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  • 1
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    Effects of simulator motion and visual characteristics on rotorcraft handling qualities evaluations (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The pilot's perceptions of aircraft handling qualities are influenced by a combination of the aircraft dynamics, the task, and the environment under which the evaluation is performed. When the evaluation is performed in a groundbased simulator, the characteristics of the simulation facility also come into play. Two studies were conducted on NASA Ames Research Center's Vertical Motion Simulator to determine the effects of simulator characteristics on perceived handling qualities. Most evaluations were conducted with a baseline set of rotorcraft dynamics, using a simple transfer-function model of an uncoupled helicopter, under different conditions of visual time delays and motion command washout filters. Differences in pilot opinion were found as the visual and motion parameters were changed, reflecting a change in the pilots' perceptions of handling qualities, rather than changes in the aircraft model itself. The results indicate a need for tailoring the motion washout dynamics to suit the task. Visual-delay data are inconclusive but suggest that it may be better to allow some time delay in the visual path to minimize the mismatch between visual and motion, rather than eliminate the visual delay entirely through lead compensation.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA. Ames Research Center, Piloting Vertical Flight Aircraft: A Conference on Flying Qualities and Human Factors; p 341-359
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Bandwidth Criteria for Category I and II PIOs (2001)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This presentation gives information on: pitch criteria based on airplane Bandwidth; apply research, experimental, operational data; compare Smith-Geddes, Gibson, Neal-Smith criteria; bandwidth criteria for Category II PIO; control/response sensitivity and PIO; extension to roll a axis; and some recommendations.
    Keywords: Aircraft Stability and Control
    Type: Pilot-Induced Oscillation Research: The Status at the End of the Century; Volume 1; 17-28; NASA/CP-2001-210389/VOL1
    Format: application/pdf
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  • 3
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    Simulation evaluation of the effects of time delay and motion on rotorcraft handling qualities (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A study aimed at determining the effects of simulator characteristics on perceived handling qualities is discussed. Evaluations were conducted with a baseline set of rotorcraft dynamics, using a simple transfer-function model of an uncoupled helicopter, under different conditions of visual and overall time delays. As the visual and motion parameters were changed, differences in pilot opinion were found reflecting a change in the pilots' perceptions of handling qualities, rather than changes in the aircraft model itself. It is concluded that it is necessary to tailor the motion washout dynamics to suit the task, with reduced washouts for precision maneuvering as compared to aggressive maneuvering. Visual-delay data suggest that it may be better to allow some time delay in the visual path to minimize the mismatch between visual and motion, rather than eliminate the visual delay entirely through lead compensation.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 91-2892
    Format: text
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  • 4
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    Effects of cockpit lateral stick characteristics on handling qualities and pilot dynamics (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of analysis of cockpit lateral control feel-system studies. Variations in feel-system natural frequency, damping, and command sensing reference (force and position) were investigated, in combination with variations in the aircraft response characteristics. The primary data for the report were obtained from a flight investigation conducted with a variable-stability airplane, with additional information taken from other flight experiments and ground-based simulations for both airplanes and helicopters . The study consisted of analysis of handling qualities ratings and extraction of open-loop, pilot-vehicle describing functions from sum-of-sines tracking data, including, for a limited subset of these data, the development of pilot models. The study confirms the findings of other investigators that the effects on pilot opinion of cockpit feel-system dynamics are not equivalent to a comparable level of added time delay, and until a more comprehensive set of criteria are developed, it is recommended that feel-system dynamics be considered a delay-inducing element in the aircraft response. The best correlation with time-delay requirements was found when the feel-system dynamics were included in the delay measurements, regardless of the command reference. This is a radical departure from past approaches.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-4443 , H-1769 , NAS 1.26:4443
    Format: application/pdf
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  • 5
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    Simulation investigation of the effects of helicopter hovering dynamics on pilot performance (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A fixed base simulation has been performed to investigate the handling qualities requirements for the mid-term pitch response of a helicopter at hover and in low-speed flight. Pilot rating results from this simulation were compared with those from previous experiments to develop handling qualities limits on the frequency and damping of the oscillatory mode in the hovering cubic. Pilot performance data obtained during the experiment were used to confirm the pilot rating results. These data show the pilot performance to closely match that predicted by the theory of piloted control. A means of predicting pilot ratings from the open-loop aircraft dynamics is presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 87-2533
    Format: text
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  • 6
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    A flight investigation of helicopter low-speed response requirements (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A flight experiment has been conducted using the Canadian National Aeronautical Establishment's variable-stability airborne simulator to define the dynamic response requirements for operations at hover and low speeds. Fourteen Attitude Command/Attitude Hold, Rate, and Rate Command/Attitude Hold configurations were evaluated by six pilots using both conventional controls and a four-axis integrated sidestick over a low-speed course consisting of precision hover, landing, sidestep, and dash/quickstop tasks. The results indicate that with conventional controls all three response-types were acceptable as long as their response bandwidth was sufficiently high, and higher bandwidths were required in roll than in pitch. With the four-axis sidestick, there was a preference for the Rate systems. The range of acceptable bandwidths was lower, and the spread in pilot ratings smaller, than were found in a similar ground-based simulation.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 87-2285
    Format: text
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  • 7
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    Development of Handling Qualities Criteria for Rotorcraft with Externally Slung Loads (2006)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Piloted simulations were performed on the NASA-Ames Vertical Motion Simulator (VMS) to explore handling qualities issues for large cargo helicopters, particularly focusing on external slung load operations. The purpose of this work was based upon the need to include handling qualities criteria for cargo helicopters in an upgrade to the U.S. Army's rotorcraft handling qualities specification, Aeronautical Design Standard-33 (ADS-33E-PRF). From the VMS results, handling qualities criteria were developed fro cargo helicopters carrying external slung loads in the degraded visual environment (DVE). If satisfied, these criteria provide assurance that the handling quality rating (HQR) will be 4 or better for operations in the DVE, and with a load mass ratio of 0.33 or less. For lighter loads, flying qualities were found to be less dependent on the load geometry and therefore the significance of the criteria is less. For heavier loads, meeting the criteria ensures the best possible handling qualities, albeit Level 2 for load mass ratios greater than 0.33.
    Keywords: Aircraft Stability and Control
    Type: NASA/CR-2006-213488 , U.S. Army RDECOM No. AFDD/TR-06-003 , A-060008
    Format: application/pdf
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  • 8
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    Flight investigation of helicopter low-speed response requirements (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 12; 623-630
    Format: text
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  • 9
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    Simulation investigation of the effects of helicopter hovering dynamics on pilot performance (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 13; 8-15
    Format: text
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