Discrete Steering Law of Variable-speed Control Moment Gyros in Integrated Power/Attitude Control System
This paper deals with steering law design of Variable-Speed Control Moment Gyros (VSCMGs)used in Integrated Power/Attitude Control System (IP ACS). Dynamic model of IPACS for a rigid spacecraft equipped VSCMGs is established. A discrete steering law of VSCMGs is proposed. By means of two weighting matrices, the steering law can perform not only torque distribution between Control Moment Gyro(CMG)mode and Reaction Wheel (RW) mode, but also the balance of the spin rates of VSCMGs. Comparing with the conventional steering laws,the new steering law has the advantage of no theoretical error between the actual torque generated by VSCMGs and the command one. A new singularity index of VSCMGs is proposed. It reflects level of CMG singularity of VSCMGs intuitively and reliably. The merit of the singularity index is that it is simple in null motion calculation and has explicit physical meaning. Simulation results validate the discrete steering law; furthermore the precision of the attitude control system is improved evidently.
Integrated Power/Attitude Control System Variable-speed Control Moment Gyro Attitude Control Steering Law Singularity
Zhang Jun Xu Shijie
Laboratory 504, School of Astronautics, Beijing University of Aeronautics and Astronautics,Beijing 100083,China
国际会议
The 11th International Space Conference of Pacific-basin Societies(第11届环太平洋国际航天会议)
北京
英文
334-341
2007-05-16（万方平台首次上网日期，不代表论文的发表时间）