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  • 1
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    Aeroelastic control of oblique-wing aircraft (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The U.S. Navy and NASA are currently involved in the design and development of an unsymmetric-skew-wing aircraft capable of 65 deg wing sweep and flight at Mach 1.6. A generic skew-wing aircraft model was developed for 45 deg wing skew at a flight condition of Mach 0.70 and 3048 m altitude. At this flight condition the aircraft has a wing flutter mode. An active implementable control law was developed using the linear quadratic Gaussian design technique. A method of modal residualization was used to reduce the order of the controller used for flutter suppression.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Determination of propulsion-system-induced forces and moments of a Mach 3 cruise aircraft (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: During the joint NASA/USAF flight research program with the YF-12 airplane, the Dutch roll damping was found to be much less during automatic inlet operation than during fixed inlet operation at Mach numbers greater than 2.5 and with the yaw stability augmentation system off. It was concluded that the significant reduction in Dutch roll damping was due to the forces and moments induced by the variable-geometry features of the inlet. Two stability-derivative extraction techniques were applied to the flight data; the recently developed Newton-Raphson technique and the time vector method. These techniques made it possible to determine the forces and moments generated by spike and bypass door movement.
    Keywords: AIRCRAFT
    Type: Parameter Estimation Tech. and Appl. in Aircraft Flight Testing; p 369-374
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Flight test experience in aircraft parameter identification (1972)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: An automatic method for determining stability and control derivatives from flight data is presented. The technique, a modification of the Newton-Raphsom method for derivative extraction, has a priori provision that makes use of initial estimates of the derivatives and provides a means of checking the validity of the results. Recommendations for applications of the method are included.
    Keywords: AIRCRAFT
    Type: AGARD Stability and Control te]; 13 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Flight experience with altitude hold and Mach hold autopilots on the YF-12 aircraft at Mach 3 (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The altitude hold mode of the YF-12A airplane was modified to include a high-pass-filtered pitch rate feedback along with optimized inner loop altitude rate proportional and integral gains. An autothrottle control system was also developed to control either Mach number or KEAS at the high-speed flight conditions. Flight tests indicate that, with the modified system, significant improvements are obtained in both altitude and speed control, and the combination of altitude and autothrottle hold modes provides the most stable aircraft platform thus far demonstrated at Mach 3 conditions.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 97-119
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Real-time flutter analysis of an active flutter-suppression system on a remotely piloted research aircraft (1983)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Flight-test results of the first three flights of an aeroelastic research wing are described. The flight flutter-test technique used to obtain real-time damping estimates from fast-frequency sweep data was obtained and the open-loop flutter boundary determined. Nyquist analyses of sweep maneuvers appear to provide additional valuable information about flutter suppression system operation, both in terms of phase-margin estimates and as a means of evaluating maneuver quality. An error in implementing the flutter-suppression system required in a one-half nominal gain configuration, which caused the wing to be unstable at lower Mach numbers than anticipated, and the vehicle experienced closed-loop flutter on its third flight. Real-time flutter-testing procedures were improved.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AGARD Ground(Flight Test Tech. and Correlation; 15 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    A review of supersonic cruise flight path control experience with the YF-12 aircraft (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Flight research with the YF-12 aircraft indicates that solutions to many handling qualities problems of supersonic cruise are at hand. Airframe/propulsion system interactions in the Dutch roll mode can be alleviated by the use of passive filters or additional feedback loops in the propulsion and flight control systems. Mach and altitude excursions due to atmospheric temperature fluctuations can be minimized by the use of a cruise autothrottle. Autopilot instabilities in the altitude hold mode have been traced to angle of attack-sensitive static ports on the compensated nose boom. For the YF-12, the feedback of high-passed pitch rate to the autopilot resolves this problem. Manual flight path control is significantly improved by the use of an inertial rate of climb display in the cockpit.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: Aircraft Safety and Operating Problems; p 147-164
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Handling qualities aspects of NASA YF-12 flight experience (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The handling qualities of the YF-12 airplane as observed during NASA research flights over the past five years were reviewed. Aircraft behavior during takeoff, acceleration, climb, cruise, descent, and landing are discussed. Pilot comments on the various flight phases and tasks are presented. Handling qualities parameters such as period, damping, amplitude ratios, roll-yaw coupling, and flight path response sensitivity are compared to existing and proposed handling qualities criteria. The influence of the propulsion systems, stability augmentation, autopilot systems, atmospheric gusts, and temperature changes are also discussed. YF-12 experience correlates well with flying qualities criteria, except for longitudinal short period damping, where existing and proposed criteria appear to be more stringent than necessary.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Proc. of the SCAR Conf., Part 1; p 193-214
    Format: application/pdf
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  • 8
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    Preliminary flight evaluation of an engine performance optimization algorithm (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A performance-seeking control (PSC) algorithm has undergone initial flight test evaluation in subsonic operation of a PW 1128-engined F-15; this algorithm is designed to optimize the quasi-steady performance of an engine for three primary modes: (1) minimum fuel consumption, (2) minimum fan-turbine inlet temperature (FTIT), and (3) maximum thrust. The flight test results have verified a thrust-specific fuel consumption reduction of 1 percent, up to 100 R decreases in FTIT, and increases of as much as 12 percent in maximum thrust. PSC technology promises to be of value in next-generation tactical and transport aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-1998
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Ground vibration test results for Drones for Aerodynamic and Structural Testing (DAST)/Aeroelastic Research Wing (ARW-1R) aircraft (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The drones for aerodynamic and structural testing (DAST) project was designed to control flutter actively at high subsonic speeds. Accurate knowledge of the structural model was critical for the successful design of the control system. A ground vibration test was conducted on the DAST vehicle to determine the structural model characteristics. This report presents and discusses the vibration and test equipment, the test setup and procedures, and the antisymmetric and symmetric mode shape results. The modal characteristics were subsequently used to update the structural model employed in the control law design process.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85906 , H-1261 , NAS 1.15:85906
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Eigensystem synthesis for active flutter suppression on an oblique-wing aircraft (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The application of the eigensystem synthesis technique to place the closed-loop eigenvalues and shape the closed-loop eigenvectors has not been practical for active flutter suppression, primarily because of the availability of only one control surface (aileron) for flutter suppression. The oblique-wing aircraft, because of its configuration, provides two independent surfaces (left and right ailerons), making the application of eigensystem synthesis practical. This paper presents the application of eigensystem synthesis using output feedback for the design of an active flutter suppression system for an oblique-wing aircraft. The results obtained are compared with those obtained by linear quadratic Gaussian techniques.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 86-2243
    Format: text
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