An approach to on-board sampled data estimation and control of the attitude motion of maneuvering spacecraft is presented. Algorithms for model following control of attitude maneuvers; estimation of spacecraft state (attitude, angular velocity, disturbance, torque); and optical-inertial attitude determination, with estimation of gyro parameters (drift rate bias, scale factor error) were developed. The algorithms were validated in single-axis software simulations of an attitude control system of the type used in the Infrared Astronomical Satellite. The control system comprises a strapdown rate-integrating gyro and a slit-type star sensor for optical-inertial attitude sensing, a reaction wheel actuator, and a digital on-board computer. The truth models for simulation of the hardware components are discussed.


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    Title :

    Application of Model Following Control and Estimation Techniques to Attitude Control of Maneuvering Spacecraft. Part 1. Theory and Simulation Results


    Contributors:

    Publication date :

    1982


    Size :

    122 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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