Relative Motion Modeling between Spacecraft and Reaction Rod & Spacecraft Attitude Control Research
Astronomy Observation Satellites (AOS) usually rotate the reaction rod to change the mounted sensor’s observation direction. Based on this fact, rigid two-body dynamic model is deduced according to Moment of Momentum Theorem in this paper. According to the being-observed object’s azimuth and elevation relative to the satellite’s body-coordinate frame, the rod’s rotation angles are solved by some mathematic deductions. The attitude change of the AOS can be determined by use of the presented dynamic model and it should be compensated. After introducing quasi Euler angles, which are modulated from attitude quaternion, a switching attitude control law based on quasi Euler angles is proposed. The attitude of the AOS is controlled to the required one by thrusters with the proposed switching attitude control law. Simulation results show that dynamic model for the presented rigid two-body is accurate and the proposed attitude control law is competent for controlling the satellite’s attitude.
Wuxing Jing Xiwang Xia Changsheng Gao Wenshu Wei Zhigang Li
Department of Aerospace Engineering,Harbin Institute of Technology,Harbin 150001,China.
国际会议
哈尔滨
英文
13-18
2010-01-08（万方平台首次上网日期，不代表论文的发表时间）