Analysis Of Attitude Control Properties Of Space Station

The space station is the most representative of large manned spacecraft, which has the huge space application value. Space Station System is the world's most complex and the most difficult to achieve, the most of the systems application of new technologies. The large flexible accessories installed of space station, the process of the cabin-style space station's relocation, the momentum management request of space station all make space station's attitude control system have new problems. This paper analyses three key points on the space station attitude control.Firstly, the kinematics model and the dynamic model of the space station attitude control are established in this paper. The main disturbance torque of the space station by orbit is analyzed. And the detailed modeling method of the aero torque and gravity gradient torque are proposed.Secondly, Analysis the influence for flexible attachment to the accuracy of space station attitude control, and the attenuation of the vibration strength is analyzed. The effect for the fundamental frequency of the panels to space station attitude control is analyzed.If the bandwidth has been designed orderly, the influence of the flexible attachment's vibration which is caused by continuous control torque to the space station attitude control is tested to be little by simulation.Thirdly, to study the relocation of the cabin of the space station, the multi-body dynamics model in the process of relocation is established. Through the simulation the influence of the aero torque and the gravity gradient torque in the process of the relocation is analyzed, the request of the relocation process to the space station control is analyzed. The conclusion of the horizontal relocation process is better than the vertical relocation process is proved; primarily because of the maximum CMG's momentum change of the horizontal relocation process is smaller.The final part of this thesis, the linearization of the kinematics model and the dynamic model of the symmetry space station near the TEA attitude is completed based on the TEA flying mode, the momentum management method is proposed, the LQR controller with the fixed stability margin is designed, the effectiveness of the controller without the disturbance filter and the controller with the disturbance filter is simulated, the effectiveness of the LQR controller with the disturbance filter for the space station attitude control and momentum management is proved.