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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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    Control and display combinations for blind vertical landings (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 15; 3, Ma; 751-760
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    NASA TECHNICAL REPORTS
  • 3
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    Simulation evaluation of an advanced control concept for a V/STOL aircraft (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 12; 334-341
    Format: text
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  • 4
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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
  • 5
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    Evaluation of a command monitoring concept for a V/STOL Research Aircraft (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 12; 46-53
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Flight evaluations of several hover control and display combinations for precise blind vertical landings (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Several control and display concepts were evaluated on a variable-stability helicopter prior to future evaluations on a modified Harrier. The control and display concepts had been developed to enable precise hover maneuvers, station keeping, and vertical landings in simulated zero-visibility conditions and had been evaluated extensively in previous piloted simulations. Flight evaluations early in the program revealed several inadequacies in the display drive laws that were later corrected using an alternative design approach that integrated the control and display characteristics with the desired guidance law. While hooded, three pilots performed landing-pad captures followed by vertical landings with attitude-rate, attitude, and translation-velocity-command control systems. The latter control system incorporated a modified version of state-rate-feedback implicit-model following. Precise landing within 2 ft of the desired touchdown point were achieved.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 90-3479
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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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
  • 8
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    Simulation evaluation of the advanced control concept for the NASA V/STOL research aircraft (VSRA) (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Two candidate control systems for the Vertical/Short Takeoff and Landing (V/STOL) Research Aircraft (VSRA) are described, both of which are limited-authority, digital, fly-by wire variants of the original YAV-8B Harrier control system. The performance of these systems was compared with that of an ideal, full-authority system in simulated, adverse-weather V/STOL shipboard operations using the Ames Research Center's Vertical Motion Simulator. Both systems showed some performance degradation relative to the ideal, but both were adequate to meet VSRA program objectives. The favored system, selected because of safety considerations, was further simulated using a precision visual hovering task that verified its acceptability.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 87-2535
    Format: text
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  • 9
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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
  • 10
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    Simulation evaluation of the control system command monitoring concept for the NASA V/STOL research aircraft (VSRA) (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A control-system monitoring concept is described that has the potential of rapidly detecting computer command failures (hardware or software) in fly-by-wire control systems. The concept has been successfully tested on the NASA Vertical/Short Takeoff and Landing Research Aircraft (VSRA) in the Ames Research Center's Vertical Motion Simulator. The test was particularly stringent, since the VSRA is required to operate in a hazardous environment. The fidelity of the aircraft model used in the simulation was verified by flying both the simulated and actual aircraft in a precision hover task using specially designed targets.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 87-2255
    Format: text
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