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  • 1
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    Improvements in hover display dynamics for a combat helicopter (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: This paper describes a piloted simulation conducted on the NASA Ames Vertical Motion Simulator. The objective of the experiment was to investigate the handling qualities benefits attainable using new display law design methods for hover displays. The new display laws provide improved methods to specify the behavior of the display symbol that predicts the vehicle's ground velocity in the horizontal plane; it is the primary symbol that the pilot uses to control aircraft horizontal position. The display law design was applied to the Apache helmet-mounted display format, using the Apache vehicle dynamics to tailor the dynamics of the velocity predictor symbol. The representations of the Apache vehicle used in the display design process and in the simulation were derived from flight data. During the simulation, the new symbol dynamics were seen to improve the pilots' ability to maneuver about hover in poor visual cuing environments. The improvements were manifested in pilot handling qualities ratings and in measured task performance. The paper details the display design techniques, the experiment design and conduct, and the results.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: American Helicopter Society, Journal (ISSN 0002-8711); 1; p. 17-28.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Improvements in hover display dynamics for a combat helicopter (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: This paper describes a piloted simulation conducted on the NASA Ames Vertical Motion Simulator. The objective of the experiment was to investigate the handling qualities benefits attainable using new display law design methods for hover displays. The new display laws provide improved methods to specify the behavior of the display symbol that predicts the vehicle's ground velocity in the horizontal plane; it is the primary symbol that the pilot uses to control aircraft horizontal position. The display law design was applied to the Apache helmet-mounted display format, using the Apache vehicle dynamics to tailor the dynamics of the velocity predictor symbol. The representations of the Apache vehicle used in the display design process and in the simulation were derived from flight data. During the simulation, the new symbol dynamics were seen to improve the pilots' ability to maneuver about hover in poor visual cuing environments. The improvements were manifested in pilot handling qualities ratings and in measured task performance. The paper details the display design techniques, the experiment design and conduct, and the results.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Piloting Vertical Flight Aircraft: A Conference on Flying Qualities and Human Factors; p 235-250
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    An Investigation of the Ability to Recover from Transients Following Failures for Single-Pilot Rotorcraft (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A moving-base simulation was conducted to investigate a pilot's ability to recover from transients following single-axis hard-over failures of the flight-control system. The investigation was performed in conjunction with a host simulation that examined the influence of control modes on a single pilot's ability to perform various mission elements under high-workload conditions. The NASA Ames large-amplitude-motion Vertical Motion Simulator (VMS) was utilized, and the experimental variables were the failure axis, the severity of the failure, and the airspeed at which the failure occurred. Other factors, such as pilot workload and terrain and obstacle proximity at the time of failure, were kept as constant as possible within the framework of the host simulation task scenarios. No explicit failure warnings were presented to the pilot. Data from the experiment are shown, and pilot ratings are compared with the proposed handling-qualities requirements for military rotorcraft. Results indicate that the current proposed failure transient requirements may need revision.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-100078 , A-88113 , USAAVSCOM-TM-88-A-001 , NAS 1.15:100078 , AD-A198150 , ARC-E-DAA-TN10470
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Integrated control and display research for transition and vertical flight on the NASA V/STOL Research Aircraft (VSRA) (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results of a substantial body of ground-based simulation experiments indicate that a high degree of precision of operation for recovery aboard small ships in heavy seas and low visibility with acceptable levels of effort by the pilot can be achieved by integrating the aircraft flight and propulsion controls. The availability of digital fly-by-wire controls makes it feasible to implement an integrated control design to achieve and demonstrate in flight the operational benefits promised by the simulation experience. It remains to validate these systems concepts in flight to establish their value for advanced short takeoff vertical landing (STOVL) aircraft designs. This paper summarizes analytical studies and simulation experiments which provide a basis for the flight research program that will develop and validate critical technologies for advanced STOVL aircraft through the development and evaluation of advanced, integrated control and display concepts, and lays out the plan for the flight program that will be conducted on NASA's V/STOL Research Aircraft (VSRA).
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-100029 , A-87350 , NAS 1.15:100029
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Integrated control and display research for transition and vertical flight on the NASA V/STOL Research Aircraft (VSRA) (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results of a substantial body of ground-based simulation experiments indicate that a high degree of precision of operation for recovery aboard small ships in heavy seas and low visibility with acceptable levels of effort by the pilot can be achieved by integrating the aircraft flight and propulsion controls. The availability of digital fly-by-wire controls makes it feasible to implement an integrated control design to achieve and demonstrate in flight the operational benefits promised by the simulation experience. It remains to validate these systems concepts in flight to establish their value for advanced short takeoff vertical landing (STOVL) aircraft designs. This paper summarizes analytical studies and simulation experiments which provide a basis for the flight research program that will develop and validate critical technologies for advanced STOVL aircraft through the development and evaluation of advanced, integrated control and display concepts, and lays out the plan for the flight program that will be conducted on NASA's V/STOL Research Aircraft (VSRA).
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: SAE PAPER 872329 , International Powered Lift Conference and Exposition; Dec 07, 1987 - Dec 10, 1987; Santa Clara, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Effects of stick dynamics on helicopter flying qualities (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An experiment that investigated the influence of typical helicopter force-feel system dynamics on roll-axis handling qualities was conducted in concurrent ground and inflight simulations. Variations in lateral control natural frequency and damping ratio, effected by changes in inertia and damping, were evaluated in a disturbance-rejection task. Pilot ratings indicated a preference for low-inertia feel systems, although measured performance was relatively constant over the range of stick characteristics. Force-sensing was compared with position sensing as the input to the control system. Force-sensing improved performance but did not improve pilot ratings. Overall, the results indicated that control-stick dynamics, at least within a reasonable range, did not have a significant effect on pilot-vehicle performance. However, the physical effort required to maintain a desired pilot/manipulator bandwidth became objectionable as the stick inertia increased beyond 5-7 lbm, which was reflected in the pilot ratings and comments.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 90-3477 , AIAA Guidance, Navigation and Control Conference; Aug 20, 1990 - Aug 22, 1990; Portland, OR; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    A pilot rating scale for evaluating failure transients in electronic flight control systems (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A pilot rating scale was developed to describe the effects of transients in helicopter flight-control systems on safety-of-flight and on pilot recovery action. The scale was applied to the evaluation of hardovers that could potentially occur in the digital flight-control system being designed for a variable-stability UH-60A research helicopter. Tests were conducted in a large moving-base simulator and in flight. The results of the investigation were combined with existing airworthiness criteria to determine quantitative reliability design goals for the control system.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 90-2827 , AIAA Atmospheric Flight Mechanics Conference; Aug 20, 1990 - Aug 22, 1990; Portland, OR; United States
    Format: text
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    NASA TECHNICAL REPORTS
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