angeles, Calif ) American Institute of Aeronautics and Astronautics, free-stream Mach number of 0 9 and 30,000 feet was the primary Aircraft Systems and Technology Conference, Los Angeles, Calif, design consideration The aerodynamic design process was initiated Aug 21-23, 1978, Paper 78-1457 13 p 8 refs with a linear theory optimization minimizing the zero percent Two remotely piloted research vehicles (RPRVs) which are 44% suction drag including jet effects and refined with three-dimensional scale versions of an advanced highly maneuverable fighter design have nonlinear potential flow techniques Allowances were made for been delivered to NASA for flight testing These research airplanes mutual interference and viscous effects The design process to arrive will demonstrate the contribution to the future air-to air fighter of at the resultant configuration is described, and the design of a several advanced technologies, including aeroelastic tailoring, super- powered 2D nozzle model to be tested in the LRC 16-foot critical airfoils, close-coupled canard, variable camber, and advanced Propulsion Wind Tunnel is shown (Author) composite materials Digital fly-by-wire control technology is employed with the control laws being implemented in a ground based A78-47905 ff The effect on block fuel consumption of a computer The HiMAT is designed with a 12-g limit load factor and strutted versus cantilever wing for a short-haul transport including can perform sustained maneuvering at 8 g at 0 9 M at 25,000-foot strut aeroelastic considerations P H Park (Boeing Aerospace Co , altitude The HiMAT has been designed and fabricated with a Seattle, Wash ) American Institute of Aeronautics and Astronautics, modular approach which facilitates modification for testing of other Aircraft Systems and Technology Conference, Los Angeles, Calif, structural, aerodynamic, propulsion, or flight-control concepts The Aug 21-23, 1978, Paper 78-1454 7p 11 refs HiMAT RPRVs will be launched from a B 52 and flown through A preliminary design of a short-haul aircraft using a strut-braced their test flight mission by a ground based pilot Landings will be wing was made to study the possibility of block fuel savings due to made on a dry lake bed, utilizing skids rather than wheels on the the decrease in wing weight allowed by the use of a strut A landing gear (Author) computer-aided wing loads and stress analysis was performed to determine the wing weight savings It was found that the wing weight savings are not large in this aircraft and the induced drag decrease is offset by the strut parasite drag The final cantilever and strutted configurations have essentially equal block fuel consumptions A A78-47909 tf Wing/store active flutter suppression - Correla- calculated strut flutter velocity was close enough to the flight tion of analyses and wind tunnel data T E Noll and L J Huttsell envelope to warrant design consideration (Author) (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio) American Institute of Aeronautics and Astronautics, Aircraft Sys- tems and Technology Conference, Los Angeles, Calif, Aug 21 23, A78-47906 ff Teaching design at all levels H W Smith 1978, Paper 78-1459 10 p 8 refs (Kansas, University, Lawrence, Kan ) American Institute of Aero- Through analyses and recent wind tunnel tests, active flutter nautics and Astronautics, Aircraft Systems and Technology Confer- suppression has been shown to be a promising technique for ence, Los Angeles, Calif, Aug 21-23, 1978. Paper 78-1455 9 p 50 preventing wing/external store flutter restrictions Data measured in refs the wind tunnel have been used to evaluate the validity of a method Some important job functions of designers in industry and employed for the design and analysis of active feedback control government are described in an attempt to put the central role of systems The results of an analytical effort to study the behavior of design courses in the engineering curriculum in proper perspective It an active flutter suppression wind tunnel model will be presented and is shown that all designs, regardless of their type and nature, bear the compared with available test data For this application, the model common hallmark of 'inventiveness', or the creation of something was aerodynamically represented by subsonic doublet lattice theory starting with nothing, and that each type of design is related to each and stability was evaluated using modified Nyquist criteria (Author)

511 A78-47910

A78-47910 ff Evolution of a cost-effective, task-oriented, and to a tendency to underestimate problem complexity when lateral-directional SAS for the A-10 aircraft. G Brandeau (Fairchild dealing with software systems These development problems are, Republic Co , Farmmgdale, N Y ) American Institute of Aeronautics however, being overcome as a result of new approaches One and Astronautics, Aircraft Systems and Technology Conference, Los approach considered involves basically the application of a disciplin- Angeles, Calif, Aug 21-23, 1978, Paper 78-1460 10 p ed software management plan in which each development software The reported investigation is concerned with the development of life cycle phase culminates in the production of one or more a task-oriented stability orientation system (SAS) having the most documents or configuration items A phase is not considered to be important functional requirements, together with cost-effectiveness complete unless the appropriate documents/items are available as a basis Attention is given to a kinematic analysis, a simplified Attention is given to the requirements definition phase, the design scenario system synthesis, preliminary simulator studies, system phase, the implementation and static test phase, the dynamic test definition and parameter selection, manned simulator studies, run phase, the software/hardware integration phase, the flight test phase, data and pilot evaluations, and the results of a manned simulator the maintenance phase, the development support library, and aspects performance evaluation A flight test performance evaluation is also of configuration control. G R discussed, taking into account abrupt heading change data, curvilinear strafe data, and a gun camera film analysis of curvilinear strafes G R A78-47914 # The role of the computer in the flight testing of general aviation aircraft P Leckman (Rockwell International Corp, General Aviation Div, Bethany, Okla ) and G Bennett A78-47911 ff Integrated test mission control - Present and (Mississippi State University, Mississippi State, Miss ) American future at the Air Force Flight Test Center C E Adolph (USAF, Institute of Aeronautics and Astronautics, Aircraft Systems and Flight Test Center, Edwards AFB, Calif ) American Institute of Technology Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper Aeronautics and Astronautics, Aircraft Systems and Technology 78-1465 9p 10 refs Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1461 6 A description is presented of the use of a minicomputer in flight p 6 refs test programs conducted by an American aerospace company In one The flight test and evaluation programs conducted on USAF program the computer was used during 235 flights and 400 flight aircraft have gravitated over the past two decades from what were hours Types of flight tests for which the computer was utilized in largely independent, sequential test programs by the contractor, Air recording data included primarily engine development tests and Force development, and operational test agencies to programs aerodynamic drag evaluations Approximately 70 parameters were conducted on a concurrent basis from a single test location measured at a maximum possible scan rate of 35 times per second Integrated mission control elements are examined, taking into Attention is given to a system description, the operating procedures, account aspects of test activity consolidation, test range integration, the performed functions, the utilization rate, the realized advantages, test planning factors, and real-time mission control Integrated implementation problems, and application similarities to a manage- systems testing is considered along with flutter tests, questions of ment information system within companies It is pointed out that aircraft performance, propulsion stability and control, flight enve- the computer has made possible flight experiments of constantly lope expansion/multiple discipline testing, data processing, and a increasing complexity with a modest expenditure of funds Current uniform flight test analysis system Attention is given to plans for developments in microprocessor systems promise to further expand improving the test capability G R the research possibilities at a reduced cost G R

A78-47912 ff Use of onboard computerized flight test analysis systems E L Wallace (Boeing Commercial Airplane Co , Seattle, A78-47915 ;/ Conceptual design study of power augmented Wash) American Institute of Aeronautics and Astronautics, Aircraft ram wing in ground effect aircraft J W Moore (Lockheed-Georgia Systems and Technology Conference, Los Angeles, Calif, Aug Co , Marietta, Ga ) American Institute of Aeronautics and Astro- 21-23, 1978, Paper 78-1462 8 p nautics, Aircraft Systems and Technology Conference, Los Angeles, In response to the challenge for increased efficiency, productiv- Calif, Aug 21-23, 1978, Paper 78-1466 14 p 15 refs ity, and cost effectiveness in the conduction of flight tests, new Conceptual design study results of a power augmented ram wing approaches involving a use of real time onboard analysis and in ground effect (PAR-WIG) logistics transport aircraft are presented monitoring of test data have been developed In 1974 the Airborne The PAR-WIG aircraft examined incorporates four unique character- Data Analysis and Monitor System (ADAMS) was implemented for istics First, power augmented ram lift is provided during all takeoff an employment in conjunction with a high speed serial PCM data and landing maneuvers, second, cruise flight occurs only in ground acquisition system The ADAMS proved to be an extremely useful effect, third, all operations are accomplished on or above the ocean tool for the flight test engineer The heart of ADAMS is a surface, and, fourth, payload containment is provided within the minicomputer It is a 16 bit machine that internally processes 32 bit wing contour and is distributed across the wing span (Author) microinstructions at a 5 MHz rate The computer is equipped with 32k of core memory and a floating point processor option Analysis programs which have been developed for ADAMS provide information regarding basic aircraft parameters, cruise performance, stall and minimum speed performance, loads performance, takeoff performance, and power plant parameters G R A78-47916 * # Quiet, Short-Haul Research Aircraft • Current status and future plans J A Cochrane and A G Boissevam (NASA, Ames Research Center, Moffett Field, Calif ) American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology A78-47913 // Software engineering a must for success in Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1468 computerized flight test J P Mayfield and R E Smith (Teledyne 11p Ryan Aeronautical, San Diego, Calif ) American Institute of The Quiet Short-Haul Research Aircraft (QSRA) is a new Aeronautics and Astronautics, Aircraft Systems and Technology research aircraft which NASA will use as a flight-test facility for Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1463 7 advanced flight experiments in terminal area operations The data p 15 refs resulting from the QSRA flight research program will be used by the Software development problems in connection with the utiliza- U S aircraft industry to establish design criteria and by regulatory tion of software systems in flight test applications are fojnd to be agencies to establish certification criteria for advanced STOL aircraft related partly to the low level of maturity of the entire digital world The total funding for the QSRA was established at $29 million in

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January 1974 Attention is given to an aircraft description, wind- A78-47920 # Sensor technology for turbine engine moni- tunnel results, simulation, predicted aircraft performance, initial toring systems J A Davis (Ohio State University, Columbus, Ohio) airworthiness flight tests, design configuration studies, and training American Institute of Aeronautics and Astronautics, Aircraft Sys- studies G R tems and Technology Conference, Los Angeles, Calif, Aug 21-23, 1978. Paper 78-1474 13 p 32 refs The Turbine Engine Monitoring System (TEMS) is proposed as a A78-47917 jj L 1011 flight data recording systems - Back- system to continuously monitor turbine engines in the USAF ground, features, implications and benefits W R Beckman operational environment Attention is given to instrumentation (Lockheed-California Co, Burbank, Calif) American Institute of requirements, transducer designs, accelerometers, position indicators, Aeronautics and Astronautics, Aircraft Systems and Technology flow meters, rotary speed transducers, function switches, pressure Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1471 9 transducers, temperature sensors, an uncertainty calculation and P error source discussion, aspects of sensor failures and detection, In connection with the introduction of the large wide-body questions of sensor reliability, and advanced sensor techniques It is transports, it was recognized by FAA and the airline industry that found that present state-of-the-art sensors are acceptable for the the complexity and high cost of these new aircraft dictated the need envisioned TEMS applications from both accuracy and reliability for recording additional flight data parameters for accident-incident standards The instrumentation systems proposed are adequate from investigations With reliable digital recording systems available, these the sensor accuracy standpoint, and software corrections to mea- additional requirements were enacted into the Federal Aviation sured data, using cross-parameter correction schemes and detailed Regulations of the US and into the Air Navigation Orders of the calibration data, can improve the accuracy G R UK Parameters to be recorded on the expanded flight data recorders are related to time, altitude, airspeed, vertical acceleration, heading, pitch attitude, roll attitude, lateral acceleration or sideslip angle, control column or pitch control surface position, control wheel or A78-47921 # Engine vibration in flight H J Rubel, K I lateral control surface position, rudder pedal or yaw control surface Peck, and J A Mclnturff (Lockheed-Georgia Co, Marietta, Ga ) position, thrust of each engine, position of each thrust reverser, angle American Institute of Aeronautics and Astronautics, A '•craft Sys- of attack, and pitch trim position The flight data systems developed tems and Technology Conference, Los Angeles, Calif, Aug 21-23, to record the parameters are discussed G R 1978, Paper 78-1475 6p The system described differentiates between true rotor unbal ance and system malfunctions The flight crew can react appropriate ly to the indicated malfunction to minimize in-flight shutdowns A78-47918 # TF41-A-2/A7E inflight engine condition moni- Typical data are presented as well as two cases of large unbalance, toring system /IECMS/ L R DeMott (General Motors Corp , Detroit one as a result of a bird strike and the other due to the loss of a Diesel Allison Div, Indianapolis, Ind ) American Institute of turbine blade This monitoring system is designed to detect and Aeronautics and Astronautics, Aircraft Systems and Technology record vibration frequencies in the range of the rotors, i e , fan and Conference, Los Angelas, Calif, Aug 21-23, 1978, Paper 78-1472 core Harmonics, noise and other vibrations within the bandpass of 10p the filter will also be detected The processor, utilizing a modified An engine condition monitoring system for the TF41-A-2 engine Fourier routine, determines amplitude and outputs appropriate installed in the A7E aircraft has been developed by Detroit Diesel messages (Author) Allison under Navy contract The system, designated as Inflight Engine Condition Monitoring System (IECMS), is designed to continuously monitor engine health, record pertinent information and provide diagnostic information to operating personnel The A78-47922 * ff Correlation of model and airplane spin charac- system has been developed in several phases from prototype to the teristics for a low-wing genera! aviation research airplane J S present production configuration now installed in 24 aircraft Bowman, Jr, H P Stough, S M Burk, Jr, and J M Patton, Jr assigned to Navy Attack Squadrons VA-46 and VA-72 Over 15,000 (NASA, Langley Research Center, Hampton, Va ) American Insti- total flight hours have been accumulated to date and the system has tute of Aeronautics and Astronautics, Aircraft Systems and Technol- met all operational requirements Future additional retrofits to the ogy Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper A7E are contingent on availability of funding Advances in state-of- 78-1477 13 p the-art computer and sensor technology can result in a vast improvement in system cost versus effectiveness in the future (Author) A78-47923 //' Whitcomb wmglet applications to general aviation aircraft J F Marchman, III, D Manor (Virginia Polytechnic Institute and State University, Blacksburg, Va ), and H F Faery, Jr A78-47919 # Detecting abnormal turbine engine deteriora- (Virginia Polytechnic Institute and State University, Blacksburg, Va , tion using electrostatic methods R P Couch (USAF, Aeronautical US Military Academy, West Point, NY) American Institute of Systems Div , Wright-Patterson AFB, Ohio) American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Aeronautics and Astronautics, Aircraft Systems and Technology Conference, Los Angeles, Calif. Aug 21-23, 1978, Paper 78-1478 7 Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1473 p 5 refs 18 p 8 refs A study was conducted to examine several of the aspects of A methd of detecting abnormal turbine engine deterioration has Whitcomb wmglet applications to low speed, general aviation been developed and tested The method observes pulse electrostatic aircraft Both supercritical and laminar flow airfoil section winglets signals in the exhaust which have been determined to originate from were tested on straight and tapered symmetrical wings Aerodynamic component rubbing, chaffing, erosion and burning de, various parameters were measured for a wide range of wing angles of attack forms of deterioration) The normal (healthy engine) deterioration and for several wmglet angles Tests were run to determine the low rate is first studied as a function of engine cycling and power This speed effect of the wing on the wmglet and of the winglets on the deterioration rate is then normalized with an engine power and an wing Towing tank and wind tunnel tests were run to examine the engine cycling parameter Tenfold increases in the normalized trailing vortices from the wmg-wmglets combinations The tests deterioration rate are then used as an indication of tnpendmg showed that winglets are effective at low speeds, however a tapered component failure Experience shows that about two out of three wing planform results in a reduction of the wmglet effectiveness turbine engine gas path failures can be predicted four or more hours Symmetrical winglets were shown to be effective at low speed Tests ahead of time by this method The false alarm rate is estimated to be also indicated that a proper choice of wmglet angle can reduce the about 5% (Author) strength of the wing wake turbulence (Author)

513 A78-47924

A78-47924 * # Section drag coefficients from pressure probe vehicle has been modified for use as a flight test facility The traverses of a wing wake at low speeds L C Montoya, P F Bikle, program currently includes flight experiments on two aeroelastic and R D Banner (NASA, Flight Research Center, Edwards, Calif ) research wings The primary purpose of the first flight experiment is American Institute of Aeronautics and Astronautics, Aircraft Sys- to demonstrate an active control system for flutter suppression on a tems and Technology Conference, Los Angeles, Calif, Aug 21-23, transport-type wing Design and fabrication of the wing are complete 1978, Paper 78-1479 12 p 20 ref s and after installing research instrumentation and the flutter suppression system, flight testing is expected to begin in early 1979 The experiment on the second research wing - a fuel-conservative A78-47925 * ft Some sound transmission loss characteristics transport type - is to demonstrate multiple active control systems of typical general aviation structural materials J Roskam, C van including flutter suppression, maneuver load alleviation, gust load Dam, F Grosveld (Kansas, University, Lawrence, Kan), and D alleviation, and reduce static stability Of special importance for this Durenberger (General Dynamics Corp , Fort Worth, Tex ) American second experiment is the development and validation of integrated Institute of Aeronautics and Astronautics, Aircraft Systems and design methods which include the benefits of active controls in the Technology Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper structural design (Author) 78-1480 10 p Grant No NsG-1301 Experimentally measured sound transmission loss characteristics A78-47930 * ff Application of advanced high speed turboprop of flat aluminum panels with and without damping and stiffness technology to future civil short-haul transport aircraft design J A treatment are presented and discussed The effect of pressunzation Conlon (U S Army, Research and Technology Laboratories, Moffett on sound transmission loss of flat aluminum panels is shown to be Field, Calif) and J V Bowles (NASA, Ames Research Center, significant (Author) Moffett Field, Calif) American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1487 13 p 8 refs With an overall goal of defining the needs and requirements for A78-47926 * # Status of aerial applications research in the short-haul transport aircraft research and development, the objective Langley Vortex Research Facility and the Langley full-scale wind of this paper is to determine the performance and noise impact of tunnel F L Jordan, Jr, H C McLemore (NASA, Langley Research short-haul transport aircraft designed with an advanced turboprop Center, Dynamics Stability Branch, Hampton, Va ), and M B Bragg propulsion system This propulsion system features high-speed (Illinois, University, Urbana, III ) American Institute of Aeronautics propellers that have more blades and reduced diameters Aircraft are and Astronautics, Aircraft Systems and Technology Conference, Los designed for short and medium field lengths, mission block fuel and Angeles, Calif, Aug 21-23, 1978, Paper 78-1481 12 p 16refs direct operating costs (DOC) are used as performance measures The propeller diameter was optimized to minimize DOC Two methods A78-47927 * ;/ Integrated avionics for future general aviation are employed to estimate the weight of the acoustic treatment aircraft D G Denery, C T Jackson, Jr, G P Callas, B K needed to reduce interior noise to an acceptable level Results show Berkstresser, and G H Hardy (NASA, Ames Research Center, decreasing gross weight, block fuel, DOC, engine size, and optimum Moffett Field, Calif) American Institute of Aeronautics and propfan diameter with increasing field length The choice of acoustic Astronautics, Aircraft Systems and Technology Conference, Los treatment method has a significant effect on the aircraft design Angeles, Calif, Aug 21-23, 1978, Paper 78-1482 13 p 18 refs (Author) The program described was initiated in 1975 to provide the critical information for the design of an advanced avionics system suitable for general aviation Emphasis is on the use of data busing, A78-47931 -7 The use of the AlAA-Bendix Design Competi- distributed microsensors, shared electronic displays and pilot entry tion in aerospace design courses J F Marchman, III (Virginia devices, innovative low-cost sensors, and improved functional char Polytechnic Institute and State University, Blacksburg, Va ) and J J actenstics Design considerations include cost, reliability, maintain- Irons (American Institute of Aeronautics and Astronautics, Inc , New ability, and modularity VP York, N Y ) American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1488 8p A78-47928 ff The design process D D Meyer, G L The evolution and refinement of the AlAA-Bendix Design Anderton, H A Crowell, and J W Southall (Boeing Commercial Competition since its beginning in 1972 is examined The criteria for Airplane Co , Seattle, Wash ) American Institute of Aeronautics and selection of design competition RFP's and the standards for design Astronautics, Aircraft Systems and Technology Conference, Los proposal evaluation are discussed in detail The use of the AlAA- Angeles, Calif, Aug 21-23, 1978, Paper 78-1483 12 p 5 ref s Bendix Competition as a basis of a typical aerospace engineering The paper describes the results of an effort made to document design course is examined with a detailed look at its use in the design the design process and extract from it a set of requirements for a course in Aerospace and Ocean Engineering at Virginia Polytechnic computer system that will integrate and manage the design product Institute and State University It is concluded that the competition data, program management information and technical computation can be and has been used successfully to boost the quality of and engineering data management activities of the aerospace design aerospace engineering design education at many universities and that process Design activities were grouped chronologically and explored the competition is responsive to the desire of industry for a realistic for activity, interface, data quantity and data flow Design levels simulation of the industrial design process in undergraduate design examined included research, preliminary design, detail design, man- classes (Author) ufacturing, product verification, and product support (Author)

A78-47929 * if Drones for aerodynamic and structural testing A78-47932 ff Aeronautical procurement - The primary speci- /DAST/ - A status report H N Murrow and C V Eckstrom (NASA, fication system J L Wemgarten (USAF, Aeronautical Systems Div , Langley Research Center, Hampton, Va ) American Institute of Wright-Patterson AFB, Ohio) American Institute of Aeronautics and Aeronautics and Astronautics, Aircraft Systems and Technology Astronautics, Aircraft Systems and Technology Conference, Los Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1485 9 Angeles, Calif, Aug 21-23, 1978, Paper 78-1489 7 p 5 refs p 13 refs The various procurement techniques which have been tested by A program for providing research data on aerodynamic loads the Department of Defense have not resolved the problem of and active control systems on wings with supercritical airfoils in the procuring aeronautical equipment The present paper deals with a transonic speed range is described Analytical development, wind promising system developed to ensure that requirement statements tunnel tests, and flight tests are included A Firebee II target drone are in terms of system/equipment performance related to operational

514 A78-4794O

needs, rather than dictating specific solutions, to provide an overall Recent studies of accidents/incidents attributed to wind shears specification system that marries the current military specifications encountered during takeoff or during landing approach, have and the type of specifications defined by MIL-STD-490, and to indicated the requirement to quantify the performance loss due to provide the rationale for the requirement statements contained in vertical downdraft combined with that due to horizontal wind shear specifications/standards V P This paper discusses the development of a system to compute and display to the flight crew this loss of performance capability Data are presented from simulation, flight test and in service evaluation These are discussed in terms of performance margins and implica A78-47933 H A computerized undergraduate aircraft design tions for flight crew technique in the recovery from a severe course G T Matsuyama (U S Air Force Academy, Colorado encounter (Author) Springs, Colo) American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1492 8p 5 refs The integration of a computer program with an undergraduate A78-47937 # Effects of wind on aircraft cruise performance aircraft design course is described with emphasis on the computer F J Hale (North Carolina State University, Raleigh, N C ) and A R program known as AER0464RPV, which was written specifically for Steiger (Booz, Allen and Hamilton, Inc , Bethesda, Md ) American the course Inputs include basic vehicle geometry, aerodynamic Institute of Aeronautics and Astronautics, Aircraft Systems and coefficients, and a mission profile The program computes Technology Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper weight/fuel fractions and 'flies' the vehicle while attempting to 78-1496 7 p achieve convergence with a historical empty weight Program Analytic expressions are developed that predict the improvements in range, flight time, and fuel consumption that can be capabilities include fuel tank sizing and fuel sequencing Output includes weight, static margin, and a flight profile vs time Successful achieved by appropriate corrections to the no-wind best-range airspeed Input data required are type of power plant, no-wind implementation has been demonstrated over 3 semesters, with best range airspeed, and magnitude of the headwind or tailwmd modifications including changes to both mission profiles and engine data (Author) component Application of these expressions to a series of typical aircraft, ranging from a wide-body turbofan to a smyle-engme piston-prop, shows that the possible fuel savings are such that the A78-47934 « The value of aerospace design synthesis effects of wind on fuel consumption might warrant more considera- courses as viewed by aerospace professionals R S Shevell (Stanford tion in flight planning ' (Author) University, Stanford, Calif) American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Conference, Los A78-47938 ff Effect of performance objectives on the design Angeles, Calif, Aug 21-23, 1978, Paper 78-1493 5p and cost of future USAF pilot training aircraft G F Qumn and D The Stanford University Department of Aeronautics and Astro- P Breidenbach (USAF, Aeronautical Systems Div .Wright-Patterson nautics offers a course in Aerospace Systems Synthesis and Analysis AFB, Ohio) American Institute of Aeronautics and Astronautics, The course has evolved into an advanced design approach teaching Aircraft Systems and Technology Conference, Los Angeles, Calif, the blend of aerodynamic and structural theory and empiricism, Aug 21-23, 1978, Paper 78-1498 8p engineering and economics, aircraft requirements and ground system The influence of performance objectives on the airframe/engine limitations which must be integrated and optimized to produce a design characteristics for future trainer aircraft is examined It is satisfactory aircraft system A recent survey of former students now shown that a new primary trainer aircraft design, optimized for working as aerospace professionals was conducted to determine the minimum life cycle cost would have a turbofan engine with a by-pass value of the design synthesis course This paper summarizes the ratio of approximately 4 The wing aspect ratio would be approx- course concepts and the survey methods and results In general, the imately 6 A twin engine aircraft would meet the performance aerospace engineers felt the design synthesis course was a highly objectives with a design takeoff gross weight of about 8,000 pounds useful part of their education (Author) and would have an engine thrust of 2050 pounds The study points toward the possibility of using a common engine for the primary and intermediate-phase aircraft, provided the primary trainer is a single- engine configuration VP A78-47935 # Improving the accuracy of HUD approaches in wmdshear with a new control law J R Lowe (Douglas Aircraft Co , Long Beach, Calif ) American Institute of Aeronautics and Astro- A78-47939 * # Improved aircraft dynamic response and nautics, Aircraft Systems and Technology Conference, Los Angeles, fatigue life during ground operations using an active control landing Calif, Aug 21-23, 1978, Paper 78-1494 6p 6 refs gear system J R McGehee, H D Garden (NASA, Langley Research Current landing approach HUDs present the information re- Center, Hampton, Va ), and R Edson (Hydraulic Research, Valencia, quired by the pilot during the landing operation and provide Calif) American Institute of Aeronautics and Astronautics, Aircraft excellent guidance in the vast majority of conditions Unfortunately, Systems and Technology Conference, Los Angeles, Calif, Aug however, the velocity vector, if airmass derived, contains wind- 21-23, 1978, Paper 78-1499 10 p 7 refs produced errors which can mislead the pilot in a severe environment A three degree-of-freedom aircraft landing analysis incorporating A description is presented of a new concept which eliminates the a series-hydraulic active control main landing gear has been develop- velocity vector and its attendant wind-produced errors It is ed and verified using preliminary experimental data from drop tests suggested that the visual approach HUD control law should be of a modified main landing gear from a 2722 kg (6000 Ibm) class of designed to the level of sophistication of the autopilot and flight airplane The verified analysis was also employed to predict the director, which are designed as feedback compensated control landing dynamics of a supersonic research airplane with an active systems Applying the concept, called Feedback Compensated control main landing gear system The results of this investigation Control HUD, the only measured angle is the selected flight path have shown that this type of active gear is feasible and indicate a Rate lead, previously provided by the velocity vector, is provided by potential for improving airplane dynamic response and reducing aircraft vertical motion measurements that are not sensitive to wind structural fatigue damage during ground operations by approximate- G R ly 90% relative to that incurred with the passive gear (Author)

A78-47936 # The airborne detection of low level wind A78-47940 # Rolling tail design and behavior as affected by shear R A Greene (Safe Flight Instrument Corp , White Plains, actuator hinge moment limits J N Ball (Calspan Corp , Los Angeles, N Y ) American Institute of Aeronautics and Astronautics, Aircraft Calif) American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Conference, Los Angeles, Calif, Aug Systems and Technology Conference, Los Angeles, Calif, Aug 21 23, 1978, Paper 78-1495 11 p 21 refs 21-23, 1978, Paper 78-1500 7 p

515 A78 47941

A high degree of roll maneuverability is required for the A78-47945 # An analytical and experimental investigation low-altitude, high-speed (LAHS) condition of the B-1 high perfor- of diffusers for VSTOL thrust augmenting ejectors M R Seller and mance bomber It was found that the spoilers alone would be £ F Schum (Rockwell International Corp , Aircraft Div , Columbus, insufficient for meeting the roll requirements of the LAHS condi- Ohio) American Institute of Aeronautics and Astronautics, Aircraft tion Additional roll control effectiveness was, therefore, to be Systems and Technology Conference, Los Angeles, Calif, Aug provided by using differential stabilizer deflections This is the 21-23, 1978, Paper 78-1509 10 p 12refs 'rolling tail' arrangement When the wings are swept back the rolling A thrust augmented ejector is a pneumatic device which tail's contribution becomes important At a representative lateral increases the thrust by transferring the energy of the turbojet engine stick deflection of two inches, it accounts for about two-thirds of the exhaust flow to a large mass of air drawn in from the atmosphere total applied rolling moment The B-1 design is used as an example to Energy transfer is obtained by the turbulent mixing of two streams illustrate some problems that can be encountered with rolling tails In the study described in the present paper, a VTOL prototype Particular attention is given to the effect of reaching the stabilizer aircraft was used to demonstrate that additional direct lift required hinge moment limit G R for VTOL operation can be obtained from the cruise engine itself Specifically, it is shown that cambered flaps can provide a higher A78-47941 jj Investigation of electrostatic discharge in air- augmentation ratio than straight flaps, for a baseline ratio of 1 48, craft fuel tanks during refueling E Radgowski and R Albrecht this improvement is 0 12 (owing to increased internal diffusion and (Fairchild Republic Co , Farmmgdale, N Y ) American Institute of greater secondary mass flow) The best location for the wall jet Aeronautics and Astronautics, Aircraft Systems and Technology nozzle is upstream of the throat on the Coanda surface Both jet Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1501 8 momentum and augmentation ratio can be increased by distributing p USAF-supported research primary air nozzles near the augmenter exit V P High levels of electrostatic charge on JP 4 fuel during aircraft refueling, due to both the flow of fuel and the charge buildup generated by fuel contacting the explosion suppression foam A78-47946 * # Studies of aerodynamic technology for installed in some aircraft fuel tanks, were eliminated in the test VSTOL fighter/attack aircraft W P Nelms (NASA, Ames Research installation using a multihole-design fuel inlet resembling a piccolo Center, Moffett Field, Calif) American Institute of Aeronautics and This is an adaptation of a manifold inlet design investigated by Astronautics, Aircraft Systems and Technology Conference, Los various agencies as a means of reducing electrostatic charge The Angeles, Calif, Aug 21-23, 1978, Paper 78-1511 32 p 17 refs 'piccolo' inlet was selected as the result of a test program conducted The paper summarizes several studies to develop aerodynamic to evaluate several fuel inlet configurations, in conjunction with two technology for high performance VSTOL aircraft anticipated after generic types of polyurethane foam polyester, presently used in 1990 A contracted study jointly sponsored by NASA-Ames and aircraft fuel tanks, and polyether, proposed as a replacement for the David Taylor Naval Ship Research and Development Center is polyester foam Of the two types of foam tested, the polyether foam emphasized Four contractors analyzed two vertical-attitude and indicated a greater potential for producing static discharges than the three horizontal-attitude takeoff and landing concepts with gross polyester foam (Author) weights ranging from about 10433 kg (23,000 Ib) to 17236 kg (38,000 Ib) The aircraft have supersonic capability, high maneuver A78-47942 ff Nacelle effects on stability of VSTOL configu- performance (sustained load factor 6 2 at Mach 0 6, 3048 m (10,000 rations including conventional, canard, and tandem wing ft)) and a 4536 kg (10,000-lb) STO overload capability The arrangements J Wolkovitch and R L Fortenbaugh (Vought Corp, contractors have estimated the aerodynamics and identified aero- Dallas, Tex ) American Institute of Aeronautics and Astronautics, dynamic uncertainties associated with their concept Example Aircraft Systems and Technology Conference, Los Angeles, Calif, uncertainties relate to propulsion-induced flows, canard-wing interac- Aug 21-23, 1978, Paper 78-1504 14 p 12refs tions, and top inlets Wind-tunnel research programs were proposed Nacelle effects on stability of conventional, canard, and tandem to investigate these uncertainties (Author) wing subsonic VSTOL aircraft are discussed Theoretical predictions of nacelle effects on stability are compared with wind tunnel results The increased tail areas required to overcome the destabilizing effects A78-47947 * # Flight experience on the need and use of of the nacelles induce performance penalties Canard or tandem wing inflight leading edge washing for a laminar flow airfoil D F Fisher configurations may reduce these penalties Low speed wind tunnel (NASA, Flight Research Center, Edwards, Calif) and J B Peterson, data on a tandem wing configuration are presented, and a new Jr (NASA, Langley Research Center, Hampton, Va ) American tandem wing configuration which employs extreme gull-type dihe- Institute of Aeronautics and Astronautics, Aircraft Systems and dral and anhedral on the rear wing is described This configuration Technology Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper yields low induced drag and small wetted area (Author) 78-1512 11 p 5 refs An investigation of leading-edge contamination by insects was conducted at the NASA Dryden Flight Research Center with a A78-47943 # Experimental determination of propulsion in- JetStar airplane instrumented to detect transition on the outboard duced ground effects of typical three fan type A V/STOL config- leading-edge flap and equipped with a system to wash the leading urations W B Weber and R W Williams (McDonnell Aircraft Co , edge in flight The results of airline-type flights with the JetStar St Louis, Mo ) American Institute of Aeronautics and Astronautics, indicated that insects can contaminate the leading edge during Aircraft Systems and Technology Conference, Los Angeles, Calif, take-off and chmbout at large jet airports in the United States The Aug 21-23, 1978, Paper 78-1507 10 p results also showed that the insects collected on the leading edges at A description is presented of one approach to the experimental 180 knots did not erode at cruise conditions for a laminar flow determination of the suckdown and fountain effects on a typical control airplane and caused premature transition of the laminar V/STOL aircraft configuration using powered models The test boundary layer None of the superslick and hydrophobic surfaces technique was used on two different V/STOL models (10% scale) tested showed any significant advantages in alleviating the insect and included careful calibration of the 5 5 inch fans used to provide contamination problem While there may be other solutions to the inlet and nozzle flow simulation On one of these models, an insect contamination problem, the results of these tests with a extensive pressure survey was made on the underside of the model in washer system showed that a continuous water spray while encoun- order to increase the understanding of the fountain and suckdown tering the insects is effective in preventing insect contamination of forces The test facility, the fan calibration procedures, the test the leading edges (Author) configurations, instrumentation, and procedures are briefly described Aspects of data reduction are discussed and the test results are presented The presented results are compared with results A78-47952 # Safety of space flights (O bezopasnosti kosmi- obtained using a nonmetric nozzle test technique G R cheskikh poletov) L S Khachatur'iants and E V Khrunov In

516 A7848212

Characteristics of cosmonaut activities during flight A78-48062 On the use of zirconium 95 data from Chinese Moscow, Izdatel'stvo Mashmostroenie, 1976, p 5-12 atmospheric thermonuclear explosions to study stratospheric trans- In Russian port in a one-dimensional parameterization E Bauer, R vj Oliver, Illustrative examples are provided to demonstrate that the safety and W Wasylkiwskyj (Institute for Defense Analyses, Arlington, of space flights involves a large number of particular problems which Va ) Journal of Geophysical Research, vol 83, Aug 20, 1978, p are closely related to the effectiveness and reliability of spacecraft 4019-4028 27 refs US Department of Transportation Contract No engineering Analysis of the psychophysiological structure of the FA76WA-3157, No FA77WA-3965 activity of a human operator engaged in space flight reveals a number Data on the transport of Zr-95 from five Chinese 3-Mt of stages in which the flight safety decreases substantially, especially thermonuclear explosions which deposited their debris clouds at in time-deficit situations where decisions must be made without approximately 18-km altitude and location (40 deg N, 90deg E) are delay It is suggested that in order to evaluate flight safety, it is analyzed in terms of one-dimensional diffusive transport into the necessary (1) to determine the conversion factor defined as the ratio troposphere The motivation for the work is that the dynamics of of time required to perform a specific operation in space to time oxides of nitrogen and other materials injected into the lower required to perform the same operation on the ground and (2) after stratosphere by supersonic transport aircraft in the general region of completing emotionally stressed flight tasks, spare time should be 15- to 18-km altitude, 40-60 deg N latitude, is not well known, and allowed for rest S D different parametenzations of the transport by different authors vary substantially A technique is developed that allows data from pulsed sources at different seasons to be used to parameterize stratospheric A78-47978 # Operator work capacity during parachutist motions in terms of a mean stratospheric eddy diffusivity and a mean free-fall (Operativnaia rabotosposobnost' v period svobodnogo tropopause height (which characterizes an effective height of padenna parashiutista) L P Gnmak, G M Kolesmkov, V A injection above the local tropopause) and thus to estimate the Sutormm, V K Filosofov, and L S Khachatunants In Characteris- atmospheric residence time (equal to burden divided by flux) and tics of cosmonaut activities during flight Mos- also the 'injection coefficient' of McElroy et al (1974) for cow, Izdatel'stvo Mashmostroenie, 1976, p 170-180 In Russian continuous sources A correction is made for the sedimentation of Parachute lumps are a training measure used to adapt cosmo- the paniculate tracers used (Author) nauts to stresses they will experience in space flight The present paper describes experiments performed to evaluate operator work capacity under various conditions of parachute jump, particular attention is given to the quality of operator performance in free fall The main experiment involved the measurement of the capacity of A78-48100 # Aerodynamic hull design for HASPA LTA the free-falling subject to track signals produced by a device strapped optimization F R Goldschmied (Westmghouse Research and to his back It was found that the tracking performance of the Development Center, Pittsburgh, Pa ) Journal of Aircraft, vol 15, operator deteriorates in free fall The quality of the operator in Sept 1978, p 634 638 16 refs Research supported by Westing- receiving and processing semantic data under parachute-jump condi- house Electric Corp tions also deteriorates, emotional tension of the operator is accom- The present design estimates for the Navy concept of a panied by a lowering of the tactile sensitivity thresholds B J high-altitude superpressure powered aerostat (HASPA) are 800,000 cu ft hull volume at an altitude of 70,000 ft, with a.maximum required speed of 30 knots Both the hull weight and the propulsion power must be minimized for a successful vehicle design On the A78-48051 Synthesis of social surveys on noise annoy- basis of extensive wind-tunnel tests at the HASPA volume Reynolds ance T J Schultz (Bolt Beranek and Newman, Inc , Cambridge, number of 2 16 times 10 to the 6th, a 3 1 body has been selected for Mass) Acoustical Society of America, Journal, vol 64, Aug 1978, minimum hull weight, and its propulsion power requirements are p 377-405 89 fefs Research supported by the U S Department of 1 80 kW, including appendage drag and stern wake propeller Housing and Urban Development efficiency Passive boundary-layer control is applied to the aftbody Since noise was first recognized as a serious environmental by means of a Rmgleb cusp at 82% length On the forebody, the pollutant, a number of social surveys have been conducted in order to assess the magnitude of the problem and to develop suitable noise boundary layer remains laminar up to 77% length, as shown by China ratings, such that, from a measurement of certain physical character Clay wind-tunnel flow visualization at the exact HASPA Reynolds istics of community noise, one could reliably predict the com- number (Author) munity's subjective response to the noise Recently, the author has reviewed the data from social surveys concerning the noise of aircraft, street traffic, expressway traffic, and railroads Going back A78-48209 Superelement method for helicopter fuselage to the original published data, the various survey noise ratings were analysis 0 M Aksenov and Z I Burman (Aviatsionnaia Tekhnika, translated to day-night average sound level, and an independent vol 20, no 2, 1977, p 12-17 ) Soviet Aeronautics, vol 20, no 2, judgment was made, where choice was possible, as to which 1977, p 7-11 7 refs Translation respondents should be counted as 'highly annoyed ' The results of 11 In the finite element technique proposed, the helicopter fuselage of these surveys show a remarkable consistency It is proposed that is broken down into bays in the frame planes These superelements the average of these curves is the best currently available relationship are then joined to a prectson equal to that of a 'nonpartioning' for predicting community annoyance due to transportation noise of scheme Using the method of forces, a theory and a general matrix all kinds (Author) algorithm for calculating a helicopter fuselage are developed Cutouts are taken into consideration by the principle of superposed initial strains, either before or after joining For illustration, the method is applied to the calculation of an actual fuselage V P A78-48052 Long-distance focusing of Concorde sonic boom L Liszka (Kiruna Geophysical Institute, Kiruna, National Board of Occupational Safety and Health, Umea, Sweden) Acousti- cal Society of America, Journal, vol 64, Aug 1978, p 631-635 9 refs Infra acoustic signals from supersonic flights of Concorde are regularly recorded in northern Sweden at distances up to 5000 km A78-48212 Analysis of GTE tolerance monitoring jjaram- from the aircraft Relatively high signal amplitudes (up to 0 1 N/sq eter formation M Kh Bikchantaev and lu V Kozhevnikov m) are explained by a kind of long-distance focusing effect Principle lAviatsionnaia Tekhnika, vol 20, no 2, 1977, p 31-35) Soviet and consequences of the focusing effect are discussed (Author) Aeronautics, vol 20, no 2, 1977, p 23-26 Translation

517 A7848215

Formulas are derived for calculating the tolerances of gas A78-48229 Influence of slots on effectiveness of wing turbine-engine parameters The determination of tolerances as a mechanization and control surfaces with separated flow V V function of measurement errors and of permissible values of the Guliaev, A A Mikhailov, and M I Nisht (Aviatsionnaia Tekhnika, engine parameters is analyzed on the basis of extensive computa- vol 20, no 2, 1977, p 119-121 ) Soviet Aeronautics, vol 20, no 2, tional data, assuming that the permissible values are symmetrical 1977, p 102-104 Translation with respect to the mathematical expectation V P

A78-48231 Fatigue crack growth in pressurized fuselage A78-48215 Optimal control synthesis in distributed sys- panel A B Kaplun and V D Kuliev (Aviatsionnaia Tekhnika, vol tems with incomplete information G L Degtiarev and T K 20, no 2, 1977, p 124-127) Soviet Aeronautics, vol 20, no 2, Sirazetdinov (Aviatsionnaia Tekhnika, vol 20, no 2, 1977, p 1977, p 108-110 Translation 45-49 ) Soviet Aeronautics, vol 20, no 2, 1977, p 36-40 In the present paper, the growth of fatigue cracks in an airliner Translation panel under the combined effect of acoustic-pressure stresses and In the present paper, the optimal control law for a system with stresses associated with the difference in external and internal distributed parameters is derived as a function of the measured pressure is analyzed within the framework of fracture mechanics variables, expressing the latter in terms of certain functionals defined The spectrum of alternating stresses generated by acoustic pressure is on the system's state The results are shown to be useful in the described by a Rayleigh distribution A method of evaluating the synthesis of a control system for aircraft with elastic elements or influence of acoustic-pressure stresses on the growth of fatigue cracks aircraft experiencing thermal processes V P in a fuselage panel is proposed It is shown that under certain conditions, the influence of acoustic loads on crack growth exceeds by far that of the pressure difference V P

A78-48216 Modeling ground plane influence on wing aerodynamic characteristics using a finite plane screen S D Ermolenko and lu A Rogozm (Aviatsionnaia Tekhnika, vol 20, no A78-48234 Experimental determination of parameters of 2, 1977, p 50-54 ) Soviet Aeronautics, vol 20, no 2, 1977, p mathematical model of airplane cabin as regulated object with 41-44 Translation respect to air temperature in the cabin V I Krutov, V G Voronm, and A V Shcherbakov (Aviatsionnaia Tekhnika, vol 20, no 2, 1977, p 133-136 ) Sower Aeronautics, vol 20, no 2, 1977, p A78-48221 Distribution of reliability characteristics 119-122 Translation among airplane system units to ensure given flight safety level G N Kotel'nikov (Aviatsionnaia Tekhnika, vol 20, no 2, 1977, p 80-84 ) Sower Aeronautics, vol 20, no 2, 1977, p 66-70 Translation A78-48244 Investigation of nonequilibrmm two-phase flows in axisymmetric Laval nozzles A A Glazunov and A D Rychkov (Akademua Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, Nov-Dec 1977, p 86-91 ) Fluid Dynamics, vol 12, no 6, A78-48222 Definition of airplane fuselage longitudinal July 1978, p 887-892 11 refs Translation lines by the special contour method S I Leliushenko and F K In the present paper, the influence of the second phase (solid Chistiakov {Aviatsionnaia Tekhnika, vol 20, no 2, 1977, p 85-88 ) particles) on such nozzle characteristics as specific impulse, impulse Sower Aeronautics, vol 20, no 2, 1977, p 71-73 Translation losses, and the discharge coefftcient is analyzed, in the two-dimen- In order to optimize a complex program of designing 'fuselage sional case, for the subsonic, transonic, and supersonic regions of the nacelle' type surfaces, it is proposed to calculate all transverse and Laval nozzle The calculations are earned out by a modification of longitudinal lines of an aircraft fuselage by the special-contour the Lax-Wendroff method, using Mac Cormack's (1969) explicit method A block diagram for computing longitudinal lines is given as finite difference scheme The losses in specific impulse are compared a complement to the block diagram for designing a complex surface with values calculated in a quasi one-dimensional approximation that satisfies a priori optimality criteria V P V P

A78-48224 Uniformly exact conformal transformation of exterior of circle onto exterior of wing profile N M Monakhov A78-48245 Method of calculating aerodynamic coeffi- (Aviatsionnaia Tekhnika, vol 20, no 2, 1977, p 94-98 ) Soviet cients of some three-dimensional bodies with arbitrary cross section Aeronautics, vol 20, no 2, 1977, p 78-82 Translation G G Skiba and B N Fedotov (Akademua Nauk SSSR, Izvestiia, In the present paper, the local irregular part of the conformal Mekhanika Zhidkosti i Gaza, Nov-Dec 1977, p 92-98) Fluid mapping function is determined with a precision to quantities of Dynamics, vol 12, no 6, July 1978, p 892-897 Translation second-order smallness, for the conformal mapping of the exterior of Using the computer aided method proposed for calculating the the sharp trailing edge of a wing section Using an irregular conformal aerodynamic coefficients of bodies of arbitrary cross section, the mapping function it proved possible to map the entire region with a problem can be reduced to the solution of a nonlinear and a linear precision to quantities of fifth-order smallness The zero-lift angle system of equations for the proper boundary conditions The which affects all the aerodynamic characteristics of the wing section procedure is illustrated by applying it to bodies of various shape and is determined with a precision to quantities of fourth-order small- aspect ratio The results obtained by this method are shown to ness V P correlate well with the experiment V P

A78-48228 Evaluating avionics weight efficiency V P A78-48248 Asymptotic theory of a wing moving near a Gogolm and I A Iskhakov (Aviatsionnaia Tekhnika, vol 20, no 2, solid wall K V Rozhdestvenskn (Akademua Nauk SSSR, Izvestiia, 1977, p 118, 119 ) Sower Aeronautics, vol 20, no 2, 1977, p 100, Mekhanika Zhidkosti i Gaza, Nov Dec 1977, p 115-124) Fluid 101 Translation Dynamics, vol 12, no 6, July 1978, p 910918 5 refs Translation

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In the present paper, the method of matched asymptotic A78-48452 * # NASA engine system technology programs - expansions is applied to the approximate solution of the problem of An overview H W Johnson (NASA, Aeronautical Propulsion Div , unsteady motion of a lifting surface in ground effect The flow Washington, D C ) and E W Conrad (NASA, Lewis Research Center, region is conditionally broken down into characteristic zones in Energy Conservation Engines Office, Cleveland, Ohio) American which asymptotic expansions for the velocity potential are obtained Institute of Aeronautics and Astronautics and Society of Automotive in the corresponding coordinates, the expansions are then matched in Engineers, Joint Propulsion Conference, 14th, Las Vegas, Nev, July regions of general validity In the first approximation (very small 25-27, 1978, AIAA Paper 78-928 5p flight altitudes), the problem is reduced to the solution_of the The various propulsion systems technology programs are exam- Poisson equation in a plane bounded by the planform of the wing for ined The Stratospheric Cruise Emission Reduction program has the boundary conditions obtained by matching V P objective to explore and demonstrate advanced technology fuel preparation and combustion systems which produce very low emission levels, particularly with respect to the oxides of nitrogen, during high altitude cruising flight Other programs considered A78-48250 Induction of subsonic wind tunnels with slight include the Quiet, Clean, General Aviation Turbofan program, the perforation N A Marevtseva (Akademna Nauk SSSR, Izvestna. Variable Cycle Engine Technology program, the Helicopter Trans- Mekhamka Zhidkosti / Gaza, Nov-Dec 1977, p 130136) Fluid mission Technology program, the Broad Specification Fuels Tech- Dynamics, vol 12, no 6, July 1978, p 922-928 Translation nology program, the Engine Component Improvement program, the In the present paper, the perforations are assumed to be very Advanced Turboprop Technology program, the Supersonic Cruise small compared to the test section itself, while the flow boundaries Propulsion Technology program, the Materials for Advanced Turbine are broken down into two regions with different boundary condi- Engines program, and the Aeroelasticity of Turbine Engines program tions The boundary conditions hold for any Mach number The G R two-dimensional limiting boundary value problem for supersonic flow past a dipole is solved, in elementary functions, under the assumption of a small perforation factor and small velocity disturbances at the flow boundary The solution provides a simple rule for A78-48453 * •> Propulsion test facilities - Capabilities and use determining the induction V P J S Kamchi (USAF, Washington, D C) and F E Compitello (NASA, Washington, D C ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Joint Propulsion Conference, 14th, Las Vegas, Nev, July 25-27, 1978, AIAA Paper A78-48374 ft Noise in airports, its measurement, and its 78-933 11 p 16refs effect on the communities in the vicinity (Ruido en aeropuestos, su A review is conducted of the additional test facilities required in medida y afectacion a las comumdades vecinas L Marquma Sanchez connection with the National Aeronautical Facilities Program and of lAA/lngenieria Aeronautics y Astronautica, vol 30, May 1978, p other new propulsion test facilities Attention is given to the 5-19 In Spanish National Transonic Facility, the AMES wind tunnel, the Turbine An investigation is conducted regarding noise problems which Engine Load Simulator, facilities for the conduction of compressor have arisen in connection with the evolution of modern air traffic research, a fuels and lubricants laboratory, and test facilities in the Developments related to the description of noise, noise measure- UK, France, and Germany It is pointed out that there is a need for ment, and the establishment of aviation regulations with respect to government and industry to support the facility investment necessary aircraft noise emission are examined, taking into account the time to make progress in aerospace technology Aspects of international period beginning with the introduction of jet aircraft in the early cooperation are also discussed G R 1950s The development of indices indicating noise exposure levels is considered Sonic pressure levels as a function of frequency for A78-48454 # Ground test facility for integral rocket ram- various aircraft are shown in a graph Attention is given to the jets T D Myers and G F Stromberg (United Technologies Corp, composite noise rating, aspects of noise exposure prediction, the Chemical Systems Div , Sunnyvale, Calif) American Institute of noise and number index, a French noise exposure index, and indices Aeronautics and Astronautics and Society of Automotive Engineers, developed in the Netherlands, Germany, and South Africa A Joint Propulsion Conference, 14th, Las Vegas, Nev, July 25-27, description is presented of the calculation of noise exposure levels in 1978, AIAA Paper 78-934 17 p the vicinity of airports Approaches of various types for the The advent of high performance integral rocket ramjet (IRR) reduction of aircraft produced noise are also discussed G R propulsion systems has introduced a new set of ground test facility requirements CSD has constructed a modern ground test facility specifically designed and developed to handle these advanced IRR propulsion systems The CSD facility provides two important new A78-48451 # The impact of contingency power concepts on test capabilities First, rocket-to-ramjet transition tests with simu- V/STOL aircraft take-off-gross-weight R A Musselwhite (United lated or live full-scale integral booster motors can be conducted Technologies Corp , Pratt and Whitney Aircraft Group, West Palm Second, complete ramjet flight trajectories can be simulated, with Beach, Fla ) American Institute of Aeronautics and Astronautics and automatic computer control of the altitude simulation apparatus, Society of Automotive Engineers, Joint Propulsion Conference, airflow and total temperature simulation, ramjet fuel flow, and 14th, Las Vegas, Nev, July 25-27, 1978, AIAA Paper 78-926 6 p external aerodynamic heating simulation (Author) The paper presents the analytical assessment of the impact of several contingency power/engine cycle concepts on aircraft take- A78-48455 H Ramjet engine testing and simulation tech- off-gross-weight A two-engine propulsion system was chosen for niques L C Dunsworth and G J Reed (Marquardt Co , Van Nuys, evaluation to illustrate maximum system benefits The four evaluated Calif) American Institute of Aeronautics and Astronautics and concepts are (1) increased combustor exit temperature at the Society of Automotive Engineers, Joint Propulsion Conference, vertical engine-out landing condition, (2) modulation of core engine 14th, Las Vegas, Nev , July 25-27, 1978, AIAA Paper 78-935 8 p primary nozzle area, (3) modulation of turbine cooling air levels, and Simulation of flow conditions within the operating regime of (4) increased fan root pressure Each concept was evaluated for ramjet engines requires unique ground test capabilities The blow- propulsion system performance and size variations Integration of down facility is an economical method of meeting the high air mass these propulsion system changes with theairframe resulted in aircraft flow and pressure ratio requirements Vitiated air heaters provide a take-off-gross-weight reductions Consideration was given to evaluat- flexible and cost effective method of simulating trajectory tempera- ing propulsion systems that would provide improved vertical emer- ture variation Adequate simulation of the inlet flow conditions in gency landing capability with minimum performance and size freejet tests plays an important role in engine development Ramjet penalties without sacrificing durability and reliability (Author) engine ground test requirements are discussed Methods of simulating

519 A7848456

the applicable parameters in direct connect and freejet tests are A78-48471 # An experimental and numerical study of reviewed Techniques and devices that have proven beneficial in three-dimensional turbulent jets J M Barton, S F Birch, G C meeting aerodynamic simulation requirements are described Paynter, and R W Crouch (Boeing Aerospace Co , Seattle, Wash ) (Author) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Joint Propulsion Conference, 14th, Las Vegas, Nev, July 25-27, 1978, AIAA Paper 78-994 10 p 15 refs A78-48456 # Center-loaded duct integral rocket-to-ramjet A numerical method which solves the parabohzed 3-D Navier- transition testing H J Readey, Jr and E R Cobb (Martin Marietta Stokes equations with a two-equation turbulence model is used to Aerospace, Orlando, Fla ) American Institute of Aeronautics and predict three complex subsonic exhaust nozzle flows The first is the Astronautics and Society of Automotive Engineers, Joint Propulsion jet from a model-scale multi-element nozzle with a quiescent Conference, 14th, Las Vegas, Nev, July 25-27, 1978, AIAA Paper ambient The second is the jet decay behind a full-scale 727 jet 78-937 9 p airplane stationary on the runway Predicted mean flow properties This paper describes the facility test equipment and techniques are in good agreement with test data for the two flows The third that have been developed for efficient integral rocket-to-ramjet flow is the jet development from a twin-podded B-52 airplane nozzle transition testing The facility and test procedures were successfully at flight conditions No test data are available for this flow The demonstrated with the use of representative advanced cruise missile computed results are presented to indicate the applicability of the test hardware and test conditions to establish the feasibility of the analysis to 'wind on' flows Major prerequisites for successful high-performance center-loaded duct propulsion concept This con- application of the analysis to 3 D jet flows are outlined (Author) cept requires that the ramjet flameholder and fuel injectors be stationed between two solid propellant rocket grains The transition test method was selected because it produces the true thermal/time history for both the test hardware and the environment The test A78-48481 # The effect of thrust vectoring and attitude series included component checkout tests, ramburner firings to control concepts on the propulsion system of V/STOL aircraft G W. establish baseline performance, simulated transition tests to verify N Lampard (Boeing Aerospace Co, Seattle, Wash ) American facility operation, and full rocket-to-ramjet transition firing for Instituteof Aeronau tics and Astronautics and Society of Au tomo five design verification (Author) Engineers, Joint Propulsion Conference, 14th, Las Vegas, Nev, July 25-27, 1978, AIAA Paper 78-1020 8 p V/STOL aircraft design and mission performance requirements A78-48469 # Wind Tunnel/Flight Test Correlation Program and configuration features of the propulsion system are identified In on the B-1 nacelle afterbody/nozzle at transonic conditions G K the configurations analyzed, an odd number of engines leads to one Richey, D L Bowers (USAF, Flight Dynamics Laboratory, Wright- engine being mounted in the fuselage This is undesirable as it Patterson AFB, Ohio), L C Kostm (Rockwell International Corp, restricts payload volume and otherwise encumbers the body Thus, Aircraft Div , Los Angeles, Calif ), and E A Price, Jr (ARO, Inc. most designs are based on two or four engines mounted in two Arnold Engineering Development Center, Arnold Air Force Station, nacelles Thrust control concepts are discussed relative to variable Tenn ) American Institute of Aeronautics and Astronautics and geometry fans, fan flow transfer, thrust spoiling, thrust vectoring, Society of Automotive Engineers, Joint Propulsion Conference, and compressor bleed flow transfer The resulting propulsion system 14th, Las Vegas, Nev, July 25-27, 1978, AIAA Paper 78-989 8 p is compared in terms of weight, fuel consumption and required The B-1 Wind Tunnel/Flight Test Correlation Program had the advanced technology components and subsystems Design of engines objective to investigate the B-1 propulsion nacelle flow field with high bleed capability for attitude control is stressed S D differences between wind tunnel and flight test and determine the sources of these differences The wind tunnel and flight tests of the program are discussed and a description is presented of the A78-48482 # Installed performance of vectoring/reversing corresponding nacelle afterbody/nozzle instrumentation A 006 non-axisymmetric nozzles P E Hiley, D E Kitzmiller, and C M scale B-1 nozzle afterbody model was used as wind tunnel model Willard (McDonnell Aircraft Co , St Louis, Mo ) American Institute Flight data were obtained during the B-1 No 2 structural test flight of Aeronautics and Astronautics and Society of Automotive Engi- development program The test results obtained in the investigations neers, Joint Propulsion Conference, 14th, Las Vegas, Nev, July provide a good data base for the study of the flow characteristics in 25-27, 1978. AIAA Paper 78-1022 11 p 15 refs transonic flow and differences/similarities between wind tunnel and A description is presented of wind tunnel tests conducted in a flight for an exhaust nozzle/aftbody system which is closely transonic propulsion wind tunnel in connection with a program integrated with the wing and fuselage G R concerned with the experimental evaluation of nonaxisymmetnc exhaust nozzles Five 2-D nozzles were tested, representing first A78-48470 * ;;' Status of a nozzle-airframe study of a highly generation, low aspects ratio designs The types of exhaust nozzles maneuverable fighter J Nugent, N V Taillon (NASA, Flight tested include 2 D convergent-divergent nozzles with internal expan- Research Center, Edwards, Calif ), and O C Pendergraft, Jr (NASA, sion only, a 2-D single expansion ramp with combined internal/ Langley Research Center, Hampton, Va ) American Institute of external expansion, and a 2-D plug with combined internal/external Aeronautics and Astronautics and Society of Automotive Engineers, expansion Installed performance was determined for all 2-D nozzle Joint Propulsion Conference, 14th, Las Vegas, Nev, July 25-27, installations at dry and low Mach afterburning power The aero- 1978. AIAA Paper 78-990 18 p dynamic performance characteristics of the nozzle concepts were NASA is sponsoring a research program that uses coordinated evaluated for unvectored, vectored, and reverse thrust conditions A wind tunnel and flight tests to investigate nozzle-airframe flow wide disparity in transonic maneuver performance was demonstrated interactions The program objective is to compare transonic flight for unvectored conditions, but nearly equal performance resulted and wind tunnel measurements over a wide Reynolds number range with optimum vector angle settings G R The paper discusses the progress of the program and the coordination of the wind tunnel and flight tests with regard to program elements, model-airplane differences, instrument locations, and test conditions A78-48483 # Non-axisymmetric nozzle design and evalua- The real-time feedback techniques used to obtain steady flight tion for F-111 flight demonstration G F Goetz.J E Petit, and M conditions are presented Available wind tunnel results are presented B Sussman (Boeing Aerospace Co, Seattle, Wash ) American for the jet effects model showing the influence of the rear-end Institute of Aeronautics and Astronautics and Society of Automotive geometry and test variables on nozzle drag Available flight results Engineers, Joint Propulsion Conference, 14th, Las Vegas, Nev, July show the effect of the variable inlet ramp angle and angle of attack 25-27, 1978, AIAA Paper 78-1025 13 p Contract No on fuselage pressures and upper surface boundary layers (Author) F33615-76-C-3107

520 A78-48496

A previous 2 D nozzle design study has been extended to airflow match, engine thrust schedule, and engine accessory location evaluate the impact of thrust vectoring during afterburning and Attention is given to propulsion system configurations, tradeoff structural integration with the aircraft The impact of one such studies, engine-inlet matching studies, aspects of nacelle design installation on the performance and flight control characteristics of integration, and engine operational procedures G R an F-111 aircraft modified for flight demonstration was evaluated Preliminary design layouts showed the feasibility of the concept and key considerations for appropriate flight research are discussed (Author) A78-48494 ff Important simulation parameters for the experimental testing of propulsion induced lift effects E P Schuster A78-48486 ff Propulsion for future supersonic transports - and J D Flood (McDonnell Aircraft Co , St Louis, Mo ) American 1978 status G B Evelyn, P E Johnson, and A Sigalla (Boeing Institute of Aeronautics and Astronautics and Society of Automotive Commercial Airplane Co , Seattle, Wash ) American Institute of Engineers, Joint Propulsion Conference, 14th, Las Vegas, Nev, July Aeronautics and Astronautics and Society of Automotive Engineers, 25-27, 1978, AIAA Paper 78-1078 1J)p_ _ Joint Propulsion Conference, 14th, Las Vegas, Nev, July 25-27, The demanding performance requirements for V/STOL aircraft 1978, AIAA Paper 78-1051 14 p 13 refs have made it important to accurately evaluate aircraft forces and Results of several studies that have taken place since the moments in ground effect Sizeable forces may be induced on the cancellation of the United States SST program in 1971 have shown airframe due to interactions with the flow field formed by the significant progress in the technology that may make such an propulsion system exhausting in close proximity to the ground This airplane eventually possible Advances in propulsion technology have paper examines experimental results obtained during a number of been a strong element of this progress The state of propulsion scale model tests on several V/STOL aircraft designs currently under technology, as applicable to a future SST, is reviewed, with emphasis investigation Induced force and moment data, exclusive of the on the progress and changes that have occurred since 1971 The propulsion system thrust, are presented as a function of ground review includes discussion of the basic technology that affects height and represent the primary test information Airframe lower thermodynamic and mechanical characteristics of supersonic engines, surface pressure measurements recorded during the tests are also competitive types of engine cycles, the state of supersonic intake presented These pressure measurements have been a significant aid technology and candidate concepts, and supersonic engine nozzles in understanding the force and moment results The ralative Emphasis is placed on the interactions of the propulsion system with importance of simulation test parameters, such as nozzle exhaust the rest of the airplane and on the assessment of the propulsion profile, nozzle geometry and model dimensional details, is identified system in terms of airplane performance and noise (Authorl (Author)

A78-48487 ff Advanced supersonic transport engine integra- A78-48495 S Evaluation of inlet remgestion for large bypass tion studies for near-term technology readiness date R D Fitz ratio V/STOL aircraft C R Limage (Vought Corp , Dallas, Tex ) Simmons, W T Rowe, and E S Johnson (Douglas Aircraft Co , American Institute of Aeronautics and Astronautics and Society of Long Beach, Calif ) American Institute of Aeronautics and Astro- Automotive Engineers, Joint Propulsion Conference, 14th, Las nautics and Society of Automotive Engineers, Joint Propulsion Vegas, Nev, July 25-27. 1978, AIAA Paper 78-1079 8 p 9 refs Conference, 14th, Las Vegas, Nev, My 25-27, 1978, AIAA Paper A parametric test program was conducted at Vought to evaluate 78-1052 8p 12 refs remgestion characteristics of large bypass ratio V/STOL aircraft The identification of the proper engine cycle, or cycles, is the Ejectors were used to simulate the propulsion flows of two, three most critical task facing the advanced supersonic technology teams and four jet configurations over a range of ground heights and angle today It determines research requirements in propulsion, acoustics of attack. Effects of number of jets, jet and inlet locations and inlet and aerodynamics plus overall program timing, requirements, funding shields on inlet remgestion were evaluated The test results show the and, eventually, airline acceptance This paper compares the results importance of jet and inlet location on the amount of inlet of a near-term engme-airframe integration study covering four U S remgestion incurred for the configurations tested By creating a engine company low-bypass-ratio turbojet engine designs that have favorable near ground flow field through correct location of jets, technology readiness dates from 1978 to 1982 for program go-ahead mlets, and aerodynamic surfaces, the amount of remgestion, can be The effects of changes in technology readiness dates are described significantly reduced (Author) and compared with variable-cycle engines of more advanced technology reported on earlier In addition, study results of a European A78-48496 ff Vectoring non-axisymmetric nozzle jet in- engine design with a 1982 technology readiness date are included A duced effects on a V/STOL fighter model W C Schnell and R L typical low-bypass-ratio engine cycle is chosen to illustrate the effect Grossman (Grumman Aerospace Corp , Bethpage, N Y ) American on airplane performance caused by optimum inlet-engine airflow Institute of Aeronautics and Astronautics and Society of Automotive matching A new Douglas Aircraft Company baseline airplane Engineers, Joint Propulsion Conference, 14th, Las Vegas, Nev, July designed to carry 225 passengers in an all metal airframe which can 25-27, 1978, AIAA Paper 78-1080 19 p 7 refs be ready for an early- to mid-1980 go-ahead is used for the detailed An experimental program sponsored by the Air Force Flight integration studies (Author) Dynamics Laboratory, utilizing a 1/8th scale advanced twin engine, thrust vectoring, V/STOL fighter wind tunnel jet effects model A78-48488 ff Propulsion system airframe integration studies developed for the Naval Air Propulsion Test Center, was completed - Advanced supersonic transport J R Wilson and J L Benson in June of 1977 at the Arnold Engineering Development Center The (Lockheed California Co , Burbank, Calif) American Institute of experimental program consisted of three primary parts (1) measure- Aeronautics and Astronautics and Society of Automotive Engineers, ment of the static internal performance characteristics of several Joint Propulsion Conference, 14th, Las Vegas, Nev, July 25-27, non-axisymmetric nozzles and a baseline axisymmetric nozzle. (2) 1978, AIAA Paper 78-1053 7 p comparison of the installed dry power performance of the non- One of the objectives of the considered integration studies is axisymmetnc nozzles with the axisymmetric nozzle, and (3) mea- related to the identification of engme/airframe configurations which surement of the inflight thrust vectoring propulsion induced aero- offer the best performance potential within environmental con- dynamic effects of the nonaxisymmetric nozzle installations This straints Other objectives include the identification of engine cycle paper describes the results from part (3) of this program Results and geometry improvements, the development of practical prelimi- from parts (1) and (2) were presented in a prior publication The part nary designs of most promising configurations, and the identification (3) findings show significant aircraft performance improvements of test and development program requirements The variables when the nonaxisymmetric nozzles are vectored The overall program examined in the study are related to the engine nacelle location, the clearly produced a major contribution to the developing nonaxi- inlet configuration, the engine cycle/configuration, engine-inlet symmetric nozzle/airplane installation data base (Author)

521 A78-48497

A78-48497 # Design for durability - The F101-GE-100 effect Some aspects of intensifying the chromium plating process engine T L Hampton and W E Schoenborn (General Electric Co , and of preparing hermetic chromium coatings are discussed The Evendale, Ohio) American Institute of Aeronautics and Astronautics influence of residual stresses in the surface layer on fatigue strength and Society of Automotive Engineers, Joint Propulsion Conference, is examined v P 14th, Las Vegas. Nev .July 25-27, 1978, A/AA Paper 78-1084 19 p 6refs In connection with the occurrence of turbine engine structural A78-48523 I: Communication and navigation antennas for problems in the late sixties, it was recognized that the existing Air aircraft (Sviaznye i navigatsionnye antenny samoletov) A A Bolbot, Force and Navy specification requirements included inadequate L la H'nitskn, and I I Kuprnanov Moscow, Izdatel'stvo Transport, specific criteria for the structural design of engines The result of this 1978 176 p 46 refs In Russian recognition was the formulation of the Engine Structural Integrity The book discusses the principles of operation and design of Program (EIMSIP) philosophy of structural design, verification and antennas for civil aircraft and provides material on the allocation and life management, with the objective of providing the using services application of antennas on the aircraft Basic theory on the operation with more durable engines The first application of the ENSIP of each type of antenna is given, and the mam operating characteris- philosophy was in the 1969 Request for Proposal for an engine to tics, parameters, and features of use of the antennas are described power the B-1 bomber The resulting competition led to the selection Topics studied include the radiation pattern, the directivity and gam of the F101-GE-100 Augmented Turbofan engine The design and coefficients, measurement of the standing wave ratio and input test verification phases of the EIMSIP philosophy were subsequently impedance, measurement of antenna efficiency, electromagnetic carried over into the Prime Item Development Specification for the compatibility of onboard antennas, stiff wire antennas, folded dipole F101 engine G R antennas, upper feed antennas, slot antennas, antennas for communication with artificial earth satellites, close feed stub antennas, surface wedge antennas, close range communication antennas for helicopters, A78-48499 # Boundary layers in axisymmetric inlets at radio compass antennas, radio altimeter antennas, and marker angle of attack I - Measurements M D Breer (Boeing Wichita Co , receiver antennas P T H Wichita, Kan) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Joint Propulsion Conference, 14th, Las Vegas, Nev, July 2527, 1978, AIAA Paper 78-1W9 7 p A78-48736 # InterScan - A new microwave approach and A 34%-contraction-ratio axisymmetric inlet model was tested in landing guidance system H C Minnett (Commonwealth Scientific a 9 x 9 ft low-speed wind tunnel for the purpose of measuring and Industrial Research Organization, Div of Radio Physics, Sydney, boundary-layer profiles at angles of attack ranging from 0 to 40 deg Australia) and G H Boyd (Department of Motor Transport, Boundary-layer total pressure profiles were measured at four Melbourne, Australia) Navigation (Australia), vol 5, Dec 1977, p circumferential and four axial positions in the inlet diffuser 583-594 Variations in tunnel wind speed, angle of attack, and model airflow InterScan is a proposed system for approach and landing resulted in 448 individual profiles Tests to establish flow separation guidance operating in C-band, designed to meet new CAO opera- were also conducted under seven different conditions The inter- tional requirements Wide sectors of azimuth and elevation angular action of shock waves with the boundary layer caused a significant guidance and also low-level height information for flare guidance are increase in profile thickness A 'quickie' method was found to transmitted to aircraft from ground-based subsystems The complete determine the boundary in an inlet design envelope between system comprises six subsystems providing these functions approach separated and attached flows The test data were used to evaluate guidance in horizontal plane, missed approach and takeoff guidance potential-flow and boundary layer analytical methods (Author) in horizontal plane, approach guidance in vertical plane, missed approach guidance in vertical plane, low-level vertical guidance for landing, and distance information throughout the coverage volume The system operates in a TDM format requiring a bandwidth of only A78-48504 # Optimization techniques for air traffic control 300 KHz for each channel, thus providing growth potential The problems (Melody optimizatsn protsessov upravlenna vozdushnym principle of angle guidance is the time-reference scanning-beam dvizheniem) G A Kryzhanovskn and V A Solodukhin Moscow, Rapid scanning of either planar or conical beams is required Results Izdatel'stvo Transport, 1978 152 p 159 refs In Russian of ground and flight tests are presented which demonstrate the The book addresses the problem of modeling the various high-quality angle guidance provided by InterScan P T H processes involved in air traffic control, and describes methods of solving the resulting optimization problems Optimization of both static and dynamic processes in air traffic control systems is A78-48864 Large deflection static analysis of typical considered Special methods treated include a method of solving tail-wheel structure of light aircraft by finite element method P N linear programming problems without the requirement of sign Raju and M R Shanbhag (Hindustan Aeronautics, Ltd , Bangalore, defmiteness of the variables, a combined method of solving problems India) International Journal for Numerical Methods in Engineering, of optimization of static nonlinear processes, a method for optimiz- vol 12, no 8, 1978, p 1203-1212 ing dynamic processes in air traffic control with allowance for time The static analysis of the tail-wheel structure of a typical light delay and incomplete measurements, and the principle of equivalence aircraft yields load-deflection characteristics, which in turn yield the of parametric equations in dynamic optimization problems The energy absorbed by the structure during landing A straight beam principles of programming hybrid computer systems to solve certain element with two end nodes and three degrees of freedom at each problems in optimization are set forth P T H node point is used as a building block to represent the finite element model of the structure The analysis is based on the theory of incremental linearization, in which changes in geometry as loading progresses are taken into account B J A78-48518 # Extending the service life of aircidtt components made of high-strength steels (Povysheme resursa aviatsion- nykh detalei iz vysokoprochnykh stalei) A la Riaboi and L D A78-48982 Application of cryogenics in experimental Brondz Moscow, Izdatel'stvo Mashmostroeme, 1977 104 p 43 refs aerodynamics (Anwendung der Tieftemperaturtechmk im stromungs- In Russian technischen Versuchswesen) T Hottner (Stuttgart, Universitat, The book deals with methods of extending the service life of Stuttgart, West Germany) Ingenieur-Archiv, vol 47, no 4, 1978, p chromium plated aircraft steels The factors responsible for the 241-256 13 refs In German pronounced decrease in durability of high-strength steels due to Difficulties concerning the study of the models of large aircraft chromium plating are examined, along with methods of avoiding this in the wind tunnel are related to the huge energy requirements for

522 A78-49334

the performance of the tests These requirements can be reduced by thermal cycling loads is demonstrated on the basis of an airliner decreasing the kinematical viscosity This can be done by increasing engine Methods of evaluating the thermal fatigue strength of the static pressure or by reducing the operational temperature The gas-turbine engines are examined, and the need for the development current status of aerodynamic simulation technology is examined of mathematical models that would take into consideration all the and a description is provided of a cryogenic wind tunnel with factors affecting thermal cyclic fatigue is pointed out V P closed-design characteristics for quasi-continuous operation Atten- tion is given to an application of cryogenic technology in the case of blow-down storage wind tunnels, the employment of cryogenics for a A78-49238 A systems approach to heliport lighting J R hybrid tunnel, and the use of heavy gases (CF2CI2) as test gas Downing (Downing Electronics, Inc , Northndge, Calif) Vertiflite, (Author) vol 24, Sept-Oct 1978, p 8,9 A heliport lighting system is described that comprises a surface floodlight-perimeter combination, a visual-approach-slope indicator, A78-49025 ff Effect of jet fuel autooxidation products on a high-intensity strobe locating beacon, a low-level perimeter light, a thermooxidation stability (Vliianie produktov avtookisleniia reaktiv- landing direction arrow floodlight, and a remote radio receiver nykh topliv na termookislitel'nuiu stabil'nost') IM la Chertkova and control Suggested layouts for the lighting system at a round heliport A A Gureev (Moskovsku Institut Neftekhimicheskoi i Gazovoi and at a rectangular one are shown P T H Promyshlennosti, Moscow, USSR) Khimna i Tekhnologna Topliv i Masel, no 8, 1978, p 48-52 14 refs In Russian Isooctane, benzol, and methanol oxygen compounds were A78-49239 LOGMOD - The fault-isolator W L Andre extracted from T-7 jet fuel stored for a long period of time in iron (U S Army, Research and Technology Laboratories, Moffett Field. tanks and were then added in measured concentrations to T 7 fuel Calif) Vertiflite, vol 24, Sept-Oct 1978, p 18,19 that was initially free of oxygen compounds in order to study the A portable 20-lb device called LOGMOD (Logic Model) can spot effect of the autooxidation products on thermooxidation stability It a malfunction in a helicopter system, isolate it, and then tell how to was found that alcohols formed during low temperature liquid phase correct it LOGMOD can fault-isolate helicopter systems such as gun oxidation of hydrogenization fuels plays the role of inhibitor of turrets, flight-control systems, and electrical-hydraulic subsystems further fuel oxidation at a certain concentration and up to a certain The unit can be operated by an untrained technician after 30 temperature limit The effectiveness of the alcohols is maintained up minutes of instruction LOGMOD operates on the actual functional to 120-150 C At 150 C their structure begins to change with dependency logic of the hardware design of a unit being tested to formation of more high-molecular densification products P T H show where and what test is needed It stores detail logic of aircraft systems containing thousands of parts A logic model is put together of an entire aircraft which can fault-isolate to any level of A78-49163 ti Highly survivable integrated avionics J J maintenance No details on design of the instrument are given PTH Deyst, Jr and A L Hopkins, Jr (Charles Stark Draper Laboratory, Inc , Cambridge, Mass ) Astronautics and Aeronautics, vol 16, Sept 1978, p 30-41 15 refs A system of highly-survivable integrated avionics is presented A78-49285 ff Dynamics of the longitudinal motion of an The distributed information-processing hierarchy is outlined with airplane with a variable-geometry wing Z Dzygadlo and J reference to sensor/effector components, regional computers, hier- Maruszkiewicz Journal of Technical Physics, vol 19, no 1, 1978, p archical-redundant data communications, and the fault tolerant 125-136 7 refs computer The three major elements of wholly integrated avionics The longitudinal motion stability of aircraft with fixed and systems are described in detail sensors, computers, and actuator/ variable sweep wings is analyzed numerically It is found that an controls S C S aircraft which is stable for fixed sweep angles undergoes considerable perturbations of the principal flight parameters if the sweepback angle varies during flight Variable sweep has a significant effect on A78-49169 Mirage 2000 - Dassault's better delta D perturbations of incidence angle, trajectory inclination angle, speed, Richardson, J M Ramsden, D Velupillai, and G Warwick Flight and altitude It is concluded that, in order to maintain flight International, vol 114, Aug 26, 1978, p 637-640 parameters within prescribed limits, it is necessary to operate the The circumstances that lead to the cancellation, in 1975, of the controls during change of sweep angle B J Super Mirage in favor of the Delta 2000 powered by a single M53-5 turbofan are reviewed The advantages of Dassault's new delta concept over the conventional delta are pointed out V P A78-49333 # Use of the U S interim standard microwave landing system in Canada W C Reed (Canadian Aeronautics and Space Institute, Canadian Symposium on Navigation, 3rd, Ottawa, A78-49175 # 10 years of contract research for the pump/ Canada, Nov 16, 17, 19771 Canadian Aeronautics and Space compressor industrial concern (10 Jahre Vertragsforschung fur das Journal, vol 24, July-Aug 1978, p 217227 Kombmat Pumpen und Verdichter) H -J Klemert (Dresden, Tech A general description of the Tull Microwave ILS serving as the nische Universitat, Dresden, East Germany) Dresden Technische US Interim Standard ILS is given The system operates at 50-525 Universitat, Wissenschaftliche Zeitschnft, vol 27, no 3-4, 1978, p GHz and uses a scanning beam technique for ease of installation and 747-752 26 refs In German siting The system uses the ILS signal format of 90 Hz and 150 Hz in The goals, trends, and results of the past ten years of research at order to provide compatibility with aircraft ILS/VOR receivers the state concern for pumps and compressors are summarized Principal ground elements are the locahzer and glide-path sub- Problems worked on included design and measurement techniques systems By the principle of beating, the 20 standard ILS frequency for piston compressors, oil and condensate precipitation from pairs can be produced by means of a single converter frequency MLS pressure gases, and flow in rotary pumps Some computer-generated airborne equipment interfaces with existing ILS receivers and velocity fields in a rotary pump are shown P T H instrumentation are illustrated The installation of the system in a first application at the heliports of a helicopter shuttle service is A78-49176 # Aspects of the thermal fatigue strength of described PTH gas-turbine engine components (Problemy termotsiklicheskoi prochnosti detalei GTD) N D Kuznetsov Problemy Prochnosti, June A78-49334 // Lateral-aerodynamic characteristics of highly- 1978, p 3-7 7 refs In Russian dihedraled wings B Kroeker and J DeLauner (Toronto, University, The present review of gas-turbine disk and blade failures points Toronto, Canada) Canadian Aeronautics and Space Journal, vol 24, toward a major contribution of thermal cycling to the failure of July-Aug 1978, p 240-245 11 refs Research supported by the these and other engine components The complexity of the action of National Research Council

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A computer was used to find the solutions for a vortex-lattice to the helicopter by the suspension Aerodynamic reactions of both model of a V-dihedraled wing or tail The formulations of Hedman the helicopter and load were expressed as stability derivatives The (1966) were used, but were extended to take into account rigid body modes of the helicopter were changed almost completely noncoplanar vortex elements The aspect ratios varied from 2 0 to by the load, the effect being generally destabilizing, the helicopter 200, the dihedral angles were 10, 20, 30, 40, and 50 deg, and the acted as a load stabilizer, however, by making the yawing motion less taper ratios were 0 25, 0 5, and 1 Incompressible, attached, and divergent B J inviscid flow is assumed The program calculated the values of K, defined as the ratio of the lift coefficient on one wing half at given A78-49399 Helicopter rotor vibration isolation R A angle of attack with the other half at the negative of this angle to the Desjardms and W E Hooper (Boeing Vertol Co , Philadelphia, Pa ) lift coefficient on one wing with both halves at equal angle of attack Vertica, vol 2, no 2, 1978, p 145-159 14 refs One result is that the K values varied little with dihedral angle from An isolation system has been developed for hmgeless rotor 10 to 50 deg Previous IMACA values were consistently higher than helicopters which has been demonstrated to be extremely effective in the present ones The use of 16 panels in the computation was found preventing rotor induced vibration from reaching the airframe to provide sufficient accuracy P T H Named IRIS (Improved Rotor Isolation System) the system has been in development for 3 years and was first flown and is currently being A78-49336 * Gas turbine engine emissions - Problems, pro- demonstrated on a BO-105 helicopter A similar system has been gress and future R E Jones (NASA, Lewis Research Center, installed in a Company-owned Model 179 helicopter and is presently Experimental Combustor Section, Cleveland, Ohio) Progress in being developed through flight testing This paper describes some of Energy and Combustion Science, vol 4, no 2, 1978, p 73-113 125 the analytical and bench testing background of both IRIS installa- refs tions and presents lastest available flight data (Author) The current status of the problem of gas turbine engine emissions is reviewed Presently promulgated EPA standards and their implications for aircraft gas turbines are discussed The progress A78-49427 * ff Volumetric pattern analysis of airborne anten- and status of emissions reduction technology programs and other nas C L Yu (U S Navy, Naval Weapons Center, China Lake, Calif), efforts which have emphasized advanced combustor technology are W D Burnside (Ohio State University, Columbus, Ohio), and M C reviewed in detail Also examined are those efforts underway to Gilreath (NASA, Langley Research Center, Hampton, Va ) IEEE determine the emissions floor and incorporate those techniques into Transactions on Antennas and Propagation, vol AP-26, Sept 1978, practical combustors of the future P T H p 636-641 8 refs Grant No NGL-36-008-138 By blending together the roll and elevation plane high-frequency A78-49396 Design and development of a multifunctional solutions, a very efficient technique has been developed for the helicopter control system W J Kubbat (Messerschmitt-Bolkow- volumetric pattern analysis of antennas mounted on the fuselage of a Blohm GmbH, Munich, West Germany) (European Rotorcraft and generalized aircraft The fuselage is simulated by an infinitely long, Powered Lift Aircraft Forum, 3rd, Aix-en-Provence, France, Sept perfectly conducting, elliptic cylinder in cross section and a 7-9, 19771 Vertica, vol 2, no 2, 1978, p 99-109 composite elliptic cylinder in profile The wings, nose section, The paper describes the design and development of helicopter stabilizers, and landing-gear doors may be modeled by finite flat or control system which incorporates the functions of control and bent plates Good agreement with accurate scale model measure- stabilization, autopilot, air data computation and strap down ments has been obtained for a variety of airborne antenna problems computation All functions mentioned are performed within one (Author) dual processor computer The system controls all four axis of the A78-49428 Conformal microstrip phased array for aircraft helicopter (roll, pitch, yaw and collective) This non-redundant tests with ATS-6 G G Sanford (Ball Brothers Research Corp, system is fail soft, that means that any failure occurring will be Boulder, Colo ) IEEE Transactions on Antennas and Propagation, detected and indicated to the pilot as well as will cause a vol AP-26, Sept 1978, p 642-646 6 refs US Department of disconnection of the system itself Flight tests with a forerunner of Transportation Contract No TSC-763 this system (with only a different computer) have been successfully The development of a novel L-band microstrip phased array for performed Final flight tests with the end configuration are soon to come (Author) aircraft is described The array is electronically steerable in elevation, conformal to the surface of an aircraft, 0 14-m thick, low cost in production quantities, installed without cutting large holes in the A78-49397 Measurement of vibratory displacements of a aircraft, and capable of 12-dB gam relative to right hand circular rotating blade D R Gaukroger and C J W Hassal (Royal Aircraft isotrope The microstrip radiating element is described, and its Establishment, Farnborough, Hants, England) Vertica, vol 2, no 2, operation is explained The array design is considered in relation to 1978, p 111-120 ground plane curvature, grating lobes, sidelobes, beam shape and An experimental technique for determining the vibratory gam A technique for obtaining 30 deg phase resolution from 3-bit displacements of a helicopter blade is described Strain-gauges are phase shifters is presented The design of simple loaded line and used to sense the vibratory behavior of the rotating blade, the switched line phase shifters is reported (Author) strain-gauge output pattern is then converted to a displacement pattern using relationships measured for the non-rotating blade Some results of the application of the technique to a model blade are A78-49439 ff Fading at 9.6 GHz on an experimentally given (Author) simulated aircraft-to-ground path H B Janes and M C Thompson, Jr (NOAA, Institute for Telecommunication Sciences, Boulder, A78-49398 Stability of a helicopter carrying an under- Colo I IEEE Transactions on Antennas and Propagation, vol AP-26, slung load A Prabhakar (Royal Military College of Science, Sept 1978, p 715-719 Contract No F30602-75-F-0256 Shrivenham, Wilts, England) (European Rotorcraft and Powered This report describes an experimental study of fading at 9 6 Lift Aircraft Forum, 3rd, Aix-en-Provence, France, Sept 7-9, 19771 GHz on a fixed slanted Ime-of-sight path simulating aircraft-to- Vertica, vol 2, no 2, 1978, p 121-143 23 refs ground propagation conditions Recordings of signal fading were A theoretical study is presented of the dynamics of a Sea King made over about one year The data were analyzed to provide a helicopter carrying a 2 ton, 20 x 8 x 8 ft standard cargo container, statistical description of the fading, and to compare some of these slung by four cables from two longitudinally separated suspension statistics with those obtained elsewhere under different climatic and points on the helicopter fuselage Equations of motion of the terrain conditions The results include the probabilities of occurrence helicopter-underslung load system were derived by representing them of fading rates and fade durations at several signal levels below the as two rigid bodies moving through space, the load being constrained hourly median level The extent to which fading behavior depends on

524 A78-49676

time-of-day and time-of-year was investigated, along with the accuracy requirements, and describes the test and demonstration correlation of hourly average fade duration and hourly fading rate program B J (Author)

A7R-49550 The US Navy bets on V/STOL R Steele and A78-49447 # An integrated analysis of the fundamental R Aurora (Grumman Aerospace Corp, Bethpage, N Y) IEEE problems of air transport (Analisis mtegrado de los problemas Spectrum, vol 15, Sept 1978, p 5863 fundamentales del transporte aereo) P Gonzalez Cristobal IA A/ The U S Navy has begun planning the next generation of Ingenieria Aeronautics y Astronautics, vol 30, June-July 1978, p sea-based aircraft, encompassing two types of V/STOL (1) a 5-14 In Spanish subsonic aircraft outfitted with ASW or AEW, and (2) a supersonic An investigation is conducted regarding the various factors fighter/interceptor/attack aircraft This paper reviews the various involved in the selection of new aircraft by companies engaged in air technologies which will be integrated to produce this new-generation transport operations Attention is also given to work and procedures V/STOL Particular consideration is given to conformal radar, required in connection with the fabrication and the acceptance of a advanced display concepts (e g , AIDS), avioptics, the data processing new aircraft, its maintenance, and the preparation of personnel of system, and the flight control system B J the company purchasing the aircraft for the various tasks which will have to be performed in connection with the operation and the maintenance of the aircraft Factors affecting the selection of a particular aircraft by a company engaged in air transport operations A78-49660 The Omega radionavigation system comes to can be divided into two categories One category includes factors the Pacific Ocean area D T Haislip and D C Scull (U S Coast related to the requirements of the company Factors of the second Guard]" Washington, D~C7~ In Oceans '77, Annual Combined category are related to the aircraft types made available by the Conference, 3rd, Los Angeles, Calif, October 17-19, 1977, Confer- aircraft manufacturers, financial aspects, purchasing conditions, and ence Record Volume 2 New York, Institute of other external matters Each factor of both categories is examined Electrical and Electronics Engineers, Inc , Washington, D C, Marine individually G R Technology Society, 1977, p 38A-1 to 38A-9 7 refs Two Omega transmitting stations have been in operation in the A78-49449 ft Operational regularity in air transport (La Pacific Ocean area for some time at Tsushima, Japan and Oahu, regulandad de la operation en el transporte aereo) L Dommguez Hawaii In addition, the Pacific region receives usable transmissions Rodrfguez lAA/lngen/eria Aeronautics y Astronautics, vol 30, from Omega stations in Aldar, Norway, La Reunion, Indian Ocean, June-July 1978, p 33-36 In Spanish and Golfo Nuevo, Argentina A final station is planned for siting in Regularity of service is a desirable trait in transport operations the South Pacific area, and probably will be located in Australia A regularity index is used to obtain a quantitative measure for this Even without the final station, adequate Omega coverage is now trait A suitable definition for the regularity index is considered and available in large portions of the Pacific Ocean area The Omega an analysis is conducted regarding the conditions which affect it in monitoring network, the processing of the collected data, the one form or another The procedures employed in the prediction of analysis of predicted and observed signal coverage, and other steps in regularity data are discussed, taking into account predictions made in Omega system validation are necessary to provide the navigating the case of an aircraft during the design phase and the actual community with a viable radio navigation system for the Pacific statistical data obtained at a later time Attention is given to various Ocean area B J factors causing operational delays, questions concerning the availabil ity of the aircraft, a review of the delay probabilities for the various A78-49661 Twoway - A position and orientation measure- systems of the DC-9, data concerning service reliability, flight safety, ment system J Kuipers (Austin Co , Roselle, N J ) In Oceans '77, and maintenance costs GR Annual Combined Conference, 3rd, Los Angeles, Calif, October 17-19, 1977, Conference Record Volume 2 A78-49524 Airliner numbers game - Does it add up M New York, Institute of Electrical and Electronics Engineers, Inc , Hewish New Scientist, vol 79, Aug 31,1978, p 615-617 Washington, DC, Marine Technology Society. 1977, p 38E-1 to Recently the nationalized British Aerospace corporation was 38E-13 authorized by the government to resume development of the 146 jet Twoway is a full six-degree-of freedom position measurement transport, which will carry 70 to 109 passengers On the same day as system which operates cooperatively between two relatively remote the 146 was relaunched, British Airways were advised to buy 19 but independent bodies The system fuuctions symmetrically, using a Boeing 737s to replace its fleet of Tridents British Airways now relatively simple electromagnetic signal which is alternately received wants to go further and order Boeing's new 757 Rolls-Royce from, processed, and transmitted to the other body in a transponding supports this application, because the airline would specify British or multiplexed manner Twoway can provide in each body a measure RB 211 engines for the 757 and give Rolls-Royce the advantage of of the two pointing angles and range which define the direction to having its powerplant as the initial standard in the new American and the position of the other body together with the three Euler airliner France, Germany, Holland, and Spain are now partners in angles (or direction cosines) which define the relative orientation Airbus Industrie, which builds the A300 wide-body airliner The type between the two bodies The system consists of an antenna which is has been ordered by Eastern Airlines in the U S , setting the seal on precisely fixed and oriented to its body, the signals received from its acceptability G R and transmitted to the other body are processed by the System Electronics Unit B J

A78-49549 Landing aircraft under poor conditions R J A78-49676 ft Airfield pavement load evaluation - An inter- Kelly, H W Redlien, and J L Shagena (Bendix Corp , Towson, national overview G D Bell (British Airports Authority, London, Md) IEEE Spectrum, vol 15, Sept 1978, p 52-57 England) (American Society of Civil Engineers, Annual Convention, The time-reference scanning-beam microwave landing system Exposition and Continuing Education Program, San Francisco, Calif, (TRSB MLS) is the new all-weather landing system designed to Oct 17-21, 1977) ASCE, Transportation Engineering Journal, vol replace ILS TRSB MLS is a systems approach to the landing- 104, Sept 1978, p 531-536 guidance problem, it can meet a variety of performance, economic, Consideration is given to airfield pavement load evaluations and and safety requirements and still supply a universal airborne procedures for reporting the findings of such studies to airfield receiver-processor able to operate with all ground systems This paper administration authorities, airline operators, aircraft manufacturers, describes the operating principles of TRSB MLS, discusses the and airfield licensing authorities Evaluation programs are discussed

525 A78-49677

with reference to determining financial balances between initial costs tion and Continuing Education Program, San Francisco, Calif, Oct and subsequent development and maintenance, and assessing load 17-21, 1977) ASCE, Transportation Engineering Journal, vol 104, ratings for aircraft and pavements Various testing methods are Sept 1978, p 581-585 reviewed including static, moving, and dynamic destructive testing, The current policy of the Federal Aviation Administration the application of vibrating loads, ultrasonic testing, and radiographic concerning airfield pavement evaluations and standards is described techniques S C S Research programs, undertaken in conjunction with the Waterways Experiment Station of the U S Army Corps of Engineers are A78-49677 # Proposed load evaluation system for U S Air discussed with reference to the California Bearing Ratio design Force G T Batrd and J P Nielsen (New Mexico, University, method Changes in design procedures for rigid pavements are Albuquerque, N Mex) (American Society of Civil Engineers, identified although it is noted that no changes have been effected Annual Convention, Exposition and Continuing Education Program, regarding the policy of landing gear design S C S San Francisco, Calif, Oct 17-21, 19771 ASCE, Transportation Engineering Journal, vol 104, Sept 1978, p 537-543 A78-49682 # Pavement strength rating methods as viewed A nondestructive pavement load evaluation system developed by by airframe manufacturers W A Woodcock (Boeing Technology the U S Air Force is described Particular attention is given to International, Inc. Seattle, Wash) (American Society of Civil computer codes which calculate stresses caused by single-wheel and Engineers, Annual Convention, Exposition and Continuing Educa- multiple-wheel landing gear configurations, soil constitutive models tion Program, San Francisco, Calif, Oct 17-21, 1977) ASCE, which describe the behavior of paving materials, and the nondestruc- Transportation Engineering Journal, vol 104, Sept 1978, p tive pavement-testing equipment Test procedures including load 587-603 5 refs deflection tests, deflection-basin tests, wave propagation tests, and The role of airframe manufacturers in pavement design and surface seismic refraction surveys are outlined Research aimed at the strength ratings is outlined for both the aircraft design phase and development of a mobile testing system is noted S C S during aircraft service life Particular attention is given to flotation techniques specified by the National Aerospace Specification 3601 A78-49678 # Transport Canada airfield pavement load Objectives for future flotation methods are identified S C S evaluation L B R Hunter. G H Argue, and A C Gamble (Canadian Air Transportation Administration, Airports and Con- struction Services Directorate, Ottawa, Canada) (American Society of Civil Engineers, Annual Convention, Exposition and Continuing A78-49684 « # Model of aircraft passenger acceptance I D Education Program, San Francisco, Calif, Oct 17-21, 19771 ASCE, Jacobson (Virginia, University, Charlottesville, Va ) ASCE, Trans- Transportation Engineering Journal, vol 104, Sept 1978, p portation Engineering Journal, vol 104, Sept 1978, p 653-663 10 545-558 7 refs refs Grant No NGR-47-005-181 The paper discusses the airfield pavement load evaluation system A technique developed to evaluate the passenger response to a used by Transport Canada The evaluation data base consists of transportation system environment is described Reactions to mo- construction histories, strength measurements, and structural con- tion, noise, temperature, seating, ventilation, sudden jolts and dition survey reports The load rating system is based on indexing descents are modeled Statistics are presented for the age, sex, aircraft loadings and pavement design bearing strengths on a scale of occupation, and income distributions of the candidates analyzed 1-12 Individual written permission is required for overload oper- Values are noted for the relative importance of system variables such ations S C S as time savings, on-time arrival, convenience, comfort, safety, the ability to read and write, and onboard services S C S A78-49679 # French procedures for airfield pavement load evaluation D Lacroix (Service Technique des Bases Aenennes, Paris, France) (American Society of Civil Engineers, Annual Convention, Exposition and Continuing Education Program, San Francisco, Calif, A78-49693 * Assessment of relative flammability and Oct 17-21, 1977) ASCE, Transportation Engineering Journal, vol thermochemical properties of some thermoplastic materials D A 104, Sept 1978, p 559-574 Kourtides and J A Parker (NASA, Ames Research Center, Moffett Procedures developed by the French Direction Generale de Field, Calif I Polymer Engineering and Science, vol 18, Aug 1978, I'Aviation Civile for evaluating airfield pavement loads are discussed p 855-860 10 refs Testing methods for both flexible and rigid pavements are described The thermochemical and flammability characteristics of some noting load application systems, vertical displacement measurement, typical thermoplastic materials currently in use and others being and horizontal strain measurement The delimitation and character- considered for use in aircraft interiors are described The properties ization of homogeneous zones are reviewed along with observations studied included (1) thermal mechanical properties such as glass of deteriorations S C S transition and melt temperature, (2) changes in polymer enthalpy by differential scanning calonmetry, (3) thermogravimetnc analysis in A78-49680 # Airfield pavement evaluation - The airline an anaerobic and oxidative environment, (4) oxygen index, (5) view C P Weisz (Air Transport Association of America, Washington, smoke evolution, (6) relative toxicity of the volatile products of D C ) (American Society of Civil Engineers, Annual Convention, pyrolysis, and (7) selected physical properties The generic polymers Exposition and Continuing Education Program, San Francisco, Calif, which were evaluated included acrylonitnle-butadiene-styrene, Oct 17-21, 1977) ASCE, Transportation Engineering Journal, vol bisphenol A polycarbonate, bisphenol fluorenone carbonate- 104, Sept 1978, p 575-579 dimethylsiloxane block polymer, phenolphthalem-bisphenol A poly- Procedures for airfield pavement evaluations are considered with carbonate, phenolphthalem polycarbonate, polyether sulfone, poly- reference to growth forecasts in airport capacity It is noted that phenylene oxide, polyphenylene sulfide, polyaryl sulfone, chlori- such evaluations are required to determine the maximum gross load nated polyvmyl chloride homopolymer, polyvinyl fluoride, and permissible for a specific aircraft, to estimate the number of traffic polyvmyhdene fluoride Processing parameters including molding repetitions allowable for a particular type of aircraft, to forecast characteristics of some of the advanced polymers are described Test pavement design life, and to assess the pavement rehabilitation results and relative rankings of some of the flammability, smoke and required for proposed traffic levels Plate bearing tests are described toxicity properties are presented (Author) along with various methods of nondestructive testing S C S

A78-49681 ;/' Airfield pavement evaluation - FAA viewpoint L E Mudd (FAA, Office of Airports Programs, Washington, D C) A78-49708 # Use of ground vibration test equipment to (American Society of Civil Engineers, Annual Convention, Exposi- determine unsteady aerodynamic forces (Utihzzazione dell'attrezza-

526 A78 49769

tura di prove di vibraziorte al suolo per la determinazione detle forze The purpose of the described simulation study of air traffic in aerodmamiche instazionane) L Lecce (Napoli, Universita, Naples, the terminal area is to facilitate the smooth functioning of the Italy) Associations Italians di Aeronautica e Astronautics. Con- terminal when the number of planes seeking entrance to the area gresso Nazionale, 4th, Milan, Italy, Sept 19-23, 1977, Paper 19 p exceeds the capacity of the area The system studied involves n air 14 refs In Italian Consiglio Nazionale delle Rtcerche Contract No routes, with possible nodes of confluence, which lead to a single 115.2648,07,CT-76,00480 runway, input-output, sequencing, hierarchy, spacing, and choice of The described wind tunnel procedure for studying structural and exit gates are considered A mathematical description of the model is sinusoidal vibrations of aircraft and their components uses ground presented, and the associated subroutines are described M L vibration test equipment to determine stability parameters required for the calculation of flutter speed Bidimensional models are used to study the effect of parameters such as the angle of incidence causing A78-49736 Design of a horizontal tail unit and related surface oscillations, oscillation amplitude, and Reynolds number adjustments (Dimensionamento di un impennaggio orizzontale e Extension of the procedure to three-dimensional models is con- degli impianti relativi) L Borello (Torino, Politecnico, Turin, Italy) sidered M L Associazione Italians di Aeronautica e Astronautica, Congresso Nazionale, 4th, Milan, Italy, Sept 19-23, 1977, Paper 22 p In A78-49713 Her mite closed splines L G Napohtano Italian Associazione Italians di Aeronautica e Astronautics, Congresso The paper describes a methodology for determining size Nazionale, 4th, Milan, Italy, Sept 19 23, 1977, Paper 23 p Grant adjustments of a tail unit and related equipment when these No AF-AFOSR-76-2889A components are to be redesigned for incorporation into a given Hermite closed splines, constructed to solve interpolation aircraft Changes required in avionics and control systems are problems related to closed curves, are described These splines are considered Procedures for examining the equilibrium, stability, defined in Hilbert space Proofs of existence and uniqueness are maneuverability, and speed are presented M L presented, and their characteristics are developed in connection with the treatment of a minimization problem formulated in a Hilbert space defined by an arbitrary regular and sufficiently smooth A78-49741 # A method for determining the stability charac- contour M L teristics of aircraft in a hehcoid flight path (Un metodo per la determinazione delle carattenstiche di stabilita dei velivoli su A78-49723 # Choice of cycle for a regenerative bypass traiettone elicoidah) M Capnli, C Casarosa, and R Lazzeretti (Pisa, turbojet for long-range aircraft (Scelta del ciclo del turboreattore a Universita, Pisa, Italy) Associazione Italiana di Aeronautica e doppio flusso con rigeneratore per velivoli a lungo raggio). 0 Astronautica, Congresso Nazionale, 4th, Milan, Italy, Sept 19-23, Scrofam (Palermo, Universita, Palermo, Italy) Associazione Italians 1977, Paper 33 p 8 refs In Italian di Aeronautica e Astronautics, Congresso Nazionale, 4th, Milan, The stability characteristics of an aircraft in a curvilinear flight Italy, Sept 19-23, 1977, Paper 25 p 16 refs In Italian path is represented in differential form, and a theorem on the A thermodynamic and dynamic analysis of a bypass turbojet existence and uniqueness of the solution of such a system for with heat exchange is presented Engine components and the physically acceptable initial conditions is presented The stability of dependence of the specific heats of air and combustion products on the differential system is considered, a nonlinear system of 12 the temperature and air/fuel ratio are taken into account, and the equations is constructed, and an algorithm which does not require effect of cycle parameters on specific fuel consumption and specific the analytic calculation of the Jacobian is proposed The necessary thrust is examined These parameters are considered with respect to and sufficient conditions for stability in a hehcoid flight path are engine weight and aerodynamic drag, and the performance capabili- investigated, and results pertinent to the control of a typical aircraft ties of bypass turbojets with and without heat exchange are are examined M L Compared M L

A78-49744 ij Takeoff performance of STOL aircraft (Sulle prestaziom in decollo dei velivoli da trasporto STOL) C Casarosa A78-49731 # Use of a field bench for testing turbojet (Pisa, Universita, Pisa, Italy) Associazione Italiana di Aeronautica e engines (Utthzzazione di un banco campale per la prova di Astronautica, Congresso Nazionale, 4th, Milan, Italy, Sept 19 23, turbomoton) A Russo.A Colantomo (Aeronautica Militare, Rome, 1977, Paper 23 p 20 refs In Italian Italy), and G Torella (Napoli, Universita, Naples, Italy) Associa- Takeoff procedures for second generation STOL aircraft are iione Italians di Aeronautica e Astronautica, Congresso Nazionale, described and compared Simulation procedures are developed to aid 4th, Milan, Italy. Sept 19-23, 1977, Paper 48 p 7 refs In Italian in the evaluation The recommended procedure involves a critical The paper describes the use of a field test bench for taking decision point defined with relation to the rotation velocity or a measurements of the thermodynamic cycle of aircraft turbojet different velocity parameter STOL and CTOL takeoff maneuvers are engines The guiding concept in selecting the instrumentation was to contrasted M L use a minimum of sensors without sacrificing measurement accuracy and reliability Two attached sensors were used, consisting of two thermocouples, of which one furnished data on the static temperature downstream of the compressor and the second measured the A78-49769 # 'Supermarket' airplanes R J Linn (American static temperature downstream of the turbine The test bench, Airlines, Inc. New York, NY) American Institute of Aeronautics sensor, and other instrumentation are described, and the method of and Astronautics, Conference on Air Transportation Technical determining the cycle from the measurements is explained P T H Perspectives and Forecasts, Los Angeles, Calif, Aug 21-24, 1978, Paper 78-1533 6p New fleets will be required to meet the noise, old-age and economic problems facing most of the air transportation industry A78-49733 # Air traffic control in the terminal area - Use of American Airlines is in the process of analyzing the numerous new a simulation technique for the definition of an operative model (La aircraft and engine designs being offered by the manufacturers to gestione ATC in area term male - Impiego delle tecniche di Simula- meet future fleet requirements The present paper covers some of the ziorte per la definizione di un modello operativo) L Balis-Crema and methodology American is using m its analysis for choosing future C Bottighen (Roma, Universita, Rome, Italy) Associazione Italians fleet types Evaluation objectives (eg, 707 replacement, 727-100 di Aeronautica e Astronautica, Congresso Nazionale, 4th, Milan, replacement, and future market requirements) are discussed with Italy, Sept 19-23, 1977, Paper 13 p 5 refs In Italian Consiglio reference to operating costs, engines and fuel consumption, and Nazionale delle Ricerche Contract No 77,01087,91,115,9694 engine rating B J

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A78-49770 # Operations and economics of U S air transpor- (Grumman Aerospace Corp , Bethpage, N Y ) American Institute of tation J M Swihart and J I Minmck (Boeing Commercial Airplane Aeronautics and Astronautics, Aircraft Systems and Technology Co , Seattle, Wash ) American Institute of Aeronautics and Astro- Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1452 nautics, Conference on Air Transportation Technical Perspectives 14 p 9 refs and Forecasts, Los Angeles, Calif, Aug 21-24, 1978, Paper 78-1545 The present paper reviews the preliminary design of an advanced 9p supersonic cruise strike-fighter configuration and compares early Operational trends indicate that the U S air transportation wind tunnel data with pre-test predictions and ultimate technology service network is adequate and that the rapid development of the goals The paper goes on to describe how these results and continued system may be over More efficient equipment, improved fleet mixes, configuration studies were factored into the aircraft design evolution higher seating densities, and higher load factors will be required to for improved performance Specific material covered will include hold down increases in airline operating costs caused by inflationary baseline configuration selection, packaging, and supersonic area- and environmental pressures Higher unit operating costs will require ruling, variable twist/variable camber wing design using 2D and 3D increases in unit revenues to provide operating profit in an era of air transonic computer codes and comparison with wind tunnel force, transportation which the author calls 'the ear of the bottom line' moment, and pressure data, propulsion-airframe integration effects BJ for several inlet and nozzle configurations, and an appraisal of the maneuvering performance compared to current state-of-the art capabilities (Author)

A78-49771 # Piloted flight simulation for active control A78-49784 # Prospects for commercial commonality in mili- design development D M Urie (Lockheed-California Co , Burbank, tary transports E A Barber, R J Marhefka, and D G Blattner Calif ) American Institute of Aeronautics and Astronautics, Confer- (Boeing Aerospace Co, Seattle, Wash ) American Institute of ence on Air Transportation Technical Perspectives and Forecasts, Aeronautics and Astronautics, Aircraft Systems and Technology Los Angeles, Calif, Aug 21-24, 1978, Paper 78-1553 10 p Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper 78 1467 This paper reviews experience with piloted flight simulation in 21 p current transport development citing the L-1011 yaw SAS and Direct A description is presented of work conducted in connection Lift Control Recent simulation studies of a relaxed static stability with the Innovative Aircraft Design Study (IADS-77) which was version of the L-1011 are discussed, as are tests using the vehicle concerned with an examination of the prospects for commercial systems simulator with pilot-m-the-loop to verify handling qualities commonality in military transports IADS-77 is an extension of a effects of active load alleviation The role of flight simulator data in previous study. Innovative Aircraft Design Study, Task II lADS-Task determining augmentation system reliability criteria are explored II was oriented toward studying the size effects of logistic transports Continued utility of piloted simulation for predicting certificabihty The viability of commercial commonality was also investigated with of flying qualities which depend on subjective evaluation are the express purpose of assessing the feasibility of the C-XX concept considered Limitations of current equipment for future needs are as proposed by the Military Airlift Command The IADS-77 discussed along with recommendations for simulator planning objectives included evaluating the validity of commercial commonal- (Author) ity as related to aircraft design, determining the impact of technology on commercial commonality, evaluating the applicability of transport design to alternative military missions, and evaluating the A78-49781 * ff A laser-powered flight transportation system military use of a minimum-size outsize design G R A Hertzberg, K C Sun (Washington, University, Seattle, Wash ), and W S Jones (Lockheed Missiles and Space Co, Inc. Palo Alto, Calif) American Institute of Aeronautics and Astronautics, Aircraft A78-49786 # Wing planforms for large military transports Systems and Technology Conference, Los Angeles, Calif, Aug C E Jobe (USAF, Flight Dynamics Laboratory, Wright-Patterson 21-23, 1978, Paper 78-1484 31 p 28 refs Grant No AFB, Ohio), R M Kulfan, and J D Vachal (Boeing Commercial IMG L-49-002-044 Airplane Co , Seattle, Wash ) American Institute of Aeronautics and Laser energy transmitted from a solar power satellite via a set of Astronautics, Aircraft Systems and Technology Conference, Los relay satellites is used to power a cruising air transport, i e , a Angeles, Calif, Aug 21 23, 1978, Paper 78 1470 17 p 8 refs laser-powered airplane The result is a nearly fuelless pollution-free Transport aircraft, designed for long-range military missions flight transportation system which is cost competitive with the with heavy payloads, lead to wings with high aspect ratios and very fuel-conservative airplane of the future The major components of large spans A wing geometry/cruise speed optimization study was this flight system include a laser-power satellite, relay satellites, made of a large cantilever wing military transport airplane Prelimi- laser powered turbofans, and a conventional airframe The relay nary design and performance evaluations were also made of a satellites are orbitiflg optical systems which intercept the beam from strut-braced wing airplane Initial results obtained with statistical a power satellite and refocus and redirect the beam to its next target weights indicated small performance advantages for the cantilever ' " (Author) wing design Subsequent results obtained with weights derived from detailed analytical structural analyses reversed the initial conclusions A78-49782 ff Technology analysis - Candidate advanced These results indicated that unusual alternative configuration con- tactical fighters R W Bratt and E W Johnston (Northrop Corp , cepts cannot be discarded, based on small differences predicted Aircraft Group, Hawthorne, Calif) American Institute of Aero- during conceptual design studies (Author) nautics and Astronautics, Aircraft Systems and Technology Confer- ence, Los Angeles, Calif, Aug 21-23, 1978, Paper 78-1451 8p Technology requirements were evaluated for candidate advanced tactical fighters, with evaluation factors including aircraft buy for A78-49787 * # A method for localizing wing flow separation fixed life cycle costs, sorties and costs to kill specific targets, and at stall to alleviate spin entry tendencies T W Feistel, S B weapons and aircraft unit costs Survivabihty, effectiveness, and cost Anderson (NASA, Ames Research Center, Moffett Field, Calif), and were evaluated separately For a representative aircraft weapon R A Kroeger (Michigan, University, Ann Arbor, Mich ) American system, the advanced high leverage technologies were identified as Institute of Aeronautics and Astronautics, Aircraft Systems and composite structure, reduced observables, conformal weapons car Technology Conference, Los Angeles, Calif, Aug 21-23, 1978, Paper riage, advanced engines, target acquisition, and detection and 78-1476 8p recognition systems. B J A wing leading-edge modification has been developed, applicable at present to single-engine light aircraft, which produces stabilizing A78-49783 ff Design evolution of a supersonic cruise strike- vortices at stall and beyond These vortices have the effect of fixing fighter R H Hendnckson, R L Grossman, and A S Sclafani the stall pattern of the wing such that the various portions of the

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wing upper surface stall nearly symmetrically The lift coefficient A78-49792 H Unsteady hypersonic gas flow past a thin wing produced is essentially constant to very high angles of attack above of finite span (Nestatsionarnoe obtekame tonkogo kryla konechnogo the stall angle of the unmodified wing It is hypothesized that these razmakha giperzvukovym potokom gaza) V T Bogatko, A A Grib, characteristics will help prevent inadvertent spin entry after a stall and G A Kolton (Lemngradskn Gosudarstvennyi Universitet, Results are presented from recent large-scale wind-tunnel tests of a Leningrad, USSR) Akademiia Nauk SSSR, Doklady, vol 240, June complete light aircraft, both with and without the modification 11,1978, p 1040,1041 In Russian (Author) The problem of the unsteady uniform hypersonic flow of an ideal gas past the windward side of a finite-span thin wing at constant angle of attack is examined It is assumed that the shape of the wing A78-49788 # The influence of propulsion and control sys- surface depends on time The thin-shock-layer method is used to find tem concepts on design of a Navy Type A V/STOL airplane J M a solution BJ Zabmsky (Boeing Military Airplane Development, Seattle, Wash ) American Institute of Aeronautics and Astronautics, Aircraft Sys- tems and Technology Conference, Los Angeles, Calif, Aug 21 23, A78-49837 Minimum weight design of stiffened panels 1978, Paper 78-1505 7 p 14 refs with fracture constraints M W Dobbs and R B Nelson (California, Airplane designs for Navy Type A V/STOL are constrained by University, Los Angeles, Calif) Computers and Structures, vol 8, the integration of the aerodynamic and propulsion systems The June 1978, p 753-759 22 refs Grant No AF-AFOSR-74-2460A propulsion/control system has a ma|or effect on the airplane An efficient optimahty criteria method is presented for the concept Airplanes with various arrangements and number of lift and automated minimum-weight design of structural components for lift cruise fans and several means of providing low speed flight which analytical solutions for developed stress intensity factors are control were examined Operational systems and requirements added not available The inclusion of fracture constraints in the automated further constraints The resulting designs are presented and discussed, design process is a logical extension of present structural optimiza- but selection of a concept is not made (Author) tion methods which include stress, displacement, buckling, frequency and aeroelastic flutter constraints The finite element method is used for stress analysis, while the strain energy release method (the compliance method) is employed to calculate developed opening A78-49789 # Ground effects testing of two, three, and four mode stress intensity factors Only two structural analyses are jet configurations H E Sherneb (Vought Corp, Dallas, Tex) needed at each design iteration to calculate the necessary response American Institute of Aeronautics and Astronautics, Aircraft Sys- gradient information and the developed stress intensity factor The tems and Technology Conference, Los Angeles, Calif, Aug 21-23, structure is iteratively resized to satisfy the Kuhn-Tucker necessary 1978, Paper 78-1510 7 p 5 refs conditions for a local optimum design The design of a flat stiffened Ground effects of V/STOL aircraft are dependent on the panel approximating an aircraft fuselage panel is presented S D number and arrangement of the propulsive flows Extensive tests of a generalized powered model have parametrically measured suckdown, buoyant fountain effects, and remgestion as a function of height A78-49850 # Aviation control system devices (Aviatsionnye above the ground The number and location of the propulsion pribory upravliaiushchikh sistem) V G Vorob'ev and I K simulators were varied to represent two-, three-, and four-fan Kadyshev Moscow, Izdatel'stvo Transport, 1978 160 p 17 refs In configurations Two nacelle-mounted ejectors at the aircraft CG Russian represented the two-fan arrangement, a nose fan and two nacelle- The principles of operation, design, and error analysis of the mounted fans gave the three-poster arrangement, and two electors mam types of control systems used in aircraft navigation and piloting ganged in tandem m nacelles represented the four-fan configuration are studied On the basis of an analysis of the complex of parameters Comparisons of the test results show that the four-poster config- characterizing the position of the aircraft in space at all stages of uration is buoyant near the ground The effects of thrust magnitude flight, a classification of the onboard control equipment ensuring and direction, differential thrust, aircraft attitude with respect to the automatic piloting is given The functional blocks are analyzed for ground, and fountain control devices on the underside of the fuselage gyroscopic devices, navigational equipment of the membrane-aneroid are identified Several means of reducing remgestion, such as nozzle group, angular sensors of velocity and acceleration, roll and pitch position, wing location, canting the thrust direction, and inlet sensors, course sensors and systems, altitude sensors, flight speed shielding, are compared (Author) sensors, angle-of-attack sensors, angle-of-slip sensors, and air signal systems P T H

A78-49790 * # V/STOL aircraft simulation • Requirements and capabilities at Ames Research Center D E Wilcox and H C Quigley (NASA. Ames Research Center, Moffett Field. Calif) A78-49851 NAECON '78, Proceedings of the National American Institute of Aeronautics and Astronautics, Aircraft Sys- Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, tems and Technology Conference, Los Angeles, Calif, Aug 21-23, 1978 Volumes 1, 2 & 3 Conference sponsored by the Institute of 1978, Paper 78-1515 12 p Electrical and Electronics Engineers New York, Institute of Elec- Ground-based flight simulation contributes greatly to the trical and Electronics Engineers, Inc. 1978 Vol 1, 492 p, vol 2, development of new aircraft and flight management systems and will 501 p, vol 3, 419 p Price of three volumes, members, S22 50, be especially important in improving the performance, safety, and nonmembers, S30 environmental characteristics of future civil and military V/STOL aircraft This paper describes existing simulation facilities at Ames The topics considered are related to navigation systems design, Research Center and discusses their capabilities and limitations for Navstar GPS-1, flight control, advanced digital system architectures, V/STOL aircraft investigations Simulation requirements for NASA improved electronic reliability through packaging and interconnec- research and support of DOD programs are also discussed, including tions, fire control technology, software engineering technology, technology development for advanced rotorcraft and civil and software support and performance monitoring tools, the manage- military V/STOL aircraft Current efforts and future plans are ment of engineering, Navstar GPS-II, sensor and signal processing, described for the upgrading of Ames simulation facilities to meet communication techniques for jamming resistance, technology in those requirements Recent advances in equipment technology and medicine, tactical guided weapon systems, avionics software support operational methodology are shown to provide significantly im systems, system design and integration, laser gyro technology, proved simulation fidelity through better motion and visual cues and microcomputer technology, electrical insulation in airborne equip- faster system response to pilot inputs (Author) ment, lightning and EMP considerations in airborne equipment,

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airborne laser systems, and tactical guided weapon technology including the Space System Segment, the Control System Segment, Attention is also given to the software executive, aerospace power and the User System Segment The operational GPS will deploy system developments, mertial technology, aerospace computer fami- twenty-four equally spaced satellites m three planes with near lies, data communication systems, energy conservation technology, circular 10,890 nautical-mile orbits inclined at approximately 63 pointing and tracking, higher order language status, power condition- degrees and having a twelve hour period A description is presented ing electronics, navigation, cost estimating methodology, communi- of field tests of GPS user equipment which are currently being cation system components, airborne radar, software standardization, conducted Attention is given to the field test concept, the history of automatic test equipment software, airborne infrared receiver sys- the GPS test program, navigational errors, pseudorange errors, and tems, Kalman filtering applications, avionics design for testability, aspects of system applications G R strategic guided weapons, topics in software acquisition management, and environmental factors on airborne electronic design G R A78-49857 Comparisons of high anti-jam design techniques for GPS receivers H L Jones and T J Macdonald (Analytic A78-49852 Modular Missionization Systems /MMS/, an Sciences Corp , Reading, Mass) In NAECON '78, Proceedings of adaptive system interface concept E L Cloud and K C Leonard, the National Aerospace and Electronics Conference, Dayton, Ohio, Jr (Westinghouse Electric Corp, Systems Development Div , Balti- May 16-18, 1978 Volume 1 New York, more, Md ) In NAECON '78, Proceedings of the National Aero- Institute of Electrical and Electronics Engineers, Inc, 1978, p space and Electronics Conference, Dayton, Ohio, May 16-18, 1978 39-46 7 refs Volume 1 New York, Institute of Electrical and The spread spectrum Global Positioning System (GPS) signal Electronics Engineers, Inc, 1978, p 2-12 5 refs Contract No structure provides inherent jammer tolerance for potential GPS users N00140-77-C-0105 Nevertheless potential jamming by CW or broadband noise jammers Operationally, the Modular Missionized Systems (MWIS) concept is still an important design issue for GPS receivers because of the low promises avionics reconfiguration on a sortie-to-sortie basis A power of the received GPS signal A description is presented of description is presented of a laboratory experiment which had the techniques for improving the tolerance of GPS receivers to such objective to demonstrate the flexibility of the MMS concept Three jammers by using advanced baseband processing techniques Atten- representative sensors were integrated Each unit could be connected tion is given to basic receiver structures, mertial navigation system alternatively or in any combination to the cockpit station This was (INS) velocity aiding, adaptive bandwidth designs, and external data accomplished through a distributed digital architecture, using stan- aiding When used in conjunction with INS velocity aiding, the dard hardware interfaces, with software that detected which sensors adaptive frequency tracker outperforms the adaptive phase tracker were connected, then automatically executed those instructions but suffers in certain applications from its inability to decode the appropriate to their integration The primary findings from the data G R investigation are that sensor technology advances can be accommodated easily in MMS configured vehicles The concept will allow off-line development of sensors, subsystems, or fully integrated vehicle weapons systems Attention is given to hardware considera- A78-49858 * A Costas loop with tangent error signal for use tions, communications between main and micro computers, soft- in Navstar GPS avionics. J H Painter, D A McClung, and R C ware, questions of practicality, and potential application G R Remmger (Texas A & M University, College Station, Tex ) In NAECON '78, Proceedings of the National Aerospace and Elec- tronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 1 New York, Institute of Electrical and Electronics A78-49855 Pattern recognition as an aid to radar naviga- Engineers, Inc , 1978, p 47-54 5 refs Grant No NsG-1374 tion A M Savol and A J Witsmeer (Boeing Aerospace Co , Seattle, This paper describes an augmented Costas loop for use in Wash ) In NAECON '78, Proceedings of the National Aerospace and low-cost avionics for the Navstar Global Positioning System A Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 1 standard loop has been augmented with supplementing feed-back to New York, Institute of Electrical and Electronics give a tracking error voltage proportional to the tangent of the phase Engineers, Inc, 1978, p 26-32 11 refs Research supported by the error, rather than to the sine The augmented loop yields increased Boeing Aerospace Co performance in the presence of input phase acceleration and jerk, as Problems of radar navigation in connection with weather caused by maneuvers of the GPS user vehicle Many Monte Carlo conditions, the unpredictability of radar reflections, high aircraft simulation results are given (Author) speeds, and low altitude penetration procedures make it very difficult for radar navigators in strategic bombers to perform their assigned tasks Research has, therefore, been conducted with the objective to develop computer-based techniques which assist the A78-49859 A compensation technique for acceleration- navigator with his landmark navigation task Preliminary algorithms induced frequency changes in crystal oscillators J M Przyjemski considered have the dual goals of enhancing the image and extracting (Charles Stark Draper Laboratory, Inc, Cambridge, Mass) In information useful for machine processing The reported investiga- NAECON '78, Proceedings of the National Aerospace and Elec- tion establishes the viability of pattern recognition as a research area tronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 1 with the potential for aiding the navigator in landmark recognition New York, Institute of Electrical and Electronics Aspects of computerized pattern recognition are discussed, taking Engineers, Inc , 1978, p 55-60 Contract No F33615-75-C-1H9 AF into account images, local edge detection, line growing, and feature Project 6095 extraction and classification G R The tracking performance of Global Positioning System (GPS) navigation receivers aboard tactical aircraft is limited by frequency A78-49856 # Navstar GPS field test results D A Lorenzim variations m crystal reference oscillators, resulting from resonator and R P Denaro (USAF, Space and Missile Systems Organization, sensitivity to acceleration A requirement exists in this connection Los Angeles, Calif) In NAECON '78, Proceedings of the National for a crystal reference oscillator that is less sensitive to acceleration Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, The requirements and characteristics of the g-sensitivity of a crystal 1978 Volume 1 New York, Institute of oscillator are discussed and a description is provided of a compensa- Electrical and Electronics Engineers, Inc, 1978, p 34-38 tion technique which is based on a simple model of g-sensitivity It is The Navstar Global Positioning System (GPS) is a space-based shown that a relatively low-cost single-axis accelerometer in conjunc- radio navigation system that will provide highly accurate position, tion with the considered model can be employed to decrease the velocity, and time to suitably equipped users located anywhere on or effects of acceleration by one, and possibly two, orders of near the earth The GPS is composed of three major segments. magnitude G R

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A78-49860 In-line monitoring of digital flight control York, Institute of Electrical and Electronics Engineers, Inc , 1978, p computers T F Westermeier (McDonnell Aircraft Co, St Louis, 83-90 9 refs Mo) In NAECON'78, Proceedings of the National Aerospace and The AFFDL/DAIS program is developing a flight engineering Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 1 facility to simulate aircraft flight control systems and avionics New York, Institute of Electrical and Electronics interfaces, using DAIS core elements and MIL-STD-1553A data Engineers, Inc , 1978, p 62-69 8 refs buses Because of practical problems in synchronizing redundant The ability of a digital fly-by-wire (FBW) system to maintain systems, the four redundant flight control channels, which consist of undegraded performance when a failure occurs in either of two computers and interface hardware (as typical of a system that might channels depends on the efficacy of in-line monitoring techniques be required for a digital fly-by-wire aircraft) are asynchronous This applied to the various systems elements Especially, the ability paper analyzes a few selected problems encountered in integrating depends on computer self-test, since the computer is frequently the such an asynchronous system performance corruption due to weakest link in the reliability chain, and also because the computer is asynchronous command updates and effect on failure detection, time used to in-line monitor other system elements The subject of delays involved in data exchange and mode engagement logic, computer self-test is introduced by reviewing certain fundamentals possibly as large as 3/8 of a second, and difficulties in avoiding relating to redundancy management and showing the significant potential single point failures with interdependent asynchronous system benefits that accrue through a reduced redundancy level channels (Author) Quantitative data is introduced to show the in-line monitoring coverage needed to achieve acceptable system reliability The A78-49864 Synthesis of digital flight control systems by relationship between in-line monitoring coverage and CP jiiter the method of entire eigenstructure assignment J J D'Azzo (USAF, self-test coverage is presented G R Institute of Technology, Wright-Patterson AFB, Ohio) and B Porter A78-49861 Laboratory testing of lightning and EMP sus- (Salford, University, Salford, England) In NAECON '78, Proceed- ings of the National Aerospace and Electronics Conference, Dayton, ceptibility of avionic systems G L Graves (Honeywell, Inc, Ohio, May 16-18, 1978 Volume 1 New York, Avionics Div , Minneapolis, Minn) and L Andersson (Saab-Scama Institute of Electrical and Electronics Engineers, Inc, 1978, p AB, Aerospace Div, Lmkoping, Sweden) In NAECON'78, Proceed- 91-99 21 refs Grant No AF-AFOSR-76-3005A ings of the National Aerospace and Electronics Conference, Dayton, For a full utilization of the capability of digital controllers, it is Ohio, May 16-18, 1978 Volume 1 New York, Institute of Electrical and Electronics Engineers, Inc, 1978, p essential that a powerful method be available for the design of 70-73 regulators for controllable and observable linear multivanable sam- In connection with the flight criticality of fly-by-wire (FBW) pled-data systems governed by state and output equations of flight control systems in aircraft, attention is now focused on the appropriate forms The method of entire eigenstructure assignment immunity of these systems to electrical hazards such as lightning reported by Moore (1976) and Porter and D'Azzo (1977) constitutes strikes A demonstrated total immunity is an absolute necessity such a method for the design of regulators governed by state- regardless of the redundancy level of the system An investigation has feedback control laws of the form u(kT) = Kx(kT) which assigns in this connection been conducted including the collection and both the eigenvalues and eigenvectors to the plant matrix of the review of all published data and literature on aircraft lightning strike resulting closed-loop system governed by the considered equations effects and test programs involving flight control systems Two major The method of entire eigenstructure assignment is illustrated by airframe test programs directed toward flight control hardware were designing a range of digital regulators for the lateral dynamics of the also reviewed On the basis of the investigation it was concluded that F-4 aircraft such that the controlled system exhibits fast settling a system or device should be subjected to an environmental characteristics while requiring only acceptably small control surface condition equivalent to that seen within an airframe when struck by deflections G R lightning This environmental condition must be duplicated in a laboratory test facility under controlled conditions and should be A78-49865 Comparison monitoring in redundant digital performed as a follow-on to EMI qualification testing Approaches flight control systems C Shvmsky and W Shoemaker (Missouri- used for implementing these requirements are discussed and the Columbia, University, Columbia, Mo) In NAECON '78, Pro- obtained test results are considered G R ceedings of the National Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 1 New York, Institute of Electrical and Electronics Engineers, Inc , 1978, p 100-106 8 refs Grant No AF-AFOSR-76-2968 The presented results are applicable to the analysis of tri- and A78-49862 ft The terrain following task for the advanced quad-redundant signals that change one at a time, but in random tactical fighter using discrete optimal control R L Simmons, M j order Particular attention is given to results applicable to the Breza, and J E Funk (USAF, Aeronautical Systems Div, Wright- monitoring process The set of binary relationships among the signals Patterson AFB, Ohio) In NAECON '78, Proceedings of the National is characterized by using seven keys that are useful for showing the Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, evolution of signal patterns as the signal states change A monitoring 1978 Volume 1 New York, Institute of algorithm based on the above characterization is developed and its Electrical and Electronics Engineers, me, 1978, p 74-82 implementation in software is given Simulation studies verify the Through the use of state space, continuous optimal control, and capabilities of the algorithm A description is presented of a means discrete optimal control, a digital flight control system was designed for characterizing all possible relationships among quad- or tri- for the terrain following task A sample rate of five hertz was shown redundant signals subjected to a monitoring scheme that uses a to be high enough to adequately form the desired controls The binary test for deciding whether two signals are within tolerance of aircraft was shown to track the desired path in a highly acceptable each other G R manner through the use of a hybrid simulation The design method utilized is recommended for consideration in designing the digital control laws for other flight control tasks (Author) A78-49866 MIL-STD-1553B proposed W A Crossgrove (Boeing Aerospace Co , Seattle, Wash ) In NAECON '78, Pro- ceedings of the National Aerospace and Electronics Conference, A78-49863 # A qualitative analysis of redundant asyn- Dayton, Ohio, May 16-18, 1978 Volume 1 New chronous operation T W Johnson (USAF, Flight Dynamics York, Institute of Electrical and Electronics Engineers, Inc , 1978, p Laboratory, Wright-Patterson AFB, Ohio) In NAECON '78, Pro- 108-120 ceedings of the National Aerospace and Electronics Conference, The Air Force military standard, MIL-STD-1553, was developed Dayton, Ohio, May 16-18, 1978 Volume 1 New in August 1973 With the production of the F-16, MIL-STD-1553

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found its first full aircraft application During late 1974 and early investigation in which multiprocessing is developed around bus 1975 the DOD directed the military to develop a single position and interfacing because of its relative simplicity and flexibility Problems made the necessary revisions to the present standard From this of task management are discussed, taking into account tasks with the effort MIL-STD-1553A was released in April 1975 Since that time, largest input buffer, tasks nearest the system input, and tasks nearest industry and the military have continued to coordinate on the the system output Attention is also given to problems of task standard through symposia, studies, and military development partitioning and an electronic warfare processing model G R programs As applications became extensive, certain difficulties were recognized in the standard In connection with these difficulties an SAE task group, MIL-STD-1553 Update was formed in October A78-49872 Non-volatile memory system for severe en- 1976 The task group's assignment was to develop suggested changes vironment flight recorders J H Trageser (Technology, Inc , Dayton, to the present MIL-STD-1553A In October 1977, after review and Ohio) In NAECON '78, Proceedings of the National Aerospace and changes, the SAE-A2K approved the proposed MIL-STD-15538 The Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 1 proposed improvements are examined G R New York, Institute of Electrical and Electronics Engineers, Inc , 1978, p 158-163 A78-49867 Application of the General Purpose Multiplex An intensive m-house study was undertaken to select the most System to the A-7E avionics J L Jones, J R Perkins (Vought cost-effective state-of-the-art technology to implement a high-perfor- Corp, Dallas, Tex), H Brown, and E Kee (US Naval Material mance nonvolatile memory system for use in microprocessor- Command, Naval Air Development Center, Warmmster, Pa ) In controlled military flight recorders Emphasis was placed on mini- NAECON '78, Proceedings of the National Aerospace and Elec- mum size and weight with proven ability to function reliably under tronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 1 the environmental requirements for Class 2 equipment as defined by / New York, Institute of Electrical and Electronics MIL-E-5400 Candidate technologies included Magnetic Core, Bub- Engineers, Inc , 1978, p 122-128 ble, MNOS, NMOS and CMOS To provide nonvolatility for A summary is presented of the results of a study conducted for semiconductor memories the study included a review of current the Navy which encompassed three primary areas of investigations, battery technology applicable to the subject requirement CMOS development of a signal data base, establishing a General Purpose RAMs combined with lithium solid-state batteries are shown to be a Multiplex System (GPMS) architecture for fulfilling the A-7E reliable, cost effective alternate to core memory with an order of requirements, and determining the impact of applying the GMPS to magnitude reduction in weight and size (Author) advanced avionic systems The data base study defined the A-7E aircraft and avionic subsystem information required to establish the GPMS architecture Attention is given to the A-7E general purpose A78-49874 Interface design considerations for F-16 sen- multiplex system, the avionics equipment with integral data ter- sors and weapons J D Watts and T G Cheatum (General Dynamics minals, multiplexed signals, and advanced aircraft applications The Corp, Fort Worth, Tex) In NAECON '78, Proceedings of the conclusions from the study are discussed, taking into account National Aerospace and Electronics Conference, Dayton, Ohio, May protocol, data bus, data rate, the integral data terminal, area 16-18, 1978 Volume 1 New York, Institute of multiplex terminals, and control group terminals G R Electrical and Electronics Engineers, Inc, 1978, p 172-176 The F-16 avionics system examined in the present paper has been designed for flexibility and growth New systems, sensors, and A78-49868 A hierarchical network for avionic systems J weapons can be accommodated without the normal proliferation of A Edwards and F Hubans, Jr (General Dynamics Corp, Fort black boxes The system is partitioned into logical functional groups Worth, Tex ) In NAECON '78 Proceedings of the National with standard interfaces The fire control computer is the integrating Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, element that ties the subsystems together Sensor computations 1978 Volume 1 New York, Institute of relating to sensor control and data processing are accomplished Electrical and Electronics Engineers, Inc, 1978, p 129-136 11 refs within each sensor subsystem The result is a design which will A hierarchical network considered in connection with a study of guarantee the F-16 as a highly effective air-to-air and air-to-surface advanced avionic system concepts can provide a means of easily weapon system V P tailoring the system hardware to the system requirements, i e, performance, reliability, growth, and cost A description is presented of the evolution of the hierarchical system from early avionics, the benefits obtained from employing such a system, the requirements A78-49875 Software structured weapon delivery L L this system places upon system partitioning and system control, and Crews (Intermetrics, Inc, Cambridge, Mass) In NAECON '78, a network implementation philosophy It is pointed out that the Proceedings of the National Aerospace and Electronics Conference, main issue in a distributed network is controllability The hierarchi- Dayton, Ohio, May 16-18, 1978 Volume 1 v New cal architecture has evolved from previous avionic configurations to York, Institute of Electrical and Electronics Engineers, Inc , 1978, p provide a structure which improves both the system controllability 177-182 and the system extensibility Additional improvements, however, are This paper deals with the air-to-ground weapon delivery OFP for needed in the areas of communication protocol and the interconnect an attack aircraft The program uses top-down structured program- methodology G R ming and has been block-structured for ease in adding new weapons or new sensors for ranging This program will be used in the Air A78-49869 Multiprocessing for electronic warfare Force DAIS system and will be used in the AN/AYK-15 with the Mil avionics. C Wise, R Koppelman, R Higgmbotham, and D Wiles Std 1553-ABus Using top-down structured programming techniques (Westmghouse Electric Corp, Baltimore, Md ) In NAECON '78, allows the user to add and eliminate blocks very easily and to also Proceedings of the National Aerospace and Electronics Conference, transfer select routines that are already debugged from one system to Dayton, Ohio, May 16-18, 1978 Volume 1 New another The program is currently programmed in JOVIAL J73/I York, Institute of Electrical and Electronics Engineers, Inc , 1978, p (Author) 137-141 A key question arising in connection with the employment of microprocessor technology is related to the type of processing architecture which will evolve Multiprocessing provides an architecture which offers many advantages Key technical problems con- A78-49876 Peace Rhine - A digital Weapon Control fronting it are related to additional considerations concerning System for the F-4 aircraft E H Thompson and E W Beaver mterprocessor communications and decisions regarding the allocation (Westmghouse Electric Corp, Baltimore, Md ) In NAECON '78, of tasks to an individual processor A description is presented of an Proceedings of the National Aerospace and Electronics Conference,

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Dayton, Ohio, May 16-18, 1978 Volume 1 ' ; New (Ga ) Air Logistics Center (WR ALC) This simulation is an element York, Institute of Electrical and Electronics Engineers, Inc , 1978, p of the overall F-15 Avionics Integrated Support Facility being 183-191 10refs Contract No F33657-77-C-0189 developed as a depot capability in support of the F-15 Subsystems The Peace Rhine Weapon Control System (WCS), currently verification is addressed by this paper since verification of the being developed for the F-4F Aircraft, is described with emphasis on simulation system as a whole will be minimally contingent on fire control methodology and performance Unique mechanizations acceptance of the component subsystems (Author) are described for the employment of present-day missiles and fixed, forward-firing guns against maneuverable A/A threats The computed launch envelopes of both Sparrow and Sidewinder Missiles are A78-49902 The role of system performance analysis in the enclosed by both the permissible lead/lag angle boundaries and the independent assessment of B-1 navigation software T E Shirley, W permissible range separation from the target Performance design F Stabenau (Logicon, Inc , Dayton, Ohio), and M M Freed (USAF, goals of less than 20% missed opportunities and 15% out-of- Aeronautical Systems Div, Wright-Patterson AFB, Ohio) In boundary launches have been achieved using the AIM-7F Missile NAECON '78, Proceedings of the National Aerospace and Electron- Flight test results also established a 10 mrad CEP in aided visual ics Conference, Dayton, Ohio, May 16-18, 1978 Volume 1 delivery of conventional A/G ordnances and an aiming accuracy of 8 New York, Institute of Electrical and Electronics mrad (CEP) utilizing the director gunnery mechanization (Author) Engineers, Inc, 1978, p 434-440 Contract No F33657 77-C 0004 The role of systems performance analysis during the independent assessment of B-1 navigation software is described Two flexible analysis techniques, functional system/software simulation and A78-49897 Scan-limited near field testing for directive covanance analysis, are shown to be useful in independent software airborne antennas K R Grimm (USAF, Avionics Laboratory, evaluations Concrete examples of their use to support Air Force Wright-Patterson AFB, Ohio) and B Schmidt (Dayton, University, management during B-1 development are given These examples Dayton, Ohio) In NAECON '78, Proceedings of the National include baseline performance evaluations, the evaluation of the Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, impact upon system performance due to changes in avionics 1978 Volume 1 New York, Institute of equipment, and the diagnosis of problems encountered during flight Electrical and Electronics Engineers, Inc , 1978, p 360-367 7 refs test These examples provide evidence that system performance Methods are introduced for estimating the nonsampled near analysis is an integral part of independent software assessment and field (IMF) in antenna test applications when the physical size of the increases Air Force management effectiveness (Author) antenna is larger than the available planar scanner With the aid of a polynomial perturbation approach it is attempted to match a A78-49903 # Digital avionics support - A retrospective view least-mean-square fit for a complete NF data set at selected match of the future M van den Broek and N J Babiak (USAF, Logistics points of a scan-limited set The forced match is achieved by random Command, Wright-Patterson AFB, Ohio) In NAECON '78, Proceed- perturbations of the unique recursion coefficients of the complete ings of the National Aerospace and Electronics Conference, Dayton, set fit, and is guided by imposing tolerances on the match and the Ohio, May 16-18, 1978 Volume 1 New York, number of match points Attention is given to planar near field Institute of Electrical and Electronics Engineers, Inc, 1978, p probing, scan-limited testing, the processing of scan-limited data, 442-448 power extrapolation, extrapolation by endpomt constraint, and The introduction and increasing utilization of digital technology extrapolation by polynomial perturbation G R in Air Force weapons systems has considerably enhanced operational capability, system flexibility, and hardware reliability There have, A78-49900 Approach for identifying avionics flight soft- however, been difficulties related to the way in which digital ware operational support requirements - PAVE TACK an example technology was approached What appears to be lacking is a single H A Montgomery (TRW Defense and Space Systems Group, focal point which will blend the efforts of academia, research, Redondo Beach, Calif) and R L Turk (USAF, Warner Robins Air development, user, and supporter into a unified whole The reported Logistics Center, Robins AFB, Ga ) In NAECON '78, Proceedings investigation has the objective to demonstrate that such a focal point of the National Aerospace and Electronics Conference, Dayton, would result in significant support improvements while simul- Ohio, May 16-18, 1978 Volume 1 ' New York, taneously enhancing operational capabilities It is shown that the Institute of Electrical and Electronics Engineers, Inc, 1978, p first stages of such a capability are now developing in the form of 418-425 5 refs Avionics Integration Support Facilities throughout the Air Force An approach is presented for identifying the types of tools Logistics Command G R required by the Air Force Logistics Command (AFLC) to support an avionics flight program over its operational life This approach A78-49904 Comparison study of MLS airborne signal involves an analysis of the avionics system with respect to the phases processing techniques R J Kelly and E F C LaBerge (Bendix of the software life cycle Characteristics of avionics systems are Corp, Communications Div , Baltimore, Md ) In NAECON '78, identified which contribute to an active operational life and have Proceedings of the National Aerospace and Electronics Conference, implications for support methods Operational support requirements Dayton, Ohio, May 16-18, 1978 Volume 2 New are then established from the activity phases of the software life York, Institute of Electrical and Electronics Engineers, Inc , 1978, p cycle and AFLC operational support objectives Tool requirements 502-510 9 refs can then be selected from a hierarchy of tools which support the The Time Reference Scanning Beam (TRSB) Microwave Landing software life cycle (Author) System (MLS) is being developed by FAA Early in the prototype hardware phase of the development, the Dwell Gate Processor (DGP) which operates on the received beam envelope, was selected as the economic airborne receiver signal processing design for the accurate A78-49901 Subsystem verification of an AFLC organically estimation of the aircraft's angular position in the presence of strong developed F-15 simulation J B Sharp and 0 P Cerny (USAF, specular multipath and receiver noise The study discussed m this Warner Robins Air Logistics Center, Robins AFB, Ga ) In NAECON paper was undertaken to review the selection of the DGP in the light '78, Proceedings of the National Aerospace and Electronics Confer of work done on other processor mechanizations in the interim The ence, Dayton, Ohio, May 16-18, 1978 Volume 1 study included the definition of an optimum phase and amplitude New York, Institute of Electrical and Electronics processor against which all of the techniques were compared The Engineers, Inc , 1978, p 426-433 6 refs comparison was based on both computer and receiver bench tests It This paper describes techniques used to verify subsystems of an was concluded that the DGP is the appropriate choice for general F-15 simulation which is under development at the Warner Robins TRSB processing requirements B J

533 A78-49905

A78-49905 Digital simulation and flight verification of the 1978 Volume 2 New York, Institute of F-5E/F Flight Director Computer R Emerson (USAF, Aeronautical Electrical and Electronics Engineers, Inc , 1978, p 688-696 Systems Div , Wright-Patterson AFB, Ohio), R E Weaver, and R A A bank-to-turn (BIT) steering mechanization has been developed Weeks (Northrop Corp, Hawthorne, Calif) In NAECON '78, and evaluated for a tactical missile concept, resulting in exceptional Proceedings of the National Aerospace and Electronics Conference, short range performance, by employing the maximum maneuvering Dayton, Ohio, May 16-18, 1978 Volume 2 New capability of an unsymmetrical airframe The control system York, Institute of Electrical and Electronics Engineers, Inc , 1978, p employs BIT steering, an adaptive autopilot, and proportional 511-518 USAF-supported research navigation (with closing velocity) The BIT steering mechanization A digital real-time flight simulation was performed to determine allows the large 'g' capability of the airframe pitch axis to be applied the modifications required to an analog Flight Director Computing in a direction to reduce the total hne-of-sight rate The adaptive System to adapt it to the F-5E/F Aircraft The investigation assumed autopilot assures adequate performance throughout a large flight that all gains would be of constant value and that the input/output envelope, without exceeding critical values of angle-of-attack and of the existing Flight Director Computer (FDC) would be unaltered side-slip A small amount of skid-to-turn maneuvering in conjunction The simulation program was carried out to permit pilot in the loop with proportional navigation with closing velocity provides high evaluations Analog FDC aircraft hardware, from which the baseline accuracy against maneuvering targets from all aspects G R Digital FDC model was derived, was interfaced to the simulation to allow parallel comparisons and validation with existing analog computing avionics Flight tests were conducted in a F-5F to validate that the gain changes made in the FDC as a result of the digital A78-49928 Strapdown seeker guidance for tactical simulation were compatible with the operational aircraft (Author) weapons T R Callen (USAF, Armament Laboratory, Eglin AFB, Fla / and R D Ehrich (Rockwell International Corp , Columbus, Ohio) In NAECON '78, Proceedings of the National Aerospace and A78-49906 Fiber optic development for tactical fighter Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 2 applications R W Uhlhorn and R G Autry (McDonnell Aircraft New York, Institute of Electrical and Electronics Co , St Louis, Mo ) In NAECON '78, Proceedings of the National Engineers, Inc , 1978, p 697-704 Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, A description is presented of the work accomplished thus far in 1978 Volume 2 New York, Institute of connection with a study which is to determine the best combination Electrical and Electronics Engineers, Inc, 1978, p 519-527 5 refs of guidance law structure, signal processing techniques, and achiev- Navy-supported research able seeker and sensor accuracy requirements for the effective use of Fiber-optic material evaluations were conducted in four areas Strapdown seekers with tactical guided weapons An evaluation is (1) terminations for bundle type cables, (2) extruded cable jacket provided of proportional navigation utilized as the guidance scheme resistance to heat and moisture, (3) hydrolytic stability of encapsu- for air-to-surface weapons with Strapdown seekers Attention is given lating epoxies, and (4) adhesion promoters between fibers and to mathematical models of air-to-surface weapons, methods of ferrules Harness assemblies were also evaluated in the following generating hne-of-sight rates, seeker models and error sources, and tests thermal aging, humidity, thermal cycling, and vibration and simulation results The results of the study thus far indicate, as flexure An EM immunity and flight test program is described in expected, that proportional navigation with reasonable navigation which digital fiber-optic data transfer systems will be installed in two gam is sufficiently sensitive to seeker and scale factor errors to make YAV-8B Harrier test aircraft, the fiber-optic instrumentation for this implementation extremely difficult G R program is described Results of cost/benefit studies on airborne fiber-optic systems are discussed along with future activities in the field BJ

A78-49920 Electromagnetic coupling analysis of a Learjet A78-49929 In-flight alignment/calibration techniques for aircraft in a lightning environment J C Corbm, Jr (USAF, Flight unaided tactical guidance J W Kraemer, N J Roessler, and D M Dynamics Laboratory, Wright-Patterson AFB, Ohio) and D F Brandm (McDonnell Douglas Astronautics Co , St Louis, Mo ) In Strawe (Boeing Aerospace Co , Seattle, Wash ) In NAECON '78, NAECON '78, Proceedings of the National Aerospace and Electron- Proceedings of the National Aerospace and Electronics Conference, ics Conference, Dayton, Ohio, May 1618, 1978 Volume 2 Dayton, Ohio, May 16-18, 1978 Volume 2 New , New York, Institute of Electrical and Electronics York, Institute of Electrical and Electronics Engineers, Inc , 1978, p Engineers, Inc, 1978, p 705-711 Contract No F08635-77-C 0210 644-648 20 refs An evaluation is conducted of various alignment/calibration A joint AFFDL/NASA lightning research program was con- procedures which permit the use of low-cost sensors in unaided ducted at Kennedy Space Center in July and August of 1977 as part navigation satisfying tactical mission requirements The missile of Project Thunderstorm (TRIP-77) A NASA Learjet aircraft was navigation system and its interface with the reference launch aircraft instrumented with E and H field antennas, field mills, and skin navigation system are illustrated in a figure Strapdown gyros and current sensors to obtain near field lightning data Special cable runs accelerometers are included in the missile's mertial sensor subsystem were installed to record induced voltages and currents within the To provide the optimum cost-effective utilization of these sensors for aircraft As part of the program, an electromagnetic coupling analysis their navigation role, in-flight estimation of critical sensor error terms of the aircraft was developed and applied to predict and interpret is achieved by processing launch aircraft navigation data through a magnitudes and waveforms of induced voltage and current transients Kalman integration filter A description is presented of the develop- on selected cables and circuits This paper describes the modeling ment of realistic launch aircraft alignment maneuvers and reduced- techniques used to calculate the external induced skin current state Kalman filter mechanizations which optimize navigation per- density for arbitrary lightning sources, the penetration fields that formance of the Strapdown Low Cost Inertial Guidance System G R produce voltage sources on interior cables and circuits, and the circuit responses to these sources (Author)

A78-49932 The DAIS Executive - An introduction W H A78-49927 Bank-to-turn /BIT/ autopilot technology R Vandever, Jr (Intermetrics, Inc, Dayton, Ohio) In NAECON '78, M McGehee (USAF, Armament Laboratory, Eglin AFB, Fla ) and R Proceedings of the National Aerospace and Electronics Conference, I Emmert (Rockwell International Corp, Missile Systems Div, Dayton, Ohio, May 16-18, 1978 Volume 2 New Columbus, Ohio) In NAECON '78, Proceedings of the National York, Institute of Electrical and Electronics Engineers, Inc , 1978, p Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, 733-740 8 refs

534 A78-49941

Ninety-five percent of the DAIS Executive was written in J73/I, involving the utilization of rare-earth permanent magnets in generat- thus aiding in its own portability The current implementation was ing 400-Hz aircraft power All of the programs discussed employ the designed to handle a federated computer network and was imple variable speed constant frequency (VSCF) approach, and all are mented in such a fashion as to isolate the network characteristics formulated to consider power generation as well as gas-turbine engine from the Applications Software This has allowed the Applications starting Three specific programs are described (1) 150 kVA Software to be developed with assurance on a virtual single processor samarium cobalt VSCF starter generator electrical system, (2) SmCo and then transferred to a federated system without modification In generator/engine integration study, and (3) permanent magnet addition, the DAIS executive tables are optimized by having a variable speed constant frequency power generation system (flight pre runtime tool (PALEFAC) create static tables to minimize the test on A-10 aircraft) Additional comments pertaining to permanent dynamic characteristics of execution and to minimize on memory magnet generator (PMG) VSCF systems in general are provided requirements Several associated results occur when a standardized (Author) executive interface is used in conjunction with a Higher Order Language These include the ability to develop a powerful and cost effective simulator on various host computer systems, the Applica A78-49936 A standard programmable I/O for the ad- tion Software has become truely portable, and a Higher Order vanced aircraft electrical system power control set J R Perkins, W Language implementation of the executive itself will add legacy to T Turnage (Vought Corp , Dallas, Tex ), H Brown, and J Davidson the executive and thus the corresponding reduction in errors and (U S Naval Material Command, Naval Air Development Center, cost (Author) Warmmster, Pa ) In NAECON '78, Proceedings of the National Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 2 New York, Institute of Electrical and Electronics Engineers, Inc , 1978, p 765-771 A78-49933 An interface management approach to soft- A description is provided of a method whereby the I/O channels ware development L C Klos (General Dynamics Corp , Fort Worth, of the multiplex terminal can be universally used for either Tex ) In NAECON '78, Proceedings of the National Aerospace and multiplexing input signals or demultiplexing output signals The Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 2 terminals can be wired directly to either signal source or power New York, Institute of Electrical and Electronics controller devices without having to reconfigure the terminal in Engineers, Inc. 1978, p 741-748 terms of signal conditioning or I/O assignments via reprogrammmg The method described was developed for managing interfaces In presenting the universal terminal concept, a brief overview is given between software modules through the use of data flow graphs, on the Solid State Electric Logic (SOSTEL) and Electrical Multiplex computerized interface lists, and automated generation of common (EMUX) type systems Attention is also given to the 'switched data declarations The tools used to accomplish this are Directed impedance' signal interface technique developed primarily for the Flowgraphs and a System Development Interface Manager These purpose of expanding the built-in-test capability of the SOSTEL tools and the rationale for using an interface management approach system A universal terminal functional diagram is presented GR are examined Interface management is important to real-time software development, because interfaces are the critical links A78-49937 tt Aircraft electrical system testing and data between program modules and between avionic subsystems The reduction using digital techniques E J Caputo (USAF, Aero management of these interfaces and their time relationships in a Propulsion Laboratory, Wright-Patterson AFB, Ohio) In NAECON controlled and standardized manner requires the clarification of '78, Proceedings of the National Aerospace and Electronics Con thought processes and leads to a thorough well-documented design ference, Dayton, Ohio, May 16-18, 1978 Volume 2 with better software partitioning and fewer problems (Author) New York, Institute of Electrical and Electronics Engineers, Inc , 1978, p 772-776 The testing and data reduction of aircraft electrical systems and A78-49934 Dynamic analysis of electrical systems P J electrical system components using digital and computerized tech- Leong and I S Mehdi (Boeing Aerospace Co , Seattle, Wash ) In niques is discussed The major objective of electrical system testing is NAECON '78, Proceedings of the National Aerospace and Electron to determine actual power quality of the various configurations of ics Conference, Dayton, Ohio, May 16 18, 1978 Volume 2 conventional (electromechanical) and solid-state electrical system New York, Institute of Electrical and Electronics components These data are then used to provide information for Engineers, Inc , 1978, p 752 756 future updates of MIL-STD-704 ('Aircraft Electrical Power Charac- A technique is presented for modeling the dynamics of an teristics') The Digital Testing System used by the Air Force Aero aircraft three-phase ac electrical power system The analysis is Propulsion Laboratory (AFAPL) is examined The system consists of accomplished using the EASY model generation and analysis five major components Several modes of operation are described program, which can determine steady-state operating points, simulate Digital computation methods used to reduce the data taken are nonlinear components, generate linearized models, and perform discussed Test methods for solid-state power controllers, circuit transient and stability analyses Mathematical models of the major breakers, generators, integrated drive generator units, and VSCF components of the electrical system, such as the generator, exciter, units are outlined Results from some of the testing done at AFAPL voltage regulator, feeders, and load, are derived and implemented are given Conclusions are presented on the effectiveness of testing of into the standard EASY component representation The program electrical system components using digital techniques (Author) user can then analyze a system by specifying the topology of a network of these predefined component models Some sample simulation results are included (Author) A78-49941 Multi-Function Inertial Reference Assembly /MIRA/ update R C Burns (McDonnell Aircraft Co, St Louis, Mo) and J M Perdzock (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio) In NAECON '78, Proceedings of the National Aerospace and Electronics Conference, Dayton, Ohio. May A78-49935 f- Application of rare earth/transition metal per- 16-18, 1978 Volume 2 New York, Institute of manent magnets to 400 Hz aircraft systems An AF overview W U Electrical and Electronics Engineers, Inc, 1978, p 798-807 Borger (USAF, Aero Propulsion Laboratory, Wright-Patterson AFB, This paper presents a summary of the preliminary assessment Ohio) In NAECON '78, Proceedings of the National Aerospace and task studies that showed significant cost savings were potentially Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 2 possible based upon projected improvements in strapped down New York, Institute of Electrical and Electronics technology Laboratory demonstrations provided added confidence Engineers, Inc , 1978, p 757-764 9 refs to the preliminary feasibility assessment Three candidate MIRA This paper describes, in overview fashion, the USAF programs configurations chosen for further analysis leading to the selection of

535 A78-49951

a single MIRA design are described Design criteria for candidate attention is given to a modular Target Acquisition System which has evaluation are discussed in relation to key study findings in the areas been designed for these applications G R of performance, survivabihty, reliability, and installation The three candidate MIRA systems are then discussed in terms of risk estimation versus potential life cycle cost savings Current design A78-49956 The versatility of Jovial J73 in avionics sys- studies and refinements are leading to the definition and selection of tems. T E Matysek (Westmghouse Electric Corp , Pittsburgh, Pa ) a single MIRA design which will be incorporated in the MIRA In NAECON '78, Proceedings of the National Aerospace and specification (Author) Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 2 New York, Institute of Electrical and Electronics Engineers, Inc , 1978, p 928-933 A78-49951 Digital area correlation tracker M G Woolf- A complete Avionics Systems Operational Software Package son (Westmghouse Electric Corp , Baltimore, Md ) In NAECON '78, must be able to handle logic functions, equation writing, and I/O Proceedings of the National Aerospace and Electronics Conference, block packing for I/O to peripheral devices A description is Dayton, Ohio, May 16-18, 1978 Volume 2 New presented of Jovial J73 which has the capability to handle all of York, Institute of Electrical and Electronics Engineers, Inc , 1978, p these needed functions The compiler is written in machine indepen- 882-886 dent FORTRAN and produces assembly language for use on the The Digital Area Correlation Tracker (DACT) and a system currently used computer An intermediate language is generated and interface were designed and built with the objective to satisfy the the target machines instructions are easily substituted in the requirements of the 'single seat' mission in which the pilot must, compiler's working tables To provide a different assembly language, among other tasks, fly the aircraft and provide inputs to the E-0 the compiler code generation tables would need to be changed sensor system Additional requirements are imposed on the auto- Attention is given to the logical functions in Jovial, equation writing tracker to minimize pilot attention and command inputs DACT uses in Jovial, aspects of I/O block packing, and questions of compiler no preprocessor controls to eliminate the need for video gain, verification G R threshold, and contrast polarity adjustments These requirements have been eliminated because the DACT employs direct conversion of the analog video signal into 5-bit digital data rather than threshold A78-49957 A flight simulation high order language study circuits which convert the analog video signal to one bit data C L Braun (SofTech, Inc, Waltham, Mass) In NAECON '78, Aspects of tracker operation are explained from a concept point of Proceedings of the National Aerospace and Electronics Conference, view G R Dayton, Ohio, May 16-18, 1978 Volume 2 New York, Institute of Electrical and Electronics Engineers, Inc , 1978, p 934-940 7 refs Contract No F33615-76-R-0029 This paper describes a study, conducted for the Air Force A78-49952 ti Prediction of angular disturbances from air- Human Resources Laboratory (Contract No F33615-76-R-0029), to frame members to airborne electro-optical packages P W Whaley determine the requirements for a Higher Order Language (HOD for and D L Brown (USAF, Flight Dynamics Laboratory, Wright programming modern flight training simulators The objective of this Patterson AFB, Ohio) In NAECON '78, Proceedings of the National study was to determine the suitability of existing HOLs to the flight Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, training simulator area, not to define a new HOL The approach 1978 Volume 2 New York, Institute of taken in this study for HOL evaluation and selection is applicable in Electrical and Electronics Engineers, Inc , 1978, p 887-896 9 refs other areas, especially those areas where assembly languages are in A description is presented of the general frequency response wide use because of the presumed inadequacy of existing HOLs behavior of aircraft angular vibration relative to linear vibration For (Author) two sets of aircraft data, the angular vibration Power Spectral Density (PSD) falls off less steeply than does the linear vibration PSD at higher frequencies Comparisons to available data from two aircraft show that these prediction models given good predictions of A78-49959 Higher order languages for avionics software • the angular PSD shape with respect to frequency Until complete A survey, summary and critique R J Rubey (SofTech, Inc, knowledge concerning the characteristics of aircraft angular vibration Waltham, Mass) In NAECON '78, Proceedings of the National is available, the designer can use the shape function to predict Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, angular vibration PSD Aspects of theoretical development are 1978 Volume 2 New York, Institute of discussed, taking into account the Bernoulli-Euler beam, the Timo- Electrical and Electronics Engineers, Inc, 1978, p 945-951 28 refs shenko beam, cylindrical shell dynamics, and parameter choices G R This paper surveys the activities of the last ten years with regard to avionics Higher Order Languages (HOLs) It presents reasons why HOLs were late arriving in the avionics arena and why they have not A78-49954 Modular target acquisition and designation been more widely used today In particular, the published exper- systems. M W Iverson (Honeywell Inc , Avionics Div , St Louis iences with existing HOLs in avionics appplications are summarized Park, Minn ) In NAECON '78, Proceedings of the National Descriptions of important HOL evaluation criteria, such as 'ef- Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, ficiency' and 'programmer productivity' are presented and the 1978 Volume 2 New York, Institute of reported measurements with respect to these criteria are discussed Electrical and Electronics Engineers, Inc , 1978, p 905 909 The problems and deficiencies of past reporting with respect to these It has been found in recent conflicts that the effectiveness of criteria are highlighted In addition to this summary of the weapons has been limited by a failure to hit the target Missiles and quantitative information regarding avionics HOL use, the need for projectiles can be sent much beyond the limit of the area for which improvements are discussed This includes the relationship of the an accurate detection, location, identification, and tracking of targets HOL to the total software development process, the improved is possible The more uncertain the target location, the larger the software tools that can be employed, and the level of HOL number of volleys required to destroy a target The significance of documentation available (Author) the anti-aircraft threat in Central Europe is examined and alternatives are discussed to extend the effective range of the weapons in this hostile environment It is found that there are really no alternatives A78-49961 Modeling refinements for the rectified super- as such Instead combinations of different systems are needed in a conducting alternator T A Stuart (Toledo, University, Toledo, mix which will yield the highest probability of success with the Ohio) and M W Tripp (Detroit Edison Co, Detroit, Mich) In lowest losses A description is presented of two of the systems NAECON '78, Proceedings of the National Aerospace and Electron- needed in the future system mix, taking into account the Target ics Conference, Dayton, Ohio, May 16-18, 1978 Volume 3 Acquisition RPV and the Mast Mount Helicopter In particular. New York, Institute of Electrical and Electronics

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The design, implementation, and operation of real-time simula- Engineers, Inc, 1978,p 1002-1009 lOrefs Grants No AF-AFOSR- 76-2997, No AF-AFOSR 77-3413 tors for augmented menial navigation systems are described Detailed Certain characteristics of an earlier steady state model developed mathematical models of the mertial platform, the Doppler radar by Stuart and Tripp (19771 for the rectified sunerconductmg sensor, and the aircraft flight profile generation are presented The alternator are examined The earlier approach involved the derivation actual software design of the simulator is not discussed B J of a set of five nonlinear equations, these equations were then solved via a standard Newton-Raphson algorithm, and the solution was used A78-49968 Reliability of mertial navigation systems A J to evaluate several other variables The present paper carries out an Brann (Litton Industries, Guidance and Control Systems Div, analysis which shows that the earlier model can be improved by Woodland Hills, Calif ) In NAECON '78, Proceedings of the eliminating an ambiguity associated with the ac field current and by National Aerospace and Electronics Conference, Dayton, Ohio, May reducing the number of system equations from five to two Data are 16-18, 1978 Volume 3 New York, Institute of included to show that the modified equations are consistent with the Electrical and Electronics Engineers, Inc , 1978, p 1054-1060 earlier model B J An analysis of several major military and commercial INS programs over the last 20 years is performed The results of the A78-49962 Impact of aircraft electrical power quality on analysis show that the older analog INS have low predicted MTBFs utilization equipment A W Schmidt and E T Reiquam (Boeing using today's prediction techniques More modern technology INS Commercial Airplane Co, Seattle, Wash) In NAECON '78, (the last 10 years) used in both military and commercial application Proceedings of the National Aerospace and Electronics Conference, show comparable predicted MTBFs using identical environmental Dayton, Ohio, May 16-18, 1978 Volume 3 New factors When an attempt is made to account for the differences York, Institute of Electrical and Electronics Engineers, Inc , 1978, p between military and commercial application with respect to 1010-1014 5 refs temperature, vibration, and on/off cycling, it is noted that the Aircraft electric power characteristics impose significant penal- principal reason for higher MTBF of commercial INS is environmen- ties - associated with voltage surges, voltage spikes, frequency tal Present-day design and test techniques for assuring high field transients, long power interruptions, unbalanced phase voltages, and reliability of INS are described B J waveform distortion - on avionics systems This paper presents a qualitative assessment of penalties imposed on avionics systems and A78-49971 The AN/APX-100/V/ transponder J T discusses some methods for improving power quality characteristics Skudrna and G L Vogt (Bendix Corp, Communications Div, In support of the penalty assessment, technical and cost data are Baltimore, Md ) In NAECON '78, Proceedings of the National presented for a large number of self-contained power supplies of Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, avionics equipment B J 1978 Volume 3 New York, Institute of Electrical and Electronics Engineers, Inc , 1978, p 1086-1093 A78-49965 Station deselection procedures to support The AN/APX 100(V), an integrated panel-mounted transponder automatic Omega receiver operation R D Healy (Analytic Sciences has been developed for military aircraft through the use of Corp, Reading, Mass) In NAECON '78, Proceedings of the microminiaturization m both digital and RF circuitry This paper National Aerospace and Electronics Conference, Dayton, Ohio, May describes the system design and system integration of the trans 16 18, 1978 Volume 3 New York, Institute of ponder and gives attention to considerations of reliability, main- Electrical and Electronics Engineers, Inc, 1978, p 10261030 9 tainability, and human factors Performance improvements mcor refs Contract No F19628-77-C-0033 porated in the transponder are discussed in detail with attention The paper discusses four types of propagation modeling errors given to such features as diversity, automatic overload control, built which can lead to navigationally significant errors in indicated Omega in test, solid state transmitter, and alternate remote configuration position (1) wrong-way path, (2) westerly signal traverse of B J magnetic equator, (3) sudden ionospheric disturbances, and (4) polar cap anomalies It is shown that position errors can be minimized by A78-49972 Dual band airborne SATCOM terminal E M using the manual deselection feature of the receiver An Omega Perdue and G K H Tsao (Raytheon Co , Equipment Div , Sudbury, station selection chart is presented containing specific recommenda- Mass I In NAECON'78, Proceedings of the National Aerospace and tions for station deselection in a number of worldwide locations B J Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 3 New York, Institute of Electrical and Electronics A78-49966 Performance of a differential Omega-ring laser Engineers, Inc, 1978, p 10941096 5 refs Contract No strapdown aircraft navigator C San Giovanni, Jr (Sperry Rand F33615-73-C-4036 Corp, Sperry Gyroscope, Great Neck, NY) In NAECON '78, An experimental airborne low level terminal is developed for Proceedings of the National Aerospace and Electronics Conference, command and control communications via either the DSCS satellites Dayton, Ohio, May 16-18, 1978 Volume 3 New in the SHF band or the LES-8/LES-9 satellites in the EHF band The York, Institute of Electrical and Electronics Engineers, Inc 1978 p terminal utilizes a agile frequency synthesizer system to generate 1031-1043 15 refs carrier frequencies with exceptionally low phase noise, wide carrier The accuracy performance of an aircraft differential Omega ring tuning range and short switching settling time The dual band laser strapdown system is evaluated on the basis of a time history of SATCOM terminal system interfaces at a 70 MHz IF with a rms position, velocity, and attitude errors Simulation results are pseudo-noise spread spectrum MODEM, USC-28 and at a 700 MHz presented for a vehicle trajectory generally corresponding to a close IF with a frequency-hopping MODEM, OM-53 (Author) air support mission A ground align period is included For the assumed nominal error models, it is shown that horizontal velocity A78-49973 Digital system architecture for a 1980's jam- error can be bounded to a steady state value of approximately 1 mer E M Drogm (Cutler-Hammer, Inc, AIL Div , Deer Park, N Y ) m/sec rms A complete three-axis mathematical model was used in In NAECON '78, Proceedings of the National Aerospace and the analysis to represent the error propagation characteristics of the Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 3 strapdown system B J New York, Institute of Electrical and Electronics Engineers, Inc, 1978, p 1097-1103 6 refs A78-49967 Real-time simulators for augmented mertial The AN/AIQ-161, initially designed for the B-1 bomber, is an navigation systems S C Bose (Litton Industries, Guidance and automatic, fully power-managed jamming system The network Control Systems Div , Woodland Hills, Calif ) In NAECON '78, which sends commands and receives status data from the jamming Proceedings of the National Aerospace and Electronics Conference, hardware may be characterized as a nonhomogeneous federated Dayton, Ohio, May 16-18, 1978 Volume 3 New multicomputer This paper describes the jamming logic organization, York, Institute of Electrical and Electronics Engineers, Inc , 1978, p the data bus structure, and the rationale behind the data rate 1044-1053 requirements imposed on the network components The jamming

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system employs advanced concepts which will have general applica- The target screener/FLIR system was designed to operate on tions in the command and control field for many military aircraft imagery data from an AAS-27 sensor It detected man-made objects and ships deployed in the 1980s B J (MMO's) and cued the operator by displaying a symbol at each sector area containing MMO's In the present paper, a modification of the system is discussed in which the thresholds for manual extraction of A78-49975 Constant false alarm rate detector for a pulse candidate MMO's were eliminated by autothreshold, which is an radar in a maritime environment L G Cole (Westinghouse Electric automated technique to extract edges and bright signals With this Corp , Pittsburgh, Pa ) and P -W Chen (Boeing Aerospace Co , technique, it proved possible to detect MMO's with a detection Seattle, Wash ) In NAECON '78, Proceedings of the National probability of 91 2 percent at a 4 3 percent false alarm probability Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, VP 1978 Volume 3 New York, Institute of Electrical and Electronics Engineers, Inc. 1978, p 1110-1113 A78-49985 # Infrared receiver performance S J Dunning (USAF, Data Systems Div , Sunnyvale Air Force Station, Calif ) and Contract No F19628-70-C-0218 A new doubly adaptive detector with target discrimination S R Robinson (USAF, Institute of Technology, Wright-Patterson circuitry is proposed, based on the use of an auxiliary parallel AFB, Ohio) In NAECON '78, Proceedings of the National adaptive detector in addition to the conventional main adaptive Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, detector The target discrimination circuitry is a simple logic circuit 1978 Volume 3 New York, Institute of inserted between the detection cell and the clutter average cells This Electrical and Electronics Engineers, Inc, 1978, p 1186-1193 9 logic circuitry prevents the target from entering the succeeding refs clutter average cells by replacing the target report with the clutter The performance of an optical receiver which uses the target's average established previously Therefore, the overall clutter average spectral signature to detect the target is discussed The receiver will not be raised significantly No detection degradation for the processes the signal in several narrow frequency bands It is based on adjacent cell will result, which minimizes target-to-target mterfer a statistical model in which the field in each band is represented in ence B J the form of a Gaussian random process whose moments depend upon the target and background characteristics The signal is detected by an array of power detectors whose outputs are modeled as random A78-49976 A high duty factor chirp radar M B Rmgel variables characterized by noncentral chi-square probability density (Westinghouse Electric Corp , Baltimore, Md ) In NAECON '78, functions V P Proceedings of the National Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volumes New A78-49987 Assessment of dynamic coordinate alignment York, Institute of Electrical and Electronics Engineers, Inc , 1978, p 1114-1119 for elastic aircraft C Wakefield (Charles Stark Draper Laboratory, A system description and simulation results are presented for a Inc, Cambridge, Mass) In NAECON '78, Proceedings of the high-duty-factor gated chirp radar Appropriate gating and processing National Aerospace and Electronics Conference, Dayton, Ohio, May of a suitable chirp signal completely eliminates the degradation 16-18, 1978 Volume 3 New York, Institute of Electrical and Electronics Engineers, Inc, 1978, p 1199-1204 suffered by a partially eclipsed chirp signal and allows the transmis- Contract No F33615-77-C-1121 AF Project 7629 sion of a signal of 50% duty cycle In addition, the matched filter for A description is presented of some results for Kalman type filter a gated chirp signal can be obtained as a straightforward modification algorithms that ignore the colored nature of the noise This implies of that for a standard chirp signal The advantages and disadvantages that the noise is treated as if it were mutually uncorrelated white of gated chirp are reviewed B J noise The data used to drive the filter is synthetically generated angular rates and accelerations that contain appropriate aeroelastic A78-49977 Air-to-air designate/track with time sharing J characteristics of a B-52 type aircraft The effects of various classes L Farrell, M Tom, and C Nemec (Westinghouse Electric Corp , of instruments used to sense linear and angular motion are also Systems Development Div, Baltimore, Md ) In NAECON '78, described The results presented illustrate the effect of some Proceedings of the National Aerospace and Electronics Conference, unmodeled error sources and improvements that can be achieved by Dayton, Ohio, May 16-18, 1978 Volume 3 < New simple modeling of specific error terms As a consequence, certain York, Institute of Electrical and Electronics Engineers, Inc , 1978, p classes of mertial measurement systems can be eliminated as possible 1121-1127 candidate systems regardless of the type of filter employed, adaptive The paper describes a system of selective designation which or otherwise G R provides high data rates for all targets under consideration, thus enabling multitarget tracking under severe dynamic conditions A A78-49988 High-accuracy three-dimensional image recon- digital program simulates flight paths for the interceptor and up to struction for an airborne line-scanning system C J Vahlberg and C 10 maneuverable targets, while verifying the application of modern C Ormsby (Analytic Sciences Corp , Reading, Mass ) In NAECON estimation techniques to all track files Both optimal and suboptimal '78, Proceedings of the National Aerospace and Electronics Confer- estimation are used to maximize computational efficiency The ence, Dayton, Ohio, May 16-18, 1978 Volume 3 optimal algorithm tracks an accelerating vehicle (acquired at sonic New York, Institute of Electrical and Electronics speed) having a 20-g thrust maintained for 1 5 sec after acquisition Engineers, Inc , 1978, p 1205-1211 Suboptimal estimation at varying data rates is used for supersonic A data processing system has been developed to accurately and subsonic aircraft Processing is organized in such a way that only analyze data produced by an airborne line-scanning system The the highest-priority target warrants high-precision tracking, while the objective is the creation of a three-dimensional sensor data base suboptimal algorithm is designed for maximally efficient time which will be used in the evaluation of correlation guidance systems sharing B J To accurately form this data base, the aircraft track and a variety of instrumentation parameters must be estimated to an accuracy beyond that normally possible using the available instrumentation (LTN-51 mertial measurement unit, laser ranging system, and metric camera) This paper presents the data analysis methodology and A78-49984 Autothreshold autoscreener/FLIR system D resulting computer program structure created to achieve these Serreyn, M Geokezas, R Larson, and K Fant (Honeywell, Inc , objectives, along with a sample of the results (Author) Minneapolis, Minn ) In NAECON 78, Proceedings of the National Aerospace and Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 3 , New York, Institute of A78-49989 Accuracy requirement and cost enectiveness Electrical and Electronics Engineers, Inc , 1978, p 1180-1185 of GPS-aided INS for tactical fighters P P Chen (Northrop Corp,

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Electro-Mechanical Div , Anaheim, Calif) In NAECON 78, Pro- permits a match point computation that provides the navigational ceedings of the National Aerospace and Electronics Conference, fix We discuss generic and derived features, feature based image Dayton, Ohio, May 16-18, 1978 Volume 3 New models, and the optimization and evaluation of a baseline pattern York, Institute of Electrical and Electronics Engineers, Inc , 1978, p match ing system (Author) 1212-1218 A method of deriving the Inertial Navigation System (INSI A78-50001 Combmatonally derived limits on the surface accuracy requirement in a Global Positioning System (GPS)-aided return for an air/surface monopulse ranging radar R E Wilcox INS configuration for tactical fighters and an assessment of its cost (Emerson Electric Co , Electronics and Space Div , St Louis, Mo ) effectiveness are presented Scenario and avionic performance param In NAECON '78, Proceedings of the National Aerospace and eters essential to this configuration are identified and their tradeoffs Electronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 3 are established Kalman covanance analysis is applied to determine New York, Institute of Electrical and Electronics the overall navigation performance in an environment with and Engineers, Inc, 1978, p 1296-1302 11 refs without jamming and for various INS qualities The analysis results This paper presents a systematic approach to placing limits upon show that an INS with an accuracy of 4 to 8 nmi/hr Circular Error the simultaneous values of the sum and difference channels in a given Probable (CEP) will be sufficient when aided by GPS for tactical range gate for a bounded but large variety of surface topologies with fighters A 30 to 60 percent cost saving over current fighter segmented sections of different cross section contributing to the navigation systems is predicted by employing the configuration with return Combinatorial generating functions are constructed over a astrapdown INS (Author) defined antenna gain space which enumerate and define all possible returns These in turn are examined for particular partitions which A78-49991 H F-15 avionics Built-in-Test L E LanglUSAF, yield maximum and minimum electromagnetic returns The paper is Aeronautical Systems Div, Wright-Patterson AFB, Ohio) In concluded with a specific example to illustrate some of the principles NAECON '78, Proceedings of the National Aerospace and Electron that are involved (Author) ics Conference, Dayton, Ohio, May 16-18, 1978 Volume 3 New York, Institute of Electrical and Electronics Engineers, Inc , 1978, p 1225-1230 A78-50002 A frequency-selective YIG limiter for airborne In the present paper, the avionics Built-in-Test (BIT) design and FM/CW X-band radar S N Stitzer and H Goldie (Westmghouse development for the F-15 aircraft is discussed The basic weapon- Defense and Electronic Systems Center, Baltimore, Md ) In system maintenance concept and BIT design philosophy are re- NAECON 78, Proceedings of the National Aerospace and Elec- viewed, and some problems encountered during integration of the tronics Conference, Dayton, Ohio, May 16-18, 1978 Volume 3 various BIT-capable avionic systems are discussed Field experience New York, Institute of Electrical and Electronics with BIT has shown that allowing BIT to detect one time or short Engineers, Inc, 1978, p 1303-1308 8 refs Contract No duration faults may cause problems in maintenance under an F 15 F33615-76-C-1036 type concept Time delaying or filtering of BIT signals has proven to This paper describes a multistage frequency-selective power enhance user confidence in BIT by restricting LRU latches to limiter in which the limiting takes place in three tandem connected indicating only hard failures which can be confirmed and repaired in stages The diameters of the YIG sphere power-limiting elements the shop Some examples of these techniques in F-15 avionics are used in each stage are optimized for sharpest selectivity, lowest presented V P threshold, and widest dynamic range The passive YIG limiter provides 28 dB of dynamic range, will handle up to 3 watts CW, has a 1 percent bandwidth in X-band, and has a below-threshold loss of 1 7 A78-49997 A parametric analysis of TERCOM false fix dB Limited output power is under 5 milliwatts, third order probability E H Conrow (General Dynamics Corp, Convair intermodulation products at the output are better than 20 dB down Aerospace Div , San Diego, Calif ) In NAECON'78 Proceedings of from a 0 dBm in-band signal beating with a second m-band signal of the National Aerospace and Electronics Conference, Dayton, Ohio, +33 dBm The device has application to high power FM/CW May 16-18, 1978 Volume 3 New York, monostatic radars when simultaneous transmission and reception is Institute of Electrical and Electronics Engineers, Inc, 1978, p required, also to RF signal leveling, long term RF memory loops for 1271-1277 ECM, ordinary limiting, and protection of communications receivers Terrain contour matching (TERCOM) is a map-matching technique that uses elevation data of the earth's surface for position from strong RF signals without causing loss of reception during the overload period (Author) location and navigation updating in some systems The accuracy of TERCOM, like other map-matching methods, is affected by temporal (environmental) and geometric variations and noise between computer-stored reference and sensor (altimeter)-generated test A78-50007 A flight qualified graphics generator R C scenes In this study a Monte Carlo simulation using the MAD Landgraf (Boeing Wichita Co , Seattle, Wash ) In NAECON 78, algorithm, was developed to investigate the sensitivity of various Proceedings of the National Aerospace and Electronics Conference, reference and sensor scenes, and vehicle parameters on the TERCOM Dayton, Ohio, May 16-18, 1978 Volume 3 New false fix probability From this, an estimate was made of the level of York, Institute of Electrical and Electronics Engineers, Inc , 1978, p each parameter necessary to significantly impact TERCOM per- 1357-1363 formance (although some scene-to-scene variation should be ex A flight qualified Graphics Generator (GG) which has been pected) (Author) developed for use on the B-1 Defensive Avionics System will be described in this paper The GG generates the symbol and graphic A78-49998 Advanced pattern matching for navigation and displays which provide information to the defensive operator to guidance D H Close and C A McNary (Hughes Research enable him to defend the B-1 aircraft The information is displayed Laboratories, Mahbu, Calif) In NAECON 78, Proceedings of the on two cathode-ray tube (CRT) Electronic Display Units (EDU) The National Aerospace and Electronics Conference, Dayton, Ohio, May GG features interchangeable circuit cards which require no recalibra- 16-18, 1978 Volume 3 New York. Institute of tion when cards are substituted The refresh rate is automatically Electrical and Electronics Engineers, Inc, 1978, p 1278-1280 adjusted based on quantity of imagery, thereby avoiding loss of Contracts No F30602-76-C-0074, No F30602-77-C-0049, No displayed information The factors considered in choosing dot F33615-77-C-1227 writing instead of stroke or television techniques will be discussed, We describe an advanced pattern matching system for providing some of these factors are positioning control, line closure, circuit navigational updates This system uses syntactic image features, such complexity, and adjustments required during circuit card manufac- as straight line segments and segmented regions, to build a semantic turing tests A block diagram will be presented and the operation of model of image content Matching of reference and sensed models the GG will be described (Author)

539 A78-50125

A78-50125 # Operating characteristics of bypass turbojet Institute of Aeronautics and Astronautics, Inc, 1978, p 20-30 25 engines (Ekspluatatsionnye kharaktenstiki dvukhkonturnykh turbo- refs Research supported by the U S Department of Energy (AIAA reaktivnykh dvigatelei) A L Khachkin Moscow, Izdatel'stvo 78-1243) Transport, 1978, 128 p 36 refs In Russian The basic framework for applying Kalman filtering techniques The bypass engines of commercial aviation are the subject of to radar terrain-clearance data is investigated By recursively Kalman this book which investigates the effects of operating conditions on processing each individual radar measurement separately, a whole engine parameters and indices and also the cost aspects of engine new class of terrain-aided navigation schemes becomes available operation The results of numerous studies on the effect of bypass which in the past could not be developed by using simple correlation ratio on engine characteristics are summarized The principal paths algorithms To dimmish the effect of terrain nonhneanties, adaptive for increasing the efficiency of bypass engines are explored P T H stochastic linearization techniques are utilized in a second-order filter formulation As an application example, results are presented A78-50160 = Flight controls of Army/Hughes YAH-64 ad- indicating the performance improvements available through con- vanced attack helicopter R E Lane (Hughes Helicopters, Culver tinuous terrain-aiding of an mertial, an air-data, and a velocity- City, Calif ) In Guidance and Control Conference, Palo Alto, Calif , sensing navigation system (Author) August 7-9, 1978, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc. 1978, p A78-50179 ff Shipboard launch and recovery of RPV heli- 1-8 (AIAA 78-1237) copters in high sea states G Gevaert and E Schulze (Lear Siegler, The flight controls of the YAH-64 have been designed to meet Inc, Santa Monica, Calif) In Guidance and Control Conference, strict requirements in performance, maintainability, survivability, Palo Alto, Calif, August 7-9, 1978, Technical Papers weight, human factors and cost To achieve these requirements a New York, American Institute of Aeronautics and blend of mechanical, hydraulic and electronic flight controls has Astronautics, Inc, 1978, p 175-182 7 refs (AIAA 78-1269) been used which provides the necessary handling qualities to perform We have recently completed an analytical design of a fully day or night missions in the critical NOE environment (Author) automatic helicopter shipboard recovery system Two simulated vehicles were used in the study, the Gyrodyne QH-50 drone A78-50161 H An investigation of potential control-display helicopter and a Development Sciences, Inc (DSI) rotary-wing configurations for V/STOL aircraft B J Eulnch and J V Lebacqz research RPV Guidance and control algorithms were developed to (Calspan Corp, Buffalo, NY) In Guidance and Control Confer- successfully land the aircraft on board a nonaviation ship in high ence Palo Alto, Calif, August 7-9, 1978, Technical Papers seas The study employed six DOF helicopter models and recorded New York, American Institute of Aeronautics and ship motion data in both fully automatic and remote pilot-m-the Astronautics, Inc, 1978, p 9-11 8 refs Contract No loop simulations which were used to establish statistical perfor- N62269-77-C0561 (AIAA 78-1238) mance The simulation, developed system and the tradeoffs that led A literature review and analytic study was conducted to define to the final design are described in this paper The expected potential combinations of control system and display presentation performance as a function of recovery conditions and recommended characteristics that will permit VTOL instrument decelerating ap- criteria for successful recovery are presented The study indicates proaches to small ship platforms under adverse weather conditions that safe launch and recovery in sea state 5 are possible (Author) The study consisted of a review of operational and experimental VTOL results since 1973, the development of procedures to relate A78-50181 ff RPV flying qualities design criteria T L these results to the pilot-centered control-display requirements as a Neighbor (USAF, Flight Dynamics Laboratory, Wright-Patterson function of approach trajectory and environmental factors such as AFB, Ohio) and C D Wiler (Rockwell International Corp , Los wind/turbulence, and finally to combinations that may be hypothe- Angeles, Calif ) In Guidance and Control Conference, Palo Alto, sized to provide an all-weather VTOL capability (Author) Calif, August 7-9, 1978, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc, A78-50162 ff Performance of a ring laser strapdown attitude 1978, p 192-201 5 refs (AIAA 78-1271) and heading reference for aircraft C San Giovanni, Jr (Sperry Rand In January 1976, a contract with an American aerospace Corp, Sperry Gyroscope, Great Neck, NY) In Guidance and company was initiated by the Air Force with the objective to Control Conference, Palo Alto, Calif, August 7-9, 1978, Technical establish a framework for remotely piloted vehicle (RPV) flying Papers New York, American Institute of Aero- qualities criteria Later phases of the program were to provide data nautics and Astronautics, Inc, 1978, p 12-19 16 refs (AIAA for that framework One of the essential aspects of RPV flying 78-1240) qualities criteria is that they must consider the total RPV system This paper describes an accuracy performance analysis of a This includes not only vehicle stability and control, but must also generic ring laser strapdown attitude and heading reference system encompass automatic and manual control, command and data link, (AHRS) operating in an aircraft environment The system configura- and man-machine interfaces The general organization of the scope tion involves the use of magnetic heading and airspeed sensors to and classification section is considered, taking into account vehicle provide the required heading and velocity reference information The classes, flight phases, and the level of RPV flying qualities The analysis is based on the assumed use of an optimal (Kalman) system requirements examined are related to automatic control, fifteen-state filter to process the available measurement data manual control, stability margins, operation and interface, and Covanance analysis results are presented to indicate the relationship atmospheric disturbances G R of system accuracy performance to gyro drift and to wind model characteristics Results show that, under straight and level flight A78-50182 ff Guidance and control problems in semiauto- conditions, a pitch/roll accuracy of approximately 4 arc-min (rms) matic recovery of the Aquila RPV T R Beal (Lockheed Missiles and can be provided using ring laser gyros with 0 15 deg/sq root hr 'white Space Co, Inc, Sunnyvale, Calif) In Guidance and Control noise' drift Selection of gyros with white noise drift of 0 05 deg/sq Conference, Palo Alto, Calif, August 7-9, 1978, Technical Papers root hr will reduce these errors to approximately 2 5 arc-min (rms) New York, American Institute of Aeronautics per axis These gyro drift characteristics are well within the range of and Astronautics, Inc, 1978, p 202-207 (AIAA 78-1272) current ring laser gyro designs The study also showed that the This paper describes the recovery system for the Aquila RPV magnitude of wind variations in the 4 5-7 rad/hr frequency region is developed by Lockheed Missiles & Space Company, Inc (LMSC).for an important characteristic of this error source (Author) the U S Army The approach flight control concept is presented, as are the guidance command algorithms that control the flight to a A78-50163 // Optimal terrain-aided navigation systems L fixed glide slope boresighted to a TV camera The camera is located D Hosteller (Sandia Laboratories, Albuquerque, N Mex) In on the ground behind a vertical net and is adjusted to define a 4-deg Guidance and Control Conference, Palo Alto, Calif, August 7-9, glide slope leading into the net To recover the RPV, an operator 1978, Technical Papers New York, American controls the motion of a cursor on a TV screen to follow the RPV

540 A78 50194

image as closely as possible The coordinates of the cursor provide Recent developments in Digital Fly-By-Wire flight control the basis for the guidance command algorithms Also, in this paper technology can offer improved survivability for combat aircraft the predominant sources of error in the recovery system are Redundancy, which is used to achieve the desired levels of reliability identified and analyzed, computer modeling of the human operator and failure tolerance, can also lead to decreased vulnerability Results transfer function is discussed, and the effects of sharp-edged gusts on are presented that show that sensor dispersion, in combination with recovery performance are presented (Author) analytic redundancy techniques, enhances flight control system survibability However, dispersion of flight control sensors, e g, gyros and accelerometers, can cause problems in sensor redundancy A78-50183 ft The evolution of a remotely piloted vehicle management and in control law dynamic performance It is shown microprocessor flight control system M Woolley (Teledyne Ryan that these problems, which are due to like sensors measuring Aeronautical, San Diego, Calif) In Guidance and Control Confer- different elastic motions and rigid body kinematic effects, can be ence, Palo Alto, Calif, August 7-9, 1978, Technical Papers eliminated by using state estimators to remove these effects from the New York, American Institute of Aeronautics and sensor data (Author) Astronautics. Inc. 1978, p 208-225 10refs (AIAA 78-1273) The development of a microprocessor flight control system (MFCS) for RPVs is traced through the evolution of the control concepts to the flight testing of the MFCS RPV control law A78-50187 U Triplex digital fly-by-wire redundancy manage- concepts were applied in the digital system and provided a natural ment techniques T F Westermeier (McDonnell Aircraft Co , St division for multirate computations, significantly alleviating compu- Louis, Mo ) In Guidance and Control Conference, Palo Alto, Calif. tational requirements Analytical aspects of the design process, such August 7-9, 1978, Technical Papers New York, as z-transform analyses, sample rate determination, computational American Institute of Aeronautics and Astronautics, Inc , 1978, p constraints and simulation analyses are discussed Data obtained 264-271 7 refs (AIAA 78-1279) from the MFCS flight tests are presented and compared with Operational fly-by-wire (FBW) systems, whether analog or simulation results and with the test data for a current analog system digital, are today mostly quadruplex The introduction of digital B J computers into FBW systems presents the possibility of reducing the A78-50184 tf Guaranteed cost control of linear systems with redundancy level from quadruplex to triplex (even, in some cases, uncertain parameters - Application to remotely piloted vehicle flight duplex) with attendant system benefits reduction in maintainability, control systems. A Vmkler (California Institute of Technology, size, weight, power, and cost Quantitative data is introduced to Pasadena, Calif) and L J Wood In Guidance and Control show the failure coverage needed to achieve acceptable system Conference, Palo Alto, Calif, August 7-9, 1978, Technical Papers reliability Redundancy management techniques are presented, their New York, American Institute of Aeronautics failure coverage determined, and an analytical link established and Astronautics, Inc , 1978, p 226-234 22 refs Research sup- between these techniques and system reliability The conclusion is ported by the Teledyne Ryan Aeronautical (AIAA 78-1274) that a triplex system is both desirable and achievable (Author) In many physical systems, an accurate knowledge of certain parameters is very difficult or very expensive to obtain The designer A78-50193 ft Optimal flight control synthesis via pilot of an RPV flight control system, for example, frequently has modeling D K Schmidt (Purdue University, West Lafayette, Ind ) available little data regarding aerodynamic coefficients, due to a lack In Guidance and Control Conference, Palo Alto, Calif, August 7-9, of wind tunnel tests Based on the concept of guaranteed cost 1978, Technical Papers New York, American control, an algorithm has been developed to analyze the effect of Institute of Aeronautics and Astronautics, Inc , 1978, p 309-313 10 parameter uncertainties on closed-loop system stability An exten- refs (AIAA 78-1286) sion of this algorithm results in a technique for choosing constant The paper deals with the development of a synthesis approach feedback gams which result in stable closed-loop behavior for a range usable in the absence of quantitative aircraft handling qualities of parameter values This technique has been applied to the design of specifications, and includes explicitly design objectives based on a lateral autopilot for a rudderless RPV with uncertain aerodynamic pilot-rating concepts by means of an optimal-control pilot model coefficients (Author) The methodology uses the pilot's objective function (from which the pilot model evolves) to design the stability augmentation The A78-50185 n Software development for fly-by-wire flight procedure involves simultaneously solving for the stability augmenta- control systems J A Bosch and P Briggs (General Electric Co , tion system gams and pilot model via optimal control techniques Binghamton, N Y ) In Guidance and Control Conference, Palo Alto, Simultaneous solution is required in this case since the pilot model Calif , August 7-9, 1978, Technical Papers New (gams, etc ) depends upon the augmented plant dynamics, and the York, American Institute of Aeronautics and Astronautics, Inc. augmentation is obviously not a priori known (Author) 1978, p 235-250 8 refs (AIAA 78-1276) A rigorous computer program documentation and configuration A78-50194 if Flight investigation and theory of direct side- control procedure is being applied successfully to the development of force control W B Binnie (U S Naval Air Training Command, the Operational Program for the F-18 Flight Control System Washington, D C ) and R F Stengel (Princeton University, Prince- Approximately 50% of this program implements and supports the ton, N J ) In Guidance and Control Conference, Palo Alto, Calif, flight critical foreground tasks, and the remainder implements August 7-9, 1978. Technical Papers ' New York, built-in tests in the background The traditional software develop- American Institute of Aeronautics and Astronautics, Inc, 1978, p ment concept has been modified to incorporate 'incremental 314-324 11 refs Office National d'Etudes et de Recherches progress' and 'manage the feedback'approaches, which are described Aerospatiales Contract No 18,884/SAT,2/LL (AIAA 78-1287) in this paper Fundamentally, the software development process Several side-force command modes were implemented for flight described provides an effective and rapid method to identify and test in Princeton's 6-DOF Variable-Response Research Aircraft correct errors while assuring successful development within a (VRA), and pilot opinions of these modes were assessed, emphasizing compressed time schedule (Author) the requirements of crosswind landing Command modes included proportional and rate thumb-switch, lateral stick, and rudder pedal A78-50186 # Improved combat survivability for fly-by-wire commands, together with various blending ratios of side-force panel sensor systems. H Berman and J Boudreau (Grumman Aerospace deflection with ailerons and rudder Pilot preferences were shaped by Corp, Bethpage, N.Y.) In Guidance and Control Conference, Palo their primary flying experience (general aviation or military), Alto, Calif, August 7-9, 1978, Technical Papers although there was consensus on the desirability of side force New York, American Institute of Aeronautics and Astronautics, Inc , commands which are uncoupled from conventional inputs Analyti- 1978, p 251-263 7 refs Contract No F33615-77-C-3041 (AIAA cal foundations of the study are presented, and future research 78-1277) directions are suggested (Author)

541 A78-50195

A78-50195 * # A learning flight control system {or the solution of algebraic (mostly linear) equations to generate a F8-DFBW aircraft R C Montgomery (NASA, Langley Research 'universal nominal', and feedforward and feedback gams Then, in Center, Hampton, Va ), R Mekel, and S Nachmias (NASA, Langley flight the additional state and control corrections due to deviation in Research Center, Hampton, Va , New York, City University, New descent rate, deceleration, and flight in a steady wind are obtained York, NY) In Guidance and Control Conference, Palo Alto, Calif, by multiplying simple precalculated functions of time by descent August 7 9, 1978, Technical Papers New York, rate, deceleration or sine and cosine components of the mean wind American Institute of Aeronautics and Astronautics, Inc, 1978, p vector Simulations of approach flights for different wind conditions, 325-331 8refs (AIAA 78-1288) assuming perfect state information in the feedback signal, indicated This report contains a complete description of a learning control satisfactory performance (Author) system designed for the F8-DFBW aircraft The system is parameter- adaptive with the additional feature that it 'learns' the variation of the control system gains needed over the flight envelope It, thus, generates and modifies its gain schedule when suitable data are A78-50203 * # Guidance and navigation for automatic land- available The report emphasizes the novel learning features of the ing, rollout, and turnoff using MLS and magnetic cable sensors S system the forms of representation of the flight envelope and the Pines (Analytical Mechanics Associates, Inc , Jericho. N Y ) and R process by which identified parameters are used to modify the gam M Hueschen (NASA, Langley Research Center, Hampton, Va ) In schedule It contains data taken during piloted real-time 6degree-of- Guidance and Control Conference, Palo Alto, Calif, August 7-9, freedom simulations that were used to develop and evaluate the 1978, Technical Papers New York, American system (Author) Institute of Aeronautics and Astronautics, Inc, 1978, p 393-406 5 refs Contract No NAS1-14311 (AIAA 78-1296) A78-50196 if Close encounters of the aeroservoelastic kind This paper describes the navigation and guidance system L R Felt, L J Huttsell, T E Noll, and D E Cooley (USAF, Flight developed for the TCV B-737, a Langley Field NASA research Dynamics Laboratory, Wright-Patterson AFB, Ohio) In Guidance aircraft, and presents the results of an evaluation during final and Control Conference, Palo Alto, Calif, August 7-9, 1978, approach, landing, rollout and turnoff obtained through a nonlinear Technical Papers New York, American Institute digital simulation A Kalman filter (implemented in square root of Aeronautics and Astronautics, Inc. 1978, p 332-341 23 refs form) and a third order complementary filter were developed and (AIAA 78-1289) compared for navigation The Microwave Landing Systems (MLS) is Aeroservoelasticity involves the interaction between aero- used for all phases of the flight for navigation and guidance In dynamics, structural dynamics, and automatic flight control systems addition, for rollout and turnoff, a three coil sensor which detects It is an increasingly important design and test consideration in the the magnetic field induced by a buried wire in the runway (magnetic synthesis and evaluation of airborne high-gain automatic control leader cable) is used The outputs of the sensor are processed into systems In the present paper, recent Air Force experience is measurements of position and heading deviation from the wire The reviewed which emphasizes the need for aeroservoelastic considera- results show the concept to be both feasible and practical for tions on a variety of research, prototype, and production aircraft commercial type aircraft term mal area control (Author) VP

A78-50200 * ,*' Navigation performance of the Triscan con- A78-50209 * # The effect of prefilter design on sample rate cept for shipboard VTOL aircraft operations L A McGee (NASA, selection in digital flight control systems U Peled and J D Powell Ames Research Center, Moffett Field, Calif), S F Schmidt (Stanford University, Stanford, Calif) In Guidance and Control (Analytical Mechanics Associates, Inc , Mountain View, Calif), and Conference, Palo Alto, Calif, August 7-9, 1978, Technical Papers S K Miyashiro (US Naval Ocean Systems Center, San Diego, New York, American Institute of Aeronautics Calif) In Guidance and Control Conference, Palo Alto, Calif, and Astronautics, Inc, 1978, p 449-454 9 refs Grant No August 7-9, 1978, Technical Papers New York, NsG-4002 (AIAA 78-1308) American Institute of Aeronautics and Astronautics, Inc , 1978, p The effect of prefliters on sample rate selection is examined and 363-373 (AIAA 78-1293) design procedures are determined for obtaining the best combination The paper deals with the Triscan concept a dual-antenna of prefilter breakpoint and sample rate The employed approach microwave landing guidance system, using tnangulation for close-in involves a quantitative comparison of the output noise response of accuracy - developed to facilitate the landing of VTOL aircraft on systems originating from the same basic plant and designed over a ships in all-weather conditions Analysis of the navigation perfor- wide range of prefilters and sample rates Each system design was mance of an onboard system receiving data from Triscan and carefully tailored so that it exhibited approximately identical data-linked information regarding the motion of the ship showed responses to commands The results presented augment the criteria that the approach navigation performance depends on the approach for sample rate selection which have been discussed by Powell and path profile flown, the magnitude of the measurement bias error, and Katz (1975) Attention is given to system characteristics, an the navigation system's knowledge of the shipboard landing pad integrator as a plant, and the short period motion of the F-8 aircraft motion, which was implemented through the concept of a landing G R pad deviation vector V P

A78-50202 * # Approach guidance logic for a tilt-rotor aircraft J Beser (Intermetrics, Inc , Long Beach, Calif) In Guidance and Control Conference, Palo Alto, Calif, August 7-9, 1978, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc , 1978, p 381-392 6 refs Grant No NGL-05-020-007 (AIAA 78-1295) The distinctive feature of a tilt-rotor aircraft is that the pilot can change the rotor mast angles to go from a helicopter configuration for take-off and landing to an airplane configuration for high cruise speeds and vice-versa An approach path for such an aircraft is proposed and the logic required to fly along this path in the presence of wind is determined The mam contribution of this work is an efficient and, to my knowledge, new method for generating the nominal state and control histories taking into account an estimate of the mean wind velocity and direction The method requires the

542 A78-30O46

J S Reaser and P H Kretsmger Jun 1978 272 p refs Sponsored in part by AVRADCOM 3 Vol (Contract NAS1-14570) (NASA-CR-145331 LR-28435-Vol-1) Avail NTIS HC A12/MF A01 CSCL 01A A cotorcraft nonlinear simulation called REXOR II divided into three volumes is described The first volume is a development STAR ENTRIES of rotorcraft mechanics and aerodynamics The second is a development and explanation of the computer code required to implement the equations of motion The third volume is a users manual and contains a description of code input/output as well N78-30O39*# National Aeronautics and Space Administration as operating instructions G Y Langley Research Center Langley Station Va AERODYNAMIC CHARACTERISTICS INDUCED ON A N78-30O43*# Lockheed-California Co Burbank SUPERCRITICAL WING DUE TO VECTORING TWIN REXOR 2 ROTORCRAFT SIMULATION MODEL VOL- NOZZLES AT MACH NUMBERS FROM 0 40 TO 0 95 UME 2 COMPUTER IMPLEMENTATION Final Technical Francis J Capone Aug 1978 115 p refs Report (NASA-CR-78746) Avail NTIS HC A06/MF A01 CSCL 01A J S Reaser and P H Kretsmger Jun 1978 177 p ref The induced lift characteristics are studied for a vectored-thrust Sponsored in part by Avradcom 3 Vol concept in which jet-exhaust nozzles were located in the (Contract NAS1-14570I fuselage at the wing trailing edge The wing had a supercritical (NASA-CR-145332 LR-28435-Vol-2) Avail NTIS airfoil section The investigation was conducted at Mach HC A09/MF A01 CSCL 01A numbers from 04 to 095 angles of attack up to 14 deg and For abstract see N78-30042 thrust coefficients up to 0 35 and nozzle deflection angles of 0 deg and 30 deg Separate force balances were used to determine both total aerodynamic and thrust forces alone which N78-30O44*# Lockheed-California Co Burbank allowed for a direct measurement of jet turning angle at forward REXOR 2 ROTORCRAFT SIMULATION MODEL VOL- speeds The Reynolds number per meter varied from 8 20 x 1 UME 3 USER'S MANUAL Final Technical Report million to 12 80 x 1 million The results show that the configuration J S Reaser and P H Kretsmger Jun 1978 247 p ref .with the supercritical wing generally had a better performance Sponsored in part by AVRADCOM 3 Vol ,with respect to both lift augmentation and drag reduction than (Contract NAS1-14570) the same configuration with a 64 series airfoil G G (NASA-CR-145333 LR-28435-Vol-3) Avail NTIS HC A11/MF A01 CSCL 01A For abstract see N78-30042 N78-30040*# National Aeronautics and Space Administration Langley Research Center Langley Station Va N78-3OO46*# Vought Corp Hampton Va WIND-TUNNEL TESTING OF VTOL AND STOL AIRCRAFT DESIGN OF A LARGE SPAN-DISTRIBUTED LOAD FLYING- Harry H Heyson Jul 1978 81 p refs Presented at the WING CARGO AIRPLANE WITH LAMINAR FLOW CON- Seminar on Aerodyn of V/STOL Aircraft and Helicopters TROL University Park Pa 31 Jul - 4 Aug 1978 W A Lovell J E Price C B Quartero R V Turriziani and G (NASA-TM-78750) Avail NTIS HC A05/MF A01 CSCL 01A F Washburn Jun 1978 45 p refs The basic concepts of wind-tunnel boundary interference are (Contract NAS1-13500) discussed and the development of the theory for VTOL-STOL (NASA-CR-145376) Avail NTIS HC A03/MF A01 CSCL 01A aircraft is described Features affecting the wall interference such A design study was conducted to add laminar flow control as wake roll-up configuration differences, recirculation limits and to a previously design span-distributed load airplane while interference nonuniformity are discussed The effects of the level maintaining constant range and payload With laminar flow control of correction on allowable model size are shown to be amenable applied to 100 percent of the wing and vertical tail chords the to generalized presentation Finally experimental confirmation of empty weight increased by 4 2 percent the drag decreased by wind-tunnel interference theory is presented for jet-flap rotor 27 4 percent the required engine thrust decreased by and fan-m-wmg models Author 148 percent, and the fuel consumption decreased by 21 8 percent When laminar flow control was applied to a lesser extent N78-30041*# National Aeronautics and Space Administration of the chord (approximately 80 percent) the empty weight Langley Research Center Langley Station Va increased by 3 4 percent the drag decreased by 20 0 percent STATUS OF AERIAL APPLICATIONS RESEARCH IN THE the required engine thrust decreased by 13 0 percent and the LANGLEY VORTEX RESEARCH FACILITY AND THE fuel consumption decreased by 162 percent In both cases the LANGLEY FULL-SCALE WIND TUNNEL required take-off gross weight of the aircraft was less than the Frank L Jordan H Clyde McLemore and Michael B Bragg original turbulent aircraft Author (Illinois Univ) Aug 1978 12 p refs (NASA-TM-78760) Avail NTIS HC A02/MF A01 CSCL 01A N78-30O46*# National Aeronautics and Space Administration Small scale models of agricultural airplanes were tested and Langley Research Center Langley Station Va numerical methods were utilized to study interactions between SHOCKLESS AIRFOILS WITH THICKNESSES OF 206 AND the airplane wake and the dispersed spray and granular materials 207 PERCENT CHORD ANALYTICALLY DESIGNED FOR Methods were developed to measure and predict dispersal A MACH NUMBER OF 068 AND A LIFT COEFFICIENT transport and wake characteristics and dispersal techniques to OF 040 obtain interactions more favorable to wide uniform deposition Dennis O Allison May 1976 38 p refs patterns and reduced drift In the full scale wind tunnel full (NASA-TM-X-73917) Avail NTIS HC A03/MF A01 CSCL scale agricultural airplanes and dispersal systems for both liquid 01A and solid applications were evaluated to improve aircraft A 20 8 percent-thick airfoil shape was designed to have aerodynamics and dispersal systems efficiency The program shockless inviscid flow at a Mach number of 0 68 and a lift status in these two facilities is reported with emphasis on wake coefficient of 0 40 In order to determine the actual airfoils which interactions and dispersal systems research G G would yield this same shockless flow when viscous effects are included boundary layer displacement thicknesses were subtracted N78-30042*# Lockheed-California Co Burbank from the inviscid shape for Reynolds numbers of 100 and 35 REXOR 2 ROTORCRAFT SIMULATION MODEL VOL- million This process yielded airfoils with thicknesses of 20 7 UME 1 ENGINEERING DOCUMENTATION Final Technical and 206 percent respectively Subtraction of boundary layer Report displacement thicknesses for Reynolds numbers below 35 million

543 A7830O48

yielded nonphysical airfoils that is airfoils with negative thickness- distributions and total lift and pitchmg-moment coefficients on es near tHe trailing edge The pitching moment about the swept and unswept USB configurations are included A wide quarter-chord point at the design condition was -0 082 for the range of thrust coefficients and flap deflection angles were mviscid shape and consequently for both airfoils Off-design considered at angles of attack up to the onset of stall S B S calculations for the two airfoils were made using a computer program which provides for the interaction of the mviscid flow and boundary layer solutions The pressure distributions of the airfoils were shockless for conditions from the design point to N78-30O61*# McDonnell-Douglas Corp St Louis Mo lower Mach numbers and lift coefficients No boundary layer MODIFICATION OF THE DOUGLAS NEUMANN PROGRAM separation was predicted except in the last 3 percent chord on TO IMPROVE THE EFFICIENCY OF PREDICTING COMPO- the upper surface Author NENT INTERFERENCE AND HIGH LIFT CHARACTERISTICS Final Report D R Bnstow and G G Grose Aug 1978 126 p refs N78-30O48*# Bthrle Applied Research Inc Jericho N Y (Contract NAS1-14756) STATIC AERODYNAMIC CHARACTERISTICS OF A (NASA-CR-3020) Avail NTIS HC A07/MF A01 CSCL 01A TYPICAL SINGLE-ENGINE LOW-WING GENERAL AVIATION The Douglas Neumann method for low-speed potential flow DESIGN FOR AN ANGLE OF-ATTACK RANGE OF -8 DEC on arbitrary three-dimensional lifting bodies was modified by TO 90 DEC substituting the combined source and doublet surface paneling William Bihrle Jr Billy Barnhart and Paul Pantason Jul 1978 based on Green s identity for the original source panels Numerical 466 p refs studies show improved accuracy and stability for thin lifting (Contract NAS1-14849) surfaces permitting reduced panel number for high-lift devices (NASA-CR-2971) Avail NTIS HC A20/MF A01 CSCL 01A and supercritical airfoil sections The accuracy of flow in concave Static force data obtained at the NASA Ames Research corners is improved A method of airfoil section design for a Center 12 foot Pressure Tunnel are presented in plotted form given pressure distribution, based on Green's identity was for a 1/7 scale, single-engine low-wing general aviation airplane demonstrated The program uses panels on the body surface model The configurations tested included the basic airplane, with constant source strength and parabolic distribution of various airfoil shapes tail designs fuselage slrakes and fuselage doublet strength and a doublet sheet on the wake The program modifications as well as airplane components The test conditions is written for the CDC CYBER 175 computer Results of included an angle-of-attack and sideslip range of -8 to 90 and calculations are presented for isolated bodies wings, wing-body -10 to 30 degrees, respectively at a Mach number of 0 2 for combinations and internal flow Author Reynolds numbers of 288000 and 3450000 The data are presented without analysis Author N78-30053*# National Aeronautics and Space Administration N78-30O49*# Bihrle Applied Research Inc Jericho N Y Langley Research Center, Langley Station Va ROTARY BALANCE DATA FOR A TYPICAL SINGLE-ENGINE STATIC AERODYNAMIC CHARACTERISTICS OF A LOW-WING GENERAL AVIATION DESIGN FOR AN WINGED SINGLE-STAGE-TO-ORBIT VEHICLE AT MACH ANGLE-OF-ATTACK RANGE OF 30 DEG TO 90 DEC NUMBERS FROM 03 TO 463 William Bihrle Jr Randy S Hultberg and William Mulcay Jul Delma C Freeman and Roger H Fournier Aug 1978 119 p 1978 446 p refs refs (Contract NAS1-14849) (NASA-TP-1233, L-12200) Avail NTIS HC A06/MF A01 (NASA-CR-2972) Avail NTIS HC A19/MF A01 CSCL01A CSCL 01A Aerodynamic characteristics obtained in a spinning flow The Langley 8 foot transonic pressure tunnel and the Langley environment utilizing a rotary balance located spin tunnel are Unitary Plan wind tunnel used to determine the longitudinal and presented in plotted form for a 1/5 scale single-engine low-wing lateral-directional aerodynamic characteristics of a winged general aviation airplane model The configurations tested include single-state-to-orbit vehicle was investigated The model was the basic airplane various airfoil shapes tail designs, fuselage tested over a Mach number range from 03 to 463 for an strakes and modifications as well as airplane components Data angle-of-attack range from 4 to 30 D at both 0 and 5 D are presented for pitch and roll angle ranges of 30 to 90 degrees sideslip S E S and 10 to -10 degrees respectively and clockwise and counter-clockwise rotations covering an Omega b/2V range from N78-30054*# National Aeronautics and Space Administration 0 to 9 The data are presented without analysis Author Langley Research Center Langley Station Va APPROXIMATE INDICIAL LIFT FUNCTION FOR TAPERED. N78-30050*# Neilsen Engineering and Research Inc Mountain SWEPT WINGS IN INCOMPRESSIBLE FLOW View Calif M J Queijo. William R Wells (Wright State Univ Dayton, Ohio), CALCULATION OF THE LONGITUDINAL AERODYNAMIC and Dmesh A Keskar (Cincinnati Univ. Ohio) Aug 1978 32 p CHARACTERISTICS OF UPPER-SURFACE-BLOWN WING- refs FLAP CONFIGURATIONS Final Report (NASA-TP-1241 L-12110) Avail NTIS HC A03/MF A01 Michael R Mendenhall and Selden B Spangler Aug 1978 CSCL 01A 83 p refs An approximate mdicial lift function associated with circulation (Contract NAS1-14086) was developed for tapered, swept wings in incompressible flow (NASA-CR-3004 NEAR-TR-157) Avail NTIS The function is derived by representing the wings with a simple HC A05/MF A01 CSCL 01A vortex system The results from the derived equations compare An engineering method for predicting the longitudinal well with the limited available results from more rigorous and aerodynamic characteristics of wing-flap configurations with upper complex methods The equations, as derived are not very surface blowing (USB) was developed Potential flow models convenient for calculating the dynamic response of aircraft, were incorporated into the prediction method a wing and flap parameter extraction or for determining frequency-response curves lifting surface model and a jet wake model The wing-flap model for wings Therefore, an expression is developed to convert the used a vortex-lattice to represent the wing and flaps The wing mdicial response function to an exponential form which is more had an arbitrary planform and camber and twist and the flap convenient for these purposes Author system was made up of a Coanda flap and other flap segments of arbitrary size The jet wake model consisted of a series of closely spaced rectangular vortex rings The wake was positioned N78-30056*# National Aeronautics and Space Administration such that it was tangent to the upper surface of the wing and Langley Research Center Langley Station Va flap between the exhaust nozzle and the flap trailing edge It THEORETICAL ESTIMATION OF THE TRANSONIC AER- was specified such that the mass momentum and spreading ODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL- rates were similar to actual USB jet wakes Comparisons of WING TRANSPORT MODEL WITH TRAILING-EDGE measured and predicted pressure distributions span load CONTROLS

544 A78 30069

James M Lucknng and Michael J Mann Aug 1978 34 p the jet which is associated with the camber does not produce a refs lift increment due to blowing which is significantly larger than (NASA-TP-1253 L-11257) Avail NTIS HC A03/MF A01 the increment produced by the same blowing momentum on a CSCL 01A plane wing However the drag for a given lift when blowing is A method for rapidly estimating the overall forces and introduced is greatly reduced and in some cases a negative moments at supercritical speeds below drag divergence of drag is predicted Author (ESA) transport configurations with supercritical wings is presented The method was also used for estimating the rolling moments N78-30O65# Cambridge Univ (England) Engineering Dept due to the deflection of wing trailmg-edge controls This analysis LINEARIZED SUPERSONIC UNSTEADY FLOW IN CAS- was based on a vortex-lattice technique modified to approximate CADES the effects of wing thickness and boundary-layer induced camber T Nagashima and D S Whitehead London Aeron Res Council Comparisons between the results of this method and experiment 1978 39 p refs Supersedes ARC-37198 indicate reasonably good correlation of the lift pitching moment (ARC-R/M-3811 ARC-37198 BR61587) Avail NTIS and rolling moment The method required much less storage HC A03/MF A01 HMSO £4, PHI $1530 and run time to compute solutions over an angle-of-attack range A linearized theory is presented for the calculation of force than presently available transonic nonlinear methods require for and moment coefficients for two-dimensional cascades of blades a single angle-of-attack solution S E S in supersonic flow The cases of both supersonic and subsonic axial velocity are treated The perturbations are due to bending vibration torsional vibration and wakes shed from moving N78-30067*# National Aeronautics and Space Administration obstructions upstream The method leads to analytical results in Lewis Research Center, Cleveland Ohio the quasi-steady case and to a fast computer program for the general unsteady case Results are in good agreement with PERFORMANCE WITH AND WITHOUT INLET RADIAL previous work The method can be used to predict forced vibration DISTORTION OF A TRANSONIC FAN STAGE DESIGNED FOR REDUCED LOADING IN THE TIP REGION and flutter in transonic fan blades Author (ESA) James F Schmidt and Robert S Ruggen Aug 1978 84 p refs N78-30O66# Queen Mary Coll London (England) (NASA-TP-1294 E-9246) Avail NTIS HCA05/MFA01 CSCL A MEAN CAMBERLINE SINGULARITY METHOD FOR 01A TWO-DIMENSIONAL STEADY AND OSCILLATORY AERO- A transonic compressor stage designed for a reduced loading FOILS AND CONTROL SURFACES IN INVISCID INCOM- in the tip region of the rotor blades was tested with and without PRESSIBLE FLOW inlet radial distortion The rotor was 50 cm in diameter and B C Basu Aeron Res Council 1978 54 p refs Supersedes designed for an operating tip speed of 420 m/sec Although QMC-EP-1019" ARC-37207 the rotor blade loading in the tip region was reduced to provide (ARC-CP-1391 QMC-EP-1019 ARC-37207) Avail NTIS additional operating range, analysis of the data indicates that HC A04/MF A01 HMSO £.2 50 PHI $9 70 the flow around the damper appears to be critical and limited A numerical method has been developed to calculate the the stable operating range of this stage For all levels of tip and pressure distribution on the surface of steady and oscillating hub radial distortion there was a large reduction in the rotor airfoils in incompressible mviscid flow In this method singularities stall margin Author are placed on the mean camber line of the airfoil and the boundary condition of tangency of flow is satisfied on the surface of the N78-30O68/J/ Air Force Flight Dynamics Lab Wright-Patterson airfoil Problems considered include steady single airfoils with AFB. Ohio and without control surfaces a cascade of airfoils airfoils oscillating in pitch airfoils oscillating in heave airfoils in harmonic A CALCULATOR PROGRAM FOR ANALYZING AIRLOADS ON A WING OF ARBITRARY PLANFORM AND CAMBER travelling gusts and control surface oscillations Comparison with IN SUBSONIC FLOW Final Report. 1 Apr 31 Aug 1976 analytic solutions and other numerical methods where available John C Sparks Jan 1978 53 p refs are good The main advantages of this method are the relatively (AD-A054180 AFFDL-TR-77-136) Avail NTIS fast computing times and the fact that the method converges HC A04/MF A01 CSCL 20/4 satisfactorily in the limit of zero airfoil thickness Author (ESA) A subsonic airloads program for small (8-K) calculators is presented Features include good man-machine interaction and quick turn-around which speed preliminary design The program N78-30O68# Queen Mary Coll London (England) Oept of is written in BASIC for the HP9830 or HP9831 calculator Aeronautical Engineering systems equipped with Matrix ROM and 9862A plotter TWO-DIMENSIONAL AEROFOILS AND CONTROL SUR- Programming techniques illustrated may be applied to any small system having special function keys or an equivalent capability FACES IN SIMPLE HARMONIC MOTION IN IN- COMPRESSIBLE INVISCID FLOW Author (GRA) B C Basu and G J Hancock Aeron Res Council 1978 62 p refs Supersedes ARC-37204 (ARC-CP-1392 ARC-37204) Avail NTIS HC A04/MF A01 N78-30064| Liverpool Univ (England) HMSO £3 PHI $11 55 CALCULATIONS OF THE EFFECTS OF BLOWING FROM A numerical method developed for the calculation of the THE LEADING EDGES OF A CAMBERED DELTA WING two-dimensional potential flow about an airfoil of arbitrary shape J E Barsby London Aeron Res Council 1978 53 p refs undergoing small amplitude simple harmonic motions is described Supersedes ARC-36252 Sponsored in part by Sci Res Council Problems considered include airfoils oscillating in pitch airfoils and Univ of East Anglia, Engl oscillating in heave airfoils in harmonic travelling gusts and control (ARC-R/M-3800 ARC-36252 BR61584) Avail NTIS surface oscillations Comparison with analytic solutions where HC A03/MF A01 HMSO £526. PHI $2020 available, is good Significant differences between linear and The thin jet model applied to the study of the jet flap is non-linear theory are shown especially for the m-phase hinge combined with the vortex sheet model applied to the study of moment coefficients Author (ESA) leading-edge separation to study the effect of blowing from the leading-edges of a cambered wing The numerical techniques used to solve problems of leading-edge separation were improved, and in the present investigation solutions were generated for various values of the lift, camber and blowing strength of the jet whose direction is restricted to lie in a plane normal to the N78-30069*| Virginia Univ Charlottesville Research Labs free stream Regions existed in the parameter space within which for the Engineering Sciences solutions could not be obtained and there were regions within DEMAND MODELLING OF PASSENGER AIR TRAVEL AN which solutions were not unique The downward deflection of ANALYSIS AND EXTENSION. VOLUME 2 Final Report

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I D Jacobson Aug 1978 151 p refs below the optimum cruise energy The existence of such a cruise (Grant NsG-7266) segment depends primarily on the fuel flow vs thrust characteristics (NASA-CR-157402 UVA/528148/MAE78/101) Avail NTIS and on thrust constraints If thrust is a free control variable HC A08/MF A01 CSCL01C along with airspeed it is shown that such cruise segments will Previous intercity travel demand models in terms of their not generally occur If thrust is constrained to some maximum ability to predict air travel in a useful way and the need for value in climb and to some minimum in descent such cruise disaggregation in the approach to demand modelling are evaluated segments generally will occur Computer calculations of typical The viability of incorporating non-conventional factors (i e short-range trajectories obtained about a 1% cost penalty for non-econometric such as time and cost) in travel demand constraining the thrust Author forecasting models are determined The investigation of existing models is carried out in order to provide insight into their strong N78-30O73*# National Aeronautics and Space Administration points and shortcomings The model is characterized as a market Langley Research Center Langley Station Va segmentation model This is a consequence of the strengths of DESCRIPTION AND PERFORMANCE OF THE LANGLEY disaggregation and its natural evolution to a usable aggregate VISUAL LANDING DISPLAY SYSTEM formulation The need for this approach both pedagogically and John D Rollins Aug 1978 74 p refs mathematically is discussed In addition this volume contains (NASA-TM-78742) Avail NTIS HC A04/MF A01 CSCL17G two appendices which should prove useful to the non-specialist A television/model board system is described which provides in the area G Y a means of generating a six-degree-of-freedom visual out-the- window scene for the pilot of a simulated aircraft The hardware N78-30070*# Aeronautical Research Foundation Cambridge and its performance of capability for meeting the visual Mass requirements for a wide range of simulation studies are detailed REQUIREMENTS FOR REGIONAL SHORT-HAUL AIR Also included is a description of the computer software required SERVICE AND THE DEFINITION OF A FLIGHT PROGRAM for the system An example of software implementation in a TO DETERMINE NEIGHBORHOOD REACTIONS TO SMALL real-time computer program is provided G G TRANSPORT AIRCRAFT Kernel Feher Lynn Bolhnger Jeffrey V Bowles and Mark H N78-30074*# National Aeronautics and Space Administration Waters Aug 1978 153 p refs Prepared in cooperation with Langley Research Center Langley Station Va NASA AMES Res Center Moffett Field Calif FLIGHT DEMONSTRATIONS OF CURVED. DESCENDING (Contract NAS2-9050) APPROACHES AND AUTOMATIC LANDINGS USING TIME (NASA-CR-152151) Avail NTIS HC A08/MF A01 CSCL REFERENCED SCANNING BEAM GUIDANCE 05C William F White comp May 1978 269 p refs An evaluation of the current status and future requirements (NASA-TM-78745) Avail NTIS HCA12/MFA01 CSCL17G of an mtraregional short haul air service is given A brief definition The Terminal Configured Vehicle (TCV) program operates a of the different types of short haul air service is given This is Boeing 737 modified to include a second cockpit and a large followed by a historical review of previous attempts to develop amount of experimental navigation guidance and control short haul air service in high density urban areas and an equipment for research on advanced avionics systems Demonstra- assessment of the current status The requirements for mtrare- tion flights to include curved approaches and automatic landings gional air service the need for economic and environmental were tracked by a phototheodolite system For 50 approaches viability and the need for a flight research program are defined during the demonstration flights the following results were A detailed outline of a research program that would determine obtained the navigation system using TRSB guidance delivered urban community reaction to frequent operations of small transport the aircraft onto the 3 nautical mile final approach leg with an aircraft is also given Both the operation of such an experiment average overshoot of 25 feet past centerhne subjet to a 2-sigma in a specific region (San Francisco Bay area) and the necessary dispersion of 90 feet Lateral tracking data showed a mean design modifications of an existing fixed wing aircraft which error of 4 6 feet left of centerlme at the category 1 decision could be used in the experiment are established An estimate is made of overall program costs G Y height (200 feet) and 2 7 feet left of centerlme at the category 2 decision height (100 feet) These values were subject to a N78-30071# Federal Aviation Administration Washington DC Sigma dispersion of about 10 feet Finally the glidepath tracking errors were 2 5 feet and 3 0 feet high at the category 1 and 2 Wind Shear/WVAS Branch decision heights respectively with a 2 sigma value of 6 feet ENGINEERING AND DEVELOPMENT PROGRAM PLAN WAKE VORTEX GG Dec 1977 6 p refs (AD-A051143. FAA-ED-21-1A) Avail NTIS N78-30075# National Aviation Facilities Experimental Center HC A02/MF A01 CSCL 01/5 Atlantic City N J The design, development testing and prototyping of a system TRSB MICROWAVE LANDING SYSTEM DEMONSTRATION to increase runway capacity by minimizing wake vortex effects PROGRAM AT BRUSSELS. BELGIUM Final Report, as an impediment to efficient and effective traffic management 20 Jan - 6 Feb 1978 in the terminal environment are discussed Major work areas Feb 1978 84 p were vortex advisory system wake vortex avoidance system, (AD-A054298 FAA-NA-78-18 FAA-RD-78-18) Avail NTIS and vortex alleviation research S B S HC A05/MF A01 CSCL 01/5 The sixth in a series of FAA conducted operational demonstrations of several TRSB system configurations at selected airports N78-30O72'# National Aeronautics and Space Administration in the United States and abroad are reported The basic wide Ames Research Center Moffett Field Calif aperture TRSB was installed to service runway 07L which was CHARACTERISTICS OF CONSTRAINED OPTIMUM the longest of three major runways at the airport Operational TRAJECTORIES WITH SPECIFIED RANGE demonstrations and data acquisition flights were made using Heinz Erzberger and Homer Lee Sep 1978 39 p refs FAA CV-880 and B-727 aircraft One-third of the landings were (NASA-TM-78519 A-7592) Avail NTIS HC A03/MF A01 autoland Flight profiles included straight-m and curved approac- CSCL 17G hes radials and partial orbits Results of the operational Necessary conditions of optimality are derived for traiectones demonstrations indicate that the performance of the TRSB whose structure is limited to climb steady cruise and descent basic wide system configuration meets the ICAO full capability segments The performance function consists of the sum of fuel system requirements B B and time 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 N78-30078# Facility Checking Squadron (1866th) (AFCS). Scott the optimum cruise energy for sufficiently large range At short AFB III ranges (500 n mi and less) a cruise segment may also occur TRACALS EVALUATION REPORT TACAN, VOR. AND ILS

546 A7830O90

STATION EVALUATION REPORT, ANDERSEN AFB. GUAM Louise C Speitel Ray E Feher and Joe C Spurgeon Mar Final Report. 25 Jul - 15 Aug 1977 1978 34 p refs Paul W Nix 12 Apr 1978 253 p (AD-A054811 FAA-NA-77-22) Avail NTIS (AD-A054244 Rept-77/66N-107) Avail NTIS HC A03/MF A01 CSCL 01/3 HC A12/MF A01 CSCL 17/7 Twelve aircraft interior materials were burned under standard This evaluation report presents data collected and analyzes flaming combustion conditions in a smoke chamber Each material capabilities and limitations of the Andersen AFB TACAN was also exposed to 600 Celsius in a combustion tube furnace (AN/GRN-19A) VOR (AN/FRN-38) ILS (AN/MRN-7A/8A) and under conditions of oxidative pyrolysis The combustion products their associated power systems The evaluation was conducted were collected m liquid-filled impingers and the contents were from 25 July to 15 August 1977 The results of the evaluation analyzed for hydrogen cyanide hydrogen sulfide hydrogen indicate that all the facilities are capable of providing satisfac- chloride hydrogen bromide and formaldehyde by differential tory service The data presented in this report can be used as pulse polarography nitrogen dioxide and sulfur dioxide by visible a valid guide to anticipated performance until there is a significant spectrophotometry and hydrogen fluoride by ion-selective change in ground equipment siting or screening Author (GRA) electrode Carbon monoxide was measured directly by a nondispersive infrared analyzer The yields of the nine gases are N78-30079jfl Anne Research Corp Annapolis Md reported in terms of milligrams per gram of material The toxic EVALUATION OF METHODS FOR CALCULATING SYSTEM gas yields were obtained for each material in the smoke chamber OPERATING TIME IN ACCORDANCE WITH RELIABILITY and compared to the yields obtained in the combustion tube IMPROVEMENT WARRANTY (RIW) CONTRACTUAL TERMS furnace The yields were also compared to those obtained using Final Report. 15 Aug 1977 - 15 Feb 1978 colorimetric detector tubes The extent of the correlation of the A A Bilodeau and P M Dallosta Mar 1978 192 p refs various procedures is reported The relative yields of HCI HCN (Contract F09603-77-A-3104) and H2S were found to be somewhat independent of the exposure (AD-A054822 Rept-1928-01-1-1704) Avail NTIS conditions The relative yields of the oxidized gases CO HCHO HC A09/MF A01 CSCL 17/7 N02 and SO2 are much more dependent on the exposure Armc Research Corporation conducted a six-month study to conditions G G investigate the validity of contractual techniques for calculating warranty statistics for the AN/ ARN-118 V TACAN TACAN N78-3OO89*# National Aeronautics and Space Administration field data were collected from eleven U S Air Force Bases by Langley Research Center Langley Station Va Armc Research Additional TACAN data submitted by the Air EVALUATION OF SEVERAL SECONDARY TASKS IN THE Force were used in support of this study Average Operating DETERMINATION OF PERMISSIBLE TIME DELAYS IN Time AOT Total Operating Hours TOH and Mean Time Between SIMULATOR VISUAL AND MOTION CUES Failures MTBF based on these field data were compared with G Kimball Miller Jr and Donald R Riley Aug 1978 68 p the values of these parameters calculated by contractual methods refs No significant differences between field data estimates and the (NASA-TP-1214 L-12006) Avail NTIS HC A04/MF A01 contractual-methods of calculation were identified Author (GRAI CSCL 05H The effect of secondary tasks in determining permissible time N78-30O80# Anne Research Corp Annapolis Md delays in visual-motion simulation of a pursuit tracking task was AVIONICS COST DEVELOPMENT FOR ALTERNATIVES OF examined A single subject a single set of aircraft handling SELECTED AIR TRAFFIC CONTROL SYSTEMS qualities and a single motion condition in tracking a target aircraft Final Report that oscillates smusoidally in altitude were used In addition to S H Kowalski Oct 1977 71 p refs the basic simulator delays the results indicate that the permissible (Contract DOT-FA76WA-3788) time delay is about 250 msec for either a tapping task an (AD-A054823 Rept-1326-01-3-1758) Avail NTIS adding task or an audio task and is approximately 125 msec HC A04/MF A01 CSCL 17'7 less than when no secondary task is involved The magnitudes This report presents the results of the cost analysis of avionics of the primary task performance measures however differ only required in support of the Upgraded Third Generdtion Air Traffic for the tapping task A power spectraldensity analysis basically Control developments The systems considered were re- confirms the result by comparing the root-mean-square perform- commended for evaluation by the Office of Systems Engineer- ance measures For all three secondary tasks the total pilot ing Management of the FAA The costs of avionics were developed workload was quite high S B S with the aid of a pricing model to provide comparative evaluations based on uniform paran.etnc data varying only in system-peculiar descriptors Author (GRA)

N78-30087*# National Aeronautics and Space Administration N78-30O90*# National Aeronautics and Space Administration Langley Research Center Langley Station Va Langley Research Center Langley Station Va STABILITY AND PERFORMANCE CHARACTERISTICS OF SIMULATOR STUDY OF THE EFFECT OF VISUAL-MOTION A FIXED ARROW WING SUPERSONIC TRANSPORT TIME DELAYS ON PILOT TRACKING PERFORMANCE WITH CONFIGURATION (SCAT 1SF-9898) AT MACH NUMBERS AN AUDIO SIDE TASK FROM 0 60 TO 1 20 Donald R Riley and G Kimball Miller Jr Aug 1978 74 p John P Decker and Peter F Jacobs Jun 1978 354 p refs refs (NASA-TM-78726) Avail NTIS HCA16/MFA01 CSCL01C (NASA-TP-1216 L-11996) Avail NTIS HC A04/MF A01 Tests on a 0015 scale model of a supersonic transport CSCL 05H were conducted at Mach numbers from 0 60 to 1 20 Tests of The effect of time delay was determined in the visual and the complete model with three wing planforms two different motion cues in a flight simulator on pilot performance in tracking leading-edge radii and various combinations of component a target aircraft that was oscillating smusoidally in altitude only parts, including both leading- and trailmg-edge flaps were made An audio side task was used to assure the subject was fully over an angle-of-attack range from about -6 deg to 13 deg and occupied at all times The results indicate that within the test at sideslip angles of 0 deg and 2 deg Author grid employed about the same acceptable time delay (250 msec) was obtained for a single aircraft (fighter type) by each of two N78-30088# National Aviation Facilities Experimental Center subjects for both fixed-base and motion-base conditions Atlantic City. N J Acceptable time delay is defined as the largest amount of delay A PRELIMINARY COMPARISON OF THERMAL DECOM- that can be inserted simultaneously into the visual and motion POSITION PRODUCTS OF AIRCRAFT INTERIOR MATERI- cues before performance degradation occurs A statistical analysis ALS USING THE NATIONAL BUREAU OF STANDARDS of the data was made to establish this value of time delay SMOKE CHAMBER AND THE COMBUSTION TUBE Audio side task provided quantitative data that documented the FURNACE subject s work level S E S

547 A78-30091

N78-30091# Princeton Univ N J Dept of Aerospace and various levels in order to study the damping characteristics for Mechanical Sciences each ply of the laminate utilizing strain recordings The strain A STUDY OF THE PRECISION HOVER CAPABILITIES OF responses were checked for accuracy with respect to theoretical THE AEROCRANE HYBRID HEAVY LIFT VEHICLES strains calculated as a function of the applied loads GRA Final Report H C Curtiss Jr W F Putnam and R M McKilhp Jr Feb N78-30O94# Air Force Flight Dynamics Lab Wright-Patterson 1978 144 p refs AFB, Ohio (Contract N62269-77-C 0074 WF4141 1000) COMPUTER PROGRAM FOR VIBRATION PREDICTION OF (AD-A054281 AMS-TR-1363 NADC-76341-30) Avail NTIS FIGHTER AIRCRAFT EQUIPMENTS Final Report. 21 Mar HC A07/MF A01 CSCL 01/3 1976 - 15 Apr 1977 An analytical study of the precision hover capabilities of the Robert W Sevy and Mark N Haller Nov 1977 218 p refs AEROCRANE based on equations of motion verified by flight (AF Proj 6146) tests of a dynamic model is described Two methods of control (AD-A054598 AFFDL-TR-77-101) Avail NTIS (cyclic pitch and wmglets) are examined A real time simulation HC A10/MF A01 CSCL 01/3 of the tasks of hovering a proposed large AEROCRANE in gusts This study details in-house efforts that culminate in a computer and translating from point to point was conducted to evaluate program for the prediction of vibration inputs to equipments the two control methods and to compaie the AEROCRANE with mounted in fighter aircraft The computer format is orchestrated proposed large helicopters The stability and control characteristics about a basic function whose thematic variations are invoked to of large AEROCRANES are compared with those of proposed describe boundary layer excitations and to synthesize a sequence large helicopters and the helicopter handling qualities specifica- of transfer functions whose operations in turn, define the resultant tions The results of the study indicate that wmglets provide a vibration spectrum beginning at the aircraft surface and very effective means of hover control With cyclic control the proceeding inward to the designated equipment Program inputs precision hover capabilities of the AEROCRANE are similar to specify flight conditions aircraft structural classes equipment helicopters of equivalent gross weight Extrapolation of helicopter weight equipment locational coordinates and mounting categories handling qualities specifications to large gross weight characteristic in order to characterize vibration inputs of fighter aircraft of proposed large AEROCRANES indicates that the configurations equipments during flight attitudes ranging from straight and level studied can meet these specifications Certain aspects of hovering states to a variety of significant flight maneuvers and phases control which are characteristic of any vehicle which derives an Program outputs digital and graphical are designed to provide appreciable portion of its lift from buoyancy and carries a heavy the direct spectral information necessary to assemble sequential sling load are examined Author (GRA) vibration histories corresponding to fighter aircraft mission profiles Author (GRA) N78-30O92jf North Carolina State Univ Raleigh Dept of Mechanical and Aerospace Engineering N78-30O95# Boeing Vertol Co Philadelphia Pa INVESTIGATION Of A WING-ROTOR INTERACTION HELICOPTER TRANSMISSION VIBRATION AND NOISE SYSTEM FOR HELICOPTERS Final Report. 1 Sep 1973 - REDUCTION PROGRAM VOLUME 2 USER'S MANUAL 31 Dec 1977 Final Report. Jun 1974 - Oct 1977 Fred R DeJarnette Neal T Frmk Mohammad A Takallu Steven John J Sciarra Robert W Howells Joseph W Lenskt Jr and L Griffith and James J Murray 6 Mar 1978 67 p refs Raymond J Drago Mar 1978 430 p refs (Grants DAHC04-74-G-0007 DAHC04-75-G-0023 (Contract DAAJ02-74-C-0040. DA Proj 1G2-62207-AH-8902) DAAG29-76-G-0045 DAAG29-76-G-0318I (AD-A054827 D210-11236-2-Vol-2. USARTL-TR-78-2B) Avail (AD-A054093 ARO-119452-E ARO-13572-E) Avail NTIS NTIS HCA19/MFA01 CSCL 01/3 HC A04/MF A01 CSCL 20/4 The objective of the Helicopter Transmission Vibration/ Noise This research includes experimental and analytical investiga- Reduction Program was to generate analytical tools for the tions to determine if favorable interference effects could be prediction and reduction of helicopter transmission vibration/noise obtained from a wing-rotor interaction system Lift and drag that provide the capability to perform trade studies during the forces were measured on a wing mounted in a cantilever fashion design stage of a program Application of this optimization from the wall and on a proprotor positioned above the wing on capability yields drive tram components that are dynamically quiet a shaft which ran through the ceiling of the test section Test with reduced vibration/noise levels and inherently longer life results showed significant increases in lift and decreases in drag The work conducted under this program is highly computer- for both the wing and the proprotor due to favorable interfer- oriented and makes extensive use of several computer programs ence effects The analytical investigation developed a new lifting as indicated in the technical report (Volume I) This User's Manual surface theory for subsonic wings which can also be interpreted describes these computer programs, presents rationale for their as a vortex lattice method Results were found to be more use and discusses their application Author (GRA) accurate and converge faster than conventional vortex lattice methods The accuracy compared well with other lifting surface theories but with much smaller computational times GRA N78-30O97# Royal Aircraft Establishment Farnborough N78-3OO93# Douglas Aircraft Co Inc Long Beach Calif (England) DAMPING. STATIC. DYNAMIC. AND IMPACT CHARACTER- DIVERSE FORMS AND DERIVATIONS OF THE EQUATIONS ISTICS OF LAMINATED BEAMS TYPICAL OF WINDSHIELD OF MOTION OF DEFORMABLE AIRCRAFT AND THEIR CONSTRUCTION Final Report. Jul 1975 - Nov 1976 MUTUAL RELATIONSHIP G F Rhodes Dec 1977 279 p refs D L Woodcock Jun 1977 123 p refs (Contract F33615-75-C-3105 AF Pro] 2202) (RAE-TR-77077 BR59543) Avail NTIS HC A06/MF A01 (AD-A054463 MDC-J6944 AFFDL-TR-76-156) Avail NTIS The equations of motion of an aircraft for small perturba- HC A13/MF A01 CSCL 11/9 tions from flight with constant linear and zero angular velocities, This eight section report contains the test plans test results are developed in detail using constant-velocity or body-fixed axes and analyses for a series of monolithic and laminated transparent encastre or free-free modes displacement or velocity body freedom beams which represent aircraft windshield segments A method coordinates The relationship is clearly stated between these of imbedding strain gages mounting strain gages and the various forms, and with other proposed forms, in particular those application of thermocouples is described The method of data using mean-body axes Author (ESA) collection was assessed for data reduction that could provide stress-strain relationships These relationships were used for the N78-30O98# Royal Aircraft Establishment Bedford (England) determination of energy transfer, dynamic response and Structures Dept displacements due to applied loads Selected portions of the FLIGHT MEASUREMENTS OF THE EFFECTS OF SIMU- test data were correlated with data output in a math model LATED LEADING-EDGE EROSION ON HELICOPTER BLADE representation of test specimens noted in Section 9 of AFFDL-TR- STALL. TORSIONAL LOADS AND PERFORMANCE 77-1 Eleven cantilevered damping specimens were tested at P Brotherhood and D W Brown London Aeron Res Council

548 N78-30110

1978 31 p refs Supersedes RAE~-TR-76039 ARC-37053 and principle reasons for the discontinuation of fixed winged (ARC-R/M-3809 RAE-TR-76039 ARC-37053) Avail NTIS aircraft for combat were illustrated Transl by B B HC A03/MF A01 HMSO£350 PHI $13 45 The leading edges of the main rotor blades of a Wessex N78-30107# Air Force Flight Dynamics Lab Wright-Patterson helicopter were artificially roughened to simulate light to moderate AFB Ohio erosion of unprotected light alloy blades Pitch link loads were SUPERCRUISER FIGHTER ANALYSIS measured in forward flight for various spanwise extents of L Earl Miller and Valentine Dahlem III In AGARD Fighter leading-edge roughness and the values of forward speed at which Aircraft Design Jun 1978 16 p a pre-set limit of oscillatory pitch link load was reached were determined This limit was set so as to avoid excessive fatigue Avail NTIS HC A13/MF A01 damage to the modified control linkage With a representative A fighter aircraft that cruises efficiently at supersonic length of roughness the speed at which the limit load occurred speeds and is effective in air to air combat is considered was reduced by 24 kn This marked reduction was associated Supersonic cruise performance and transonic maneuvering with premature blade stall, detected by trailing edge pressure requirements are emphasized Speed advantage ability to engage measurements and subsequent stall flutter with an increased or disengage at will maintaining control over the combat arena power requirement Author (ESA) and target acquisition are among the factors analyzed From differential game technology, supercruiser maneuvering require- N78-30099f Advisory Group for Aerospace Research and ments are determined as a function of the threat s maneuvering Development. Paris (France) capability Wind tunnel results indicate that a small single aircraft FIGHTER AIRCRAFT DESIGN can be configured to produce the level of efficiency necessary Jun 1978 292 p refs Partly in ENGLISH and FRENCH for supersonic cruise JMS Presented at the Multi-Panel Symp on Fighter Aircraft Design. Florence, 3-6 Oct 1977 N78-30108# Naval Air Systems Command Washington D C (AGARD-CP-241. ISBN-92-835-0215-9) Avail NTIS ANALYSIS OF ADVANCED VARIABLE CAMBER CON- HC A13/MF A01 CEPTS The state of technology as related to future fighter aircraft R F Siewert and R E Whitehead (ONR Arlington Va) In design is assessed in terms of military requirements for the AGARD Fighter Aircraft Design Jun 1978 21 p refs 80s System design approach, aerodynamics and aircraft configurations propulsion structures design avionics/guidance Avail NTIS HC A13/MF A01 and human factors are among to topics covered A survey of variable camber devices used on contemporary fighter aircraft to improve maneuverability in the air combat flight regime is presented Variable camber concepts which offer potential for even greater benefits on future fighter aircraft designs N78-30104# Dornier-Werke GmbH. Fnednchshafen (West are discussed Finally some analysis is presented which provides Germany) insight into the advantages that are achieved in various off design ADVANCED CONTROL CONCEPTS FOR FUTURE FIGHTER conditions with the use of these variable camber concepts AIRCRAFT JMS Horst Wunnenberg and Wolfgang J Kubbat (Messerschmitt- Boelkow-Blohm GmbH Ottobrunn West Ger) In AGARD N78-30109# Motoren- und Turbmen-Umon Muenchen GmbH Fighter Aircraft Design Jun 1978 15 p refs (West Germany) VARIABLE-CYCLE ENGINE FIGHTER AIRCRAFT AD- Avail NTIS HCA13/MFA01 VANCE IN PERFORMANCE AND DEVELOPMENT PROB- In detail the possibilities and limits of new control concepts LEMS such as active control technology and reduced static stability H Gneb W Weiler, and G Weist In AGARD Fighter Aircraft and the criteria for the corresponding control surface layout are Design Jun 1978 16 p refs Sponsored by Mm of Defence discussed Requirements and the technical realization methods of Federal Rep of Ger for a modern fly by wire digital control technology are presented Comments on current research programs and future Avail NTIS HCA13/MFA01 The requirements on engines for civil and military super- prospects are given J M S sonic aircraft and the interest in variable cycle engines are explained In addition the variable cycle engine concepts and N78-30105# McDonnell Aircraft Co St Louis Mo their function are described briefly For two concepts of variable FIGHTER SUPERIORITY BY DESIGN cycle engines for fighter aircraft the operating characteristics W P Murden H D Altis. and M L Ramey In AGARD Fighter performance data and leading design features are discussed Aircraft Design Jun 1978 16 p These examples are used to contrast the advances offered by such engines against the problems to be overcome It is shown Avail NTIS HCA13/MFA01 that whereas the desired flexibility in operating characteristic Aspects of the F-18 program are discussed in terms of and performance is feasible the extra engine weight and increasing combat effectiveness and decreasing combat costs complexity compared with conventional engines is very substan- Combat performance firepower and weapon system capability tial For a fighter aircraft a simplified comparison of effectivity multimission versatility increased reliability and maintainability is made between the installation of variable cycle engine concepts and combat survivability are among the factors considered and two types of conventional engines with different bypass JMS ratio It is shown that the extra weight to be expected with variable cycle engines investigated so far does not justify their N78-30106# Avions Marcel Dassault-Breguet Aviation future application JMS Saint-Cloud (France) Div des Etudes Avancees AERODYNAMICS OF THE NEW GENERATION OF COMBAT AIRCRAFT WITH DELTA WINGS [AERODYNAMIQUE DE N78-30110# National Gas Turbine Establishment Farnborough LA NOUVELLE GENERATION D-AVIONS DE COMBAT A (England) AILE DELTA] INTAKE DESIGN FOR FIGHTER AIRCRAFT M Pierre Bohn In AGARD Fighter Aircraft Design Jun 1978 J Dunham In AGARD Fighter Aircraft Design Jun 1978 13 p In FRENCH 15 p refs Sponsored in part by RAE Avail NTIS HC A13/MF A01 Utilization of various aerodynamic configurations for modern Avail NTIS HCA13/MFA01 delta wing combat aircraft is discussed in relation to approach An outline is given of the requirements placed upon the speeds and reducing impact damage at Supersonic speeds Mission intake designer Low external drag high intake pressure recovery, requirements such as maneuverability were examined in detail and low distortion of the engine face flow are demanded over

549 N78-30111 a wide range of aircraft maneuvers at subsonic speeds as well N78-30116# Messerschmitt-Boelkow-Blohm G m b H Munich as through the transonic and supersonic speed ranges All this (West Germany) Dept of Human Engineering is to be accomplished at minimum cost weight and complex- DISPLAY SYSTEMS AND COCKPIT DESIGN ity Some of the factors involved in the design are discussed Ruediger Seifert and Hans Denkscherz In AGARD Fighter Aircraft These include intake location, blunt cowl lips and their influence Design Jun 1978 11 p on incidence range matching of engine flow demand with intake capacity dynamic distortion measurement and the control system Avail NTIS HC A13/MF A01 for a variable intake An assessment of the state of the art A concept for a new cockpit design technology is pre- research requirements and possible technological advances is sented The need for a technology is dictated by the technical given J M S requirement for saving cockpit weight and space resulting from the high g operations requirements and from the operational requirement for limiting the quantitative personnel requirements N78-30111# Air Force Aero Propulsion Lab Wright-Patterson The basis for the technology is given by the present knowledge AFB Ohio Turbine Engine Div concerning the information processing capabilities of man. and ADVANCE NOZZLE TECHNOLOGY by the empirical results of measurements of the time budget of Lawrence D Wolfe and Arthur E Fanning In AGARD Fighter man in man machine operations From this the display and control Aircraft Design Jun 1978 31 p modalities are derived, which ensure better utilization of the pilot's capabilities in the future fighter aircraft This concept is Avail NTIS HC A13/MF A01 considered to increase the system capacity of manned fighter The exhaust concepts developed as design options for use aircraft, compared with the equipment overloaded aircraft of today on turbine engines which are to power advanced fighter aircraft The principle allocation of the display and control function to are discussed with emphasis on nonaxisymmetric nozzle the equipment and an example for the required characteristic configurations Nozzle performance cooling effectiveness and for the functions in accordance to the time budget considerations structural integrity at minimum weight are among the topics are given J M S studied Variations in thrust vector schedule aircraft wing loading and thrust loading are included An example is used to illustrate the point that certain nonaxisymmetric nozzle and thrust vectoring N78-30117# Boeing Co Seattle, Wash schemes introduce an additional degree of complexity into the APPLICATION TECHNIQUES FOR DIGITAL FLIGHT procedures necessary to properly account for the applied forces CONTROL SYSTEMS J M S Donald L Martin In AGARD Fighter Aircraft Design Jun 1978 12 p refs Avail NTIS HC A13/MF A01 System design and implementation considerations in applica- N78-30113# Messerschmitt-Boelkow-Blohm G m b H , Munich tion of digital processing and signal transmission techniques to (West Germany) flight control systems are discussed The digital flight control IMPACT OF ACTIVE CONTROL ON STRUCTURES DE- design cycle and both the overall similarity with analog implemen- SIGN tation and the differences associated with software requirements 0 Sensburg and H Zimmermann (Veremigte Flugtechn Werke- specification are covered Design problems that result from the FokkerGmbH Bremen WestGer) In AGARD Fighter Aircraft digital processing are reviewed along with software development Design Jun 1978 26 p refc and testing at both the software and system development levels The three channel redundant flight control computer used on Avail NTIS HC A13/MF A01 the Boeing YC-14 advanced medium STOL transport is described A review of active control technologies is given with along with advantages of digital applications J M S emphasis on fighter aircraft structures design Artificial lateral stability, longitudinal stability maneuver load control and gust load alleviation are considered along with fatigue reduction, ride N78-30118# British Aircraft Corp . Warton (England) Military quality improvement and active flutter suppression J M S Aircraft Div THE DESIGN OF A HIGH g COCKPIT A G Barnes In AGARD Fighter Aircraft Design Jun 1978 12 p refs N78-30114| Departement Structures B E Aerospatiale. Avail NTIS HCA13/MFA01 Toulouse (France) The physiological factors of operating under high g are NEW STRUCTURES MADE OF COMPOSITE MATERIALS discussed The geometric aspects of reclining the pilot s seat, in FOR HIGH PERFORMANCE COMBAT AIRCRAFT [STRUC- order to achieve a measure of g alleviation are illustrated The TURES NOUVELLES EN MATERIAUX COMPOSITES A implications of such a change with respect to displays and controls HAUTES PERFORMANCES POUR AVIONS DE COMBAT] are considered along with techniques which offer solutions to Gilbert Correge In AGARD Fighter Aircraft Design Jun 1978 the problems associated with displays and controls Radical 18 p In FRENCH changes in cockpit layout are implied J M S Avail NTIS HC A13/MF A01 Composite materials utilized in aircraft construction are described Other areas of study are the following (1) Types of composite structures utilized. (2) Materials, (3) Principles of local reinforcement and (4) Protection against lightning strike N78-30119# Institute for Defense Analyses Arlington Va Cost Transl by B B Analysis Group THE FEASIBILITY OF ESTIMATING AVIONICS SUPPORT COSTS EARLY IN THE ACQUISITION CYCLE VOLUME N78-30115# Hawker Siddeley Aviation Ltd. Kingston upon 1 THE BASIC REPORT Final Report. 17 Jan - Sep 1977 Thames (England) John D Morgan and Aaron B Fuller Sep 1977 248 p METAL TECHNOLOGY FOR FUTURE AIRCRAFT DESIGN (Contract DAHC15-73-C-0200) Roger S Dabbs In AGARD Fighter Aircraft Design Jun (AD-A054016 AD-E500025 P-1292-Vol-1) Avail NTIS 1978 16 p HC A11/MF A01 CSCL 15/5 Avail NTIS HC A13/MF A01 This paper reports on research to determine the feasibility Requirements of a material to be used for aircraft structures of developing methods to estimate early in the system acquisition are discussed These include strength and stiffness service life, cycle the potential support cost inputs of alternative avionics vulnerability repairability inspectability. and cost effectiveness components envisioned for Air Force and Navy fighter aircraft Aluminum alloys, titanium alloys and steels are among the metallic Support costs are defined as those costs incurred at the materials considered for application to future aircraft structures organizational intermediate and depot levels to maintain avionics The performance of metallic materials and graphite composites equipment and the costs of avionics spares and repair parts is compared J M S support The results of the study are presented in two volumes

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Volume I reviews and evaluates current methods used in industry time on the IBM 360/67 for one Mach number one altitude, and in the Air Force and Navy to estimate these avionics support and one power setting is about 0 1 seconds about 0 1 costs Finally the paper concludes that it is feasible and desirable seconds The principal assumption used in the calculation is that to prepare these estimates for avionics support costs The specific the compressor is operated along a line of maximum adiabatic method to be adopted depends on the amount of resources efficiency on the compressor map The fluid properties are OSD wishes to devote to this effort Volume II is a compilation computed for the combustion mixture but dissociation is not of appendixes containing additional material to support the basic included The procedure included in the program is only for the report including summary evaluations of fortv-eight key documents combustion of JP-4 methane or hydrogen G G encountered in the literature search GRA N78-30123*# McDonnell Aircraft Co St Louis Mo F-15 INLET/ENGINE TEST TECHNIQUES AND DISTORTION N78-30120# RCA Government and Commercial Systems METHODOLOGIES STUDIES VOLUME 1 TECHNICAL Burlington, Mass Automated Systems Oiv DISCUSSION Final Report C H Stevens E D Spong and M S Hammock Jun 1978 HHSD DEMONSTRATION MODEL DEVELOPMENT 248 p refs 9 Vol Final Report. Sep 1976 - Dec 1977 (Contract NAS4-2364) G T Burton and B R Clay Dec 1977 63 p (Contract N62269-76-C-0390) (NASA-CR-144866) Avail NTIS HC A11/MF A01 CSCL 21E (AD-A054437) Avail NTIS HC A04/MF A01 CSCL 01/4 This Final Report summarizes the status of the Holographic Peak distortion data taken from a subscale inlet model were Horizontal Situation Display effort This programs objective was studied to determine if the data can be used to predict peak the development and optimization of the techniques and hardware distortion levels for a full scale flight test vehicle and to provide required to demonstrate a bright high contrast annotatable a better understanding of the time variant total pressure distortion multicolor display Display hardware with a CRT tape transport and the attendant effects of Reynolds number/scale and frequency and source tapes were developed that demonstrate the characteris- content The data base used to accomplish this goal covered a tics of the focussed image holographic storage technique as range from Mach 0 4 to 2 5 and an angle of attack range from applied to the annotated moving map display requirement of -10 degrees to +12 degrees Data are presented which show the HHSD application of the AIDS program Author (GRA) that (1) increasing the Reynolds number increases total pressure recovery decreases peak distortion and decreases turbulence (2) increasing the filter cutoff frequency increases both peak N78-30121*# Pratt and Whitney Aircraft Group East Hartford distortion and turbulence and (3) the effect of engine presence Conn Commercial Products Div on total pressure recovery peak distortion and turbulence is SHORT-TERM PERFORMANCE DETERIORATION IN small but favorable B B JT9D-7A(SP) ENGINE 695743 R J Bouchard W R Beyerly and G P Sallee 30 Jun 1978 236 p (Contract NAS3-20632) N78-30124*# McDonnell Aircraft Co St Louis Mo (NASA-CR-135431 PWA-5512-17) Avail NTIS F-15 INLET/ENGINE TEST TECHNIQUES AND DISTORTION HCA11/MFA01 CSCL21E The level of performance deterioration that occurred during METHODOLOGIES STUDIES VOLUME 2 TIME VARIANT early service was studied and also the contribution of each engine DATA QUALITY ANALYSIS PLOTS Final Report C H Stevens E 0 Spong. and M S Hammock Jun 1978 module to the overall level of engine performance deterioration To assist in the distribution of the performance losses to the 64 p 9 Vol (Contract NAS4-2364) module level, testing with expanded experimental instrumenta- (NASA-CR-144867) Avail NTIS HC A04/MF A01 CSCL tion was accomplished to permit direct measurement of module performance An analytical teardown of the engine was ac- 21E Time variant data quality analysis plots were used to determine complished to permit assignment of module performance losses if peak distortion data taken from a subscale inlet model can to individual mechanical damage mechanisms including blade be used to predict peak distortion levels for a full scale flight and seal wear roughness and thermal distortion of turbine parts test vehicle For abstract see N78-30123 BB The results of the testing show that the engine deteriorated 1 5 percent in thrust specific fuel consumption from its performance when new Initial testing which included water washing showed N78-30125*# McDonnell Aircraft Co St Louis Mo that 0 2 percent in performance deterioration was due to surface F-15 INLET/ENGINE TEST TECHNIQUES AND DISTORTION contamination (dirt) and 0 1 percent was due to drift of the METHODOLOGIES STUDIES VOLUME 3 POWER engine vane control system leaving 1 2 percent in basic TSFC SPECTRAL DENSITY PLOTS Final Report deterioration This 1 2 percent TSFC loss was distributed among C H Stevens E D Spong and M S Hammock Jun 1978 the engine modules with 0 6 percent caused by clearance changes 103 p refs 9 Vol 04 percent loss due to thermal distortion and 02 percent loss (Contract NAS4-2364) due to increased roughness of the fan and low-pressure (NASA-CR-144868) Avail NTIS HC A06/MF A01 CSCL compressor airfoils G G 21F Power spectral density plots were used to determine if N78-30122*# National Aeronautics and Space Administration peak distortion data taken from a subscdle inlet model can be Langley Research Center Langley Station Va used to predict peak distortion levels for a full scale flight test vehicle Foi abstract see N78-30123 BB COMPUTER PROGRAM FOR THE DESIGN AND OFF- DESIGN PERFORMANCE OF TURBOJET AND TURBOFAN ENGINE CYCLES N78-30126*# McDonnell Aircraft Co St Louis Mo Shelby J Morns Jun 1978 76 p refs F-15 INLET/ENGINE TEST TECHNIQUES AND DISTORTION (NASA-TM-78653) Avail NTIS HC A05/MF A01 CSCL21E METHODOLOGIES STUDIES VOLUME 4 AUTOCOR- The rapid computer program is designed to be run in a RELATION FUNCTIONS Final Report stand-alone mode or operated within a larger program The C H Stevens E D Spong and M S Hammock Jun 1978 computation is based on a simplified one-dimensional gas turbine 99 p 9 Vol cycle Each component in the engine is modeled thermo- (Contract NAS4-2364) dynamically The component efficiencies used in the thermody- (NASA CR-144869) Avail NTIS HC A05/MF A01 CSCL namic modeling are scaled for the off-design conditions from 21E input design point values using empirical trends which are included Autocorrelation function plots were used to determine if peak in the computer code The engine cycle program is capable of distortion data taken from a subscale inlet model can be used producing reasonable engine performance prediction with a to predict peak distortion levels for a full scale flight test minimum of computer execute time The current computer execute vehicle For abstract see N78-30123 BB

551 N78-30127

N78-30127*# McDonnell Aircraft Co St Louis Mo Windsor L Sherman Aug 1978 63 p refs F-15 INLET/ENGINE TEST TECHNIQUES AND DISTORTION (NASA-TM-78678 L-12066) Avail NTIS HC A04/MF A01 METHODOLOGIES STUDIES VOLUME 5 EFFECT OF CSCL 01C FILTER CUTOFF FREQUENCY ON TURBULENCE PLOTS Programs are presented for calculating airplane stability Final Report characteristics with a card programmable pocket calculator These C H Stevens E D Spong and M S Hammock Jun 1978 calculations include eigenvalues of the characteristic equations 103 p 9 Vol of lateral and longitudinal motion as well as stability parameters (Contract NAS4-2364) such as the time to damp to one-half amplitude or the damping (NASA-CR-144870) Avail NTIS HC A06/MF A01 CSCL ratio The effects of wind shear are included Background 21E information and the equations programmed are given The The effect of filter cutoff frequency on turbulence plots were programs are written for the International System of Units the used to determine if peak distortion data taken from a subscale dimensional form of the stability derivatives and stability axes inlet model can be used to predict peak distortion levels for a In addition to programs for stability calculations an unusual full scale flight test vehicle For abstract see N78-30123 BB and short program is included for the Euler transformation of coordinates used in airplane motions The prgrams have been N78-30128*# McDonnell Aircraft Co St Louis Mo written for a Hewlett Packard HP-67 calculator However, the F-15 INLET/ENGINE TEST TECHNIQUES AND DISTORTION use of this calculator does not constitute an endorsement of METHODOLOGIES STUDIES VOLUME 6 DISTORTION the product by the National Aeronautics and Space Administra- ANALYSIS PLOTS Final Report tion Author C H Stevens E D Spong and M S Hammock Jun 1978 1056 p 9 Vol N78-30139*# Virginia Polytechnic Inst and State Umv (Contract NAS4-2364) Blacksburg (NASA-CR-144871) Avail NTIS HC A99/MF A01 CSCL STRUCTURAL DYNAMICS. STABILITY, AND CONTROL OF 21E HELICOPTERS Distortion analysis plots were used to determine if peak Leonard Meirovitch and Arthur L Hale Jul 1978 55 p refs distortion data taken from a subscale inlet model can be used (Grant NsG-1114) to predict peak distortion levels for a full scale flight test (NASA-CR-158909) Avail NTIS HC A04/VIF A01 CSCL vehicle For abstract see N78-30123 B B 01C The dynamic synthesis of gyroscopic structures consisting N78-30129*# McDonnell Aircraft Co St Louis Mo of point-connected substructures is investigated The objective F 15 INLET/ENGINE TEST TECHNIQUES AND DISTORTION is to develop a mathematical model capable of an adequate simulation of the modal characteristics of a helicopter using a METHODOLOGIES STUDIES VOLUME 7 CROSS minimum number of degrees of freedom The basic approach is CORRELATION FUNCTIONS Final Report C H Stevens E D Spong and M S Hammock Jun 1978 to regard the helicopter structure as an assemblage of flexible 49 p 9 Vol substructures The vanational equations for the perturbed motion (Contract NAS4-2364) about certain equilibrium solutions are derived The discretized (NASA-CR-144872) Avail NTIS HC A03/MF A01 CSCL Vdriational equations can be conveniently exhibited in matrix form 21E and a great deal of information about the system modal Cross correlation function plots were used to determine if characteristics can be extracted from the coefficient matrices peak distortion data taken from a subscale inlet model can be The derivation of the vanational equations requires a monumental used to predict peak distortion levels for a full scale flight test amount of algebraic operations To automate this task a symbolic vehicle For abstract see N78-30123 BB manipulation program on a digital computer is developed Author

N78-30130*# McDonnell Aircraft Co St Louis Mo N78-30141*# National Aeronautics and Space Administration F 15 INLET/ENGINE TEST TECHNIQUES AND DISTORTION Langley Research Center Langley Station Va METHODOLOGIES STUDIES VOLUME 8 CROSS SIMULATION STUDY OF THE OSCILLATORY LONGITU- SPECTRAL DENSITY PLOTS Final Report DINAL MOTION OF AN AIRPLANE AT THE STALL C H Stevens E D Spong and M S Hammock Jun 1978 William H Phillips Aug 1978 43 p refs 58 p 9 Vol (NASA-TP-1242 L-12064) Avail NTIS HC A03/MF A01 (Contract NAS4 2364) CSCL 01C (NASA CR 144873) Avail NTIS HC A04/MF A01 CSCL Hybrid simulation of the longitudinal motion of a straight-wing 21F airplane at the stall was studied to investigate the effect of Cioss spectral density plots were used to detPrmme if peak hysteresis in the development of lift and pitching moments on distortion data taken from a subscale inlet model can be used the wing as a function of angle of attack on the occurrence of to predict peak distortion levels for a full scale flight test vehicle longitudinal oscillations at the stall Flight data for the simulated For abstract see N78-30123 BB airplane and for various other airplanes are shown for the simulated airplane and for comparison The results show that oscillations N78-30131*# McDonnell Aircraft Co St Louis Mo similar to those measured in flight may be obtained by incorpora- F-15 INLET ENGINE TEST TECHNIQUES AND DISTORTION ting hysteresis in the lift and pitching-moment curves SB S METHODOLOGIES STUDIES VOLUME 9 STABILITY AUDITS Final Report N78-30142# Massachusetts Inst of Tech Cambridge Dept C H Stevens E D Spong and M S Hammock Jun 1978 of Aeronautics and Astronautics 35 p 9 Vol EXPERIMENTAL INVESTIGATION OF GUST RESPONSE OF (Contract NAS4-2364) HINGELESS HELICOPTER ROTORS M S Thesis (NASA-CR-144874) Avail NTIS HC A03/MF A01 CSCL Charles A Vehlow Jun 1977 105 p refs 21E (AD-A054752) Avail NTIS HC A06/MF A01 CSCL 01/3 Stability audit plots were used to determine if peak distortion The response to wind gusts of a 1/10-scale hingeless data taken from a subscale inlet model can be used to predict helicopter rotor model in hovering and forward flight is studied peak distortion levels for a full scale flight test vehicle For abstract experimentally through wind tunnel testing The experimental see N78-30123 BB program involving design construction and testing of a five-foot- diameter rotor utilizing either three NACA 0012 planform blades or one operable blade with two. dummy blades is described N78-30138*# National Aeronautics and Space Administration The rotor design is such that the torsional stiffness of the blade Langley Research Center Langley Station Va assembly as well as the blade chordwise center-of-gravity location AIRPLANE STABILITY CALCULATIONS WITH A CARD can be varied during the various phases of the test Wind tunnel PROGRAMMABLE POCKET CALCULATOR testing incorporates the variation of wind tunnel speed and the

552 N78-30273

application of variable frequency, sinusoidal waveform gusts The The need for eficient space utilization in military aircraft flap lag and torsional response of the rotor in its various has led to the use of wing and fuselage cavities as fuel tanks configurations was measured and compared with theoretical Of the three methods of sealing these cavities (filleting faying predictions Author (GRA) and channel) channel sealants are the least understood and have the most contrast between behavior and requirements N78-30143# Royal Aircraft Establishment Farnborough Potential failure mechanisms were identified against the thermal, (England) Flight Systems Dept chemical and physical aspects of the fuel tank environment A PYRAMID SKEWED AXIS SENSOR SET FOR MULTIPLEX Thermal degradation low temperature embrittlement thermal FLIGHT CONTROL SYSTEMS expansion and viscosity reduction were mechanisms associated D Kimberley London Aeron Res Council 1978 35 p refs with the -54 C to + 177 C temperature range Hydrolysis Supersedes RAE-TR-75055 ARC-36355 oxidation closed system reversion and crosslmking were (ARC-R/M-3808 BR61586 RAE-TR-75055 ARC-36355) associated with the chemical aspect Fuel swelling of the sealant Avail NTIS HC A03/MF A01 HMSO £4 PHIS1530 extraction by fuel system pressure vibration shear and In order to meet the two defect survival capability in future adhesion/cohesion were associated with the physical aspect full-time flight control systems, one approach is to use four Selected polymers with a wide variety of formulating ir ^redients identical sensors in each axis giving a total of twelve for a were evaluated as channel sealants in laboratory ized test three-axis system An alternative eight sensor pyramid arrange- apparatus to confirm the suspected failure mechanisms The results ment has been developed which offers a similar two defect have been digested as engineering principles that govern the survival capability in all three axes leading to reduced cost and behavior of channel sealants Application of these principles maintenance effort but with slightly larger transients following resulted in some immediate benefits and a basis for long range failure of a sensor The pyramid arrangement can also be used sealant development GRA for fail safe systems reducing the number of sensors from six to four or alternatively for a twelve gyro four defect survival configuration Author (ESA) N78-30259# Southwest Research Inst San Antonio Tex Army Fuels and Lubricants Research Lab EFFECTS OF HIGH AVAILABILITY FUELS ON COMBUSTOR N78-30182# California Umv, Livermore Lawrence Livermore PROPERTIES Interim Report Lab C A Moses and D W Naegeli Jan 1978 100 p refs ROTOR DESIGN IMPLICATIONS FOR COMPOSITE (Contracts DAAG53-76-C-0003 DAAK70-78-C-0001) MATERIAL PROPERTIES (AD-A054229. AFLRL-101) Avail NTIS HC A05/MF A01 R H Toland 25 Oct 1977 7 p Presented at the Flywheel CSCL 21/5 Technol Symp. San Francisco. 5-7 Oct 1977 Engines now in production or under development were (Contract W-7405-eng-48) designed for satisfactory performance and life on current (UCRL-80117 Conf-771053-8) Avail NTIS HC A02/MF specification fuels many of these engines may not be able to A01 handle the stress implied by a broadened fuel specification Among The role and needs of materials research and characterization the fuel properties of greatest concern to turbine engine are defined within the context of the rotor design and analysis combustion are the aromatic content, the distillation curve and process In particular, material/geometry tailoring permits design the viscosity Fuel bound nitrogen is one new property which optimization Composites can be utilized most efficiently when has emerged from the use of syncrude fuels because of additional fiber properties govern rotor performance and reliability Time- NOx found in the exhaust GRA dependent properties are essential for practical and reliable rotor design ERA N78-30271 Aeronautical Research Labs Melbourne (Australia) AIRCRAFT STRUCTURAL FATIGUE Apr 1977 504 p refs Proc held in Melbourne 19-20 Oct N78-30213# Battelle Columbus Labs Ohio 1976 ENGINEERING DATA ON NEW AEROSPACE MATERIALS (ARL/Struc-Rept-363 AR L/Mat-Rept-104 AR-000-724) STRUCTURAL MATERIALS Final Summary Report. Feb Copyright Avail Issuing Activity 1975 - Sep 1977 The assessment of structural fatigue is discussed in terms Omar Deel Wright-Patterson AFB. Ohio AFML Dec 1977 of ensuring safe fatigue lives for aircraft structures and compo- 116 p nents Fundamentals of fatigue and of fracture mechanics data (Contract F33615-75-C-5065 AF Pro| 7381) acquisition and interpretation and structural life prediction are (AD-A054461. AFML-TR-77-198) Avail NTIS included along with current research and development in structural HC A06/MF A01 CSCL11/6 and materials fatigue The major objectives of this program were to evaluate newly developed materials of interest to the Air Force for potential airframe structural usage and to provide data sheet-type presentations of engineering data for these materials The N78-30272 Aeronautical Research Labs Melbourne (Australia) materials effort on this program concentrated on MP 159 SAFETY AGAINST FATIGUE IN FLIGHT A PERSPECTIVE Multiphase Bar Ti-6AI-2Sn-4Zr-2Mo castings 7175-T73511 and OF AUSTRALIAN EXPERIENCE AND RESEARCH -T76511 extrusions 7050-T73 Extrusions. Ti-6AI-4V PM Product F H Hooke In its Aircraft Structural Fatigue Apr 1974 p 5-22 Ti-6AI-4V superplastically formed product Ti-10V-2Fe-3AI Alloy refs Bar and 4330 M Steel Forgings The properties investigated Copyright Avail Issuing Activity include tension, compression, shear bearing impact fracture Research efforts in aircraft structures and materials to reduce toughness, fatigue creep and stress-rupture and stress corrosion metal fatigue and improve aircraft safety are reviewed Endurance at selected temperatures Author (GRA) of structures and materials, the loading actions on the structure and inspection methods to maintain structural integrity are among the factors discussed J M S

N78-30247# Air Force Materials Lab Wright-Patterson AFB N78-30273 Aeronautical Research Labs Melbourne (Australia) Ohio Elastomers and Coatings Branch MECHANISMS OF FATIGUE AND FRACTURE FUNDAMENTALS OF NONCURING SEALANTS FOR S P Lynch In its Aircraft Structural Fatigue Apr 1977 p 25-55 AIRCRAFT FUEL TANKS Final Report. Jan. 1975 - Jan refs 1977 Copyright Avail Issuing Activity Warren R Griffin Dec 1977 95 p refs Overload fracture liquid-metal embrittlement. stress corrosion (AD-A054627 AFML-TR-77-195) Avail NTIS cracking, fatigue crack initiation fatigue crack growth and HC A05/MF A01 CSCL 11/1 corrosion fatigue are discussed and related Observations suggest

553 N78-30274 that crack growth in many metallic materials generally occurs constraints such as weighting the nomntersection of curves within by plastic flow and that fracture characteristics are determined a family, and the choice of a fatigue limit, is also discussed mainly by the distribution of slip around crack tips This distribution Many factors associated with the determination of fatigue data governs ductile versus brittle behavior and is influenced by influence the resultant S/N relationship and some of the more microstructure stress intensity temperature and environment significant ones are considered Those factors examined include the effects of environment are attributed mainly to chemisorption the loading accuracy of the testing machine, specimen manufactur- at crack tips and are discussed in some detail Changes in ing methods and the number of specimens tested, the definition microstructure induced by cyclic stress and the association of of fatigue failure variability between batches J M S such changes with initiation and growth of fatigue cracks, are also examined Relationships between crack growth rates and N78-30279 Aeronautical Research Labs Melbourne (Australia) stress intensity factors, and the application of mechanistic STRUCTURAL FATIGUE TESTING understanding are then briefly discussed J M S R A Bruton and C A Patching In its Aircraft Structural Fatigue Apr 1977 p 179-202 refs N78-30274 Aeronautical Research Labs. Melbourne (Australia) FRACTURE MECHANICS FUNDAMENTALS WITH REFER- Copyright Avail Issuing Activity ENCE TO AIRCRAFT STRUCTURAL APPLICATIONS The various testing techniques available selection of the B C Hoskin In its Aircraft Structural Fatigue Apr 1977 p 57-89 test article data obtainable from fatigue testing of components, refs ' assemblies and complete structures and the conclusions that Copyright Avail Issuing Activity have been reached based on experience from a large number of Fracture mechanics and its applications to problems associ- fatigue tests on aircraft wings are discussed J M S ated with cracked or potentially cracked aircraft structures is considered Such applications include assessment of the residual N78-30280 Aeronautical Research Labs Melbourne (Australia) strength of cracked components and also the prediction of fatigue CURRENT DEVELOPMENTS IN THE LIFE OF AIRCRAFT crack growth Limitations of fracture mechanics likely to be of STRUCTURE importance in aircraft structural applications are emphasized A 0 Payne In its Aircraft Structural Fatigue Apr 1977 J M S p 205-226 refs Copyright Avail Issuing Activity Procedures for fatigue design and fatigue life estimation N78-30276 Aeronautical Research Labs Melbourne (Australia) substantiation and monitoring of aircraft structures are re- GUST MEASUREMENTS AND THE N SUB o PROBLEM viewed Major gaps in the present state of knowledge are identified and further research directed towards filling these gaps is Douglas John Sherman In its Aircraft Structural Fatigue Apr discussed It is shown that the fatigue assessment of modern 1977 p 103-135 refs aircraft structures is a very complex problem for which no general method of solution has yet been established despite the extensive Copyright Avail Issuing Activity research programs being conducted A trend toward examining The problem of interpreting level crossing counts superim- various aspects of fatigue behavior to find increasing application posed on a lesser number of large fluctuations is considered It is documented J M S is shown that if fluctuations smaller than some specified amount are removed from a time history, the number of level crossings is reduced An empirical formula is given for the amount of the reduction in a time series of atmospheric turbulence velocities N78-30281 Aeronautical Research Labs, Melbourne (Australia) JM S AIRCRAFT STRUCTURAL LIFE MONITORING AND THE PROBLEM OF CORROSION L M Bland In its Aircraft Structural Fatigue Apr 1977 N78-30277 Aeronautical Research Labs. Melbourne (Australia) p 227-253 refs DEVELOPMENT OF A LOAD SEQUENCE FOR A STRUCTUR- Copyright Avail Issuing Activity AL FATIGUE TEST The principles of fatigue design and related structural P J Howard In its Aircraft Structural Fatigue Apr 1977 maintenance are briefly described for two essentially different p 137-148 refs I / philosophies of structural fatigue life In once case it is assumed Copyright Avail Issuing Activity that no crack is present in any structural component at the A method for generating a load sequence for a structural beginning of service and that the components should remain fatigue test is described and is illustrated by reference to the crack-free throughout the service life In the other case, it is Mirage wing fatigue test Flight sequence and load spectra for conservatively assumed that cracks are present in all components this test were defined by fatigue meter data and withm-flight which service beings but that these cracks growing slowly can maneuver loead sequences were derived from recorded time be tolerated for the required service life The relevance of the histories J M S chemical and physical environment in which the structure exists is discussed for the two cases The role of structural service N78-30278 Aeronautical Research Labs, Melbourne (Australia) monitoring in ensuring safe and economic operation of aircraft FATIGUE S/N DATA IN RELATION TO VARIABILITY IN is considered and the place of environment and corrosion PREDICTED LIFE monitoring in the general monitoring scheme is identified The J M Fmney and J Y Mann In its Aircraft Structural Fatigue importance of nondestructive inspection in corrosion monitoring Apr 1977 p 149-178 refs is also considered with an assessment of the applicability and adequacy of various inspection methods in the monitoring task Copyright Avail Issuing Activity Indications are given of the limitations of these methods and of The variability which may arise from either fitting a mean the requirements for improved planning of the corrosion monitoring curve to a given set of fatigue stress and cycles to failure (S/N) process J M S data points or from sources affecting the data points themselves was investigated Mean lives to failure were predicted S/N curves N78-30282 Aeronautical Research Labs Melbourne (Australia) for several multi-load-level spectra The range of values of NDI AND THE DETECTION OF FATIGUE predicted life from the largest to the smallest and averaged I G Scott In its Aircraft Structural Fatigue Apr 1977 p 255-267 over the several spectra was 3 1 for one set of data points refs and 2x4 1 for the other set Five mathematical methods of curve Copyright Avail Issuing Activity fitting were applied to one set of data points, with the resultant The problems of monitoring fatigue cracks by nondestructive average range in predicted life being 1 x4 1 This variability arises inspection (NDI) are discussed and recent developments in the mainly from the subjective choice of a functional form for the methods and techniques are reviewed Three aspects are S/N curve The added variability due to other arbitrarily-chosen considered in some detail (1) the part played by the operator

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in NDI (2) applications of acoustic emission to fatigue studies at the crack tip of the elastically deforming structure The and 13) future trends in NDI Some new philosophies fatigue model is validated under a wide range of load histories and the testing are also considered J M S implications for practical aircraft materials are discussed J M S

N78-30283 Aeronautical Research Labs Melbourne (Australia) THE DEVELOPMENT OF THE THEORY OF STRUCTURAL N78-30288 Aeronautical Research Labs Melbourne (Australia) FATIGUE FIBRE COMPOSITE REINFORCEMENT OF CRACKED D G Ford In its Aircraft Structural Fatigue Apr 1977 p 269-298 AIRCRAFT STRUCTURES refs A A Baker and M M Hutchison In its Aircraft Structural Copyright Avail Issuing Activity Fatigue Apr 1977 p 419-457 refs The relation of structural fatigue to other branches of fatigue is outlined by a brief historical survey which includes the mam Copyright Avail Issuing Activity ideas of the theory and ends with some of the current problems The fatigue performance of a range of commercially available and possible developments Cumulative damage and reliability adhesive materials was examined to enable the selection of an are included J M S adhesive system suitable for bonding of fiber composite reinforce- ments to cracked aircraft structures Small constant stress N78-30284 Aeronautical Research Labs, Melbourne (Australia) cantilever 7075-T6 aluminum alloy fatigue specimens were used AIRCRAFT STRUCTURAL RELIABILITY AND RISK THEORY to evaluate the characteristics of the adhesives and also to examine A REVIEW the feasibility of using fiber composites to control crack F H Hooke In its Aircraft Structural Fatigue Apr 1977 propagation The adhesive selected for the repair application p 299-344 refs I required curing at 130 C which due to the low thermal expansion Copyright Avail Issuing Activity of the composite induced residual tensile stresses in the aluminum Evaluation of the structural reliability and probability of failure at room temperature Wedge-loaded precracked stress corrosion during the lifetime a statistical exercise based upon load history specimens were used to show that these internal stresses do data and strength decay properties known or attributed to the not significantly limit the practical usefulness of the proposed structures in question are discussed Reliability of reliability repair schemes Finally two practical aircraft repairs are described estimates is examined and is shown to be usually limited by which are currently being evaluated under operating conditions sampling problems and arbitrary judgments concerning the J M S attribution of properties to the population in question The estimates are compared with those derived by semiprobabihstic or limit analysis methods J M S N78-30291*# National Aeronautics and Space Administration Langley Research Center Langley Station Va N78-30285 Aeronautical Research Labs Melbourne (Australia) EXPERIMENTAL DETERMINATION OF THE RATTLE OF LOAD INTERACTION EFFECTS IN FATIGUE CRACK PROPAGATION SIMPLE MODELS Clevenson A Sherman Jul 1978 22 p refs G W Revill, Nmgaiah. and J M Fmney In its Aircraft Structural (NASA-TM-78756) Avail NTIS HC A02/MF A01 CSCL 20K Fatigue Apr 1977 p 347-372 refs The effect of the excitation frequency on the rattle boundaries of simple models was investigated The frequency range Copyright Avail Issuing Activity investigated was from 40 to 4000 Hz A 1-inch steel ball was Some experiments on the influence of material thickness studied to determine the rattle boundary for both vertical motion are described For 2024-T3 aluminum alloy specimens the delay and for the ball suspended as a pendulum Effects of surface in crack growth caused by a single overload was greater by a contact and weight were also studied Results indicate that the factor of about 8 5 for 1 6 mm thick specimens than for 6 4 mm shape of the rattle boundary depends on the particular configura- thick specimens The practical importance of this effect is tion being investigated as well as the range of frequency being emphasized Various proposed mechanisms of load interaction investigated Although there was condiderable scatter in the da'a are described as well as models for quantitative predictions the general trend indicates that the level of acceleration required The models all incorporate the extent of crack tip plasticity into for the onset of rattle was independent of excitation frequency the Paris formulation of fatigue crack growth They do not SES accurately detail the course of crack growth through the interaction period It is concluded that satisfactory prediction of interaction effects will require some materials information obtainable only by test J M S N78-30S83*# Jet Propulsion Lab Calif Inst of Tech Pasadena ANALYSIS OF A SUSPENSION SYSTEM FOR A WHEEL ROLLING ON A FLAT TRACK N78-30286 Aeronautical Research Labs. Melbourne (Australia) H McGmness 1 Aug 1978 24 p ref A MODEL OF CRACK-TIP BEHAVIOUR FOR FATIGUE LIFE (Contract NAS7-100) DETERMINATION (NASA-CR-157563 JPL-Pub-78-43) Avail NTIS F P Bullen J A Retchford C B Rogers and B J Wicks In HC A02/MF A01 CSCL 131 its Aircraft Structural Fatigue Apr 1977 p 373-391 refs A flexure strut wheel suspension system is described which keeps a wheel flat against the track and maintains a small interface Copyright Avail Issuing Activity moment Equations are presented for the evaluation of this The evaluation o1 fatigue life by simulating the performance moment A comparison of the flexure strut system is made with of critically stressed areas of a structure using individual tests a rigid link design containing pivot bearings Author on small specimens is considered The experiments which are presented have been earned out on polycrystallme copper since the physical basis of crack tip behavior in this simple metal is N78-30603# Industneanlagen-Betriebsgesellschaft mbH also applicable to conventional aircraft materials It is shown Ottobrunn (West Germany) that in these materials cracks propagate under cyclic loading THE INFLUENCES OF RESIDUAL STRESSES ON OSCILLAT- as a result of irreversible plastic strain and a parameter describing ING TENSILE STRENGTH AND THE MEASUREMENT OF the plastic strain at the crack tip is defined which is shown to RESIDUAL STRESS. WITH EMPHASIS ON AIRCRAFT be directly related to the rate of crack propagation A simple CONSTRUCTION [UNTERSUCHUNG DES EINFLUSSES model of crack tip behavior is proposed in which the elastic VON EIGENSPANNUNGEN AUF DIE SCHWINGFESTIGKEIT and plastic contributions from material around the crack tip can SOWIE MESSUNG DER EIGENSPANNUNG. MIT BES- be isolated and recombmed in varying proportions This could ONDERER BERUECKSICHTIGUNG DES FLUGZEUGBAUS] allow the behavior of a cracked component in a structure to be P Schrader and W Schuetz 1977 105 p refs replicated on small cracked specimens, by superimposing on the (BMVG-FBWT-77-23) Avail NTIS HC A06/MF A01 specimen load spectrum a stress variation representing the effect DOKZENTBW 30 DM

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Surface rolling and coining of holes in notched specimens of supersonic technology and improved aircraft engine designs, shot peening of unnotched flat bars and rolling of fillets of uses the most recent chemical reaction rate data From the stepped shafts induced compressive residual stresses in aircraft results of the present assessment it would appear that realistic components and increased fatigue life of high strength aluminum fleet sizes should not cause concern with regard to the depletion titanium and steel alloys Under fhght-by-flight loading the fatigue of the total ozone overburden For example the NOx emission life was increased by coming 6-fold for the notched aluminum of one type designed to cruise at 20 km altitude will cause the specimens, 9-fold for the titanium specimens and 3-fold for the ozone overburden to increase by 0 03% to 0 12%. depending steel specimens Shot peening improved the fatigue life by a upon which vertical transport is used These ozone changes can factor of 3 for the aluminum, and of more than 10 for the be compared with the predictions of a 1 74% ozone decrease titanium and the steel The life under a random load sequence (for 100 Large SSTs flying at 20 km) made in 1974 by the was increased 3-fold for the rolled stepped shafts The increases FAA s Climatic Impact Assessment Program Author in fatigue life cannot be explained in all cases by the effect of the residual stresses alone because they had already been reduced to zero after about 2 per cent of the fatigue life to failure of N78-30896*# National Aeronautics and Space Administration the shot peened aluminum specimens although the fatigue life Lewis Research Center Cleveland Ohio increased by a factor of 3 In the shot peened Ti- and steel specimens however the residual stresses had not decreased after PROCEDURES FOR GENERATION AND REDUCTION OF 40 percent of the life to failure ARM LINEAR MODELS OF A TURBOFAN ENGINE Kurt Seldner and David S Cwynar Aug 1978 45 p refs (NASA-TP-1261 E-9460) Avail NTIS HC A03/MF A01 CSCL 12B N78-306O6*# National Aeronautics and Space Administration A real time hybrid simulation of the Pratt & Whitney Langley Research Center Langley Station Va F100-PW-F100 turbofan engine was used for linear-model RECENT DEVELOPMENTS IN ANALYSIS OF CRACK generation The linear models were used to analyze the effect PROPAGATION AND FRACTURE OF PRACTICAL MATERI- of disturbances about an operating point on the dynamic ALS performance of the engine A procedure that disturbs samples H F Hardrath. J C Newman Jr W Elber and C C Poe Jr and records the state and control variables was developed For Jun 1978 20 p refs Presented at the Intern Symp of large systems such as the F100 engine the state vector is Fracture Mechanics Washington D C 11-13Sep 1978 large and may contain high-frequency information not required (NASA-TM-78766) Avail NTIS HC A02/MF A01 CSCL 20K for control This reducing the full-state to a reduced-order model The limitations of linear elastic fracture mechanics in aircraft may be a practicable approach to simplifying the control design design and in the study of fatigue crack propagation in aircraft A reduction technique was developed to generate reduced-order structures are discussed NASA-Langley research to extend the models Selected linear and nonlinear output responses to capabilities of fracture mechanics to predict the maximum load exhaust-nozzle area and main-burner fuel flow disturbances are that can be carried by a cracked part and to deal with aircraft presented for comparison Author design problems are reported Achievements include (1) improved stress intensity solutions for laboratory specimens (2) fracture N78-30909# European Space Agency, Pans (France) criterion for practical materials (3) crack propagation predictions THEORETICAL AND EXPERIMENTAL STUDIES OF ACOUS- that account for mean stress and high maximum stress effects TIC PROPAGATION IN INHOMOGENEOUS MOVING (4) crack propagation predictions for variable amplitude loading MEDIA and (5) the prediction of crack growth and residual stress in Sebastien Candel Jun 1978 315 p refs Transl into ENGLISH built-up structural assemblies These capabilities are incorporated of 'Etudes Theonques et Exptl de la Propagation Acoustique en into a first generation computerized analysis that allows for Milieu Inhomogene et en Mouvement, ONERA Pans Report damage tolerance and tradeoffs with other disciplines to produce ONERA-P-1977-1. 1977 Original report in FRENCH previously efficient designs that meet current airworthiness requirements announced as N78-24905 ARM (ESA-TT-477 ONERA-P-1977-1) Avail NTIS HC A14/MF A01 Three problems are treated in particular the propagation of N78-30620# National Aerospace Lab , Amsterdam (Netherlands) plane and modal pressure waves in nozzles and diffusers. the Structures and Materials Div adiation of the jet noise high-frequency components and the COMPILATION OF TEST DATA FROM AN INVESTIGATION propagation of an acoustic field in the free flow of an open ON THE EFFECT OF ENVIRONMENT ON CRACK GROWTH wind tunnel A numerical algorithm based on the geometrical UNDER FLIGHT-SIMULATION LOADING approximation was developed and allows the calculation of the 3 Sep 1976 39 p refs Supplement to NLR-TR-76104 wave field (amplitude and phase) in the case of very general (Contract NIVR-1725) media (mhomogeneous dispersive including reflecting surfaces) (NLR-TR-76096-U NLR-TH-76104) Avail NTIS A comparison between calculations and experimental results HC A03/MF A01 obtained in an open wind tunnel was made to check the proposed The present report is a supplement to NLR-TR-76104 numerical method and to demonstrate its practical utility Numerical test results and several evaluations are given in full Author (ESA) detail However the discussion of the results is presented in NLR-TR-76104 Author (ESA) N78-30910# Loughborough Univ of Technology (England) Dept of Transport Technology N78-30774*# National Aeronautics and Space Administration A FURTHER SURVEY OF SOME EFFECTS OF AIRCRAFT Ames Research Center Moffett Field Calif NOISE IN RESIDENTIAL COMMUNITIES NEAR LONDON AN ASSESSMENT OF THE EFFECT OF SUPERSONIC (HEATHROW) AIRPORT AIRCRAFT OPERATIONS ON THE STRATOSPHERIC J B Ollerhead and R M Edwards Jun 1977 148 p refs OZONE CONTENT (Contract SN/1170/012) I G Poppoff R C Whitten. R P Turco (R and 0 Associates (TT-7705) Avail NTIS HC A07/MF A01 Marina del Rey, Calif) and L A Capone (San Jose State Univ Six hundred residents of suburban communities near London Calif) Aug 1978 60 p refs (Heathrow) airport were interviewed in a pilot survey designed (NASA-RP-1026 A-7399) Avail NTIS HC A04/MF A01 CSCL to compare alternative methods of scaling aircraft noise exposure 13B and human reactions to it The various associations between An assessment of the potential effect on stratospheric ozone noise variables is discussed It is concluded that no new noise of an advanced supersonic transport operations is presented scale is likely to emerge which is a more reliable or convenient This assessment which was undertaken because of NASA's desire predictor of aircraft noise annoyance than Noise and Number for an up-to-date evaluation to guide programs for the development Index (NNI) ESA

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N78-30911# Loughborough Univ of Technology (England) FOR A HIGH-ASPECT-RATIO SUPERCRITICAL WING Dept of Transport Technology Boyd Perry. Ill Sep 1978 26 p refs A COMPARISON OF ANNOYANCE CAUSED BY AIRCRAFT (NASA-TM-78664 L-12219) Avail NTIS HC A03/MF A01 NOISE NEAR LONDON. MANCHESTER AND LIVERPOOL CSCL 01A AIRPORTS The hinge moments at selected flight conditions resulting J B Ollerhead Jun 1977 77 p refs from deflecting two trailing edge control surfaces (one inboard (Contract SN/1170/012) and one midspan) on a high aspect ratio swept, fuel conservative (TT-7706) Avail NTIS HC A05/MF A01 wing with a supercritical airfoil are estimated Hinge moment In a postal survey designed to investigate the validity of results obtained from procedures which employ a recently Noise and Number Index (NNI) for scaling aircraft noise impact developed transonic analysis are given In this procedure a at airports other than London (Heathrow) questionnaires were three dimensional mviscid transonic aerodynamics computer sent simultaneously to some 3000 residents near London program is combined with a two dimensional turbulent boundary (Heathrow) Manchester and bverpool airports Although the layer program in order to obtain an interacted solution These response rate was poor the results indicate that NNI is One of results indicate that trends of the estimated hinge moment as a several noise scales which show optimum correlation with function of deflection angle are similar to those from experimental annoyance reactions However the mean reactions differed hinge moment measurements made on wind tunnel models with between airports with Manchester residents being slightly more swept supercritical wings tested at similar values of free stream sensitive and Liverpool residents significantly less sensitive to a Mach number and angle of attack J M S given amount of aircraft noise than their Heathrow counterparts It is recommended that rather than perform more surveys to N78-31044*# National Aeronautics and Space Administration identify an optimum noise scale a suitable convenient scale be Langley Research Center, Hampton Va standardized and that the primary objective of future surveys ANALYSIS OF STABILITY CONTRIBUTIONS OF HIGH should be to establish the relevant dose-response relations An DIHEDRAL V-TAILS important step in this direction would be the development of a Carl E Freeman (AVRADCOM Res and Technol Labs) and general procedure for the measurement of noise annoyance William T Yeager (AVRADCOM Res and Technol Labs) Aug Author (ESA) 1978 22 p refs (DA Proj 1L1-61102-AH-45) (NASA-TM-78729. AVRADCOM-TR-78-34, L-12277) Avail NTIS HC A02/MF A01 CSCL 01A N78-31O07# Rohr Industries Inc Chula Vista Calif An investigation was undertaken to determine the effective- TEST AND DEMONSTRATION PROTOTYPE TRACKED AIR ness of four analytical methods (empirical modified empirical, CUSHION VEHICLE (PTACV) PHASE INC Final Report. vortex-lattice, and an mviscid three dimensional, potential flow, Jan 1976 - Nov 1977 wing body program) to estimate the lateral and longitudinal static A K Smith J Dallas R Stott Dynes and L Samusson Nov stability characteristics of an isolated V-tail wind tunnel model 1977 330 p refs The experimental tests were conducted in the V/STOL tunnel (Contract DOT-FR-54089) at a Mach number of 0 18 Angle-of-attack data were obtained (PB-279970/8 FRA/ORD-78/03) Avail NTIS from -12 deg to 8 deg at 0 deg sideslip Sideslip sweeps from HC A15/MF A01 CSCL 13F -5 deg to 10 deg were made at angles of attack of 4 deg, A six year multi-phased program for design development 0 deg and -4 deg The V-tail dihedral angles were 45 deg, and test of a prototype tracked air cushion vehicle was culminated 50 deg 55 deg and 60 deg B B in a six month test and demonstration Descriptions of the various mator sub-systems are presented with design and operational performance data Technical data covering test objectives, N78-31046*# National Aeronautics and Space Administration descriptions and results are furnished on a wide variety of Langley Research Center Hampton Va functional assemblies, subsystems and performance conditions AERODYNAMIC CHARACTERISTICS OF A HYPERSONIC Physical characteristics were measured for accelerations braking RESEARCH AIRPLANE CONCEPT HAVING A 70 DEG aerodynamic drag ride comfort acoustical quality reliability and SWEPT DOUBLE-DELTA WING AT MACH NUMBER 02 maintainability performance GRA Jim A Penland Theodore R Creel. Jr. and James L Dillon Sep 1978 83 p refs (NASA-TP-1252 L-12215) Avail NTIS HC A05/MF A01 CSCL 01A N78-31042 Stanford Univ Calif A wind-tunnel of the static longitudinal, lateral and directional THE TRANSONIC FLOW ON A HELICOPTER ROTOR stability characteristics of a hypersonic research airplane concept PhD Thesis having a 70 deg swept double-delta wing was conducted in the Francis Xavier Caradonna 1978 197 p Langley low-turbulence pressure tunnel The configuration Avail Univ Microfilms Order No 7814162 variables included wing planform, tip fins, center fin, and The flow on a hovering helicopter rotor operating at a scramjet engine modules A mach number of 0 2 was investigated supercritical tip Mach number is modeled using potential theory over a Reynolds number (based on fuselage length) range of The general potential equation is casted in blade-fixed coordinates 2.200000 to 1975 x 1,000.000 (with a majority of tests at and the transonic small disturbance approximation is invoked 100 x 1 000000 Tests were conducted through an angle-of- The resulting equation only differs from its fixed-wing counterpart attack range from about -2 deg to 34 deg at angles of sideslip in having a spanwise increasing free-stream Mach number of 0 deg to 5 deg. and at eleven deflection of 0 deg -5 deg. Solutions shown use an arbitrary but not untypical vortex location -10 deg -15 deg. and -20 deg The drag coefficient of the and the strength is assumed to be the maximum blade circulation integrated scramjet engine appears relatively constant with Solutions obtained show the onset of supercritical flow and Reynolds number at the test Mach number of 0 2 Mild pitch-up ultimately drag divergence The drag divergence Mach number was exhibited by the models equipped with tip fins The forward was considerably higher than that at which supercritical flow delta a highly swept forward portion of the wing, was destabilizing first occurs Although there is some good comparison of computed The center fin model has a higher trimmed maximum lift-drag results with fixed-wmg-model data there currently exists no body ratio and a wider trim lift and angle-of-attack range than the of hovering wake and load data adequate to test the present tip fin model Both the tip fin models and center fin models code Dissert Abstr exhibited positive dihedral effect and positive directional stability Roll control was positive for the tip fin model but yaw due to roll control was unfavorable Author

N78-31043*# National Aeronautics and Space Administration N78-31O46| Naval Air Test Center Patuxent River Md Strike Langley Research Center. Hampton. Va Aircraft Test Directorate CONTROL-SURFACE HINGE-MOMENT CALCULATIONS MAXIMUM LIKELIHOOD IDENTIFICATION OF THE

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LONGITUDINAL AERODYNAMIC COEFFICIENTS OF THE HC A10/MF A01 CSCL 20/4 EA-6B AIRPLANE IN THE CATAPULT LAUNCH CONFIGU- This report describes a numerical method to predict the RATION detailed pressure distribution and force and moment results for David E Bischoff 8 May 1978 34 p refs wing-body combinations at transonic Mach numbers less than (AD-A054243. NATC-TM-78-2-SA) Avail NTIS one The resulting computer code has been developed with the HC A03/MF A01 CSCL 01/3 intent of providing the user with an easy to use and reliable The aerodynamic coefficients describing the longitudinal tool that produces the most accurate possible engineering equations of motion of the EA-6B airplane with landing gear predictions In order to provide accurate surface pressure and flaps down were determined from flight test data through predictions on the wing several additional features of the typical use of a maximum likelihood identification algorithm These transonic flow field have been incorporated These consist of identified coefficients were accurately determined and were utilized the viscous displacement effect, local strong viscous interaction to both (1) predict short and long period time history responses at the shock wave foot and at the trailing edge (including an and (2) duplicate the results of conventional flight test specification approximate treatment of local shallow separations) and finally requirement test procedures The identified results provide an the interaction effect of the fuselage GRA example of the type of information available through the application of parameter estimation technology in the areas of airplane data base generation These data can be utilized for N78-31061*# National Aeronautics and Space Administration ACLS and Operational Flight Trainer simulations as well as for Lewis Research Center Cleveland, Ohio parametric studies of aerodynamic characteristics Author (GRA) SIMULTANEOUS MEASUREMENTS OF OZONE OUTSIDE AND INSIDE CABINS OF TWO B-747 AIRLINERS AND A N78-31047| Naval Ship Research and Development Center GATES LEARJET BUSINESS JET Bethesda Md Aviation and Surface Effects Dept Porter J Perkins and Daniel Bnel 1978 11 p refs Proposed TWO-DIMENSIONAL SUBSONIC WIND TUNNEL EVALUA- for presentation at the Conf on Atmospheric Environ of Aerospace TION OF TWO RELATED CAMBERED 15-PERCENT THICK Systems and Appl Meteorology New York, 13-16 Nov 1978 CIRCULATION CONTROL AIRFOILS Final Report sponsored by the Am Meteorol Soc and the AIAA Jane Abramson Sep 1977 68 p refs (NASA-TM-78983 E-9760) Avail NTIS HC A02/MF A01 (AD-A055140. DTNSRDC/ASED-373) Avail NTIS CSCL 06T HC A04/MF A01 CSCL 20/4 The average amount of ozone measured in the cabins of Two circulation control cambered elliptic airfoil sections with two B-747 airliners varied from 40 percent to 80 percent of a thickness-to-chord ratio of 0 15 and 1 0 percent circular arc the atmospheric concentrations without special ozone destruction camber were evaluated subsomcally to determine their aerody- systems A charcoal filter in the cabin air inlet system of one namic characteristics The two models designated NCCR B-747 reduced the ozone to about 5 percent of the atmospheric 1510-7067N and NCCR 1510-7567S have a common leading concentration A Learjet 23 was also instrumented with edge but different Coanda surfaces GRA monitors to measure simultaneously the atmospheric and ozone concentrations Results indicate that a significant portion of the N78-31048| Hydronautics Inc Laurel. Md atmospheric ozone is not destroyed in the pressurization system MEASUREMENTS AND ANALYSIS OF THE FORCES and remains in the aircraft cabin of the Learjet For the two ACTING ON A SMALL AIRCRAFT FLYING IN THE UPWASH cabin configurations tested the ozone retentions were 63 and OF A LARGE AIRCRAFT Final Report. 1 Jan 1976 - 31 Dec 41 percent of the atmospheric ozone concentrations Ozone 1977 concentrations measured in the cabin near the conditioned-air Clinton E Brown Peter VanDyke and John W Kloetzh Apr outlets were reduced only slightly from atmospheric ozone 1978 30 p refs concentrations It is concluded that a constant difference (Contract F44620-76-C-0073 AF Proj 2307) between ozone concentrations inside and outside the cabin does (AD-A055286 TR-7615, AFOSR-78-0903TR) Avail NTIS not exist G G HC A03/MF A01 CSCL 20/4 Preliminary analysis of the expected ranges of forces and moments were made using available theoretical methods and N78-31064# Rockwell International Corp Los Angeles. Calif confirming experiments were performed in the Hydronautics Ship HAZARD ASSESSMENT OF AIRCRAFT GUN COMPART- Model Basin The tests used a large model of the Boeing 747 MENTS Final Report. May 1976 - Oct. 1977 transport aircraft and a smaller model typifying a fighter-type William A Pace Dec 1977 240 p refs aircraft The range of positions of the small model relative to (Contract F33615-76-C-2051) the large model extended laterally 30 full-scale feet from the (AD-A055026, NA-77-938, AFAPL-TR-77-79) Avail NTIS wing tip or from the tip vortex and downstream roughly 80 feet HCA11/MFA01 CSCL 19/6 behind the wing tip Consideration was given to the problem of Aircraft gun compartments provide an inherent fire/explosion maintaining steady position at a point that provided a maximum risk potential because of the common location of flammable increase in the lift to drag ratio (L/D) of the small aircraft The fluids thermal ignition source and various environmental model tests have shown that an increase of 50% in L/D can conditions This program, while specifically addressing the hazards be obtained by a small fighter-type aircraft flying close to the associated with aircraft gun compartments investigated other tip trailing vortex of a larger aircraft Higher increases in L/D related area of concern The areas include gun compartment for the same relative aircraft positions would result if the smaller hazard identification, accident/incident reports, historical data on aircraft exhibited higher performance (max L/D was 8 9 in free aircraft gun compartment design and evaluation, development air) Calculations made for the models tested indicate that control of a hazard assessment methodology, the chemical composition power of typical fighters would be sufficient to maintain level and behavior of typical gun gases and various types of sensors flight in the favorable positions close to a tip vortex GRA to detect and measure combustible gases The results of the study were used to prepare technical design guidance for possible inclusion in the Armament Handbook DH2-5 Author (GRA) N78-31052# Grumman Aerospace Corp Bethpage N Y AN AUTOMATED PROCEDURE FOR COMPUTING THE THREE-DIMENSIONAL TRANSONIC FLOW OVER WING- BODY COMBINATIONS. INCLUDING VISCOUS EFFECTS N78-31068*# Ohio Univ Athens Dept of Electrical VOLUME 1 DESCRIPTION OF^ANALYSIS METHODS AND Engineering APPLICATIONS Final Report. May 197S - Oct 1977 PHASE-LOCKED TRACKING LOOPS FOR LORAN-C William H Mason Donald Mackenzie Mark Stern William F R W Burhans Aug 1978 25 p Ballhaus and Juamta Fnck Feb 1978 220 p refs (Grant NGR-36-009-017) (Contract F33615-75-C-3073) (NASA-CR-157582 TM-60) Avail NTIS HC A02/MF A01 (AD-A055899 AFFDL-TR-77-122-Vol-1) Avail NTIS CSCL 17G

558 N78-31076

Portable battery operated LORAN-C receivers were fabricated N78-31073| Westmghouse Defense and Electronic Systems to evaluate simple envelope detector methods with hybrid analog Center Baltimore Md to digital phase locked loop sensor processors The receivers CAPTURE EFFECT ARRAY GLIDE SLOPE GUIDANCE are used to evaluate LORAN-C in general aviation applications STUDY Interim Report Complete circuit details are given for the experimental sensor J T Godfrey H F Hartley R A Moore and G J Moussally and readout system Author Mar 1978 95 p (Contract DOT-FA74WA-3353) (AD-A055678 FAA-RD-78-41) Avail NTIS N78-31070# National Aviation Facilities Experimental Center HC A05/MF A01 CSCL 17/7 Atlantic City. N J The performance of the capture effect glide slope array as TRSB MICROWAVE LANDING SYSTEM DEMONSTRATION a function of the quality and quantity of required ground planes PROGRAM AT JOHN F KENNEDY INTERNATIONAL was examined Methods of improvement were also investigated AIRPORT. LONG ISLAND. NEW YORK. USA Final Report. Wherein either a smoothing of the glide path structure or a Dec. 1977 • Jan. 1978 reduction of the required ground plane was considered an 4 Jan 1978 134 p improvement An extensive computer model was developed and (AD-A055447 FAA-NA-78-16 FAA-RD-78-16) Avail NTIS it was used to study the effect on glide path DDM of different HC A07/MF A01 CSCL 17/2 position arrangements of elements It was found that a unique The TRSB (Time Reference Scanning Beam) system was arrangement of elements could be found for any terrain demonstrated at JFK airport in December 1977 and consisted environment which would give a zero DDM along the entire of a 1 degree phased array azimuth subsystem, a 1 5 degree glide path up to threshold G Y elevation subsystem with an antenna of the Rotman lens design and a precision L-Band DME A laser tracker was provided for precise aircraft position data but was considered unusable However. TRSB airborne recordings are available for several flights N78-31074jjl Lincoln Lab Mass Inst of Tech Lexington and provide useful data output During the operational demonstra- IPC DESIGN VALIDATION AND FLIGHT TESTING tions national and international observers in the NASA B-737 Final Report aircraft flew the Canarsie approaches, under fully coupled and J W Andrews. J C Koegler and K D Senne 31 Mar 1978 manual flight conditions to touchdown and rollout These 267 p refs demonstrations highlighted the important capability of Microwave (Contracts DOT-FA72WAI-261 F19628-78-C-0002 Proj Landing Systems to provide precision guidance over complex 034-241-012) approach paths to a busy international airport G Y (AD-A055529. ATC-85 FAA-RD-77-150) Avail NTIS HC A12/MF A01 CSCL 01/4 N78-31O71# National Aviation Facilities Experimental Center A series of flight tests were conducted to evaluate the collision Atlantic City N J avoidance system known as intermittent positive control TRSB MICROWAVE LANDING SYSTEM DEMONSTRATION (subsequently re-named automatic traffic advisory and resolution PROGRAM AT KRISTIANSAND. NORWAY Final Report. service ATARS) These tests involved both professional test pilots 15-17 Jan 1978 and subject pilots selected from the aviation community Analysis Jan 1978 82 p of the collision avoidance algorithm pilot visual acquisition (AD-A055317 FAA-NA-78-17 FAA-RD-78-17) Avail NTIS performance and pilot reaction to avoidance instructions are HC A05/MF A01 CSCL 01/2 also included B B A demonstration of Kjevik Airport Knstiansand Norway, was the fifth in a series of operational demonstrations of several TRSB system configurations at selected airports m the United N78-31076I Federal Aviation Administration Washington D C States and abroad Operational demonstrations and data IFR AIRCRAFT HANDLED FORECAST BY AIR ROUTE acquisition flights were made utilizing an FA A Boeing 727 test TRAFFIC CONTROL CENTER. FISCAL YEARS 1978-1989 aircraft Flight profiles included approaches radials. and partial Bernard Hannan Nov 1977 51 p orbits perpendicular to the runway centerlme Some flight tests (AD-A049305 FAA-AUP-77-34) Avail NTIS were also made by Norwegian and British Civil Aviation Authority HC A04/MF A01 CSCL 17/7 personnel using TRSB equipment installed in their respective The forecasts of instrument flight rule aircraft handled by flight inspection aircraft Results of the operational demonstrations FAA air route traffic control centers are presented They serve indicated that the performance of both system configurations as a base for the FAA planning and budget process in determining was well within their respective U S program design requirements future requirements for facilities equipment and manpower The and also met ICAO (AWOP) full capability system requirements forecasts show that total aircraft handled will increase from B B 25 7 million FY 1977 to 41 5 million in FY 1989 These national total numbers along with those for the intervening years are N78-31072# National Aviation Facilities Experimental Center, broken down by FAA region and by each air route traffic control Atlantic City. N J center in this report G G TRSB MICROWAVE LANDING SYSTEM DEMONSTRATION PROGRAM AT CHARLEROI. BELGIUM Final Report. N78-31076/C Committee on Science and Technology (U S 18 Jan. - 6 Fab 1978 House) Feb 1978 52 p FUTURE NEEDS AND OPPORTUNITIES IN THE AIR (AD-A055920. FAA-NA-78-19 FAA-RD-78-19) Avail NTIS TRAFFIC CONTROL SYSTEM HC A04/MF A01 CSCL 01/4 Washington GPO 1977 716 p refs Hearings before Subcomm A demonstration was held at Gosselies Airport. Charleroi. on Transportation Aviation and Weather of the Comm on Sci Belgium in conjunction with the United States TRSB demonstra- and Techno! 95th Congr 1st Sess 8-9 14-16 Jun 8 Sep tion program, and was the sixth in a series of operational 1977 demonstrations of several TRSB system configurations at selected (GPO-98-931) Avail Subcomm on Transportation Aviation airports in the United States and abroad Operational demonstra- and Weather tions were made utilizing FAA Boeing 727 and Convair 880 Testimony concerning the philosophies and issues related to test aircraft Flight performance data was acquired with the Boeing future or post third generation air traffic control (ATC) systems 727 test aircraft only Flight profiles included approaches on is presented Research and development programs microwave centerlme and offset plus and minus 1 and 2 degrees at various landing systems, wind shear wake vortex availability of energy elevation angles and radials at constant altitude on centerlme and the economic climate are among the factors considered and offset plus and minus 10 degrees Results of the operational Emphasis is placed on the enhancement of system capacity demonstrations indicated that the performance of the TRSB Small safety and productivity Aviation demands of the public are Community azimuth subsystem met ICAO (AWOP)full capability projected through the turn of the century in terms of expansion systems requirements B B of ATC services J M S

559 N78-31077

N78-31077# Air Force Inst of Tech Wright-Patterson AFB G D Brewer R E Morris G W Davis, E F Versaw G R Ohio School of Engineering Cunnmgton Jr (Lockheed Missiles and Space Co, Inc) J C A DESIGN OF TRAJECTORY ESTIMATOR USING MULTIPLE Riple (AiResearch Mfg Co ), C F Baerst (AiResearch Mfg Co), DME RANGE MEASUREMENTS M S Thesis and G Garmong (Rocketdyne) Jul 1978 202 p 2 Vol Robert Riggins Mar 1978 134 p refs (Contract NAS1-14614) (AD-A055191. AFIT/GGC/EE/78-4) Avail NTIS (NASA-CR-145369-Vol-1 LR-28384-Vol-1) Avail NTIS HC A07/MF A01 CSCL 17/7 HC A10/MF A01 CSCL 01C This report is directed toward the design of a real-time Several engine concepts examined to determine a preferred estimation algorithm, a Kalman filter, that estimates aircraft design which most effectively exploits the characteristics of position and velocity using multiple DME range measurements hydrogen fuel in aircraft tanks received major emphasis Many The estimator is designed and tested lor feasibility as a reference candidate designs of tank structure and cryogenic insulation system for examining Inertial Navigational System (INS) low systdms were evaluated Designs of all major elements of the frequency errors Both a 9 state estimator including jerk states aircraft fuel system including pumps lines, valves, regulators, and a 7 state estimator without the jerk states are designed and heat exchangers received attention Selected designs of boost GRA pumps to be mounted in the LH2 tanks and of a high pressure pump to be mounted on the engine were defined A final N78-31078# Air Force Inst of Tech . Wright-Patterson AFB. design of LH2-fueled transport aircraft was established which Ohio School of Engineering incorporates a preferred design of fuel system That aircraft was PERFORMANCE IN A JAMMING ENVIRONMENT OF A then compared with a conventionally fueled counterpart designed LOW-COST GPS USER RECEIVER ALGORITHM FOR to equivalent technology standards Author AIDING A TACTICAL INS M S Thesis Stephen E Cross Dec 1977 133 p rets N78-31086*# Lockheed-California Co Burbank (AD-A055239 AFIT/EE/GGC/77-2) Avail NTIS STUDY OF FUEL SYSTEMS FOR LH2 FUELED SUBSONIC HC A07/MF A01 CSCL 17/4 TRANSPORT AIRCRAFT. VOLUME 2 Final Report. Sep The design and evaluation of a position and velocity estimation 1976 - Dec 1977 algorithm for a low-cost Global Positioning System (GPS) user G D Brewer R E Morris, G W Davis E F Versaw G R receiver is presented The algorithm is intended as a navigation Cunnmgton Jr (Lockheed Missiles and Space Co, Inc), J C aid for a tactical aircraft The algorithm is based on linearized Hiple tAiBesearch Mfg Co), C F Baerst (AiResearch Mig Co) range and range rate equations using the INS indicated position and G Garmong (Rocketdyne) Jul 1978 356 p refs 2 Vol and velocity and the GPS user receivers measured range and (Contract NAS1-14614) range rate Hotellmg s iterative matrix inversion algorithm is used (NASA-CR-145369-Vol-2) Avail NTIS HC A16/MF A01 CSCL to invert a (4 x 4) measurement matrix A feedback and 01C feedforward mechanization is proposed for the estimation For abstract, see N78-31085 algorithm The performance is based on simulations using a dynamic F-4 flight profile Comparisons are made with results N78-31087# Royal Aircraft Establishment Farnborough obtained from a Carlson Square Root Filter and an unaided (England) INS Author (GRA) TECHNICAL EVALUATION OF FLYING WEAPON SYS- TEMS P Ebelmg Mar 1978 28 p refs Transl into ENGLISH of N78-31083 Iowa State Umv of Science and Technology, Ames Technische Bewertung Fliegender Waffensysteme ' Rept TRAJECTORY OPTIMIZATION FOR SOME SAILPLANE BMVg-FBWT-75-29-Pt-2 Fed German Mm of Defense West PERFORMANCE PROBLEMS Ph D Thesis Germany 1975 p 243-272 Imao Chen 1978 217 p (RAE-Ub-Trans-1948. BR64083) Avail NTIS Avail Ur.iv Microfilms Order No 78-13220 HC A03/MF A01 Three specific sailplane performance problems are formu'ated Some details on the evaluation of military aircraft and missile as optimal control problems and studied (1) minimum landing- weapon systems are presented A technical evaluation of the approach distance problem, (2) minimum altitude-loss problems different phases of weapon systems development and procurement in the presence of sinusoidal vertical winds, and (3) minimum is explained and a brief survey is given of the different methods time problems m the presence of sinusoidal vertical winds Both involved Two digital computer programs are detailed for design minimum altitude-loss and minimum time problems have and scaling of aircraft and tactical missiles and their possible several cases involved (1) fixed and equal initial and final states. applications within the technical evaluation of weapon systems (2) free but equal initial and final states, (3) effects of varying GG the wind amplitude (4) effects of varying the fixed range, and (5) wing-loading effects One more case of effects of varying N78 31088# Lockheed-California Co . Burbank the prescribed altitude loss for minimum time problems is also GENERAL AVIATION AIRPLANE STRUCTURAL CRASH- studied Dissert Abstr WORTHINESS USER'S MANUAL VOLUME 1 PROGRAM KRASH THEORY Final Report. Jun 1976 - Feb 1978 N78-31084 Purdue Umv Lafayette Ind Max A Gamon Feb 1978 278 p refs EFFECTS OF DYNAMIC AEROELASTICITY ON HANDLING (Contract DOT-FA75WA-3707) QUALITIES AND PILOT RATING Ph D Thesis (AD-A055898. LR-28307-Vol-1 FAA-RD-77-189-1-Vol-1) Wen-Yo Yen 1977 122 p Avail NTIS HC A13/MF A01 CSCL 01/2 Avail Unw Microfilms Otdef No 78-13142 A comprehensive description of program KHASH is pro- Pilot performance parameters, such as pilot ratings tracking vided Included are the following sections 0 (Program KRASH errors and pilot comments were determined for a longitudinal Description and Theory and (2)Program Controls and Listing pitch tracking task using a large flexible bomber with parametric B B variations in the undamped natural frequencies of the two lowest frequency symmetric elastic modes This pitch tracking task was programmed on a fixed base simulator with an electronic N78-31089| Boeing Vertol Co Philadelphia Pa attitude-director display of pitch command, pitch angle and pitch HELICOPTER TRANSMISSION VIBRATION AND NOISE error The results of this study indicate that low-frequency REDUCTION PROGRAM VOLUME 1 TECHNICAL REPORT structural flexibility can significantly affect the handling qualities Final Report. Jun 1974 - Oct 1977 and pilot ratings in the task evaluated Dissert Abstr John J Sciarra. Robert W Howells Joseph W Lenski Jr. Raymond J Drago and Edward G Schaeffer Mar 1978 N78-31085*# Lockheed-California Co. Burbank 307 p refs STUDY OF FUEL SYSTEMS FOR LH2-FUELED SUBSONIC (Contract DAAJ02-74-C-0040 DA Proj 1G2-62207-AH-89) TRANSPORT AIRCRAFT. VOLUME 1 Final Report. Sep (AD-A055104 D210-11236-1 USARTL-TR-78-2A) Avail 1976 - Dec 1977 NTIS HC A14/MF A01 CSCL 01/3

560 N78 31096

The objective of the Helicopter Transmission Vibration/ Noise Ralph 0 Tate May 1978 35 p refs Reduction Program was to generate analytical tools for the (AD-A055784. USAAVRADCOM-TR-78-9) Avail NTIS prediction and reduction of helicopter transmission vibration/noise HC A03/MF A01 CSCL 01/3 that provide the capability to perform trade studies during the The Computerized Aircraft Attrition Program (THAAP) pre- design stage of a program Application of this optimization sented in this report provides for a rapid method of calculating the capability yields drive train components that are dynamically quiet forecasted attrition to be experienced by a given homogenous with reduced vibration/noise levels and inherently longer life fleet of aircraft over a specified period of time The THAAP Author (GRA) program is designed to be a time-saving tool which will provide the quantity of aircraft attnted and resultant flying hour program for the adjusted operational fleet The program will provide for N78-31091# Army Aviation Engineering Flight Activity. Edwards the time-phased induction and withdrawal of aircraft from the AFB, Calif fleet over the operational life of the system The information or MODIFIED HELICOPTER ICING SPRAY SYSTEM EVALUA- output from the program is intended to be used as input to TION Final Report. 23 Sap - 4 Dec 1976 time-phased cost estimates particularly operating and support Gary L Bender Mat hew S Mathews III and John S Tulloch cost estimates The program s output is ideally suited for those Mar 1977 87 p refs studies which are performed manually or by computerized cost (AD-A055039. USAAEFA-75-04) Avail NTIS models which do not have a fleet attrition capability HC A05/MF A01 CSCL 01/3 Author (GRA) All tests required 55 flight hours (41 flights) During the first testing period, structural and dynamic tests were conducted N78-31096| Aeronautical Systems Div Wright-Patterson AFB. throughout the CH-47C flight envelope and the physical properties Ohio of the spray cloud generated by the modified icing spray system CARGO AIRCRAFT AND SPACECRAFT FORWARD were measured Two deficiencies were found boom stresses RESTRAINT CRITERIA Final Report. Jun 1976 - Dec. greater than the materials endurance limit which severely restricted 1977 the maximum airspeed at which the system could be operated Joseph L Wemgarten Dec 1977 91 p refs Revised (110 knots true airspeed) and an inadequate and unsafe boom (AD-A055343. ASD-TR-76-30I Avail NTIS HC A05/MF A01 extension/retraction system Additional modification was made CSCL 01/2 to the system and envelope expansion tests were repeated During This investigation was primarily conducted to review probabil- the second testing period, the two deficiencies were eliminated ity projections of crashes of Air Force cargo aircraft as developed However, flight with the boom retracted (except at very low in 1971 The 1971 effort resulted in considerable changes to airspeeds) and flight at a rotor speed of 235 rpm continued to the air cargo operations This included a lowering of restraint produce excessive boom stresses These excessive stresses criteria to 3Gs with an auxiliary 9G net system The objective constituted a shortcoming Additional modification to the HISS of this effort was to determine if further reductions could be was made to correct this shortcoming The modified HISS with made through removal of the auxiliary 9G net. in addition to this additional change is airworthy within the unrestricted CH-47C both aircraft and spacecraft cargo restraint criteria Restraint flight envelope GRA and aircraft modifications were also examined This effort viewed probabilities, based on the original data from January 1960 to N78-31092# Army Agency for Aviation Safety, Fort Pucker July 1971. and an expanded base to July 1976 for a total of Ala 404 million hours Further the original study viewed only major ANTITOROUE TRAINING: EVALUATION OF EFFECTIVE- accidents, minor accidents have been added to this review The NESS IN REDUCING MISHAP LOSSES probabilities developed in 1971 were conservative relative to William C McDamel Feb 1978 19 p refs actual occurrence over the past few years Further, new (AD-A055040, USAAVS-TR-78-2) Avail NTIS probabilities were developed that show removal of the barrier HC A02/MF A01 CSCL 05/9 net is feasible and appropriate changes are recommended to This evaluation addressed the effectiveness of training for the current criteria Commercial experience with barrier nets was antitorque system malfunctions An evaluation team composed also investigated and accidents where barriers were impacted of 11 analysts reviewed 121 mishaps meeting established criteria are detailed GRA Results indicated that emergency antitorque training was effective in those situations involving loss or impaired control of the N78-31096# Mechanics Research. Inc. McLean, Va antitorque system In the case of emergency situations involving DEMONSTRATION OF THE MICROWAVE ICE PROTECTION a loss of thrust or loss of component present antitorque training CONCEPT Final Report. Jun 1976 - Jun 1977 appears to be less than adequate The data supports continuation Bertram Magenheim May 1978 127 p refs of emergency antitorque training Results further imply that written (Contract DAAJ02-76-C-0052 DA Proj 1L2-62209-AH-76) procedures for coping with loss of thrust in the UH-1 and OH-58 (AD-A055824. USAAMRDL-TR-77-34) Avail NTIS should be reviewed for clarity and revised for ease of application HC A07/MF A01 CSCL 01/3 Further study shpuld be conducted to determine the optimal An experimental demonstration of the microwave ice course of action to take in the event of antitorque failure or protection concept for helicopter rotor blades is presented By malfunction Author (GRA) shedding ice samples from experimental ice protection devices, microwave ice protection theory was verified Increased power N78-31093# Anne Research Corp. Annapolis. Md density in the ice layer is achieved by operating at higher PROGRAM ANALYSES FOR THE S-3 WEAPON SYSTEM microwave frequencies, resulting in significantly shorter shed times IMPROVEMENT PROGRAM Final Summary Report. 16 Sap for the same microwave power The microwave concept offers 1977-16 Jun. 1978 the possibility of constructing ice protection systems totally out W Amos 15 Jun 1978 20 p of nonmetallic materials that will not deteriorate the radar cross (Contract N00019-77-C-0495) section of composite blades Incremental weight, cost and (AD-A055887. Rept-1708-01-1-1762) Avail NTIS power estimates for equipping vanous helicopters are presented HC A02/MF A01 CSCL 01/3 An evolving microwave tube technology promises significant The overall objective of the program is to update maior improvements in cost, efficiency, weight and power drain while avionic and weapon subsystems of the S-3A to provide providing higher microwave powers and consequently shorter improvements and additional capabilities required to perform shed times It is demonstrated that a combination erosion certain sea control mission elements dunng the late 1980s through shield/surface waveguide constructed from ultrahigh molecular the 1990s GRA weight polyethylene (UHMWPE) fortified with a layer of polyurethane near the tip did not deteriorate the mean time N78-31094# Army Aviation Research and Development between unscheduled maintenance (MTBUM) of the blade below Command. St Louis. Mo that of the polyurethane erosion shield by itself When the erosion COMPUTERIZED AIRCRAFT ATTRITION PROGRAM shield/surface waveguide reaches the MTBUM it can be replaced Final Report without discarding the blade Author (GRA)

561 N78 31097

N78-31097# Massachusens Inst of .Tech Cambridge Aeroelas- small resultant cost increases can potentially be offset by the tic and Structures Research Lab delivery of more capable production items lessened needs for A STUDY OF ANALOG PROGRAMMING FOR PREDICTION postdelivery modification or retrofit and lower total-life system OF CRACK GROWTH IN AIRCRAFT STRUCTURES costs Author (GRA) SUBJECTED TO RANDOM LOADS Final Report. Sap 1976 - Jun 1977 Michael Wemreich Richard F Harris, Oscar Orrmger. and John N78-31101*# National Aeronautics and Space Administration F McCarthy. Jr Jun 1977 94 p refs Langley Research Center. Hampton. Va (Contract F33615-76-C-3109) SIMULATION AND FLIGHT EVALUATION OF A HEAD-UP (AD-A055789. ASRL-TR-186-2. AFFD L-TR-77-58) Avail LANDING AID FOR GENERAL AVIATION NTIS HC A05/MF A01 CSCL 01/3 Randall L Hams. Sr, Maxwell W Goode and Kenneth R Yenni Results of a program to study an analog approach to risk Sep 1978 38 p refs analysis of random-load crack growth are presented The two (NASA-TP-1276 L-12197) Avail NTIS HC A03/MF A01 major objectives were to implement certain specific simulations CSCL 01D A head-up general aviation landing aid called a landing site of crack growth on hybrid analog/digital hardware and to develop an improved approach to the modeling of random loads Under indicator (LASI) was tested in a fixed-base visual simulator and the first objective all but two of the specific simulations were in an airplane to determine the effectiveness of the LASI The implemented and verified One not implemented required hardware display, which had a simplified format and method of implementa- unavailable at the installation utilized for the simulations The tion presented to the pilot in his line of sight through the other was identified as not conducive to analog simulation These windshield a graphic representation of the airplane's velocity simulations utilized a 'damage parameter (rather than crack size vector In each testing model (simulation of flight) each of 4 pilots itself as the random variable) to provide well behaved and stable made 20 landing approaches with the LASI and 20 approaches analog behavior Under the second objective, a method of without it The standard deviations of approach and touchdown generating load statistics by direct inspection of large quantities parameters were considered an indication of pilot consistency of flight data was developed In the course of this development Use of the LASI improved consistency and also reduced elevator the applicability of estimation theory to the present problem aileron and rudder control activity Pilots comments indicated was identified The techniques of estimation theory applied to that the LASI reduced work load An appendix is included with analysis of damage in terms of an appropriately chosen damage a discussion of the simulator effectiveness for visual flight parameter promise to provide improved efficiency and accuracy tasks Author in aircraft fatigue damage risk analysis GRA N78-31102# Research Triangle Inst. Research Triangle Park N C AFAL SIMULATION FACILITY/CAPABILITY MANUAL N78-31O98jjl Naval Air Development Center Warmmster Pa VOLUME 1 EXECUTIVE SUMMARY AND SYSTEMS Aircraft and Crew Systems Technology Directorate AVIONICS DIVISION Final Technical Report. Jul 1976 - STATISTICAL REVIEW OF COUNTING ACCELEROMETER Jun 1977 DATA FOR NAVY AND MARINE FLEET AIRCRAFT FROM Richard A Whisnant. W Howard Ruedger Ronald L Earp and 1 JANUARY 1962 TO 31 DECEMBER 1977 Semi-annual James Haidt Wright-Patterson AFB Ohio AFAL 30 Jun 1977 Summary Report. 1 Jan 1962 - 31 Dec 1977 411 p refs Alan M Kaniss 1 May 1978 153 p (Contract F33615-76-C-1308) (AD-A055672 NADC-13920-2) Avail NTIS (AD-A055591. AFAL-TR-77-118-Vol-1) Avail NTIS HC A08/MF A01 CSCL 01/3 HC A18/MF A01 CSCL 01/3 This report is a specialized summary of normal acceleration The Air Force Avionics Laboratory (AFAL) at Wright-Patterson data recorded by counting accelerometers Data are separated AFB is the focal point for development of new avionics technology by calendar time and mission category Only data reported in for the Air Force In order to carry out this responsibility a the counting accelerometer program are included Author (GRA) significant capability to simulate physical avionics systems and components has been created by the AFAL divisions Of prime concern is the effective use of these simulation facilities in the face of continually increasing performance requirements technological advances and rising flight-test costs GRA N78-31099| Sandia Labs Livermore Calif Test Products Div 8412 GRAPHICS FOR THE HYBRID STORES SEPARATION N78-31103*jjf National Aeronautics and Space Administration SIMULATION OF THE B77 SYSTEM Lewis Research Center Cleveland Ohio R G Marmon Mar 1978 43 p refs GAS PATH SEAL Patent Application (Contract EY-76-C-04-789) Robert C Bill and Lawrence P Ludwig inventors (to NASA) (SAND-78-8212) Avail NTIS HC A03/MF A01 Filed 4 Aug 1978 9 p The B77 is pictonally illustrated with the B52 F111 F4 (NASA-Case-Lew-12131-2. US-Patent-Appl-SN-931090) Avail and A7 aircraft in hybrid simulations The design goals are covered NTIS HC A02/MF A01 CSCL 21E and pictorial plots are given to verify the results Actual flight A gas path seal for a turbine engine or compressor is provided test film is compared to a simulation with good results ERA The gas path seal comprises a shroud of material wearable or abradable relative to the material of the turbine or compressor blades and closely spaced from the blade tips A compliant backing preferably of several layers of corrugated metal or a compliant N78-3110O# RAND Corp. Santa Monica Calif material covered with a thin layer of ductile material is provided ESTIMATED COSTS OF EXTENDED LOW-RATE AIRFRAME about the shroud and a rigid mounting surrounds the compliant PRODUCTION Interim Report backing The novel feature is a compliant backing between the David J Dreyfuss and Joseph P Large Mar 1978 69 p refs shroud and mounting As a result normal forces during a blade (Contract F49620-77-C-0023) rub are limited and wear is reduced and the life of the shroud (AD-A054834, RAND/R-2243-AF) Avail NTIS is lengthened for a design of comparable clearance of blade to HC A04/MF A01 CSCL 01/3 shroud NASA Achieving a high rate of production as quickly as possible has traditionally been viewed as the most effective way of satisfying time-urgent inventory requirements while keeping N78-311O4 Aeronautical Research Labs. Melbourne (Australia) production costs low One common consequence has been the A THEORETICAL STUDY OF THE PERFORMANCE OF A delivery of less than fully qualified production articles This NUMBER OF DIFFERENT AXIAL-FLOW TURBINE CONFIG- report discusses the cost of extending initial low-rate production URATIONS UNDER CONDITIONS OF PULSATING FLOW while tests of early production articles continue The relatively Lincoln Erm Jul 1977 55 p refs

562 N78-31112

(ARL-Mech-Eng-Rept-149 AR-OOO-734) Copynght Avail part of the flight envelope In the frequency domain category, Issuing Activity works were published in the areas of low-interaction design The best turbine configuration for operation with the pulsating polynomial design and multiple setpomt studies A number of flow occurring in a constant volume gas turbine was determined these ideas progressed to the point at which they are starting and described The method of turbine performance prediction to attract practical interest In the nonlinear category, advances for steady flow operating conditions was developed for a single were made both in engine modelling and in the details associated stage axial flow turbine During this development it was found with software for determination of time optimal controls Nonlinear that existing correlations for determining turbine loss characteris- models for a two spool turbofan engine were expanded and tics at high negative angles of incidence were inadequate, and refined and a promising new approach to automatic model consequently a modified approach was developed Four basic generation was placed under study A two time scale scheme two stage turbines each having different blades angles as well was developed to do two-dimensional dynamic programming as several versions of one of these were chosen for analysis and an outward spiral sweep technique has greatly speeded The mean efficiencies of these machines for pulsating flow convergence times in time optimal calculations F O S operating conditions were estimated by using a quasi-steady method of analysis The results obtained for the selected turbines N78-31108*| General Electric Co Cincinnati Ohio Aircraft are presented and compared with the results for the radial inflow Engine Group turbine A configuration is proposed that could possibly give ENERGY EFFICIENT ENGINE PRELIMINARY DESIGN AND better mean efficiencies under pulsating flow conditions than INTEGRATION STUDIES Final Report. Jan 1977 - Apr those actually considered B B 1978 R P Johnston R Hirschkron C C Koch R E Neitzel and P N78-31105*# Naval Air Propulsion Test Center Trenton NJ W Vmson Sep 1978 417 p refs ROTOR BURST PROTECTION PROGRAM STATISTICS ON (Contract NAS3-20627) AIRCRAFT GAS TURBINE ENGINE ROTOR FAILURES THAT (NASA-CR-135444 R78AEG510) Avail NTIS OCCURRED IN US COMMERCIAL AVIATION DURING 197S HC A18/MF A01 CSCL 21E Final Report. 1974 - 1975 Parametric design and mission evaluations of advanced R A DeLucia and G J Mangano May 1977 29 p turbofan configurations were conducted for future transpct aircraft (NASA Order C-41581-B) application Economics environmental suitability and fuel efficiency (NASA-CR-135304 NAPTC-PE-106) Avail NTIS /.ere investigated and compared with goals set by NASA Of HC A03/MF A01 CSCL 21E the candidate engines which included mixed- and separate-flow, Statistics on gas turbine rotor failures that have occurred in direct-drive and geared configurations an advanced mixed-flow US commercial aviation during 1975 are presented The compiled direct-drive configuration was selected for further design and data were analyzed to establish (1) The incidence of rotor failures evaluation All goals were judged to have been met except the and the number of contained and uncontamed rotor bursts (2) The acoustic goal Also conducted was a performance risk analysis distribution of rotor bursts with respect to engine rotor component. and a preliminary aerodynamic design of the 10 stage IB fan compressor or turbine (3) The type of rotor fragment 23 1 pressure ratio compressor used in the study engines (disk rim or blade) typically generated at burst (4) The cause Author of failure. (5) The type of engines mvolvad. and (6) The flight condition at the time of failure B B N78-31111# Mechanical Technology Inc Latham N Y TURBINE ENGINE ROTORDYNAMIC EVALUATION. N78-31106*fjl Pratt and Whitney Aircraft Group West Palm VOLUME 1 Final Report. 1 May 1975 - 1 Jun 1976 Beach Fla Government Products Div R A Rio Wright-Patterson AFB Ohio AFAPL Jan 1978 ADVANCED OPTICAL BLADE TIP CLEARANCE MEASURE- 218 p MENT SVSTEM (Contract F33615-75-C-2035 AF Proj 3066) M J Ford R E Honeycutt R E Nordlund and W W Robinson (AD-A055262 MTI-76TR41-Vol-1 AFAPL-TR-76-81-Vol-1) Jul 1978 85 p refs Avail NTIS HC A10/MF A01 CSCL 21/5 (Contract NAS3-20479) Eight jet engine models within the Air Force inventory (the (NASA-CR-159402 FR-1020OA) Avail NTIS T56 J57 J79 J85 TF30 TF33 TF39 and TF41) have been HC A05/MF A01 CSCL 21 E analyzed to determine critical speeds unbalance response blade An advanced electro-optical system was developed to measure loss effects and maneuver deflections The effects of dampers single blade tip clearances and average blade tip clearances thrust loads and balancing requirements while not analyzed in between a rotor and its gas path seal in an operating gas turbine depth were noted where applicable in the description of the engine This system is applicable to fan compressor and turbine engine s dynamic behavior Each rotor design was then classified blade tip clearance measurement requirements and the system into categories of dynamic sensitivity Five test elements were probe is particularly suitable for operation in the extreme turbine manufactured and vibrated to obtain experimental data for environment A study of optical properties of blade tips was correlation with analytical modeling predictions The four cylindrical conducted to establish measurement system application limita- elements each of which incorporated either a steep cone tions A series of laboratory tests was conducted to determine shallow cone, flat plate or thin shell were excited to obtain the the measurement system's operational performance characteris- first three lateral natural frequencies Because of manufacturing tics and to demonstrate system capability under simulated problems with hardness and weld penetration measured operating gas turbine environmental conditions Operational and frequencies were below those predicted The fifth test element environmental performance test data are presented Author was a machined flexible bearing support for use in parallel with a squeeze film damper After static and dynamic testing of this N78-31107*# Notre Dame Umv Ind Dept of Electrical representative flexible bearing support the results were within Engineering 10% of the analytical prediction for this element The information ALTERNATIVES FOR JET ENGINE CONTROL Final Technical from this analytical and experimental study has resulted in a Report. 1 Mar 1977 - 28 F«b 1978 technology plan whose goal is to improve the technological R J Leake and M K Sam 26 Feb 1978 233 p refs capabilities for the purpose of reducing costs associated with (Grant NsG-3048) reliability and maintainability of U S Air Force engines (NASA-CR-157578) Avail NTIS HC A11/MF A01 CSCL Author (GRA) 21E General goals of the research were classified into two N78-31112jjl Grumman Aerospace Corp Bethpage. N Y categories The first category involves the use of modern Research Dept multivanable frequency domain methods for control of engine GROUND IMPINGEMENT OF A FAN JET EXHAUST models in the neighborhood of a quiescent point The second PLUME category involves the use of nonlinear modelling and optimization William G Hill Jr and Richard C Jenkins May 1978 52 p techniques for control of engine models ox or a more extensive refs

563 N78 31113

(AD-A054832 RM-653) Avail NTIS HC A04/MF A01 CSCL FLAME STABILIZATION IN A RAMJET COMBUSTION 21/2 CHAMBER BY MEANS OF A PILOT GAS GENERATOR This report describes an investigation of the ground impinge- Egbert Riester 16 Dec 1977 54 p refs In GERMAN, ENGLISH ment properties of a fan jet engine exhaust Measurements were summary Report will also be announced as translation taken using both a simulated fan jet of laboratory scale and a (ESA-TT-511) large scale operating fan jet engine The results of this work (DLR-FB-77-54) Avail NTIS HC A04/MF A01. DFVLR, Cologne will be used to modify existing models of exhaust-ground DM 28.20 interactions to include the unique properties of fan jet impingement Flame stabilization in ramjet combustors being difficult on the flow field under a hovering VTOL aircraft with particular because of the high combustion chamber entrance velocity and application to the Grumman Design 698 The simulated fan jet the low temperature the shifting of the flame out limit towards exhaust was produced by cold air issuing from a concentric lower equivalent ratios by use of a pilot gas generator was nozzle and utilizing a screen in the inner section to develop the investigated The velocity distributions are determined in a typical lower dynamic pressure that is characteristic of a real fan jet arrangement of a ramjet combustor The flame-out limit was engine Measurements taken during impingement of the jet engine measured, at first without, afterwards with a pilot gas genera- exhaust consisted of pilot pressure profiles above the ground tor The results were compared with each other As pilot gas Wall jet velocity profiles obtained in these two impingement generator a small stoichiometrical propane-oxygen-burner was flows showed close agreement when scaled by size and nozzle used Author (ESA) pressure ratio This favorable comparison demonstrates the effectiveness of using cold air scale model flows to simulate N78-31118f Iowa State Univ of Science and Technology the impingement flow field of a real fan jet engine exhaust The Ames Engineering Research Inst effects on the impingement flow of an immersed control vane ANALYSIS OF MULTISTAGE. AXIAL FLOW TUR- were investigated in both the simulated and the fan jet engine BOMACHINE WAKE PRODUCTION. TRANSPORT. AND exhausts Author (GRA) INTERACTION Interim Report. 1 Oct. 1976 - 30 Sep 1977 J H Wagner and T H Okiishi Dec 1977 113 p refs (Grant AF-AFOSR-2916-76) N78-31113# Pratt and Whitney Aircraft Group, West Palm (AD-A055754, ISU-ERI-AMES-78173, TCRL-10 Beach, Fla Government Products Div AFOSR-78-1028TR) Avail NTIS HC A06/MF A01 CSCL RADIOGRAPHIC EXAMINATION OF T55 ENGINE 20/4 Final Report. Apr 1977 - Jan. 1978 A periodic-average flow measurement technique involving a John T Carroll Jan 1978 24 p refs hot-wire anemometer system was used to measure the periodically (Contract DAAJ01-77-C-0354) unsteady and three-dimensional fluid velocity field between blade (AD-A055108 FR-9560 USAAVRADCOM-CH47-M-78-01) rows in the first stage of a low-speed multistage, axial-flow Avail NTIS HC A02/MF A01 CSCL 21/5 research compressor These data suggest that the fluid flow Approximately 1000 radiographs and three hours of video through the imbedded rotor and stator rows is appreciably fluoroscope tapes of a Lycoming T55-L-712 turbine engine were unsteady, in a periodic fashion in portions of the compressor obtained at various engine operating conditions These X-ray annulus Illustrative examples of periodic-average fluid flow field images were needed to determine certain static and running variation with rotor blade sampling position in stop-action clearances in the T55 engine Author (GRA) sequence are presented for different locations in the compressor A simple, first order approximation physical description of the N78-31114# Boeing Vertol Co. Philadelphia Pa blade wake flow transport and interaction process largely based ENGINE/AIRFRAME/ORIVE TRAIN DYNAMIC INTERFACE on experimental data interpretation is proposed to organize and DOCUMENTATION Final Report to help explain the obsdrvations made Blade span variations of D A Richardson and J R Alwang Apr 1978 209 p refs flow data reflect erid-wall effects Inlet guide vane exit flow (Contract DAAJ02-77-C-0040) data involve some unusual unsteady flow effects Author (GRA) (AD-A055766 D210-11328-1, USARTL-TR-78-11) Avail NTIS HC A10/MF A01 CSCL 21/5 Engme/airframe/drive train dynamic interface problems of Boeing helicopters are described The investigation leading to N78-31119# Hughes Helicopters. Culver City, Calif the problem solution, the solution and its limitations are discussed EVALUATION OF A CIRCULATION CONTROL TAIL BOOM Forecasts of potential future problems recommendation for FOR YAW CONTROL Final Report. 1 Mar 1977-1 Feb investigations, and specifications are included Author (GRA) 1978 A H Logan Apr 1978 52 p refs N78-3111S| General Electric Co Lynn Mass Aircraft Engine (Contract DAAJ02-77-C-0018) Group (AD-A055116, HH-77-307, USARTL-TR-78-10) Avail NTIS TURBINE TIP CLEARANCE MEASUREMENT Final Report. HC A04/MF A01 CSCL 01/3 Jun 1975 - Oct 1977 An experimental tail boom which uses circulation control Lawrence C Baker Gordon E Grady, and Hagen R Mauch principles to produce antitorque force from the mam rotor Mar 1978 179 p refs downwash was flight-tested over a typical flight regime The (Contract DAAJ02-75-C-0046) flight envelope included hover, sideward and rearward flight to (AD-A055765 R78AEG017 USARTL-TR-78-4) Avail NTIS 30 knots forward flight to 80 knots, climbs, turns, and maneuvers, HC A09/MF A01 CSCL 21/5 such as pull-ups, and push-overs at 60 knots, and autorotation Turbine tip clearance design and prediction techniques have GRA been limited to analytical methods for lack of an accurate direct measurement device It was the purpose of this program to N78-3112Of Applied Devices Corp Kissimmee. Fla substantiate prediction correlations utilizing direct measurements A MODULAR ADAPTIVE, VARIABLE FUNCTION FLIGHT from a laser-powered miniaturized turbine tip clearance device CONTROL SENSOR Final Report. Mar 1975 - Feb 1977 (MTCMO) previously developed under Applied Technology Roland Pittman Oct 1977 80 p refs Laboratory support The resultant comparisons of measured versus (Contract F33615-75-C-3154) analytically determined clearances based on measured tempera- (AD-A055175 AFFDL-TR-77-112) Avail NTIS tures would be used to verify or to improve the analytical HC A05/MF A01 CSCL 01/4 techniques GRA This development effort culminated in flight-worthy test articles of multi-function sensors, for use m 'strap-down' flight N78-31117# Deutsche Forschungs- und Versuchsanstalt fuer control systems The multi-function sensor with one moving part, Luft- und Raumfahrt Brunswick (West Germany) Abt performs the equivalent to a two-axis rate gyro two-axis linear Flugkoerperantnebe accelerometer. a three-axis magnetic field sensor a two-axis

564 N7831126

electric field sensor and a two-axis air data probe This 1978 182 p refs development effort demonstrated the feasibility of a multi-function (Contract N00019-75-C-0528) sensor which brings together the elements of a multi-mode flight (AD-A055892, AMS-1325) Avail NTIS HC A09/MF A01 control sensing scheme' that is one which takes a measure of CSCL 01/2 the earth's electric and magnetic fields the air mass through The results of an analysis and flight test research program which the carrying vehicle is moving, and a measure of vehicle sponsored by the Naval Air Systems Command are presented angular velocity and linear acceleration Its use is intended to The equivalence between Approach Power Compensator System determine vehicle heading velocity, and attitude with respect to (APCS) feedbacks and aircraft stability derivatives is shown and the magnetic north air mass flow and local vertical The aim of expressions relating these terms to system decoupling are the effort was to reduce cost, power consumption, volume and developed in the analysis Attitude command washout prefilter mechanical complexity by an order of magnitude GRA and conventional flight control systems are compared in ground and flight tests Pseudo-velocity-type APCS configurations were found to provide better flight path control than predominantly N78-31121# Air Force Inst of Tech Wright-Patterson AFB. Ohio School of Engineering angle of attack type APCS configurations for the carrier approach task For typical levels of aircraft static stability, increasing the THE TERRAIN FOLLOWING TASK FOR THE ADVANCED short period frequency through a simple pitch attitude command TACTICAL FIGHTER USING DISCRETE OPTIMAL CONTROL flight control system improved the flight path response MS Thesn Author (GRA) Ross Leon Simmons Dec 1977 110 p refs (AD-A055196 AFIT/GE/EE/77-39) Avail NTIS HC A06/MF A01 CSCL 01/3 N78-31124jjf Missouri Univ - Columbia Dept of Electrical Through the use of state space continuous optimal control, Engineering and discrete optimal control, a digital flight control system was INHERENT ERRORS IN ASYNCHRONOUS DIGITAL FLIGHT designed for the terrain following task After formulating the CONTROLS Annual Technical Report. 1 Feb 1977 - 31 Jan aircraft linear perturbation model the deterministic regulator 1978 problem was solved with a quadratic performance index to provide Charles Slrvmsky 31 Mar 1978 254 p refs the desired continuous closed loop system The system and (Grant AF-AFOSR-2968-76) performance index were then discretized to form a discrete (AD-A055649. AFOSR-78-1054TR) Avail NTIS deterministic regulator problem This discrete regulator problem HC A12/MF A01 CSCL 01/4 was then solved as a function of sample rate using eigenvector This report describes research on redundancy management decomposition to determine a minimum acceptable rate for in digital flight control systems The emphasis is on the properties, sampling The effects of sample rate on the system were then techniques, and requirements associated with the operations of examined A sample rate of five hertz was shown to be high monitoring and voting and their effects on the closed loop system enough to adequately form the desired controls A reference operation when asynchronous sampling is used Part 1 is command generator based on constant energy path legs was concerned primarily with the monitoring operation for quadredun- developed to provide the required reference states and control dant input signals Part 2 presents three extensions to a previously inputs The reference terrain following path was generated by reported model for closed loop flight control systems that have an optimal cubic spline algorithm The aircraft was shown to dual-redundant asynchronous digital controllers GRA track the desired path in a highly acceptable manner through the use of a hybrid simulation The design method utilized is N78-31126# Deutsche Forschungs- und Versuchsanstalt fuer recommended for consideration in designing the digital flight Luft- und Raumfahrt, Oberpfaffenhofen (West Germany) Abt control system for other flight control tasks Author (GRA) Regelungssysteme CONTROL SYSTEM DESIGN USING VECTOR-VALUED N78-31122# Air Force Inst of Tech Wright-Patterson AFB. PERFORMANCE CRITERIA WITH APPLICATION TO THE Ohio School of Engineering CONTROL RATE REDUCTION IN PARAMETER INSENSI- OPTIMAL TERRAIN FOLLOWING CONTROLLER FOR AN TIVE CONTROL SYSTEMS OPTIMIZED SPLINE REFERENCE PATH M S Trieste Gerhard Kreisselmeier 20 Dec 1977 36 p refs In GERMAN, Ronald T Kelly Dec 1977 136 p refs ENGLISH summary Report will also be announced as translation (AD-A055234. AFIT/GA/EE/77-3) Avail NTIS (ESA-TT-512) HC A07/MF A01 CSCL 01/3 (DLR-FB-77-55) Avail NTIS HCA03/MFA01 DFVLR Cologne This thesis presents the design of a proposed terrain following DM 17 flight controller capable of tracking a cubic spline reference path For a realistic flight control problem it is shown that a The controller tracks only the longitudinal motion, however, it vector performance criterion is a natural and meaningful criterion provides both thrust and elevator control The controller is based for the judgement and the design of a control system For the on a nonlinear reference model constructed from an optimized controller design then a strategy is suggested, which includes spline path The spline path altitude and associated derivatives the vector-valued performance criterion in the optimization of are computed The longitudinal equations of motion are linearized the control system such that a systematic step by step about the reference trajectory and a truth model of actual aircraft improvement of the performance vector is achieved. IB motion is developed Deviations from the nonlinear reference improvement of certain of its components without undesirable trajectory to the actual provide a linear system Optimal control deterioration of the remaining components which finally yields theory is used to solve the resulting linear regulator problem the best possible controller design This technique is applied to The feedback gains are calculated from the steady-state Ricatti the design of a parameter insensitive flight path controller which matrix equation The two system controls are updated using shows a larger sensitivity reduction than obtained previously while these feedback gams Results show the feedback controller to a considerable reduction of the maximal control rate is achieved be stable and capable of tracking the cubic spline reference This controller is the first to prove, that a considerable sensitivity path The performance index weighting matrices can be adjusted reduction can be possible without increasing the requirements to improve the controller The resulting controller can provide of the actuator system These results are primarily due to the both good path control and engine control to improve vehicle direct consideration of the control rate in the design survivabihty engine life and fuel consumption Author (GRA) Author (ESA)

N78-31123| Princeton Univ N J Dept of Aerospace and Mechanical Sciences N78-31126# Advisory Group for Aerospace Research and THE INFLUENCE OF THROTTLE AUGMENTED STABILITY Development. Pans (France) (APCS) AND SHORT PERIOD CONTROL CHARACTERIS- CONSIDERATIONS ON WING STORES FLUTTER ASYM- TICS ON THE LANDING APPROACH Final Technical Report. METRY. FLUTTER SUPPRESSION Jul. 1976 - Jun. 1976 Jul 1978 42 p Presented at the 46th Struct and Mater George E Miller, Shigeo Sembongi. and Edward Seckel Mar Panel Meeting. Aalborg. Denmark. 10-14 Apr 1978

565 N78-31127

(AGARD-R-668. ISBN-92-835-1290-1) Avail NTIS longer runway occupancy times today are identified as they relate HC A03/MF A01 to airline, exit, aircraft, runway and airport Identified are potential The problems pertaining to aeroelasticity and flutter of aircraft short-term improvements that might be expected at particular wing stores are explained and solutions are suggested runways given an appropriately motivated environment G G

N78-31132jjf National Aviation Facilities Experimental Center N78-31127))/ Messerschmitt-Boelkow-Blohm G m b H Munich Atlantic City. N J (West Germany) DULLES CONTROL TOWER CONSOLE DESIGN STUDY ASYMMETRIC STORE FLUTTER Final Report, May 1977 - May 1978 A Lotze In AGARD Considerations on Wing Stores Flutter J Roy Bradley, Jr Jun 1978 46 p refs Jul 1978 p 1-19 refs (AD-A056200, FAA-NA-78-30. FAA-RD-78-69) Avail NTIS HC A03/MF A01 CSCL 01/5 Avail NTIS HC A03/MF A01 The development and testing effort directed toward providing A large number of asymmetncal store configurations were a plan for inservice improvements to the operational quarters of investigated by analysis and wind tunnel testing, to establish Dulles International Airport Control Tower is described Through the physical background for the flutter mechanism of asymmetrical the use of full-scale mockups, console designs and equipment stores and to find out whether unfavorable effects of asymmetries arrangements were established, modified and appraised Opinions exist only for mild flutter or could also occur for flutter cases and recommendations of Air personnel from Dulles Tower were exhibiting large gradients of aerodynamic damping with airspeed used as a basis for determining the advantages or disadvantages Based on the results it is recommended to establish flutter trends of particular equipments and their locations, console designs by variation of important parameters before actual store and modifications A proposal for refurbishing the operation s configurations are calculated Once the regions with possible quarters of Dulles Tower is included along with drawings for a lower flutter speeds of asymmetncal stores are defined, those new console and a plan for an improved position and equipment configurations can be selected which have to be investigated arrangement A R H LS N78-31133I Air Force Inst of Tech Wright-Patterson AFB N78-31128*|jf National Aeronautics and Space Administration Ohio School of Engineering Langley Research Center. Hampton, Va SOFTWARE DESIGN FOR A VISUALLY-COUPLED AIR- DEMONSTRATION OF AIRCRAFT WING/STORE FLUTTER BORNE SYSTEMS SIMULATOR (VCASS) M S. Thesis SUPPRESSION SYSTEMS William H Reeve and Jerry L Stmson Mar 1978 215 p Chmtsun Hwang (Northrop Corp. Hawthorne. Calif). Bertil A refs Wmther (Northrop Corp. Hawthorne, Calif). Thomas E Noll (AD-A055226 AFIT/GCS/EE/78-6) Avail NTIS (AFFDL, Wright-Patterson AFB. Ohio), and Moses G Farmer In HC A10/MF A01 CSCL 01/4 AGARD Considerations on Wing Stores Flutter Jul 1978 This thesis contains an analysis of a Visually Coupled Airborne p 21-37 refs Systems Simulator (VCASS) and the design of the software for. Avail NTIS HC A03/MF A01 this system The design is developed in three steps First, an Preliminary results are presented of the design analysis and informal requirements definition is written to establish the the test progress of active wing/store flutter suppression systems viewpoint and the purpose on which the analyst bases his design on a lightweight fighter aircraft Three configurations were selected This requirements definition explains why the simulator is to be for final testing Two of these configurations were deliberately created and what it is to do Second a top-down strategy called designed to exhibit low flutter speeds with rapid reduction in structured analysis is applied to obtain a formal requirements damping at the incipient flutter condition After initial tunnel definition The structured analysis is presented in a blueprint-type entries, which showed the need for certain improvements in the language consisting of activity and data models These models model and the control system design, substantial increases in represent graphically the functions performed by the simulator the flutter speeds were achieved using both leading and trailing and the information upon which those functions act Third a edge control surfaces separately For the most critical configura- design is obtained through a structured design methodology tion, a demonstrated improvement of 18% and a projected consisting of transform analysis and 'transaction analysis improvement of 29% in the dynamic pressure were accom- techniques The structure charts drawn during the analysis phase plished L S reveal system characteristics which illustrate design quality The activity model is used to make a successful transition from a top-down analysis to a structured design which can be evaluated N78-31130# Mitre Corp . McLean Va Metrek Div The resulting simulator design with minor revisions satisfies PARAMETERS OF FUTURE ATC SYSTEMS RELATING TO the design goals established for the project The methodologies AIRPORT CAPACITY/DELAY Final Report used are highly recommended for the analysis and design of Andrew L Hames Apr 1978 25 p refs any software system Author (GRA) (Contract DOT-FA78WA-4075) (AD-A055482 MTR-7766, FAA-EM-78-8) Avail NTIS N78-31134| Anne Research Corp Annapolis Md HC A02/MF A01 CSCL 01/5 EXPERIMENTAL TEST PLAN FOR THE EVALUATION OF Estimates of changes in longitudinal spacing on final approach AIRCRAFT SEPARATION ASSURANCE DISPLAYS USING that may be realized as the products of the engineering and AIRLINE FLIGHT SIMULATORS development programs become available are presented The Thomas Berry Jun 1978 68 p potential for reducing interarnval errors and runway occupancy (Contract DOT-FA78WA-4091) time is also discussed The parametric values presented are to (AD-A055849 Rept-1343-01-1-1753) Avail NTIS be used by the FAA/User Group Airport Case Study Teams in HC A04/MF A01 CSCL 01/3 assessing the potential impact of future airport changes on This test plan describes an experiment for evaluating the delay/capacity Parameter values related to the estimation of cockpit impact of the use of Aircraft Separation Assurance present day delay/capacity are also presented S B S information using a jet transport aircraft simulator and operational airline flight crews Three concepts for displaying ASA informa- N78-31131jjf Mitre Corp McLean. Va Metrek Div tion will be utilized during the evaluation, six flight scenarios, ANALYSIS OF RUNWAY OCCUPANCY TIMES AT MAJOR each with a set of six flight conflicts will be used Figures of AIRPORTS Final Report merit for evaluating the display concepts include response delay Steven E Koenig May 1978 56 p refs times achieved miss distances deviation from desired flight (Contract DOT-FA78WA-4075) path achieved acceleration rates and qualitative crew opinions (AD-A056052 MTR-7837 FAA-EM-78-9) Avail NTIS _ Author (GRA) HC A04/MF A01 CSCL 01/5 N78-31135# Deutsche Forschungs- und Versuchsanstalt fuer Future airport capacity is greatly dependent on the levels to Luft- und Raumfahrt Goettmgen (West Germany) Inst fuer which interarnval spacmgs can be reduced Specific causes of Aeroelastik

566 N78-31946

INVESTIGATIONS ON UNSTEADY PRESSURE DISTRIBU- N78-31336# Air Force Inst of Tech Wright-Patterson AFB TION MEASUREMENTS IN ROTATING SYSTEMS Ohio School of Engineering Karl Kienappel 5 Oct 1977 47 p refs In GERMAN. ENGLISH ANALYSIS OF MONOPOLE ANTENNA ARRAYS ON summary Report will also be announced as translation CYLINDERS BY THE GEOMETRICAL THEORY OF DIFFRAC- (ESA-TT-503) TION M.S. Thesis (DLR-FB-77-43) Avail NTIS HCA03/MFA01 DFVLR. Cologne Bruce A Thieman Dec 1977 77 p refs DM 2380 (AD-A055197 AFIT/GE/EE/77-41) Avail NTIS The theoretical basic requirements to measure unsteady HC A05/MF A01 CSCL 17/2 periodic pressure distributions in a rotating system are discussed Using the Geometrical Theory of Diffraction (GTD) the fields An experimental test setup to investigate the problems of the due to a monopole array mounted on an aircraft near the top measurement technology is described First results of this or bottom were analyzed The aircraft was modeled in its most experiment made in a 3 m windtunnel are presented It is basic form an infinitely long elliptical cylinder The aircraft concluded that the indirect measurement method used is suitable cross-section at the location of the antenna was modeled as a to establish unsteady nonharmonic pressure distributions in 2 meter by 4 meter ellipse The frequency band of operation rotating systems Author (ESA) was 250 mHz to 400 mHz with an average wavelength assumed of 1 meter The three element array was found to have a beam broadening effect when compared to the array mounted on an N78-31249# Bendix Corp Kansas City Mo infinite ground plane The array exhibited a poor potential to MATERIAL EVALUATION OF POLYURETHANE FOAM. form a single major lobe in its antenna pattern but had a high 0 06 g/cm3 DENSITY mobility of pattern nulls Author (GRA) J R Fender Mar 1978 57 p (Contract EY-76-C-04-0613) (BDX-613-1836-Rev) Avail NTIS HC A04/MF A01 Rigifoam 6003-2 a C02 blown polyester polyurethane N78-31873*| Kansas Univ . Lawrence Center for Research foam system was chosen for use as the prime material for Inc production of parts with a foam density of 0 05g cu cm Studies A RESEARCH PROGRAM TO REDUCE INTERIOR NOISE of the 6003-2 physical properties chemical analysis, dimensional IN GENERAL AVIATION AIRPLANES NOISE REDUCTION stability moisture content and the machining and gaging THROUGH A CAVITY-BACKED FLEXIBLE PLATE capabilities of this material are summarized ERA Jan Roskam and Cornells P G vanDam Aug 1978 103 p refs (Grant NsG-1301) N78-31261/f Deutsche Forschungs- und Versuchsanstalt fuer (NASA-CR-157588 KU-FRL-317-8) Avail NTIS Luft- und Raumfahrt Brunswick (West Germany) Abt HC A06/MF A01 CSCL 20A Verbundwerkstoffe A prediction method is reported for noise reduction through THE INFLUENCE OF THE ENVIRONMENT ON THE a cavity-backed panel The analysis takes into account only cavity ELASTOPLASTIC PROPERTIES OF ADHESIVES IN METAL modes in one direction The results of this analysis were to find BONDED JOINTS the effect of acoustic stiffness of a backing cavity on the panel Walter Althof Gerhard Klingei Gerhard Neumann and Johanna behavior The resulting changes in the noise reduction through Schlothauer 8 Mar 1978 82 p refs In GERMAN ENGLISH the panel are significant G G summary Report will also be announced as translation (ESA-TT-521) N78-31874*| Kansas Univ Center for Research. Inc Lawrence (DLR-FB-77-63) Avail NTIS HC A05/MF A01. DFVLR. Cologne Center for Research Inc DM 43 40 A RESEARCH PROGRAM TO REDUCE INTERIOR NOISE The shear modulus, the stress at 1% shear-strain, the IN GENERAL AVIATION AIRPLANES INVESTIGATION OF fracture strength the strain at fracture and the appertaining shear THE CHARACTERISTICS OF AN ACOUSTIC PANEL TEST stress-strain diagrams were analyzed for 10 aircraft structural FACILITY adhesives The values were calculated from the measured load Ferd Grosveld and Jan vanAken Sep 1978 151 p refs deformation behavior of the adhesives in the bond line of lap (Grant NsG-1301) joints with a thick adherend and a small overlap length as well (NASA-CR-157587. KU-FRL-317-9) Avail NTIS as from the torsion pendulum testing (DIN 53 445) of cast HC A08/MF A01 CSCL 20A adhesives The measurements were made before and after a Sound pressure levels in the test facility were studied that long exposure to heat cold moisture heat combined with are caused by varying (1) microphone positions, (2) equalizer moisture and changes between cold and combined heat and setting and (3) panel clamping forces Measurements were moisture The environmental effects on the adhesion between done by using a Beranek tube or this Beranek tube in combinations adherend and adhesives as observed in the tests are described with an extension tube and a special test section In all Author (ESA) configurations tests were executed with and without a test panel installed The influence of the speaker back panel and the back panel of the Beranek tube on the sound pressure levels inside the test tube were also investigated It is shown that the definition N78-31326j|l National Aviation Facilities Experimental Center of noise reduction is more useful in relation to this test facility Atlantic City. N J than transmission loss G G TEST AND EVALUATION OF AIR/GROUND COMMUNICA- TIONS ANTENNAS Final Report. J«n - Dec 1977 James J Coyle Jun 1978 130 p (AD-A056148. FAA-NA-77-39) Avail NTIS N78-31946# General Accounting Office Washington. D C HC A07/MF A01 CSCL 17/7" Procurement and Systems Acquisition Div Data from the evaluation and analysis of a select group of very STATUS OF THE AIR FORCE'S F-16 AIRCRAFT PROGRAM high frequency (VHP) and ultrahigh frequency (UHF) air/ground Report to the Congress (A/G) communication antennas are presented Antenna patterns 24 Apr 1978 48 p refs gam. and voltage standing wave ratio measurements were made (PB-280304/7. PSAD-78-36) Avail NTIS HC A03/MF A01 at the National Aviation Facilities Experimental Center (NAFEC) CSCL 01C antenna range on both Federal Aviation Administration (FAA) The Department of Defense approved full production for the specified and commercially available off-the-shelf antennas These F-16 on October 13 1977 Although sufficient testing was antenna data show that improved A/G communications coverage accomplished for the program to enter full production a number can be obtained with some of the commercially available of uncertainties are associated with the program The uncertainties antennas G G include {j-100 engine problems, an ambitious deployment schedule

567 N78-31952 and support requirements generated by this deployment, subsystem design problems support of European manufacturers and survivability/vulnerabihty issues GAO recommends that the Secretary of Defense require a complete program review before making any commitments for USAF F-16 purchases beyond the first 650 aircraft This review should include an updated military need assessment and comparison of F-16 performance under realistic operational conditions GRA

N78-31962# United Technologies Corp Windsor Locks Conn Hamilton Standard Div PRELIMINARY DESIGN OF AN ACCIDENT INFORMATION RETRIEVAL SYSTEM (AIRS) Final Report. Jun 1976 - Aug 1977 Henry R Ask Marston E Moffatt. Ivor Hughes, Larry Brock and John Bikowski Apr 1978 277 p refs (Contract DAAJ02-76-C-0058 DA Proj 1F2-62209-AH-76) (AD-A055590, HSER-7342. USARTL-TR-77-51) Avail NTIS HC A13/MF A01 CSCL 01/2 This report covers the phase 1 activity entitled Concept Investigation and phase 2 entitled Preliminary Design and System Analysis The report details the analyses involving requirements parameters trade-offs, and definition of a recommended AIRS The Phase 1 effort included the intense analysis of the airborne portion of the system since it is the most sensitive element in terms of size, weight, and cost This included examination of the parameter and sensor requirements, survivabihty and software Actual flight data was used to run a program on a large-scale computer to determine limits accuracy and sampling rate effects on flight data reconstruction and aircraft memory storage requirements Phase 2 included a detailed preliminary design of the AIRS A preliminary hardware concept was established and the essential features of the recommended concept are included The recommended system was analyzed to determine performance weight, size cost, installation, survivabihty. reliability data retrieval, maintenance and functional test factors Results indicate that the current state of the art w.ll allow an AIRS to be developed for installation on production UTTAS and AAH aircraft The recommended system employs an all solid-state design including the mass data storage device Factors of two or more improvements in size, weight reliability maintainability are indicated over current data recording systems Author (GRA)

568 SUBJECT INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Suppl 103) DECEMBER 1978

Typical Subject Index Listing

AEBIAL EXPLOSIOHS •APOBIZEBS Hazard assessment of aircraft gun compartments "Liquid hydrogen flash vaporizer — — for aircraft- [AD-A055026] N78-3106H fnel systeis AEBIAL PBOTOGBAPHT [NASA-CASF.-LAB-121S9-1] N78-11260 Bigh-accuracy three-dimensional image reconstruction for an airborne line-scanning system A78-19988 REPORT AEBOACOOSTICS NUMBER Jn acoustic range for the measurement of the noise signature of aircraft during flyby operations A78-172112 AEHODYHABIC BBAKES The title ts used to provide a description of the subject matter When the title is Influence of slots on effectiveness of wing insufficiently descriptive of the document content a title extension is added mechanization and control surfaces with separated from the title by three hyphens The NASA or AIAA accession number separated flow A78-D8229 is included in each entry to assist the user in locating the abstract in the abstract AEBODYRABIC CHABACTEBISTICS section of this supplement If applicable a report number is also included as an Progress in propeller aerodynamics aid in identifying the document A78-U7173 Quiet, Short-Hani Research Aircraft - current status and future plans [AIAA PAPEB 78-1168] A78-47916 Whitcomb winglet applications to general aviation A-7 AIBCBAFT aircraft TFH1-A-2/A7E inflight engine condition monitoring [AIAA PAPEB 78-1H78] A78-U7923 system /IECHS/ Modeling ground plane influence on wing [AIAA PAPEB 78-1172] A78-Q7918 aerodynamic characteristics using a finite plane Application of the General Purpose Multiplex screen System to the A-7E avionics A78-K8216 478-1(9867 Uniformly exact conformal transformation of A-10 HBCBAFT exterior of circle onto exterior of wing profile Evolution of a cost-effective, task-oriented, A78-U822U lateral-directional SAS for the A-10 aircraft Influence of slots on effectiveness of wing Stability Augmentation System mechanization and control surfaces with [AIAA PAPEB 78-1K60] A78-H7910 separated flow AC GEHEBATOBS A78-U8229 Modeling refinements for the rectified Asymptotic theory of a wing moving near a solid wall superconducting alternator airborne power A78-t(82i(8 supply Application of cryogenics in experimental 178-U9961 aerodynamics JCCELEBATIOH (PBTSICS) 178-1(8982 A compensation technique for acceleration-induced Lateral-aerodynamic characteristics of frequency changes in crystal oscillators highly-dihedraled wings A78-119859 A78-«933« ACCE1EEOBETEBS Aerodynamic characteristics induced on a Statistical review of counting accelerometer data supercritical wing due to vectoring twin nozzles for Navy and Marine fleet aircraft from 1 at Hach nombers from 0.40 to 0.95 January 1962 to 31 December 1977 [NASA-TH-78746] N78-30039 [AD-A055672] N78-31098 Botary balance data for a typical single-engine ACODSTIC FSTIGOB low-wing general aviation design for an Fatigue crack growth in pressurized fuselage panel angle-of-attack range of 30 deg to 90 deg J78-K8231 [NASA-CB-2972] N78-300U9 ACOUSTIC PBOPAGATIOS Theoretical estimation of the transonic Theoretical and experimental studies of acoustic aerodynamic characteristics of a propagation in inhomogeneous moving media supercritical-wing transport model with [ESA-TT-I(77] N78-30909 trailing-edge controls ACTOATOBS [NASA-TP-1253] N78-30056 Boiling tail design and behavior as affected by Analysis of stability contributions of high actuator hinge moment limits for B-1 dihedral V-tails maneuverability [HASA-TH-78729] H78-310I(K [AIAA PAPEB 78-1500] A78-U79DO Aerodynamic characteristics of a hypersonic ADAPTIVE COSTEOL research airplane concept having a 70 deg swept Stability augmentation by eigenvalues control and double-delta wing at Mach number 0.2 model matching [HASA-TP-1252] N78-310i(5 A78-Q6965 AEBODTIABIC COEFFICIENTS A learning flight control system for the F8-DFBS Section drag coefficients from pressure probe aircraft Digital Fly-By-Sire traverses of a wing wake at low speeds [AIAA 78-1288] A78-50195 [AIAA PAPEB 78-11(79] I78-<(792K ADAPTIVE FILTEBS Method of calculating aerodynamic coefficients of Constant false alarm rate detector for a pulse some three-dimensional bodies with arbitrary radar in a maritime environment cross section A78-U9975 A78-U82K5

A-1 AEBODYNAHTC COHFIGOBATIONS SOBJECT IHDEI

Shockless airfoils with thicknesses of 20.6 and F-15 inlet engine test technigues and distortion 20.7 percent chord analytically designed for a methodologies studies. Volume 9: Stability Hach number of 0.68 and a lift coefficient of 0.10 audits [NASA-TM-X-73917] H78-300U6 [HASA-CB-111871] K78-30131 Maximum likelihood identification of the AEBODTHAHIC STALLING longitudinal aerodynamic coefficients of the A method for localizing wing flow separation at EA-6B airplane in the catapult launch stall to alleviate spin entry tendencies configuration [AIAA PAPEB 78-1176] A78-19787 fAD-!l051213] 1178-31016 Simulation study of the oscillatory longitudinal AEBODYNAHIC COHFIGOBATIOHS motion of an airplane at the stall Correlation of model and airplane spin [NASA-TP-1212] H78-30111 characteristics for a low-wing general aviation AEBOELASTICITY research airplane The influence of high twist on the dynamics of [AIAP P4PEB 78-1177] A78-17922 rotating blades Studies of aerodynamic technology for VSTOL A78-17599 fighter/attack aircraft Assessment of dynamic coordinate alignment for [AIAJ P^PEB 78-1511] A78-17916 elastic aircraft flight control Kalman Definition of airplane fuselage longitudinal lines filter estimates • by the special contour method A78-19987 A78-18222 Close encounters of the aeroservoelastic kind Propulsion test facilities - Capabilities and use aerodynamics, structural dynamics, and automatic fAIAA PAPEE 78-933] A78-18153 flight control systems for aircraft design Status of a nozzle-airframe study of a highly applications maneuverable fighter [AIAA 78-1289] J78-50196 [AIAA P\PEB 78-990] A78-18170 AEBOSPACE EHGI1EEBIH6 King planforms for large military transports Teaching design at all levels in aerospace TAIAA PAPEE 78-1170] A78-19786 engineering curricula Ground effects testing of two, three, and four jet [AIAA PAPEB 78-1155] A78-17906 configurations The nse of the AIAA-Bendir Design Competition in [AIAA PIPES 78-1510] A78-19789 aerospace design courses Close encounters of the aeroservoelastic kind [AIAA PAPEB 78-1188] A78-17931 aerodynamics, structural dynamics, and automatic The value of aerospace design synthesis courses as flight control systems for aircraft design viewed by aerospace professionals applications [AIAA PAPEB 78-1193] A78-17931 [AIAi 78-1289] 478-50196 AEBOSPACE SYSTEHS Aerodynamics of the new generation of combat The design process computer aided design for aircraft with delta wings complex aerospace systems N78-30106 [AIAA PAPEB 78-1183] A78-17928 AEBODYNAHIC DBAG NAECON '78; Proceedings of the National Aerospace On the theory of drag calculation and profile and Electronics Conference, Dayton, Ohio, Hay optimization in Shockless near free molecular flow 16-18, 1978. Volumes 1,263 A78-47887 A78-19851 Section drag coefficients from pressure probe ABBOTHEBBOELASTICITY traverses of a wing wake at low speeds Optimal control synthesis in distributed systems [AIAA PAPEB 78-1(179] \78-17921 with incomplete information noting aircraft Design of a large span-distributed load applications flying-wing cargo airplane with laminar flow A78-18215 control &FTEBBODIES fNASA-CB-115376] N78-300U5 Hind Tunnel/Flight Test Correlation Program on the Investigation of a wing-rotor interaction system B-1 nacelle afterbody/nozzle at transonic for helicopters conditions [AD-A051093] 178-30092 [AIAA PAPEB 78-989] A78-18169 AEEODIBABIC FOBCES AGBICOLTDBB Important simulation parameters for the Status of aerial applications research in the experimental testing of propulsion indnced lift Langley vortex research facility and the Langley effects full-scale wind tunnel CAIAA PAPEB 78-1078] A78-18191 [NASA-TH-78760] H78-300D1 nse of ground vibration test equipment to AH-61 HE1ICOPTEB determine unsteady aerodynamic forces Flight controls of Army/Hughes YAH-61 advanced A78-19708 attack helicopter An automated procedure for computing the [AIAA 78-1237] A78-50160 three-dimensional transonic flow over wing-body AILEBOHS combinations, including viscous effects. Volume Flutter suppressor for transonic flight 1: Description of analysis methods and [OHEBA, TP HO. 1978-102] A78-17316 applications AIB DEFENSE [AD-A055899] N78-31052 Rodular target acquisition and designation systems iEHODTNABIC INTEBFEBEHCE A78-19951 Induction of subsonic wind tunnels with slight AIB DOCTS perforation Center-loaded duct integral rocket-to-ramjet A78-18250 transition testing Hind-tunnel testing of VTOI and STOL aircraft [AIAA PAPEB 78-937] A78-18156 [NASf-TH-78750] H78-30010 AIB LAUNCHING AEBODYHABTC LOADS In-flight alignment/calibration techniques for On the linear superposition of aerodynamic forces unaided tactical guidance of air-launched on wings in periodic gusts missiles A78-17869 A78-19929 Drones for aerodynamic and structural testing AIB NAVIGATION /DAST/ - A status report BNAV - Corporate operators set the pace [AIAA P»PEB 78-1185] A78-17929 A78-17121 i calculator program for analyzing airloads on a Communication and navigation antennas for aircraft wing of arbitrary planform and camber in Bussian book subsonic flow A78-18523 [AD-A05U180] N78-30058 The Onega radionavigation system comes to the AEBODYHAHIC STABILITY Pacific Ocean area Close encounters of the aeroservoelastic kind A78-19660 aerodynamics, structural dynamics, and automatic In-flight alignment/calibration techniques for flight control systems for aircraft design unaided tactical guidance of air-launched applications missiles TAIAA 78-1289] A78-50196 A78-19929

A-2 SUBJECT IHDEJ, ilBBOBBB/SPACEBOBBE COBPUTEBS

Station deselection procedures to support Airliner numbers game - Does it add up automatic Omega receiver operation political and technological aspects of A78-49965 international aircraft industries Perfornance of a differential Onega-ring laser A78-49524 strapdovn aircraft navigator Airfield pavement load evaluation - An A78-49966 international overview Heal-tine simulators for augmented inertial £78-19676 navigation systems Proposed load evaluation system for U.S. Air Force A78-49967 of airfield pavement Reliability of inertial navigation systems for A78-49677 military and commercial aircraft Transport Canada airfield pavement load evaluation 178-a9968 A78-I19678 Accuracy requirement and cost effectiveness of Model of aircraft passenger acceptance GPS-aided INS for tactical fighters A78-49681 A78-49989 •Supermarket' airplanes aircraft replacement A parametric analysis of TERCOM false fix cycle in major airlines probability TEErain contour Hatching [ilAA PAPER 78-1533] A78-19769 A78-49997 Operations and economics of D.S. air transportation Optimal terrain-aided navigation systems [AIA& PAPER 78-1545] 478-19770 [AIAA 78-1243] A78-50163 Demand modelling of passenger air travel: An Guidance and navigation for automatic landing, analysis and extension, volume 2 rollout, and turnoff using HIS and magnetic [ HASA-CR-157402] N78-30069 cable sensors AIEBOBHE EQUIPMENT FAIAA 78-1296] A78-50203 Flight application of optical fiber transmission TRSB microwave landing system demonstration on a Falcon 10 aircraft program at Brussels, Belgium [ONERA, TP NO. 1978-105] A78-47349 [AD-A054298] N78-30075 Application of rare earth/transition metal AIB POILUTIOS permanent magnets to 100 Hz aircraft systems - Gas turbine engine emissions - Problems, progress An AF overview and future A78-19935 A78-19336 Prediction of angular disturbances from airframe AIR TO AIR MISSILES members to airborne electro-optical packages Bank-to-tarn /BIT/ autopilot technology for A78-19952 missiles Modeling refinements for the rectified A78-49927 superconducting alternator airborne power AIE TO SURFACE MISSILES supply Strapdown seeker guidance for tactical weapons A78-49961 A78-49928 Impact of aircraft electrical power quality on ilE TEAPPIC utilization egnipment Trailing vortices. II 178-49962 A78-47172 Dual band airborne SATCOM terminal AIR TR1FPIC CONTROL A78-49972 Integrated avionics for future general aviation Infrared receiver performance airborne warning aircraft . system by detection of target spectral signature tAIAA PAPER 78-1182] A78-47927 A78-49985 Air traffic control in the terminal area - Use of High-accuracy three-dimensional image a simulation technigue for the definition of an operative model system 178-19733 ?78-49988 Engineering and development program plan: Bake Combinatorially derived limits on the surface vortex return for an air/surface monopulse ranging radar [AD-A051I43] N78-30071 A78-50001 Characteristics of constrained optimum A frequency-selective TIG limiter for airborne trajectories with specified range FH/CB X-band radar (NASA-TH-78519] 178-30072 A78-50002 TRACALS evaluation report. TACAN, VOR, and ILS AIRBORSE/SPACEBOENE COMPUTERS station evaluation report, Andersen AFB, Guam RNAV - Corporate operators set the pace [AD-A054244] B78-30078 A78-47424 Avionics cost development for alternatives of AIDS in military aircraft Airborne Integrated selected air traffic control systems Data Systems Computer [AD-A054823] N78-30080 A78-47866 IFR aircraft handled forecast by air route traffic Ose of onboard computerized flight test analysis control center, fiscal years 1978-1989 systems [AD-A049305] N78-31075 [AIAA PAPER 78-1162] A78-47912 Future needs and opportunities in the air traffic Software engineering a must for success in control system computerized flight test [GPO-98-931] N78-31076 [AIAA PAPER 78-1463] A78-47913 Parameters of future ATC systems relating to L-1011 flight data recording systems - Background, airport capacity/delay features, implications and benefits [AD-A055482] _ N78-31130 [AIAfi PAPER 78-1471] A78-47917 Dulles control tower 'console design study NAECON "78; Proceedings of the Rational Aerospace [AD-A056200] N78-31132 and Electronics Conference, Dayton, Ohio, Hay Experimental test plan for the evaluation of 16-18, 1978. Volumes 1, 2 S 3 aircraft separation assurance displays using A78-49851 airline flight simulators Modular Hissionization Systems /HHS/, an adaptive [AD-A055849] N78-31131 system interface concept Test and evaluation of air/ground communications £78-49852 antennas Pattern recognition as an aid to radar navigation [AD-A056148] N78-31325 A78-49855 AIR TRANSPORTATION In-line monitoring of digital flight control Stability of a helicopter carrying an underslung computers load A78-49860 A78-19398 A qualitative analysis of redundant asynchronous An integrated analysis of the fundamental problems operation of air transport A78-49863 A78-19117 HIL-STD-1553B proposed data bus development in Operational regularity in air transport avionic architecture A78-49149 A78-49866

A-3 AIRCB1FT ACCIDEHT INVESTIGATION SUBJECT INDEX

A hierarchical network for avionic systems AIRCRAFT CONSTRUCTION BATERIALS A78-49868 Some sound transmission loss characteristics of Non-volatile memory system for severe environment typical general aviation structural materials flight recorders [AIAA PAPER 78-1180] A78-47925 A78-49872 Assessment of relative flammability and Software structured weapon delivery thermochemical properties of some thermoplastic A78-49875 materials Peace Rhine - J digital Weapon Control System for A78-49693 the F-4 aircraft A preliminary comparison of thermal decomposition A78-49876 prodncts of aircraft interior materials using Approach for identifying avionics flight software the National Bureau of Standards smoke chamber operational support regnirements - PAVE TACK an and the combustion tube furnace example [AD-A054811] N78-30088 A78-49900 New structures made of composite materials for Comparison study of HLS airborne signal processing high oerformance combat aircraft techniques N78-30114 A78-49904 Engineering data on new aerospace materials Digital simulation and flight verification of the structural materials F-5E/F Flight Director Computer [AD-A05IK161] N78-30213 A78-49905 Safety against fatigue in flight: A perspective An interface management approach to software of Australian experience and research development N78-30272 A78-49933 Fibre composite reinforcement of cracked aircraft AIRCRAFT ACCIDEHT INVESTIGATION structures Preliminary design of an accident Information N78-30288 Retrieval System (AIRS) The influences of residual stresses on oscillating [AD-; 055590] H78-31952 tensile strength and the measurement of residnal AIRCRAFT ANTENNAS stress, with emphasis on aircraft construction Communication and navigation antennas for aircraft fatigue life of aircraft construction Russian book materials J78-48523 [BHVG-FBVT-77-23] N78-30603 Volumetric pattern analysis of airborne antennas Baterial evaluation of polyurethane foam, 0.05 g/ J78-49427 cm 3 density Conformal microstrip phased array for aircraft [BDX-613-1836-REV] N78-31249 tests with ATS-6 AIRCRAFT CONTROL A78-49428 Digital control law synthesis in the w prime domain Scan-limited near field testing for directive A78-46962 airborne antennas Stability augmentation by eigenvalues control and A78-119897 model matching Test and evaluation of air/ground communications A78-46965 antennas Drones for aerodynamic and structural testing [AD-A056148] N78-31325 /DAST/ - A status report Analysis of monopole antenna arrays on cylinders [AIAA PAPER 78-1485] A78-47929 I by the geometrical theory of diffraction Improved aircraft dynamic response and fatigue [AD-A055197] N78-31335 life during ground operations using an active AIRCRAFT APPROACH SPACING control landing gear system Parameters of future ATC systems relating to [AIAA PAPER 78-1499] A78-U7939 airport capacity/delay Rolling tail design and behavior as affected by rAD-A055482] N78-31130 actuator hinge moment limits for B-1 AIRCRAFT CARRIERS maneuverability The influence of throttle augmented stability [AIAA PAPER 78-1500] A78-47940 (APCS) and short period control characteristics Optimal control synthesis in distributed systems on the landing approach with incomplete information noting aircraft [SD-A055892] N''8-31123 applications AIRCRAFT COBBDHICATION A78-48215 Communication and navigation antennas for aircraft A method for determining the stability Russian book characteristics of aircraft in a helicoid flight A78-48523 path Conformal microstrip phased array for aircraft A78-49741 tests with ATS-6 Piloted flight simulation for active control A78-49428 design development Fading at 9.6 GHz on an experimentally simulated [AIAA PAPER 78-1553] A78-49771 aircraft-to-ground path The influence of propulsion and control system A78-49439 concepts on design of a Navy Type A V/STOL The AN/iPY-100/V/ transponder for military airplane aircraft [AIAA PAPER 78-1505] J78-19788 A78-49971 Aviation control system devices Russian book Dual band airborne SATCOH terminal A78-49850 A78-49972 A qualitative analysis of redundant asynchronous AIRCRAFT COHPARTBEHTS operation Experimental determination of parameters of A78-49863 mathematical model of airplane cabin as A hierarchical network for avionic systems regulated object with respect to air temperature A78-49868 in the cabin Assessment of dynamic coordinate alignment for A78-48234 elastic aircraft flight control Kalman A preliminary comparison of thermal decomposition filter estimates products of aircraft interior materials using A78-49987 the National Bureau of Standards smoke chamber An investigation of potential control-display and the combustion tube furnace configurations for V/STOL aircraft fAD-A054811] N78-30088 [ilAA 78-1238] A78-50161 AIRCRAFT CONFIGURATIONS RPV flying qualities design criteria Canard configured aircraft with 2-D nozzle [AIAA 78-1271] A78-50181 [AIAA PapER 78-1450] J78-47904 Guidance and navigation for automatic landing, Design evolution of a supersonic cruise rollout, and turnoff using BLS and magnetic strike-fighter cable sensors CATAA PAPER 78-1452] A78-49783 [AIAA 78-1296] A78-50203 The effect of prefilter design on sample rate selection in digital flight control systems [AIAA 78-1308] A78-50209 SUBJECT IHDEI AIBCBAFT BBGIHES

Advanced control concepts for fotore fighter Design evolution of a supersonic cruise aircraft strike-fighter N78-30104 [AIAA PAPEB 78-1452] A78-49783 Impact of active control on structures design Prospects for commercial commonality in military H78-30113 transports ilECHSFT DESIGH [AIAA PAPEB 78-1467] A78-49784 Progress in propeller aerodynamics A method for localizing wing flow separation at A78-47173 stall to alleviate spin entry tendencies The promise of tilt rotor [AIAA PAPEB 78-1476] A78-49787 J78-47266 The influence of propulsion and control system Design philosophy for airframes concepts on design of a Navy Type f V/STOL i78-«7H53 airplane Prom Challenger to winner Canadair executive [AIAA PAPEB 78-1505] 478-49788 jet design and development nodular Nissionization Systems /BBS/, an adaptive A78-117570 system interface concept On the linear superposition of aerodynamic forces A78-49852 on wings in periodic gusts The terrain following task for the advanced A78-U7869 tactical fighter using discrete optimal control Gates Learjet nodel 28/29, the first 'longhorn' A78-U9862 Learjet Interface design considerations for F-*6 sensors [AIAA PAPEB 78-1445] A78-U7901 and weapons The effect on block fuel consumption of a strutted A78-49874 versus cantilever wing for a short-haul BPV flying qualities design criteria transport including strut aeroelastic [AIAA 78-1271] A78-50181 considerations Close encounters of the aeroservoelastic kind [AIAA PfPEB 78-1454] A78-47905 aerodynamics, structural dynamics, and automatic The HiMAT HPBV system flight control systems for aircraft design CAIAA PAPER 78-1457] J78-47908 applications Conceptual design study of power augmented ram [AIAA 78-1289] A78-50196 wing in ground effect aircraft Fighter aircraft design conferences [AIAi PAPEB 78-1466] A78-47915 [AGABD-CP-241] 1178-30099 Quiet, Short-Haul Research Aircraft - Current Fighter superiority by design status and future plans N78-30105 fAIAA PAPEB 78-1468] A78-47916 Analysis of advanced variable camber concepts vhitcomb winglet applications to general aviation 1178-30108 aircraft Intake design for fighter aircraft [AIAA PAPEB 78-1478] A78-47923 H78-30110 The design process computer aided design for Impact of active control on structures design complex aerospace systems 1178-30113 fAIAA P4PEB 78-1483] A78-47928 Hetal technology for future aircraft design Application of advanced high speed turboprop N78-30115 technology to future civil short-haul transport The design of a high g cockpit aircraft design 1178-30118 [AIAA PAPEB 78-1487] A78-47930 Analysis of a suspension system for a wheel The use of the AIAA-Bendix Design Competition in rolling on a flat track aerospace design courses [ NASA-CB-157563] S78-30583 [AIAA PAPEB 78-1488] A78-47931 An assessment of the effect of supersonic aircraft A computerized undergraduate aircraft design course operations on the stratospheric ozone content [AIAA PAPEB 78-1492] 578-47933 [N4SA-BP-1026] N78-30774 The value of aerospace design synthesis courses as Graphics for the hybrid stores separation viewed by aerospace professionals simulation of the B77 system [AIAA PAPEB 78-1493] 478-47934 [SAND-78-8212] 878-31099 Effect of performance objectives on the design and AIBCBA7T ENGINES cost of future OSAP pilot training aircraft Operation of oil seales of aircraft piston engines [AIAA PAPEB 78-1498] A7B-47938 under conditions of cavitation. I Studies of aerodynamic technology for VSTOL A78-47175 fighter/attack aircraft The second generation of high-bypass turbofans - A [AIAA PAPEB 78-1511] A78-47946 market clouded by uncertainty Aerodynamic hull design for HASPA LTA optimization A78-47423 High Altitude Superpressure Powered Aerostat TF41-A-2/A7E inflight engine condition monitoring Lighter Than Air system /IECHS/ A78-48100 [AIAA PAPEB 78-1472] A78-47918 Definition of airplane fuselage longitudinal lines Analysis of GTE tolerance monitoring parameter by the special contour method formation gas turbine engine A78-48222 A78-48212 Status of a nozzle-airframe study of a highly NASA engine system technology programs - An overview maneuverable fighter [AIAA PAPEB 78-928] A78-48452 [AIAA PAPEB 78-990] A78-48470 Propulsion for future supersonic transports - 1978 Non-axisymmetnc nozzle design and evaluation for status P-111 flight demonstration [AIAA PAPEB 78-1051] A78-48486 [AIAA PAPER 78-1025] A78-48483 Design for durability - The F101-GE-100 engine Propulsion system airframe integration studies - [AIAA PAPER 78-1084] * 78-48497 Advanced supersonic transport Boundary layers in axisymmetric inlets at angle of [AIAA PAPER 78-1053] A7B-48488 attack. I - neasnrements Highly snrvivable integrated avionics [AIAA PAPEB 78-1109] A78-48499 A78-49163 Aspects of the thermal fatigue strength of Rirage 2000 - Dassault's better delta gas-turbine engine components A78-49169 J78-49176 The D.S. lavy bets on V/STOL technological Gas turbine engine emissions - Problems, progress integration for next generation aircraft design and future A78-49550 A78-49336 Hodel of aircraft passenger acceptance Choice of cycle for a regenerative bypass turbojet A78-49684 for long-range aircraft Design of a horizontal tail unit and related A78-49723 adjustments A laser-powered flight transportation system A78-49736 [AIAi PAPEB 78-1484] A78-49781 Piloted flight simulation for active control Operating characteristics of bypass turbojet engines design development Russian book [AIAA PAPEB 78-1553] A78-49771 A78-50125

A-5 AIBCBiFT EQOIPHEHT SUBJECT IHDEI

Variable-cycle engine fighter aircraft: Advance AIECBAFT HA2ABDS in performance and development problems Investigation of electrostatic discharge in H78-30109 aircraft fuel tanks during refueling Turbine engine rotordynamic evaluation, volume 1 [AIAA PAPEB 78-1501] A78-47941 [AD-A055262] N78-31111 Simultaneous measurements of ozone outside and AIBCBiFT EQDIPBEHT inside cabins of two B-747 airliners and a Gates *IDS in military aircraft Airborne Integrated Learjet business jet Data Systems Computer [NASA-TH-78983] N78-31061 A78-17866 AIBCBIFT IHDDSTBI Evaluating avionics weight efficiency Airliner numbers game - Does it add up A78-48228 political and technological aspects of Dynamic analysis of electrical systems international aircraft industries A78-49934 A78-49524 A standard programmable I/O for the advanced •Supermarket' airplanes aircraft replacement aircraft electrical system power control set cycle in major airlines 178-19936 [AIAA PAPEB 78-1533] A78-49769 i Aircraft electrical system testing and data ilBCBAFT IHSTBOHEHTS reduction using digital techniques COBED - The cockpit display of the future A78-49937 combined Nap and Electronic Display The AN/APX-100/V/ transponder for military A78-47268 aircraft Flight deck display trends A78-19971 A78-U7899 Air-to-air designate/track with time sharing Solid-state displays for fuel management systems A78-1I9977 for aircraft Damping, static, dynamic, and impact A78-47900 characteristics of laminated beams typical of The airborne detection of low-level wind shear windshield construction [AIAA PAPEB 78-1495] A78-Q7936 [AD-A0514463] H78-30093 Aviation control system devices Eossian book Computer program for vibration prediction of f.78-49850 fighter aircraft equipments In-flight alignment/calibration techniques for [AD-A054598] H78-3009U unaided tactical guidance of air-launched HHSD demonstration model development missiles [AD-A054437] N78-30120 A78-1I9929 Fundamentals of noncuring sealants for aircraft Multi-Function Inertial Beference Assembly /BIBA/ fuel tanks update digital aircraft systems [AD-A051627] H78-30247 J78-49911 fiodified helicopter icing spray system evaluation Digital area correlation tracker [AD-A055039] N78-31091 478-119951 Statistical review of counting accelerometer data Autothreshold autoscreener/FLIB system for Navy and Marine fleet aircraft from 1 airborne target screener/Forward-Iooking January 1962 to 31 December 1977 Infrared imaging system [AD-A055672] 1178-31098 A78-49984 AIBCB1FT FtJBl SISIEHS Display systems and cockpit design Solid-state displays for fuel management systems N78-30116 for aircraft AIBCBAFT LAHDIRS A78-D7900 Probabilistic model of an instrument landing system Investigation of electrostatic discharge in A78-47407 aircraft fuel tanks during refueling Improving the accuracy of HUD approaches in [AIAA PAPEB 78-1501] \78-47941 windshear with a new control law Study of fuel systems for lH2-fueled subsonic [AIAA PAPEB 78-1«9

A-6 SOBJECT IHDEI AIBCB4FT STBOCTOBES

The HlHAT BPHV system Distribution of reliability characteristics among [»IAA PAPEB 78-11457] A78-<17908 airplane systea units to ensure given flight Boiling tail design and behavior as affected by safety level actuator hinge moment limits for B-1 A78-18221 maneuverability In-line monitoring of digital flight control [IlIAA PAPER 78-1500] A78-17910 computers Status of a nozzle-airfra«e stndy of a highly A78-19860 maneuverable fighter Laboratory testing of lightning and EBP [&IAA PiPEB 78-990] A78-I48170 susceptibility of avionic systems Subsystem verification of an 4F1C organically A78-19861 developed F-15 simulation Air Force Aircraft structural reliability and risk theory: logistics Command A review A78-19901 B78-30281 Flight investigation and theory of direct AIBCBAFT SAFE!! side-force control Safety against fatigue in flight: A perspective [AIAA 78-1287] A78-50191 of Australian experience and research AIBCBAFT BODSLS N78-30272 Experimental determination of paraaeters of Hazard assessment of aircraft gun compartments mathematical model of airplane cabin as [AD-A055026] H78-31061 regnlated object with respect to air temperature AIBCBAFT SPECIFICATIOBS in the cabin feronautical procurement - The primary A78-18231 specification system Application of cryogenics in experimental [MAA PAPER 78-11189] A78-17932 aerodynamics ilfiCBAFT STIBIlIir A78-148982 Stability augmentation by eigenvalues control and AIECBAFT BOISE model matching Long-distance focusing of Concorde sonic boom A78-16965 A78-(I8052 Gates Learjet Hodel 28/29, the first 'Longhorn1 Noise in airports, its measurement, and its effect Learjet on the communities in the vicinity [AIAA PAPEB 78-1105] A78-17901 A78-18371 Evolution of a cost-effective, task-oriented, Experimental determination of the rattle of simple lateral-directional SJS for the A-10 aircraft models Stability Augmentation System CBASA-TM-78756] N78-30291 [AIAA PAPER 78-1160] A78-17910 A farther survey of some effects of aircraft noise Nacelle effects on stability of VSTOL in residential communities near London configurations including conventional, canard, (Heathrow) airport and tandem wing arrangements [TT-7705] N78-30910 [AIAA PAPEB 78-1501] A78-17912 A comparison of annoyance caused by aircraft noise Dynamics of the longitudinal motion of an airplane near London, Manchester and Liverpool airports with a variable-geometry wing CTT-7706] N78-30911 A78-19285 ilBCBAPT PABTS Stability of a helicopter carrying an underslung Extending the service life of aircraft components load made of high-strength steels Bussian book A78-M9398 A78-U8518 Design of a horizontal tail unit and related AIRCRAFT PEBFOBHAHCE adjustments Gates Learjet Model 28/29, the first 'Longhorn* J78-19736 Learjet A method for determining the stability [AIAA PAPER 78-1445] A78-<|7901 characteristics of aircraft in a helicoid flight B-1 flight test progress report path [AIAA PAPER 78-1118] A78-17903 A78-19711 Use of onboard computerized flight test analysis Airplane stability calculations with a card systems % programmable pocket calculator [AIAA PAPER 78-1162] A78-17912 [HASA-TH-78678] B78-30138 The airborne detection of low-level wind shear AIBCBAFI STBOCTOBES [AIAi P\PER 78-1195] A78-17936 Large electroformed nickel moulds for aircraft parts Effects of wind on aircraft cruise performance A78-17267 [ilAA PAPER 78-11196] A78-17937 Large deflection static analysis of typical Status of a nozzle-airframe study of a highly tail-wheel structure of light aircraft by finite maneuverable fighter element method [AIAA PAPER 78-990] A78-18170 A78-18861 Installed performance of vectoring/reversing Minimum weight design of stiffened panels with non-axisymmetric nozzles fracture constraints [AIAA PAPER 78-1022] A78-18U82 A78-19837 Takeoff performance of STOL aircraft Aircraft structural fatigue A78-19711 [ABL/STBOC-BEPT-363] B78-30271 Electromagnetic coupling analysis of a Learjet lechanisms of fatigue and fracture aircraft in a lightning environment N78-30273 A78-19920 Fracture mechanics fundamentals with reference to Performance of a ring laser strapdown attitude and aircraft structural applications heading reference for aircraft N78-30270 [AIAA 78-1210] A78-50162 Gust measurements and the N sub o problem Status of aerial applications research in the N78-30276 Langley vortex research facility and the Langley Development of a load sequence for a structural full-scale wind tunnel fatigue test [NASA-TM-787601 H78-300U1 N78-30277 Fighter superiority by design Fatigue S/B data in relation to variability in 178-30105 predicted life Effects of dynamic aeroelasticity on handling H78-30278 qualities and pilot rating Structural fatigue testing B78-3108II N78-30279 AIBCBiFT PBODOCTIOH Current developments in the life of aircraft Pavement strength rating methods as viewed by structure airframe manufacturers N78-30280 A78-19682 Aircraft structural life monitoring and the AIBCB1FT BELIiBIlITt problem of corrosion Integrated avionics for future general aviation B78-30281 aircraft HOI and the detection of fatigue [AIAA PAPEB 78-1182] A78-I17927 B78-30282

A-7 AIRCRAFT SORVIVABILITT SUBJECT IHDEX

The development of the theory of structnral fatigue REXOR 2 rotorcraft simulation model. Volume 1: N78-30283 Engineering documentation Load interaction effects in fatigue crack [NfSA-CR-115331] N78-30042 propagation REXOR 2 rotorcraft simulation model. Volume 2: H78-30285 Computer implementation * model of crack-tip behaviour for fatigue life [NASA-CR-115332] N78-30013 determination Shockless airfoils with thicknesses of 20.6 and 1178-30286 20.7 percent chord analytically designed for a Fibre composite reinforcement of cracked aircraft Hach number of 0.68 and a lift coefficient of 0.40 structures [NASA-TB-X-73917] N78-30046 N78-30288 Two-dimensional subsonic wind tunnel evaluation of The influences of residual stresses on oscillating two related cambered 15-percent thick tensile strength and the measurement of residual circulation control airfoils stress, with emphasis on aircraft construction [AD-A055140] N78-31017 fatigue life of aircraft construction AIHFRABE HA1ERIALS materials Design philosophy for airframes [BHVG-FBWT-77-231 U78-30603 A78-17153 Recent developments in analysis of crack 4IHFRABES propagation and fracture of practical materials Status of a nozzle-airframe study of a highly stress analysis in aircraft structures maneuverable fighter rHSSA-TM-78766] S78-30606 [AIAA PAPER 78-990] A78-48470 A study of analog programming for prediction of Propulsion system airframe integration studies - crack growth in aircraft structures subjected to Advanced supersonic transport random loads [AIAA PAPER 78-1053] A78-48488 [AD-A055789] N78-31097 Pavement strength rating methods as viewed by Estimated costs of extended low-rate airframe airframe manufacturers production A78-49682 [AD-A054834] N78-31100 Prediction of angular disturbances from airframe The influence of the environment on the members to airborne electro-optical packages elastoplastic properties of adhesives in metal 578-19952 bonded joints in aircraft structures Engineering data on new aerospace materials fDLH-FB-77-631 H78-31251 structural materials AIRCRAFT SOHYIVABILIT1 [AD-A054461] N78-30213 Highly survivable integrated avionics Estimated costs of extended low-rate airframe A78-49163 production Technology analysis - Candidate advanced tactical [AD-A051831] N78-31100 fighters Engine/airframe/drive train dynamic interface [AIAA PAPEP 78-11(51] A78-49782 documentation Improved combat survivability for fly-by-wire [AD-A055766] N78-31111 sensor systems AIBLIHE OPESATIOHS [AIAA 78-1277] A78-50186 Distribution of reliability characteristics among Computerized aircraft attrition program airplane system units to ensure given flight [ AD-A055784] N78-31094 safety level AIRCRAFT HAKES A78-H8221 Trailing vortices. II An integrated analysis of the fundamental problems A78-47172 of air transport Status of aerial applications research in the A78-U94I17 Langley vortex research facility and the Langley Operational regularity in air transport full-scale wind tunnel A78-19119 [NASA-TH-78760] N78-300t1 Airliner numbers game - Does it add up Engineering and development program plan: Rake political and technological aspects of vortex international aircraft industries fAD-A051143] N78-30071 A78-19524 AIRFIELD SURFACE BOVEHEHTS 'Supermarket* airplanes aircraft replacement Airfield pavement load evaluation - An cycle in major airlines international overview [AIAA PAPER 78-1533] A78-19769 478-19676 Operations and economics of O.S. air transportation Proposed load evaluation system for 0.S. fir Force [AIAA PAPER 78-1545] A78-19770 of airfield pavement IFR aircraft handled forecast by air route traffic A78-49677 control center, fiscal years 1978-1989 Transport Canada airfield pavement load evaluation [AD-A049305] N78-31075 478-19678 Analysis of runway occupancy times at major airports French procedures for airfield pavement load [AD-A056052] N78-31131 evaluation AIRPORT PLASHING A78-H9679 Noise in airports, its measurement, and its effect Airfield pavement evaluation - The airline view on the communities in the vicinity A78-49680 A78-18370 firfield pavement evaluation - FAA viewpoint Airfield pavement load evaluation - An A78-19681 international overview AIRFOIL PROFILES A78-19676 Progress in propeller aerodynamics Proposed load evaluation system for D.S. Air Force A78-47173 of airfield pavement On the theory of drag calculation and profile A78-49677 optimization in shockless near free molecular flow Transport Canada airfield pavement load evaluation A78-H7887 A78-49678 A mean camberline singularity method for French procedures for airfield pavement load two-dimensional steady and oscillatory aerofoils evaluation and control surfaces in inviscid incompressible A78-19679 flow Airfield pavement evaluation - The airline view [ARC-CP-1391] H78-30066 A78-19680 Two-dimensional aerofoils and control surfaces in Airfield pavement evaluation - FAA viewpoint simple harmonic motion in incompressible A78-19681 inviscid flow Pavement strength rating methods as viewed by [AHC-CP-1392] H78-30068 airframe manufacturers AIRFOILS A78-49682 Hermite closed splines AIRPORT TOBERS A78-19713 Dulles control tower console design study [AD-A056200] N78-31132 SUBJECT IHDEX ATTITODE COHTBOL

ilBPOBTS ANTENNA AEBAIS TRSB mcrovave landing system deionstration Analysis of nonopole antenna arrays on cylinders program at Brussels, Belgium by the geometrical theory of diffraction [AD-A0542981 H78-30075 [AD-A055197] N78-31335 A farther survey of some effects of aircraft noise AHTESSA DESIGN in residential communities near London Communication and navigation antennas for aircraft (Heathrow) airport Bnssian book [TT-7705] N78-30910 A78-48523 A comparison of annoyance caused by aircraft noise Conformal microstnp phased array for aircraft near London, Manchester and Liverpool airports tests with ATS-6 [TT-7706] H78-30911 J78-49428 TBSB oicrovave landing system demonstration ANTENNA BADI4TIOH PATTERNS program at Knstiansand, Norway Volumetric pattern analysis of airborne antennas [AD-A055317] U78-31071 J78-49427 TBSB microwave landing system demonstration Scan-limited near field testing for directive program at Charleroi, Belgium airborne antennas [AD-A055920] S78-31072 J78-49897 Parameters of future ATC systems relating to APPROACH CONTROL airport capacity/delay InterScan - A new microwave approach and landing [AD-A055082] N78-31130 guidance system Analysis of runway occupancy times at na^or airports A78-48736 C4D-A056052] B78-31131 Guidance and control problems in semiautomatic ALGOBITHHS recovery of the Aguila RP7 Guaranteed cost control of linear systems with [AIAA 78-1272] J78-50182 uncertain parameters - Application to remotely Approach guidance logic for a tilt-rotor aircraft piloted vehicle flight control systems [AIAA 78-1295] A.78-50202 [AIAA 78-1274] A78-5018H The influence of throttle augmented stability Performance in a jamming environment of a low-cost (JPCS) and short period control characteristics GPS user receiver algorithm for aiding a on the landing approach tactical INS [AD-A055892] N78-31123 [AD-A055239] N78-31078 ABCBITECTDBB (COBPOTEBS) ALIGNBERT BIL-STD-1553B proposed data bus development in In-flight alignment/calibration techniques for avionic architecture unaided tactical guidance of air-launched A78-U9866 missiles Digital system architecture for a 1980's jammer A78-49929 for military aircraft and ships ALL-SEATBEB AIR NAVIGATION A78-U9973 An investigation of potential control-display ABEA NAVIGATION configurations for V/STOL aircraft RNAV - Corporate operators set the pace CAIAA 78-1238] A78-50161 A78-M71424 ALL-KEATHEB LANDING STSTEBS ABROH RINGS InterScan - A new microwave approach and landing Stability and performance characteristics of a guidance system fixed arrow wing supersonic transport A78-48736 configuration (SCAT 15F-9898) at Hach numbers Landing aircraft under poor conditions from 0.60 to 1.20 A78-49549 [NASA-TM-78726] N78-30087 Navigation performance of the Triscan concept for ASTHIOHICS shipboard VTOL aircraft operations NPECON '78; Proceedings of the National Aerospace [AIAA 78-1293] A78-50200 and Electronics Conference, Dayton, Ohio, Bay ALOHINOH 16-18, 1978. Volumes 1, 2 6 3 Some sound transmission loss characteristics of A78-U9851 typical general aviation structural materials ASTBOHADT PEBFOBRANCE [AIAA PAPEB 78-11180] A78-47925 Safety of space flights ALOHINtJH ALLOTS A78-47952 Hetal technology for future aircraft design ATBOSEHEBIC COBPOSITION H78-30115 Simultaneous measurements of ozone outside and AHBIENT TEBPEBATOBE inside cabins of two 3-747 airliners and a Gates Experimental determination of parameters of Learjet business jet mathematical model of airplane cabin as [NASA-TB-78983] N78-31061 regulated object with respect to air temperature ATBOSPHEBIC DIFFUSION in the cabin On the use of zirconium 95 data from Chinese A78-48234 atmospheric thermonuclear explosions to study ANALOG COBPOTEES stratospheric transport in a one-dimensional A study of analog programming for prediction of parameterization crack growth in aircraft structures subjected to A78-48062 random loads ATSOSPHEBIC TOBBOLENCE [AD-A055789] N78-31097 Gust measurements and the N snb o problem ANGLE 0? ATTACK N78-30276 Boundary layers in axisymmetric inlets at angle of ATS 6 attack. I - neasnrements Conformal microstrip phased array for aircraft [AIAA PAPEB 78-1109] A78-48499 tests with ATS-6 Static aerodynamic characteristics of a typical A78-49428 single-engine low-wing general aviation design ATTACK AIBCBAFT for an angle-of-attack range of -8 deg to 90 deg COBED - The cockpit display of the future [NASA-CB-2971] N78-30048 combined Map and Electronic Display Botary balance data for a typical single-engine A78-47268 low-wing general aviation design for an Software structured weapon delivery angle-of-attack range of 30 deg to 90 deg A78-49875 [NASA-CB-2972] N78-30019 Flight controls of Army/Hughes YAH-64 advanced &NGOLAH VELOCITY attack helicopter Prediction of angular disturbances from airframe [AIAA 78-1237] A78-50160 members to airborne electro-optical packages ATTITUDE COHTBOL 478-19952 The effect of thrust vectoring and attitude Diverse forms and derivations of the equations of control concepts on the propnlsion system of motion of deformable aircraft and their mutual V/STOL aircraft relationship [AIAA PAPER 78-1020] A78-48481 [BAE-TB-77077] N78-30097 Bank-to-turn /BIT/ autopilot technology for •issiles A78-49927

A-9 ATTITDDE INDICATORS SUBJECT IHDEI

Performance of a ring laser strapdown attitude and F-15 avionics Built-in-Test beading reference for aircraft A78-19991 [AIAA 78-12401 A78-50162 AVIOHICS A learning flight control system for the F8-DFBB Advances in inertial navigation aircraft Digital Fly-By-Hire A78-17181 [AIAA 78-1288] A78-50195 AIDS in military aircraft Airborne Integrated ATTITDDE IHDICATOBS Data systems Computer Twoway - A position and orientation measurement A78-17866 system helicopter/VTOl landing aid application Flight deck display trends A78-19661 A78-17899 "ODITOBY T4SKS L-1011 flight data recording systems - Background, Evaluation of several secondary tasks in the features, implications and benefits determination of permissible time delays in [AIAA PAPEB 78-1171] f78-17917 simulator visual and motion cues Integrated avionics for future general aviation [NiSA-^P-1210] H78-30089 aircraft Simulator study of the effect of visual-motion [AIAA PAPEB 78-1182] 478-17927 time delays on pilot tracking performance with Evaluating avionics weight efficiency an audio side task A78-18228 [NASA-TP-12161 N78-30090 Highly survivable integrated avionics AOTOCOBBELATIOH A78-19163 F-15 inlet/engine test techniques and distortion IOGHOD - The fault-isolator for helicopter methodologies studies. Volume 1: electronic systems Autocorrelation functions A78-19239 fNASA-CH-111869] N78-30126 Design of a horizontal tail unit and related AOTOBATIC COHTB01 adjustments Digital area correlation tracker A78-19736 A78-19951 Aviation control system devices Russian book AUTOHATIC FLIGHT COSTBOL A78-19850 Design and development of a multifunctional NAECON '78; Proceedings of the National Aerospace helicopter control system and Electronics Conference, Dayton, Ohio, Hay A78-19396 16-18, 1978. Volumes 1,283 In-line monitoring of digital flight control A78-19851 computers A Costas loop with tangent error signal for use in A78-19860 Havstar GPS avionics Comparison monitoring in redundant digital flight A78-19858 control systems Laboratory testing of lightning and EBP A78-19865 susceptibility of avionxc systems The evolution of a remotely piloted vehicle A78-19861 microprocessor flight control system A qualitative analysis of redundant asynchronous [AHA 78-12731 A78-50183 operation Guaranteed cost control of linear systems with A78-19863 uncertain parameters - Application to remotely Comparison monitoring in redundant digital flight piloted vehicle flight control systems control systems [AIAA 78-12711] A78-50181 A78-19865 Software development for fly-by-wire flight HIL-STD-1553B proposed data bus development in control systems avionic architecture [AIAA 78-1276] A78-50185 A78-19866 Improved combat survivability for fly-by-wire Application of the General Purpose Multiplex sensor systems System to the A-7E avionics CAIAA 78-1277] ,178-50186 A78-19867 Close encounters of the aeroservoelastic kind A hierarchical network for avionic systems aerodynamics, structural dynamics, and automatic A78-19868 flight control systems for aircraft design Multiprocessing for electronic warfare avionics applications A78-19869 [AIAA 78-1289] A78-50196 Interface design considerations for F-16 sensors The effect of prefilter design on sample rate and weapons selection in digital flight control systems A78-19871 [AIAA 78-1308] A78-50209 Approach for identifying avionics flight software Control system design using vector-valued operational support reguirements - PAVE TACK an performance criteria with application to the example control rate reduction in parameter insensitive A78-19900 control systems Digital avionics support - A retrospective view of [DLR-FB-77-55] 878-31125 the future AOTOHATIC 1AHDISG COSTBOL A78-19903 Shipboard launch and recovery of HPV helicopters Digital simulation and flight verification of the in high sea states F-5E/F Flight Director Computer [AIAf 78-1269] A78-50179 A78-19905 Guidance and navigation for automatic landing, The DAIS Executive - An introduction avionics rollout, and turnoff using HLS and magnetic computer software cable sensors A78-19932 [AIAA 78-1296] A78-50203 Bulti-Function Inertial Beference fssembly /HIBA/ Flight demonstrations of curved, descending update digital aircraft systems approaches and automatic landings using time A78-19911 referenced scanning beam guidance The versatility of Jovial J73 in avionics systems fNASA-TH-78715] H78-30071 A78-19956 AUTOBATIC PILOTS Higher order languages for avionics software - A Bank-to-turn /BIT/ autopilot technology for survey, summary and critique missiles £78-19959 A78-19927 Impact of aircraft electrical power quality on AOTOBATIC TEST BQOIP8EHT utilization equipment Integrated test oission control - Present and A78-19962 future at the Air Force Flight Test Center The AH/APX-100/V/ transponder for military [AIAA PAPEB 78-1061] A78-17911 aircraft TF11-A-2/A7E inflight engine condition monitoring A78-19971 system /IECBS/ Digital system architecture for a ^980fs jammer [AIAA PAPEB 78-1172] A78-17918 for military aircraft and ships Ground test facility for integral rocket ramjets A78-19973 [AIAA PAPEF 78-931] A78-18151 F-15 avionics Built-in-Test S78-19991

A-10 SUBJECT INDEX CARBEB

A flight qualified graphics generator for B-1 BLOWING defense system Calculations of the effects of blowing from the 478-50007 leading edges of a cambered delta wing Flight demonstrations of curved, descending [ARC-B/H-3800] H78-30060 approaches and automatic landings using tine BODT-WIN6 ABD TAIL CORFIGOBATIONS referenced scanning bean guidance Nacelle effects on stability of VSTOL [HASA-TB-787W5] H78-30071I configurations including conventional, canard, Avionics cost development for alternatives of and tandem wing arrangements selected air traffic control systems [AIAA PAPER 78-1504] A78-U79H2 [AD-A05U823] N78-30080 BODY-WIHG CONFIGURATIONS The feasibility of estimating avionics support Modification of the Douglas Neuoann program to costs early in the acquisition cycle. Volume 1: improve the efficiency of predicting component The basic report interference and high lift characteristics [AD-A05I1016] N78-301"9 [NASA-CR-3020] R78-30051 Program analyses for the S-3 veapon system An automated procedure for computing the improvement program three-dimensional transonic flow over wing-body [AD-A055887] H78-31093 combinations, including viscous effects. Volume AFAL simulation facility/capability manual. 1: Description of analysis methods and Volume 1: Executive summary and Systems applications Avionics Division [AD-A055899] N78-31052 [AD-A055591] 1178-31102 BOBIHG 717 AIBCHAFT A modular adaptive, variable function flight Short-term performance deterioration in control sensor JT9D-7A (SP) engine 69571)3 [AD-A055175] N78-31120 rnASA-CR-135431] R78-30121 AXES OF ROTATION BOHBIHG BQOIPBENT Diverse forms and derivations of the equations of Software structured weapon delivery motion of deforoable aircraft and their mutual A78-U9875 relationship BOONDABY LATEB CONTROL fRAE-TR-77077] N78-30097 Two-dimensional subsonic wind tunnel evaluation of AIIAI FLOW two related cambered 15-percent thick ?. theoretical study of the performance of a number circulation control airfoils of different axial-flow turbine configurations fAD-A055110] N78-310U7 under conditions of pulsating flow Evaluation of a circulation control tail boom for [ > HI/BECH-F.NS-HEPT-1U9 1 R78-31101 yaw control OH-6 helicopter AXIAL FIOB TOBBIRES [AD-A055116] H78-31119 Pnalysis of multistage, axial flow turbonachine BOOHDABY LATEB PLOW wake production, transport, and interaction Solution of an adjoint problem of steady-state [AD-A05575«] N78-31118 heat transfer associated with the cooling of AXISTHHETBIC FLOW gas-turbine blades, by means of a Analysis of multistage, axial flow tnrbomachine quasi-analog/digital system wake production, transport, and interaction A78-47Q02 [AD-A055754] 878-31118 Boundary layers in axisymmetric inlets at angle of attack. I - Measurements [AIAA PAPEB 78-1109] A78-«8lt99 B Evaluation of a circulation control tail boom for B-1 AIBCHAFT yaw control OH-6 helicopter B-1 flight test progress report [AD-A055116] R78-31119 fAIAA PAPER 78-14181 A78-47903 BUILDINGS Rolling tail design and behavior as affected by Experimental determination of the rattle of simple actuator hinge moment limits for B-1 models maneuverability [HASA-TB-78756] B78-30291 [AIAA PAPEK 78-15003 A78-U7910 BYPASSES Wind Tunnel/Flight Test Correlation Program on the Evaluation of inlet reingestion for large bypass B-1 nacelle afterbody/nozzle at transonic ratio 7/STOL aircraft conditions [AIAA PAPEB 78-1079] A78-18195 [AIAA PAPER 78-989] A78-U8469 Operating characteristics of bypass turbojet engines The role of system performance analysis in the Russian book independent assessment of B-1 navigation software A78-50125 A78-M9902 A flight qualified graphics generator for B-1 defense system A78-50007 C BARD BEAB PIDER 6DIDANCE Landing aircraft under poor conditions Flight demonstrations of curved, descending A78-I49519 approaches and automatic landings using time CABIH ATBOSPHEBES referenced scanning beam guidance Simultaneous measurements of ozone outside and [RASA-TB-787q5] R78-3007H inside cabins of two B-747 airliners and a Gates BEABS (SUPPORTS) Learjet business jet Damping, static, dynamic, and impact [RASA-TB-78983] F78-31061 characteristics of laminated beans typical of CALCULATOBS windshield construction Jirplane stability calculations with a card [AD-A0541163] N78-30093 programmable pocket calculator BELGIDB [NASA-TB-78678] N78-30138 THSB microwave landing system demonstration CALIBRATING program at charleroi, Belgium In-flight alignment/calibration techniques for [AD-A055920] H78-31072 unaided tactical guidance of air-launched BLADE TIPS missiles Advanced optical blade tip clearance measurement A78-49929 system CAHBEE [RASA-C5-159U02] R78-31106 A mean camberline singularity method for Turbine tip clearance neasnrenent two-dimensional steady and oscillatory aerofoils fAD-A055765] H78-31115 and control surfaces in inviscid incompressible BIOIDOSN BIND TUNNELS flow Application of cryogenics in experimental [SHC-CP-1391] H78-30066 aerodynamics Analysis of advanced variable camber concepts A78-48982 R78-30108

A-11 CABBEBED SINGS SOBJECT IBDEX

Two-dimensional subsonic vind tunnel evaluation of CLOITEB two related cambered 15-percent thick Constant false alarm rate detector for a pulse circulation control airfoils radar in a maritime environment [AD-A055110] N78-31017 178-19975 CAMBERED KINGS A high duty factor chirp radar Calculations of the effects of blowing from the A78-19976 leading edges of a cambered delta sing CROS [ARC-B/M-3800] N78-30061 Non-volatile memory system for severe environment CAN&DAIB AIBCBAFT flight recorders From Challenger to winner Canadair executive A78-1*9872 ]et design and development COCKPITS A78-17570 COHED - The cockpit display of the future CiNABD COBFIGOBATIOBS combined Hap and Electronic Display Canard configured aircraft with 2-0 nozzle A78-17268 [AIAA PAPEB 78-11(50] A78-17901 Display systems and cocKpit design Nacelle effects on stability of VST01 N78-30116 configurations including conventional, canard, The design of a high g cockpit and tandem wing arrangements N78-30118 [AIAA PAPEB 78-1501] A78-17912 COLLISION AVOIDANCE CABTILEVER BEBBEBS IPC design validation and flight testing The effect on block fuel consumption of a strutted [AD-A055529] N78-31071 versus cantilever wing for a short-haul Experimental test plan for the evaluation of transport including strut aeroelastic aircraft separation assurance displays using considerations airline flight simulators [AIAA PAPEB 78-11511] A78-1790S [AD-A055819] N78-31131 CAPACITY COMBAT Analysis of runway occupancy times at major airports Air-to-air combat simulation [AD-A056052] B78-31131 A78-17868 CAPTDBE EFFECT Computerized aircraft attrition program Capture effect array glide slope guidance study [AD-A05578I)] B7B-31091 TAD-A055678] N78-31073 COHBIBATOBIAL ANALYSIS CABGO AIBCBAFT Combinatorially derived limits on the surface Cargo aircraft and spacecraft forward restraint return for an air/surface monopulse ranging radar criteria A78-50001 [AD-A055313] N78-3109S COBBOSTION CBAHBEBS CABGO SPiCECBlFT Methods available to OSBRA for analysis of Cargo aircraft and spacecraft forward restraint combustion chambers criteria [ONEBA, TP NO. 1978-93] A78-16915 [AD-A055313] 178-31095 Effects of high availability fuels on combustor CASCADE FLOW properties Linearized theory of plane, unsteady, supersonic [AD-A051229] N78-30259 flow through a cascade - Subsonic part of the Flame stabilization in a ramjet combustion chamber leading edge by means of a pilot gas generator [ONEBA, TP NO. 1978-103] 1178-17317 [DLB-FB-77-51] N78-31117 Linearized supersonic unsteady flow in cascades COBBOSTIOB EFFICIEBCT [ABC-R/M-3811 ] N78-30065 Let's put fuel efficiency into perspective CATHODE BAI TOBES A78-U7269 HHSD demonstration model development COBBOSTIOB PHYSICS [AD-J051137] N78-30120 Methods available to ONEBA for analysis of C&VITATIOB COBBOSIOH combustion chambers Operation of oil seales of aircraft piston engines [ONEBA, TP NO. 1978-93] A78-16915 under conditions of cavitation. I COBBOSTIOH PBODOCTS A78-17175 A preliminary comparison of thermal decomposition CAVITIES products of aircraft interior materials using ? research program to reduce interior noise in the National Bureau of Standards smoke chamber general aviation airplanes: Noise reduction and the combustion tube furnace through a cavity-backed flexible plate [AD-A051811] N78-30088 [NASA-CR-157588] N78-31873 COBFOBT CEHTBAL PBOCESSIHS OBITS Model of aircraft passenger acceptance Comparison study of BLS airborne signal processing A78-19681 technigues COBBABD AND COHTBOL A78-19901 Dual band airborne SATCOH terminal CENTRIFUGAL POHPS A78-19972 10 years of contract research for the COBREBCIAL AIBCBIFT pump/compressor industrial concern RNAV - Corporate operators set the pace A78-19175 A78-17121 CH-17 HEIICOPTEB Prospects for commercial commonality in military Modified helicopter icing spray system evaluation transports [AD-A0550391 H78-31091 [AIAA PAPER 78-1167] A78-19781 CHABBELS (DATA TBABSBISSIOB) Operating characteristics of bypass turbojet engines HIL-STD-1553B proposed data bus development in Bussian book avionic architecture A78-50125 A78-19866 Rotor burst protection program: Statistics on CHEnlCAL AHALYSIS aircraft gas turbine engine rotor failures that Material evaluation of polyurethane foam, 0.05 g/ occurred in OS commercial aviation during 1975 cm 3 density [NASA-CR-135301] N78-31105 [BDX-613-1836-BEV] N78-31219 COHBOJALITT (EQUIPMENT) CBIHP SIGBALS Prospects for commercial commonality in military A high duty factor chirp radar transports A78-19976 [AIAA PAPEB 78-1167] 478-19781 CHBOBIOH COBBOBICATIOB CABLES Extending the service life of aircraft components Fiber optic development for tactical fighter made of high-strength steels Russian book applications A78-18518 A78-19906 CLEABABCES COBPBTITIOB a dvanced optical blade tip clearance measurement The use of the AIAA-Bendiz Design Competition in system aerospace design courses [NASA-CS-159102] N78-31106 [AIAA PAPEB 78-1188] A78-17931

A-12 SUBJECT INDEX COBPOTEBIZED SIBDLATION

COBPILEBS COHPOTEB STOBAGE DEVICES The versatility of Jovial J73 in avionics systems Bon-volatile memory system for severe environment 478-49956 flight recorders COBPLEI SISTERS 478-49872 The design process cooputer aided design for COBPOTEB STSTEHS DESIGN couples aerospace systens A hierarchical network for avionic systeos [AI4A P4PEB 78-1483] 478-47928 478-49868 COHPOSITB HATBBIALS Digital avionics support - A retrospective view of New stroctnres Bade of composite materials for the future high performance conbat aircraft A78-49903 B78-30111 An interface management approach to software Hotor design implications for composite material development properties 478-19933 [aCEL-80117] N78-30182 Bulti-Function Inertial Reference fssembly /BIRA/ Fibre composite reinforcement of cracked aircraft update digital aircraft systems structures 478-49941 H78-30288 Application techniques for digital flight control COHPOSITE STBOCTUBES systems New structures made of composite materials for H78-30117 high perforuance combat aircraft COBPDTEB STSTBBS PBOGBABS N78-30114 The role of system performance analysis in the COHPBESSOBS independent assessment of B-T navigation software 10 years of contract research for the 478-49902 pump/compressor industrial concern The DAIS Executive - An introduction avionics A78-49175 computer software COHPDTEB GRAPHICS 478-49932 A flight gualified graphics generator for B-1 Higher order languages for avionics software - A defense system survey, summary and critique J78-50007 478-19959 COHPDTEB EBOGBABHIHG Real-time simulators for augmented inertial The DfIS Executive - An introduction avionics navigation systems computer software 478-49967 478-19932 Software development for fly-by-wire flight The versatility of Jovial J73 in avionics systems control systems 478-19956 tAIAA 78-12761 478-50185 A flight simulation high order language study Software design for a Visually-Coupled Airborne 478-49957 Systems Simulator (VC4SS) Higher order languages for avionics software - A [AD-4055226] N78-31133 survey, summary and critigue COBPOTEB TECHNIQUES 478-119959 Hethods available to ONEBA for analysis of COBPOTEB PBOSBAHS combustion chambers Software engineering a must for success in [OHBR4, TP HO. 1978-93] 478-16915 computerized flight test COHPDTEBIZBD DESIGN [AIAA PAPER 78-1463] 478-47913 The design process computer aided design for A computerized undergraduate aircraft design course complex aerospace systems [4IJ4 PAPER 78-1492] 478-47933 [4I4A PAPER 78-1183] 478-17928 Software structured weapon delivery Definition of airplane fuselage longitudinal lines A78-U9875 by the special contour method Approach for identifying avionics flight software J78-18222 operational support requirements - PAVE TACK an ninimum weight design of stiffened panels with example fracture constraints 478-49900 J78-49837 An interface management approach to software 4FAL simulation facility/capability manual. development Volume 1: Executive summary and Systems 478-49933 Avionics Division High-accuracy three-dimensional image [4D-A055591] N78-31102 reconstruction for an airborne line-scanning COHPDTEBIZBD SIBDL1TIOH system Solution of an adjoint problem of steady-state A78-119988 heat transfer associated with the cooling of REXOR 2 rotorcraft simulation model. Volume 1: gas-turbine blades, by means of a Engineering documentation guasi-analog/digital system [NASA-CR-145331] N78-30042 478-17402 REXOR 2 rotorcraft simulation model. Volume 2: V/STOI aircraft simulation - requirements and Computer implementation capabilities at Ames Research Center fHASA-CR-145332] N78-30043 [AIAS PAPER 78-1515] 478-49790 A calculator program for analyzing airloads on a A costas loop with tangent error signal for use in wing of arbitrary planform and camber in Navstar GPS avionics subsonic flow 478-49858 CAD-A054180] 178-30058 The terrain following task for the advanced Computer program for vibration prediction of tactical fighter using discrete optimal control fighter aircraft equipments 478-49862 [AD-A054598] N78-30094 Subsystem verification of an AFLC organically Helicopter transmission vibration and noise developed F-15 simulation Air Force reduction program. Volume 2: User's manual Logistics Command [AD-A054827J N78-30095 »78-«9901 Computer program for the design and off-design Real-time simulators for augmented inertial performance of turbojet and turbofan engine cycles navigation systems [NASA-TB-78653] N78-30122 J78-19967 General aviation airplane structural REXOR 2 rotorcraft simulation model. Volume 1: crashworthiness user's manual. Volume 1: Engineering documentation Program KRASH theory [NASA-CR-145331] H78-30042 CAD-AOS5898] N78-31088 REXOR 2 rotorcraft simulation model. Volume 2: Computerized aircraft attrition program Computer implementation [AD-4055784] N78-31091 [HASA-CR-145332] N78-30013 A study of analog programming for prediction of BEXOH 2 rotorcraft simulation model. Volume 3: crack growth in aircraft structures subjected to User's manual random loads [HASA-CB-115333] N78-30044 [AD-A055789] N78-31097

A-13 CONCORDE AIRCRAFT SUBJECT IHDEI

Description and performance of the Langley visual CONTROL THEORY landing display system Optimal control synthesis in distributed systems rNASA-Tn-78712] H78-30073 with incomplete information noting aircraft Procedures for generation and reduction of linear applications models of a turbofan engine A78-U8215 [NASA-TP-1261] N78-30896 Experimental determination of parameters of Graphics for the hybrid stores separation mathematical nodel of airplane cabin as simulation of the B77 system regulated object with respect to air temperature rSAND-78-8212] N78-31099 in the cabin AFfL simulation facility/capability manual. A78-1823H Volume 1: Executive summary and Systems Optimization techniques for air traffic control Avionics Division problems Russian book [AD-A055591] H78-31102 A78-U8504 COHCORDE AIRCRAFT Advanced control concepts for future fighter Long-distance focusing of Concorde sonic boom aircraft A78-H8052 N78-3010U CONFERENCES CONVERGENT-DIVERGENT NOZZLES Fighter aircraft design conferences Investigation of nonequilibrium two-phase flows in [AGAED-CP-2t1] ST8-30099 axisymmetric Laval nozzles COHFOBHAl HAPPING A78-182111 Dniformly exact conformal transformation of CORROSION PREVENTION exterior of circle onto exterior of wing profile Operation of oil seales of aircraft piston engines A78-U822U under conditions of cavitation. I CONGHESSIOHAI REPORTS A78-17175 Future needs and opportunities in the air traffic COBBOSIOB RESISTANCE control system Aircraft structural life monitoring and the [GPO-98-9311 ^78-31076 problem of corrosion COHHECTORS N78-30281 Fiber optic development for tactical fighter COST ANALYSIS applications Technology analysis - Candidate advanced tactical A78-U9906 fighters CONSOLES TAIAA PAPER 78-1U51] A78-U9782 Dulles control tower console design study Avionics cost development for alternatives of [\D-A056200] H78-31132 selected air traffic control systems COHTISOOOS SAVE BADAB [JD-A05U823] N78-30080 A freguency-selective TIG liuiter for airborne COST EFFECTIVENESS FH/CS X-band radar Non-volatile memory system for severe environment A78-50002 flight recorders COBTODRS A78-U9872 Definition of airplane fuselage longitudinal lines Accuracy requirement and cost effectiveness of by the special contour method GPS-aided INS for tactical fighters J78-18222 A78-U9989 CONTROL CONFIGURED VEHICLES COST ESTIHATES Highly survivable integrated avionics The feasibility of estimating avionics support A78-19163 costs early in the acquisition cycle. Volume 1: Assessment of dynamic coordinate alignment for The basic report elastic aircraft flight control Kalman [AD-A051016] H78-30119 filter estimates Estimated costs of extended low-rate airframe A78-19987 production CONTROL EQOIPBENT [AD-A051831] N78-31100 fviation control system devices Russian book COST REDUCTION A78-t9850 ^ Costas loop with tangent error signal for use in A standard programmable I/O for the advanced Navstar GPS avionics aircraft electrical system power control set A78-«9858 A78-49936 CRACK PROPAGATION Control system design using vector-valued Fatigue crack growth in pressurized fuselage panel performance criteria with application to the A78-18231 control rate reduction in parameter insensitive Load interaction effects in fatigue crack control systems propagation [DLR-FB-77-55] N78-31125 U78-30285 CONTROL SIBOLATION A model of crack-tip behaviour for fatigue life Digital control law synthesis in the w prime domain determination A78-46962 H78-30286 Air traffic control in the terminal area - Use of Recent developments in analysis of crack a simulation technique for the definition of an propagation and fracture of practical materials operative model stress analysis in aircraft structures 478-19733 [FASA-TB-78766] N78-30606 A gualitative analysis of redundant asynchronous Compilation of test data from an investigation on operation the effect of environment on crack growth under A78-U9863 flight-simulation loading Comparison monitoring in redundant digital flight [NLR-TR-76096-0] N78-30620 control systems CBACKIBG (FBACTOBIBG) A78-U9865 A study of analog programming for prediction of CONTROL SURFACES crack growth in aircraft structures subjected to Influence of slots on effectiveness of wing random loads mechanisation and control surfaces with tAD-A055789] N78-31097 separated flow CRANES A78-H8229 A study of the precision hover capabilities of the Two-dimensional aerofoils and control surfaces in aerocrane hybrid heavy lift vehicles simple harmonic motion in incompressible [i,D-A05U281] B78-30Q91 inviscid flow CRASBES [ARC-CP-1392] N78-30068 General aviation airplane structural Control-surface hinge-moment calculations for a crashworthiness user's manual. Volume 1: high-aspect-ratio supercritical wing Program KRASH theory rNASA-TB-78661] N78-31013 [AD-A055898] N78-31088 Two-dimensional subsonic wind tunnel evaluation of CREEP BUPTUBE STRENGTH two related cambered 15-percent thick Engineering data on new aerospace materials circulation control airfoils structural materials N7S-3"047 [AD-A05M61] N78-30213

A-1H SUBJECT IHDEX DIGITAL SIB01ATIOB

CROSS COBHELSTIOH DELTA BIHGS F-15 inlet/engine test techniques and distortion nirage 2000 - Dassault's better delta methodologies studies. Volume 7: cross A78-19169 correlation functions. Calculations of the effects of blowing from the [NASA-CB-111872] N78-30129 leading edges of a cambered delta wing CBOSS SECTIOHS [ABC-B/H-3800] H78-30061 Hethod of calculating aerodynamic coefficients of Aerodynamics of the new generation of combat some three-dinensional bcdies with arbitrary aircraft with delta wings cross section H78-30106 478-1(92115 Aerodynamic characteristics of a hypersonic CBDISE BISSILES research airplane concept having a 70 deg swept Center-loaded duct integral rocket-to-ramjet double-delta winq at nach number 0.2 transition testing [HASA-TP-1252] H78-31015 [AIAA PAPEB 78-937] 478-18156 DEHABD (ECOHOBICS) CBDISIHG FLIGHT Demand modelling of passenger air travel: An Effects of wind on aircraft cruise performance analysis and extension, volume 2 fAIAA PAPEB 78-1196] A78-17937 [NASA-CB-157102] N78-30069 CBYOGEFIC »IHD TOHBEIS DESIGN ABALYSIS fpplication of cryogenics in experinental Design philosophy for engine forgings aerodynamics A78-17152 A78-18982 Design philosophy for airframes CBYSTAL OSCHLATOBS A78-17153 A compensation technique for acceleration-induced A computerized undergraduate aircraft design course frequency changes in crystal oscillators [AIAA PAPEB 78-11492] A78-17933 A78-1I9859 Effect of performance objectives on the design and COSHIOHCBiPT GBOOHD EFFECT HACBTHE cost of future OSAF pilot training aircraft Test and demonstration prototype tracked air [AIAA PAPEB 78-1198] A78-17938 cushion vehicle (PTACV): Phase IIIC Design for durability - The F101-GE-100 engine [PB-279970/8] N78-31007 [AIAA PAPEB 78-1081] A78-18197 CYCLIC LOADS DETECTOBS Fatigue S/N data in relation to variability in A modular adaptive, variable function flight predicted life control sensor N78-30278 [AD-A055175] N78-31120 DETBBIOBATIOH Detecting abnormal turbine engine deterioration using electrostatic methods DASSAULT AIBCBAFT [4IAA PAPEB 78-1173] A78-17919 Hirage 2000 - Dassault's better delta DIGITAL COHBAHD STSTESS 478-19169 Highly survivable integrated avionics DATA ACQUISITION A78-19163 Ose of onboard computerized flight test analysis The terrain following task for the advanced systems tactical fighter using discrete optimal control [AIAA PAPEB 78-11162] 478-17912 A78-19862 The role of the computer in the flight testing of Comparison monitoring in redundant digital flight general aviation aircraft control systems [AIAA PAPEB 78-1165] 478-17911 A78-19865 TBACfLS evaluation report. TiCAH. VOB, and ILS DIGITAL COBPOTEBS station evaluation report, Andersen AFB, Guam The role of the computer in the flight testing of [AD-A051211] N78-30078 general aviation aircraft IPC design validation and flight testing [AIAA PAPEE 78-1165] A78-17911 [AD-A055529] H78-31071 Digital simulation and flight verification of the DATA HAHAGEBEHT F-5E/F Flight Director Computer The design process computer aided design for A78-19905 complex aerospace systems Application techniques for digital flight control [AIAA PAPEH 78-1183] 178-17928 systems An interface management approach to software N78-30117 development General aviation airplane structural 478-19933 crashworthiness user's manual. Volume 1: DATA BECOBDIBG Program RBASH theory L-1011 flight data recording systems - Background, [AD-A055898] H78-31088 features, implications and benefits DIGITAL FILTEBS [AIAA PAPEB 78-1171] A78-17917 Synthesis of digital flight control systems by the DATA BEDOCTIOR method of entire eigenstructure assignment Aircraft electrical system testing and data A78-19861 reduction using digital techniques The effect of prefilter design on sample rate A78-19937 selection in digital flight control systems DATA SAHPLIHG [AIAA 78-1308] A78-50209 The effect of prefilter design on sample rate DIGITAL BAVIGATIO8 selection in digital flight control systems In-line monitoring of digital flight control [AIAA 78-1308] A78-50209 computers DATA SYSTBHS J78-19860 AIDS in military aircraft Airborne Integrated Synthesis of digital flight control systems by the Data Systems Computer method of entire eigenstrncture assignment A78-17866 A78-19861 Integrated test mission control - Present and DIGITAL SIBDLATIOH future at the Air Force Flight Test Center Digital control law synthesis in the w prime domain [AIAA PAPEB 78-1161] A78-U7911 A78-16962 High-accuracy three-dimensional image Comparison monitoring in redundant digital flight reconstruction for an airborne line-scanning control systems system J78-19865 A78-19988 Digital simulation and flight verification of the DATA TB4HSHISSIOS F-5E/F Plight Director Computer Application of the General Purpose Hultiplez 478-19905 System to the A-7S avionics Air-to-air designate/track with time sharing A78-19867 A78-19977 DEICEBS Guidance and navigation for automatic landing, Demonstration of the nicrowave ice protection rollout, and turnoff using HLS and magnetic concept cable sensors [AD-A055821] H78-31096 [AIAA 78-1296] 478-50203

A-15 DIGITAL SYSTEHS SUBJECT IHDEI

DIGITAL SYSTEBS DISTOBTIOS Stability augmentation by eigenvalues control and F-15 inlet/engine test techniques and distortion model matching methodologies studies. Volume 2: Time variant A78-46965 data quality analysis plots Design and development of a multifunctional [BASA-CB-141867] H78-30124 helicopter control system DISTBIBDTED PABABBTEE SISTERS A78-49396 Optimal control synthesis in distributed systems Peace Shine - A digital Weapon Control System for with incomplete information noting aircraft the F-« aircraft applications A78-49876 A78-18215 Digital avionics support - A retrospective view of DBAG BEDDCTIOH the future Flight experience on the need and use of inflight 478-49903 leading edge washing for a laminar flow airfoil aulti-Function Inertial Reference Assembly /BIBA/ [AIAA PAPEH 78-1512] A78-17917 update digital aircraft systems DYHAHIC CHABACTEBISTICS A78-49941 Dynamic analysis of electrical systems Digital area correlation tracker A78-49934 A78-49951 Airplane stability calculations with a card Digital system architecture for a 1980's yammer programmable pocket calculator for military aircraft and ships [BASA-TB-78678] B78-30138 A78-49973 Turbine engine rotordynamic evaluation, volume 1 £ flight gualified graphics generator for B-1 [AD-A055262] K78-31111 defense system DIBASIC LOADS A78-50007 Airfield pavement load evaluation - An Triplex digital fly-by-wire redundancy management international overview technigues A78-19676 [AIA1 78-1279] A78-50187 DYBARIC HODELS The effect of prefilter design on sample rate Optimal flight control synthesis via pilot modeling selection in digital flight control systems [AIAA 78-1286] " A78-50193 [AIAA 78-1308] A78-50209 DIBASIC EESPOSSE Inherent errors in asynchronous digital flight Improved aircraft dynamic response and fatigue controls life during ground operations using an active [AD-A055649] N78-31124 control landing gear system DIGITAL TECHNIQUES [AIAA PAPEE 78-1199] A78-17939 Aircraft electrical system testing and data Experimental investigation of gust response of reduction using digital techniques hingeless helicopter rotors J78-49937 [AD-A054752] B78-30142 DIBECTIONAL ANTENNAS Engine/airframe/drive train dynamic interface Scan-limited near field testing for directive documentation airborne antennas [AD-A055766] N78-31111 A78-49897 DYBABIC STABILITY DIBECTIONAL STABILITY Ose of ground vibration test equipment to Evolution of a cost-effective, task-oriented, determine unsteady aerodynamic forces lateral-directional SAS for the iV-10 aircraft A78-49708 Stability Augmentation System DYHABIC STBOCTOBAL ANALYSIS [AIAA PAPER 78-1460] A78-47910 Structural dynamics, stability, and control of DISPLACBBENT BEASOBEHEHT helicopters Measurement of vibratory displacements of a [BASA-CB-158909] N78-30139 rotating blade A78-49397 French procedures for airfield pavement load evaluation ECOBOHIC ANALYSIS A78-49679 An integrated analysis of the fundamental problems DISPLAY DEVICES of air transport COHED - The cockpit display of the future A78-49447 combined Bap and Electronic Display 'Supermarket1 airplanes aircraft replacement A78-47268 cycle in major airlines Flight deck display trends [AIAA PAPEB 78-1533] A78-49769 A78-147899 Operations and economics of U.S. air transportation Solid-state displays for fuel management systems [AIAA PAPEB 78-1545] A78-49770 for aircraft EDUCATION A78-47900 Teaching design at all levels in aerospace A flight qualified graphics generator for B-1 engineering curricula defense system [AIAA PAPEB 78-1155] A78-47906 A78-50007 A computerized undergraduate aircraft design course ?n investigation of potential control-display [AIAA PAPEB 78-1492] A78-47933 configurations for V/STOL aircraft The value of aerospace design synthesis courses as [AIAA 78-1218] A78-50161 viewed by aerospace professionals Description and performance of the langley visual [AIAA PAPEB 78-1493] A78-47934 landing display system EIGENVALUES [IHSA-TB-78742] N78-30073 Synthesis of digital flight control systems by the Display systems and cockpit design method of entire eigenstructure assignment B78-30116 A78-49864 HHSD demonstration model development EIGENVECTOBS rAD-A054437] N78-30120 Synthesis of digital flight control systems by the Dulles control tower console design study method of entire eigenstructure assignment [AD-A056200] N78-31132 A78-49864 Experimental test plan for the evaluation of EJECTOBS aircraft separation assurance displays using An analytical and experimental investigation of airline flight simulators diffnsers for VSTOL thrust augmenting ejectors [AD-A0558491 N78-31134 [AIAA PAPEB 78-1509] A78-47945 DISTANCE BEASOBING EQOIPBENT ELASTIC BODIES Tvovay - \ position and orientation measurement Assessment of dynamic coordinate alignment for system helicopter/VTOL landing aid application elastic aircraft flight control Kalman A78-49661 filter estimates A design of trajectory estimator using multiple A78-49987 DBE range measurements [AD-A055191] H78-31077

A-16 SUBJECT ISDBX ENGINE ISLETS

ELASIOPLASTICITY ELECTBOSTATIC PROBES The inflaence of the environment on the Detecting abnormal turbine engine deterioration elastoplastic properties of adhesives in metal using electrostatic methods bonded joints in aircraft structures [AIAA PAPEB 78-1173] A78-17919 [DLB-FB-77-63] N78-31251 EBBBGI CONSEB7ATION BLECTBIC DISCH4ESES The second generation of high-bypass turbofans - A Flight application of optical fiber transmission market clouded by uncertainty on a Falcon 10 aircraft 478-47123 rOHEBA, IP HO. 1978-105] 478-47309 EBEBGT COH7EBSIOH EIECTBIC BQUIPBENT TESTS 10 years of contract research for the Aircraft electrical systea testing and data pump/compressor industrial concern redaction nsing digital techniques 478-49175 478-49937 EBEBGY COBVEBSION EFFICIENCY ELECTBIC POTENTIAL Fnergy efficient engine: Preliminary design and Neutralization problem for a Space Shuttle integration studies 478-17121 tNASA-CB-135444] N78-31108 E1ECTBIC POBEB SUPPLIES BHEBGY DISSIPATION Dynamic analysis of electrical systems Short-term performance deterioration in 478-49934 JT9D-7A(SP) engine 695713 Application of rare earth/transition metal [BASA-CB-135431] N78-30121 permanent magnets to 100 Hz aircraft systems - ENEBGY BEQDIBERENTS ftn AF overview Impact of aircraft electrical power quality on A78-19935 utilization equipment A standard programmable I/O for the advanced A78-49962 aircraft electrical system power control set ENGINE CONTROL A78-19936 Alternatives for jet engine control Modeling refinements for the rectified [N4SA-CE-157578] N78-31107 superconducting alternator airborne power ENGINE COOLANTS supply Solution of an adjoint problem of steady-state 478-49961 heat transfer associated with the cooling of Impact of aircraft electrical power quality on gas-turbine blades, by means of a utilization equipment guasi-analog/digital system A78-19962 478-47402 ELECTBO-OPTICS ENGINE DESIGN Prediction of angular disturbances from airframe Design philosophy for engine forgings members to airborne electro-optical packages A78-47152 478-49952 NASA engine system technology programs - An overview Advanced optical blade tip clearance measurement [AIAA PAPEB 78-928] J78-48452 system Propulsion for future supersonic transports - 1978 [N4S4-CH-159402] N78-31106 status ELECTBOPOBHIHS [AIAA PAPEB 78-1051] A78-48486 Large electroformed nickel moulds for aircraft parts Advanced supersonic transport engine integration A78-17267 studies for near-term technology readiness date BLECTBOBAGNETIC IHTEBACTIONS [AI44 P4PEK 78-1052] A78-48487 Electromagnetic coupling analysis of a Lear jet Design for durability - The F101-GE-100 engine aircraft in a lightning environment [4144 P4PEB 78-1084] 478-48497 A78-19920 Operating characteristics of bypass turbojet engines BLECTBOMAGNETIC PULSES Russian book Laboratory testing of lightning and EWP 478-50125 susceptibility of avionic systems Advance nozzle technology 478-49861 N78-30111 ELECTBON BEARS Computer program for the design and off-design Neutralization problem for a Space Shuttle performance of turbojet and turbofan engine cycles 478-47121 [NASA-Tfl-78653] N78-30122 ELECTBOBIC CO01TEBBEASOBBS Energy efficient engine: Preliminary design and Comparisons of high anti-jam design technigues for integration studies GPS receivers Global Positioning System [NASA-CB-135444] N78-31108 >78-19857 ENGINE FAILURE Multiprocessing for electronic warfare avionics Rotor burst protection program: Statistics on A78-19869 aircraft gas turbine engine rotor failures that Performance in a jamming environment of a low-cost occurred in OS commercial aviation during 1975 GPS user receiver algorithm for aiding a [NASA-CR-135301] H78-31105 tactical INS ENGINE INLETS [40-4055239] N78-31078 Boundary layers in axisymmetric inlets at angle of ELECTBOSIC EQUIPBEHT attack. I - Heasurements Evaluation of methods for calculating system [4IJ4 PAPER 78-1109] A78-48199 operating time in accordance with Reliability Intake design for fighter aircraft Improvement Warranty (RIB) contractual terms N78-30110 [AD-A051822] N78-30079 F-15 inlet/engine test techniques and distortion ELECTRONIC EQDIPBENT TESTS methodologies studies. Volume 1• Technical LOGHOD - The fanlt-isolator for helicopter discussion electronic systems [NASA-CH-111866] N78-30123 A78-19239 F-15 inlet/engine test techniques and distortion Laboratory testing of lightning and EBP methodologies studies. Volume 2: Time variant susceptibility of avionic systems data quality analysis plots A78-49861 [NASA-CE-111867] N78-30124 ELECTBOBIC RODOLES F-15 inlet/engine test technignes and distortion Modular Hissionization Systems /HMS/, an adaptive methodologies studies. Volume 3: Power system interface concept spectral density plots 478-49852 [HASA-CH-141868] N78-30125 A nodular adaptive, variable function flight F-15 inlet/engine test technigues and distortion control sensor methodologies studies. Volune 1: TAD-A055175] N78-31120 Autocorrelation functions ELECTBOSTATIC CBABGE [N4SA-CR-144869] N78-30126 Investigation of electrostatic discharge in P-15 inlet/engine test technigues and distortion aircraft fuel tanks during refueling methodologies studies. Volume 5: Bffect of T4I4A PAPEB 78-1501] 178-47981 filter cutoff frequency on turbulence plots [N4S4-CH-144870] N78-30127

A-17 EHGIHE BOHITOBIHG INSTBOHEHTS SUBJECT IHDEI

F-15 inlet/engine test techniques and distortion EBVIBOHBERTAL QUALITY methodologies studies. Volume 6: Distortion Noise in airports, its measurement, and its effect analysis plots on the communities in the vicinity [NASA-CR-144871] N78-30128 A78-48374 F-15 inlet/engine test techniques and distortion EHVIROHHEHTAL TESTS methodologies studies. Volume 7: Cross Fiber optic development for tactical fighter correlation functions. applications ^ fNASA-CR-11118721 N78-30129 A78-49906 EHGIHE HOHITOBIHG IHSTHOHEHTS EQUATIONS OF BOTIOB 'IDS in engine management programmes Airborne BEXOB 2 rotorcraft simulation model. Volume 2: Integrated Data Systems Computer implementation A78-47865 [HASA-CB-145332] N78-30043 Detecting abnormal turbine engine deterioration A study of the precision hover capabilities of the using electrostatic methods aerocrane hybrid heavy lift vehicles fAIAf PAPER 78-1173] A78-U7919 [AD-A054281] H78-30091 Sensor technology for turbine engine monitoring Diverse forms and derivations of the equations of systems motion of deformable aircraft and their mutual [AIAA PAPER 78-1471] A78-17920 relationship Engine vibration in flight [BAE-TB-77077] H78-30097 fAIAA PAPER 78-1475] A78-47921 EQDIPBEHT SPECIFICATIONS Ose of a field bench for testing turbojet engines Aeronautical procurement - The primary A78-49731 specification system EHGIHE PABTS (AIAA PAPEB 78-1489] A78-47932 Operation of oil scales of aircraft piston engines Botor design implications for composite material under conditions of cavitation. I properties A78-47175 [DCRL-80117] H78-30182 Aspects of the thermal fatigue strength of EBBOB ANALYSIS gas-turbine engine components Inherent errors in asynchronous digital flight A78-49176 controls Turbine tip clearance measurement [AD-A055649] N78-31124 [AD-A055765] N78-31115 EBBOB SIGNALS EHGIHE TESIS A Costas loop with tangent error signal for use in TF41-A-2/A7E inflight engine condition monitoring Navstar GPS avionics system /IECHS/ A78-49858 (AIAA PAPEB 78-1472] A78-47918 EIBADST DIFFOSEBS Analysis of GTE tolerance monitoring parameter An analytical and experimental investigation of formation gas turbine engine diffusers for VSTOL thrust augmenting e3ectors A78-48212 [AIAA PAPEB 78-1509] A78-47945 Ground test facility for integral rocket ramjets EXHAUST GASES CAIAA PAPEB 78-934] A78-48454 Gas turbine engine emissions - Problems, progress Ramjet engine testing and simulation techniques and future [ilAA PIPER 78-935] A78-48455 A78-49336 Center-loaded duct integral rocket-to-ramjet EXHAUST HOZZLES transition testing Aerodynamic characteristics induced on a [AIAA PAPEB 78-937] A78-48456 supercritical wing due to vectoring twin nozzles Dse of a field bench for testing turbojet engines at Hach numbers from 0.40 to 0.95 A78-49731 [HASA-TH-78746] N78-30039 F-15 inlet/engine test techniques and distortion Advance nozzle technology methodologies studies. Volume 1: Technical N78-30111 discussion EXTEBHAL STOBES [NASf-CR-144866] H78-30123 Wing/store active flutter suppression - F-15 inlet/engine test techniques and distortion Correlation of analyses and wind tunnel data methodologies studies. Volume 2: Tine variant (AIAA PAPER 78-1459] A78-47909 data quality analysis plots Graphics for the hybrid stores separation [NASA-CR-144867] 1178-30124 simulation of the B77 system F-15 inlet/engine test techniques and distortion [SAHD-78-8212] H78-31099 methodologies studies. Volume 3: Power EXTEBHAL SDBFACE COBBEHTS spectral density plots Flight application of optical fiber transmission [NfSA-CR-144868] N78-30125 on a Falcon 10 aircraft F-15 inlet/engine test techniques and distortion [ONEBA, TP HO. 1978-105] A78-47349 methodologies studies. Volume 4: BITBEBELT BIGB FEEQOEHCIES Autocorrelation functions Dual band airborne SATCOH terminal [NASA-CR-144869] N78-30126 A78-19972 F-15 inlet/engine test techniques and distortion methodologies studies. Volume 5: Effect of filter cutoff frequency on turbulence plots [NASA-CR-144870] 1178-30127 F-4 AIBCBAFT F-'5 inlet/engine test techniques and distortion Synthesis of digital flight control systems by the methodologies studies. Volume 7: Cross method of entire eigenstructure assignment correlation functions. A78-49864 [HASA-CR-144872] S78-30129 Peace Rhine - A digital Weapon control System for F-15 inlet/engine test techniqnes and distortion the F-4 aircraft methodologies studies. Volume 8: Cross A78-49876 spectral density plots F-5 AIBCBAFT [NASA-CS-144873] N78-30130 Some observations on the mechanism of aircraft F-15 inlet engine test techniques and distortion ving rock methodologies studies. Volume 9: Stability [AIAA PAPEB 78-1456] A78-47907 audits Digital simulation and flight verification of the [NASA-CB-144874] H78-30131 F-5E/F Flight Director Computer EHVIBOHBEHT EFFECTS A78-49905 fn assessment of the effect of supersonic aircraft F-8 AIBCBAFT operations on the stratospheric ozone content A learning flight control system for the F8-DFBS [HASA-RP-1026] N78-30774 aircraft Digital Fly-By-Bire The influence of the environment on the [AIAA 78-1288] A78-50195 elastoplastic properties of adhesives in metal The effect of prefilter design on sample rate bonded joints in aircraft structures selection in digital flight control systems [DIR-FB-77-63] H78-31251 [AIAA 78-1308] A78-50209

A-18 SUBJECT ISDEI FIGHTEB ilBCBAPT

F-15 AIRCRAFT Fracture mechanics fundamentals with reference to Subsystem verification of an APLC organically aircraft structural applications developed F-15 simulation Air Force H78-30271 Logistics Command Structural fatigue testing A78-49901 N78-30279 F-15 avionics Built-in-Test HDI and the detection of fatigue A78-19991 B78-30282 F-15 inlet/engine test techniques and distortion The development of the theory of structural fatigue methodologies studies. Volume 1: Technical N78-30283 discussion Load interaction effects in fatigue crack rHASA-CB-111866] N78-30123 propagation F-15 inlet/engine test techniques and distortion H78-3028S methodologies studies. Volume 2: Time variant Becent developments in analysis of crack data quality analysis plots propagation and fracture of practical materials [RASA-CB-111867] U78-30121 stress analysis in aircraft structures F-15 inlet/engine test technigaes and distortion [HASA-TH-78766] H78-30606 methodologies studies. Volume 3: Power FATIGDE LIFE spectral density plots Improved aircraft dynanic response and fatigue [NASA-CB-111868] H78-30125 life during ground operations using an active F-15 inlet/engine test technigaes and distortion control landing gear system methodologies studies. Volume t: [AIAA PAPEB 78-1199] A78-17939 Autocorrelation functions Aircraft structural fatigue [HASA-CB-111869] 178-30126 [ABL/STBUC-BEPT-363] N78-30271 F-'5 inlet/engine test techniques and distortion Fatigue S/N data in relation to variability in methodologies studies. Volume 5: Effect of predicted life filter cutoff frequency on turbulence plots S78-30278 rNASA-CB-1Hl|870] N78-30127 Current developments in the life of aircraft F-15 inlet/engine test techniques and distortion structure methodologies studies. Volume 6: Distortion H78-30280 analysis plots Aircraft structural life monitoring and the fNASA-CB-111871 ] H78-30128 problem of corrosion F-15 inlet/engine test techniques and distortion H78-30281 methodologies studies. Volume 7: Cross A model of crack-tip behaviour for fatigue life correlation functions. determination [HASA-CB-111872] N78-30129 H78-30286 F-15 inlet/engine test techniques and distortion The influences of residual stresses on oscillating methodologies studies, volume 8: Cross tensile strength and the measurement of residual spectral density plots stress, with emphasis on aircraft construction [NASA-CB-111873] N78-30130 fatigue life of aircraft construction F-15 inlet engine test techniques and distortion materials methodologies studies. Volume 9: Stability [BSVG-FBHT-77-23] H78-30603 audits FATIGUE TESTS [NASA-CB-11U871] H78-30131 Development of a load sequence for a structural Hazard assessment of aircraft gun compartments fatigue test [AD-A055026] N78-31061 N78-30277 F-16 1IHCBAFT Structural fatigue testing Interface design considerations for F-16 sensors N78-30279 and weapons Current developments in the life of aircraft A78-19871 structure An interface management approach to software N78-30280 development Aircraft structural life monitoring and the H78-49933 problem of corrosion Status of the Air Force's F-16 aircraft program N78-30281 rPB-28030U/7] H78-319H6 NDI and the detection of fatigue F-18 AIBCBAFT H78-30282 Software development for fly-by-wire flight The development of the theory of structural fatigue control systems N78-30283 [AIAA 78-1276] A78-50185 FEEDBACK COHTBOL Fighter superiority by design Digital control law synthesis in the w prime domain N78-30105 A78-46962 F-111 AISCBAFT Hing/store active flutter suppression - Non-axisymmetric nozzle design and evaluation for Correlation of analyses and wind tunnel data F-111 flight demonstration [AIAA PAPER 78-1159] A78-17909 [AIAA PAPEB 78-1025] A78-18183 Improving the accuracy of HOD approaches in FAIL-SAFE STSTBHS windshear with a new control law F-15 avionics Built-in-Test [AIAA PAPEB 78-1191] A78-17935 A78-49991 Guaranteed cost control of linear systems with FAItUBE ANALYSIS uncertain parameters - Application to remotely Detecting abnormal turbine engine deterioration piloted vehicle flight control systems using electrostatic methods [AIA1 78-1274] A78-50181 [1IAA PAPEB 78-1173] A78-17919 Software development for fly-by-wire flight FALLOUT control systems On the use of zirconium 95 data from Chinese [AIAA 78-1276] A78-50185 atmospheric thermonuclear explosions to study Inherent errors in asynchronous digital flight stratospheric transport in a one-dimensional controls parameterization [AD-A055619] H78-31121 A78-18062 FIBBB OPTICS FABS Flight application of optical fiber transmission Ground impingement of a fan jet exhaust plume on a Falcon 10 aircraft TSD-A051832] N78-31112 [OHEBA, TP 80. 1978-105] A78-47319 FATIGUE (BiTBBIALS) Fiber optic development for tactical fighter Aircraft structural fatigue applications [ABL/STBDC-BEPT-363] H78-30271 A78-H9906 Safety against fatiqne in flight: a perspective FIGHTBB AIBCBAFT of Australian experience and research Air-to-air combat simulation N78-30272 A78-07868 Mechanisms of fatigue and fracture Canard configured aircraft with 2-D nozzle B78-30273 [AIAA PAPEB 78-1150] A78-Q7901

A-19 FIGDBE OF HEBIT SUBJECT IHDBJ

The HiHAT BPBV system Large deflection static analysis of typical [AIAA PAPER 78-111571 A78-47908 tail-wheel structure of light aircraft by finite Studies of aerodynamic technology for VSTOI element method fighter/attack aircraft A78-48864 [AIAS PAPEB 78-1511] A78-47946 FIBEBBB 2 MBeET DROSS 4IBCB4FT Status of a nozzle-airframe study of a highly Drones for aerodynamic and structural testing maneuverable fighter /DAST/ - A status report TAIAA PAPEE 78-990] A78-48470 [AIAA PAPEB 78-1485] A78-47929 Installed performance of vectoring/reversing FIXED SIHGS non-axisyrometric nozzles Effects of wind on aircraft crnise performance [AIAA PAPEE 78-1022] A78-48482 [AIAA PAPEB 78-1496] A78-47937 Vectoring non-axisymmetric nozzle jet induced FLAHE STABILITI effects on a V/STOL fighter model Flame stabilization in a ramjet combustion chamber [AIA' PAPEE 78-1080] A78-48496 by means of a pilot gas generator Birage 2000 - Dassault's better delta [DIE-FB-77-54] N78-31117 A78-49169 FLABBABILITT Technology analysis - Candidate advanced tactical Assessment of relative flammability and fighters thermochemical properties of some thermoplastic [AIAA PAPEE 78-1451] A78-49782 materials Design evolution of a supersonic cruise A78-49693 strike-fighter PliBHABLE GASES [AIAA PAPEF 78-1152] A78-49783 Hazard assessment of aircraft gun compartments The terrain folloving task for the advanced [AD-A055026] N78-31064 tactical fighter using discrete optimal control Fill PL1TBS A78-49862 Some sound transmission loss characteristics of Fiber optic development for tactical fighter typical general aviation structural materials applications [SIAA PAPER 78-1480] A78-47925 A78-H9906 FLAT SDBFACES Accuracy reguirement and cost effectiveness of Analysis of a suspension system for a wheel GPS-aided INS for tactical fighters rolling on a flat track A78-49989 [BASA-CB-157563] H78-30583 Improved combat survivability for fly-by-wire FLIGHT CHABACTEHISTICS sensor systems Bide quality evaluation. IV - Models of subjective [AIAA 78-1277] A78-50186 reaction to aircraft motion Computer program for vibration prediction of A78-47490 fighter aircraft equipments ?IDS in engine management programmes Airborne [AD-A054598] N78-30094 Integrated Data Systems Fighter aircraft design conferences A78-07865 [AGABD-CP-241] N78-30099 Dynamics of the longitudinal motion of an airplane Advanced control concepts for future fighter with a variable-geometry wing aircraft A78-49285 N78-30104 BPV flying qualities design criteria Aerodynamics of the new generation of combat [AIAA 78-1271] A78-50181 aircraft with delta wings FlIGHT CONDITIOHS N78-30106 Landing aircraft under poor conditions Snpercruiser fighter analysis A78-49549 N78-30'07 FLIGHT COHTBOL Analysis of advanced variable camber concepts Constant-control rolling maneuver N78-30108 A78-46961 Variable-cycle engine fighter aircraft: Advance Non-axisymmetric nozzle design and evaluation for in performance and development problems P-111 flight demonstration N78-30109 [AIAA PAPEE 78-1025] A78-48483 Intake design for fighter aircraft Optimization technigues for air traffic control N78-30110 problems Russian book Advance nozzle technology A78-H8504 B78-30111 Design of a horizontal tail unit and related Impact of active control on structures design adjustments N78-30113 A78-49736 Sew structures made of composite materials for V/STOL aircraft simulation - Eeguirements and high performance combat aircraft capabilities at Ames Besearch Center N78-30114 [AIAA PAPER 78-1515] A78-49790 Metal technology for future aircraft design A qualitative analysis of redundant asynchronous H78-30115 operation Display systems and cockpit design A78-49863 H78-30116 Synthesis of digital flight control systems by the Application technigues for digital flight control method of entire eigenstructure assignment systems A78-49864 H78-30117 Bank-to-turn /BIT/ autopilot technology for The design of a high g cockpit missiles H78-30118 A78-49927 The feasibility of estimating avionics support Strapdown seeker guidance for tactical weapons costs early in the acquisition cycle. Volume 1: 478-49928 The basic report Assessment of dynamic coordinate alignment for [4D-A054016] N78-30119 elastic aircraft flight control Kalman The terrain following task for the advanced filter estimates tactical fighter using discrete optimal control A78-49987 [AD-A055196] N78-31121 Flight controls of Army/Hughes YAH-64 advanced FIGURE OP BBBIT attack helicopter Operational regularity in air transport [AIAA 78-1237] A78-50160 A78-49449 An investigation of potential control-display FINITE ELEBEHT HETHOD configurations for V/STOL aircraft Calculation of exchange coefficients for [AIAA 78-1238] A78-50161 high-temperature turbine blades Optimal terrain-aided navigation systems [ONEEA. Tp NO. 1978-104] A78-47348 [AIAA 78-1243] A78-50163 Superelement method for helicopter fuselage analysis BPV flying qualities design criteria A78-48209 [AIAA 78-1271] A78-50181 Optimal flight control synthesis via pilot modeling [AIAA 78-1286] A78-50193

A-20 SUBJECT IHDEI FLIGHT TESTS

A learning flight control system for the F8-DFBS Piloted flight simulation for active control aircraft Digital Fly-By-Wire design development [AIAA 78-1288] A78-50195 [AIAA PAPEB 78-1553] A78-l(9771 Characteristics of constrained optimun V/STOL aircraft simulation -fiegnireraent san d trajectories with specified range capabilities at Ames Besearch Center [BASA-TH-78519] 1178-30072 [AIAA PAPEB 78-1515] A78-Q9790 Application techniques for digital flight control Subsystem verification of an AFLC organically systems developed P-15 simulation Air Force H78-30117 Logistics Command A pyramid skewed axis sensor set for maltiplex A78-U9901 flight control systems A flight simulation high order language study [ABC-B/H-3808] »78-301t3 A78-l(9957 A modular adaptive, variable function flight Flight investigation and theory of direct control sensor side-force control rAD-A055175] N78-31120 [AIAA 78-1287] A78-50193 The terrain following task for the advanced Approach guidance logic for a tilt-rotor aircraft tactical fighter using discrete optinal control [AIAA 78-1295] A78-50202 [AD-A055196] N78-31121 Simulation study of the oscillatory longitudinal Optimal terrain following controller for an motion of an airplane at the stall optimized spline reference path [SASA-TP-12K2] N78-3011(1 [AD-A055234] N78-31122 Compilation of test data from an investigation on The influence of throttle augmented stability the effect of environment on crack growth under (APCS) and short period control characteristics flight-simulation loading on the landing approach [NLR-TB-76096-0] N78-30620 [AD-A055892] H78-31123 Simulation and flight evaluation of a head-up Inherent errors in asynchronous digital flight landing aid for general aviation controls [NASA-TP-1276] H78-31101 fAD-A055649] N78-3112U Software design for a Visually-Coupled Airborne PLIGHT HiZABDS Systems Simulator (VC«SS) The airborne detection of low-level wind shear [AD-A055226] H78-31133 [AIAA PAPER 78-1495] A78-U7936 FLIGHT SIHOLATOBS FLIGHT IHSTBDHEHTS Air-to-air combat simulation Flight deck display trends A78-47868 A78-1(7899 V/STOL aircraft simulation - Reguirements and Aviation control system devices Russian book capabilities at Ames Besearch Center A78-U9850 [AIJA PAPEB 78-1515] A78-U9790 A modular adaptive, variable function flight Evaluation of several secondary tasks in the control sensor determination of permissible time delays in [AD-A055175] N78-31120 simulator visual and motion cues FLIGHT QPEBATIOHS [HASA-TP-1214 ] N78-30089 Approach for identifying avionics flight software Simulator study of the effect of visual-motion operational support regairements - PAVE TACK an time delays on pilot tracking performance with example an audio side task A78-I19900 [HASA-TP-1216] N78-30090 FLIGHT OPTIBIZATIOH Software design for a Visually-Coupled Airborne Trajectory optimization for some sailplane Systems Simulator (VCASS) performance problems [1D-A055226] B78-31133 H78-31083 Experimental test plan for the evaluation of FLIGHT PATHS aircraft separation assurance displays using A method for determining the stability airline flight simulators characteristics of aircraft in a helicoid flight [AD-A0558K9] N78-3113U path FLIGHT TEST VEHICLES A78-K9741 Drones for aerodynamic and structural testing Optimal terrain following controller for an /DAST/ - A status report optimized spline reference path [AIAA PAPEB 78-1H85] A78-U7929 [AD-A0552314] S78-31122 FLIGHT TESTS FLIGHT BLAHS Flight application of optical fiber transmission IFB aircraft handled forecast by air route traffic on a Falcon 10 aircraft control center, fiscal years 1978-1989 [OSEBA, TP NO. 1978-105] A78-K731(9 [AD-AOU9305] 1178-31075 B-1 flight test progress report FLIGHT RECORDERS [AIAA PAPEB 78-1U118] A78-U7903 L-1011 flight data recording systems - Background, Integrated test mission control - Present and features, implications and benefits future at the Air Force Flight Test Center [AIAA PAPEB 78-11(71] A78-t[7917 [AIAA PAPEB 78-11(61] A78-K7911 Non-volatile memory system for severe environment flse of onboard computerized flight test analysis flight recorders systems A78-H9872 [AIAA PAPEB 78-1M62] A78-U7912 Preliminary design of an accident Information Software engineering a must for success in Betrieval System (AIBS) computerized flight test [AD-A055590] N78-31952 [AIAA PAPEB 78-11)63] 178-1(7913 FLIGHT SAFETT The role of the computer in the flight testing of Flutter suppressor for transonic flight general aviation aircraft [OBEBA, TP NO. 1978-102] A78-1I73146 [AIAA PAPEB 78-11(65] A78-l(791t( AIDS m engine management programmes Airborne Wind Tunnel/Flight Test Correlation Program on the Integrated Data Systems B-1 nacelle afterbody/nozzle at transonic A78-K7865 conditions Safety of space flights [AIAA PAPER 78-989] A78-l(81(69 J78-U7952 Non-axisymmetric nozzle design and evaluation for Distribution of reliability characteristics among F-111 flight demonstration airplane system units to ensure given flight [AIAA PAPEB 78-1025] A78-M8C83 safety level Havstar GPS field test results A78-48221 A78-i)9856 FLIGHT SIHOL1TIOH Digital simulation and flight verification of the Bamjet engine testing and simulation technigues F-5E/F Flight Director Computer [AIAA PAPEB 78-935] A78-»8K55 A78-K9905 Important simulation parameters for the Flight measurements of the effects of simulated experimental testing of propulsion induced lift leading-edge erosion on helicopter blade stall, effects torsional loads and performance [AIAA PAPEB 78-1078] A78-Q8I(9(( [ABC-R/B-3809] N78-30098

A-21 FLIGHT TB&ISIHG SUBJECT IBDEI

Compilation of test data from an investigation on FLT BI VIBE COHIBOL the effect of environment on crack growth under In-line monitoring of digital flight control flight-simulation loading computers [HLB-TB-76096-U] H78-30620 A78-19860 TPSB microwave landing system demonstration Laboratory testing of lightning and EBP program at Kristiansand, Norway susceptibility of avionic systems [AD-J055317] N78-31071 A78-49861 TRSB microwave landing system demonstration Software development for fly-by-wire flight program at Charleroi, Belgium control systems [AD-A055920] N78-31072 [AIAA 78-1276] A78-50185 1PC design validation and flight testing Improved combat survivability for fly-by-wire [AD-A055529;) H78-3107U sensor systems FLIGHT TRAINING [AIAA 78-1277] A78-50186 Pntitorgue training: Evaluation of effectiveness Triplex digital fly-by-wire redundancy management in reducing mishap losses techniques [AD-J0550<(0] N78-31092 [AIAA 78-1279] A78-50187 FLIGHT VEHICLES A learning flight control system for the F8-DFBB Optimization techniques for air traffic control aircraft Digital Fly-By-Wire problems Bossian book [AIAA 78-1288] A78-50195 A78-08501) The terrain following task for the advanced FLIB DETECTORS tactical fighter using discrete optimal control Autothreshold autoscreener/FLIB system [AD-A05S196] N78-31121 airborne target screener/Forward-Looking FOCOSIRG Infrared imaging system Long-distance focusing of Concorde sonic boon A78-«998i| A78-08052 FLOS CHAB1CTBBISTICS FOBECiSTISG Calculation of the longitudinal aerodynamic IFB aircraft handled forecast by air route traffic characteristics of upper-surface-blown wing-flap control center, fiscal years 1978-1989 configurations [AD-A049305] N78-31075 [IASa-CB-3004] N78-30050 FOBGISG FLOi DISTOBTION Design philosophy for engine forgings F-'5 inlet/engine test technigues and distortion A78-07152 methodologies studies. Volume 1: Technical Design philosophy for airframes discussion A78-U7U53 CNASA-CB-1i(i)866] H78-30123 FBACTDBE HECBANICS F-15 inlet/engine test techniques and distortion Minimum weight design of stiffened panels with methodologies studies. Volume 3: Power fracture constraints spectral density plots A78-<49837 [NASA-CB-1011868] N78-30125 Mechanisms of fatigue and fracture F-15 inlet/engine test technigues and distortion N78-30273 methodologies studies. Volume U: Fracture mechanics fundamentals with reference to futocorrelation functions aircraft structural applications [NASA-CB-11«869] 1178-30126 H78-3027II F-15 inlet/engine test techniques and distortion Recent developments in analysis of crack methodologies studies. Volume 5: Effect of propagation and fracture of practical materials filter cutoff frequency on turbulence plots stress analysis in aircraft structures [NASA-CR-110870] N78-30127 [NASA-TH-78766] N78-30606 F-15 inlet/engine test techniques and distortion FBACTOBE STBEHGTB methodologies studies. Volume 6: Distortion Engineering data on new aerospace materials analysis plots structural materials [NASA-CE-14U871] N78-30128 [AD-A05it061] S78-30213 F-15 inlet/engine test techniques and distortion FBEE FALL methodologies studies. Volume 7: Cross Operator work capacity during parachutist free-fall correlation functions. A78-U7978 [NASA-CR-111872] N78-30129 FBEE VIBBATIOH F-15 inlet/engine test techniques and distortion The influence of high twist on the dynamics of methodologies studies. Volume 8: Cross rotating blades spectral density plots A78-U7599 [NASA-CB-1«l|873] 878-30130 FBEQOEHCY DISTBIBOTION F-15 inlet engine test technigues and distortion F-15 inlet/engine test techniques and distortion methodologies studies. Volume 9: Stability methodologies studies. Volume 5: Effect of audits filter cutoff frequency on turbulence plots [NASA-CB-1l4l|87(t] N78-30131 [NASA-CR-11

A-22 SUBJECT INDZI GRODBD TESTS

FUEL GAGES Some sound transmission loss characteristics of Solid-state displays for fuel management systems typical general aviation structural materials for aircraft [AIAA PAPEB 78-1180] A78-17925 178-17900 Integrated avionics for future general aviation FUEL TANKS aircraft Investigation of electrostatic discharge in [AIAA PAPER 78-1182] A78-17927 aircraft fnel tanks during refueling Phase-locked tracking loops for LOPAF-C [AIAA PfPEB 78-1501] A78-17911 [BASA-CH-157582] B78-31068 Fundamentals of noncaring sealants for aircraft General aviation airplane structural fuel tanks crashworthiness user's manual. Volume 1: [AD-A051627] N78-30217 Program KRASH theory FUSBL4GES [AD-A055898] B78-31088 Saperelement method for helicopter fuselage analysis Simulation and flight evaluation of a head-up A78-18209 landing aid for general aviation Definition of airplane faselage longitudinal lines [BASA-TP-1276] N78-31101 by the spectal contour method A research program to reduce interior noise in A78-48222 general aviation airplanes: noise reduction Fatigue crack growth in pressurized fuselage panel through a cavity-backed flexible plate A78-18231 [NASA-CB-157588] B78-31873 F»-12t AIBCB&FT A research program to reduce interior noise in Jn analytical and experimental investigation of general aviation airplanes: Investigation of diffnsers for VSTOL thrust augmenting ejectors the characteristics of an acoustic panel test PAPEB 78-1509] 478-079115 facility fHASA-CB-157587] H78-31871 GLIDE PATHS Capture effect array glide slope guidance study GAS ANALYSIS [AD-A055678] B78-31073 A preliminary comparison of thermal decomposition GLIDEBS products of aircraft interior materials using Trajectory optimization for some sailplane the National Bureau of Standards smoke chamber performance problems and the combustion tube furnace H78-31083 tAD-A054811] N78-30088 GLOBAL POSITIONING SYSTEH GAS GEHEBATOBS Bavstar GPS field test results Flame stabilization in a ramjet combustion chamber A78-19856 by means of a pilot gas generator Comparisons of high anti-jam design techniques for tDLB-FB-77-51] N78-31117 GPS receivers Global Positioning System GAS TUBBINE ENGINES A78-19857 Operation of oil scales of aircraft piston engines A Costas loop with tangent error signal for use in under conditions of cavitation. I Bavstar GPS avionics A78-17175 A78-19858 Engine vibration in flight \ compensation technique for acceleration-induced CAIAA PAPEB 78-1075] A78-17921 frequency changes in crystal oscillators Analysis of GTE tolerance monitoring parameter A78-19859 formation gas turbine engine Accuracy requirement and cost effectiveness of A78-18212 GPS-aided ISS for tactical fighters Aspects of the thermal fatigue strength of A78-19989 gas-turbine engine components G07EBNBENT PBOCdBEHEBT A78-1I9176 Aeronautical procurement - The primary Gas turbine engine emissions - Problems, progress specification system and future [AIJA PAPER 78-1189] A78-17932 A78-19336 GRAVITATIONAL EFFECTS Computer program for the design and off-design Constant-control rolling maneuver performance of turbojet and turbofan engine cycles A78-16961 [BASA-TB-78653] H78-30122 GBOUND BASED CONTBOL A theoretical study of the performance of a number The HiHAT BPBT system of different anal-flow turbine configurations [AIAA PAPER 78-1157] A78-17908 under conditions of pulsating flow Capture effect array glide slope guidance study tARL/HECH-ENG-BEPT-119] H78-31101 [AD-A055678] N78-31073 Rotor burst protection program: Statistics on GROOHD EFFECT (AEBODYNAHICS) aircraft gas turbine engine rotor failures that Conceptual design study of power augmented ram occurred in OS commercial aviation during 1975 wing in ground effect aircraft [BASA-CB-135301] B78-31105 [AIAA PAPER 78-1166] A78-17915 Advanced optical blade tip clearance measurement Experimental determination of propulsion induced system ground effects of typical three fan type A [BASA-CB-159102] N78-31106 V/STOL configurations GAS TOBBIBES [AIAA PAPER 78-1507] A78-17913 Application of electrical analogy to the nodeling ground plane influence on wing substantiation and comparison of some analytical aerodynamic characteristics using a finite plane methods of determining temperature fields in screen gas-turbine blades A78-18216 A78-17101 Asymptotic theory of a wing moving near a solid wall Turbine engine rotordynamic evaluation, volume 1 A78-18218 [AD-A055262] N78-31111 Important simulation parameters for the GENERAL AVIATIOB AIRCRAFT experimental testing of propulsion induced lift From Challenger to winner Canadair executive effects jet design and development [AIAA PAPER 78-1078] A78-18191 A78-17570 Ground effects testing of two, three, and four jet The role of the computer in the flight testing of configurations general aviation aircraft [AIAA PAPEB 78-1510] A78-19789 [AIAA PAPEB 78-1165] A78-17911 GBOOHD STATIONS Correlation of model and airplane spin IPB aircraft handled forecast by air route traffic characteristics for a low-wing general aviation control center, fiscal years 1978-1989 research airplane [AD-AOH9305] H78-31075 [AIAA PAPEB 78-1177] A78-17922 GBOOHD TESTS Whitcomb winglet applications to general aviation Ground test facility for integral rocket ramjets aircraft [AIAA PAPEB 78-931] A78-18151 [AIAA PAPEB 78-1178] A78-17923

A-23 GUIDANCE SENSORS SUBJECT INDEX

Important simulation parameters for the A study of the precision hover capabilities of the experimental testing of propulsion induced lift aerocrane hybrid heavy lift vehicles effects [AD-A054281] B78-30091 [ilAA PIPES 78-1078] A78-H8it9it Helicopter transmission vibration and noise Dse of ground vibration test equipment to reduction program. Volume 2: User's manual determine unsteady aerodynamic forces [AD-A051827] H78-30095 A78-U9708 Structural dynamics, stability, and control of GUIDANCE SENSORS helicopters Strapdown seeker guidance for tactical weapons CHASA-CB-158909] 1178-30139 A78-49928 Helicopter transmission vibration and noise Multi-Function Inertial Reference Assembly /HIBA/ reduction program. Volume 1t Technical report update digital aircraft systems [AD-A055104] N78-31089 A78-199H1 HELIPORTS GOBS (OBDNASCE) A systems approach to heliport lighting Hazard assessment of aircraft gun compartments A78-U9238 [AD-A055026] H78-31061 HEBHITIAH POLYNOHIAL GDST LOADS Hermite closed splines On the linear superposition of aerodynamic forces J78-U9713 on vings in periodic gusts HIGH ALTITUDE BALLOONS A78-H7869 Aerodynamic hull design for HASPA LTA optimization Experimental investigation of gust response of High Altitude Superpressure Powered Aerostat hingeless helicopter rotors Lighter Than Air rAD-A0547521 N78-30112 A78-U8100 Gust measurements and the N sub o problem HIGH ASPECT RATIO S78-30276 Control-surface hinge-moment calculations for a GTBOSCOPES high-aspect-ratio supercritical wing 1 pyramid skewed axis sensor set for multiplex [SASA-TH-78661] N78-31013 flight control systems HIGH GBAVITI BHVIROHBENTS [ARC-B/B-3808] H78-301U3 The design of a high g cockpit H78-30118 HIGH STRENGTH STEELS H Extending the service life of aircraft components HEAD-tJP DISPLAYS made of high-strength steels Bussian book Improving the accuracy of HOD approaches in A78-18518 windshear with a new control law HIGH TEBPEBATDBE [AIAA PAPEB 78-11914] A78-Q7935 Calculation of exchange coefficients for Simulation and flight evaluation of a head-up high-temperature turbine blades landing aid for general aviation [OUEBA, IP NO. 1978-101] A78-U7318 [NASA-TP-1276] N78-31101 HOLOGRAPHI HEAT TBANSFEB HHSD demonstration model development Application of electrical analogy to the [AD-A054437] N78-30120 substantiation and comparison of some analytical HOBIZONTAL TAIL SURFACES methods of determining temperature fields in Design of a horizontal tail unit and related gas-turbine blades adjustments A78-U9736 HBLICOPTEB CONTROL HOVERING Design and development of a multifunctional A study of the precision hover capabilities of the helicopter control system aerocrane hybrid heavy lift vehicles A78-U9396 [AD-A054281] N78-30091 Flight controls of Army/Hughes YAH-64 advanced HULLS (STRUCTURES) attack helicopter Aerodynamic hull design for HASPi LTA optimization TAIAf 78-12371 A78-50160 High Altitude Superpressure Powered Aerostat Shipboard launch and recovery of BPV helicopters Lighter Than Air in high sea states A78-118100 [AIAA 78-1269] A78-50179 HDHAN FACTORS ENGINEERING HELICOPTER DESIGN Bodel of aircraft passenger acceptance Superelement method for helicopter fuselage analysis A78-19681 A78-18209 RDHAN PEBFOBBANCE Plight controls of Army/Hughes YAH-6<4 advanced Operator work capacity during parachutist free-fall attack helicopter A78-17978 fAIAA 78-1237] i78-50160 BOBAS BEACIIOBS HELICOPTER EHGINES Bide guality evaluation. IV - Models of subjective Engine/airf rame/drive train dynamic interface reaction to aircraft motion documentation A78-47190 [AD-A055766] H78-3111S Hodel of aircraft passenger acceptance HELICOPTEB PEBFOBBANCE A78-<19681 A systems approach to heliport lighting Beguirements for regional short-haul air service A78-119238 and the definition of a flight program to LOGBOD - The fault-isolator --- for helicopter determine neighborhood reactions to small electronic systems transport aircraft A78-H9239 [NASA-CB-152151] N78-30070 Stability of a helicopter carrying an underslung A further survey of some effects of aircraft noise load in residential communities near London A78-1I9398 (Heathrow) airport Flight measurements of the effects of simulated [TT-7705] K78-30910 leading-edge erosion on helicopter blade stall, HYDROCARBON FOELS torsional loads and performance Effect of jet fuel antooxidation products on [ABC-B/H-3809] B78-30098 thermooxidation stability Evaluation of a circulation control tail boom for A78-1)9025 yaw control --- OH-6 helicopter HYPERSONIC AIRCRAFT [AD-A055116] B78-31119 Aerodynamic characteristics of a hypersonic BELICOPTEBS research airplane concept having a 70 deg swept leasurement of vibratory displacements of a double-delta wing at Bach number 0.2 rotating blade [NASA-TP-1252] N78-31015 A78-U9397 HYPERSONIC FLOW Helicopter rotor vibration isolation Unsteady hypersonic gas flow past a thin wing of A78-U9399 finite span A78-U9792

A-2Q SUBJECT IBDBX JABBEBS

IBFBABED DETECTOBS Infrared receiver performance airborne warning system by detection of target spectral signature ICE FOBBATIOB 178-19985 Modified helicopter icing spray system evaluation IBFBABED IBICES! [AD-A055039] N78-31091 Antothreshold autoscreener/FLIB system IH1GE COBBELATOBS airborne target screener/Forward-Looking Advanced pattern matching for navigation and Infrared imaging system guidance A78-1998H A78-49998 IBPBASOHIC FBEQOBHCIES IBAGE BBBAHCEHEHT Long-distance focusing of Concorde sonic boom Pattern recognition as an aid to radar navigation A78-18052 A78-I19855 INBOHOGENEITT IBASE PBOCESSIHG Theoretical and experimental studies of acoustic Pattern recognition as an aid to radar navigation propagation in inhomogeneous moving media A78-19855 [ESA-TT-177] N78-30909 High-accnracy three-diaensional image ISPOI/OOTPOt BODTINBS reconstruction for an airborne line-scanning A standard programmable I/O for the advanced system aircraft electrical systen power control set A78-19988 A78-U9936 IBA6ING TECBNIQ0ES BEXOB 2 rotorcraft simulation model. Volume 3: A flight gnalified graphics generator for B-1 User's manual defense system [HASA-CB-115333] N78-30011 A78-S0007 IHSBCTS IHPINGEBENT Flight experience on the need and use of inflight Gronnd impingement of a fan jet exhaust plume leading edge washing for a laminar flow airfoil [AD-A051832] N78-31112 [AIAA PAPEB 78-1512] A78-17917 IH-FLIGHT BOHITOBIHG INSTBUHENT CORPENSATION Integrated test mission control - Present and a compensation technigue for acceleration-induced future at the Air Force Flight Test Center frequency changes in crystal oscillators [AIAA PAPEH 78-1fl61] A78-17911 A78-19859 Use of onboard computerized flight test analysis IBSTBOBEB? BBBOBS systems Accuracy requirement and cost effectiveness of [AIAA PAPEB 78-1162] A78-17912 GPS-aided INS for tactical fighters Software engineering a oust for success in A78-19989 computerized flight test IISTBDBENT FLIGBT BDLES [AIAA PAPEB 78-1163] A78-17913 IFB aircraft handled forecast by air route traffic 1-1011 flight data recording systems - Background, control center, fiscal years 1978-1989 features, implications and benefits [AD-A019305] N78-31075 [AIAA PAPES 78-1171] A78-17917 USTHOBENT LANDING SYSTEMS TF11-A-2/A7E inflight engine condition monitoring Probabilistic model of an instrument landing system systen /IECHS/ A78-17107 [AIAA PAPEB 78-1172] A78-17918 TBSB microwave landing system demonstration Sensor technology for turbine engine monitoring program at Brussels, Belgium systems [AD-A05H298] N78-30075 [AIAA PAPEB 78-1171] A78-U7920 TBACALS evaluation report. TACAN, VOB, and ILS Engine vibration in flight station evaluation report, Andersen AFB, Guam [AIAA PAPEF 78-1175] A78-17921 [AD-A051211] N78-30078 In-line monitoring of digital flight control Capture effect array glide slope guidance study computers [AD-A055678] N78-31073 A78-19860 INTAKE SISTEBS Comparison monitoring in redundant digital flight Investigation of electrostatic discharge in control systems aircraft fuel tanks during refueling A78-U9865 [AIAA PAPEB 78-1501] A78-179U1 Electromagnetic coupling analysis of a Learjet Performance with and without inlet radial aircraft in a lightning environment distortion of a transonic fan stage designed for A78-19920 reduced loading in the tip region IHCOBPEESSIB1E FLOH [NASA-TP-1291] N78-30057 Approximate indicial lift function for tapered, F-*5 inlet/engine test techniques and distortion svept vings in incompressible flow methodologies studies. Volume 8: Cross [HASA-TP-1211] N78-30051 spectral density plots IHDOCTIOH BOTOBS [NASA-CB-111873] N78-30130 Test and demonstration prototype tracked air IITEBFEBERCE cushion vehicle (PTACV): Phase IIIC Investigation of a wing-rotor interaction system [PB-279970/8] N78-31007 for helicopters INEBTIAL GUIDANCE [AD-A051093] N78-30092 BNAV - Corporate operators set the pace INTERNATIONAL COOPEBATION A78-17121 Airliner numbers game - Does it add up IHEBTIAI HA7IGATIOS political and technological aspects of Advances in inertial navigation international aircraft industries A78-17181 A78-19521 Beal-time simulators for augmented inertial INVENTIONS navigation systems Gas path seal A78-19967 [NASA-CASE-LED-12131-2] N78-31103 Beliability of inertial navigation systems for IOHOSPHEBIC PBOPAGATION military and commercial aircraft Station deselection procedures to support A78-19968 automatic Omega receiver operation Accuracy requirement and cost effectiveness of A78-19965 GPS-aided INS for tactical fighters A78-H9989 IBFOBBATIOH FLOW An interface management approach to software JABBEBS development Comparisons of high anti-jam design techniques for A78-09933 GPS receivers Global Positioning System IHFOBHATION BETBIBVAL A78-U98S7 Preliminary design of an accident Information Digital systen architecture for a 1980"s jammer Betrieval System (AIBS) for military aircraft and ships [AD-A055590] N78-31952 A78-19973

i-25 SDBJECT IHDEI

JABHING LANDING GEAR Performance in a jamming environment of a low-cost Improved aircraft dynamic response and fatigue GPS user receiver algorithm for aiding a life during ground operations using an active tactical IMS control landing gear system [AD-A055239] N78-31078 [AIAA PAPER 78-1499] A78-17939 JET AIBCBAFT LAHDISG INSTHOBENTS From Challenger to winner Canadair executive Probabilistic model of an instrument landing system jet design ana development A78-117107 A78-K7570 Dse of the U.S. interim standard microwave landing JET AIECBAFT HOISE system in Canada in acoustic range for the measurement of the noise A78-49333 signature of aircraft during flyby operations LASER APPLICATIONS A78-47242 A laser-powered flight transportation system Theoretical and experimental studies of acoustic [AIAA PAPEB 78-148U] A78-49781 propagation in inhomogeneous moving media LASEB GDIDANCE [ESA-TT-477] S78-30909 Performance of a differential Omega-ring laser JET ENGINE FOELS strapdown aircraft navigator Let's put fuel efficiency into perspective A78-49966 A78-47269 LASEB EANGER/TBACKEE Effect of jet fuel autooxidation products on Navstar GPS field test results thermooxidation stability A78-U9856 J78-49025 LATERAL COBTBOL JET ENGINES Boiling tail design and behavior as affected by Design philosophy for engine forgings actuator hinge moment limits for B-1 A78-47452 maneuverability Detecting abnormal turbine engine deterioration [AIAA PAPEB 78-1500] A78-47940 using electrostatic methods LATERAL STABILITY fAIAA PAPEE 78-1473] A78-H7919 Constant-control rolling maneuver Sensor technology for turbine engine monitoring A78-46961 systems Evolution of a cost-effective, task-oriented, TAIAA PAPEB 78-1474] H78-47920 lateral-directional SAS for the A-10 aircraft flternatives for jet engine control Stability Augmentation System [NJSA-CB-157578] N78-31107 [AIAA PAPEB 78-1460] A78-47910 Status of the Air Force's F-16 aircraft program Lateral-aerodynamic characteristics of [PB-280304/7] H78-31946 highly-dihedraled wings JET NOZZLES A78-49334 Vectoring non-axisynmetnc nozzle jet induced Analysis of stability contributions of high effects on a V/STOL fighter model dihedral V-tails CAIAA PAPER 78-1080] A78-48496 [NASA-TU-78729] N78-31044 JP-5 JET FUEL LEADING EDGES Effects of high availability fuels on combustor Flight experience on the need and use of inflight properties leading edge washing for a laminar flow airfoil [AD-A054229] H78-30259 [AIAA PAPEB 78-1512] A78-47947 A method for localizing wing flow separation at stall to alleviate spin entry tendencies K [AIAA PAPEB 78-1476] A78-49787 KALHAB FItTEBS Calculations of the effects of bloving from the Assessment of dynamic coordinate alignment for leading edges of a cambered delta wing elastic aircraft flight control Kalnan [ARC-R/B-3800] N78-30064 filter estimates Flight measurements of the effects of simulated A78-U9987 leading-edge erosion on helicopter blade stall, Performance of a ring laser strapdovn attitude and torsional loads and performance heading reference for aircraft [ARC-B/H-3809] N78-30098 [AIAA 78-121(0] A78-50162 LEAB JET AIRCRAFT Optimal terrain-aided navigation systems Gates Learjet Bodel 28/29, the first 'Longhorn' [AIAA 78-1243] A78-50163 Learjet [AIAA PAPEB 78-1445] A78-47901 Electromagnetic coupling analysis of a Learjet aircraft in a lightning environment L-1011 4IBCHAFT A78-49920 L-1011 flight data recording systems - Background, LIFE CYCLE COSTS features, implications and benefits Estimated costs of extended low-rate airframe [AIAA PAPEB 78-1471] A78-47917 production LAHIBAR FLOB [AD-A054834] N78-31100 Flight experience on the need and use of inflight LIFT leading edge washing for a laminar flow airfoil Important simulation parameters for the [AIAA PAPER 78-1512] A78-47947 experimental testing of propulsion induced lift Design of a large span-distributed load effects flying-wing cargo airplane with laminar flow [AIAA PAPER 78-1078] A78-48494 control Shockless airfoils with thicknesses of 20.6 and [NASA-CR-145376] H78-30045 20.7 percent chord analytically designed for a LARDING AIDS Bach number of 0.68 and a lift coefficient of 0.40 A systems approach to heliport lighting [NASA-TB-X-73917] N78-30046 A78-49238 Approximate indicial lift function for tapered, Navigation performance of the Triscan concept for swept wings in incompressible flow shipboard VTOL aircraft operations [HASA-TP-1241] N78-30054 [AIAA 78-1293] f78-50200 Investigation of a wing-rotor interaction system Description and performance of the Langley visual for helicopters landing display system [AD-A054093] N78-30092 [NASA-m-78712] S78-30073 LIFT AOGBBNT1TION Simulation and flight evaluation of a head-up fn analytical and experimental investigation of landing aid for general aviation diffusers for VSTOL thrust augmenting ejectors [BASA-TP-1276] N78-31101 [AIAA PAPEB 78-1509] A78-47945 Parameters of future ATC systems relating to LIFTING BODIES airport capacity/delay Asymptotic theory of a wing moving near a solid wall [AD-A055482] S78-31130 A78-48248

A-26 SUBJECT IBDEX HATBEBATICAL 80DE1S

Bodification of the Douglas Bennann program to Bodification of the Douglas Benmann program to improve the efficiency of predicting component improve the efficiency of predicting component interference and high lift characteristics interference and high lift characteristics [HASA-CB-3020] N78-30051 [BASA-CB-3020] B78-30051 LIGHT AIBCB4FT LO1 ilBG AIBCBAFT Large deflection static analysis of typical Correlation of model and airplane spin tail-wheel structure of light aircraft by finite characteristics for a low-wing general aviation element method research airplane 178-48861 [AIAA PAPEB 78-1477] A78-47922 A method for localizing wing flow separation at stall to alleviate spin entry tendencies [AIAA PAPER 78-11761 A78-19787 M LIGHTING BQOIPHBNT BACH 1UHBEB f systems approach to heliport lighting Shockless airfoils with thicknesses of 20.6 and A78-19238 20.7 percent chord analytically designed for a LIGHTBIBG Bach number of 0.68 and a lift coefficient of 0.40 Laboratory testing of lightning and EBP [BASA-TB-I-73917] B78-30046 sasceptibility of avionic systems Stability and performance characteristics of a A78-19861 fixed arrow wing supersonic transport Electromagnetic conpling analysis of a Learjet configuration (SCAT 15F-9898) at Bach numbers aircraft in a lightning environment from 0.60 to 1.20 A78-19920 [BASA-TH-78726] H78-30087 LIHE OF SIGHT COBSOBICATIOB BAGBETIC COHTBOL Fading at 9.6 GHz on an experimentally simulated Guidance and navigation for automatic landing, aircraft-to-ground path rollout, and tnrnoff using BLS and magnetic A78-19039 cable sensors LIHEAB STSTEHS [AIAA 78-1296] A78-50203 Guaranteed cost control of linear systems with RAGNETS uncertain parameters - Application to remotely Application of rare earth/transition metal piloted vehicle flight control systems permanent magnets to 400 Hz aircraft systems - [AIAA 78-1274] A78-50184 An AF overview LINEARIZATION A78-49935 Linearized theory of plane, unsteady, supersonic HALFOBCTIOBS flow through a cascade - Subsonic part of the LOGBOD - The fault-isolator for helicopter leading edge electronic systems [OHEBA, TP NO. 1978-103] A78-47347 478-49239 LIQUID HTDEOGEB HAS BACBISE STSTEHS Study of fnel systems for LH2-fueled subsonic A hierarchical network for avionic systems transport aircraft, volnme 1 A78-19868 [NASA-CR-145369-VOL-1] 878-31085 An investigation of potential control-display Study of fuel systems for LH2-fueled subsonic configurations for V/STOL aircraft transport aircraft, volume 2 [AIAA 78-1238] A78-50161 [BASA-CB-145369-VOL-2] R78-31086 HAHAGEHBNt STSTEBS LOAD TESTS AIDS in engine management programmes Airborne proposed load evaluation system for O.S. Air Force Integrated Data Systems of airfield pavement A78-17865 A78-49677 BAHEOVEBABILITI Airfield pavement evaluation - The airline view Supercruiser fighter analysis A78-19680 B78-30107 LOADS (FOBCBS) Analysis of advanced variable camber concepts Development of a load sequence for a structural H78-30108 fatigue test BAP BATCBIHG GUIDANCE H78-30277 A parametric analysis of TEBCOB false fix Load interaction effects in fatigue crack probability TEBrain contour Batching propagation A78-U9997 178-30285 Advanced pattern matching for navigation and LOGIC CIHCDITS guidance LOGBOD - The fault-isolator for helicopter A78-49998 electronic systems BAPS A78-49239 COBED - The cockpit display of the future LOGISTICS BABAGBBEBT combined Bap and Electronic Display Digital avionics support - A retrospective view of A78-47268 the future HABIBE EBVIBOBBESTS A78-49903 Constant false alarm rate detector for a pnlse The feasibility of estimating avionics support radar in a maritime environment costs early in the acquisition cycle. Volnme 1: A78-49975 The basic report HABKOV CHAIRS [AD-A051016] B78-30119 Probabilistic model of an instrument landing system LOHGITODIBAL STABILITY A78-47407 Dynamics of the longitudinal motion of an airplane BiTHEBATICAL BODELS with a variable-geometry wing Probabilistic model of an instrument landing system A78-19285 A78-47407 Calculation of the longitudinal aerodynamic Bide quality evaluation. IV - Bodels of subjective characteristics of npper-snrface-blown wing-flap reaction to aircraft motion configurations A78-47490 [HASA-CK-3004] B78-30050 On the theory of drag calculation and profile Simulation study of the oscillatory longitudinal optimization in Shockless near free molecular flow motion of an airplane at the stall A78-47887 [HASA-TP-1242] N78-30141 Experimental determination of parameters of LOBAB C mathematical model of airplane cabin as Phase-locked tracking loops for LORAK-C regulated object with respect to air temperature [BASA-CB-157582] B78-31068 in the cabin LOR SPEED A78-48234 Section drag coefficients from pressure probe Bodeling refinements for the rectified traverses of a wing wake at low speeds superconducting alternator airborne power C&IAA PAPEB 78-1479] 178-47924 supply A78-49961

S-27 BAXIBOB LIKELIHOOD ESTIBiTES SUBJECT IHDBX

Demand modelling of passenger air travel: An TESB microwave landing system demonstration analysis and extension, volume 2 program at Brussels, Belgian [NASA-CB-157102] B78-30069 [AD-A051298] B78-30075 Structural dynamics, stability, and control of TBSB microwave landing system demonstration helicopters program at John F. Kennedy International [BASA-CB-158909] S78-30139 Airport, Long Island, New York, OSA Procednres for generation and redaction of linear [AD-A0551»7] S78-31070 models of a turbofan engine TBSB microwave landing system demonstration [NASA-TP-1261] 1178-30896 program at Kristiansand, Norway BAIIBDB LIKELIHOOD ESTIBATES [AD-A055317] N78-31071 Maximum likelihood identification of the TBSB microwave landing system demonstration longitudinal aerodynamic coefficients of the program at Charleroi, Belgium EA-6B airplane in the catapult launch [AD-A055920] H78-31072 configuration BICBOIAVE SEHSOBS [JD-A051213] N78-31016 Scan-limited near field testing for directive HEASOBIHG IHSTBtJBBHTS airborne antennas Turbine tip clearance measurement A78-I49897 [AD-A055765] N78-31115 BICBOBAVE TBAHSBISSIOH A research program to reduce interior noise in Fading at 9.6 GHz on an experimentally simulated general aviation airplanes: Investigation of aircraft-to-ground path the characteristics of an acoustic panel test 478-19139 facility BILITABY AIE FACILITIES [NASA-CE-157587] H78-31874 AFAL simulation facility/capability manual. BECHAHICAL DBITES Volnme 1: Executive summary and Systems Engine/airframe/drive train dynamic interface Avionics Division documentation [4D-4055591] H78-31102 [AD-A055766] B78-31111 BILITABY AIBCBAFT BECHAHICAL EHGIHEEBIBG AIDS in military aircraft Airborne Integrated Botor design implications for composite material Data Systems Computer properties A78-U7866 [DCHL-80117] B78-30182 Integrated test mission control - Present and HET&L BOBDIHG future at the Air Force Flight Test Center The influence of the environment on the [AIAA PAPEB 78-1161] A78-17911 elastoplastic properties of adhesives in metal Prospects for commercial commonality in military bonded joints in aircraft structures transports [DLB-FB-77-63] B78-31251 [AIAA PAPEB 78-1167] A78-19781 BET1L COATINGS Bing planforms for large military transports Extending the service life of aircraft components [AIAA PAPEB 78-1170] A78-19786 made of high-strength steels Russian book The 4S/API-100/V/ transponder for military A78-H8518 aircraft BICBOHIHIATUSIZED ELECTRONIC DEVICES A78-19971 The 4H/JPX-100/V/ transponder for military Technical evaluation of flying weapon systems aircraft [BAE-LIB-TBANS-19II8] N78-31087 A78-19971 BIHTABY A7IATIOB BICBOPBOCESSORS Proposed load evaluation system for U.S. Air Force Software engineering a must for success in of airfield pavement computerized flight test A78-19677 [AIAA PAPEB 78-1163] A78-M7913 BIL-STD-1553B proposed data bus development in Multiprocessing for electronic warfare avionics avionic architecture A78-19869 A78-19866 Non-volatile memory system for severe environment Status of the Air Force's F-16 aircraft program flight recorders [PB-28030U/7] B78-31916 478-19872 BILITABY HELICOPTERS The evolution of a remotely piloted vehicle Preliminary design of an accident Information microprocessor flight control system Betrieval System (AIBS) [AIAA 78-1273] 578-50183 [AD-A055590] B78-31952 BICBOSTSIP TBAHSIISSIOB LIHES BILITABY OPEBATIOBS Conformal microstrip phased array for aircraft Shipboard launch and recovery of RPV helicopters tests with ATS-6 in high sea states A78-19128 [AIAA 78-1269] A78-50179 BICBOBAVB AHTBSSAS HISICOHPOTBBS Conformal microstrip phased array for aircraft Software engineering a must for success in tests with ATS-6 computerized flight test A78-19128 [AIAA PAPEB 78-1163] A78-17913 HICBOSAVB EQOIPBENT BISSILE COHTBOL Demonstration of the microwave ice protection Peace Ehme - A digital Weapon Control System for concept the F-1 aircraft [AD-A055821] N78-31096 A78-19876 niCBOBAVE LAHDI8G SISTERS Bank-to-turn /BIT/ autopilot technology for InterScan - A new microwave approach and landing missiles guidance system A78-19927 A78-U8736 In-flight alignnent/calibration techniques for Dse of the O.S. interim standard microwave landing unaided tactical guidance of air-launched system in Canada missiles A78-19333 A78-19929 Landing aircraft under poor conditions Hodnlar target acquisition and designation systems A78-H9549 A78-09951 Comparison study of HLS airborne signal processing BISSILE DESIGN technigues Center-loaded duct integral rocket-to-ramjet 478-19901 transition testing navigation performance of the Triscan concept for [AIAA PAPEB 78-937] A78-18156 shipboard VTOL aircraft operations HISSILE LAOBCBEBS [AIAA 78-1293] A78-50200 Peace Rhine - A digital Weapon Control system for Guidance and navigation for automatic landing, the P-1 aircraft rollout, and turnoff using HLS and magnetic A78-19876 cable sensors BISSILE SISTEBS [AIAA 78-1296] A78-50203 Technical evaluation of flying weapon systems [BAE-LIB-TBASS-1918] B78-31087

A-28 SUBJECT IHDEI HOZZLE DESIGB

BOISTOBE CONTEST BETS laterial evaluation of polyorethane xoao, 0.05 g/ Guidance and control problems in semaotonatic ca 3 density recovery of the Aguila RPV [BDI-613-1836-RE7] B78-312Q9 [AIAA 78-1272] A78-50182 BO1DS BEBTBALIZBBS Large electroformed nickel moulds for aircraft parts Neutralization problem for a Space Shuttle A78-17267 A78-1712H BONOPOLE ABTBBHAS BICEEL ALLOTS Analysis of uonopole antenna arrays on cylinders large electroformed nickel moulds for aircraft parts by the geometrical theory of diffraction A78-17267 [AD-A055197] H78-31335 SIGHT FLIGHTS (AIECEAPT) HOSOPDZSE B1DJB A systems approach to heliport lighting Coebinatorially derived Units on the surface A78-19238 return for an air/surface monopulse ranging radar BOISE IHTBBSITI A78-50001 Noise in airports, its measurement, and its effect BOTIOB PERCEPTION on the communities in the vicinity Simulator stody of the effect of visual-motion A78-U8371 time delays on pilot tracking performance with BOISE BEASOBEBEBt an audio side task An acoustic range for the measurement of the noise [NASJ-TP-1216] H78-30090 signature of aircraft during flyby operations HTBF A78-U72U2 Reliability of inertial navigation systems for BOISE POLLOTIOB military and commercial aircraft Synthesis of social surveys on noise annoyance A78-tt9968 A78-«8051 BULTIPiTH TBiSSBISSIOJ Boise in airports, its measurement, and its effect Fading at 9.6 GHz on an experimentally simulated on the communities in the vicinity aircraft-to-grouncl path A7.8-U837U A78-H9H39 BOISE PBOPAG1TIOH BULTIPLEIING Long-distance focusing of Concorde sonic boom Application of the General Purpose Bultiplex A78-118052 System to the A-7E avionics BOISE HEDOCTIOH A78-49867 Some sound transmission loss characteristics of BOLTIPROCESSIN6 (COBPDTEBS) typical general aviation structural materials Hultiprocessing for electronic warfare avionics [AIAA PAPER 78-111801 A78-U7925 478-09869 Helicopter transmission vibration and noise BULTISPBCTBll BIRD SCAHBBRS reduction program. Volume 2: oser's manual High-accuracy three-dimensional image [ AD-A05H827] N78-30095 reconstruction for an airborne line-scanning Helicopter transaission vibration and noise system reduction program. Volume 1: Technical report A78-H9988 [1D-A055101] N78-31089 J research program to reduce interior noise in general aviation airplanes: Noise reduction N through a cavity-backed flexible plate NACELLES [NASA-CH-157588] N78-31873 Nacelle effects on stability of VSTOL A research program to reduce interior noise in configurations including conventional, canard, general aviation airplanes: Investigation of and tandem wing arrangements the characteristics of an acoustic panel test [AIAA PAPER 78-1501] A78-U79U2 facility Wind Tunnel/Plight Test Correlation Program on the [NASf-CR-157587] N78-31871 B-1 nacelle afterbody/nozzle at transonic BOISE SPECTBA conditions An acoustic range for the measurement of the noise [AIA? PAPER 78-989] A78-II8069 signature of aircraft during flyby operations BASA PBOGHABS A78-U72I12 NASA engine system technology programs - An overview BOISE TBBESBOLD fAIAA PAPER 78-928] A78-Q8452 Synthesis of social surveys on noise annoyance HAVIBB-STOKES EQOATIOB A78-U8051 An experimental and numerical study of BOISE TOLEBABCE three-dimensional turbulent jets A further survey of some effects of aircraft noise [AIAA PAPER 78-99t] A78-I181171 in residential communities near London HAVIGSTION AIDS (Heathrow) airport Aviation control system devices Russian book [TT-7705] N78-30910 A78-119850 A comparison of annoyance caused by aircraft noise The role of system performance analysis in the near London, Manchester and Liverpool airports independent assessment of B-1 navigation software [TT-7706] N78-30911 A78-1I9902 HOBDESTBDCTITE TESTS Advanced pattern matching for navigation and NDI and the detection of fatigue guidance B78-30282 A78-II9998 BOBBQOILIBBIOB FLOB NAVIGATION IBSTBOBEBTS Investigation of nonequilibrium two-phase flows in Communication and navigation antennas for aircraft axisymmetnc Laval nozzles Russian book A78-U8200 J78-I48523 BOBOBIFOBH FLOg A modular adaptive, variable function flight Analysis of multistage, axial flow turbomachine control sensor wake production, transport, and interaction [AD-A055175] N78-31120 [AD-A05575!!] K78-31118 HAVSTAR SATELLITES BOBBAI Navstar GPS field test results TRSB oicrowave landing system demonstration A78-U9856 program at Kristiansand, Norway A Costas loop with tangent error signal for use in [AD-A055317] N78-31071 Savstar GPS avionics SOZZLE DESIGN A78-B9858 Canard configured aircraft with 2-D nozzle SATI [AIAA PAPEB 78-1050] A78-1790U The U.S. Navy bets on v/STOL technological An experimental and numerical study of integration for next generation aircraft design three-dimensional turbulent jets A78-M9550 [AIAA PAPER 78-99*] A78-H8D71 HEAR P1ELDS Non-axisym»etnc nozzle design and evaluation for Scan-limited near field testing for directive F-111 flight demonstration airborne antennas [AIAA PAPER 78-1025] A78-08H83 A78-U9897

A-29 NOZZLE PLOW SUBJECT INDEZ

Advance nozzle technology Optimization techniques for air traffic control H78-30111 problems Russian book NOZZLE FLOW A78-18501 Experimental determination of propulsion induced The terrain following task for the advanced ground effects of typical three fan type 4 tactical fighter using discrete optimal control V/STOI configurations A78-19862 [4IAA PAPER TB-iSOT) A78-17913 Performance of a ring laser strapdovn attitude and Investigation of nonequilibnum two-phase flows in heading reference for aircraft axisymmetnc Laval nozzles [AIAA 78-1210] A78-50162 A78-182KI Optimal terrain-aided navigation systems Kind Tunnel/Flight Test Correlation Program on the [AIAA 78-1213] A78-50163 B-" nacelle afterbody/nozzle at transonic Guaranteed cost control of linear systems with conditions uncertain parameters - Application to remotely [AIA? PAPER 78-9891 478-18169 piloted vehicle flight control systems Status of a nozzle-airframe study of a highly [AIAA 78-1271] 478-50181 maneuverable fighter Optimal flight control synthesis via pilot modeling [AIAA PAPER 78-990] 478-18170 [AIAA 78-1286] 478-50193 NOZZLE GEOHETBY Trajectory optimization for some sailplane Installed performance of vectoring/reversing performance problems non-axisymmetric nozzles S78-31083 [AIAA PAPER 78-1022] A78-18182 OPTIBIZATIOH vectoring non-axisymmetric nozzle jet induced On the theory of drag calculation and profile effects on a V/STOL fighter model optimization in shockless near free molecular flow TilAA PAPER 78-1080] A78-18196 A78-17887 NDBEBICAl ANALYSIS Definition of airplane fuselage longitudinal lines JO experimental and numerical study of by the special contour method three-dimensional turbulent jets A78-18222 [AIAA PAPEE 78-991] A78-18171 Control system design using vector-valued volumetric pattern analysis of airborne antennas performance criteria with application to the A78-19127 control rate reduction in parameter insensitive Hermite closed splines control systems A78-1I9713 [DLR-FB-77-55] 878-31125 NUMERICAL CONTROL OXIDATION RESISTANCE Digital control law synthesis in the w prime domain Effect of jet fuel autooxidation products on A78-U6962 thermooxidation stability Design and development of a multifunctional 478-19025 helicopter control system OZONE A78-119396 An assessment of the effect of supersonic aircraft The evolution of a remotely piloted vehicle operations on the stratospheric ozone content microprocessor flight control system [NASA-RP-1026] H78-30771 [AIA4 78-1273] A78-50183 Simultaneous measurements of ozone outside and software development for fly-by-wire flight inside cabins of two B-717 airliners and a Gates control systems Learjet business jet [AIAA 78-1276] A78-50185 [NASA-TM-78983] N78-31061 NUSEBICAL INTEGRATION Methods available to ONEHJ for analysis of combustion chambers [ONERA, TP NO. 1978-93] A78-16915 PACIFIC OCEAN The Omega radionavigation system comes to the Pacific Ocean area A78-U9660 OH-6 HELICOPTER PANEL FLUTTER Evaluation of a circulation control tail boom for Wing/store active flutter suppression - yaw control OH-6 helicopter Correlation of analyses and wind tunnel data [AD-A055116] N78-31119 [4144 PAPER 78-1159] A78-17909 OHEG4 NAVIGATION SYSTEH PANELS RBAV - Corporate operators set the pace Fatigue crack growth in pressurized fuselage panel A78-17121 A78-18231 The Omega radionavigation system comes to the Minimum weight design of stiffened panels with Pacific Ocean area fracture constraints A78-19660 A78-49837 Station deselection procedures to support PABACHOTE DESCENT automatic Omega receiver operation Operator work capacity during parachutist free-fall A78-19965 A78-17978 Performance of a differential Omega-ring laser PASSENGER AIRCRAFT strapdovn aircraft navigator Airliner numbers game - Does it add up A78-19966 political and technological aspects of OPERATING SYSfEBS (COMPUTERS) international aircraft industries The DAIS Executive - An introduction avionics A78-19521 computer software PASSENGERS A78-19932 Hodel of aircraft passenger acceptance OPERATIONAL PHOBLEBS A78-1968U An integrated analysis of the fundamental problems PATTERN RECOGNITION of air transport Pattern recognition as an aid to radar navigation A78-19117 A78-19855 Operational regularity in air transport Advanced pattern matching for navigation and A78-19119 guidance OPTICAL GYROSCOPES A78-09998 Performance of a ring laser strapdown attitude and A learning flight control system for the F8-DFBW heading reference for aircraft aircraft Digital Fly-By-Wire [AIAA 78-12110] A78-50162 [AIAA 78-1288] A78-50195 OPTIHAL CONTROL PAVEBBNTS Stability augmentation by eigenvalues control and Airfield pavement load evaluation - An model matching international overview A78-46965 478-19676 Optimal control synthesis in distributed systems Proposed load evaluation system for U.S. Air Force with incomplete information noting aircraft of airfield pavement applications 478-19677 A78-II8215

4-30 SUBJECT INDEX PRODUCTION P1AHBIBG

Transport Canada airfield pavement load evaluation PLATES (STRUCTURAL BEHBEBS) A78-49678 A research program to reduce interior noise in French procedures for airfield pavenent load general aviation airplanes: Noise reduction evaluation through a cavity-backed flexible plate A78-U9679 [NASA-CS-157588] N78-31873 Airfield pavenent evaluation - The airline view POIHTIHG CONTROL STSTEBS A78-U9680 nodular target acquisition and designation systems Airfield pavement evaluation - FAA viewpoint A78-I49951 A78-<»9681 POLABIZATIOB (SPIN ALIGNHBNT) Pavement strength rating nethods as viewed by Turbine tip clearance measurement airfrane manufacturers [AD-A055765] N78-31115 A78-K9682 POLLOTIOB COHTBOL PATLOADS Gas turbine engine emissions - Problems, progress Stability of a helicopter carrying an nnderslnng and future load A78-19336 A78-I19398 POLTOBETBANE FOAH Design of a large span-distributed load naterial evaluation of polyurethane foam, 0.05 g/ flying-wing cargo airplane with laminar flow cm 3 density control [BDX-613-1836-BEV] N78-312H9 [NASA-CB-145376] H78-300D5 POBOOS RILLS PBBFORHANCE PHEDICTIOH Induction of subsonic wind tunnels with slight Effects of wind on aircraft crnise performance perforation [AIAA PAPER 78-1U96] 478-1)7937 A78-I48250 Operational regularity in air transport POSITION (LOCUTION) A78-

A-31 PROGB1H VEBIFICATION (COBPOTEBS) SUBJECT INDEX

PBOGEiH VEEIFICATIOH (COBPUTEBS) Subsystem verification of an AFLC organically developed F-15 simulation Air Force Q Logistics Command QUALITATIVE ANALYSIS A78-19901 F-15 inlet/engine test techniques and distortion The role of system performance analysis in the methodologies studies. Volume 2: Time variant independent assessment of B-1 navigation software data quality analysis plots A78-19902 [HASA-CR-111867] B78-30121 PBOGBAHHING LANGUAGES QUALITY CONTBOL The D4IS Executive - Pn introduction avionics Analysis of GTE tolerance monitoring parameter computer software formation gas turbine engine A78-19932 A78-18212 The versatility of Jovial J71 in avionics systems Statistical review of counting accelerometer data A78-U9956 for Davy and Harine fleet aircraft from 1 A flight simulation high order language study January 1962 to 31 December 1977 A78-19957 [AD-A055672] N78-31098 Higher order languages for avionics software - A survey, summary and critigue A78-19959 PHOPEILEES BADAB DETECTION Progress in propeller aerodynamics Constant false alarm rate detector for a pnlse A78-17173 radar in a maritime environment PBOPOLSIOH SYSTEH COHFIGORATIOHS A78-19975 NASA engine system technology programs - An overview BADAB EQOTPHEHT [AIAA PAPER 78-928] A78-18052 A frequency-selective TIG limiter for airborne Propulsion test facilities - Capabilities and use FM/CB X-band radar [AIAA PAPER 78-933] A78-18153 A78-50002 Advanced supersonic transport engine integration Avionics cost development for alternatives of studies for near-term technology readiness date selected air traffic control systems [AIAA PAPER 78-1052] 478-18487 [AD-A054823] H78-30080 Propulsion system airframe integration studies - BADAB BEASUBBHENT Advanced supersonic transport Combinatorially derived limits on the surface [AIAA PAPER 78-1053] A78-18188 return for an air/surface monopnlse ranging radar Evaluation of inlet reingestion for large bypass A78-50001 ratio V/STO1 aircraft Optimal terrain-aided navigation systems [AIAA PAPER 78-1079] A78-18195 [AIAA 78-1213] A78-50163 A laser-powered flight transportation system BADAB NAVIGATION [AlfA PAPEH 78-1181] A78-19781 Pattern recognition as an aid to radar navigation The influence of propulsion and control system A78-19855 concepts on design of a Navy Type A V/STOL BADAB BECEIVEBS airplane Infrared receiver performance airborne warning [AIAA PAPER 78-1505] A78-19788 system by detection of target spectral signature Ground effects testing of two, three, and four jet A78-19985 configurations Phase-locked tracking loops for LOEAB-C [AI'.A PAPER 78-1510] \78-19789 [NASA-CR-157582] N78-31068 PHOPU1SIOH SYSTEH PEBF08HAHCE BADAB EXCEPTION Experimental determination of propulsion induced Combinatorially derived limits on the surface ground effects of typical three fan type A return for an air/surface monopulse ranging radar V/STOL configurations A78-50001 [AIAA PAPER 78-1507] A78-47913 BAD&B TRACKING The impact of contingency power concepts on V/STOI Air-to-air designate/track with time sharing aircraft take-off-gross-weight A78-19977 [AIAA PAPER 78-926] A78-18151 BADAB TRAHSBISSION Ramjet engine testing and simulation technigues A high duty factor chirp radar [AIAA PAPEB 78-935] A78-18155 A78-19976 The effect of thrust vectoring and attitude BADIO ANTENNAS control concepts on the propulsion system of Test and evaluation of air/ground communications V/STOL aircraft antennas [AIAA PAPER 78-1020] A78-18181 [AD-A056118] N78-31325 Propulsion for future supersonic transports - 1978 RADIO COHHUBICATION status Dual band airborne SATCOH terminal [AIAf PAPER 78-1051] A78-18186 A78-19972 A laser-powered flight transportation system BADIO EQUIPHENT [AIAA PAPEH 78-11181] 478-19781 Evaluating avionics weight efficiency PBOPDLSIVE EFFICIENCY A78-18228 Operating characteristics of bypass turbojet engines BADIO NAVIGATION Russian book Navstar GPS field test results AT8-50125 A78-19856 PBOVISG BADIO RECEIVERS TRSB microwave landing system demonstration Station deselection procedures to support program at John F. Kennedy International automatic Omega receiver operation Airport, Long Island, New York, OSA A78-19965 [AD-A055117] N78-31070 Performance in a jamming environment of a low-cost PUBLIC RELATIONS GPS user receiver algorithm for aiding a Reguirements for regional short-haul air service tactical INS and the definition of a flight program to [AD-A055239] N78-31078 determine neighborhood reactions to small RADIOGRAPH! transport aircraft Radiographic examination of T55 engine [NASA-CH-152151] N78-30070 [AD-A055108] N78-31113 PULSE BADAB BADOBE HATBBIiLS Constant false alarm rate detector for a pulse Large electroformed nickel moulds for aircraft parts radar in a maritime environment A78-17267 A78-19975 BAILS 1 high duty factor chirp radar Test and demonstration prototype tracked air A78-19976 cushion vehicle (PTACV): Phase IIIC PYBAHIDS [PB-279970/8] N78-31007 ? pyramid skewed axis sensor set for multiplex R1HJET ENGINES flight control systems Ground test facility for integral rocket ramjets [4HC-R/M-38081 N78-30113 [AIAA PAPEB 78-931] A78-18151

A-32 SUBJECT IBDEI ROCKET EBGIBZ DESI6H

Ramjet engine testing and simulation techniques Evaluation of methods for calculating system [Alii PAPER 78-935] A78-18155 operating time in accordance with Reliability Center-loaded duct integral rocket-to-raajet Improvement Warranty (RIB) contractual terms transition testing [AD-A051822] 1178-30079 tilii PiPBS 78-937] i78-18156 REMOTELY PILOTED VEHICLES Flame stabilization in a ramjet combustion chamber The HiHAT HPRV system by means of a pilot gas generator [Alii PiPEB 78-1157] A78-17908 [DLR-FB-77-51] H78-31117 Shipboard launch and recovery of RPV helicopters BiHGB FIBDEBS in high sea states t design of trajectory estimator using multiple [AIAA 78-1269] A78-50179 DUE range neasorements RPV flying qualities design criteria [iD-A05519-] H78-31077 [AIAA 78-1271] A78-50181 BiPID THAHSIT STSTEHS Guidance and control problems in semiautomatic Test and demonstration prototype tracked air recovery of the Aguila RPV cushion vehicle (PTACV): Phase IIIC [AIAA 78-1272] A78-50182 [PB-279970/8] B78-31007 The evolution of a remotely piloted vehicle BABE EABTB ELEBEHTS microprocessor flight control system Application of rare earth/transition metal [AIAA 78-1273] A78-50183 permanent magnets to 100 Hz aircraft systems - Guaranteed cost control of linear systems with in AF overview uncertain parameters - Application to remotely A78-19935 piloted vehicle flight control systems BAB1FIED GAS DYHAHICS [AIAi 78-127U] A78-50181 On the theory of drag calculation and profile RESEARCH AIBCBAFT optimization in shockless near free molecular flow Quiet, Short-Hani Research Aircraft - Current A78-17887 status and future plans BATIHGS [AIAA PAPER 78-1168] A78-17916 Pavement strength rating methods as viewed by Aerodynamic characteristics of a hypersonic airfrane manufacturers research airplane concept having a 70 deg swept A78-19682 double-delta wing at Hach number 0.2 REAL TIDE OPEBATIOH [SiSi-TP-1252] N78-31015 Integrated test mission control - Present and EESEABCB AND DEVELOPMENT future at the Air Force Flight Test center 10 years of contract research for the fAIAA PAPER 78-1 U61] A78-17911 pump/compressor industrial concern Real-time simulators for augmented inertial A78-19175 navigation systems Future needs and opportunities in the air traffic A78-19967 control system A design of trajectory estimator using multiple [GPO-98-931] N78-31076 DUE range measurements RESEABCB FACILITIES CAD-J055191] N78-31077 Status of aerial applications research in the HEDOBDiHCY Langley Vortex Research Facility and the Langley Improved combat survivability for fly-by-wire full-scale wind tunnel sensor systems [AIAA PAPER 78-11481] A78-17926 [AIAA 78-1277] A78-50186 RESEABCB VEHICLES Triplex digital fly-by-vire redundancy management The HiMAT BPRV system techniques [AliA PAPER 78-1157] A78-17908 [AIAi 78-1279] A78-50187 RESIDOAL STRESS REFUELIHG The influences of residual stresses on oscillating Investigation of electrostatic discharge in tensile strength and the measurement of residual aircraft fuel tanks during refueling stress, with emphasis on aircraft construction [AIAi PAPER 78-1501] i78-i!79IH fatigue life of aircraft construction REGBHEBATIOH (EHGIHEERIHG) materials Choice of cycle for a regenerative bypass turbojet [BHVG-FBHT-77-23] N78-30603 for long-range aircraft REVERSED F10B A78-H9723 Installed performance of vectoring/reversing EEGEESSIOB AHiLTSIS non-axisymmetnc nozzles Computerized aircraft attrition program [AIAA PAPER 78-1022] A78-18182 [iD-A055781] N78-31091 RHEOELECTBICAL SIHOLATIOH BEIBFORCED PliSTICS Application of electrical analogy to the Damping, static, dynamic, and impact substantiation and comparison of some analytical characteristics of laminated beams typical of methods of determining temperature fields in windshield construction gas-turbine blades [AD-A051163] N78-30093 A78-17101 BEIHFOBCED PLATES BIDIBS QDillTY Rinimnm weight design of stiffened panels with Side quality evaluation. IV - Models of subjective fracture constraints reaction to aircraft motion A78-II9837 A78-17190 REIHFOBCIBG FIBEBS Hodel of aircraft passenger acceptance Fibre composite reinforcement of cracked aircraft A78-U9681 structures RIGID BOTOBS N78-30288 Helicopter rotor vibration isolation RELIABILITY AHA1YSIS A78-19399 Reliability of inertial navigation systems for BIBG LASEBS military and commercial aircraft Performance of a differential Omega-ring laser A78-19968 strapdown aircraft navigator RELIABILITY EBGIBEEHIHG A78-19966 Distribution of reliability characteristics among Performance of a ring laser straprtown attitude and airplane system units to ensure given flight heading reference for aircraft safety level [AIAA 78-1210] A78-50162 A78-18221 BISK Comparisons of high anti-jam design techniques for P study of analog programming for prediction of GPS receivers Global Positioning Systen crack growth in aircraft structures subjected to A78-19857 random loads Hon-volatile memory system for severe environment [AD-A055789] N78-31097 flight recorders ROCKET EHGIHE DESIGB A78-09872 Ground test facility for integral rocket ramjets Triplex digital fly-by-wire redundancy management [AIAi PAPER 78-931] A78-18151 technigues [AIAA 78-1279] A78-50187

A-33 SOCKET ENGINES SUBJECT IHDEZ

SOCKET EBGISES Center-loaded duct integral rocket-to-ramjet transition testing [AIAA PAPEB 78-937] 178-181156 S-3 AIRCBAFT SOCKET EXHAUST Program analyses for the S-3 weapon system Ground impingement of a fan jet exhaust plane improvement program [AD-A054832] N78-31112 [AD-A055887] N78-31093 B01LISG BOHEHTS SATELLITE POBEB TB1HSHISSIOB (TO EASTS) Constant-control tolling maneuver A laser-powered flight transportation system A78-46961 [AIAA PAPER 78-1484] A78-49781 BOOT-HE1N-SQUABE EBBOBS SATELLITE SOLAS ESEBGY COHVEBSIOB Performance of a differential Omega-ring laser A laser-powered flight transportation system strapdown aircraft navigator [AIAA PAPER 78-1484] A78-49781 A78-1(9966 SCALE EFFECT BOTAEI BUGS F-15 inlet/engine test techniques and distortion The influence of high twist on the dynamos of methodologies studies. Volume 6: Distortion rotating blades analysis plots A78-47599 [SASJ-CB-144871] N78-30128 Measurement of vibratory displacements of a SCALE BODELS rotating blade Some observations on the mechanism of aircraft A78-49397 wing rock Helicopter rotor vibration isolation [AIAA PAPEB 78-1456] A78-47907 A78-49399 Stability and performance characteristics of a Investigation of a wing-rotor interaction system fixed arrow wing supersonic transport for helicopters configuration (SCAT 15F-9898) at Bach numbers [AD-A054093] N78-30092 from 0.60 to 1.20 Flight measurements of the effects of simulated [NASA-TB-78726] N78-30087 leading-edge erosion on helicopter blade stall, SCAHIEBS torsional loads and performance TRSB microwave landing system demonstration [ARC-R/M-38091 H78-30098 program at Kristiansand, Norway Experimental investigation of gust response of [AD-A055317] H78-31071 hingeless helicopter rotors TRSE microwave landing system demonstration [AD-A054752] N78-30142 program at Charleroi, Belgium The transonic flow on a helicopter rotor [AD-A055920] S78-31072 N78-31042 SCHEDULING Antitorque training: Evaluation of effectiveness Analysis of runway occupancy times at ma^or airports in reducing mishap losses TAD-J056052] N78-31131 [AD-J055040] H78-31092 SEA LAUNCHING Demonstration of the microwave ice protection Shipboard launch and recovery of BPV helicopters concept in high sea states fAD-A055824] N78-31096 [AIAA 78-1269] A78-50179 BOTATIHG BODIES SEA STATES Investigations on unsteady pressure distribution Shipboard launch and recovery of EPV helicopters measurements in rotating systems in high sea states [DLR-FB-77-43] N78-31135 [AIAA 78-1269] A78-50179 BOTOB ABBODYHAHICS SEALERS Progress in propeller aerodynamics Fundamentals of noncunng sealants for aircraft A78-47173 fuel tanks The influence of high twist on the dynamics of [JD-A054627] N78-30247 rotating blades SEALS (STOPPEBS) A78-47599 Gas path seal Turbine engine rotordynamic evaluation, volume 1 [HASA-CASE-LEW-12131-2] N78-31103 fAD-A055262] N78-31111 SENSORS BOTOB BLADES Improved combat survivability for fly-by-wire The influence of high twist on the dynamics of sensor systems rotating blades [AIA1 78-1277] A78-50186 A78-47599 SEPABATED FLOS Demonstration of the microwave ice protection Influence of slots on effectiveness of wing concept mechanization and control surfaces with fAD-A0558241 N78-31096 separated flow BOTOB BLADES (TUBBOH11CHIHBBT) A78-48229 Performance with and without inlet radial A method for localizing wing flow separation at distortion of a transonic fan stage designed for stall to alleviate spin entry tendencies reduced loading in the tip region [AIAA PAPEB 78-1476] A78-49787 rHASA-TS-129!!] 1178-30057 SEBVICE LIFE tdvanced optical blade tip clearance measurement Design for durability - The F101-GE-100 engine system [AIAA PAPER 78-1084] S78-48497 [NASA-CB-159402] R78-31106 Approach for identifying avionics flight software BOTOBCBAFT AIBCBAFT operational support requirements - PAVE TACK an BEXOR 2 rotorcraft simulation nodel. Volume 1: example Engineering documentation A78-49900 [NASA-CR-145331] N78-30042 Computerized aircraft attrition program PEIOB 2 rotorcraft simulation model. Volume 2: [AD-A055784] N78-31094 Computer implementation SH-3 HELICOPTEB [HASA-CB-115332] 1178-30013 Stability of a helicopter carrying an underslnng EEXOS 2 rotorcraft simulation model. Volume 3: load User's manual A78-49398 [NAS&-CR-145333] H78-30044 SHIPS BOTOBS Navigation performance of the Triscan concept for Eotor design implications for composite material shipboard VTOL aircraft operations properties [AIAA 78-1293] A78-50200 [UCRL-80117] N78-30182 SHOBT HAUL AIBCBAFT BDHWATS Ride quality evaloation. IV - Hodels of subjective Engineering and development program plan: Hake reaction to aircraft motion vortex A78-47490 [AD-A051143] H78-30071 Analysis of runway occupancy times at major airports [AD-A056052] N78-31131

A-3» S0BJECT 1SDBI STANDARDS

The effect on block fuel consumption of a strutted SODND TBABSBISSIOH versus cantilever wing for a short-haul Some sound transmission loss characteristics of transport including strut aeroelastic typical general aviation structural naterials considerations [AIAA PAPEB 78-1080] A78-47925 [AIAA PAPEB 78-1050] S78-U7905 SOUBCE PBOGBABS Quiet, Short-Baal Research Aircraft - Current Modification of the Douglas Neumann prograa to status and future plans improve the efficiency of predicting component fAIAA PAPEB 78-1468] A78-U7916 interference and high lift characteristics Application of advanced high speed turboprop [NASA-CB-3020] N78-30051 technology to fature civil short-haal transport SPACE FLIGHT STBESS aircraft design Safety of space flights [AIAA PAPEH 78-1087] A78-U7930 A78-U7952 Requirements for regional short-haal air service SPACE SHUTTLES and the definition of a flight prograa to Neutralization problem for a Space Shuttle determine neighborhood reactions to snail A78-07121 transport aircraft SPACECBAFT CHABGIHG fNASA-CR-152151] H78-30070 Neutralization problem for a Space Shuttle SHOBT TAKEOFF AIBCBAFT A78-07120 Takeoff performance of STOI aircraft SPACECBAFT COBHDHIC1TIOH A78-09700 Dual band airborne SATCOB terminal Wind-tunnel testing of VTOI and STOI aircraft A78-U9972 rNASA-TB-78750] N78-30010 SPACECBAFT DESIGN SIDESLIP The design process computer aided design for Flight investigation and theory of direct complex aerospace systems side-force control [AIAA PAPEB 78-1183] A78-U7928 [AIAI 78-1287] A78-5019H The use of the AIAA-Bendix Design Competition in SIGNAL DETECTORS aerospace design courses Phase-locked tracking loops for LOBAN-C [AIAA PAPEB 78-1088] A78-07931 [NASA-CB-157582] N78-31068 Modular Hissionization Systems /BBS/, an adaptive SIGNAL FADING system interface concept Fading at 9.6 GHz on an experimentally simulated A78-U9852 aircraft-to-ground path SPECTBAL ENEBGT DISTRIBUTION A78-19039 P-15 inlet/engine test technigues and distortion SIGHAL PBOCESSING methodologies studies. Volume 8: Cross Comparison study of HIS airborne signal processing spectral density plots technigues [NASA-CB-111873] N78-30130 !78-U990» SPECTBAL SIGNATOBBS Station deselection procedures to support An acoustic range for the measurement of the noise automatic Omega receiver operation signature of aircraft during flyby operations A78-19965 A78-17212 A high duty factor chirp radar Infrared receiver performance airborne warning A78-09976 system by detection of target spectral signature SIGHAL TBANSBISSION A78-49985 Flight application of optical fiber transmission SPIN TESTS on a Falcon 10 aircraft Correlation of model and airplane spin fONEBA, TP NO. 1978-105] \78-U7?09 characteristics for a low-wing general aviation SIBPLE HABBONIC HOTION research airplane Tvo-dimensional aerofoils and control surfaces in CAIAA PAPEB 78-iii77] A78-U7922 simple harmonic motion in incompressible SPLINE FUNCTIONS inviscid flow Semite closed splines [ABC-CP-13921 B78-30068 A78-19713 SINGLE STAGE TO OBBIf VEHICLES Optimal terrain following controller for an Static aerodynamic characteristics of a winged optimized spline reference path single-stage-to-orbit vehicle at Bach numbers [AD-A055231] N78-31122 from 0.3 to 1.63 SPRAYERS [NASA-TP-1233] N78-30053 Bodified helicopter icing spray systen evaluation SIHGULABITY (BATHBBATICS) [AD-A055039] N78-31091 A mean camberline singularity method for SPBAIING , two-dimensional steady and oscillatory aerofoils Status of aerial applications research in the and control surfaces in inviscid incompressible Langley vortex research facility and the Langley flow fall-scale wind tunnel [ABC-CP-1391] N78-30066 [NASA-TS-78760] N78-30001 SOCIAL FACTOBS STABILITY AUGBENTATION Synthesis of social surveys on noise annoyance Stability augmentation by eigenvalues control and A78-18051 model matching SOLID STATE DEVICES A78-B6965 Solid-state displays for fuel management systems Evolution of a cost-effective, task-oriented, for aircraft lateral-directional S*S for the A-10 aircraft A78-07900 Stability Augmentation System SONIC BOOBS [1IAA PAPEB 78-1460] A78-U7910 Long-distance focusing of Concorde sonic boom STABILITY DERIVATIVES A78-08052 Important simulation parameters for the SOUND FIELDS experimental testing of propulsion induced lift Theoretical and experimental studies of aconstic effects propagation in inhomogeneous noving media [AIAA PAPEB 78-1078] A78-18094 [ESA-TT-077] N78-30909 Lateral-aerodynamic characteristics of SOOHD INTENSITY highly-dihedraled wings A research program to reduce interior noise in A78-Q9330 general aviation airplanes: Investigation of STAGE SEPABATION the characteristics of an aconstic panel test Graphics for the hybrid stores separation facility sinnlation of the B77 system [NASA-CB-157587] 878-3187* [SAND-78-8212] 878-31099 SOUND PBESSUBE STANDARDS Fatigue crack growth in pressurized fuselage panel BIL-STD-1553B proposed data bus development in A78-08231 avionic architecture SOUND PROPAGATION A78-B9866 Theoretical and experimental studies of acoustic propagation in inhomogeneons moving media [ESA-TT-077] U78-30909

A-35 ST&TIC AEBODYNABIC CHABACTEBISTICS SUBJECT IHDEX

STATIC ABBODYBAMIC CHABACTEBISTICS Pavement strength rating methods as viewed by Static aerodynamic characteristics of a typical airframe manufacturers single-engine low-wing general aviation design A78-U9682 for an angle-of-attack range of -8 deg to 90 deg Hinimnm weight design of stiffened panels with [NASA-CB-297*] N78-30048 fracture constraints Static aerodynamic characteristics of a winged A78-49837 single-stage-to-orbit vehicle at Mach numbers Dulles control tower console design study from 0.3 to U.63 [AD-A056200] B78-31132 [HASA-TP-1233] N78-30053 STRUCTURAL DESIGN CRITERIA STATIC STABILITY Design philosophy for airframes "nalysis of stability contributions of high A78-II71153 dihedral v-tails STBOCTUBIL ENGINEERING [msA-TB-78729] N78-31044 Engineering data on new aerospace materials STATISTICAL ANALYSIS structural materials Evaluation of methods for calculating system [AD-A054461] H78-30213 operating tine in accordance with Reliability STBOCTDBAL BELIABILITI Improvement warranty (HIH) contractual terms Aircraft structural fatigue [AD-4054822] N78-30079 [ABL/STBUC-REPT-363] H78-30271 Statistical review of counting accelerometer data Aircraft structural reliability and risk theory: for Navy and Marine fleet aircraft from 1 A review January 1962 to 31 December 1977 N78-30284 [AD-A055672] N78-31098 STRUCTURAL STABILITY Botor burst protection program: Statistics on Flutter suppressor for transonic flight aircraft gas turbine engine rotor failures that [ONERA, TP NO. 1978-102] A78-47346 occurred in US commercial aviation during 1975 STRUCTURAL STBAIB [NASA-CB-135304] N78-31105 Fatigue crack growth in pressurized fuselage panel STEELS A78-U8231 Metal technology for future aircraft design STEDCTDBAI VIBRATION N78-30115 Engine vibration in flight STBAPDOWN INEBTIAL GUIDANCE [AIAA PAPEB 78-1475] A78-47921 Advances in inertial navigation Measurement of vibratory displacements of a A78-47481 rotating blade Strapdown seeker guidance for tactical weapons A78-U9397 A78-D9928 Ose of ground vibration test equipment to In-flight alignment/calibration techniques for determine unsteady aerodynamic forces unaided tactical guidance of air-launched A78-119708 missiles Prediction of angular disturbances from airframe A78-U9929 members to airborne electro-optical packages Multi-Function Inertial Reference assembly /MIBA/ A78-49952 update digital aircraft systems Computer program for vibration prediction of A78-49941 fighter aircraft equipments Performance of a differential Omega-ring laser [AD-A054598] N78-30094 strapdown aircraft navigator Considerations on wing stores flutter: Asymmetry, A78-49966 flutter suppression Performance of a ring laser strapdown attitude and [AGABD-R-668] N78-31126 heading reference for aircraft STBDTS UlAA 78-121(0] >78-50162 The effect on block fuel consumption of a strutted STBATOSPHEBE versus cantilever wing for a short-haul On the use of zirconium 95 data from Chinese transport including strut aeroelastic atmospheric thermonuclear explosions to study considerations stratospheric transport in a one-dimensional [AIAA PAPEB 78-11154] A78-47905 parameterization Analysis of a suspension system for a wheel A78-U8062 rolling on a flat track Pn assessment of the effect of supersonic aircraft [NASA-CB-157563] 1178-3058? operations on the stratospheric ozone content SUBSONIC AIRCRAFT rNASA-BP-1026] N78-3077U Whitcomb winglet applications to general aviation STREAH FUNCTIONS (FLUIDS) aircraft Method of calculating aerodynamic coefficients of [AIAA PAPER 78-1478] A78-47923 some three-dimensional bodies with arbitrary SUBSONIC FLO* cross section A calculator program for analyzing airloads on a A78-48245 wing of arbitrary planform and camber in STRESS ABALYSIS subsonic flow Recent developments in analysis of crack [AD-A054180] N78-30058 ptopagation and fracture of practical materials StJBSONIC RIND TUNNELS stress analysis in aircraft structures Induction of subsonic wind tunnels with slight rNASf-TB-78766] S78-30606 perforation STRESS HEASOBEHEHT A78-48250 The influences of residual stresses on oscillating SUPERCONDUCTING POWER TRANSMISSION tensile strength and the measurement of residual Modeling refinements for the rectified stress, with emphasis on aircraft construction superconducting alternator airborne power fatigue life of aircraft construction supply materials J78-49961 [BHVG-FBHT-77-23] N78-30603 SUPBBCBITICAL BINGS STRESS-STBAIN BELATIOBSHIPS Aerodynamic characteristics induced on a General aviation airplane structural supercritical wing due to vectoring twin nozzles ccashworthiness user's manual. Volume 1: at Mach numbers from 0.40 to 0.95 Program KHASH theory [NASA-TH-78746] 1178-30039 [AD-A055898] 1178-31088 Theoretical estimation of the transonic STBOCTUBAL AHALYSIS aerodynamic characteristics of a Large deflection static analysis of typical supercritical-wing transport model with tail-wheel structure of light aircraft by finite trailing-edge controls element method [NASA-TP-1253] 1178-30056 A78-48864 Control-surface hinge-moment calculations for a STRUCTUBAL DESIGN high-aspect-ratio supercritical wing Teaching design at all levels in aerospace [NASA-TH-7866I1] H78-31043 engineering curricula SOPEEHIGB FEBQOBHCIBS [AIAA PAPEB 78-1155] A78-II7906 Dual band airborne SATCOH terminal Airfield pavement evaluation - FAS viewpoint A78-49972 A78-49681

A-36 SUBJECT IBDEX TAIL ASSBHBLIES

SDPEBPOSITIOH (HATHEHiTICS) Aerodynamic characteristics of a hypersonic On the linear saperposition of aerodynaoic forces research airplane concept having a 70 deg swept OD wings in periodic gusts double-delta wing at Hach number 0.2 A78-17869 [HASA-TP-1252] 878-31005 SOPEBPBESSOHE B&LLOOHS SYSTEH EFFBCTIVEHESS Aerodynamic hall design for HASPA LTA optimization Technology analysis - Candidate advanced tactical High Altitude Saperpressare Powered Aerostat fighters Lighter Than Pir [AIAA PAPEB 78-1D51] A78-09782 A78-i»8100 nodular target acquisition and designation systems SOPEBSOHIC AIBCBAFT A78-09950 Mirage 2000 - Dassault's better delta A parametric analysis of TEBCOM false fix A78-09169 probability TEBrain contour Hatching Design evolution of a supersonic cruise A78-09997 strike-fighter STSTEB FAILOBES [AIAA PAPEB 78-1052] A78-19783 Triplex digital fly-by-wire redundancy management Theoretical estimation of the transonic techniques aerodynamic characteristics of a [AIAA 78-1279] A78-50187 supercritical-wing transport model with SYSTEBS ABALTSIS trailing-edge controls The value of aerospace design synthesis courses as [HASA-TP-1253] H78-30056 viewed by aerospace professionals SOPEBSOHIC FLIGHT [AIAA PAPEB 78-1093] A78-07930 Bamjet engine testing and sinnlation techniques The role of system performance analysis in the [AIAA PAPEB 78-935] A78-08055 independent assessment of B-1 navigation software SOPEBSOHIC FLOW A78-09902 Linearized theory of plane, unsteady, supersonic Dynamic analysis of electrical systems flow through a cascade - Subsonic part of the A78-09930 leading edge SYSTEHS EHGIHEERIHG [ONEBA, TP HO." 1978-103] A78-07307 Teaching design at all levels in aerospace Method of calculating aerodynamic coefficients of engineering curricula some three-dimensional bodies with arbitrary [AIAA PAPEB 78-1155] A78-07906 cross section Integrated avionics for future general aviation A78-08205 aircraft Linearized supersonic unsteady flow in cascades [AIAA PAPEB 78-1082] A78-07927 [ABC-B/H-3811] 878-30065 The value of aerospace design synthesis courses as SOPEBSOHIC SPEEDS viewed by aerospace professionals Supercruiser fighter analysis [AIAA PAPEB 78-1093] A78-07930 178-30107 A systems approach to heliport lighting SOPEBSOHIC TBiSSPOBTS A78-09238 Propulsion for future supersonic transports - 1978 Design and development of a multifunctional status helicopter control system [&IAA PAPEB 78-1051] &78-08086 A78-09396 Advanced supersonic transport engine integration The D.S. Havy bets on V/STOL technological studies for near-terra technology readiness date integration for next generation aircraft design CAIAA PIPES 78-1052] A78-08087 A78-09550 Propulsion system airframe integration studies - Modular Missionization Systems /MMS/, an adaptive Advanced supersonic transport system interface concept [AIAA PAPEB 78-1053] A78-18U88 A78-09852 Stability and performance characteristics of a Comparisons of high anti-]am design techniques for fixed arrow wing supersonic transport GPS receivers Global Positioning System configuration (SCAT 15F-9898) at Bach numbers A78-09857 from 0.60 to 1.20 A hierarchical network for avionic systems [NASH-TH-78726] N78-30087 A78-09868 An assessment of the effect of supersonic aircraft Digital system architecture for a 1980's jammer operations on the stratospheric ozone content for military aircraft and ships [HASA-RP-1026] 1H8-30770 A78-09973 SUPPORT SYSTEHS SYSTEHS HANAGEBEHT Approach for identifying avionics flight software AIDS in engine management programmes Airborne operational support requirements - PATE TACK an Integrated Data Systems example A78-07865 A78-09900 SYSTEHS STABILITY Digital avionics support - A retrospective view of Guaranteed cost control of linear systems with the future uncertain parameters - Application to remotely A78-19903 piloted vehicle flight control systems SDBFACE BAVIGATIOB [AIAf 78-1270] A78-50180 The Omega radionavigation system cooes to the Pacific Ocean area A78-09660 SOBFACE PROPERTIES T-55 EBGIHB Modeling ground plane influence on wing Badiographic examination of T55 engine aerodynamic characteristics using a finite plane [AD-A055108] N78-31113 screen TABLES (DATA) A78-118216 Evaluation of methods for calculating system SURFACE ROUGBNESS operating tioe in accordance with Beliability Flight measurements of the effects of simulated Improvement Barranty (BIB) contractual terms leading-edge erosion on helicopter blade stall, [AD-A050822] N78-30079 torsional loads and performance TACAB [ABC-B/H-3809] H78-30098 TBACALS evaluation report. TACAH. VOB, and ILS SOBVEIS station evaluation report, Andersen AFS, Guam Synthesis of social surveys on noise annoyance [AD-A050200] N78-30078 A78-118051 TAIL ASSERBLIES SOSPEHSIOH SISTERS (VEHICLES) Correlation of lodel and airplane spin Analysis of a suspension system for a wheel characteristics for a low-wing general aviation rolling on a flat track research airplane [HASA-CR-157563] N78-30583 [AIAA PAPEB 78-1077] A78-07922 SWEPT VIRGS Boiling tail design and behavior as affected by Approximate indicial lift function for tapered, actuator hinge moment limits for B-1 swept wings in incompressible flow maneuverability [HASA-TP-1201] N78-30051 [AIAA PAPEB 78-1500] A78-17900

A-37 TAIL EOTOES SUBJECT INDEX

large deflection static analysis of typical Application of electrical analogy to the tail-wheel structure of light aircraft by finite substantiation and comparison of some analytical element method methods of determining temperature fields in A78-4886U gas-turbine blades Evaluation of a circulation control tail boom for A78-47404 yaw control OH-6 helicopter TENSILE STBBNGTH [AD-A055116] H78-31119 The influences of residual stresses on oscillating T&IL BOTOHS tensile strength and the measurement of residual fntitorgue training: Evaluation of effectiveness stress, with emphasis on aircraft construction in reducing mishap losses fatigue life of aircraft construction [AD-A0550401 N78-31092 materials TAKEOFF fBHVG-FBWT-77-23] N78-30603 Takeoff performance of STOI aircraft TEBCOH A78-49744 A parametric analysis of TERCOM false fix Flight investigation and theory of direct probability TERrain contour Batching side-force control A78-49997 fAIAA 78-1287] A78-50194 TEBBIHAL CONFIGURED VEHICLE PBOGBAH TABGET ACQUISITION Flight demonstrations of curved, descending Digital area correlation tracker approaches and automatic landings using time A78-49951 referenced scanning beam guidance nodular target acquisition and designation systems [NASA-TH-78745] N78-3007U A78-49954 TEBHIBAL FACILITIES Autothreshold autoscreener/FLIR system Application of the General Purpose Multiplex airborne target screener/Forward-Looking System to the A-7E avionics Infrared imaging system A78-49867 A78-49984 TERMINAL GUIDANCE TiBGET BBCOGBITION Strapdown seeker guidance for tactical weapons Constant false alarm rate detector for a pulse A78-49928 radar in a maritime environment TEBBAIH ANALYSIS A78-U9975 Pattern recognition as an aid to radar navigation Infrared receiver performance airborne warning A78-19855 system by detection of target spectral signature TEBB4IN FOLLOWING AIBCBAFT A78-49985 The terrain following task for the advanced TECHHOLOGICAI FOBECASTING tactical fighter using discrete optimal control The D.S. Navy bets on V/STOL technological .178-19862 integration for next generation aircraft design Optimal terrain-aided navigation systems A78-49550 [AIAA 78-12431 A78-50163 Digital system architecture for a 1980's jammer The terrain following task for the advanced for military aircraft and ships tactical fighter using discrete optimal control A78-49973 [AD-A055196] N78-31121 Metal technology for future aircraft design Optimal terrain following controller for an N78-30115 optimized spline reference path Future needs and opportunities in the air traffic [AD-4055234] S78-31122 control system TEST EQOIPHEHT [GPO-98-931] N78-31076 French procedures for airfield pavement load TECHNOLOGY ASSESSBENT evaluation Quiet, Short-Haul Eesearch Aircraft - Current A78-19679 status and future plans TEST FACILITIES [AIAH PAPER 78-11I68] A78-17916 Propulsion test facilities - Capabilities and use Sensor technology for turbine engine monitoring [AIAA PAPEB 78-933] A78-48453 systems Ground test facility for integral rocket ramjets [AIAA PAPEB 78-1H7II] A78-47920 [AIAA PAPEB 78-934] A78-4845U Advanced supersonic transport engine integration A research program to reduce interior noise in studies for near-tern technology readiness date general aviation airplanes: Investigation of TAIfA PAPEB 78-1052] A78-48487 the characteristics of an acoustic panel test Technology analysis - Candidate advanced tactical facility fighters [NASA-CB-157587] N78-31874 fAIAA PAPEB 78-1U51] A78-49782 TEST STANDS Requirements for regional short-hanl air service Ose of a field bench for testing turbojet engines and the definition of a flight program to A78-49731 determine neighborhood reactions to small TF-41 ENGINE transport aircraft TF41-A-2/A7E inflight engine condition monitoring [NASA-CB-152151] N78-30070 system /IECHS/ Technical evaluation of flying weapon systems [AIAA PAPEB 78-1472] A78-47918 [RAE-LIB-TBANS-1948] N78-31087 THEBHAL CYCLING TESTS TECHNOLOGY UTILIZATION Aspects of the thermal fatigue strength of The D.S. Navy bets on V/ST01 technological gas-turbine engine components integration for next generation aircraft design A78-49176 A78-49550 THEBHAL STABILITY TELEVISION CAHEEAS Effect of jet fuel autooxidation products on Guidance and control problems in semiautomatic thermooxidation stability recovery of the Aquila BPV A78-49025 [AIAA 78-1272] A78-50182 THEBHOCHEHICiL FBOPEBTIES TELEVISION SYSTEHS Assessment of relative flammability and Description and performance of the Langley visual theroochemical properties of some thermoplastic landing display system materials tNASA-TH-787l|2] N78-30073 A78-49693 TEHPEBATUBE CONTBOL THEBHODYHARIC CYCLES Experimental determination of parameters of Choice of cycle for a regenerative bypass turbojet mathematical model of airplane cabin as for long-range aircraft regulated object with respect to air temperature A78-49723 in the cabin Use of a field bench for testing turbojet engines A78-48234 A78-49731 TEHPEBATUBE DISTBIBOTION THEBHOHUCLEAB EXPLOSIONS Calculation of exchange coefficients for On the use of zirconium 95 data from Chinese high-temperature turbine blades atmospheric thermonuclear explosions to study [ONEBA, TP NO. 1978-101] A78-47348 stratospheric transport in a one-dimensional parameterization A78-48062

A-38 SUBJECT INDEX TB&BSORIC FLOB

THEBBOPLASTIC BESIHS TOBQOE Assessment of relative flanmability and Boiling tail design and behavior as affected by themochemical properties of some thernoplastic actuator hinge moment limits for B-1 materials maneuverability A78-49693 [AIAA PAPEB 78-1500] A78-47940 TBTCKRESS BATIO Control-surface hinge-moment calculations for a Shockless airfoils vith thicknesses of 20.6 and high-aspect-ratio supercritical wing 20.7 percent chord analytically designed for a [NASA-TB-78664] B78-310U3 Bach nanber of 0.68 and a lift coefficient of 0.10 Antitorgne training: Evaluation of effectiveness [NASA-TB-x-73917] H78-300U6 in reducing mishap losses THIS WIRGS [AD-A055040] D78-31092 Asymptotic theory of a wing moving near a solid wall TBACKISG (POSITION) A78-48248 Digital area correlation tracker Unsteady hypersonic gas flow past a thin wing of A78-49951 finite span Evaluation of several secondary tasks in the A78-<19792 determination of permissible time delays in THESE DIBENSIOHAL FLOB simulator visual and motion cues Method of calculating aerodynamic coefficients of [BASA-TP-1214] H78-30089 some three-dimensional bodies with arbitrary TBACKIHG 8BTBOBKS cross section Modular target acquisition and designation systems A78-48245 A78-49954 »n experimental and numerical stndy of TBAILIRG EDGES three-dimensional turbulent jets Trailing vortices. II [AliA PAPEE 78-991] A78-48471 A78-47172 THHOTTLIHG Uniformly exact conformal transformation of The influence of throttle augmented stability exterior of circle onto exterior of wing profile (APCS) and short period control characteristics A78-48224 on the landing approach Theoretical estimation of the transonic [AD-A055892] N78-31123 aerodynamic characteristics of a THBDST ADGBBRTATIOR supercritical-wing transport model with An analytical and experimental investigation of trailing-edge controls diffusers for VSTOL thrust augmenting ejectors [NASA-TP-1253] N78-30056 TAIAf PAPEB 78-1509] A78-17945 TBAIRIRG AIBCBAFT THBOST VECTOB CORTBOL Effect of performance objectives on the design and The effect of thrust vectoring and attitude cost of future DSAF pilot training aircraft control concepts on the propulsion system of [AIAA PAPEB 78-11198] A78-47938 V/STOL aircraft TBAIFING SIBOLATOBS CAIAA PAPER 78-1020] A78-48481 Air-to-air combat simulation Installed performance of vectoring/reversing A78-47868 A flight simulation high order language study [AIAf PAPEB 78-1022] A78-48482 A78-49957 Non-axisymmetric nozzle design and evaluation for TBAJBCTOBIES P-111 flight demonstration A design of trajectory estimator using multiple fAIAA PAPEB 78-1025] A78-48483 DHE range measurements Vectoring non-axisymmetnc nozzle jet induced [AD-A055191] B78-31077 effects on a V/STOL fighter model Trajectory optimization for some sailplane [AIAA PAPEB 78-1080] A78-48496 performance problems Aerodynamic characteristics induced on a N78-31083 supercritical wing due to vectoring twin nozzles TBAJECTOBT ARALTSIS at Bach numbers from 0.40 to 0.95 A method for determining the stability [RASA-TB-78746] N78-30039 characteristics of aircraft in a helicoid flight Optimal terrain following controller for an path optimized spline reference path i78-»97U1 [AD-A055234] H78-31122 TBAJBCTOBI COHTBOL THBOST-BBIGHT BATIO Software structured weapon delivery The impact of contingency power concepts on V/STOL A78-119875 aircraft take-off-gross-weight TBAJECTOBY OPTIBIZATIOH CAIAA PAPEB 78-926] ?78-48451 Characteristics of constrained optimum TUT BOTOB ilBCBAFT trajectories with specified range The promise of tilt rotor [NASA-TB-78519] N78-30072 A78-47266 TEiRSITIOH BETALS Approach guidance logic for a tilt-rotor aircraft Application of rare earth/transition metal [AIAA 78-1295] A78-50202 permanent magnets to 400 Hz aircraft systems - TIBB DEPENDENCE An AF overview Flight demonstrations of curved, descending A78-49935 approaches and automatic landings using time TBABS1ISSIOR LOSS referenced scanning bean guidance Some sound transmission loss characteristics of [NASA-TS-78745] N78-3007

A-39 TEAHSOHIC PLOTTER SUBJECT INDEX

The transonic flow on a helicopter rotor Turbine tip clearance measurement N78-31012 [AD-A055765] N78-31115 fn automated procedure for computing the TOBBIHES three-dimensional transonic flow over wing-body A theoretical study of the performance of a number combinations, including viscous effects. Volume of different axial-flow turbine configurations 1: Description of analysis methods and under conditions of pulsating flow applications [ABL/HECH-ENG-BEPT-149] N7 8-31101 [AD-A055899] N78-31052 TDBBOCOHPBESSOBS TBAHSOHIC FLOTTEB Analysis of multistage, axial flow turbomachine Platter suppressor for transonic flight wake production, transport, and interaction [ONEBA, TP NO. 1978-102] A78-47346 [AD-A055754] N78-31118 Drones for aerodynamic ana structural testing TOBBOF1H EHGIHES /D1ST/ - A status report The second generation of high-bypass turbo fans - A [AIAA PAPEB 78-1"l85] A78-47929 market clouded by uncertainty TBAHSONIC WIBD TOHBELS A78-47423 Some observations on the mechanism of aircraft Design for durability - The F101-GE-100 engine wing rock [AIAA PAPEE 78-1084] A78-48497 [AIAA PAPEB 78-1456] A78-47907 Choice of cycle for a regenerative bypass turbojet TBANSPOBDEBS for long-range aircraft The AN/APX-'OO/V/ transponder for military A78-49723 aircraft Short-term performance deterioration in A78-19971 JT9D-7A(SP) engine 695743 TBASSPOBT AIECB1FT [NJSA-CB-135431 ] N78-30121 From Challenger to winner Canadair executive Procedures for generation and reduction of linear ]et design and development models of a turbofan engine A78-17570 [NASA-TP-1261] H78-30896 Dse of onboard computerized flight test analysis Energy efficient engine: Preliminary design and systems integration studies [flA? PAPEB 78-11162] A78-47912 [ NASA-CB-1 35444] B78-31108 Conceptual design study of power augmented ram TOBBOJET ENGINES wing in ground effect aircraft An analytical and experimental investigation of [AIAA PAPEB 78-11(66] A78-47915 diffusers for VSTOL thrust augmenting ejectors Application of advanced high speed turboprop [AIAA PAPEB 78-1509] A78-U791I5 technology to future civil short-haul transport Dse of a field bench for testing turbojet engines aircraft design A78-49731 [AIAA PAPEB 78-1487] A78-47930 Operating characteristics of bypass turbojet engines Takeoff performance of STOI aircraft Bussian book f 78-49744 A78-50125 Prospects for commercial commonality in military Ground impingement of a fan jet exhaust plume transports [AD-A054832] H78-31112 TAIfA PAPEB 78-11167] A78-49784 TDBBOBACHINE BLADES Ring planforms for large military transports Botor burst protection program: Statistics on [AIAA PAPEB 78-1170] A78-49786 aircraft gas turbine engine rotor failures that Beguirements for regional short-haul air service occurred in DS commercial aviation during 1975 and the definition of a flight program to [NASA-CB-135304] N78-31105 determine neighborhood reactions to small TOBBOPBOP AIBCBAFT transport aircraft The promise of tilt rotor [NASA-CE-152151] B78-30070 A78-47266 Measurements and analysis of the forces acting on Application of advanced high speed turboprop a small aircraft flying in the upwash of a large technology to future civil short-haul transport aircraft aircraft design [AD-A055286] H78-31048 [AIAA PAPEB 78-1187] A78-47930 Study of fuel systems for IH2-fuelea subsonic TOBBOSBAFIS transport aircraft, volume 1 Badiographic examination of T55 engine [NASA-CE-HSSSg-VOL-l ] N78-31085 [AD-A055108] N78-31113 Study of fuel systems for lH2-fueled subsonic TDBBOLEFT FLOi transport aircraft, volume 2 Calculation of exchange coefficients for [NASA-CR-145369-VOL-2] N78-31086 high-temperature turbine blades Energy efficient engine: Preliminary design and [ONEBA, TP NO. 1978-104] A78-17318 integration studies TOBBOLBHf BEAT TRAHSFEB [NASA-CB-13541I14] N78-31108 Solution of an adjoint problem of steady-state TBASSPOBT PBOPEBTIES heat transfer associated with the cooling of Analysis of multistage, axial flow turbomachine gas-turbine blades, by means of a wake production, transport, and interaction guasi-analog/digital system [AD-A0557511] B78-31118 A78-47402 TOBBINE BLADES TOBBOLEHT JETS Calculation of exchange coefficients for An experimental and numerical study of high-temperature turbine blades three-dimensional turbulent jets [ONERA, TP NO. 1978-104] A78-1I731I8 [AIAA PAPEE 78-994] A78-18471 Solution of an adjoint problem of steady-state TOBBIHG FLIGHT heat transfer associated with the cooling of Bank-to-turn /BIT/ autopilot technology for gas-turbine blades, by means of a missiles quasi-analog/digital system A78-49927 A78-»7il02 TWISTED SINGS Application of electrical analogy to the The influence of high twist on the dynamics of substantiation and comparison of some analytical rotating blades methods of determining temperature fields in A78-17599 gas-turbine blades T10 DIHENSIONAL FLOW A78-47404 Linearized theory of plane, unsteady, supersonic Gas path seal flow through a cascade - Subsonic part of the [NASA-CJSE-I,E»-12131-2] N78-31103 leading edge TOBBIHE ENGINES [ONEEA, TP NO. 1978-103] A78-47347 Effects of high availability fuels on combustor TWO PHASE FLOW properties Investigation of nonegailibrinm two-phase flows in [AD-A054229] N78-30259 axisymmetric Laval nozzles Gas path seal A78-48244 [NJSA-CB=E-LEW-12131-2] N78-31103 Turbine engine rotordynamic evaluation, volume 1 [AD-A055262] N78-31111

A-flO SUBJECT IHDEI VISUAL PEBCEPTION

Ground effects testing of two, three, and four jet configurations [AIAA PAPEB 78-1510] 478-U9789 ULTB&BIGB FSBQOEICIES V/STOL aircraft simulation - Beqniresents and Test and evaluation of air/ground communications capabilities at Ames Besearch center antennas [AIAA PAPEB 78-1515] A78-09790 [AD-A056118] N78-31325 An investigation of potential control-display UNSTEADY F10W configurations for V/STOL aircraft Linearized theory of plane, unsteady, supersonic [AIAA 78-1238] A78-50161 flow through a cascade - Subsonic part of the ViBIABLB CTCLE EBGINES leading edge Variable-cycle engine fighter aircraft: Advance [ONEBA, TP HO. 1978-103] A78-07317 in performance and development problems Unsteady hypersonic gas flow past a thin ving of H73-30109 finite span VARIABLE SWEEP BIHGS A78-U9792 Dynamics of the longitudinal motion of an airplane Linearized supersonic unsteady flov in cascades with a variable-geometry wing [ABC-B/H-3811] N78-30065 478-U9285 & theoretical study of the performance of a number 7ECTOHS (BATBEBiTICS) of different axial-flow turbine configurations Control system design using vector-valued under conditions of pulsating flow performance criteria with application to the [ABL/HECH-ENG-BEPT-109] 1178-31100 control rate reduction in parameter insensitive Investigations on unsteady pressure distribution control systems measurements in rotating systems [DLB-FB-77-55] S78-31125 [DLB-FB-77-H3] N78-31135 VERTICAL LANDING UNSTEADY STATE Shipboard launch and recovery of RPV helicopters Dse of ground vibration test equipment to in high sea states determine unsteady aerodynamic forces [AIAA 78-1269] J78-50179 A78-U9708 Navigation performance of the Triscan concept for DPPEB SDBFACE BLOSB FLIPS shipboard VTOL aircraft operations Calculation of the longitudinal aerodynamic [AIAA 78-1293] A78-50200 characteristics of upper-surface-blown wing-flap VEBTICAL TAKEOFF configurations The impact of contingency power concepts on V/STOL [NASA-CB-300U] N78-30050 aircraft take-off-gross-weight DPHASH [AIAA PAPEE 78-926] A78-18U51 Measurements and analysis of the forces acting on VERTICAL TAKEOFF ilBCBAFT a snail aircraft flying in the upwash of a large Navigation performance of the Triscan concept for aircraft shipboard VTOL aircraft operations [AD-A055286] N78-31018 [AIAA 78-1293] A78-50200 OSEB HAHOALS (COHPOTBB PBOGBABS) Wind-tunnel testing of VTOL and STOL aircraft EEXOR 2 rotorcraft simulation model. Volume 3: [ NASA-TH-78750] N78-30010 User's manual VEBI HIGH FBEQUBNCIES rNASA-CR-1«5333] N78-300UU TRACALS evaluation report. TACAN, VOE, and ILS APAL simulation facility/capability manual. station evaluation report, Andersen iPB, Guam Volume •*! Executive summary and systems [AD-A05124II] S78-30078 Avionics Division Test and evaluation of air/ground communications [AD-A055591] N78-31102 antennas [AD-A0561M8] N78-31325 VIBBATION Helicopter transmission vibration and noise 7/STOL AIHCBAfT reduction program. Volume 1: Technical report Nacelle effects on stability of 7STOL fAD-A05510«] N78-31089 configurations including conventional, canard, VIBRATION DARPIBG and tandem wing arrangements Helicopter rotor vibration isolation [A1AA PAPEB 78-150111 A78-17942 A78-U.9399 Experimental determination of propulsion induced Considerations on wing stores flutter: Asymmetry, ground effects of typical three fan type A flutter suppression V/ST01 configurations [AGARD-B-668] N78-31126 [AIAA PfPEB 78-1507] A78-"79t3 Demonstration of aircraft wing/store flutter >n analytical and experimental investigation of suppression systems diffusers for VSTOL thrust augmenting ejectors N78-31128 TAIAi PAPEE 78-1509] A78-U79H5 VIBBATIOB ISOLATORS Studies of aerodynamic technology for VSTOL Flutter suppressor for transonic flight fighter/attack aircraft [OKEBA, TP NO. 1978-102] ?78-«73q6 [AIA» PAPEB 78-1511] A78-U79H6 Helicopter rotor vibration isolation The impact of contingency power concepts on V/STOL A78-19399 aircraft take-off-gross-weight VIBBATION HEASOBEHENT [AIAA PAPEB 78-926] A78-18U51 Engine vibration in flight The effect of thrust vectoring and attitude [AIAA PAPEB 78-1U75] A78-U7921 control concepts on the propulsion system of VIBBATIOH TESTS V/STOL aircraft Experimental determination of the rattle of simple [AIAA PAPEB 78-1020] 478-18081 models Important simulation parameters for the [BASA-TH-78756] N78-30291 experimental testing of propulsion induced lift VISCOUS F10S effects An automated procedure for computing the [AIAA PAPEB 78-1078] A78-18H94 three-dimensional transonic flow over wing-body Evaluation of inlet reingestion for large bypass combinations, including viscous effects. Volume ratio V/STOL aircraft 1: Description of analysis methods and [AIAA PAPEB 78-1079] A78-08II95 applications Vectoring non-axisymmetric nozzle jet induced [AD-A055899] N78-31052 effects on a V/STOL fighter model VISUAL AIDS [AIAf PAPEB 78-1080] A78-H8096 Description and performance of the Langley visual The U.S. Navy bets on V/STOL technological landing display system integration for next generation aircraft design [NASA-TH-787U2] N78-30073 A78-19550 VISUAL PERCEPTION The influence of propulsion and control system Simulator study of the effect of visual-motion concepts on design of a Navy Type A V/STOL time delays on pilot tracking performance with airplane an audio side task [AIAA PAPEB 78-1505] A78-19788 [NASA-TP-1216] N78-30090 VISUAL TASKS SUBJECT ISDB7.

VISUAL TASKS ninimnm weight design of stiffened panels with Evalnation of several secondary tasks in the fracture constraints determination of permissible time delays in 478-1)9837 simulator visual and motion cues Fiber optic development for tactical fighter [NASA-TP-1211] N78-30089 applications VOLT-iHPEBE CHAHACTEBISTICS A78-19906 Impact of aircraft electrical power quality on WHEELS utilization equipment large deflection static analysis of typical 478-19962 tail-wheel structure of light aircraft by finite VOBTICES element method Trailing vortices. II A78-18861 478-17172 Analysis of a suspension system for a wheel Progress in propeller aerodynamics rolling on a flat track A78-H7173 [NASA-CR-157563] H78-30583 Engineering and development program plan: Hake BUD EFFECTS vortex Effects of wind on aircraft cruise performance fAD-J051113] N78-30071 [AIAA PAPEB 78-1496] A78-17937 Measurements and analysis of the forces acting on Approach guidance logic for a tilt-rotor aircraft a small aircraft flying in the upvash of a large [AIAA 78-1295] A78-50202 aircraft BIRD SBEAB fAD-A055286] F78-31018 Improving the accuracy of HOD approaches in windshear with a new control law [AIAA PAPEB 78-1191] A78-17935 w The airborne detection of low-level wind shear RAKES ~ [AIAA PAPEB 78-1195] A78-17936 Section drag coefficients from pressure probe WIID TUNNEL HODELS traverses of a ving wake at low speeds Analysis of stability contributions of high [AlfA PAPER 78-11179] 478-17921 dihedral V-tails Status of aerial applications research in the [NASA-TH-78729] N78-31011 Langley Vortex Besearch Facility and the Langley BIBD TDNNEI STSBIIITI TESTS full-scale wind tunnel Stability and performance characteristics of a [AIAA PAPEB 78-1181] A78-17926 fixed arrow wing supersonic transport Analysis of multistage, axial flow turbomachine configuration (SCAT 15F-9898) at Bach numbers wake production, transport, and interaction from 0.60 to 1.20 fBD-A055751] N78-31118 [HASA-TH-78726] B78-30087 WALL FLOS BIRD TUNNEL TESTS Asymptotic theory of a wing moving near a solid wall Some observations on the mechanism of aircraft A78-18218 wing rock WASHING SYSTEMS [AIAA PAPEB 78-1156] A78-17907 Infrared receiver performance airborne warning Wing/store active flutter suppression - system by detection of target spectral signature Correlation of analyses and wind tunnel data A78-19985 [AIAA PAPEB 78-1159] 478-17909 Experimental test plan for the evaluation of Status of aerial applications research in the aircraft separation assurance displays using Langley Vortex Besearch Facility and the Langley airline flight simulators full-scale wind tunnel [AD-A0558U9] N78-31131 [AIAA PAPEB 78-1181] A78-17926 WAVEGUIDES Aerodynamic hull design for HASPA LTA optimization Demonstration of the microwave ice protection High Altitude Superpressure Powered Aerostat concept Lighter Than Air rAD-A055821] U78-31096 A78-18100 BEAPON SYSTEMS Wind Tunnel/Flight Test Correlation Program on the Interface design considerations for F-16 sensors B-1 nacelle afterbody/nozzle at transonic and weapons conditions A78-19871 fAIAA PAPEB 78-989] A78-18469 Software structured weapon delivery Application of cryogenics in experimental A78-19875 aerodynamics Peace Bhine - A digital Weapon Control System for A78-18982 the P-1 aircraft Use of ground vibration test equipment to A78-19876 determine unsteady aerodynamic forces Digital avionics support - A retrospective view of A78-19708 the future Wind-tunnel testing of VTOL and STOL aircraft 178-19903 [NASA-TH-78750] N78-30010 Strapdown seeker guidance for tactical weapons Status of aerial applications research in the A78-39928 Langley vortex research facility and the Laagley nodular tarqet acguisition and designation systems full-scale wind tunnel A78-19951 [S4SA-TM-78760] N78-30011 F-*5 avionics Built-in-Test Static aerodynamic characteristics of a typical A78-i(9991 single-engine low-wing general aviation design Technical evaluation of flying weapon systems for an angle-of-attack range of -8 deg to 90 deg [RAE-LIB-TB1NS-1918] N78-31087 [NAS4-CB-2971] N78-30018 Program analyses for the S-3 weapon system Rotary balance data for a typical single-engine improvement program low-wing general aviation design for an [AD-A055887] N78-31093 angle-of-attack range of 30 deg to 90 deg BEAPOHS DKVE10PHEIIT [HASA-CB-2972] H78-30019 Technology analysis - Candidate advanced tactical Investigation of a wing-rotor interaction system fighters for helicopters [AIAA PAPEB 78-1U51] 178-09782 [AD-A051093] N78-30092 WEIGHT ANALYSIS F-15 inlet/engine test techniques and distortion The impact of contingency power concepts on V/STOL methodologies studies. Volume 1: Technical aircraft take-off-gross-weight discussion fAIAS PAPER 78-926} 178-18151 [NASA-CB-111866] N78-30123 •EIGHT BEDOCTIOB Experimental investigation of gust response of ferodynamic hull design for HASPA 1TA optimization hingeless helicopter rotors High Altitude Superpressure Powered Aerostat [AD-A051752] ' H78-30112 Lighter Than Air Two-dinensional subsonic wind tunnel evaluation of A78-18100 two related cambered 15-percent thick Evaluating avionics weight efficiency circulation control airfoils 478-18228 [AD-4055110] N78-31017

A-12 SUBJECT IHDEI ZIBCOHIOB 95

BIRD TOHBE1 »AllS Rhitcomb winglet applications to general aviation Induction of subsonic wind tunnels with slight aircraft perforation [AIAA PAPEB 78-1478] A78-47923 A78-U8250 RUGS BIHDSHIELDS On the linear superposition of aerodynamic forces Danping, static, dynamic, and inpact on wings in periodic gusts characteristics of laminated beans typical of A78-17869 windshield construction Modeling ground plane influence on wing [AD-A05H63] N78-30093 aerodynamic characteristics using a finite plane BIHG PIO» BBTHOD TESTS screen Asymptotic theory of a wing moving near a solid wall A78-48216 A78-1(82148 BOBK CAPACITY A method for localizing wing flow separation at Operator work capacity during parachutist free-fall stall to alleviate spin entry tendencies A78-47978 [AIAA PAPEB 78-1 476] A78-I19787 (IBS L01DIHG Trailing vortices. II A78-K7172 17-15 1IBCBAFT BIHG OSCILIATIOHS The promise of tilt rotor Some observations on the mechanism of aircraft A78-47266 wing rock [AIAA PAPEB 78-1156] A78-47907 BIHG PAHE1S Wing/store active flatter suppression - TAR Correlation of analyses and wind tannel data Evaluation of a circulation control tail boom for TAIAA PAPEB 78-1459] H78-47909 yaw control OH-6 helicopter BIHG PLAKPOBBS [AD-A055116] N78-31119 Lateral-aerodynamic characteristics of TTTBIDH-IBOB GiBHBT highly-dihedraled wings il frequency-selective TIG limiter for airborne A78-49334 FB/CB x-band radar Wing planforms for large military transports A78-50002 [AIAA PfPEB 78-1470] A78-49786 A calculator program for analyzing airloads on a wing of arbitrary planform and camber in subsonic flow ZIBCORIOB 95 [AD-A054180] H78-30058 On the use of zirconium 95 data from Chinese BISG PROFILES atmospheric thermonuclear explosions to study The effect on block fuel consumption of a strutted stratospheric transport in a one-dimensional versus cantilever wing for a short-haul parameterization transport including strut aeroelastic A78-48062 considerations [AIAA PAPEB 78-1454] A78-47905 Conceptual design study of power augmented ran wing in ground effect aircraft [AIAA PAPEB 78-1466] A78-47915 Section drag coefficients from pressure probe traverses of a wing wake at low speeds [AIAA PAPEB 78-11(79] A78-47924 Drones for aerodynamic and structural testing /DAST/ - A status report [AIAA PAPEB 78-11(85] A78-47929 Uniformly exact conformal transformation of exterior of circle onto exterior of wing profile A78-48224 Aerodynamics of the new generation of combat aircraft with delta wings H78-30106 WING SLOTS Influence of slots on effectiveness of wing mechanization and control surfaces with separated flow A78-48229 BIHG TANKS Flutter suppressor for transonic flight [ONEBA, TP HO. 1978-102] A78-47346 HIHG TIP TOBT1CES Status of aerial applications research in the Langley vortex Research Facility and the Langley full-scale wind tunnel [AIAA PAPEB 78-1181] A78-K7926 RING TIPS Heasurements and analysis of the forces acting on a snail aircraft flying in the upwash of a large aircraft [AD-A0552861 H78-31008 BIHG-FUSELAGE STORES Considerations on wing stores flutter: Asymmetry, flutter suppression [AGABD-B-668] N78-31126 Asymmetric store flutter H78-31127 Demonstration of aircraft wing/store flutter suppression systems H78-31128 SIHGLETS Gates Learjet Bodel 28/29, the first 'Longhorn' Learjet [AIAA PAPEB 78-1115] A78-K7901

i-13 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl 103) DECEMBER 1978

Typical Personal Author Index Listing

PERSONALAUTHOR ABDBE, I. L. BEiSLEI, I. LOGSOD - The fault-isolator An exploratory investigation of the effects of a A78-49239 thin plastic film cover on the profile drag of ANDREWS, J. I. |{ an aircraft wing panel IPC design validation and flight testing [HASA-TH-74073] H78-10023 [AD-A055529] H78-31074 1 ABGDE, G. B. 1 Transport Canada airfield pavement load evaluation A78-U9678 TITLE REPORT ASK, B. B. NUMBER Preliminary design of an accident Information Betrieval System (AIBS) [AD-A055590] N78-31952 ASPIIALL, J. H. Listings in this index are arranged alphabetically by personal author The title Solid-state displays for fuel management systems of the document provides the user with a brief description of the subject matter A78-M7900 The report number helps to indicate the type of document cited (eg NASA AOBOBA, B. report translation NASA contractor report) The accession number is located The U.S. Savy bets on 7/STO1 A78-49550 beneath and to the right of the title eg N78-10023 Under any one authors ADTET, B. G. name the accession numbers are arranged in sequence with the 1AA accession Fiber optic development for tactical fighter numbers appearing first applications A78-U9906 ABBAHSOH, J. Two-dimensional subsonic wind tunnel evaluation of B two related cambered 15-percent thick BABIAK, H. J. circulation control airfoils Digital avionics support - A retrospective view of [AD-\055140] R78-31047 the future ADOLPB, C. E. A78-49903 Integrated test mission control - Present and BAEBST, C. F. future at the Air Force Plight Test Center Study of fuel systems for lH2-fueled subsonic [AIAA PAPER 78-11161] A78-47911 transport aircraft, volume 1 AKSBROV, 0. B. [NASA-CB-145369-VOL-1] S78-31085 Superelement method for helicopter fuselage analysis Study of fuel systems for IH2-fueled subsonic A78-48209 transport aircraft, volume 2 ALBBECHT, B. [SASA-CR-1U5369-V01-2] S78-31086 Investigation of electrostatic discharge in BAILLIE, I. L. G. aircraft fuel tanks during refueling Design philosophy for airframes TAIAA PAPER 78-1501] A78-U79U1 A78-t7153 ALEXAHDEB. J. D. BAIBD, G. f. Design philosophy for engine forgings Proposed load evaluation system for U.S. Air Force A78-47U52 A78-B9677 ALLISOH, D. 0. BAKBB, A. A. Shockless airfoils with thicknesses of 20.6 and Fibre composite reinforcement of cracked aircraft 20.7 percent chord analytically designed for a structures Hach number of 0.68 and a lift coefficient of 0.40 H78-30288 [NASA-TH-X-73917] N78-30046 BAKBB, L. C. ALTHOF, R. Turbine tip clearance measurement The influence of the environment on the [AD-A055765] N78-31115 elastoplastic properties of adhesives in metal BALIS-CEEHA, L. bonded joints Air traffic control in the terminal area - Dse of [DLR-FB-77-63] H78-31251 a simulation technique for the definition of an ALTIS, B. D. operative model Fighter superiority by design A78-U9733 H78-30105 BALL, J. H. ALRAHG, J. B. Rolling tail design and behavior as affected by Enqine/airframe/dnve train dynaaic interface actuator hinge moment limits documentation [AIAA PAPEB 78-1500] A78-Q79UO [JSD-A055766] S78-31114 BilLHJOS, B. T. ABOS, 8. An automated procedure for computing the Program analyses for the S-3 weapon system three-dimensional transonic flow over wing-body improvement program combinations, including viscous effects. Volume [AD-A0558871 H78-31093 1: Description of analysis methods and AHDBBSON, S. B. applications A method for localizing wing flow separation at [AD-A055899] H78-31052 stall to alleviate spin entry tendencies BiHBEB, B. D. [AIAP PAPEB 78-1476] A78-49787 Section drag coefficients from pressure probe AHDEBSSOH, L. traverses of a wing wake at low speeds laboratory testing of lightning and EHP [AIAA PAPEB 78-1U79] A78-47924 susceptibility of avionic systens BABBBB, E. A. A78-I19861 Prospects for conmercial coamonality in military AHDEBTOH, G. L. transports The design process [AIAA PAPEB 78-1467] A78-49784 [AIAA PAPEE 78-1183] A78-H7928

B-1 BABHES, i. G. PERSONAL AOTHOB INDEX

BABNES, A. G. Rotary balance data for a typical single-engine Air-to-air combat simulation low-wing general aviation design for an A78-17868 angle-of-attack range of 30 deg to 90 deg The design of a high g cockpit [NASA-CB-2972] N78-300H9 F78-30118 BIKCHANT1E7, H. KB. BABHHART. B. Analysis of GTE tolerance monitoring parameter Static aerodynamic characteristics of a typical formation single-engine low-wing general aviation design A78-18212 for an angle-of-attack range of -8 deg to 90 deg BIKLB. P. 1. [N&SA-CH-2971] N78-30018 Section drag coefficients from pressure probe B1BSBT, 3. E. traverses of a wing wake at low speeds Calculations of the effects of bloving from the [AIAA PAPER 78-1179] A78-17921 leading edges of a cambered delta wing BIKORSKI, J. [ARC-R/H-3800] H78-30061 Preliminary design of an accident Information BARTON. J. H. Retrieval System (AIRS) An experimental and numerical study of [AD-A055590] H78-31952 three-dimensional turbulent jets BILL, B. C. [AIAA PAPER 78-994] A78-18171 Gas path seal BASD, B. C. [NASA-CASE-LEH-12131-2 ] N78-31103 A mean camberline singularity method for BILODBAO, A. A. two-dimensional steady and oscillatory aerofoils Evaluation of methods for calculating system and control surfaces in inviscid incompressible operating time in accordance with Reliability flow Improvement Warranty (RIH) contractual terms [ABC-CP-1391] N78-30066 [AD-A051822] H78-30079 Two-dimensional aerofoils and control surfaces in BINBIE, f. B. simple harmonic motion in incompressible Flight investigation and theory of direct inviscid flow side-force control [ARC-CP-1392] N78-30D68 [AIAA 78-1287] A78-50191 BitJEB, E. BIRCH, S. P. On the use of zirconium 95 data from Chinese An experimental and numerical study of atmospheric thermonuclear explosions to study three-dimensional turbulent jets stratospheric transport in a one-dimensional [AIAA PAPER 78-991] A78-18171 parameterization BISCHOFF, D. E. A78-U8062 Maximum likelihood identification of the BBAL, T. B. longitudinal aerodynamic coefficients of the Guidance and control problems in semiautomatic EA-6B airplane in the catapult launch recovery of the Aguila BPV configuration [AIAA 78-1272] A78-50182 [AD-A051213] N78-31016 BEAVER, B. H. BLAND, L. H. Peace Rhine - A digital Weapon Control system for Aircraft structural life monitoring and the the F-1 aircraft problem of corrosion A78-19876 N78-30281 BECKBAN, I. B. BLATTBEB, D. G. L-1011 flight data recording systems - Background, Prospects for commercial commonality ID military features, implications and benefits transports [AIAA PAPEB 78-1171] A78-17917 [AIAA PAPEB 78-1167] A78-19781 BELL, G. 0. BOGATKO, V. T. firfield pavement load evaluation - An Unsteady hypersonic gas flow past a thin wing of international overview finite span A78-19676 A78-U9792 BBHDEB, G. L. BOBN, H. P. Modified helicopter icing spray system evaluation Aerodynamics of the new generation of combat [AD-A055039] H78-31091 aircraft with delta wings BENNETT, G. N78-30106 The role of the computer in the flight testing of BOISSEVAIN, A. G. general aviation aircraft Quiet, Short-Haul Research Aircraft - Current [AIAA PAPEB 78-1U65] ^78-17911 status and future plans BENSON, J. L. [AIAA PAPER 78-1168] A78-17916 Propulsion system airframe integration studies - BOLBOT, A. A. Advanced supersonic transport Communication and navigation antennas for aircraft [AIAA PAPEB 78-1053] A78-18188 A78-18523 BEBKSTBESSEB, B. K. BOLLIRGEB, L. Integrated avionics for future general aviation Requirements for regional short-haul air service aircraft and the definition of a flight program to [AIAA PAPER 78-11182] A78-17927 determine neighborhood reactions to small BEBBAH, B. transport aircraft Improved combat survivability for fly-by-wire [HASA-CR-152151] N78-30070 sensor systems BOBELLO, L. fAIAA 78-1277] A78-50186 Design of a horizontal tail unit and related BEBBT, T. adjustments Experimental test plan for the evaluation of A78-19736 aircraft separation assurance displays using BOBGEB, ». 0. airline flight simulators Application of rare earth/transition metal [AD-A055819] N78-31131 permanent magnets to 100 Hz aircraft systems - BESEB, J. An AF overview Approach guidance logic for a tilt-rotor aircraft A78-19935 [AIAA 78-1295] A78-50202 BOBGBI, B. BETEBLY, B. B. Methods available to ONERA for analysis of Short-term performance deterioration in combustion chambers JT9D-7A(SP) engine 695713 [ONEBA, TP NO. 1978-93] A78-16915 [HASA-CR-135131] N78-30121 BOSCH, J. A. BIHBLE, »., JS. Software development for fly-by-wire flight Static aerodynamic characteristics of a typical control systems single-engine low-wing general aviation design [AIAA 78-1276] J78-50185 for an angle-of-attack range of -8 deg to 90 deg BOSE, S. C. [HASA-CB-2971] N78-30018 Real-time simulators for augmented inertial navigation systems A78-19967

B-2 PEBSOHAl iOTHOB IHDEX BDBTOB, 6. T.

BOTTIGLIEBI, C. BBIEL, D. Air traffic control in the terminal area - Use of Simultaneous measurements of ozone outside and a simulation technique for the definition of an inside cabins of two B-717 airliners and a Gates operative nodel Learjet business jet A78-19733 [BASA-TR-78983] B78-31061 BOOCBABD, B. J. BBIGGS, P. Short-tern performance deterioration in Software development for fly-by-wire flight JT9D-7A(SP) engine 695713 control systems [NASi-CB-135131] H78-30121 [AIAA 78-1276] A78-50185 BOODBEAO, J. BRIBDLEI, J. F. Improved combat survivability for fly-by-wire The second generation of high-bypass turbofans - £ sensor systems market clouded by uncertainty CAIA4 78-1277] A78-5Q186 A78-17123 BOBEBS, D. L. BBISTOV, D. B. Bind Tunnel/Flight Test Correlation Program on the Modification of the Douglas Neumann program to B-1 nacelle afterbody/nozzle at transonic improve the efficiency of predicting component conditions interference and high lift characteristics [AIAi PAPEB 78-989] A78-18169 [HASA-CB-3020] 1178-30051 BOWLES, J. V. BBOCE, L. Application of advanced high speed turboprop Preliminary design of an accident Information technology to futare civil short-haul transport Betrieval System (AIRS) aircraft design [AD-A055590] H78-31952 [AIAf PAPEB 78-H87] 478-17930 BBOD2KI, Z. Regnirements for regional short-haul air service Progress in propeller aerodynamics and the definition of a flight program to A78-17173 determine neighborhood reactions to small BROBDZ, I. D. transport aircraft Extending the service life of aircraft components fNASA-CR-152151] B78-30070 made of high-strength steels BOBHAH, J. S., JB. A78-18518 Correlation of model and airplane spin BBOTHEBBOOD, P. characteristics for a low-wing general aviation Flight neasurements of the effects of simulated research airplane leading-edge erosion on helicopter blade stall, [AIAA PAPEB 78-1477] A78-17922 torsional loads and performance BOYD. G. B. [ABC-B/B-3809] H78-30098 InterScan - A new microwave approach and landing BBOUGHTOH, B. B. guidance system B-1 flight test progress report A78-18736 [AIAA PJPEB 78-1118] A78-17903 BBJDLEY, J. B., JB. BBOBH, C. E. Dulles control tower console design study Measurements and analysis of the forces acting on fAD-A056200] H78-31132 a small aircraft flying in the upwash of a large BBAGG, 8. B. aircraft Status of aerial applications research in the [AD-A055286] H78-31018 Langley vortex Research Facility and the Langley BBOBH, D. L. full-scale wind tunnel Prediction of angular disturbances fron airframe [AIAA PAPEB 78-1181] A78-47926 members to airborne electro-optical packages Status of aerial applications research in the A78-49952 Langley vortex research facility and the Langley BBOBB, D. H. full-scale wind tunnel Flight measurements of the effects of simulated [NASA-Tn-78760] N78-30011 leading-edge erosion on helicopter blade stall, BH1SDE4U, G. torsional loads and performance Evolution of a cost-effective, task-oriented, [AHC-B/R-3809] H78-30098 lateral-directional SAS for the A-10 aircraft BBOBi, B. [AIAA PAPEB 78-1160] \78-17910 Application of the General Purpose Multiplex BBAHDIH, 0. B. System to the A-7E avionics In-flight alignment/calibration techniques for A78-19867 unaided tactical guidance A standard programmable I/O for the advanced A78-19929 aircraft electrical system power control set BBAHH, A. J. A78-19936 Reliability of inertial navigation systems BBOBB, L. E., JB. A78-19968 The HiHAT BPB7 system BBiTT, R. H. [AIAA PAPEB 78-1157] A78-17908 Technology analysis - Candidate advanced tactical BBOTOB, B. A. fighters Structural fatigue testing [AIAA PAPEB 78-1151] A78-19782 N78-30279 BRAON, C. L. BOLLEI, F. P. A flight simulation high order language study A model of crack-tip behaviour for fatigue life A78-19957 determination BBEEB, R. D. F78-30286 Boundary layers in axisymmetric inlets at angle of BOBBABS, B. B. attack. I - Reasorements Phase-locked tracking loops for LORAN-C [AIRA PAPEB 78-1109] A78-18199 [NASA-CR-157582] H78-31068 BBEIDSHBACH, D. P. BORK, S. H., JB. Effect of performance objectives on the design and Correlation of model and airplane, spin cost of future BSAP pilot training aircraft characteristics for a low-wing general aviation [AIAA PAPEB 78-1198] A78-17938 research airplane BBEBEB, G. D. [ilAi PAPEB 78-1177] A78-17922 Study of fuel systems for LH2-fueled subsonic BOBHAB, Z. I. transport aircraft, volume 1 Superelement method for helicopter fuselage analysis [HAS&-CB-115369-VOL-1] H78-31085 A78-18209 Study of fuel systems for LH2-fueled subsonic BDBBS, fi. C. transport aircraft, volume 2 Haiti-Function Inertial Beference Assembly /HIRA/ [NASA-CR-1U5369-VOL-2] H78-31086 update BBEZA, R. J. A78-199U1 The terrain following task for the advanced BOBHSIDE, i. 0. tactical fighter using discrete optimal control Volumetric pattern analysis of airborne antennas A78-19862 A78-19127 BOBTOB, 6. T. HBSD demonstration model development [AD-A051137J B78-30120

B-3 CALLAS, G. P. PEBSONiL AOTBOB IBDEI

CLOUD, E. L. Nodular Hissionization Systems /MBS/, an adaptive system interface concept CALLAS, S. P. A7 8-19 852 Integrated avionics for fatnre general aviation COBB, E. B. aircraft Center-loaded duct integral rocket-to-ramjet [AIAA PAPEB 78-1182] A78-47927 transition testing CALLER, T. ft. [AIAA PAPEB 78-937] A78-18456 Strapdown seeker guidance for tactical weapons COCBBARE, 3. 1. A78-49928 Quiet, Short-Baul Research Aircraft - Current CANDBL, S. status and future plans -- Theoretical and experimental studies of acoustic [AIAA PAPEB 78-1468] 478-47916 propagation in inhomogeneons moving media COLARTOHIO, 1. [ESA-TT-477] N78-30909 Ose of a field bench for testing turbojet engines CAPONE, F. J. A78-19731 Aerodynamic characteristics induced on a COLE, L. G. supercritical wing due to vectoring twin nozzles Constant false alarm rate detector for a pulse at Bach numbers from 0.10 to 0.95 radar in a maritime environment [NASA-TH-78716] N78-30039 A78-49975 CJPOHE, L. A. COHPITELLO, F. E. An assessment of the effect of supersonic aircraft Propulsion test facilities - Capabilities and use operations on the stratospheric ozone content [AIAA PAPEB 78-933] A78-48153 [HASA-RP-1026] N78-30771 CORLOR, J. A. CAPBILI, 8. Application of advanced high speed turboprop P method for determining the stability technology to future civil short-haul transport characteristics of aircraft in a helicoid flight aircraft design path [AIAA PAPEE 78-1187] A78-17930 A78-19711 CORBAD, E. S. CiPOTO, E. J. NASA engine system technology programs - An overview Aircraft electrical system testing and data [AIAA PAPEB 78-928] A78-18152 reduction using digital techniques CORBOW, B. B. A78-49937 A parametric analysis of TEHCOB false fix CABADORRA, F. X. probability The transonic flow on a helicopter rotor A78-19997 N78-31042 COOLEY, D. E. CABDEB, H. D. Close encounters of the aeroservoelastic kind Improved aircraft dynamic response and fatigue [AIAA 78-1289] A78-50196 life during ground operations using an active COBBIN. J. C., JB. control landing gear system Electromagnetic coupling analysis of a Learjet [AIAA PAPEB 78-1199] A78-17939 aircraft in a lightning environment CABBOIL, J. T. A78-19920 Radiographic examination of T55 engine COBBEGE, G. [AD-A055108] N78-31113 New structures made of composite materials for CASiEOSA, C. high performance combat aircraft A method for determining the stability N78-30114 characteristics of aircraft in a helicoid flight COUCH, B. P. path Detecting abnormal turbine engine deterioration A78-19711 using electrostatic methods Takeoff performance of STOL aircraft [AIAA PAPEE 78-1173] A78-17919 A78-19711 COYLE, J. J. CEBSI. 0. P. Test and evaluation of air/ground communications Subsystem verification of an AFLC organically antennas developed F-15 simulation [AD-A056148] N78-31325 A78-119901 CBEEL, T. B., JB. CHEATDH, T. G. Aerodynamic characteristics of a hypersonic Interface design considerations for F-16 sensors research airplane concept having a 70 deg swept and weapons double-delta wing at Hach number 0.2 A78-19874 [NASA-TP-1252] N78-31045 CHEN, I. CBBWS, L. L. Trajectory optimization for some sailplane Software structured weapon delivery performance problems A78-49875 N78-31083 CBOSS, S. B. CHER, P. P. Performance in a jamming environment of a low-cost Accuracy requirement and cost effectiveness of GPS user receiver algorithm for aiding a GPS-aided INS for tactical fighters tactical INS A78-19989 [AD-A055239] N78-31078 CHER, P.-I. CBOSSGBOVE, fl. A. Constant false alarm rate detector for a pulse MIL-STD-1553B proposed radar in a maritime environment A78-19866 A78-49975 CBOBCH, B. I. CHEBTKOV&, I. IA. An experimental and numerical study of Effect of jet fuel antooxidation products on three-dimensional turbulent jets thermooxidation stability [AIAA PAPEB 78-991] A78-48471 A78-19025 CBORBLL, H. A. CHILD, R. D. The design process Canard configured aircraft with 2-D nozzle [AIAA PAPEB 78-1183] A78-47928 [AIAA P».PER 78-1150] A78-47904 CORRIRGTOR, G. B., JB. CHISTIAKOY, F. 1C. Study of fuel systems for LB2-fueled subsonic Definition of airplane fuselage longitudinal lines transport aircraft, volume 1 by the special contour method [HASA-CB-145369-VOL-1] N78-31085 A78-18222 Study of fuel systems for LH2-fueled subsonic CL1T, B. B. transport aircraft, volume 2 BHSD demonstration model development [RASA-CB-145369-TOL-2] N78-31086 [AD-1054137] N78-30120 CDBTISS, H. C., JB. CLOSE, D. B. A study of the precision hover capabilities of the Advanced pattern matching for navigation and aerocrane hybrid heavy lift vehicles guidance [AD-A054281] N78-30091 A78-19998

B-4 PEBSOIAl AOTHOB IBDEI ECKSTEOH, C. V.

CWYHAB. D. S. DEHKSCHBBZ, B. Procedures for generation and redaction of linear Display systems and cockpit design models of a turbofan engine B78-30116 [HASA-TP-1261] H78-30896 DEBTOR, H. B. Plight deck display trends A78-47899 DESJABDIBS, B. A. D4BBS, B. S. Helicopter rotor vibration isolation Metal technology for future aircraft design 478-49399 B78-30115 DESTOYHDEB, B. DAHLEH, Y., Ill Flatter suppressor for transonic flight Snpercruiser fighter analysis [OBEBA, IP BO. 1978-102] 478-47346 H78-30107 DEIST, J. J., JB. DALE!, E. Highly snrvivable integrated avionics AIDS in military aircraft 478-49163 A78-47866 DILLOH, J. 1. DALLAS, J. Aerodynamic characteristics of a hypersonic Test and demonstration prototype tracked air research airplane concept having a 70 deg swept cushion vehicle (PTACV): Phase IIIC double-delta wing at Hach number 0.2 [PB-279970/8] 1178-31007 [HAS4-TP-1252] B78-31045 DALLOST4, P. H. DOBBS. H. 9. Evaluation of methods for calculating system Hinimum weight design of stiffened panels with operating time in accordance with Eeliability fracture constraints Improvement warranty (BIS) contractual terms 478-49837 [AD-A054822] 878-30079 DOHIFGOEZ BODEIGDEZ, I. D&VIDSOH, J. Operational regularity in air transport A standard programmable I/O for the advanced 478-49449 aircraft electrical system power control set DOR, J. P. A78-49936 Let's put fuel efficiency into perspective DAVIES, 1. E. 478-47269 AIDS in engine management programmes DOHHIHG, J. B. A78-47865 4 systems approach to heliport lighting DAVIS. G. S. 478-49238 Study of fuel systems for IH2-fueled subsonic DBiGO, B. J. transport aircraft, volume 1 Helicopter transmission vibration and noise [BASA-CE-145369-VOL-1] B78-31085 reduction program. Volume 2: User's manual Study of fuel systems for lH2-fneled subsonic [4D-4054827] B78-30095 transport aircraft, volume 2 Helicopter transmission vibration and noise [BASA-CR-145369-VOL-2] H78-31086 reduction program. Volume 1: Technical report DAVIS, J. A. [AD-4055104] B78-31089 Sensor technology for turbine engine monitoring DEEVPOSS, D. 3. systems Estimated costs of extended low-rate airframe FAIAA PAPER 78-11711] 478-47920 production DiZZO, J. J. [AD-4051834] B78-31100 Synthesis of digital flight control systems by the DEOGIB, E. I. method of entire eigenstructure assignment Digital system architecture for a 1980's jammer A78-49864 478-49973 DECREE, J. P. DONHiB, J. Stability and performance characteristics of a Intake design for fighter aircraft fixed arrow wing supersonic transport B78-30110 configuration (SCAT 15F-9898) at Hach numbers DDBBIHG, S. J. from 0.60 to 1.20 Infrared receiver performance [BASA-TH-78726] N78-30087 A78-49985 DEEL, 0. DOBSSOETH, I. C. Engineering data on new aerospace materials Ramjet engine testing and simulation techniques structural materials [4144 PAPER 78-935] 478-48455 [AD-A054461] 878-30213 DOBEBBEBGES, D. DBGTIABEV, 6. I. Some sound transmission loss characteristics of Optimal control synthesis in distributed systems typical general aviation structural materials with incomplete information [4IA4 PAPER 78-1480] 478-47925 A78-148215 DDTOY4, D. DEJ4BBETTE, P. B. Calculation of exchange coefficients for Investigation of a wing-rotor interaction system high-temperature turbine blades for helicopters [OKEB4, TP SO. 1978-104] 478-47348 [AD-JO5H093] H78-30092 DYRES. B. S. DELAHDSTY, A. Test and demonstration prototype tracked air AIDS in military aircraft cushion vehicle (PTACV): Phase IIIC 178-47866 [PB-279970/8] H78-31007 DELAORIEB, J. DZIGADLO, Z. Lateral-aerodynamic characteristics of Dynamics of the longitudinal motion of an airplane highly-dihedraled wings with a variable-geometry wing \78-4933

B-5 EDSOH, B. PEBSONAL AOTBOB INDEX

EDSOH, B. FEISTBL, T. W. Improved aircraft dynamic response and fatigue A method for localizing wing flow separation at life during ground operations using an active stall to alleviate spin entry tendencies control landing gear system [AIAA PAPEE 78-1476] A78-49787 [AIAA PAPEB 78-1199] J78-47939 FSIT, L. B. EDBABDS. J. ». Close encounters of the aeroservoelastic kind A hierarchical network for avionic systems [AIAA 78-1289] A78-50196 A78-49868 FEHDEB, J. B. EDBABDS, B. B. Material evaluation of polyurethane foam, 0.05 g/ A farther survey of some effects of aircraft noise cm 3 density in residential communities near London [BDX-613-1836-REV] N78-31249 (Heathrow) airport FILOSOFOV, V. K. [TT-7705] 1178-30910 Operator work capacity during parachutist free-fall EHBICB, B. D. A78-47978 Strapdown seeker guidance for tactical weapons FIFNEY, J. S. A78-49928 Fatigue S/N data in relation to variability in ELBEE, K. predicted life Becent developments in analysis of crack N78-30278 propagation and fracture of practical materials Load interaction effects in fatigue crack [NAS4-TM-78766] N78-30606 propagation EBEBSOI. B. N78-30285 Digital simulation and flight verification of the FISHEB, D. F. F-5E/F Plight Director Computer Flight experience on the need and use of inflight 478-49905 leading edge washing for a laminar flow airfoil EBMBBT. B. I. [AIAA PAPEE 78-1512] 478-47947 Bank-to-turn /BIT/ autopilot technology FITZSIBHOIS, B. D. 478-19927 Advanced supersonic transport engine integration EBH, L. studies for near-term technology readiness date A theoretical study of the performance of a number [AIAA PAPEB 78-1052] A78-48487 of different axial-flow tnrbine configurations FLOOD, 3. D. under conditions of pulsating flow Important simulation parameters for the [ABL/HECH-ENG-HEPT-149] N78-31104 experimental testing of propulsion induced lift EBBOLEIKO, S. D. effects Modeling ground plane influence on wing [4IAA PAPEB 78-1078] £78-48494 aerodynamic characteristics using a finite plane FOGGIE, F. B. screen Advances in inertial navigation A78-U82-6 A78-47U81 EBZBEBGBB. B. FOBD, D. G. Characteristics of constrained optimum The development of the theory of structural fatigue trajectories with specified range N78-30283 [NASA-TH-78519] N78-30072 FOBD, H. J. BOLBICH, B. J. Advanced optical blade tip clearance measurement ?n investigation of potential control-display system configurations for V/STOI aircraft [NAS4-CB-159402] N78-31106 [AIAA 78-1238] 478-50161 FOBTEHBADGH, B. L. EVELYN, 6. B. Nacelle effects on stability of VSTOL Propulsion for future supersonic transports - 1978 configurations including conventional, canard, status and tandem wing arrangements [AIAA PiPEB 78-1051] A78-48486 [AIAA PAPEB 78-1504] J78-47942 FOOH8IEB, B. B. Static aerodynamic characteristics of a winged single-stage-to-orbit vehicle at Hach numbers FAEBT, B. P., JB. from 0.3 to 4.63 Hhitcomb winglet applications to general aviation [NASA-TP-1233] N78-30053 aircraft FBEED, H. H. [AIAA PAPEB 78-1*78] A78-47923 The role of system performance analysis in the FAIRING, A. E. independent assessment of B-1 navigation software Advance nozzle technology A78-49902 N78-30111 FBEEBAI, C. E. PANT, K. Analysis of stability contributions of high Autothreshold autoscreener/FLIS system dihedral V-tails 478-49984 [SASA-TH-78729] N78-31044 FABMEB, B. G. FBEEBAI, D. C., JB. Demonstration of aircraft wing/store flutter Static aerodynamic characteristics of a winged suppression systems single-stage-to-orbit vehicle at Mach numbers N78-31128 from 0.3 to 4.63 FABBELL, J. I. [NASA-TP-1233] N78-30053 Air-to-air designate/track with time sharing FBICK, J. A78-119977 An automated procedure for computing the FEDOTOV, B. B. three-dimensional transonic flow over wing-body Method of calculating aerodynamic coefficients of combinations, including viscous effects. Volume soBe three-dimensional bodies with arbitrary 1: Description of analysis methods and cross section applications 478-118245 [AD-A055899] N78-31052 FEHEB, K. FBIIK, H. T. Heguirements for regional short-haul air service Investigation of a wing-rotor interaction system and the definition of a flight program to for helicopters determine neighborhood reactions to small [AD-A054093] N78-30092 transport aircraft FOLLEB, A. B. [NASA-CB-15215'] N78-30070 The feasibility of estimating avionics support FEHEB, B. E. costs early in the acquisition cycle. Volume 1: A preliminary comparison of thermal decomposition The basic report products of aircraft interior materials using [AD-A054016] N78-30119 the National Bureau of Standards smoke chamber FDHK, J. E. and the combustion tube furnace The terrain following task for the advanced [AD-A054811] N78-30088 tactical fighter using discrete optimal control 478-49862

B-6 PEBSOHAL A0TBOB IHDBI HABBOCK, H. S.

FOZIK, H. I. GBIFFIH, B. B. Probabilistic nodel of an instrument landing system Fundamentals of Honouring sealants for aircraft A78-47407 fuel tanks [AD-A054627] B78-30247 GRIFFITH, S. L. Investigation of a wing-rotor interaction system GABBLE, i. C. for helicopters Transport Canada airfield pavement load evaluation [AD-A05U093] H78-30092 A78-II9678 GRIBAK, L. F. GABOB. B. i. Operator work capacity dnring parachutist free-fall General aviation airplane structural A78-17978 crashvorthiness user's manual. Volume 1: GBIBB, K. S. Program KBASH theory Scan-linited near field testing for directive [AD-A055898] N78-31088 airborne antennas GABBOHG, G. A78-49897 Study of fuel systems for LH2-fneled subsonic GBOSE, G. G. transport aircraft, volume 1 Modification of the Douglas Neumann program to [HASA-CH-145369-VOL-1 ] U78-31085 improve the efficiency of predicting component Study of fuel systems for LH2-fueled subsonic interference and high lift characteristics transport aircraft, volume 2 [HASA-CR-3020] H78-30051 CSASA-CH-KI5369-VOL-2] N78-31086 GEOSSBAB, B. L. GAOKHOGEB, D. fi. Vectoring non-axisymmetnc nozzle jet induced Measurement of vibratory displacements of a effects on a V/STOL fighter model rotating blade [AIAA PAPEB 78-1080] A78-48496 A78-19397 Design evolution of a supersonic cruise GEOKEZAS, H. strike-fighter Autothreshold autoscreener/FLIR system [AIAA PAPER 78-1452] A78-49783 A78-49984 GBOSVBLD, F. GEBTSEH, R. fl. Some sound transmission loss characteristics of Gates Learjet Hodel 28/29, the first 'Longhorn1 typical general aviation structural materials Iear3et [AIAA PAPEB 78-1480] A78-47925 [AIAA PAPEB 78-1445] R78-47901 A research program to reduce interior noise in GEVAEBT, G. general aviation airplanes: Investigation of Shipboard launch ana recovery of HPT helicopters the characteristics of an acoustic panel test in high sea states facility [AIAi 78-1269] A78-50179 [NASA-CB-157587] N78-31871 GILBEATB, fl. C. GOZIAEV, V. V. Volumetric pattern analysis of airborne antennas Influence of slots on effectiveness of wing A78-191)27 mechanization and control surfaces with GLAZONOV, A. A. separated flow Investigation of nonegnilibrinm two-phase flows in A78-48229 axisyametric Laval nozzles GDBEEV, A. A. A78-48244 Effect of jet fuel autoozidation products on GODPBET, J. T. thermooxidation stability Capture effect array glide slope guidance study A78-49025 [AD-A055678] H78-31073 GOETZ, G. F. Non-axisymmetnc nozzle design and evaluation for H F-111 flight demonstration HACKEE, T. [AIAA PAPER 78-1025] A78-48483 Constant-control rolling maneuver GOGOLIN, T. P. A78-46961 Evaluating avionics weight efficiency BAIDT. J. A78-48228 AFAL simulation facility/capability manual. GOLDIE, B. Volnme 1: Executive summary and Systems A freguency-selective TIG limiter for airborne Avionics Division FH/CB X-band radar [AD-A055591] 1178-31102 A78-50002 HilUBS, t. L. GOLDSCHBIED, F. B. Parameters of future ATC systems relating to Aerodynamic hull design for HASPA LTA optimization airport capacity/delay A78-48100 [AD-A055482] S78-31130 GONZALEZ CRISTOBAL, t. H1ISLIP, D. T. An integrated analysis of the fundamental problems The Omega radionavigation system comes to the of air transport Pacific Ocean area A78-49447 A78-U9660 GOODB, B. B. BALE, A. L. Simulation and flight evaluation of a head-up Structural dynamics, stability, and control of landing aid for general aviation helicopters [HASA-TP-1276] N78-31101 [NASA-CB-158909] B78-30139 GBADT, G. E. BALE, F. J. Turbine tip clearance measurement Effects of wind on aircraft cruise performance [AD-A055765] N78-31115 [AIAA PAPER 78-1496] A78-47937 GRAVES, G. L. BALLBB, H. B. Laboratory testing of lightning and EBP Computer program for vibration prediction of susceptibility of avionic systems fighter aircraft equipments A78-49861 [AD-A054598] H78-30094 GREESE, B. A. BABBOCK, B. S. The airborne detection of low-level wind shear F-15 inlet/engine test techniques and distortion [AIAA PAPER 78-1195] A78-17936 methodologies studies. Volnme 1: Technical GBIB, A. A. discussion Unsteady hypersonic gas flow past a thin wing of [NASA-CB-144866] S78-30123 finite span F-15 inlet/engine test techniques and distortion A78-19792 methodologies studies. Volnme 2: Time variant GBIBB, B. data guality analysis plots Variable-cycle engine fighter aircraft: Advance [SASA-CB-144867] N78-30124 in performance and development problems F-15 inlet/engine test technigoes and distortion H78-30109 methodologies studies. Volnme 3: Power spectral density plots [NASA-CB-144868] N78-30125

B-7 HAHPTON, T. I. PERSONAL AOTBOB IHDEX

F-15 inlet/engine test techniques and distortion BIGGISBOTHAH, B. methodologies studies. Volume 1: Multiprocessing for electronic warfare avionics Autocorrelation functions 178-19869 [NASA-CR-111869] N78-30126 HILEY, P. E. F-15 inlet/engine test techniques and distortion Installed performance of vectoring/reversing methodologies studies. Volume 5: Effect of non-axisymmetric nozzles filter cutoff frequency on turbulence plots [AIAA PAPER 78-1022] A78-18182 [NASA-CR-111870] N78-30127 HILL, R. G., JB. F-15 inlet/engine test techniques and distortion Ground impingement of a fan jet exhaust plume methodologies studies. Volume 6: Distortion [AD-A051832] N78-31112 analysis plots HILTON, D. A. fNASA-CR-111871] N78-30128 An acoustic range for the measurement of the noise F-15 inlet/engine test techniques and distortion signature of aircraft during flyby operations methodologies studies. Volume 7: Cross A78-17212 correlation functions. HIRSCHKROH, B. [NASA-CR-111872] H78-30129 Energy efficient engine: Preliminary design and F-15 inlet/engine test techniques and distortion integration studies methodologies studies. Volume 8: Cross [NASA-CR-135111] N78-31108 spectral density plots BIBSINGER, F. [NASA-CR-111873] N78-30130 Methods available to OHERA for analysis of F-15 inlet engine test techniques and distortion combustion chambers methodologies studies. Volume 9t Stability [ONER1, TP NO. 1978-93] A78-16915 audits HOFHAHI, L. G. [NASA-CR-111871] H78-30131 Digital control law synthesis in the w prime domain HAHPTON, I. L. A78-16962 Design for durability - The F101-GE-100 engine HOBBYCOTT, B. E. [AIAA PAPER 78-1081] A78-18197 Advanced optical blade tip clearance measurement HAHCOCK, 6. J. system Two-dimensional aerofoils and control surfaces in [NASA-CR-159U02] 1178-31106 simple harmonic motion in incompressible HOOKE, F. H. inviscid flow Safety against fatigue in flight: A perspective [ASC-CP-1392] H78-30068 of Australian experience and research HANNAH, B. N78-30272 IPR aircraft handled forecast by air route traffic Aircraft structural reliability and risk theory: control center, fiscal years 1978-1989 A review [AD-A019305] N78-31075 N78-30281 HABDBATH, B. F. HOOPEB, 8. E. Recent developments in analysis of crack Helicopter rotor vibration isolation propagation and fracture of practical materials A78-19399 [BASA-TH-78766] H78-30606 HOPKINS, A. L., JB. HABDT, G. H. Highly survivable integrated avionics Integrated avionics for future general aviation A78-19163 aircraft BOSKIN, B. C. [AIAA PAPER 78-1482] A78-07927 Fracture mechanics fundamentals with reference to HABE, E. W. aircraft structural applications COHED - The cockpit display of the future N78-30271 A78-17268 BOSTETLER, L. D. HARRIS, B. F. Optimal terrain-aided navigation systems A study of analog programming for prediction of [AIAA 78-1213] A78-50163 crack growth in aircraft structures subjected to HOTTNEB, I. random loads Application of cryogenics in experimental [AD-A055789] N78-31097 aerodynamics HABBIS, B. I., SB. A78-18982 Simulation and flight evaluation of a head-up HODGHTOH, D. E. A. landing aid for general aviation Air-to-air combat simulation [HASA-TP-1276] N78-31101 A78-17868 HARTLEY, H. f. HOIABD, P. J. Captnre effect array glide slope guidance study Development of a load sequence for a structural [AD-A055678] H78-31073 fatigue test BASSiL, C. J. W. H78-30277 neasurement of vibratory displacements of a HOSELLS, B. B. rotating blade Helicopter transmission vibration and noise A78-19397 reduction program. Volume 2: User's manual HEA1Y, B. D. [AD-J051827] N78-30095 Station deselection procedures to support Helicopter transmission vibration and noise automatic Omega receiver operation reduction program. Volume 1: Technical report A78-19965 [AD-A055101] N78-31089 HENDERSON, H. R. HOBABS, F., JB. An acoustic range for the measurement of the noise A hierarchical network for avionic systems signature of aircraft during flyby operations A78-19868 A78-17212 HOESCHEN, B. H. HENDEBSON, W. P. Guidance and navigation for automatic landing, Canard configured aircraft with ?-D nozzle rollout, and tnrnoff using HLS and magnetic [AIAA PAPEB 78-111505 A78-17901 cable sensors HENDBICKSOR, B. H. [AIAA 78-1296] A78-50203 Design evolution of a supersonic cruise HDGHES, I. strike-fighter Preliminary design of an accident Information [AIAA PAPER 78-1152] A78-19783 Retrieval System (AIRS) HERTZBBBG, A. [AD-A055590] N78-31952 A laser-powered flight transportation system HOLTBERG, B. S. [AIAA PAPER 78-1181] A78-19781 Rotary balance data for a typical single-engine HEWISB, H. low-wing general aviation design for an Airliner numbers game - Does it add up angle-of-attack range of 30 deg to 90 deg A78-19521 [NASA-CR-2972] N78-30019 HETSON, H. H. HDHTER, L. B. B. Wind-tunnel testing of VT01 and STOl aircraft Transport Canada airfield pavement load evaluation [NASA-TH-78750] N78-30010 A78-19678

B-8 PEBSOJAL SOTHOB IHDEI KIBHAPPEL, K.

BOTCBISOB, H. H. JOBISOH, T. H. Fibre conposite reinforcement of cracked aircraft A qualitative analysis of redundant asynchronous strnctures operation S78-30288 A78-09863 HUTTSELL, 1. J. JOEBSTOH, E. H. Ding/store active flatter suppression - Technology analysis - Candidate advanced tactical Correlation of analyses and wind tunnel data fighters [AIAA PAPEB 78-1059] A78-17909 [1IAA PAPEH 78-1151] A78-09782 Close encounters of the aeroservoelastic kind JOB US-PON, 8. P. [AIAA 78-1289] A78-50196 Energy efficient engine: Preliminary design and HB4HG, C. integration studies Some observations on the mechanisn of aircraft [8ASA-CB-135100] B78-31108 wing rock JOBES, H. L. [AIAA PAPEB 78-11(56] A78-07907 Comparisons of high anti-jam design techniques for Demonstration of aircraft wing/store flatter GPS receivers suppression systems A78-U9857 H78-31128 JOBES, J. L. Application of the General Purpose Multiplex System to the A-7E avionics A78-U9867 IGOBIB, V. I. JOBES, B. B. Solution of an adjoint problem of steady-state Gas turbine engine emissions - Problems, progress heat transfer associated »ith the cooling of and future gas-turbine blades, by means of a A78-09336 gnasi-analog/digital system JOBES, W. S. A78-07U02 A laser-powered flight transportation system Application of electrical analogy to the [HAi PAPER 78-1180] A78-H9781 substantiation and cooparison of some analytical JOBDAB, F. L., JB. methods of determining temperature fields in Status of aerial applications research in the gas-turbine blades langley Vortex Research Facility and the Langley A78-07000 full-scale wind tunnel ILHIISKII, L. IA. [AIAA PAPEB 78-1081] A78-07926 Probabilistic model of an instrument landing system Status of aerial applications research in the A78-17007 Langley vortex research facility and the Langley Communication and navigation antennas for aircraft full-scale wind tunnel A78-48523 [SASA-TB-78760] N78-30001 IRONS. J. J. The use of the AIAA-Bendix Design Competition in aerospace design courses K [AIAA PAPER 78-11488] A78-17931 KADISHBV, I. K. ISKHAK07, I. JL. Aviation control system devices Evaluating avionics weight efficiency A78-tt9850 A78-08228 KAHCHI, J. S. IVEBSOB. H. W. Propulsion test facilities - Capabilities and use Nodular target acquisition and designation systems [1IAA PAPEB 78-933] A78-08153 A78-09950 KABISS, A. B. Statistical review of counting accelerometer data for Navy and Marine fleet aircraft from 1 January 1962 to 31 December 1977 JACKSOH, C. I., JB. [AD-A055672] N78-31098 Integrated avionics for future general aviation KAPLDB, A. B. aircraft Fatigue crack growth in pressurized fuselage panel [AIA* PfPEB 78-11182] A78-U7927 A78-08231 JACOBS, P. F. KEE, E. Stability and performance characteristics of a Application of the General Purpose Multiplex fixed arrow wing supersonic transport System to the A-7E avionics configuration (SCAT 15F-9898) at Nach lumbers A78-09867 from 0.60 to 1.20 KELLY, B. J. [HASA-TH-78726] N78-30087 Landing aircraft under poor conditions JACOBSOB, I. D. J78-09509 Bide gnality evaluation. IV - Models of subjective Comparison study of MLS airborne signal processing reaction to aircraft motion techniques A78-U7U90 A78-09900 Hodel of aircraft passenger acceptance KELLY, B. T. A78-09680 Optimal terrain following controller for an Demand modelling of passenger air travel: An optimized spline reference path analysis and extension, volume 2 [AD-A055230] B78-31122 [HASA-CR-1571102] N78-30069 KESKAB, D. A. JIBES, B. 6. Approximate indicial lift function for tapered, Fading at 9.6 GHz on an experimentally simulated swept wings in incompressible flow aircraft-to-ground path [SASA-TP-1201] N78-30050 J78-19039 KHACHiTOEIiNTS, L. S. JEHKIRS, B. C. Safety of space flights Ground impingement of a fan jet exhaust plume A78-U7952 [AD-A050832] N78-31112 Operator work capacity during parachutist free-fall JOBS, C. E. A78-07978 iing planforms for large military transports KHOBOLSKII, V. H. tAIAA PAPEB 78-1070] A78-H9786 Application of electrical analogy to the JOHNSON, B. S. substantiation and comparison of some analytical Advanced supersonic transport engine integration methods of determining temperature fields in studies for near-tern technology readiness date gas-turbine blades [AIAA PAPEB 78-1052] A78-08087 A78-07000 JOHBSOH, H. V. KHBOBOV, E. V. HASA engine system technology programs - An overview Safety of space flights CAIAA PAPER 78-928] A78-98H52 A78-07952 JOHNSON, P. E. KIESAPPEL, K. Propulsion for future supersonic transports - 1978 Investigations on unsteady pressure distribution status measurements in rotating systems tAIAA PAPEB 78-1051] A78-08H86 [DLB-FB-77-H3] N78-31135

B-9 KIKOCHI, a. PEBSOHAL AOTBOB IRDEX

KIKOCHI, B. BEXOB 2 rotorcraft simulation model. Volume 2: Neutralization problem for a Space Shuttle Computer implementation X78-I1712I) [SASA-CB-1H5332] 878-30013 KIHBEBLBY, D. BEXOB 2 rotorcraft simulation model. Volume 3: A pyramid skewed axis sensor set for multiple! Dser's manual flight control systems [NASA-CB-115333] 1178-30011 CAHC-B/H-3808] N78-30113 KBOEGEB, B. A. KITZHILLEB. D. E. A method for localizing wing flow separation at Installed performance of vectoring/reversing stall to alleviate spin entry tendencies non-axisymmetnc nozzles [AIAA PAPEB 78-1176] A78-19787 fAIAA PAPER 78-1022] A78-18182 KBOEKEB, B. KLEIREBT, H.-J. Lateral-aerodynamic characteristics of 10 years of contract research for the highly-dihedraled wings pump/compressor industrial concern >73-19331 A78-19175 KBOTOV, V. I. KLILCHKIB, A. 1. Experimental determination of parameters of Operating characteristics of bypass turbojet engines mathematical model of airplane cabin as A78-50125 regulated object with respect to air temperature KLIR6EB, G. in the cabin The influence of the environment on the A78-18231 elastoplastic properties of adhesives in metal KBTZHAI07SKII, G. A. bonded joints Optimization technigues for air traffic control [DLB-FB-77-63] N78-31251 problems KLOETZLI, J. «. ?78-«8501 Measurements and analysis of the forces acting on KUBBAT, I. 3. a small aircraft flying in the upwash of a large Design and development of a multifunctional aircraft helicopter control system [AD-A055286] H78-31018 A78-19396 KLOS, L. C. Advanced control concepts for future fighter »n interface management approach -to software aircraft development N78-30101 A78-19933 KOIPEBS, J. KOCH, C. C. Twoway - A position and orientation measurement Energy efficient engine: Preliminary design and system integration studies A78-19661 [NASA-CB-135111] H78-31108 KDLFAR, B. H. KOBGLEB, J. C, Hing planforms for large military transports IPC design validation and flight testing [AI»A PAPEB 78-1170] A78-19786 [AD-A055529] H78-31071 KDLIEV, 7. D. KOESIG, S. B. Fatigue crack growth in pressurized fuselage panel Analysis of runway occupancy times at major airports A78-18231 [AD-A056052] N78-31131 KDPHIIAHOV, I. I. KOLESRIKOV, G. B. Communication and navigation antennas for aircraft Operator work capacity during parachutist free-fall A78-18523 A78-17978 KDZBETSOV, R. D. KOLTOH. G. A. Aspects of the thermal fatigue strength of Unsteady hypersonic gas flow past a thin wing of gas-turbine engine components finite span A78-19176 A78-49792 KOPPELHAH, B. Multiprocessing for electronic warfare avionics A78-i(9869 LABEBGE, E. F. C. KOSTIH, 1. C. Comparison study of HLS airborne signal processing Wind Tunnel/Flight Test Correlation Program on the techniques B-1 nacelle afterbody/nozzle at transonic A78-19901 conditions LACBOIX, D. [AIAA PAPEB 78-989] A78-18169 French procedures for airfield pavement load KOTELRIK07, G, R. evaluation Distribution of reliability characteristics among A78-19679 airplane system units to ensure given flight IAHPABD, G. 8. R. safety level The effect of thrust vectoring and attitude A78-18221 control concepts on the propulsion system of KOOETIDES, D. I. V/STOL aircraft Assessment of relative flammability and HIIA PAPEB 78-1020] A78-U8081 thermochenical properties of some thermoplastic LARDGBAF, B. C. materials 4 flight qualified graphics generator A78-19693 A78-50007 KOSALSKI, S. H. USE, B. E. Avionics cost development for alternatives of Flight controls of Army/Hughes YAH-61 advanced selected air traffic control systems attack helicopter [AD-A051823] N78-30080 [AIAA 78-1237] A78-501CO KOZHEVHIKOy, tO. V. tARG, L. E. Analysis of GTE tolerance monitoring parameter F-15 avionics Built-in-Test formation A78-19991 A78-18212 LABGE, J. p. KBAEREB, J. V, Estimated costs of extended low-rate airframe In-flight alignment/calibration techniques for production unaided tactical guidance [AD-A051831] S78-31100 A78-II9929 LABSON, B. KBBISSBLHBIBB, G. futothreshold autoscreener/FlIB system Control system design using vector-valued A78-19981 performance criteria with application to the LAZZERETTI, B. control rate reduction in parameter insensitive A method for determining the stability control systems characteristics of aircraft in a helicoid flight fDlB-FB-77-55] N78-31125 path KBBTSIBGEB, P, H. A78-19711 BEXOB 2 rotorcraft simulation model. Volume 1: LEAKE, B. J. Engineering documentation Alternatives for jet engine control [HASA-CB-1145331] H78-30012 [HASA-CB-157578] N78-31107

B-10 PEBSOBSL ADTHOB IHDEI BCCLOB6, D. A.

IEBACQZ. J. V. BAGEBHEIB, B. An investigation of potential control-display Demonstration of the microwave ice protection configurations for V/STOL aircraft concept [AIAA 78-1238] 478-50161 [AD-A055821] H78-31096 LECCE, L. BABGABO, 6. J. Ose of ground vibration test equipment to Botor burst protection program: Statistics on determine unsteady aerodynamic forces aircraft gas turbine engine rotor failures that A78-I19708 occurred in DS commercial aviation during 1975 LECKHAB, P. [HASA-CB-135301] B78-31105 The role of the computer in the flight testing of BABB, J. T. general aviation aircraft Fatigue S/B data in relation to variability in [AHA PAPEB 78-1165] &78-17911 predicted life LEE, H. B78-30278 Characteristics of constrained optimua BiBB, H. 3. trajectories with specified range Theoretical estimation of the transonic [BASi-TB-785"i9] H78-30072 aerodynamic characteristics of a LELIOSBEBKO, S. I. supercritical-wing transport model with Definition of airplane fuselage longitudinal lines trailing-edge controls by the special contour method [FASA-TP-1253] H78-30056 478-18222 BABOB, D. LBHSKI, J. »., JB. Bhitcomb winglet applications to general aviation Helicopter transmission vibration and noise aircraft redaction program. Volume 2: User's manual [AliJ PAPEB 78-1178] A78-17923 [AD-AC51827] H78-30095 BABCHHAS, 3. f.. Ill Helicopter transmission vibration and noise Rhitcomb winglet applications to general aviation redaction program. Volune 1: Technical report aircraft [AD-A055101] N78-31089 [AIAA PiPEB 78-1178] A78-17923 LEONJED, K. C., JB. The use of the AIAA-Bendiz Design Competition in Modular Bissionization Systems /BBS/, an adaptive aerospace design courses system interface concept [AIAi PAPEB 78-1188] A78-17931 A78-198S2 HABBVTSBV1, H. 1. LEONG, P. J. Induction of subsonic wind tunnels with slight Dynamic analysis of electrical systems perforation A78-19931 A78-18250 HBAGE, C. B. BARBEFKA, B. J. Evaluation of inlet reingestion for large bypass Prospects for commercial commonality in military ratio V/STOL aircraft transports [AI?A PAPER 78-10791 A78-18195 [AIAA PAPEB 78-1167] A78-19781 LINN, B. J. B1HBOH, B. G. •Supermarket1 airplanes Graphics for the hybrid stores separation [AIAA PIPER 78-15331 A78-U9769 simulation of the B77 system LISZKA, L. [SASD-78-8212] B78-31099 Long-distance focusing of Concorde sonic boon B1RQDIBA SAHCHEZ, L. A78-98052 Poise in airports, its measurement, and its effect IQGAB, A. B. on the communities in the vicinity Evaluation of a circulation control tail boom for A78-18371 yaw control RABTIB, D. L. [AD-A055116] H78-31119 Application techniques for digital flight control LQBEBZIHl, D. A. systems Havstar GPS field test results N78-30117 A78-19856 HABOSZKIE8ICZ, 3. LOTZB, A. Dynamics of the longitudinal motion of an airplane Asymmetric store flutter with a variable-geometry wing H78-31127 A78-19285 LOVEIL, B. A. BASOB, H. B. Design of a large span-distributed load An automated procedure for computing the flying-wing cargo airplane with laminar flow three-dimensional transonic flow over wing-body control combinations, including viscous effects. Volume [NASf-CK-115376] B78-30015 1: Description of analysis methods and LOBE, J. B. applications Improving the accuracy of HDD approaches in [AD-A055899] N78-31052 windshear vith a new control law HATHEiS, B. S., Ill [AIAA PAPE8 78-1191] A78-17935 Bodified helicopter icing spray system evaluation LIICKEIBG, 3. B. [AD-A055039] K78-31091 Theoretical estimation of the transonic BATSOIAHA, G. T. aerodynamic characteristics of a A computerized undergraduate aircraft design course supercritical-wing transport model with [AIAA PAPEB 78-1192] A78-17933 trailing-edge controls HATYSEK, T. E. [NASJ-TP-1253] N78-30056 The versatility of Jovial J73 in avionics systems LODWIG. I. P. A78-19956 Gas path seal BADCH, B. B. [NASA-CASE-LEW-12131-2] N78-31103 Turbine tip clearance measurement LTHCH, S. P. [AD-A055765] H78-31115 Hechanisms of fatigue and fracture HATFIELD, J. P. H78-30273 Software engineering a must for success in computerized flight test [AIAA PAPEB 78-1163] A78-17913 M BCCABTHT, J. F., JB. BACDOHSLD, T. J. A study of analog programming for prediction of Comparisons of high anti-jam design techniques for crack growth in aircraft structures subjected to GPS receivers random loads A78-19857 [AD-A055789] H78-31097 BACKBBZIB, D. BCCLDBG, D. A. An automated procedure for computing the A Costas loop with tangent error signal for use in three-dimensional transonic flow over wing-body Bavstar GPS avionics combinations, including viscous effects. Volume A78-19858 1: Description of analysis methods and applications [AD-A055899] S78-31052

B-11 BCDANIE1, ». C. PEBSOIAL AUTHOB IHDEI

BCDAHIEL, ». C. BIHHICK, J. I. Antitorgue training: Evaluation of effectiveness Operations and economics of n.S. air transportation in reducing mishap losses [AIAA PAPER 78-1505] A78-19770 [AD-A055010] N78-31092 BIYASBIBO, S. K. HCGEE, 1. A. Navigation performance of the Tnscan concept for Navigation performance of the Tnscan concept for shipboard VTOL aircraft operations shipboard VTOL aircraft operations [AIAA 78-1293] A78-50200 [AIAA 78-1293] 178-50200 BOFFATT, H. B. I1CGEHEE, J. B. Preliminary design of an accident Information Improved aircraft dynamic response and fatigue Retrieval System (AIRS) life during ground operations using an active [AD-A055590] N78-31952 control landing gear system BOHACO, B. [AIAA PAPER 78-11199] A78-U7939 On the theory of drag calculation and profile HCGBHEE, B. B. optimization in shockless near free molecular flow Bank-to-turn /BIT/ autopilot technology A78-47887 A78-49927 BOHAKHOV, H. B. BCGINHESS, H. Uniformly exact conformal transformation of Analysis of a suspension system for a wheel exterior of circle onto exterior of wing profile rolling on a flat track A78-18224 [NASA-CB-157563] B78-30583 BOHTGOBERT, H. A. BCIBTOBFF. J. ». Approach for identifying avionics flight software Engine vibration in flight operational support requirements - PAVE TACK an UIAA PAPER 78-1H75] A78-H7921 example BCKILLIP, B. B., JB. A78-49900 ?. study of the precision hover capabilities of the BOBTGOBEBY, B. C. aerocrane hybrid heavy lift vehicles A learning flight control system for the P8-DPBH [AD-A054281] H78-30091 aircraft BCLBBOBE, B. C. [AIAA 78-1288] ' A78-50195 Status of aerial applications research in the BOHTOYA, L. C. langley Vortex Research Facility and the langley Section drag coefficients from pressure probe full-scale wind tunnel traverses of a wing wake at low speeds [AIAA PAPER 78-1»81] A78-47926 [AIAA PAPER 78-1U79] A78-U792U Status of aerial applications research in the BOORE, J. R. Langley vortex research facility and the langley Conceptual design study of power augmented ram full-scale wind tunnel wing in ground effect aircraft [NASf-TH-78760] N78-300<41 [AIAA PAPER 78-11)66] A78-47915 BCHABY, C. A. BOORE, B. A. Advanced pattern matching for navigation and Capture effect array glide slope guidance study guidance [AD-A055678] N78-31073 A78-I19998 BORGAB, J. D. HEHDI, I. S. The feasibility of estimating avionics support Dynamic analysis of electrical systems costs early in the acquisition cycle. Volume 1: A78-i|993i| The basic report BEIBOTITCH, I. [AD-A051016] N78-30119 Structural dynamics, stability, and control of BOBBIS, B. E. helicopters Study of fuel systems for LH2-fueled subsonic [NASA-CR-158909] N78-30139 transport aircraft, volume 1 KEKEL, B. [HASA-CB-1H5369-VOL-1] N78-31085 1 learning flight control system for the F8-DPBW Study of fuel systems for LH2-fueled subsonic aircraft transport aircraft, volume 2 [AHA 78-1288] A78-50195 [NASA-CR-1«5369-VOL-2] N78-31086 BENDENHALL, H. B. BOBBIS, S. J. Calculation of the longitudinal aerodynamic Computer program for the design and off-design characteristics of upper-surface-blown wing-flap performance of turbojet and turbofan engine cycles con figurations [NASA-TH-78653] N78-30122 [NASA-CR-3001] N78-30050 BOSES, C. A. HEYBB, D. D. Effects of high availability fuels on combustor The design process properties [AIAA PAPEB 78-1U83] A78-U7928 [AD-A050229] N78-30259 BICBABD, P. BOOSSALLY, G. J. Calculation of exchange coefficients for Capture effect array glide slope guidance study high-temperature turbine blades [AD-A055678] N78-31073 [ONERA, TP NO. 1978-10U] A78-«73t8 BDDD, L. E. BIKHAILOV, A. i. Airfield pavement evaluation - PAA viewpoint Influence of slots on effectiveness of wing A78-09681 mechanization and control surfaces with BOLCAY, R. separated flow Rotary balance data for a typical single-engine H78-18229 low-wing general aviation design for an BIHEB, G. E. angle-of-attack range of 30 deg to 90 deg The influence of throttle augmented stability [NASA-CB-2972] N78-300U9 (APCS) and short period control characteristics BORDBH, «. P. on the landing approach Fighter superiority by design [AD-A055892] S78-31123 S78-30105 BIIIER, G. K., JB. BDRBAT, J. J. Evaluation of several secondary tasks in the Investigation of a wing-rotor interaction system determination of permissible time delays in for helicopters simulator visual and motion cues [AD-A050093] N78-30092 [NASA-TP-121II] N78-30089 BURBOi, B. H. Simulator study of the effect of visual-motion Drones for aerodynamic and structural testing time delays on pilot tracking performance with /DAST/ - A status report an audio side task [AIAi PAPER 78-1H85] A78-K7929 [NASA-TP-1216]' H78-30090 BOSSELKBITE, B. A. BILLEB, I. E. The impact of contingency power concepts on V/STOL Supercruiser fighter analysis aircraft take-off-gross-weight N78-30107 [AIAA PAPEB 78-926] A78-08U51 BIHHBTT, H. C. BYEBS, T. D. InterScan - A new microwave approach and landing Ground test facility for integral rocket ramjets guidance system [AIAA PAPEB 78-931] A78-«8«5<1 A78-U8736

B-12 PEBSOBAL AOTHOB IBDEI PEBDEEGBiFT, O. C., JB.

OLIYEB, B. C. On the use of zirconium 95 data from Chinese N atmospheric thermonuclear explosions to study BACBBIAS, S. stratospheric transport in a one-dinensional A learning flight control system for the F8-DFBW parameterization aircraft 478-18062 [4144 78-1288] A78-50195 OLLEBHEAD, J. B. HAEGELI, D. B. *, further survey of sone effects of aircraft noise Effects of high availability fuels on combustor in residential communities near London properties (Heathrow) airport [AD-A051229] H78-30259 [TT-7705] H78-30910 SAGASHIHA, T. 4 comparison of annoyance caused by aircraft noise Linearized sapersonic unsteady flow in cascades near London, Hanchester and Liverpool airports [4RC-B/H-3811 ] H78-30065 [TT-7706] H78-30911 BAPOLITJHO, L. 6. OEBSBY, C. C. Bemite closed splines High-accuracy three-dimensional image A78-19713 reconstruction for an airborne line-scanning NEIGBBOB, T. I. system RPV flying gnalities design criteria 478-19988 [AIA> 78-1271] A78-50181 OBBIHGEB, 0. BEITZEL, B. E. A study of analog programming for prediction of Energy efficient engine: Preliminary design and crack growth in aircraft structures subjected to integration studies random loads rsJSA-CB-1351111 N78-31108 [1D-4055789] N78-31097 NELHS, W. P. OSTAPKOBICZ, 8. Studies of aerodynamic technology for VSTOL Operation of oil seales of aircraft piston engines fighter/attack aircraft under conditions of cavitation. I [AIAA PAPEB 78-1511] 478-17946 A78-»7175 HELSOH. B. B. Rinimum weight design of stiffened panels with fracture constraints A78-19837 PACE, S. 1. BEHEC, C. Bazard assessment of aircraft gun compartments Air-to-air designate/track tilth time sharing [4D-4055026] H78-31061 A78-19977 PAIHTEB, J. H. HBBHABH. G. A Costas loop with tangent error signal for use in The influence of the environment on the Navstar GPS avionics elastoplastic properties of adhesives in metal 478-09858 bonded joints PABTASOB, P. [DLR-FB-77-63] H78-31251 Static aerodynamic characteristics of a typical NEWHAB, J. C., JR. single-engine low-wing general aviation design Becent developments in analysis of crack for an angle-of-attack range of -8 deg to 90 deg propagation and fracture of practical materials [BSS4-CE-2971 ] H78-300I18 [SASA-TH-78766] H78-30606 PARK, I. B. HIELSEB. J. P. The effect on block fuel consumption of a strutted Proposed load evaluation system for O.S. Air Force versus cantilever wing for a short-haul 478-19677 transport including strut aeroelastic SIHGAIAH considerations load interaction effects in fatigue crack [SIAA PAPEB 78-1051] 478-47905 propagation PABKEB. J. 4. H78-30285 Assessment of relative flammability and BISBT, H. I. thermochemical properties of some thermoplastic Influence of slots on effectiveness of wing materials mechanization and control surfaces with A78-H9693 separated flow PATCBIHG, C. 1. A78-18229 Structural fatigue testing HII, P. W. H78-30279 TRACALS evaluation report. TACAH, VOR, and IIS PATBL, H. B. station evaluation report, Andersen AFB, Guam On the linear superposition of aerodynamic forces [AD-A051211] B78-30078 on wings in periodic gusts NOLL, T. E. A78-U7869 Sing/store active flutter suppression - PATTOB, J. B., JB. Correlation of analyses and wind tunnel data Correlation of model and airplane spin fAIAA PAPEB 78-1159] A78-U7909 characteristics for a low-wing general aviation Close encounters of the aeroservoelastic kind research airplane [AIAA 78-1289] A78-50196 [6IAA PAPER 78-1177] 478-17922 Demonstration of aircraft wing/store flutter PATHS, A. 0. suppression systems Current developments in the life of aircraft K78-31128 structure BOBDLDBD, B. E. B78-30280 Advanced optical blade tip clearance measurement PiTBTEB, G. C. system An experimental and numerical study of [NASA-CB-15914021 178-31106 three-dimensional turbulent jets BDGEHT, J. [AI44 PAPER 78-991] 478-18171 Status of a nozzle-airframe study of a highly PECK, K. I. maneuverable fighter Engine vibration in flight fi!4A PAPEB 78-990] 478-18170 [AIA4 PAPEB 78-1175] 478-17921 PELED, 0. The effect of prefilter design on sample rate selection in digital flight control systems OKIISBI, T. H. (AIAA 78-1308] 478-50209 Analysis of multistage, axial flow turbomachine PEHDBBGBAFT, O. C., JB. wake production, transport, and interaction Status of a nozzle-airframe study of a highly [40-4055754] H78-31118 •anenverable fighter [4144 PAPEB 78-990] 478-18170

B-13 PEHLABD, J. A. PBBSOHAL iOTHOB IBDEI

PEHLA8D, J. A. POTVAB, R. F. Aerodynamic characteristics of a hypersonic A study of the precision hover capabilities of the research airplane concept having a 70 deg s»ept aerocrane hybrid heavy lift vehicles double-delta wing at Hach number 0.2 [AD-A05U281] 878-30091 [BASA-TP-1252] 878-31015 PEEDDE. E. B. Dual band airborne SATCOH terminal Q A78-19972 QDAETESO, C. B. PEBDZOCK, J. H. Design of a large span-distributed load Bulti-Fnnction Inertial Reference Assembly /HIBA/ flying-wing cargo airplane with laminar flow update control A78-19911 [SASA-CR-115376] N78-30015 PEBKIHS, J. B. QOEIJO, B. J. Ipplication of the General Purpose Hultiplex Approximate indicial lift function for tapered, System to the A-7E avionics swept wings in incompressible flow A78-19867 [BASA-TP-1211] H78-30051 A standard programmable I/O for the advanced QDIGLEY, B. C. aircraft electrical system power control set V/STOL aircraft simulation - Beguirements and A78-19936 capabilities at Ames Besearch Center PEBKINS, P. J. [AIAA PAPEB 78-1515] A78-H9790 Simultaneous measurements of ozone outside and QOIBB, G. F. inside cabins of two B-717 airliners and a Gates Effect of performance objectives on the design and learjet business jet cost of future DSAF pilot training aircraft [BASA-TB-78983] H78-31061 [AIAA PAPEB 78-1198] A78-17938 PEBBT. B., Ill Control-surface hinge-moment calculations for a bigh-aspect-ratio supercritical wing [BASA-TH-78661] 878-31013 BADGORSKI, E. PETEBSOH, J. B., JR. Investigation of electrostatic discharge in Flight experience on the need and use of inflight aircraft fuel tanks during refueling leading edge washing for a laminar flow airfoil [AIAA PAPEB 78-1501] A78-17911 [AIAA PAPEB 78-1512] A78-17917 RAJO, P. B. PETIT, J. B. Large deflection static analysis of typical Hon-aiisymmetric nozzle design and evaluation for tail-wheel structure of light aircraft by finite P-111 flight demonstration element method [&IAA PAPEB 78-1025] A78-18183 A78-1886H PHILLIPS, 8. H. BAHET, B. L. Simulation study of the oscillatory longitudinal Fighter superiority by design motion of an airplane at the stall 878-30105 [BASA-TP-1212] 878-30111 BABSDEB, J. B. PI, R. S. Birage 2000 - Dassault's better delta Some observations on the mechanisn of aircraft J78-19169 wing rock BEADET, B. J., JB. [AIAA PAPBB 78-1156] A78-17907 Center-loaded duct integral rocket-to-ramjet PIHES, S. transition testing Guidance and navigation for automatic landing, [AIAA PAPEE 78-937] 178-18156 rollout, and tnrnoff using HLS and magnetic BEASEB, J. S. cable sensors REXOR 2 rotorcraft simulation model. Volume 1: [AIAA 78-1296] A78-50203 Engineering documentation PITTHiH, B. [BASA-CR-115331] N78-30012 A modular adaptive, variable function flight BEXOB 2 rotorcraft simulation model. Volume 2: control sensor Computer implementation [AD-A055175] N78-31120 [8ASA-CR-115332] H78-30013 POK, C. C., JE. EEXOR 2 rotorcraft simulation model. Volume 3: Becent developments in analysis of crack User's manual propagation and fracture of practical materials [NASA-CB-115333] N78-30011 [BASA-TH-78766] H78-30606 BEDLIER, B. R. POPPOFF, I. G. Landing aircraft under poor conditions An assessment of the effect of supersonic aircraft A78-19519 operations on the stratospheric ozone content BEED, G. J. [SASA-BP-10261 878-30771 Ramjet engine testing and simulation techniques POBTEB, B. [AIAA PAPER 78-935] A78-48155 Synthesis of digital flight control systems by the BEED, R. C. method of entire eigenstructure assignment Dse of the 0.S. interim standard microwave landing A78-19861 system in Canada PORELL, J. D. J78-19333 The effect of prefilter design on sample rate REEVE, R. B. selection in digital flight control systems Software design for a Visually-Coupled Airborne (AIAA 78-1308] A78-50209 Systems Simulator (VCASS) PBABBAKAB, A. [AD-A055226] N78-31133 Stability of a helicopter carrying an nnderslnng BEIBAOD, J. load Flight application of optical fiber transmission A78-149398 on a Falcon 10 aircraft PEICE, E. A., JB. [ONERA, TP BO. 1978-105] A78-17319 Rind Tunnel/Flight Test Correlation Program on the BEIBIBGEB, B. C. B-1 nacelle afterbody/nozzle at transonic A Costas loop with tangent error signal for use in conditions Navstar GPS avionics [AIAA PAPEB 78-9891 A78-18169 A78-19858 PBICE, J. E. BEIQOAB, E. T. Design of a large span-distributed load Impact of aircraft electrical power quality on flying-wing cargo airplane with laminar flow utilization equipment control A78-19962 [NASA-CB-115376] 878-300115 SETCHFOBD, J. A. PBZYJEHSKI, J. H. A model of crack-tip behaviour for fatigue life A compensation technique for acceleration-induced determination frequency changes in crystal oscillators 878-30286 A78-19859

B-11 PEBSOJAL AOTBOB IBDEI SCBSIDT, ». B.

BEVIIL. G. ». B01IIBS, 3. D. Load interaction effects in fatigue crack Description and performance of the Langley visual propagation landing display system H78-30285 [BASA-TH-78742] H78-30073 BEVOK, A. G. BOSK!I, J. Probabilistic model of an instrument landing systea Sone sound transmission loss characteristics of 178-971107 typical general aviation structural materials BETBOLDS, P. T. [AIAA PAPEB 78-1480] A78-17925 Gates Learjet Nodel 28/29, the first 'longhorn' A research program to reduce interior noise in Learjet general aviation airplanes: Noise reduction [AIAA P4PEB 78-1445] A78-47901 through a cavity-backed flexible plate BBODES, G. F. [BASA-CB-157588] H78-31873 Damping, static, dynamic, and mpact BOBE, I. T. characteristics of laminated beans typical of Advanced supersonic transport engine integration windshield construction studies for near-term technology readiness date [AD-A054463] H78-30093 [AIAA PAPEB 78-1052] A78-48487 BIABOI, 4. IA. BOZHDESTVEHSKII, K. V. Extending the service life of aircraft components Asymptotic theory of a wing moving near a solid vail made of high-strength steels A78-48248 A78-48518 BOBEL, H. 3. BICBABDS, L. G. Engine vibration in flight Side quality evaluation. IV - Hodels of subjective [AIAA PAPEB 78-1475] A78-47921 reaction to aircraft motion BOBBY, B. 3. A78-47490 Higher order languages for avionics software - A RICBASDSON, D. survey, summary and critigue Birage 1000 - Dassault's better delta A78-49959 478-49169 BDEDGEB, B. B. BICHABDSOS, D. A. AFAL simulation facility/capability manual. Engine/airframe/drive train dynamic interface Volume 1: Executive summary and Systems documentation Avionics Division rAD-A055766] H78-31114 [AD-A055591] B78-31102 BICHET, G. K. BOGGEBI, B. S. Wind Tunnel/Flight Test Correlation Program on the Performance with and without inlet radial B-1 nacelle afterbody/nozzle at transonic distortion of a transonic fan stage designed for conditions reduced loading in the tip region fAIAA PIPES 78-989] A78-48469 [HASA-TP-1294] N78-30057 BIESTER, E. BOSSO, a. Flame stabilization in a ramjet combustion chamber Use of a field bench for testing turbojet engines by means of a pilot gas generator A78-49731 [DLB-FB-77-5II J B78-31117 BICHKOV, A. D. BIGGIBS, B. Investigation of noneguilibnum two-phase flows in A design of trajectory estimator using multiple axisymmetric Laval nozzles DUE range measurements A78-48244 [AD-A055191] F78-31077 BI1ET, D. B. Evaluation of several secondary tasks in the determination of permissible time delays in SAIH, H. K. simulator visual and motion cues Alternatives for jet engine control [NASA-TP-1214] H78-30089 [HASA-CB-157578] N78-31107 Simulator study of the effect of visual-motion SALiUS, P. time delays on pilot tracking performance with Linearized theory of plane, unsteady, supersonic an audio side task flow through a cascade - Subsonic part of the [BASA-TP-1216] N78-30090 leading edge BIBGBL, H. B. [OHEBA, TP BO. 1978-103] A78-47347 A high duty factor chirp radar SAIL BE, G. P. V78-49976 Short-term performance deterioration in BIO, B. A. JT9D-7A(SP) engine 695743 Turbine engine rotordynamic evaluation, volume 1 [HASA-CB-135431] H78-30121 [AD-A055262] 878-31111 SABOSSOS, L. BIPLE, J. C. Test and demonstration prototype tracked air Study of fuel systems for !B2-fneled subsonic cushion vehicle (PTACV): Phase IIIC transport aircraft, volume 1 [PB-279970/8] H78-31007 rNASA-CE-145369-VOL-1] H78-31085 SAS GIOVAHHI, C., JB. Study of fuel systems for LH2-fueled subsonic Performance of a differential Omega-ring laser transport aircraft, volume 2 strapdown aircraft navigator [NASA-CB-145369-VOL-2] N78-31086 A78-49966 ROBISSOH, S. B. Performance of a ring laser strapdown attitude and Infrared receiver performance heading reference for aircraft A78-49985 [AIAA 78-1240] A78-50162 ROBIHSON, B. I. SABFOBD, G. G. Advanced optical blade tip clearance measurement Conformal microstrip phased array for aircraft system tests with ATS-6 [NASA-CB-1 591)02] H78-31106 A78-49428 BOE, B. B. SAVOL, A. B. The HiHAT BPBV system Pattern recognition as an aid to radar navigation [AIAA PAPEB 78-1457] A78-47908 A78-49855 BOESSLEB, B. 3. SCHAEFfEB, B. G. In-flight alignaent/calibration techniques for Helicopter transmission vibration and noise unaided tactical guidance reduction program. Volume 1: Technical report A78-49929 [AD-A055104] 1178-31089 BOGEBS, C. B. SCBLOTBAOEB, J. A model of crack-tip behaviour for fatigue life The influence of the environment on the determination elastoplastic properties of adhesives in metal H78-30286 bonded joints BOGOZIH, 10. A. [DLB-FB-77-63] B78-31251 Modeling ground plane influence on ving SCBRIDT, A. I. aerodynamic characteristics using a finite plane Impact of aircraft electrical power quality on screen utilization equipment A78-48216 A78-49962

B-15 SCHHIDT, B. PE8SOHAL AOTHOH IHDEI

SCHHIDT, B. SERBOHGI, S. Scan-limited near field testing for directive The influence of throttle augmented stability airborne antennas (APCS) and short period control characteristics A78-19897 on the landing approach SCHHIDT, D. K. [AD-A055892] N78-31123 Optimal flight control synthesis via pilot modeling SEHHE, K. D. [AIAA 78-12861 A78-50193 IPC design validation and flight testing SCHHIDT, J. F. [AD-A055529] S78-3107U Performance with and vithout inlet radial SEHSBOEG, 0. distortion of a transonic fan stage designed for Impact of active control on structures design reduced loading in the tip region N78-30113 [NASA-TP-1291] N78-30057 SEBBETH, D. SCHHIDT, S. F. Autothreshold autoscreener/FLIH system Navigation performance of the Triscan concept for A78-19981 shipboard 7TOL aircraft operations SEVT, B. B. TAIAA 78-12931 A78-50200 Computer program for vibration prediction of SCBNELL, 8. C. fighter aircraft eguipments Vectoring non-axisymmetnc nozzle jet induced [AD-A051598] 1178-30091 effects on a V/STOL fighter model SHAGEBA, J. L. [AIA? PAPER 78-1080] A78-18196 landing aircraft under poor conditions SCHOENBOBH, B. E. A78-19519 Design for durability - The P101-GE-100 engine SHAHBHAG, II. B. [AIAA PAPEB 78-1081] A78-1481197 Large deflection static analysis of typical SCHBADER, P. tail-wheel structure of light aircraft by finite The influences of residual stresses on oscillating element method tensile strength and the measurement of residual 178-08861 stress, mth emphasis on aircraft construction SHABP, J. B. [BHVG-FBWT-77-23] S78-30603 Subsystem verification of an JFLC organically SCHUETZ, B. developed F-15 simulation The influences of residual stresses on oscillating f.78-19901 tensile strength and the measurement of residual SHCHEBBAKOV, A. V. stress, viith emphasis on aircraft construction Experimental determination of parameters of [BHVG-FBST-77-231 N78-30603 mathematical model of airplane cabin as SCHOLTZ, T. J. regulated object with respect to air temperature Synthesis of social surveys on noise annoyance in the cabin A78-18051 A78-18231 SCHOLZE, E. SHEEHAH, C. A. Shipboard launch and recovery of BPV helicopters Experimental determination of the rattle of simple in high sea states models [AIAA 78-1269] A78-50179 [NASA-TH-78756] S78-30291 SCHOB, E. F. SHEBHAH, D. J. An analytical and experimental investigation of Gust measurements and the N sub o problem diffusers for VSTOI thrust augmenting ejectors S78-30276 [AIAA PAPEE 78-1509] A78-17915 SHEBIAI, B. L. SCHOSTEB, E. P. Airplane stability calculations with a card Important simulation parameters for the programmable pocket calculator experimental testing of propulsion induced lift [BASA-TH-78678] H78-30138 effects SBEEBIEB, H. E. [AIAA PAPEE 78-1078] A78-18191 Ground effects testing of two, three, and four jet SCIAEBA, J. J. configurations Helicopter transmission vibration and noise [AIAA PAPEE 78-1510] A78-19789 reduction program. Volume 2: User's manual SHETE1L, B. S. [AD-A051827] N78-30095 The value of aerospace design synthesis courses as Helicopter transmission vibration and noise viewed by aerospace professionals reduction program. Volume 1: Technical report [AIAA PJPEB 78-1193] ?78-17931 [AD-A055101] N78-31089 SHIBLEY, T. E. SCIAFAHI, A. S. The role of system performance analysis in the Design evolution of a supersonic cruise independent assessment of B-1 navigation software strike-fighter A78-19902 [AIAA PAPEE 78-1152] A78-19783 SHOERAKEB, R. SCOTT, I. G. Comparison monitoring in redundant digital flight HDI and the detection of fatigue control systems N78-30282 J78-19865 SCBOFiBI, 0. SIEBEBT, B. F. Choice of cycle for a regenerative bypass turbojet Analysis of advanced variable camber concepts for long-range aircraft 1178-30108 A78-U9723 SIGALLA, A. SCOL1, D. C. Propulsion for future supersonic transports - 1978 The Omega radionavigation system comes to the status Pacific Ocean area [AIAA PAPEE 78-1051] A78-18186 A78-19660 SIHHORS, B. L. SECKEL, E. The terrain following task for the advanced The influence of throttle augmented stability tactical fighter using discrete optimal control (APCS) and short period control characteristics A78-19862 on the landing approach The terrain following task for the advanced [AD-A055892] N78-31123 tactical fighter using discrete optimal control SEIFEBT, B. [AD-A055196] 578-31121 Display systems and cockpit design SIBAZETDIHOV, T. K. H78-30116 Optimal control synthesis in distributed systems SEILEB, H. B. with incomplete information Pn analytical and experimental investigation of A78-18215 diffusers for VSTOL thrust augmenting ejectors SKIBA, G. G. [AIAA PAPEE 78-1509] A78-17915 Method of calcnlating aerodynamic coefficients of SELDHEB, K. some three-dimensional bodies with arbitrary Procedures for generation and reduction of linear cross section models of a turbofan engine J.78-18215 rHASA-TP-1261] N78-30896 SKDDBHA, J. T. The AN/APX-100/V/ transponder J78-19971

B-1 6 PEBSOHAl AflTBOB INDEX STBOHBEBG, G. F.

S1IVIHSKI, C. SPOBGEOH, J. C. Comparison monitoring an redundant digital flight A preliainary comparison of thermal decomposition control systems products of aircraft interior materials using A78-19865 the Rational Bureau of Standards smoke chamber Inherent errors in asynchronous digital flight and the combustion tube furnace controls [ AD-A051811 ] H78-30088 [AD-A055619] N78-31121 STABEHAO, B. F. SniTR. A. K. The role of system performance analysis in the Test and demonstration prototype tracked air independent assessment of B-1 navigation software cushion vehicle (PT'CV): Phase IIIC A78-19902 [PB-279970/8] N78-31007 STASZEK. 3. SBITB. H. 8. Trailing vortices. II Teaching design at all levels A78-17172 [AIAA PAPEB 78-1155] i78-a7906 STEELE, B. SHITB, B. E. The O.S. Havy bets on V/STOL Software engineering a mast for success in A78-19550 computerized flight test STEICEB, A. B. fAIfA PAPEB 78-1163] A78-17913 Effects of vind on aircraft cruise performance SOLODUKHIH, V. i. [AIAA PAPEB 78-1196] A78-17937 Optimization techniques for air traffic control STEBGEl, B. F. problems Flight investigation and theory of direct A78-18501 side-force control SOPEB, H. P. C. [AIAA 78-1287] A78-50191 Design philosophy for airframes SIEBB, 8. «78-17153 An automated procedure for computing the SOOTHA11, J. W. three-dimensional transonic flow over wing-body The design process combinations, including viscous effects. Volume [AIAA PiPEB 78-1183] A78-17928 1: Description of analysis methods and SPAH6IEB, S. B. applications Calculation of the longitudinal aerodynamic [AD-A055899] N78-31052 characteristics of upper-surface-blown wing-flap STEYEHS, C. H. configurations F-15 inlet/engine test techniques and distortion [NJSA-CB-3001] H78-30050 methodologies studies. Volume 1: Technical SPARKS, J. C. discussion £ calculator program for analyzing airloads on a [HASA-CR-111866] H78-30123 wing of arbitrary planform and camber in F-15 inlet/engine test techniques and distortion subsonic flow methodologies studies. Volume 2: Time variant [AD-A051180] B78-30058 data quality analysis plots SPEITEL, I. C. [NASA-CB-111867] N78-30121 A preliminary comparison of thermal decomposition F-15 inlet/engine test techniques and distortion products of aircraft interior materials using methodologies studies, volume 3: Power the National Bureau of Standards smoke chamber spectral density plots and the combustion tube fnrnace [NASA-CB-111868] B78-30125 [AD-A05W1] H78-30088 F-15 inlet/engine test techniques and distortion SPIBO, P. methodologies studies. Volume 1: Large electroforraed nickel moulds for aircraft parts Autocorrelation functions A78-17267 [NASA-CR-1U1869] N78-30126 SPOHG, E. D. F-15 inlet/engine test techniques and distortion F-15 inlet/engine test techniques and distortion methodologies studies. Volume 5: Effect of methodologies studies. Volume 1: Technical filter cutoff frequency on turbulence plots discussion [NASA-CB-141870] H78-30127 [NASA-CB-111866] N78-30123 F-15 inlet/engine test techniques and distortion F-15 inlet/engine test techniques and distortion methodologies studies. Volume 6: Distortion methodologies studies. Volume 2: Time variant analysis plots data quality analysis plots [NASA-CB-111871] N78-30128 [NJSA-CB-111867] N78-30121 F-15 inlet/engine test techniques and distortion F-15 inlet/engine test techniques and distortion methodologies studies. Volume 7: cross methodologies studies. Volume 3: Power correlation functions. spectral density plots [NASA-CE-111872] N78-30129 [NASA-CB-111868] N78-30125 F-15 inlet/engine test techniques and distortion F-15 inlet/engine test techniques and distortion methodoloqies studies. Volume 8: Cross methodologies studies. Volume 1: spectral density plots Autocorrelation functions [SASA-CB-111873] N78-30130 [NASA-CP-111869] H78-30126 F-15 inlet engine test techniques and distortion F-15 inlet/engine test techniques and distortion methodologies studies. Volume 9: Stability methodologies studies. Volume 5: Effect of audits filter cutoff frequency on turbulence plots [NASA-CB-111871] N78-30131 [NfSA-CB-111870] H78-30127 SIINSON, J. I. F-15 inlet/engine test techniques and distortion Software design for a Visually-Coupled Airborne methodologies studies. Volume 6: Distortion Systems Simulator (VCASS) analysis plots [AD-A055226] N78-31133 fNASA-CB-111871] N78-30128 STITZEB, S. H. F-15 inlet/engine test technigues and distortion A frequency-selective TIG limiter for airborne methodologies studies. Volume 7: Cross FH/CS X-band radar correlation functions. A78-50002 [NASH-CB-141872] N78-30129 STODGE, H. P. F-15 inlet/engine test techniques and distortion Correlation of model and airplane spin methodologies studies. Volume 8: Cross characteristics for a low-wing general aviation spectral density plots research airplane fHASA-CB-1U1873] N78-30130 [AIAA PAPEB 78-1177] A78-17922 F-'5 inlet engine test techniques and distortion STRABE, D. F. methodologies studies. Volume 9: Stability Electronagnetic coupling analysis of a Learjet audits aircraft in a lightning environoent [NASA-CB-111871] H78-30131 A78-19920 STBOHBEBG. G. F. Ground test facility for integral rocket ramjets [AIAA PAPEB 78-931] A78-18151

B-17 STDABT, T. A. PBBSONAL 10THOE IHDEX

STOiBT, T. 1. TOBCO, B. P. Modeling refinements for the rectified An assessment of the effect of supersonic aircraft superconducting alternator operations on the stratospheric ozone content A78-149961 [NASA-BP-1026] N78-3077D SON, K. C. TDBK, B. L. i laser-powered flight transportation system Approach for identifying avionics flight software [AIAA PAPEB 78-U8II] A78-49781 operational support requirements - PAVE TACK an SDSSHA8. B. B. example Non-axisynmetric nozzle design and evaluation for A78-19900 F-111 flight demonstration TDBRAGE. I. T. [AIAA PAPER 78-1025] J78-48483 A standard programmable I/O for the advanced SOTOBHIN, V. i. aircraft electrical system power control set Operator work capacity during parachutist free-fall A78-19936 A78-47978 TDBBIZIABI, B. V. SHIHABT, J. H. Design of a large span-distributed load Operations and economics of D.S. air transportation flying-wing cargo airplane with laminar flow [AIAA PJ1PBB 78-1515] A78-1I9770 control [NASA-CB-145376] N78-30015

TAI11ET, J. u Flight application of optical fiber transmission DBLBOBR, B. I. on a Falcon 10 aircraft Fiber optic development for tactical fighter [ONESA. TP BO. 1978-105] A78-47349 applications TAItLON, H. V. A78-49906 Status of a nozzle-airframe study of a highly DBIE, D. B. maneuverable fighter Piloted flight simulation for active control [AIAA PAPEB 78-990] A78-48170 design development TAKALIO, B. A. [AIAA PAPEB 78-1553] A78-49771 Investigation of a wing-rotor interaction system for helicopters [AD-A054093] N78-30092 TATE, B. 0. VACHAL, J. D. Computerized aircraft attrition program Wing planforms for large military transports [AD-A05578IO N78-31094 [AIAA PAPEB 78-1470] A78-49786 TEBRIKOV, A. V. VAHLBEBG, C. J. Solution of an adjoint problem of steady-state High-accuracy three-dimensional image heat transfer associated with the cooling of reconstruction for an airborne line-scanning gas-turbine blades, by means of a system guasi-analog/digital system A78-499B8 A78-47402 VAB DAB, C. Application of electrical analogy to the Some sound transmission loss characteristics of substantiation and comparison of some analytical typical general aviation structural materials methods of determining temperature fields in [AIAA PAPEB 78-1180] A78-47925 gas-turbine blades VAB DEI BBOEK, B. A78-47401; Digital avionics support - A retrospective view of TBIEBAH, B. A. the future Analysis of monopole antenna arrays on cylinders J78-49903 by the geometrical theory of diffraction VANAKEN, J. [AD-A055197] N78-31335 A research program to reduce interior noise in TBOBASON, T. B. general aviation airplanes: Investigation of The promise of tilt rotor the characteristics of an acoustic panel test A78-47266 facility THOMPSOH, E. H. [NASA-CB-157587] N78-31874 Peace Bhine - A digital Weapon Control System for VABDAB, C. P. G. the F-i) aircraft A research program to reduce interior noise in A78-49876 general aviation airplanes: Noise reduction THOBPSOH, B. C., JB. through a cavity-backed flexible plate Fading at 9.6-GHz on an experimentally simulated [NASA-CB-157588] N78-31873 aircraft-to-ground path VABDEVEB, W. B., JB. A78-49439 The DAIS Executive - An introduction TICHTIBSICT, B. A78-49932 Methods available to ONEBA for analysis of VANDYKE, t. combustion chambers Measurements and analysis of the forces acting on [ONEBA, TP NO. 1978-93] A78-46915 a small aircraft flying in the upwash of a large TOLAND, B. B. aircraft Botor design implications for composite material [AD-A055286] N78-31048 properties VEBLOW, C. A. [DCBL-80117] H78-30182 Experimental investigation of gust response of TOB, B. hingeless helicopter rotors Air-to-air designate/track with time sharing [1D-A054752] N78-30142 A78-49977 VELDPILLAI, D. TOBEI1A, G. Mirage 2000 - Dassault's better delta Dse of a field bench for testing turbojet engines A78-19169 A78-49731 VEBSAW, B. t. TBASESEE, J. B. Study of fuel systems for LH2-fueled subsonic Non-volatile memory system for severe environment transport aircraft, volume 1 flight recorders [HASA-CB-1U5369-V01-1] N78-31085 A78-49872 Study of fuel systems for LH2-fueled subsonic TBIPP, B. H. transport aircraft, volume 2 Modeling refinements for the rectified [HASA-CB-145369-VOL-2] N78-31086 superconducting alternator VIHKLEB, A. A78-U9961 Guaranteed cost control of linear systems with TSAO, G. K. B. uncertain parameters - Application to remotely Dual band airborne SATCOH terminal piloted vehicle flight control systems A78-49972 [AIAA 78-127H] ' A78-50184 TOLLOCfl, J. S. Modified helicopter icing spray system evaluation [AD-A055039] H78-31091

B-18 PEBSOBAL AOTHOB IBDEI RILLABD, C. B.

VIBSOH, P. H. WEIHGABTEI, J. L. Energy efficient engine: Preliminary design and Aeronautical procurement - The primary integration studies specification systen [BASA-CB-135Bia] B78-31108 [AIAA PAPEB 78-1U89] A78-D7932 VOGT, G. L. Cargo aircraft and spacecraft forward restraint The AH/APX-100/V/ transponder criteria A78-49971 [AD-A055343] B78-31095 VOOBBEES, C. G. WZIBBEICH, R. Gates Learjet Model 28/29, the first 'longhorn1 A study of analog programming for prediction of Learjet crack growth in aircraft structures subjected to [AIAA PAPEB 78-1HII5] A78-B7901 raudom loads VOBOBEV, V. G. [AD-A055789] B78-31097 Aviation control system devices WEIST, G. A78-II9850 Variable-cycle engine fighter aircraft: Advance VOBOBIR, V. G. in performance and development problems Experimental determination of parameters of B78-30109 mathematical model of airplane cabin as WEISZ, C. P. regulated object mth respect to air temperature Airfield pavement evaluation - The airline view in the cabin A78-19680 A78-H823U BELLS, 8. B. VTTCBIICOV, 10. S. Approximate indicial lift function for tapered, Solution of an adjoint problem of steady-state swept wings in incompressible flow heat transfer associated with the cooling of [BiSA-TP-1241] B78-3005I1 gas-turbine blades, by means of a BESIEBBEIBB, I. F. quasi-analog/digital system In-line monitoring of digital flight control A78-17II02 computers A78-49860 Triplex digital fly-by-wire redundancy management w techniques HAGDI, fl. B. [AIAA 78-1279] A78-50187 Stability augmentation by eigenvalues control and BB4LEI, P. B. model matching Prediction of angular disturbances from airframe A78-46965 members to airborne electro-optical packages HJGHEB, J. B. A78-09952 Pnalysis of multistage, anal flow tnrbomachine RHISIAHT, B. A. wake production, transport, and interaction AFAL simulation facility/capability manual. rAD-A05575U] H78-31118 Volume 1: Executive summary and Systems RAKEFIELD. C. Avionics Division Assessment of dynamic coordinate alignment for [AD-A055591] N78-31102 elastic aircraft BHITBECK, B. ?. A78-H9987 Digital control law synthesis in the w prime domain WALLACE, E. L. A78-i)6962 Dse of onboard computerized flight test analysis BBITE, R. F. systems Flight demonstrations of curved, descending [AIAA PAPEB 78-11162] A78-47912 approaches and automatic landings using time WARWICK, G. referenced scanning beam guidance Hirage 2000 - Dassault's better delta [BASA-TH-78745] N78-30074 A78-49169 WHITE, R. F., JB. BASHBDRH, G. t. The influence of high twist on the dynamics of Design of a large span-distributed load rotating blades flying-wing cargo airplane with laminar flow A78-17599 control BHITBBEAD, D. S. [NASA-CK-145376] H78-300H5 Linearized supersonic unsteady flow in cascades RASYtKIRSKYJ, R. [ABC-B/H-3811] B78-30065 On the use of zirconium 95 data from Chinese WBITEBEAD, B. B. atmospheric thermonuclear explosions to study Analysis of advanced variable camber concepts stratospheric transport in a one-dimensional B78-30108 parameterization BBIITEH, B. C. A78-U8062 An assessment of the effect of supersonic aircraft WATERS, H. B. operations on the stratospheric ozone content Bequirements for regional short-haul air service [BASA-BP-1026] B78-3077I4 and the definition of a flight program to RICKS, B. J. determine neighborhood reactions to small A model of crack-tip behaviour for fatigue life transport aircraft determination [NASS-CB-152151] N78-30070 B78-30286 SAMS, J. D. WILCOX, D. E. Interface design considerations for F-^6 sensors V/STOL aircraft simulation - Beguirements and and weapons capabilities at Ames Besearch Center A78-1987II [AIAA PAPEB 78-1515] A78-99790 SEAVEB, B. E. BILCOI, B. E. Digital simulation and flight verification of the Combinatorially derived limits on the surface F-5E/F Flight Director Computer return for an air/surface monopnlse ranging radar 178-119905 A78-50001 WEBER, R. B. BILBE, C. D. Experimental determination of propulsion induced The BiHAT BPBV system ground effects of typical tbree fan type A [AIJA PAPEB 78-1057] A78-17908 V/STOL configurations BPV flying qualities design criteria [AISA PAPEB 78-1507] A78-H7943 [AIAA 78-1271] A78-50181 REEKS, B. A. RILES, D. Digital simulation and flight verification of the Hultiprocessing for electronic warfare avionics F-5E/F Flight Director Computer A78-49869 A78-H9905 BILLABD, C. H. WEILEB, B. Installed performance of vectoring/reversing Variable-cycle engine fighter aircraft: Advance non-axisymmetric nozzles in performance and development problems [AIAA PAPEB 78-1022] A78-18082 N78-30109

B-19 RILIIAHS, E. R. PEBSOHAL AOTHOB IHDEI

BILLI4BS, E. 8. Experimental determination of propulsion induced ground effects of typical three fan type \ V/STOI configurations (AI44 P4PEE 78-1507] 478-1179113 BILSON, J. R. Propulsion system airframe integration studies - idvanced supersonic transport [AI4A P4PEE 78-1053] A78-48488 RIHTBEB, B. A. Demonstration of aircraft wing/store flutter suppression systems H78-31128 RISE. C. Multiprocessing for electronic warfare avionics 478-19869 RITSBESB, A. J. Pattern recognition as an aid to radar navigation A78-19855 ROLFE, L. 0. Advance nozzle technology N78-30111 ROLK07ITCH, J. Nacelle effects on stability of VSTOI configurations including conventional, canard, and tandem wing arrangements [-&I4A PAPEB 78-1504] 478-47942 ROOD, 1. J. Guaranteed cost control of linear systems with uucertain parameters - Application to remotely piloted vehicle flight control systems filAA 78-12711] A78-501811 WOODCOCK, D. 1. Diverse forms and derivations of the equations of motion of deformable aircraft and their mutual relationship [RAE-TB-77077] N78-30097 ROODCOCK, R. A. Pavement strength rating methods as viewed by airframe manufacturers 478-1)9682 BOOtFSOH, H. 6. Digital area correlation tracker 478-1(9951 ROOLIET, H. The evolution of a remotely piloted vehicle microprocessor flight control system TAI44 78-12731 AT8-50183 ROOTED, E. BN1V - Corporate operators set the pace 478-1171(24 BDNSEHBESG, B. Advanced control concepts for future fighter aircraft N78-30104

TE4GEE, R. T., JE. Analysis of stability contributions of high dihedral V-tails [KASA-TM-78729] N78-31044 YES, R. I. Effects of dynamic aeroelasticity on handling qualities and pilot rating S78-31084 YESNI, K. B. Simulation and flight evaluation of a head-up landing aid for general aviation [NASA-TP-1276] N78-31101 in, c. L. Volumetric pattern analysis of airborne antennas A78-49427

ZABIHSKT, J. B. The influence of propulsion and control system concepts on design of a Havy Type 4 V/STOL airplane CAIAA PAPEB 78-1505] 478-49788 ZIHHEBBABB, B. Impact of active control on structures design N78-30113

B-20 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl 103) DECEMBER 1978

P33615-76-C-2051 OHEBA-18,884/SAT,2/1L Typical Contract Number Index Listing H78-3106H A78-50190 F33615-76-C-3107 PBOJ. 03Q-2al-012 &78-Q8I483 H78-3107« HAS»-2«83 B78-11061 F33615-76-C-3109 SH/1170/012 B78-30910 H78-31097 H78-30911 F33615-76-S-0029 W-7a05-EBG-ll8 CONTRACT NASA ACCESSION A78-U9957 H78-30182 NUMBER NUMBER F33615-77-C-1121 WF1iai1000 H78-30091 478-89987 198-30-02 H78-3077U F33615-77-C-1227 505-02-33-03 B78-30606 Listings in this index are arranged alphanumencally by contract number A78-U9998 505-OH H78-30057 F33615-77-C-3026 505-05 B78-30896 Under each contract number the accession numbers denoting documents A78-H6962 505-06-31-03 B78-30016 that have been produced as a result of research done under that contract F33615-77-C-30«1 505-06-63-02 H78-3005q are arranged in ascending order with the IAA accession numbers appearing A78-50186 H78-30089 first The accession number denotes the number by which the citation is F33657-77-C-000« H78-30090 identified tn either the lAAor STAR section A78-a9902 505-07-10 H78-30072 F33657-77-C-0189 505-08-23-01 H78-30138 •-F PBOJ. 2202 DAAK70-78-C-0001 A78-U9876 505-09-13-11 H78-30291 N78-30093 N78-30259 F»U620-76-C-0073 505-10-13-00 B78-30iai fF PBOJ. 2307 DABCOH-7U-G-0007 H78-310U8 505-10-13-02 578-31101 B78-11018 H78-30092 F49620-77-C-0023 505-10-13-07 H78-30019 'F PBOJ. 3066 DAHC01I-75-G-0023 H78-31100 505-10-1307 H78-300U8 r78-3111'1 N78-30092 H1SA OBDEB C-41581-B 505-11-16-07 H78-30056 &F PBOJ. 6116 DAHC1S-73-C-0200 H78-31105 505-11-23-06 S78-30039 178-3009Q N78-30119 H1S1-13500 H78-30015 505-11-33-01 H78-31045 11 PBOJ. 7381 DOT-FA72HAI-261 NAS1-14086 578-30050 506-26-33-03 H78-30053 N78-30213 N78-3107U HAS1-1II311 A78-50203 510-54-04 K78-30123 AF PBOJ. 6095 DOT-FA7HHA-3353 NAS1-14570 H78-30042 B78-30124 A78- 119859 178-31073 H78-30043 B78-30125 AF PBOJ. 7629 DOT-FA75WA-3707 H78-30044 S78-30126 A7H- 119987 H78-31088 NAS1-1l»6la H78-31085 H78-30127 AF-AFOSB-2160A-71! DOT-FA76SA-3157 H78-31086 H78-30128 A78-II9837 A78-U8062 HAS1-14756 H78-30051 S78-30129 AF-AFOSB-2889J-76 DOT-FA76WA-3788 BAS1-1U849 H78-300H8 B78-30130 f 78-H9713 N78-30080 B78-30049 H78-30131 AF-AFOSB-2968 -76 DOT-FA77WA-3965 NAS2-873I4 A78-47907 516-50-23-01 N78-300UO A78-U9865 A78-U8062 HAS2-9050 F78-30070 S78-300U5 AF-AFOSB-2997-76 DOT-FA78SA-H075 HAS3-20479 H78-31106 516-53-03-21 B78-310K3 A78- 119961 N78-31130 HAS3-20627 N78-31108 716-01-02 F78-31108 AF-AFOSB-3005A-76 N78-31131 HAS3-20632 N78-30121 7H3-OH-13-01 H78-30122 A78-U9860 DOT-FA78WA-11091 KAS4-236U N78-30123 7U3-00-13-02 N78-30087 AF-AFOSB-31113-77 H78-3113I1 N78-3012H A78-U9961 DOT-FB-5II089 H78-31007 H78-30125 iF-AFOSB-2916-76 DOT-TSC-763 A78-H9U28 B78-30126 H78-31118 ET-76-C-OI1-789 N78-30127 AF-AFOSB-2968-76 H78-31099 H78-30128 S78-31121 ET-76-C-OU-0613 N78-30129 CNB-77, 01087, 9 1,1 15, 96911 N78-312H9 N78-30130 A78-U9733 F08635-77-C-0210 H78-30131 CHB- 11 5, 26118, 07, CT- 76, 00480 A78-I19929 BAS7-100 N78-30583 A78-U9708 F09603-77-A-310U NGL-05-020-007 Dt PBOJ. 1F2-62209-AH-76 N78-30079 A78-S0202 N78-31952 F19628-70-C-0218 SGI-36-008-138 DA PROJ. 1G2-62207-AH-89 A78-49975 A78-I19U27 R78-31089 F19628-77-C-0033 KGI-19-002-0*'* DA PBOJ. 1G2-62207-AH-8903 A78-99965 A78-U9781 N78-30095 F19628-78-C-0002 SGH-36-009-017 DA PEOJ. U1-61102-AH-1I5 N78-310711 N78-31068 N78-310HH F30602-75-F-0256 HGfi-q7-005-181 D> PBOJ. 1L2-62209-AH-76 A78-19139 A78-H7U90 N78-31096 F30602-76-C-007H A78-U968II DAAG29-76-G-OOI15 A78-09998 NIVE-1725 H78-30620 H78-30092 F30602-77-C-0009 HSG-1111 B78-30139 DAAG29-76-G-0318 A78-1I9998 NSG-1301 A78-«7925 H78-30092 F33615-73-C-H036 H78-31873 DAAG53-76-C-0003 A78-119972 B78-3187a H78-30259 F33615-75-C-11U9 HSG-137* A78-19858 DAAJ01-77-C-0354 A78- 49859 HSG-3018 M78-31107 N78-31113 F33615-75-C-2035 NSG-H002 A78-50209 DAAJ02-7U-C-OOQO N78-31111 NSG-7266 H78-30069 H78-30095 F33615-75-C-3073 H00019-75-C-0528 N78-31089 N78-31052 H78-31123 DAAJ02-75-C-OOa6 F33615-75-C-3105 H00019-77-C-0195 N78-31115 N78-30093 H78-31093 DAAJ02-76-C-0052 F33615-75-C-315H S001UO-77-C-0105 N78-31096 H78-31120 A78-U9852 DAAJ02-76-C-0058 F33615-75-C-5065 H62269-76-C-0390 S78-31952 N78-30213 H78-30120 D4AJ02-77-C-0018 F33615-76-C-1036 H62269-77-C-007H F78-31119 A78-50002 H78-30091 DA&J02-77-C-001IO F33615-76-C-1308 B62269-77-C-0561 H78-3111Q •178-31102 A78-50161

C-1 1 Report No 2 Government Accession No 3 Recipient's Catalog No NASA SP-7037 (103) 4 Title and Subtitle 5 Report Date AERONAUTICAL ENGINEERING December 1978 A Continuing Bibliography (Supplement 103) 6 Performing Organization Code

7 Author(s) 8 Performing Organization Report No

10 Work Unit No 9 Performing Organization Name and Address

National Aeronautics and Space Administration 11 Contract or Grant No Washington, D. C. 205^6 13. Type of Report and Period Covered 12 Sponsoring Agency Name and Address

14 Sponsoring Agency Code

15 Supplementary Notes

16 Abstract

This bibliography lists kSl reports, articles, and other documents introduced into the NASA scientific and technical information system in November 1978.

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

19 Security dassif (of this report) 22 Price* E02 Unclassified 20 Security Classif (of this page) 21. No of Pages Unclassified $^.75 HC

For sale by the National Technical Information Service, Springfield. Virginia 22161 NASA-Langley, 1979 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC NASA distributes its technical documents and bibliographic tools to ten special libraries located in the organization* listed below Each library it prepared to furnish the public such services as reference assistance, mterlibrary loans, photocopy service and assistance in obtaining copies of NASA documents for retention CALIFORNIA MASSACHUSETTS University of California. Berkeley Massachusetts Institute of Technology. Cambridge COLORADO MISSOURI University of Colorado. Boulder Linda Hall Library. Kansas City DISTRICT OF COLUMBIA NEW YORK Library of Congress Columbia University. New York GEORGIA PENNSYLVANIA Georgia Institute of Technology. Atlanta Carnegie Library of Pittsburgh ILLINOIS WASHINGTON The John Crerar Library, Chicago University of Washington, Seattle

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NASA CONTINUING BIBLIOGRAPHY SERIES

NUMBER TITLE FREQUENCY NASA SP-7011 AEROSPACE MEDICINE AND BIOLOGY Monthly Aviation medicine, space meditine, and space biology

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