基于SiC材料的空间相机非球面反射镜结构设计  

Space telecope aspherical mirror structure design based on SiC material

作　　者：张学军[1] 李志来[1] 张忠玉[1] 

机构地区：[1]中国科学院长春光学精密机械研究所,吉林长春130033

出　　处：《红外与激光工程》2007年第5期577-582,共6页Infrared and Laser Engineering

基　　金：中科院三期创新支持项目

摘　　要：针对空间相机中优质轻型光学反射镜对材料提出的要求,详细讨论了设计基于SiC材料空间反射镜的一系列问题,包括径厚比的选择、支撑点数量、轻量化结构形式、材料特性匹配等,提出了一种背部半封闭、三角形孔的轻量化形式,并设计制造了Φ600 mm轻量化SiC反射镜实验件。抛光后反射镜面形精度优于λ/20 rms。为验证重力变形的影响,将反射镜分别旋转了90°和180°,用Zygo干涉仪检验,3个方向检测结果误差均小于λ/100 rms。在此基础上设计完成了某空间相机中的SiC非球面主镜、次镜、第三镜,结果表明基于SiC材料的反射镜在重力变形、谐振频率、热变形等方面均能满足使用要求,而且与玻璃材料相比,在很大程度上降低了重量。According to the demand of material of high quality reflection mirror in space telescope, the design issues for SiC mirror such as aspect ratio of diameter to thickness, light-weighting structure, number of support points, characteric match and so on are discussed. A new design with semi-closed back and triangular hole light-weighting structure is proposed. To verify its reliability, a 600 mm diameter lightweighting SiC mirror was designed and manufactured, the final surface figure accuracy is superior to λ/20 rms after polishing. Interferometric measurement with Zygo interferometer at three orientations of 0°, 90°, 180° was taken respectively, the difference is less than λ/100 rms.Based on the above discussions, the primary mirror, secondary mirror and tertiary mirror in a space telescope and the primary mirror of missile guider optics were designed, it has proven that the performance such as self-weight deflection, fundamental frequency, thermal stability all meets the requirement. In addition, compared to glass mirrors, SiC mirrors can reduce big amount of weight.

关 键 词：碳化硅 空间相机 反射镜 非球面 

分 类 号：V447[航空宇航科学与技术—飞行器设计]