空间光学遥感器主镜展开机构锁紧刚度分析  

Analysis of Locking Stiffness of Primary Mirror Deployment Mechanism for Space Optical Remote Sensors

作　　者：孙国鹏[1] 刘志全[1] 

机构地区：[1]中国空间技术研究院,北京100094

出　　处：《中国空间科学技术》2008年第2期21-27,共7页Chinese Space Science and Technology

摘　　要：采用等效弹簧模型对空间光学遥感器主镜的旁瓣子镜与中央子镜的锁紧刚度进行简化处理,分别分析了"旁瓣子镜与中央子镜之间锁紧力"和"旁瓣子镜与中央子镜之间定位装置的定位球直径"对空间光学遥感器主镜结构固有频率的影响。分析结果表明,旁瓣子镜与中央子镜通过运动支承定位并由锁紧装置锁紧后,结构1阶固有频率由整体式结构的33.592赫兹下降为十几赫兹,下降幅度约50%。增大锁紧力和定位球直径都可以提高主镜结构的固有频率,但是增大定位球直径对固有频率的提高比增大锁紧力对固有频率的提高要明显得多。The locking stiffness between the petal and the central part was simplified by the equivalent spring model. Using this model, the effects of the locking force and the ball diameter on the modal frequencies of the structure were analyzed. The analytical results show that the fundamental frequency of the structure connected by the kinematic couplings declines from 33. 592 Hz of the fixed structure to 10-20 Hz, and it is more effective to increase the modal frequencies of the structure connected by the kinematic couplings by increasing the diameters of the location balls than by increasing the locking force.

关 键 词：等效弹簧模型 展开机构 刚度 锁定紧固装置 光学遥感器 航天器 

分 类 号：V443.5[航空宇航科学与技术—飞行器设计] O327[理学—一般力学与力学基础]