Research On The Close Distance Approach Schemes Of Minitype Space Aerocraft

With the rapid development of space technology, space aerocraft technique using for implement multifarious operation in the space has become more and more mature. Many countries including China have been participating in this field with different extent. In this thesis, we do some research in the approaching process of space aerocraft and complete some analysis on several kinds of guidance and attitude control means, the effectiveness of the different schemes above are verified by simulation.Firstly, this thesis gives the definition of reference frame describing the rendezvous and docking process, finishes the modeling analysis of aerocraft dynamics, which include the translational dynamic equation—Hill equation, the attitude dynamic and kinematic equations. We also give the dynamic model of actuator for completing the translational control and attitude control. Secondly, this thesis gives several translational guidance strategies of the close range approaching process of aerocraft, which include the beeline guidance rule and potential function guidance rule based on the Hill equation and the phase plane guidance rule based on the simple form of it. We give the basic principle introduction of every guidance strategies and the implement methods of them through thruster as actuator. The Matlab simulations of each guidance strategy are given here. We also introduce the design means of the semi-physics simulation flat for the space aerocraft close range approaching process and the experiment verification of the beeline guidance rule is also done on the semi-physics simulation flat.Finally, in the thesis, we also give two schemes on the attitude control of close range approaching process. One of them is obtaining the linearization form of the attitude dynamic equation and implementing the combination of proportion and differential control strategy with PWPF regulator, the necessary condition for the stability of this method is also given here. the other is the application of phase plane method like translational control on the relative attitude control of these two flying vehicle. The Matlab simulation and the experiment verification of Former method are given, with the latter only Matlab simulation is done.