空间成像光谱仪的主体支撑方式

摘要

为了改善空间成像光谱仪主体支撑方式对系统光机结构稳定性的影响,分析了成像光谱仪对主体支撑结构的要求,介绍了常用空间光学遥感仪器的支撑方式.在传统支耳支撑方式不能满足离轴非球面三反射镜(TMA)系统热稳定性的情况下,提出了一种新的双耦合的支撑方案并对其进行了理论分析.优化设计过程中,采用有限元分析软件MSC.PATRAN对其三维样机进行工程分析,结果显示,在正弦振动载荷作用下,主体一阶频率为95 Hz;在10 ℃均匀温降与自重耦合作用下,各反射镜的镜面变形RMS最大值为12 nm、PV最大值为60 nm,主镜绕Z轴的转角由原来的55″降低为12″,热真空环境下整机成像试验获得的光谱数据验证了工程分析的正确性,表明双耦合的支撑方案能满足整机刚度和光机系统对热稳定性的要求.%With the aim to improve the effect of the primary support of a space High Resolution Imaging Spectrometer (HRIS) on its stability of optic-mechanic system,the requirements were analyzed for the rigidity and heat stability of a common space remote sensor.The traditional support structures to the space optical remote sensors were introduced.As the traditional supports by lags could not meet the need of the three-mirror anastigmatic (TMA) imaging system,a new coupling support structure by two axes was presented and its theory was analyzed.The finite element analysis of a 3D model was realized by software MSC.PATRAN during the optimum designing.The results show that the first order natural frequency is 95 Hz under sine vibration loading.The maximum RMS value and the maximum PV value of the mirror surface aberration are 12 nm and 60 nm under both of a 10 "C temperature fall and the influence of the gravity,respectively.The angle rotation by the Z axis of primary mirror is reduced from 55" to 12".The spectral data of the optical system under the hot vacuum environments verify the analysis results,which shows the coupling support structure is able to meet the needs of thernrigidity and the heat-stability of optic-mechanic systems.