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  • 1
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    Handling qualities of light aircraft with advanced control systems and displays (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Flight tests to determine handling qualities of general aviation aircraft during ILS approaches in turbulent air
    Keywords: AIRCRAFT
    Type: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 189-206
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Experience with flight test trajectory guidance (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 3, p. 325, Accession no. A82-14379
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: (ISSN 0731-5090)
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Pilot human factors in stall/spin accidents of supersonic fighter aircraft (1983)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A study has been made of pilot human factors related to stall/spin accidents of supersonic fighter aircraft. The military specifications for flight at high angles of attack are examined. Several pilot human factors problems related to stall/spin are discussed. These problems include: (1) unsatisfactory nonvisual warning cues; (2) the inability of the pilot to quickly determine if the aircraft is spinning out of control, or to recognize the type of spin; (3) the inability of the pilot to decide on and implement the correct spin recovery technique; (4) the inability of the pilot to move, caused by high angular rotation; and (5) the tendency of pilots to wait too long in deciding to abandon the irrecoverable aircraft. Psycho-physiological phenomena influencin pilot's behavior in stall/spin situations include: (1) channelization of sensor inputs, (2) limitations in precisely controlling several muscular inputs, (3) inaccurate judgment of elapsed time, and (4) disorientation of vestibulo-ocular inputs. Results are given of pilot responses to all these problems in the F14A, F16/AB, and F/A-18A aircraft. The use of departure spin resistance and automatic spin prevention systems incorporated on recent supersonic fighters are discussed. These systems should help to improve the stall/spin accident record with some compromise in maneuverability.
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: AGARD Flight Mech. and System Design Lessons from Operational Experience; 10 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Modernizing engine displays (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The introduction of electronic fuel control to modern turbine engines has a number of advantages, which are related to an increase in engine performance and to a reduction or elimination of the problems associated with high angle of attack engine operation from the surface to 50,000 feet. If the appropriate engine display devices are available to the pilot, the fuel control system can provide a great amount of information. Some of the wealth of information available from modern fuel controls are discussed in this paper. The considered electronic engine control systems in their most recent forms are known as the Full Authority Digital Engine Control (FADEC) and the Digital Electronic Engine Control (DEEC). Attention is given to some details regarding the control systems, typical engine problems, the solution of problems with the aid of displays, engine displays in normal operation, an example display format, a multipage format, flight strategies, and hardware considerations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Advanced Aircrew Display Symposium; May 15, 16, 1984; Patuxent River, MD
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Flight evaluation of advanced control systems and displays on a general aviation airplane (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight-test program was conducted to determine the effect of advanced flight control systems and displays on the handling qualities of a light twin-engined airplane. A flight-director display and an attitude-command control system, used separately and in combination, transformed a vehicle with poor handling qualities during ILS approaches in turbulent air into a vehicle with good handling qualities. The attitude-command control system also improved the ride qualities of the airplane. A rate-command control system made only small improvements to the airplane's ILS handling qualities in turbulence. Both the rate- and the attitude-command control systems reduced stall warning in the test airplane, increasing the likelihood of inadvertent stalls. The final approach to the point of flare was improved by both the rate- and the attitude-command control systems. However, the small control wheel deflections necessary to flare were unnatural and tended to cause overcontrolling during flare. Airplane handling qualities are summarized for each control-system and display configuration.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7703 , H-783
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Flight evaluation of angle of attack as a control parameter in general-aviation aircraft (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Investigation of angle of attack information display for pilots to increase efficiency of general aviation aircraft operation
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6210 , H-603
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flight test experience with high-alpha control system techniques on the F-14 airplane (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Improved handling qualities of fighter aircraft at high angles of attack can be provided by various stability and control augmentation techniques. NASA and the U.S. Navy are conducting a joint flight demonstration of these techniques on an F-14 airplane. This paper reports on the flight test experience with a newly designed lateral-directional control system which suppresses such high angle of attack handling qualities problems as roll reversal, wing rock, and directional divergence while simultaneously improving departure/spin resistance. The technique of integrating a piloted simulation into the flight program was used extensively in this program. This technique had not been applied previously to high angle of attack testing and required the development of a valid model to simulate the test airplane at extremely high angles of attack.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 81-2505 , Flight Testing Conference; Nov 11, 1981 - Nov 13, 1981; Las Vegas, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Pilot Human Factors in Stall/Spin Accidents of Supersonic Fighter Aircraft (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A study has been made of pilot human factors related to stall/spin accidents of supersonic fighter aircraft. The military specifications for flight at high angles of attack are examined. Several pilot human factors problems related to stall/spin are discussed. These problems include (1) unsatisfactory nonvisual warning cues; (2) the inability of the pilot to quickly determine if the aircraft is spinning out of control, or to recognize the type of spin; (3) the inability of the pilot to decide on and implement the correct spin recovery technique; (4) the inability of the pilot to move, caused by high angular rotation; and (5) the tendency of pilots to wait too long in deciding to abandon the irrecoverable aircraft. Psycho-physiological phenomena influencing pilot's behavior in stall/spin situations include (1) channelization of sensory inputs, (2) limitations in precisely controlling several muscular inputs, (3) inaccurate judgment of elapsed time, and (4) disorientation of vestibulo-ocular inputs. Results are given of pilot responses to all these problems in the F14A, F16/AB, and F/A-18A aircraft. The use of departure spin resistance and automatic spin prevention systems incorporated on recent supersonic fighters are discussed. These systems should help to improve the stall/spin accident record with some compromise in maneuverability.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-84348 , A-9297 , NAS 1.15:84348 , AGARD Conf. Flight Mech. Sys. Design Lessons from Operational Exper.; May 10, 1983 - May 13, 1983; Athens
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Limited evaluation of an F-14A airplane utilizing an aileron-rudder interconnect control system in the landing configuration (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A flight test was conducted for preliminary evaluation of an aileron-rudder interconnect (ARI) control system for the F-14A airplane in the landing configuration. Two ARI configurations were tested in addition to the standard F-14 flight control system. Results of the flight test showed marked improvement in handling qualities when the ARI systems were used. Sideslip due to adverse yaw was considerably reduced, and airplane turn rate was more responsive to pilot lateral control inputs. Pilot comments substantiated the flight data and indicated that the ARI systems were superior to the standard control system in terms of pilot capability to make lateral offset corrections and heading changes on final approach.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-81972 , L-14756
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Flight test evaluation of an RAF high altitude partial pressure protective assembly (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A partial pressure suit was evaluated during tests in an F-104 and F-15 as a protective garment for emergency descents. The garment is an pressure jerkin and modified anti-g suit combined with an oronasal mask. The garment can be donned and doffed at the aircraft to minimize thermal buildup. The oronasal mask was favored by the pilots due to its immobility on the face during high g-loading. The garment was chosen to provide optimum dexterity for the pilot, which is not available in a full pressure suit, while protecting the pilot at altitudes up to 18,288 meters, during a cabin decompression, and subsequent aircraft descent. During cabin decompressions in the F-104 and F-15, cabin pressure altitude was measured at various aircraft angles of attack, Mach numbers, and altitudes to determine the effect of the aerodynamic slipstream on the cabin altitude.
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: NASA-TM-72864
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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