This paper proposes a direct parametric design method for the attitude tracking control of a rigid spacecraft to address the problem of satellite attitude control performance affected by external disturbance. Firstly, the fully-actuated system model for attitude tracking control of a rigid spacecraft is established using quaternions. An extended state observer (ESO) is then developed to handle the influence caused by external disturbances. Then, a controller is designed using the direct parametric method to achieve high-accuracy attitude tracking control of the rigid spacecraft and reach the desired position. Finally, a numerical example involving a rigid spacecraft is presented to demonstrate the effectiveness of the proposed approach in achieving the design objective and exhibiting good control performance.
Attitude Tracking Control of Rigid Spacecraft Based on Fully Actuated System Models
2023-07-14
822300 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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