The design of a multivariable control system for gust alleviation is demonstrated. The use of computers for control design, summarized under the name computer aided design, is described. The gust control system for gust alleviation is integrated into an overall flight guidance control system. Two control designs, using optimal control laws, are achieved, one with complete and the second with incomplete state measurement. In the model description the elastic behavior of the wing is included, as well as the non-steady aerodynamic lift generation and the dynamic behavior of the actuators. The efficiency of gust alleviation is shown in a flight through turbulent air for a STOL-transport aircraft. The increase of wing lifetime and the corresponding decrease in structure weight by use of a gust alleviation system is calculated. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Control of an Elastic Aircraft Using Optimal Control Laws


    Contributors:
    W. Dressler (author)

    Publication date :

    1974


    Size :

    13 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Robust dynamic inversion control laws for aircraft control

    BALAS, GARY / GARRARD, WILLIAM / REINER, JAKOB | AIAA | 1992



    Aircraft elastic mode control

    SWAIM, R. L. | AIAA | 1971


    Mixed H2/H-infinity optimal control for an elastic aircraft

    Fan, Yigang / Cliff, Eugene M. / Lutze, Frederick H. et al. | AIAA | 1996