为了模拟卫星在轨全年的太阳辐照情况, 检验、优化整星的杂散光抑制能力, 分析了光学载荷的在轨成像条件, 设计了一种基于7维扫描镜+2维折反镜+1维被测样件共计10维运动机构的扫描式氙灯太阳模拟器, 并建立了它们关于照明姿态和位置的控制方程, 完成了被测样件的空间环境模拟照明。实验表明, 对1 700 mm×2 700 mm的被测样件可实现方位角为-90°~+90°、俯仰角为-29°~+42.5°的模拟照明, 角精度分别可达0.2°和0.1°, 位置精度优于10 mm。该扫描式太阳模拟器可较精确地为部分卫星提供全年太阳照明空间环境模拟实验。

In order to simulate the annual solar irradiation of a satellite in orbit, thus verifying and optimizing the ability of entire satellite to stray light suppression, the paper analyzes on-orbit imaging condition of optical payload and designs a scanning xenon lamp solar simulator, which has a ten dimensional scanning system including 7-dimension scanning mirror and 2-dimension folding mirror and 1-dimension sample. The controlling formula of all the mechanisms in terms of attitude and location are deduced. Then the simulation of irradiation in space environment is completed. The results show that the solar simulator scans an area of 1 700 mm×2 700 mm with the azimuth angle from -90 ° to + 90 ° and the pitch angle from -29 ° to 42.5 °. Their angular accuracies are up to 0.2 ° and 0.1 ° separately, and the position accuracy is better than 10 mm. Thus the scanning solar simulator can be applied to the accurate simulation of year-round solar irradiation condition for some satellite in orbit.