The Robust Control For The Spacecraft Attitude And Orbit

The relative motion of the spacecraft attitude and orbit control is an important research direction in space technology, which is widely used in space missions such as rendezvous and docking, spacecraft formation flying and flying around the spacecraft, etc. As the growth of the space mission requirements, performance requirements of the controller are higher and higher. The finite-time control with finite-time convergence, high control precision and strong robustness has attracted wide attention of scholars. In addition, with the improvement of relative motion control accuracy, attitude and orbit coupling phenomenon has received more and more attention. The main research in this paper is as follows.Firstly, the attitude and orbit motion models of the spacecraft were given without attitude and orbit coupling effect. Quaternion is used to describe the attitude of the rigid body and the body frame is reference frame. In the orbit motion model,the orbital coordinate system is reference frame. Further, considering the coupling of attitude and orbit, the six degrees of freedom coupling model was given and the body frame is reference frame.Secondly, in view of the problem of spacecraft attitude control, based on the sliding mode control theory, the exponential approach controller with known bounds of the disturbance was designed. In addition, a robust exponential approach controller with unknown bounds of the disturbance and the uncertainty of inertia was given based on the theory of sliding mode control and adaptive control theory.Finally the proof and simulation of above controllers were given.Thirdly, in view of the problem of the spacecraft orbit relative motion control,the finite-time controllers with known bounds, unknown bounds of the disturbance and the uncertainty of inertia were given based on the theory of terminal sliding mode control and adaptive control theory, respectively. Finally the proof and simulation of above controllers were given.Finally, on the basis of the above research, the results of the orbit control are generalized to the relative motion of the spacecraft attitude and orbit coupling control. The strict proofs of the controllers were given and numerical simulations were used to illustrate the proposed controller.