基于反作用飞轮和磁力矩器的卫星姿态控制系统分析-analysis of satellite attitude control system based on reaction flywheel and magnetic torque device.docxVIP

哈尔滨工业大学工程硕士学位论文 II Abstract the attitude control system which based on reaction flywheel and magnetic torque has infinite life in theory because of no consumption of cold gas or fuel. It has been one of the key research directions for domestic and foreign scholars. In this paper, design and simulation study for attitude control system which based on flywheel was presented in different attitude control modes of a certain satellite. The major technical parameters about reaction flywheel and magnetic torque were studied through the simulation. First, dynamic model and kinematics model of the micro-satellite were established, and then a certain amount of research on the space interference was made. Second, flywheel simulation model which reflected main performance parameters of the flywheel was established after the analysis about the reaction flywheel model of the control system. It prepared the grind for our further study about the influence of the flywheel performance on the attitude control system. Magnetic unloading model of the attitude control system was also presented in the paper. Then, the design for attitude control system were classified mainly in four ways according to the different control mode when satellite run in space. It mainly included directional three-axis stability control system, attitude maneuver attitude control system, directional attitude control system and omni-directional to capture the day the attitude control system. The feasibility of the design for these control systems was verified by simulation implementation from one to the other. In addition, the simulation about the attitude maneuver control system and all-round to capture the day control system was further investigated in this paper. III Through the simulation, we can conclude the reference range of main performance parameters about the reaction flywheel and the magnetic torque. Finally, the fault conditions that the micro-satellite may arise were analyze