Active attitude control of a spinning Skylab is analyzed to determine a simple control law that will provide a satisfactory response, considering the dynamics of attached flexible appendages. A simplified model of the complex Skylab vehicle is selected to make it analytically tractable. The vehicle is modeled as a single rigid-core body with two attached flexible massless booms having masses on their tips. The equations of motion describing the attitude dynamics of the model are presented as a linear matrix-differential equation. The states of the vehicle are small perturbations about its steady-state spin. An analysis is performed to determine the domain of stability. Next, attitude dynamics are analyzed; both frequency domain (parameter plane) and time domain (an optimal linear quadratic loss program) techniques are compared. An analysis of the nonlinear effect of control torque saturation of Skylab's control moment gyroscopes is discussed. The results of the analysis compare favorably with a large-scale digital simulation of the Skylab.


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    Titel :

    Attitude control of a spinning Skylab.


    Beteiligte:
    Seltzer, S. M. (Autor:in) / Schweitzer, G. (Autor:in) / Asner, B., Jr. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics, Guidance and Control Conference ; 1972 ; Stanford, CA


    Erscheinungsdatum :

    01.08.1972


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Attitude Control of a Spinning Skylab

    S. M. SELTZER / GERHARD SCHWEITZER AND BERNARD ASNER | AIAA | 1973


    Attitude control of a spinning Skylab

    SELTZER, S. / SCHWEITZER, G. / ASNER, JR., B. | AIAA | 1972


    Skylab attitude control system

    Coon, T. R. / Irby, J. E. | NTRS | 1976


    Skylab attitude control system

    Coon, T.R. / Irby, J.E. | Tema Archiv | 1976


    Skylab thruster attitude control system

    Wilmer, G. E., Jr. | NTRS | 1974