摘要
描述了空间相机运载发射及在轨运行阶段经历的力学和热环境,提出空间相机主支撑结构优化设计方法,用有限元分析法对卡塞格林和TMA两种具体空间相机光学系统主支撑结构进行了优化设计。对拓扑优化前后分析结果进行比较,卡塞格林光学系统主支撑结构一阶固有频率从41Hz提高到72Hz,重量降低15%;TMA光学系统主支撑结构一阶固有频率不变,重量降低35%。结果表明,采用此优化设计方法不仅缩短了设计周期,而且有效地降低了支撑结构重量,提高了主支撑结构的性能,满足系统设计要求。
After described the mechanical and thermal environments during launching period and in orbit period of space camera,the main support structure optimization design method of space camera is brought forward.Based on the method,two kinds of main support structure of space camera with Cassegrain and TMA optical system are optimized by Finite Element Method.Comparing the results gained after the topology optimization with before,the first inherent frequency of main support structure of Cassegrain optical system is raised from 41Hz to 72 Hz with 15 percent weight lost and no change on the first inherent frequency of main support structure of TMA optical system with 35 percent weight lost.The results indicate,adopting this optimization design method,not only is the design period shortened,but the support structure weight is effectively reduced and the capability of the main support structure is enhanced which can satisfied the system design requirements.
出处
《光学技术》
CAS
CSCD
北大核心
2006年第z1期651-653,658,共4页
Optical Technique
基金
863基金资助项目(863-2-5-1-13B)
