An analytical method was developed for studying the combined effects of rotational coupling and nonlinear aerodynamics on aircraft response for specified control inputs. The method involves the simultaneous solution of two nonlinear equations which are functions of angle attack, roll rate, and control inputs. The method was applied to a number of maneuvers for a fighter-type aircraft. Time history responses verified the usefulness of the analysis for predicting a variety of response characteristics caused by interacting nonlinear aerodynamic and inertial effects, including spin conditions.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Pseudosteady-state analysis of nonlinear aircraft maneuvers


    Contributors:
    Young, J. W. (author) / Schy, A. A. (author) / Johnson, K. G. (author)

    Publication date :

    1980-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Pseudosteady state analysis of nonlinear aircraft maneuvers

    Young, J. W. / Schy, A. A. / Johnson, K. G. | NTRS | 1980


    Pseudosteady state analysis of nonlinear aircraft maneuvers

    YOUNG, J. / SCHY, A. / JOHNSON, K. | AIAA | 1980


    Pseudosteady-State Analysis of Nonlinear Aircraft Maneuvers

    J. W. Young / A. A. Schy / K. G. Johnson | NTIS | 1980


    Nonlinear decoupling control of aircraft maneuvers

    Zhou, Z. | British Library Online Contents | 1996


    Nonlinear Decoupling Control and Aircraft Agility Maneuvers

    Zhou, Z. Q. / Gao, H. / International Council of Aeronautical Sciences | British Library Conference Proceedings | 1994