微小卫星天线与飞轮共支撑结构优化设计与试验  

Optimization design and test of a co-support structure of borne antenna and flywheel of a micro-satellite

作　　者：李林[1,2] 王栋[2,3] 谭陆洋 孔林[2] 杨洪波[2] 

机构地区：[1]中国科学院大学,北京100049 [2]中国科学院长春光学精密机械与物理研究所,吉林长春130033 [3]长光卫星技术有限公司,吉林长春130033

出　　处：《红外与激光工程》2016年第10期191-197,共7页Infrared and Laser Engineering

基　　金：国家863计划(2012AA121502)

摘　　要：针对基于星载一体化理念设计的某微小卫星星载天线与S飞轮支撑结构随机振动响应不满足总体设计指标的问题,将星载天线与飞轮进行共支撑结构设计,提出以随机振动加速度响应为目标的优化设计方法。以支撑结构敏感点随机响应RMS值为优化目标,体积分数和基频为约束条件,建立数学模型,对结构进行优化设计;对优化后的支撑结构工程分析,基频达到200 Hz以上,质量由1.9 kg减少到0.65 kg,降低65.6%;开展了力学环境试验对支撑结构性能进行验证,支撑结构基频210 Hz,加速度响应RMS值最大相对放大率为0.54,满足总体基频大于185 Hz和相对放大率小于等于0.6的要求。结果表明,该优化方法有效可行,支撑结构动力学参数较好地满足了微小卫星总体设计要求。For the random vibration response of a micro satellite loaded antenna and S-flywheel supporting structure does not meet the criteria for system design of the micro-satellite based on integrated design concept, a co-supporting structure design of the satellite borne antenna and the flywheel was presented. The support structure sensitive point of random response RMS value as the optimization objective, the volume integral number and frequency constraints, the optimization mathematical model was established, the structure was optimized by using OptiStruct software, the support structure optimization treated by finite element analysis, the fundamental frequency reach 200 Hz, the quality is reduced by 65.6%; the vibration test of support structure performance was verified, the maximum relative amplification rate of x, y, z three direction acceleration response RMS value is 0.54. Results show that the optimization method is effective and feasible, and the supporting structure dynamic performance meets the requirements of a micro satellite design index optimization design well.

关 键 词：星载一体化 微小卫星 支撑结构 优化设计 加速度响应 随机振动 

分 类 号：V423.4[航空宇航科学与技术—飞行器设计]