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  • 1
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    Analysis of aeroelastic model stability augmentation systems (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical and mechanization study was conducted for two flutter stability augmentation systems. One concept uses only the wing trailing edge control surface. Another concept uses leading and trailing edge control surfaces operating simultaneously. The combined use of leading and trailing edge control surfaces should improve the surface coupling (controllability) with vertical bending and torsional structural modes and decrease the coupling between bending and torsional modes. The study was directed toward stability augmentation systems characteristics for the supersonic transport aircraft.
    Keywords: AIRCRAFT
    Type: NASA-CR-132354 , D3-8390-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Analysis and testing of stability augmentation systems (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Testing and evaluation of stability augmentation systems for aircraft flight control were conducted. The flutter suppression system analysis of a scale supersonic transport wing model is described. Mechanization of the flutter suppression system is reported. The ride control synthesis for the B-52 aeroelastic model is discussed. Model analyses were conducted using equations of motion generated from generalized mass and stiffness data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132349 , D3-8884
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Analysis and testing of aeroelastic model stability augmentation systems (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Testing and evaluation of a stability augmentation system for aircraft flight control were performed. The flutter suppression system and synthesis conducted on a scale model of a supersonic wing for a transport aircraft are discussed. Mechanization and testing of the leading and trailing edge surface actuation systems are described. The ride control system analyses for a 375,000 pound gross weight B-52E aircraft are presented. Analyses of the B-52E aircraft maneuver load control system are included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132345 , D3-9245
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Subminiature hydraulic actuator (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Subminiature, single-vane rotary actuator for wind-tunnel test-model control-surface actuation systems presents severe torque and system band-pass requirements with stringent space and weight limitations. Actuator has very low leakage of fluid from one side to other, permitting use in precision position servo-systems.
    Keywords: MACHINERY
    Type: LAR-11522 , NASA Tech Briefs (ISSN 0145-319X); 3; 2; P. 277
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Design and evaluation of miniature control surface actuation systems for aeroelastic models. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: AIRCRAFT
    Type: AIAA PAPER 73-323 , Dynamics Specialists Conference; Mar 19, 1973 - Mar 20, 1973; Williamsburg, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    A wind-tunnel investigation of a B-52 model flutter suppression system (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Flutter modeling techniques have been successfully extended to the difficult case of the active suppression of flutter. The demonstration was conducted in a transonic dynamics tunnel using a 1/30 scale, elastic, dynamic model of a Boeing B-52 control configured vehicle. The results from the study show that with the flutter suppression system operating there is a substantial increase in the damping associated with the critical flutter mode. The results also show good correlation between the damping characteristics of the model and the aircraft.
    Keywords: AIRCRAFT
    Type: AIAA PAPER 74-401 , Structures, Structural Dynamics and Materials Conference; Apr 17, 1974 - Apr 19, 1974; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
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