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  1. FLIGHT AND WIND-TUNNEL COMPARISONS OF THE INLET-AIRFRAME INTERACTION OF THE F-15 AIRPLANE , Technical Paper
    Authors: L. D. Webb, D. Andriyich-Varda and S. A. Whitmore
    Report Number: NASA-TP-2374
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
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    Report Date: November 1984
    No. Pages: 35
    Keywords:      Flight tests; Force distribution; Inlet airframe configurations; Pressure distribution; Wind tunnel tests.


  2. FLIGHT-DETERMINED AERODYNAMIC DERIVATIVES OF THE AD-1 OBLIQUE-WINGRESEARCH AIRPLANE , Technical Paper
    Authors: A. G. Sim and R. E. Curry
    Report Number: NASA-TP-2222
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The AD-1 is a variable-sweep oblique-wing research airplane that exhibits unconventional stability and control characteristics. In this report, flight-determined and predicted stability and control derivatives for the AD-1 airplane are compared. The predictions are based on both wind tunnel and computational results. A final best estimate of derivatives is presented.
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    Report Date: October 1984
    No. Pages: 40
    Keywords:      Aerodynamic coefficients; Aircraft control; Oblique wings; Research aircraft; Variable sweep wings.


  3. IN-FLIGHT TOTAL FORCES, MOMENTS AND STATIC AEROELASTIC CHARACTERISTICS OF AN OBLIQUE-WING RESEARCH AIRPLANE , Technical Paper
    Authors: R. E. Curry and A. G. Sim
    Report Number: NASA-TP-2224
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A low-speed flight investigation has provided total force and moment coefficients and aeroelastic effects for the AD-1 oblique-wing research airplane. The results were interpreted and compared with predictions that were based on wind tunnel data. An assessment has been made of the aeroelastic wing bending design criteria. Lateral-directional trim requirements caused by asymmetry were determined. At angles of attack near stall, flow visualization indicated viscous flow separation and spanwise vortex flow. These effects were also apparent in the force and moment data.
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    Report Date: October 1984
    No. Pages: 30
    Keywords:      Aeroelastic research wings; Aircraft design; Flight tests; Oblique wings; Research aircraft.


  4. HIGHLY MANEUVERABLE AIRCRAFT TECHNOLOGY (HIMAT) FLIGHT-FLUTTER TEST PROGRAM , Technical Memorandum
    Authors: M. W. Kehoe
    Report Number: NASA-TM-84907
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The highly maneuverable aircraft technology (HiMAT) vehicle was evaluated in a joint NASA and Air Force flight test program. The HiMAT vehicle is a remotely piloted research vehicle. Its design incorporates the use of advanced composite materials in the wings, and canards for aeroelastic tailoring. A flight-flutter test program was conducted to clear a sufficient flight envelope to allow for performance, stability and control, and loads testing. Testing was accomplished with and without flight control-surface dampers. Flutter clearance of the vehicle indicated satisfactory damping and damping trends for the structural modes of the HiMAT vehicle. The data presented include frequency and damping plotted as a function of Mach number.
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    Report Date: May 1984
    No. Pages: 20
    Keywords:      Flight characteristics; Flight control; Flight tests; Flutter; Highly maneuverable aircraft.


  5. EVALUATION OF A FLOW DIRECTION PROBE AND A PITOT-STATIC PROBE ON THE F-14 AIRPLANE AT HIGH ANGLES OF ATTACK AND SIDESLIP , Technical Memorandum
    Authors: T. J. Larson
    Report Number: NASA-TM-84911
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The measurement performance of a hemispherical flow-angularity probe and a fuselage-mounted pitot-static probe was evaluated at high flow angles as part of a test program on an F-14 airplane. These evaluations were performed using a calibrated pitot-static noseboom equipped with vanes for reference flow direction measurements, and another probe incorporating vanes but mounted on a pod under the fuselage nose. Data are presented for angles of attack up to 63, angles of sideslip from -22 deg to 22 deg, and for Mach numbers from approximately 0.3 to 1.3. During maneuvering flight, the hemispherical flow-angularity probe exhibited flow angle errors that exceeded 2 deg. Pressure measurements with the pitot-static probe resulted in very inaccurate data above a Mach number of 0.87 and exhibited large sensitivities with flow angle.
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    Report Date: March 1984
    No. Pages: 42
    Keywords:      Angle of attack; F-14 aircraft; Flow measurement; Mach number; Sideslip.


  6. THE ROLE OF SIMULATION IN THE DEVELOPMENT AND FLIGHT TEST OF THE HIMAT VEHICLE , Technical Memorandum
    Authors: M. B. Evans and L. J. Schilling
    Report Number: NASA-TM-84912
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Real time simulations have been essential in the flight test program of the highly maneuverable aircraft technology (HiMAT) remotely piloted research vehicle at NASA Ames Research Center's Dryden Flight Research Facility. The HiMAT project makes extensive use of simulations in design, development, and qualification for flight, pilot training, and flight planning. Four distinct simulations, each with varying amounts of hardware in the loop, were developed for the HiMAT project. The use of simulations in detecting anomalous behavior of the flight software and hardware at the various stages of development, verification, and validation has been the key to flight qualification of the HiMAT vehicle.
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    Report Date: April 1984
    No. Pages: 38
    Keywords:      Computerized simulation; Flight tests; Pilot training; Real time operation; Remotely piloted vehicles.


  7. THE USE OF OIL FOR IN-FLIGHT FLOW VISUALIZATION , Technical Memorandum
    Authors: R. E. Curry, R. R. Meyer, Jr. and M. O'Connor
    Report Number: NASA-TM-84915
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Oil was used to visualize inflight aerodynamic characteristics such as boundary layer transition, shock wave location, regions of separated flow, and surface flow direction. The technique, which is similar to wind tunnel oil-flow testing, involves an oil mixture to test aircraft before takeoff. After takeoff, the airplane climbs immediately to the test altitude and photographs are taken. The developmental experience is summarized, several examples of inflight oil-flow photographs are presented and discussed, and an approach for potential users of the technique is presented.
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    Report Date: January 1984
    No. Pages: 17
    Keywords:      F-111 aircraft; Flight characteristics; Flow distribution; Oils; Photography.
    Notes: Presented at 14th Ann. Symp. of the Soc. of Flight Test Engr., Newport Beach, Cal., 15-19 Aug. 1983.


  8. PREFLIGHT TRANSIENT DYNAMIC ANALYSES OF B-52 AIRCRAFT CARRYING SPACE SHUTTLE SOLID ROCKET BOOSTER DROP-TEST VEHICLE , Technical Memorandum
    Authors: W. L. Ko and L. S. Schuster
    Report Number: NASA-TM-84925
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: This paper concerns the transient dynamic analysis of the B-52 aircraft carrying the Space Shuttle solid rocket booster drop test vehicle (SRB/DTV). The NASA structural analysis (NASTRAN) finite element computer program was used in the analysis. The B-52 operating conditions considered for analysis were (1) landing and (2) braking on aborted takeoff runs. The transient loads for the B-52 pylon front and rear hooks were calculated. The results can be used to establish the safe maneuver envelopes for the B-52 carrying the SRB/DTV in landings and brakings.
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    Subject Category: 39
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    Report Date: January 1984
    No. Pages: 17
    Keywords:      B-52 aircraft; Dynamic structural analysis; Landing gear; Preflight analysis; Space shuttle boosters.
    Notes: Presented at the AIAA 2nd Flight Test Conf., Las Vegas, Nev., 16-18 Nov. 1983.


  9. X-29 FLIGHT-RESEARCH PROGRAM , Technical Memorandum
    Authors: T. W. Putnam
    Report Number: NASA-TM-86025
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The X-29A aircraft is the first manned, experimental high-performance aircraft to be fabricated and flown in many years. The approach for expanding the X-29 flight envelope and collecting research data is described including the methods for monitoring wind divergence, flutter, and aeroservoelastic coupling of the aerodynamic forces with the structure and the flight-control system. Examples of the type of flight data to be acquired are presented along with types of aircraft maneuvers that will be flown. A brief description of the program management structure is also presented and the program schedule is discussed.
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    Report Date: January 1984
    No. Pages: 16
    Keywords:      Aircraft design; Control; Fighter aircraft; Flight; Flight characteristics.
    Notes: Presented at the AIAA 2nd Flight Test Conf., Las Vegas, Nev., 16-18 Nov. 1983.


  10. PRELIMINARY FLIGHT EVALUATION OF F100 ENGINE MODEL DERIVATIVE AIRSTART CAPABILITY IN AN F-15 AIRPLANE , Technical Memorandum
    Authors: T. K. Cho and F. W. Burcham, Jr.
    Report Number: NASA-TM-86031
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A series of airstarts was conducted in an F-15 airplane with two prototype F100 engine model derivative (EMD) engines equipped with digital electronic engine control (DEEC) systems. The airstart envelope and time required for airstarts were defined. The success of an airstart is most heavily dependent on airspeed. Spooldown airstarts at 200 knots and higher were all successful. Spooldown airstart times ranged from 53 sec at 250 knots to 170 sec at 175 knots. Jet fuel starter (JFS) assisted airstarts were conducted at 175 knots at two altitudes, and airstart times were 50 and 60 sec, significantly faster than unassisted airstart. The effect of altitude on airstarts was small. In addition, the airstart characteristics of the two test engines were found to closely resemble each other. The F100 EMD airstart characteristics were very similar to the DEEC equipped F100 engine tested previously. Finally, the time required to spool down from intermediate power compressor rotor speed to a given compressor rotor speed was found to be a strong function of altitude and a weaker function of airspeed.
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    Subject Category: 07
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    Report Date: July 1984
    No. Pages: 31
    Keywords:      Electronic control; Engine control; F-15 aircraft; Ignition; Turbofan engines.


  11. DIGITAL ELECTRONIC ENGINE CONTROL (DEEC) FLIGHT EVALUATION IN AN F-15AIRPLANE , Conference Publication
    Authors: Various
    Report Number: NASA-CP-2298
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Flight evaluation in an F-15 aircraft by digital electronic engine control (DEEC) was investigated. Topics discussed include: system description, F100 engine tests, effects of inlet distortion on static pressure probe, flight tests, digital electronic engine control fault detection and accommodation flight evaluation, flight evaluation of a hydromechanical backup control, augmentor transient capability of an F100 engine, investigation of nozzle instability, real time in flight thrust calculation, and control technology for future aircraft propulsion systems. It is shown that the DEEC system is a powerful and flexible controller for the F100 engine.
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    Report Date: March 1984
    No. Pages: 243
    Keywords:      Conferences; Digital techniques; Engine control; F-15 aircraft; Flight tests.
    Notes: Symposium held in Edwards, Calif., 25-26 May 1983.


  12. LOCALLY LINEARIZED LONGITUDINAL AND LATERAL-DIRECTIONAL AERODYNAMIC STABILITYAND CONTROL DERIVATIES FOR THE X-29A AIRCRAFT , Technical Memorandum
    Authors: G. D. Budd
    Report Number: NASA-TM-84919
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The locally linearized longitudinal and lateral-directional aerodynamic stability and control derivatives for the X-29A aircraft were calculated for altitudes ranging from sea level to 50,000 ft, Mach numbers from 0.2 to 1.5, and angles of attack from -5 deg to 25 deg. Several other parameters were also calculated, including aerodynamic force and moment coefficients, control face position, normal acceleration, static margin, and reference angle of attack.
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    Report Date: January 1984
    No. Pages: 480
    Keywords:      Attitude control; Lateral stability; Longitudinal stability; Swept forward wings; X-29 aircraft.


  13. REAL-TIME PILOT GUIDANCE SYSTEM FOR IMPROVED FLIGHT TEST MANEUVERS , Technical Memorandum
    Authors: R. R. Meyer, Jr. and E. T. Schneider
    Report Number: NASA-TM-84922
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The Dryden Flight Research Facility of the NASA Ames Research Center has developed a pilot trajectory guidance system that increases the accuracy of flight-test data and decreases the time required to achieve and maintain desired test conditions. The system usually presented to the pilot computed differences between reference or desired and actual flight state conditions. The pilot then used a cockpit display as an aid to acquire and hold desired test conditions. This paper discusses various flight-test maneuvers and the quality of data obtained using the guidance system. Some comparisons are made between the quality of maneuvers obtained with and without the system. Limited details of the guidance system and algorithms used are included. In general, the guidance system improved the quality of the maneuvers and trajectories flown, as well as allowing trajectories to be flown that would not have been possible without the system. This system has moved from the developmental stage to full operational use in various Dryden research and test aircraft.
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    Subject Category: 06
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    Report Date: January 1984
    No. Pages: 23
    Keywords:      Angle of attack; Cockpits; Display devices; Dynamic pressure; Flight tests.


  14. EVALUATION OF HIMAT AIRCRAFT LANDING APPROACH LATERAL CONTROL GEARING USING SIMULATION AND A VISUAL DISPLAY , Technical Memorandum
    Authors: S. K. Sarrafian
    Report Number: NASA-TM-84916
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The utility of a visual display when studying the influence of changes in lateral stick gearing gains on the Highly Maneuverable Aircraft Technology (HiMAT) vehicle handling qualities during simulated approaches and landings is investigated. The visual display improved the validity of the simulation and provided improved roll response cues for the HiMAT aircraft landing approach. A range of acceptable constant lateral stick gearing gains is found that provides adequate maneuverability and allows for precision moments.
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    Report Date: May 1984
    No. Pages: 23
    Keywords:      Computerized simulation; Display devices; Flight characteristics; Flight simulation; Highly maneuverable aircraft.


  15. AFTI/F-16 DIGITAL FLIGHT CONTROL SYSTEM EXPERIENCE , Conference Paper
    Authors: D. A. Mackall
    Report Number: H-1207
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The Advanced Flighter Technology Integration (AFTI) F-16 program is investigating the integration of emerging technologies into an advanced fighter aircraft. The three major technologies involved are the triplex digital flight control system; decoupled aircraft flight control; and integration of avionics, pilot displays, and flight control. In addition to investigating improvements in fighter performance, the AFTI/F-16 program provides a look at generic problems facing highly integrated, flight-crucial digital controls. An overview of the AFTI/F-16 systems is followed by a summary of flight test experience and recommendations.
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    Report Date: March 1984
    No. Pages: 19
    Keywords:      Automatic flight control; Avionics; Display devices; F-16 aircraft; Systems integration.
    Notes: In NASA. Langley Research Center NASA Aircraft Controls Research, 1983 p 469-487, NASA CP-2296.


  16. AN AUTOMATED STALL-SPEED WARNING SYSTEM , Technical Memorandum
    Authors: D. O. Wilner and G. A. Bever
    Report Number: NASA-TM-84917
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The development and testing of a stall-speed warning system for the OV-1C was examined. NASA designed and built an automated stall-speed warning system which presents both airspeed and stall speed to the pilot. The airspeed and stall speed are computed in real time by monitoring the basic aerodynamic parameters (dynamic pressure, horizontal and vertical accelerations, and pressure altitude) and other parameters (elevator and flap positions, engine torques, and fuel flow). In addition, an aural warning at predetermined stall margins is presented to the pilot through a voice synthesizer. Once the system was designed and installed in the aircraft, a flight-test program of less than 20 hrs was anticipated to determine the stall-speed software coefficients. These coefficients would then be inserted in the system's software and then test flown over a period of about 10 hr for the purpose of evaluation.
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    Subject Category: 06
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    Report Date: February 1984
    No. Pages: 17
    Keywords:      Aerodynamic stalling; Aircraft instruments; Airspeed; Avionics; Flight safety.
    Notes: Presented at the AIAA 2nd Flight Test Conf., Las Vegas, Nev., 16-18 Nov. 1983.


  17. DESIGN IMPLICATIONS FROM AFTI/F-16 FLIGHT TEST , Technical Memorandum
    Authors: S. D. Ishmael, V. A. Regenie and D. A. Mackall
    Report Number: NASA-TM-86026
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Advanced fighter technologies are evolving into highly complex systems. Flight controls are being integrated with advanced avionics to achieve a total system. The advanced fighter technology integration (AFTI) F-16 aircraft is an example of a highly complex digital flight control system integrated with advanced avionics and cockpit. The architecture of these new systems involves several general issues. The use of dissimilar backup modes if the primary system fails requires the designer to trade off system simplicity and capability. This tradeoff is evident in the AFTI/F-16 aircraft with its limited stability and fly-by-wire digital flight control systems. In case of a generic software failure, the backup or normal mode must provide equivalent envelope protection during the transition to degraded flight control. The complexity of systems like the AFTI/F-16 system defines a second design issue, which can be divided into two segments: the effect on testing, and the pilot's ability to act correctly in the limited time available for cockpit decisions. The large matrix of states possible with the AFTI/F-16 flight control system illustrates the difficulty of both testing the system and choosing real-time pilot actions.
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    Report Date: January 1984
    No. Pages: 13
    Keywords:      Avionics; Digital systems; Display devices; F-16 aircraft; Flight control.
    Notes: Presented at IEE/AIAA 5th Digital Avionics Systems Conf., Seattle, 31 Oct. - 3 Nov. 1983.


  18. FLIGHT TEST EXPERIENCE WITH PILOT-INDUCED-OSCILLATION SUPPRESSION FILTERS , Technical Memorandum
    Authors: M. F. Shafer, R. E. Smith, J. F. Stewart and R. E. Bailey
    Report Number: NASA-TM-86028
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Digital flight control systems are popular for their flexibility, reliability, and power; however, their use sometimes results in deficient handling qualities, including pilot-induced oscillation (PIO), which can require extensive redesign of the control system. When redesign is not immediately possible, temporary solutions, such as the PIO suppression (PIOS) filter developed for the Space Shuttle, have been proposed. To determine the effectiveness of such PIOS filters on more conventional, high-performance aircraft, three experiments were performed using the NASA F-8 digital fly-by-wire and USAF/Calspan NT-33 variable-stability aircraft. Two types of PIOS filters were evaluated, using high-gain, precision tasks (close formation, probe-and-drogue refueling, and precision touch-and-go landing) with a time delay or a first-order lag added to make the aircraft prone to PIO. Various configurations of the PIOS filter were evaluated in the flight programs, and most of the PIOS filter configurations reduced the occurrence of PIOs and improved the handling qualities of the PIO-prone aircraft. These experiments also confirmed the influence of high-gain tasks and excessive control system time delay in evoking pilot-induced oscillations.
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    Report Date: January 1984
    No. Pages: 18
    Keywords:      Adaptive filters; Automatic flight control; Control stability; Digital systems; Fighter aircraft.
    Notes: Presented at the AIAA Atmospheric Flight Mech. Conf., Gatlinburg, Tenn., 15-17 Aug. 1983.


  19. AIR DATA POSITION-ERROR CALIBRATION USING STATE RECONSTRUCTION TECHNIQUES , Technical Memorandum
    Authors: S. A. Whitmore, T. J. Larson and L. J. Ehernberger
    Report Number: NASA-TM-86029
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: During the highly maneuverable aircraft technology (HiMAT) flight test program recently completed at NASA Ames Research Center's Dryden Flight Research Facility, numerous problems were experienced in airspeed calibration. This necessitated the use of state reconstruction techniques to arrive at a position-error calibration. For the HiMAT aircraft, most of the calibration effort was expended on flights in which the air data pressure transducers were not performing accurately. Following discovery of this problem, the air data transducers of both aircraft were wrapped in heater blankets to correct the problem. Additional calibration flights were performed, and from the resulting data a satisfactory position-error calibration was obtained. This calibration and data obtained before installation of the heater blankets were used to develop an alternate calibration method. The alternate approach took advantage of high-quality inertial data that was readily available. A linearized Kalman filter (LKF) was used to reconstruct the aircraft's wind-relative trajectory; the trajectory was then used to separate transducer measurement errors from the aircraft position error. This calibration method is accurate and inexpensive. The LKF technique has an inherent advantage of requiring that no flight maneuvers be specially designed for airspeed calibrations. It is of particular use when the measurements of the wind-relative quantities are suspected to have transducer-related errors.
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    Report Date: September 1984
    No. Pages: 31
    Keywords:      Calibrating; Flight tests; Flow velocity; Highly maneuverable aircraft; Kalman filters.


  20. NASTRAN/FLEXSTAB PROCEDURE FOR STATIC AEROELASTIC ANALYSIS DOCUMENT , Technical Memorandum
    Authors: L. S. Schuster
    Report Number: NASA-TM-84897
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Presented is a procedure for using the FLEXSTAB External Structural Influence Coefficients (ESIC) computer program to produce the structural data necessary for the FLEXSTAB Stability Derivatives and Static Stability (SD&SS) program. The SD&SS program computes trim state, stability derivatives, and pressure and deflection data for a flexible airplane having a plane of symmetry. The procedure used a NASTRAN finite-element structural model as the source of structural data in the form of flexibility matrices. Selection of a set of degrees of freedom, definition of structural nodes and panels, reordering and reformatting of the flexibility matrix, and redistribution of existing point mass data are among the topics discussed. Also discussed are boundary conditions and the NASTRAN substructuring technique.
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    Report Date: September 1984
    No. Pages: 21
    Keywords:      Aircraft design; Aircraft models; Aircraft structures; Computer programs; Deflection.


  21. STARS: A GENERAL-PURPOSE FINITE ELEMENT COMPUTER PROGRAM FOR ANALYSIS OFENGINEERING STRUCTURES , Reference Publication
    Authors: K. K. Gupta
    Report Number: NASA-RP-1129
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: STARS (Structural Analysis Routines) is primarily an interactive, graphics-oriented, finite-element computer program for analyzing the static, stability, free vibration, and dynamic responses of damped and undamped structures, including rotating systems. The element library consists of one-dimensional (1-D) line elements, two-dimensional (2-D) triangular and quadrilateral shell elements, and three-dimensional (3-D) tetrahedral and hexahedral solid elements. These elements enable the solution of structural problems that include truss, beam, space frame, plane, plate, shell, and solid structures, or any combination thereof. Zero, finite, and interdependent deflection boundary conditions can be implemented by the program. The associated dynamic response analysis capability provides for initial deformation and velocity inputs, whereas the transient excitation may be either forces or accelerations. An effective in-core or out-of-core solution strategy is automatically employed by the program, depending on the size of the problem. Data input may be at random within a data set, and the program offers certain automatic data-generation features. Input data are formatted as an optimal combination of free and fixed formats. Interactive graphics capabilities enable convenient display of nodal deformations, mode shapes, and element stresses.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 39
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    Report Date: October 1984
    No. Pages: 68
    Keywords:      Computer programs; Dynamic structural analysis; Finite element method; FORTRAN; Structural engineering.


  22. SPACE SHUTTLE PILOT-INDUCED-OSCILLATION RESEARCH TESTING , Technical Memorandum
    Authors: B. G. Powers
    Report Number: NASA-TM-86034
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The simulation requirements for investigation of pilot-induced-oscillation (PIO) characteristics during the landing phase are discussed. Orbiters simulations and F-8 digital fly-by-wire aircraft tests are addressed.
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    Report Date: February 1984
    No. Pages: 10
    Keywords:      Computerized simulation; F-8 aircraft; Oscillations; Pilot induced oscillation; Pilot performance.


  23. EFFECT OF CREEP IN TITANIUM ALLOY TI-6AL-4V AT ELEVATED TEMPERATURE ON AIRCRAFT DESIGN AND FLIGHT TEST , Technical Memorandum
    Authors: J. M. Jenkins
    Report Number: NASA-TM-86033
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Short-term compressive creep tests were conducted on three titanium alloy Ti-6Al-4V coupons at three different stress levels at a temperature of 714 K (825 F). The test data were compared to several creep laws developed from tensile creep tests of available literature. The short-term creep test data did not correlate well with any of the creep laws obtained from available literature. The creep laws themselves did not correlate well with each other. Short-term creep does not appear to be very predictable for titanium alloy Ti-6Al-4V. Aircraft events that result in extreme, but short-term temperature and stress excursions for this alloy should be approached cautiously. Extrapolations of test data and creep laws suggest a convergence toward predictability in the longer-term situation.
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    Subject Category: 39
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    Report Date: February 1984
    No. Pages: 11
    Keywords:      Aircraft design; Compression tests; Creep tests; Flight tests; High temperature tests.


  24. A COMPARISON OF WORTMANN AIRFOIL COMPUTER-GENERATED LIFT AND DRAG POLARS WITH FLIGHT AND WIND TUNNEL RESULTS , Technical Memorandum
    Authors: A. H. Bowers and A. G. Sim
    Report Number: NASA-TM-86035
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Computations of drag polars for a low-speed Wortmann sailplane airfoil are compared with both wind tunnel and flight test results. Excellent correlation was shown to exist between computations and flight results except when separated flow regimes were encountered. Smoothness of the input coordinates to the PROFILE computer program was found to be essential to obtain accurate comparisons of drag polars or transition location to either the flight or wind tunnel flight results.
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    Subject Category: 02
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    Report Date: November 1984
    No. Pages: 16
    Keywords:      Aerodynamic drag; Airfoils; Computerized simulation; Gliders; Lift.


  25. PERIPHERAL VISION HORIZON DISPLAY (PVHD) , Conference Publication
    Authors: Various
    Report Number: NASA-CP-2306
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A Canadian invention, the peripheral vision horizon display (PVHD), shows promise in alleviating vertigo or disorientation in pilots flying under instrument conditions and easing the piloting task when flying in weather or other conditions requiring close attention to aircraft attitude instruments. A diversity of research and applied work was being done to investigate and validate the benefits of the PVHD during the years immediately preceding this conference. Organizers of the conference were able to assemble a group of outstanding presenters representing academic, industrial, and military. The theoretical foundation and applied use of the PVHD are discussed, and results from operational tests are presented.
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    Subject Category: 06
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    Report Date: April 1984
    No. Pages: 136
    Keywords:      Attitude indicators; Conferences; Display devices; Instrument flight rules; Peripheral vision.
    Notes: Conf. held at Edwards, Calif., 15-16 Mar. 1983.


  26. THE DEVELOPMENT OF AN AIRBORNE INSTRUMENTATION COMPUTER SYSTEM FOR FLIGHT TEST , Technical Memorandum
    Authors: G. A. Bever
    Report Number: NASA-TM-86036
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Instrumentation interfacing frequently requires the linking of intelligent systems together, as well as requiring the link itself to be intelligent. The airborne instrumentation computer system (AICS) was developed to address this requirement. Its small size, approximately 254 by 133 by 140 mm (10 by 51/4 by 51/2 in), standard bus, and modular board configuration give it the ability to solve instrumentation interfacing and computation problems without forcing a redesign of the entire unit. This system has been used on the F-15 aircraft digital electronic engine control (DEEC) and its follow on engine model derivative (EMD) project and in an OV-1C Mohawk aircraft stall speed warning system. The AICS is presently undergoing configuration for use on an F-104 pace aircraft and on the advanced fighter technology integration (AFTI) F-111 aircraft.
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    Subject Category: 06
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    Report Date: April 1984
    No. Pages: 16
    Keywords:      Digital systems; F-15 aircraft; Flight tests; Microprocessors; Warning systems.
    Notes: Presented at the AGARD Flight Mech. Panel Symp. on Flight Test Tech., Lisbon, 2-5 Apr. 1984.


  27. A REVIEW OF RECENT DEVELOPMENTS IN FLIGHT TEST TECHNIQUES AT THE AMES RESEARCH CENTER, DRYDEN FLIGHT RESEARCH FACILITY , Technical Memorandum
    Authors: G. P. Layton
    Report Number: NASA-TM-86039
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: New flight test techniques in use at Ames Dryden are reviewed. The use of the pilot in combination with ground and airborne computational capabilities to maximize data return is discussed, including the remotely piloted research vehicle technique for high-risk testing, the remotely augmented vehicle technique for handling qualities research, and use of ground computed flight director information to fly unique profiles such as constant Reynolds number profiles through the transonic flight regime. Techniques used for checkout and design verification of systems-oriented aircraft are discussed, including descriptions of the various simulations, iron bird setups, and vehicle tests. Some newly developed techniques to support the aeronautical research disciplines are discussed, including a new approach to position-error determination, and the use of a large skin friction balance for the measurement of drag caused by various excrescencies.
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    Report Date: April 1984
    No. Pages: 17
    Keywords:      Flight tests; Pilot performance; Remotely piloted vehicles; Systems analysis; Systems integration.
    Notes: Presented at the Canadian Aeronautics and Space Inst. (CASI) Flight Test Symp., Cold Lake, Alberta, 11-12 Apr. 1984.


  28. COMPUTER CONTROL FOR AUTOMATED FLIGHT TEST MANEUVERING , Journal Article
    Authors: E. L. Duke and F. P. Jones
    Report Number: H-1239
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The application of an experimental flight test maneuver autopilot test technique for collecting aerodynamic and structural flight research data on a highly maneuverable aircraft is described in this paper. This technique, which was developed to increase the quality and quantity of data obtained during flight test, was applied to the highly maneuverable aircraft technology (HiMAT) vehicle. A primary flight experiment was to verify the design techniques used to develop the HiMAT aerodynamics and structures. This required the performance of maneuvers for collection of large quantities of high-quality pressure distribution, loads, and wing and canard deflection data. Flight data obtained while executing these research maneuvers are presented to demonstrate the effectiveness of this new technique.
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    Report Date: October 1984
    No. Pages: 7
    Keywords:      Aircraft maneuvers; Automatic pilots; Computer systems design; Control systems design; Flight tests.
    Notes: Journal of Aircraft (ISSN 0021-8669), vol. 21, Oct. 1984, p. 776-782.


  29. HIGHLY INTEGRATED DIGITAL ENGINE CONTROL SYSTEM ON AN F-15 AIRPLANE , Technical Memorandum
    Authors: F. W. Burcham, Jr. and E. A. Haering, Jr.
    Report Number: NASA-TM-86040
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The Highly Integrated Digital Electronic Control (HIDEC) program will demonstrate and evaluate the improvements in performance and mission effectiveness that result from integrated engine/airframe control systems. This system is being used on the F-15 airplane. An integrated flightpath management mode and an integrated adaptive engine stall margin mode are implemented into the system. The adaptive stall margin mode is a highly integrated mode in which the airplane flight conditions, the resulting inlet distortion, and the engine stall margin are continuously computed; the excess stall margin is used to uptrim the engine for more thrust. The integrated flightpath management mode optimizes the flightpath and throttle setting to reach a desired flight condition. The increase in thrust and the improvement in airplane performance is discussed.
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    Report Date: June 1984
    No. Pages: 13
    Keywords:      Airborne/spaceborne computers; Computer programs; Engine airframe integration; Flight control; Performance prediction.
    Notes: Presented at the 20th AIAA/ASME/SAE Joint Propulsion Conf., Cincinnati, 11-13 Jun. 1984.


  30. FLIGHT CHARACTERISTICS OF A MANNED, LOW-SPEED, CONTROLLED DEEP STALL VEHICLE , Technical Memorandum
    Authors: A. G. Sim
    Report Number: NASA-TM-86041
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A successful manned, low speed, controlled deep stall flight research program was conducted at NASA Ames Research Center's Dryden Flight Research Facility. Piloting techniques were established that enabled the pilot to attain and stabilize on an angle of attack in the 30 deg to 72 deg range. A flight determined aerodynamic data base was established for angles of attack as high as 72 deg. Poor lateral directional flying qualities were encountered at angles of attack above 60 deg. Insight into the high angle of attack lateral directional dynamics was gained through a basic root locus analysis.
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    Report Date: August 1984
    No. Pages: 10
    Keywords:      Aerodynamic stalling; Angle of attack; Data bases; Flight characteristics; Low speed.


  31. MINIMUM TIME AND FUEL FLIGHT PROFILES FOR AN F-15 AIRPLANE WITH A HIGHLY INTEGRATED DIGITAL ELECTRONIC CONTROL (HIDEC) SYSTEM , Technical Memorandum
    Authors: E. A. Haering, Jr. and F. W. Burcham, Jr.
    Report Number: NASA-TM-86042
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A simulation study was conducted to optimize minimum time and fuel consumption paths for an F-15 airplane powered by two F100 Engine Model Derivative (EMD) engines. The benefits of using variable stall margin (uptrim) to increase performance were also determined. This study supports the NASA Highly Integrated Digital Electronic Control (HIDEC) program. The basis for this comparison was minimum time and fuel used to reach Mach 2 at 13,716 m (45,000 ft) from the initial conditions of Mach 0.15 at 1524 m (5000 ft). Results were also compared to a pilot's estimated minimum time and fuel trajectory determined from the F-15 flight manual and previous experience. The minimum time trajectory took 15 percent less time than the pilot's estimate for the standard EMD engines, while the minimum fuel trajectory used 1 percent less fuel than the pilot's estimate for the minimum fuel trajectory. The F-15 airplane with EMD engines and uptrim, was 23 percent faster than the pilot's estimate. The minimum fuel used was 5 percent less than the estimate.
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    Report Date: June 1984
    No. Pages: 25
    Keywords:      Combustion efficiency; Digital systems; Flight paths; Flight simulation; Fuel consumption.


  32. EFFECT OF CONTROL LOGIC MODIFICATIONS ON AIRSTART PERFORMANCE OF F100 ENGINE MODEL DERIVATIVE ENGINES IN AN F-15 AIRPLANE , Technical Memorandum
    Authors: D. B. Crawford and F. W. Burcham, Jr.
    Report Number: NASA-TM-85900
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A series of airstarts were conducted in an F-15 airplane with two prototype Pratt and Whitney F100 Engine Model Derivative engines equipped with Digital Electronic Engine Control (DEEC) systems. The airstart envelope and the time required for airstarts were defined. Comparisons were made between the original airstart logic, and modified logic which was designed to improve the airstart capability. Spooldown airstarts with the modified logic were more successful at lower altitudes than were those with the original logic. Spooldown airstart times ranged from 33 seconds at 250 knots to 83 seconds at 175 knots. The modified logic improved the airstart time from 31 percent to 53 percent, with the most improved times at slower airspeeds. Jet fuel starter (JFS)-assisted airstarts were conducted at 7000 m and airstart times were significantly faster than unassisted airstarts. The effect of altitude on airstart times was small.
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    Report Date: August 1984
    No. Pages: 30
    Keywords:      Aircraft control; Aircraft design; Aircraft engines; Digital systems; Electronic control.


  33. FLIGHT INVESTIGATION OF VARIOUS CONTROL INPUTS INTENDED FOR PARAMETER ESTIMATION , Technical Memorandum
    Authors: M. F. Shafer
    Report Number: NASA-TM-85901
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: An experiment assessing the stability and control derivatives resulting from various control inputs was undertaken using the F-8 digital fly by wire aircraft. Improved control inputs have been proposed as a means of making stability and contol derivative estimation more efficient, thus reducing the cost of flight testing and data analysis. The subject inputs were either generated by the pilot or preprogrammed in a remote ground computer and telemetered to the aircraft. Nine preprogrammed inputs and three pilot generated inputs were assessed at subsonic and supersonic flight conditions, and both unaugmented and highly augmented flight control systems were used. Effects of input amplitude were also assessed. The inputs were divided into two general types - sinusoidal or with corners (a rapid and distinct change in slope). The inputs with corners, performed in the unaugmented mode, produced the best sets of stability and control derivatives. The simplest of these inputs, the pilot generated doublet, produced sets of derivatives as good as those produced by the more complex inputs. Small inputs produced worse derivatives than the unaugmented mode, and sinusoidal inputs produced worse derivatives than corner containing inputs.
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    Subject Category: 08
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    Report Date: August 1984
    No. Pages: 20
    Keywords:      F-8 aircraft; Flight tests; Fly by wire control; Maximum likelihood estimates; Parameter identification.
    Notes: Presented at the AIAA Atmospheric Flight Mech. Conf., Seattle, 21-23 Aug. 1984.


  34. SIMULATOR EVALUATION OF A REMOTELY PILOTED VEHICLE LATERAL LANDING TASK USING A VISUAL DISPLAY , Technical Memorandum
    Authors: S. K. Sarrafian
    Report Number: NASA-TM-85903
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A simulator evaluation of a remotely piloted research vehicle was conducted at NASA Ames Research Center's Dryden Flight Research Facility to determine the utility of a visual display when studying the influence of changes in the lateral stick gearing gains during landing approaches. The test vehicle used in this study was a highly maneuverable aircraft technology (HiMAT) aircraft, which is a 0.44 scale version of an envisioned small, single seat fighter airplane. Handling qualities ratings and comments obtained from pilots using a simulated visual display of a runway scene and a simulated instrument landing system (ILS) display were compared with the results of actual flight tests. The visual display was found to provide an adequate representation of the test vehicle in a visual landing approach, and it improved the roll response cues provided to the pilot. The handling qualities ratings and comments for flight and simulation visual landing approaches correlated well. The ILS simulation results showed reduced correlation compared with the flight results for ILS approaches. Handling qualities criteria for remotely piloted research vehicles are also discussed in this paper.
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    Report Date: August 1984
    No. Pages: 16
    Keywords:      Controllability; Display devices; Flight tests; Landing; Remotely piloted vehicles.
    Notes: Presented at the AIAA Atmospheric Flight Mech. Conf., Seattle, 21-23 Aug. 1984.


  35. PRELIMINARY FLIGHT TEST RESULTS OF THE F100 EMD ENGINE IN AN F-15 AIRPLANE , Technical Memorandum
    Authors: L. P. Myers and F. W. Burcham, Jr.
    Report Number: NASA-TM-85902
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: flight evaluation of the F100 Engine Model Derivative (EMD) is conducted. The F100 EMD is an advanced version of the F100 engine that powers the F15 and F16 airplanes. The F100 EMD features a bigger fan, higher temperature turbine, a Digital Electronic Engine Control system (DEEC), and a newly designed 16 segment afterburner, all of which results in a 15 to 20 percent increase in sea level thrust. The flight evaluations consist of investigation of performance (thrust, fuel flow, and airflow) and operability (transient response and airstart) in the F-15 airplane. The performance of the F100 EMD is excellent. Aircraft acceleration time to Mach 2.0 is reduced by 23 percent with two F100 EMD engines. Several anomalies are discovered in the operability evaluations. A software change to the DEEC improved the throttle, and subsequent Cooper Harper ratings of 3 to 4 are obtained. In the extreme upper left hand corner of the flight enveloped, compressor stalls occurr when the throttle is retarded to idle power. These stalls are not predicted by altitude facility tests or stability for the compressor.
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    Report Date: June 1984
    No. Pages: 12
    Keywords:      Engine design; Engine tests; Jet engines; Performance tests; Propulsion system configurations.
    Notes: Presented at the 20th AIAA/ASME/SAE Joint Propulsion Conf., Cincinnati, 11-13 Jun. 1984.


  36. MEASUREMENTS OF PILOT TIME DELAY AS INFLUENCED BY CONTROLLER CHARACTERISTICS AND VEHICLES TIME DELAYS , Conference Paper
    Authors: C. M. Privoznik, D. T. Berry and A. G. Bartoli
    Report Number: H-1253
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A study to measure and compare pilot time delay when using a space shuttle rotational hand controller and a more conventional control stick was conducted at NASA Ames Research Center's Dryden Flight Research Facility. The space shuttle controller has a palm pivot in the pitch axis. The more conventional controller used was a general-purpose engineering simulator stick that has a pivot length between that of a typical aircraft center stick and a sidestick. Measurements of the pilot's effective time delay were obtained through a first-order, closed-loop, compensatory tracking task in pitch. The tasks were implemented through a space shuttle cockpit simulator and a critical task tester device. The study consisted of 450 data runs with four test pilots and one nonpilot, and used three control stick configurations and two system delays. Results showed that the heavier conventional stick had the lowest pilot effective time delays associated with it, whereas the shuttle and light conventional sticks each had similar higher pilot time delay characteristics. It was also determined that each control stick showed an increase in pilot time delay when the total system delay was increased.
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    Subject Category: 54
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    Report Date: September 1984
    No. Pages: 12
    Keywords:      Controllers; Delay; Pilot performance; Pilots (personnel); Time lag.
    Notes: In its 20th Ann. Conf. on Manual Control, Vol. 1 p 210-221. NASA CP-2341.


  37. THERMAL RESPONSE OF SPACE SHUTTLE WING DURING REENTRY HEATING , Technical Memorandum
    Authors: L. Gong, W. L. Ko and R. D. Quinn
    Report Number: NASA-TM-85907
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A structural performance and resizing (SPAR) finite element thermal analysis computer program was used in the heat transfer analysis of the space shuttle orbiter that was subjected to reentry aerodynamic heatings. One wing segment of the right wing (WS 240) and the whole left wing were selected for the thermal analysis. Results showed that the predicted thermal protection system (TPS) temperatures were in good agreement with the space transportation system, trajectory 5 (STS-5) flight-measured temperatures. In addition, calculated aluminum structural temperatures were in fairly good agreement with the flight data up to the point of touchdown. Results also showed that the internal free convection had a considerable effect on the change of structural temperatures after touchdown.
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    Subject Category: 16
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    Report Date: January 1984
    No. Pages: 18
    Keywords:      Buckling; Finite element method; Heat transfer; Reentry effects; Thermal protection.
    Notes: Presented at the 19th AIAA Thermophys. Conf., Snowmass, Colo., 24-28 Jun. 1984.


  38. SOFTWARE CONTROL AND SYSTEM CONFIGURATION MANAGEMENT: A SYSTEMS-WIDE APPROACH , Technical Memorandum
    Authors: K. L. Petersen and C. Flores, Jr.
    Report Number: NASA-TM-85908
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A comprehensive software control and system configuration management process for flight-crucial digital control systems of advanced aircraft has been developed and refined to insure efficient flight system development and safe flight operations. Because of the highly complex interactions among the hardware, software, and system elements of state-of-the-art digital flight control system designs, a systems-wide approach to configuration control and management has been used. Specific procedures are implemented to govern discrepancy reporting and reconciliation, software and hardware change control, systems verification and validation testing, and formal documentation requirements. An active and knowledgeable configuration control board reviews and approves all flight system configuration modifications and revalidation tests. This flexible process has proved effective during the development and flight testing of several research aircraft and remotely piloted research vehicles with digital flight control systems that ranged from relatively simple to highly complex, integrated mechanizations.
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    Report Date: August 1984
    No. Pages: 21
    Keywords:      Airborne/spaceborne computers; Automatic flight control; Computer programs; Configuration management; Software engineering.
    Notes: Presented at IEEE/AIAA 5th Digital Avionics Systems Conf., Seattle, 31 Oct. - 3 Nov. 1983.


  39. X-29A LONGITUDINAL AND DIRECTIONAL FORCE AND MOMENT SUPPLEMENTAL TRANSONIC WIND TUNNEL TEST RESULTS , Technical Memorandum
    Authors: A. H. Bowers
    Report Number: NASA-TM-85909
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Aerodynamic data from NASA Ames Research Center's 11-Foot Transonic Wind Tunnel are plotted for the 1/8-scale X-29A forward-swept wing aircraft model. Eleven configurations were tested to provide supplemental data to investigate single surface failure modes, complex nonlinearities, and model buildup. These data can be used for control system refinements, pilot training, flight planning, and aerodynamic model validation. Data are presented as corrected wind tunnel data without analysis to document results that are being used for the aerodynamic model.
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    Report Date: August 1984
    No. Pages: 289
    Keywords:      Models; Swept forward wings; Transonic wind tunnels; Wind tunnel tests; X-29 aircraft.


  40. ACTIVE CONTROL TECHNOLOGY EXPERIENCE WITH THE SPACE SHUTTLE IN THE LANDING REGIME , Technical Memorandum
    Authors: B. G. Powers
    Report Number: NASA-TM-85910
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The shuttle program took on the challenge of providing a manual landing capability for an operational vehicle returning from orbit. Some complex challenges were encountered in developing the longitudinal flying qualities required to land the orbiter manually in an operational environmental. Approach and landing test flights indicated a tendency for pilot-induced oscillation near landing. Changes in the operational procedures reduced the difficulty of the landing task, and an adaptive stick filter was incorporated to reduce the severity of any pilot-induced oscillatory motions. Fixed-base, moving-base, and in-flight simulations were used for the evaluations, and in general, flight simulation was the only reliable means of assessing the low-speed longitudinal flying qualities problems. Overall, the orbiter control system and operational procedures have produced a good capability for routinely performing precise landings in a large, unpowered vehicle with a low lift-to-drag ratio.
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    Subject Category: 08
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    Report Date: October 1984
    No. Pages: 12
    Keywords:      Active control; Flight characteristics; Flight simulation; Space shuttles; Spacecraft landing.
    Notes: Presented at the AGARD Flight Mech. Panel Symp. on Active Control Systems, Toronto, 15-18 Oct. 1984.


  41. ROTOR SYSTEMS RESEARCH AIRCRAFT AIRPLANE CONFIGURATION FLIGHT-TEST RESULTS , Technical Memorandum
    Authors: W. D. Painter
    Report Number: NASA-TM-85911
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The rotor systems research aircraft (RSRA) has undergone ground and flight tests, primarily as a compound aircraft. The purpose was to train pilots and to check out and develop the design flight envelope. The preparation and flight test of the RSRA in the airplane, or fixed-wind, configuration are reviewed and the test results are discussed.
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    Report Date: October 1984
    No. Pages: 13
    Keywords:      Aerodynamics; Aerospace technology transfer; Flight tests; Helicopters; Rotor systems research aircraft.
    Notes: Presented at the AIAA Aircraft Design Systems and Operations Meeting, San Diego, Calif., 31 Oct. - 2 Nov. 1984.


  42. ROLE OF RESEARCH AIRCRAFT IN TECHNOLOGY DEVELOPMENT , Technical Memorandum
    Authors: K. J. Szalai
    Report Number: NASA-TM-85913
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The United States's aeronautical research program has been rich in the use of research aircraft to explore new flight regimes, develop individual aeronautical concepts, and investigate new vehicle classes and configurations. This paper reviews the NASA supercritical wing, digital fly-by-wire, HiMAT, and AD-1 oblique-wing flight research programs, and draws from these examples general conclusions regarding the role and impact of research aircraft in technology development. The impact of a flight program on spinoff technology is also addressed. The secondary, serendipitous results are often highly significant. Finally, future research aircraft programs are examined for technology trends and expected results.
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    Report Date: January 1984
    No. Pages: 30
    Keywords:      Aerodynamic configurations; Flight tests; Fly by wire control; Research aircraft; Technology assessment.
    Notes: Presented at the AIAA/AHS/ASEE Aircraft Design Systems and Operation Meeting, 31 Oct. - 2 Nov. 1984, San Diego, Calif.


  43. PROPULSION CONTROL EXPERIENCE USED IN THE HIGHLY INTEGRATED DIGITAL ELECTRONIC CONTROL (HIDEC) PROGRAM , Technical Memorandum
    Authors: L. P. Myers and F. W. Burcham, Jr.
    Report Number: NASA-TM-85914
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The highly integrated digital electronic control (HIDEC) program will integrate the propulsion and flight control systems on an F-15 airplane at NASA Ames Research Center's Dryden Flight Research Facility. Ames-Dryden has conducted several propulsion control programs that have contributed to the HIDEC program. The digital electronic engine control (DEEC) flight evaluation investigated the performance and operability of the F100 engine equipped with a full-authority digital electronic control system. Investigations of nozzle instability, fault detection and accommodation, and augmentor transient capability provided important information for the HIDEC program. The F100 engine model derivative (EMD) was also flown in the F-15 airplane, and airplane performance was significantly improved. A throttle response problem was found and solved with a software fix to the control logic. For the HIDEC program, the F100 EMD engines equipped with DEEC controls will be integrated with the digital flight control system. The control modes to be implemented are an integrated flightpath management mode and an integrated adaptive engine control system mode. The engine control experience that will be used in the HIDEC program is discussed.
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    Report Date: October 1984
    No. Pages: 18
    Keywords:      Aircraft engines; Digital systems; F-15 aircraft; Flight control; Numerical control.
    Notes: Presented at the SAE Aerospace Congr. and Exposition, Long Beach, Calif., 15-18 Oct. 1984.


  44. TEST EXPERIENCE ON AN ULTRARELIABLE COMPUTER COMMUNICATION NETWORK , Technical Memorandum
    Authors: L. W. Abbott
    Report Number: NASA-TM-85915
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The dispersed sensor processing mesh (DSPM) is an experimental, ultra-reliable, fault-tolerant computer communications network that exhibits an organic-like ability to regenerate itself after suffering damage. The regeneration is accomplished by two routines - grow and repair. This paper discusses the DSPM concept for achieving fault tolerance and provides a brief description of the mechanization of both the experiment and the six-node experimental network. The main topic of this paper is the system performance of the growth algorithm contained in the grow routine. The characteristics imbued to DSPM by the growth algorithm are also discussed. Data from an experimental DSPM network and software simulation of larger DSPM-type networks are used to examine the inherent limitation on growth time by the growth algorithm and the relationship of growth time to network size and topology.
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    Subject Category: 62
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    Report Date: December 1984
    No. Pages: 9
    Keywords:      Communication networks; Computer networks; Digital systems; Fault tolerance; Reliability.
    Notes: Presented at the AIAA/IEEE 6th Digital Avionics Conf., Baltimore, 3-6 Dec. 1984.


  45. CLOSING THE DESIGN LOOP ON HIMAT (HIGHLY MANEUVERABLE AIRCRAFT TECHNOLOGY) , Technical Memorandum
    Authors: T. W. Putnam and M. R. Robinson
    Report Number: NASA-TM-85923
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The design methodology used in the HiMAT program and the wind tunnel development activities are discussed. Selected results from the flight test program are presented and the strengths and weaknesses of testing advanced technology vehicles using the RPV concept is examined. The role of simulation on the development of digital flight control systems and in RPV's in particular is emphasized.
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    Subject Category: 05
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    Report Date: December 1984
    No. Pages: 12
    Keywords:      Aerodynamics; Digital command systems; Flight tests; Highly maneuverable aircraft; Remote control.
    Notes: Presented at the 14th Congr. of the International Council of the Aeronautical Sciences, Toulouse, 9-14 Sep. 1984.


  46. THE WESTERN AERONAUTICAL TEST RANGE OF NASA AMES RESEARCH CENTER , Technical Memorandum
    Authors: A. L. Moore
    Report Number: NASA-TM-85924
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: An overview of the Western Aeronautical Test Range (WATR) of NASA Ames Research Center (ARC) is presented in this paper. The three WATR facilities are discussed, and three WATR elements - mission control centerns, communications systems, real-time processing and display systems, and tracking systems -are reviewed. The relationships within the NASA WATR, with respect to the NASA aeronautics program, are also discussed.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 09
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    Report Date: January 1984
    No. Pages: 18
    Keywords:      Communication equipment; Real time operation; Spacecraft tracking; Test facilities; Test ranges.
    Notes: Presented at the 23rd AIAA Aerospace Sci. Meeting, Reno, Nev., 14-17 Jan. 1985.
 
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