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  • AIRCRAFT STABILITY AND CONTROL  (9)
  • 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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    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
  • 3
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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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    NASA TECHNICAL REPORTS
  • 4
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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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    NASA TECHNICAL REPORTS
  • 5
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    Real-time flutter identification with close mode resolution (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Real-time flutter prediction including close modes can be effectively estimated from turbulence or on-board excitation with an Extended Kalman Filter (EKF) approach. A physically based model form enables prediction of the damping rate as well as damping, giving a time to instability estimate with its variance. The approach is recursive and can operate asynchronously to drop data outliers and hence is quite robust. Its speed is reasonable for on-line application but can also be used effectively as an off-line analysis tool for application to any modal testing situation.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 86-2019
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Development and flight test results of an autothrottle control system at Mach 3 cruise (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight test results obtained with the original Mach hold autopilot designed the YF-12C airplane which uses elevator control and a newly developed Mach hold system having an autothrottle integrated with an altitude hold autopilot system are presented. The autothrottle tests demonstrate good speed control at high Mach numbers and high altitudes while simultaneously maintaining control over altitude and good ride qualities. The autothrottle system was designed to control either Mach number or knots equivalent airspeed (KEAS). Excellent control of Mach number or KEAS was obtained with the autothrottle system when combined with altitude hold. Ride qualities were significantly better than with the conventional Mach hold system.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-1621 , H-1090
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Results from flight and simulator studies of a Mach 3 cruise longitudinal autopilot (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: At Mach numbers of approximately 3.0 and altitudes greater than 21,300 meters, the original altitude and Mach hold modes of the YF-12 autopilot produced aircraft excursions that were erratic or divergent, or both. Flight data analysis and simulator studies showed that the sensitivity of the static pressure port to angle of attack had a detrimental effect on the performance of the altitude and Mach hold modes. Good altitude hold performance was obtained when a high passed pitch rate feedback was added to compensate for angle of attack sensitivity and the altitude error and integral altitude gains were reduced. Good Mach hold performance was obtained when the angle of attack sensitivity was removed; however, the ride qualities remained poor.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-1180 , H-940
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Eigensystem synthesis for active flutter suppression on an oblique-wing aircraft (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    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: NASA-TM-88275 , H-1359 , NAS 1.15:88275 , AIAA PAPER 86-2243-CP , AIAA Guidance, Navigation and Control Conference; Aug 18, 1986 - Aug 20, 1986; Williamsburg, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Aeroelastic control of oblique-wing aircraft (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    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
    Type: NASA-TM-86808 , H-1346 , NAS 1.15:86808 , American Control Conference; Jun 18, 1986 - Jun 20, 1986; Seattle, WA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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