卫星多轴指向姿态控制全物理仿真实验研究

Experiment Research for Satellites' Multi-axis Pointing Attitude Control

具有大型天线和大面积太阳帆板的多体卫星多轴指向控制技术是航天器控制的关键技术之一,针对这一问题,设计了“前馈+变结构”方案控制卫星本体,天线指向控制根据任务要求结合本体姿态产生,形成本体与天线多轴指向控制方案。基于常用的“飞轮—喷气”执行机构模式,考虑了控制精度和喷气消耗量问题。利用带有大型挠性板与程控天线系统的单轴气浮台物理仿真实验系统,成功地进行了卫星多轴指向控制物理仿真实验,本体姿态控制精度达到0.020,天线指向精度达到0.50。该研究对多轴指向卫星控制系统设计具有实际参考价值。

Multi-axis pointing control is a key issue for multi-body satellites with large flexible solar panels and antenna. This paper designed a ＂forward and variable structure＂ scheme to control the attitude of the satellite body, the antenna pointing was decided by the attitude of the satellite body, to achieve multi-axis pointing control goal. A simple control algorithm was designed according to the ＂wheel-thruster＂ actuator mode, considering control precision and gas consumption. On a physical testhed composed by a single axis air bearing table, flexible appendages and an antenna, the physical simulation experiments for multi-axis pointing control were successfully carried out. The precision of the satellite body attitude is within 0.02°, the precision of the antenna pointing is within 0.5°. This has important value for the control of multi-axis satellites.