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  • AIRCRAFT STABILITY AND CONTROL  (3)
  • MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT  (1)
  • NAVIGATION
  • 1980-1984  (4)
  • 1
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    Simulator evaluation of the effects of reduced spoiler and thrust authority on a decoupled longitudinal control system during landings in wind shear (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of reduced control authority, both in symmetric spoiler travel and thrust level, on the effectiveness of a decoupled longitudinal control system was examined during the approach and landing of the NASA terminal configured vehicle (TCV) aft flight deck simulator in the presence of wind shear. The evaluation was conducted in a fixed-base simulator that represented the TCV aft cockpit. There were no statistically significant effects of reduced spoiler and thrust authority on pilot performance during approach and landing. Increased wind severity degraded approach and landing performance by an amount that was often significant. However, every attempted landing was completed safely regardless of the wind severity. There were statistically significant differences in performance between subjects, but the differences were generally restricted to the control wheel and control-column activity during the approach.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-83188 , L-14652
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    An analytical technique for the analysis of airplane spin entry and recovery (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The dynamic equations of motion for a spinning airplane are simplified to facilitate the analysis of spin entry and recovery maneuvers. Solutions of a nonlinear, first order equation for spin rate enable calculation of spin entry and recovery times and control required for recovery. The analysis is applied to a light airplane for which both aerodynamic data, rotory balance wind tunnel tests, and spin flight test data have been obtained. A comparison of predicted and actual transient spin responses is made which supports the validity of the analytical approach taken but which also illustrates the difficulty in obtaining accurate aerodynamic data for spinning airplanes. Certain normalized parameters of the reduced state spin equation suggest criteria for assessing the transient spin characteristics of light airplanes.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 82-0243 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A decoupled control system for improved flight performance in wind shear (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A fixed-base simulation study has been made to compare the approach and landing performance of a decoupled longitudinal control system and the velocity-vector control-wheel steering (VCWS) system that currently exists on the NASA Terminal Configured Vehicle (TCV). The decoupled control system employed constant prefilter and feedback gains to provide steady-state decoupling of flight-path angle, pitch angle, and forward velocity using symmetric spoilers, throttle, and elevator as active control elements. In severe wind shear, of the Kennedy-type, the decoupled control system improved both approach performance and touchdown performance even when the spoiler deflection was limited to 16 deg. On a 10-point rating scale, three research pilots rated the approach and landing task with decoupled controls as much as 3 to 4 increments better than the use of the VCWS system in severe winds
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: In: Joint Automatic Control Conference; Jun 17, 1981 - Jun 19, 1981; Charlottesville, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Pilot opinions of sampling effects in lateral-directional control (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Flight experiments with a microprocessor control system were conducted to determine the effects of variations in sampling parameters on several pilots' opinions of lateral-directional flying qualities. Princeton's variable-response research aircraft (VRA), which is equipped with a microprocessor based digital flight control system (Micro-DFCS), was the test vehicle. Two U.S. Navy pilots evaluated the effects of sampling rate, quantization, and pure time delay during tracking, approach, and landing. Aircraft carrier approach tasks were conducted using a Navy approach mirror. Acquisition and tracking of fixed objects on the ground provided additional information related to the Navy misson. The longitudinal controls were implemented with analog electronics, while the lateral-directional pilot inputs (stick and rudder) were fed to the Micro-DFCS, which commanded the ailerons and rudder. The conceptual relationship between the evaluation pilot's lateral-directional inputs, the flight computer, and the aircraft are illustrated.
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: NASA. Ames Research Center 16th Ann. Conf. on Manual Control; p 265-270
    Format: text
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    NASA TECHNICAL REPORTS
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