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  • 1
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    The effects of stability augmentation on the gust response of a STOL aircraft during a curved manual approach (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The task of investigating the effect of SAS was formulated as two optimal control problems for stochastic systems: (1) to compute SAS gains with a rate model in the performance index algorithm; and (2) to calculate the pilot gains and system gust response using an optimal pilot model. Both problems were solved to yield reasonable low gains for the pilot and SAS, and the lateral directional mode poles and the longitudinal short period poles could be placed accurately by the model matching algorithm. Of the longitudinal (SAS) poles achieved, the vertical rms path error was least for the unaugmented poles. The lateral rms path error was an order of magnitude larger than the vertical error and showed a plus or minus 50 percent variation with SAS. It increased with dutch roll frequency and damping, and it decreased most significantly with increased roll stability. The variation in lateral error with bank angle for curved flight was also a significant function of the augmented poles.
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: NASA. Ames Res. Center 11th Ann. Conf. on Manual Control; p 486-503
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Manual control displays for a four-dimensional landing approach (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Six instrument rated pilots flew a STOL fixed base simulator to study the effectiveness of three displays for a four dimensional approach. The three examined displays were a digital readout of forward position error, a digital speed command, and an analog display showing forward position error and error prediction. A flight director was used in all conditions. All test runs were for a typical four dimensional approach in moderate turbulence that included a change in commanded ground speed, a change in flight path angle, and two standard rate sixty degree turns. Use of the digital forward position error display resulted in large overshoot in the forward position error. Some type of lead (rate or prediction information) was shown to be needed. The best overall performance was obtained using the speed command display. It was demonstrated that curved approaches can be flown with relative ease.
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: NASA. Ames Res. Center 11th Ann. Conf. on Manual Control; p 245-267
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Effects of dynamic aeroelasticity on handling qualities and pilot rating (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pilot performance parameters, such as pilot ratings, tracking errors, and pilot comments were determined for a longitudinal pitch tracking task using a large, flexible bomber with parametric 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 attitude-director display of pitch command, pitch angle, and pitch error. Low frequency structural flexibility significantly affects the handling qualities and pilot ratings in the task evaluated.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-155339 , REPT-77-7
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Ride quality sensitivity to SAS control law and to handling quality variations (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The RQ trends which large flexible aircraft exhibit under various parameterizations of control laws and handling qualities are discussed. A summary of the assumptions and solution technique, a control law parameterization review, a discussion of ride sensitivity to handling qualities, and the RQ effects generated by implementing relaxed static stability configurations are included.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-148207
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A unique formulation of elastic airplane longitudinal equations of motion (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Control-configured vehicle technology has increased the demand for detailed analysis of dynamic stability and control, handling and ride qualities, and control system dynamics at early stages of preliminary design. An approximate, but reasonably accurate, set of equations of motion are needed for these early analyses. Such a formulation is developed for the longitudinal dynamics of elastic airplanes. It makes use of only rigid-body aerodynamic stability derivatives in formulating the forces and moments due to elastic motion. Verification of accuracy using data for the B-1 airplane shows very good agreement. Frequencies and damping ratios of the coupled modes corresponding to complex roots of the characteristic equations agree closely with four symmetric elastic modes included.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-148205
    Format: application/pdf
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  • 6
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    Minimum control power for VTOL aircraft stability augmentation (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: VTOL aircraft stability augmentation system design based on control theory state variable methods, using minimum power levels
    Keywords: AIRCRAFT
    Type: ; YSICA STATUS SOLIDI
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Effects of control laws and relaxed static stability on vertical ride quality of flexible aircraft (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: State variable techniques are utilized to generate the RMS vertical load factors for the B-52H and B-1 bombers at low level, mission critical, cruise conditions. A ride quality index is proposed to provide meaningful comparisons between different controls or conditions. Ride quality is shown to be relatively invariant under various popular control laws. Handling quality variations are shown to be major contributors to ride quality variations on both vehicles. Relaxed static stability is artificially implemented on the study vehicles to investigate its effects on ride quality. The B-52H ride quality is generally degraded when handling characteristics are automatically restored by a feedback control to the original values from relaxed stability conditions. The B-1 airplane shows little ride quality sensitivity to the same analysis due to the small rigid body contribution to load factors at the flight condition investigated.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-143843 , H-962
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Design of a manual control system for a STOL aircraft on microwave landing system curved approaches (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: GENERAL
    Type: AF Inst. of Technol. Proc. of the 10th Ann. Conf. on Manual Control; p 641-666
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Handling qualities of large flexible control-configured aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effects on handling qualities of low frequency symmetric elastic mode interaction with the rigid body dynamics of a large flexible aircraft was analyzed by use of a mathematical pilot modeling computer simulation. An extension of the optimal control model for a human pilot was made so that the mode interaction effects on the pilot's control task could be assessed. Pilot ratings were determined for a longitudinal tracking task with parametric variations in the undamped natural frequencies of the two lowest frequency symmetric elastic modes made to induce varying amounts of mode interaction. Relating numerical performance index values associated with the frequency variations used in several dynamic cases, to a numerical Cooper-Harper pilot rating has proved successful in discriminating when the mathematical pilot can or cannot separate rigid from elastic response in the tracking task.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-163206
    Format: application/pdf
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  • 10
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    Effects of dynamic aeroelasticity on handling qualities and pilot rating (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Pilot performance parameters, such as pilot ratings, tracking errors, and pilot comments, were recorded and analyzed for a longitudinal pitch tracking task on a large, flexible aircraft. The tracking task was programmed on a fixed-base simulator with a CRT attitude director display of pitch angle command, pitch angle, and pitch angle error. Parametric variations in the undamped natural frequencies of the two lowest frequency symmetric elastic modes were made to induce varying degrees of rigid body and elastic mode interaction. The results indicate that such mode interaction can drastically affect the handling qualities and pilot ratings of the task.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 78-1365 , Atmospheric Flight Mechanics Conference; Aug 07, 1978 - Aug 09, 1978; Palo Alto, CA
    Format: text
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