地面姿态模拟光源控制系统研究

太阳敏感器和红外地球敏感器是卫星升空以后进行姿态控制的两个重要部件, 地面姿态模拟光源作为地面测试设备, 用来在地面上给这两个部件提供太阳模 拟信号和红外地球模拟信号. 本文设计了一套由4条光缝组成的模拟卫星自旋转 动的小型太阳模拟光源及针对地球同步轨道高度模拟15.6°张角的南 (北)红外两个地球模拟光源, 并为南北地球敏感器太阳保护探头提供了模拟 的太阳保护光源. 根据地面姿态模拟光源控制系统的组成和总体结构, 通 过分析计算给出各模拟光源之间严格的时序关系, 并对各模拟光源之间的时序 进行了实验测试, 结果表明模拟转速锁相误差不大于1ms, 各模拟光源时序 之间的角度误差小于0.5°. 

Research on the Control System of the Ground Attitude Simulation Light Source

The Sun sensor and the infrared Earth sensor are two important components of attitude control after satellite launch. The ground attitude simulation light provides solar simulation signal and infrared Earth analog signal for the two parts as a ground test equipment. This paper designs a set of ground attitude simulation light which consists of one solar simulation light including 4 light seams and one north as well as one south infrared Earth simulators to simulate the opening angle of 15.6°, and provides an analog Sun protection signal for south and north Earth sensors' Sun protection probes. Composition and the overall structure of the ground attitude simulation light control system are described in detail. Through analysis and calculation of each simulation, strict timing relationship between the sources is given, and through the experiments of each source simulation between sequential test, it can be shown that the simulation speed phase-locked error is no more than 1ms, and the angle error between light source simulation timing is less than 0.5°.