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  • 1
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    Flight evaluation of pursuit displays for precision approach of powered-lift aircraft (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Flight experiments with NASA Ames Research Center's quiet short-haul research aircraft evaluated the influence of pursuit displays on the ability of pilots to execute precision-instrument flight operations in the terminal area, particularly approaches to and landings on a short runway. The aircraft is a powered-lift, short-takeoff and landing configuration equipped with a modern digital fly-by-wire flight control system, a head-up display, and a color head-down display that make it possible to investigate control and display concepts for full-envelope, powered-lift operations. Flight-path-oriented displays that provide status and command information in a format with minimal clutter were investigated. The pilots could fly the aircraft with the precision associated with flight-director guidance and with a high degree of situation awareness. The primary benefits of this display concept were realized when the pilot was required to execute a complex transition and approach under instrument conditions and in the presence of a wide range of wind and turbulence conditions.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 12; 521-529
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Wind-shear endurance capability for powered-lift aircraft (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The present treatment of safety margin considerations for powered-lift (upper wing surface blowing) STOL aircraft emphasizes wind shear endurance, in order to establish safety margin criteria for such aircraft that are equivalent to those of conventional transport aircraft. The simulation results obtained show that a 6.6 deg climb gradient at V(app) for STOL aircraft is required for equivalent shear endurance in approaching a long STOL airport runway, if the STOL aircraft is equipped with an elaborate control/display system and is permitted a change in configuration.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 93-3670 , In: AIAA Atmospheric Flight Mechanics Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers (A93-48301 20-08); p. 461-469.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A method of wind shear detection for powered-lift STOL aircraft (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new wind shear warning system for powered-lift STOL aircraft was evaluated by using a flight simulator. Wind shear warning systems for CTOL aircraft have been designed to detect horizontal shear only. Because the approach air speed of STOL aircraft is lower than that for CTOL aircraft, STOL aircraft are more vulnerable to vertical wind due to (1) a gradient of horizontal shear that is smaller for STOL than for CTOL aircraft because of slower airspeed; (2) STOL aircraft spend longer time in a downdraft; and (3) vertical wind causes a more radical change in the STOL aircraft's flight path because of its lower airspeed. In order to detect the vertical wind, the wind shear warning system proposed calculates the difference between potential flight path measured on-board during shear traversal and trimmed flight path estimated from aircraft status. The most characteristic feature of this new system is that it utilizes only inertial information and pitot-static airspeed data; this yields a convenient means of on-board implementation. Simulation test results confirm that the new system can detect the vertical shear.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: AIAA PAPER 93-3667 , In: AIAA Atmospheric Flight Mechanics Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers (A93-48301 20-08); p. 442-447.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Synthesis from Design Requirements of a Hybrid System for Transport Aircraft Longitudinal Control (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Volume I of this report presents a new method for synthesizing hybrid systems directly from desi gn requirements, and applies the method to design of a hybrid system for longitudinal control of transport aircraft. The resulting system satisfies general requirement for safety and effectiveness specified a priori, enabling formal validation to be achieved. Volume II contains seven appendices intended to make the report accessible to readers with backgrounds in human factors, flight dynamics and control, and formal logic. Major design goals are (1) system design integrity based on proof of correctness at the design level, (2) significant simplification and cost reduction in system development and certification, and (3) improved operational efficiency, with significant alleviation of human-factors problems encountered by pilots in current transport aircraft. This report provides for the first time a firm technical basis for criteria governing design and certification of avionic systems for transport aircraft. It should be of primary interest to designers of next-generation avionic systems.
    Keywords: Air Transportation and Safety
    Type: NASA/TP-2007-213475/VOL2 , A-070008
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Synthesis from Design Requirements of a Hybrid System for Transport Aircraft Longitudinal Control (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Volume I of this report presents a new method for synthesizing hybrid systems directly from design requirements, and applies the method to design of a hybrid system for longitudinal control of transport aircraft. The resulting system satisfies general requirement for safety and effectiveness specified a priori, enabling formal validation to be achieved. Volume II contains seven appendices intended to make the report accessible to readers with backgrounds in human factors, fli ght dynamics and control. and formal logic. Major design goals are (1) system desi g n integrity based on proof of correctness at the design level, (2), significant simplification and cost reduction in system development and certification, and (3) improved operational efficiency, with significant alleviation of human-factors problems encountered by pilots in current transport aircraft. This report provides for the first time a firm technical basis for criteria governing design and certification of avionic systems for transport aircraft. It should be of primary interest to designers of next-generation avionic systems.
    Keywords: Air Transportation and Safety
    Type: NASA/TP-2007-213474/VOL1 , A-070007
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Flight evaluation of an integrated control and display system for high-precision manual landing flare of powered-lift STOL aircraft (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An account is given of the features and performance of a manual landing flare and touchdown system capable of great precision, as demonstrated by its installation in the NASA Quiet Short-haul Research Aircraft (QSRA). The integrated cockpit display and closed-loop control employed constitutes a trajectory-augmentation system that extends QSRA flight control from augmentation of altitude, flight path angle, and airspeed, to the augmentation of the trajectory itself. The + or - 18 ft touchdown dispersion achieved is approximately equal to that obtained during aircraft carrier trials of the same aircraft.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 872316 , 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
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