A GPS Based Autonomous Attitude Determination and Nonlinear Adaptive Robustness Controller Design for Spacecraft
GPS based spacecraft attitude autonomous determination technology is researched, and a Lyapunov stability theory based attitude control law with strong adaptivity and robustness is presented in the paper. A new strategy of spacecraft attitude autonomous determination technology is researched, which aligns two groups of baselines on the spacecraft. One group called short baselines resolves integer ambiguity since its shorter than half of the carrier wave. The other group called long baselines is used to make up the shortages of shorter baseline based attitude determination precision. Adaptive and sliding mode variable structure controller with the stronger adaptability and robustness is designed considering uncertainty of inertia moment of spacecraft and outer disturbance torque. In the control process, an online uncertainty estimator corrects the parameters of sliding mode variable structure controller based on the adaptive law. Finally, numerical simulation about the integrated attitude closed loop composed of determination system and control system is executed on some section of spacecrafts orbit. The results of simulation sustain the effectiveness of the attitude determination and control algorithm presented in the paper.
Fan Yujie Han Yanhua Zhou Changzheng
College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016,China Unit 63892 of PLA , Luoyang 471003 , China
国际会议
International Conference on Space Information Technology 2009(2009年第三届空间信息技术国际会议)
北京
英文
1-11
2009-11-26（万方平台首次上网日期，不代表论文的发表时间）