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  • 11
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    The Effect of Lateral-Directional Control Coupling on Pilot Control of an Airplane as Determined in Flight and in a Fixed-Base Flight Simulator (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A flight and fixed-base simulator study was made of the effects of aileron-induced yaw on pilot opinion of aircraft lateral-directional controllability characteristics. A wide range of adverse and favorable aileron-induced yaw was investigated in flight at several levels of Dutch-roll damping. The flight results indicated that the optimum values of aileron- induced yaw differed only slightly from zero for Dutch-roll damping from satisfactory to marginally controllable levels. It was also shown that each range of values of aileron-induced yawing moment considered satisfactory, acceptable, or controllable increased with an increase in the Dutch- roll damping. The increase was most marked for marginally controllable configurations exhibiting favorable aileron-induced yaw. Comparison of fixed-base flight simulator results with flight results showed agreement, indicating that absence of kinesthetic motion cues did not markedly affect the pilots' evaluation of the type of control problem considered in this study. The results of the flight study were recast in terms of several parameters which were considered to have an important effect on pilot opinion of lateral-directional handling qualities, including the effects of control coupling. Results of brief tests with a three-axis side-arm controller indicated that for control coupling problems associated with highly favorable yaw and cross-control techniques, use of the three-axis controller resulted in a deterioration of control relative to results obtained with the conventional center stick and rudder pedals.
    Keywords: Aircraft Stability and Control
    Type: NASA-TN-D-1141
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    A Pilot Opinion Study of Lateral Control Requirements for Fighter-Type Aircraft (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: As part of a continuing NASA program of research on airplane handling qualities, a pilot opinion investigation has been made on the lateral control requirements of fighter aircraft flying in their combat speed range. The investigation was carried out using a stationary flight simulator and a moving flight simulator, and the flight simulator results were supplemented by research tests in actual flight. The flight simulator study was based on the presumption that the pilot rates the roll control of an airplane primarily on a single-degree-of-freedom basis; that is, control of angle of roll about the aircraft body axis being of first importance. From the assumption of a single degree of freedom system it follows that there are two fundamental parameters which govern the airplane roll response, namely the roll damping expressed as a time constant and roll control power in terms of roll acceleration. The simulator study resulted in a criterion in terms of these two parameters which defines satisfactory, unsatisfactory, and unacceptable roll performance from a pilot opinion standpoint. The moving simulator results were substantiated by the in-flight investigation. The derived criterion was compared with the roll performance criterion based upon wing tip helix angle and also with other roll performance concepts which currently influence the roll performance design of military fighter aircraft flying in their combat speed range.
    Keywords: Man/System Technology and Life Support
    Type: NASA-MEMO-1-29-59A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Operational Technique for Transition of Several Types of V/Stol Aircraft (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Flight test experience has been obtained with five test bed aircraft which employed widely differing principles of V/STOL operation. speeds these aircraft were supported by wing lift and in the hovering condition they were supported by engine-produced thrust. used to transfer the lift from the wing to the engine are examined. primary items considered in the transition region are longitudinal trim changes, stability , stalled flow during descending transitions, and the flexibility of the transition procedure of each type of aircraft.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TN-D-774 , L-1418
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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