基于导星电子星图模拟器的卫星控制系统半物理试验方法

为了实现卫星的高精度高稳定度控制,中法天文卫星建立了卫星姿轨控半物理仿真试验系统.对该系统采用导星电子星图模拟器引入仿真闭环进行研究.首先,将导星敏感器作为高精度姿态测量部件引入控制系统,地面动力学为其提供输入信息.接着,高精度测量单机和高精度控制机构引入到闭环中.然后,粗测量敏感器和粗控执行机构由数学模型替代.最后,通过地面实时系统将控制系统、星务计算机、载荷计算机和整星电源系统组成了实时仿真验证系统.实验结果表明:在地面半物理条件下,可以达到导星进入开小窗条件,y、z轴稳定度达到2(″)/10 s及5(″)/100 s.导星敏感器可以提高姿态测量精度和姿态控制的稳定度.满足控制稳定度在亚角秒级别卫星的要求.

Semi-physical Test Method of Satellite Control System Based on Fine Guidance Sensor Electronic Star Map Simulator

In order to control the satellite with high precision and stability, a semi-physical simulation system for satellite attitude and orbit control was established by Chinese and French astronomical satellite. The simulation closed-loop of the fine guidance sensor electronic star map simulator used in the system was studied. Firstly, the fine guidance sensor was introduced into the control system as a high precision attitude measurement component, and the input information was provided by ground dynamics. Secondly , the high precision measuring sensors and high precision control actuators were introduced into the closed loop. Thirdly , the rough measuring sensors and rough control actuators were replaced by mathematical model. Finally, the real-time simulation verification system was composed of the control system, the satellite management unit, the payload computer and the satellite power system through the ground real-time system. The experimental results show that under the condition of semi-physical test, small open window conditions of fine guidance sensor can be achieved, y, z axis stability is reached 2?/10 s and 5?/100 s. The attitude measurement accuracy and attitude control stability can be improved by the fine guidance sensor. It meets the requirement of satellite with control stability of sub-angular second.