The attitude-tracking control of a rigid spacecraft using only two internal torques is addressed. First, a given reference trajectory is classified as feasible or unfeasible according to the preservation or violation of the momentum conservation law. The dynamics of the attitude-tracking error is then formulated on the attitude manifold SO(3) with the angular momentum of the actuators as inputs. Given the Lie group structure of SO(3), the transverse function approach is utilized to design an attitude-tracking law ensuring asymptotically ultimately bounded tracking error for any reference trajectory. For feasible reference trajectories satisfying certain persistence conditions, asymptotic tracking is achieved by constructing an asymptotically stable zero dynamics for the closed-loop system. To deliver control torques to the actuator command signals, steering laws are designed for two reaction wheels, two single-gimbal control moment gyros mounted in parallel, and one variable-speed control moment gyro, respectively. The resulting control law can be applied to a spacecraft with different kinds of momentum actuators but underactuated for tasks ranging from bounded tracking of a generic trajectory, three-axis earth pointing to line-of-sight pointing, etc. Numerical examples are presented to verify the effectiveness of the proposed method.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Attitude tracking of a rigid spacecraft using two internal torques


    Contributors:


    Publication date :

    2015-10-01


    Size :

    3374939 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Spacecraft Attitude Control Using Aerodynamic Torques (AAS 07-178)

    Gargasz, M. L. / Titus, N. A. / American Astronautical Society et al. | British Library Conference Proceedings | 2007


    Attitude Stabilization of an Asymmetrical Rigid Spacecraft Using Two Impulsive Control Torques (AAS 03-582)

    Kojima, H. / Hashimoto, T. / American Astronautical Society | British Library Conference Proceedings | 2004


    Spacecraft attitude control strategy for reducing disturbance torques

    WASSON CHRISTOPHER JAMES / LEMKE GARY E / MILLS JOHN PRESTON CHARLES et al. | European Patent Office | 2022

    Free access