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  • 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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    Study of an aircraft decoupled longitudinal control system for approach and landing (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A series of ground-based and in-flight simulation studies of the application of steady-state decoupled longitudinal controls to a short take-off and landing (STOL) transport have been made. The externally blown flap STOL was selected for study because it was considered to be a worst-case situation from the control viewpoint. The decoupled longitudinal control system used constant prefilter and feedback gains to provide independent control of flight-path angle, pitch angle, and forward velocity during landing approach. The decoupled controls were compared to a more conventional stability augmentation system. The pilots were enthusiastic about the decoupled controls; the pilot workload was reduced and the landing performance significantly improved. The benefit of the decoupled controls was more dramatic during in-flight simulation using a variable stability airplane than was the case with either fixed- or moving-base, ground-based simulators.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Atmospheric Flight Mechanics Conference; Jun 07, 1976 - Jun 09, 1976; Arlington, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Decoupled longitudinal controls for shear penetration in the terminal area environment (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The use of decoupled longitudinal controls is simulated for the approach and landing of a twin engine jet transport in the presence of wind shear. Decoupled or independent control of pitch angle, flight-path angle and forward velocity using constant prefilter and feedback gains was compared to conventional control of a B-737 aircraft simulator. It is found that the mean flight-path angle, the mean glideslope error and the mean deviation in indicated airspeed generally improved when decoupled controls were used in the approach. An improvement in touchdown parameters was also observed, especially in strong shear, when 44% of conventionally-controlled flights impacted short of the runway. Simulator pilots reported improved approach performance and a reduced workload when decoupled controls were used.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 79-1678 , Atmospheric Flight Mechanics Conference for Future Space Systems; Aug 06, 1979 - Aug 08, 1979; Boulder, CO
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Moving-base visual simulation study of decoupled controls during approach and landing of a STOL transport aircraft (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The simulation employed all six rigid-body degrees of freedom and incorporated aerodynamic characteristics based on wind-tunnel data. The flight instrumentation included a localizer and a flight director which was used to capture and to maintain a two-segment glide slope. A closed-circuit television display of a STOLport provided visual cues during simulations of the approach and landing. The decoupled longitudinal controls used constant prefilter and feedback gains to provide steady-state decoupling of flight-path angle, pitch angle, and forward velocity. The pilots were enthusiastic about the decoupled longitudinal controls and believed that the simulator motion was an aid in evaluating the decoupled controls, although a minimum turbulence level with root-mean-square gust intensity of 0.3 m/sec (1 ft/sec) was required to mask undesirable characteristics of the moving-base simulator.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TN-D-7790 , L-9721
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Fixed-base simulation study of decoupled longitudinal controls during approach and landing of a medium jet transport in the presence of wind shear (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of decoupled longitudinal controls during the approach and landing of a typical twin-engine jet transport in the presence of wind shear was studied. The simulation included use of a localizer and flight director to capture and maintain a 3 deg glide slope. The pilot then completed the landing by using visual cues provided below an altitude of 200 m by closed-circuit television and a terrain model. The decoupled controls used constant prefilter and feedback gains to provide steady state decoupling of flight path angle, pitch angle, and forward velocity. The use of the decoupled control system improved pilot performance during the approach and at touchdown in the presence of wind shears. The pilots preferred the decoupled controls and rated the task 1 to 3 increments better on a pilot rating scale, depending on wind conditions, than was the case when conventional controls were used.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-1519 , L-12842
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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