用单框架控制力矩陀螺的大型航天器姿态控制系统实物仿真研究

Research on Physics Simulation of Large Spacecraft Attitude Control System Using SGCMG

利用三轴气浮台模拟航天器空间力学环境,进行了单框架控制力矩陀螺(SGCMG)姿态控制/动量管理系统全实物仿真研究。推导了大型航天器姿态控制/动量管理系统数学模型。设计调试了实物仿真系统。研究了单框架控制力矩陀螺奇异回避问题、失效操纵问题和动量管理优化问题。证明了系统构形分析、奇异性分析和操纵律设计的正确性和有效性。通过大型航天器姿态控制/动量管理系统实物仿真,检验了设计方案的可行性和系统硬、软件的可靠性。

The physics simulation of large spacecraft Single Gimble Control Moment Gyro (SGCMG) attitude control and momentum management system was established, making use of three-axis air-bearing table as spacecraft dynamics simulation object. The mathematics model of SGCMG attitude control and momentum management system was deduced. The physics simulation system was designed and debugged. The problem of SGCMG singularity avoidance, steering law in the condition of SGCMG failure, optimization of momentum management was studied. The experiment proves system configuration and singularity analysis, steering law design is correct. According to simulation of large spacecraft SGCMG attitude control and momentum management system, the design scenario is valid and the hardware and software of system are reliable.