空间天线展开机构运动学分析  

Motion Analysis on Structure for Space Deployment Antenna

作　　者：秦丽华[1] 刘成国[1] 邵春收[1] 段雅丽[1] 穆立民 Qin Li-hua;Liu Cheng-guo;Shao Chun-shou;Duan Ya-li;Mu Li-min(Beijing Institute of Space Long March Vehicle, Beijing, 100076)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《导弹与航天运载技术》2017年第4期26-29,共4页Missiles and Space Vehicles

摘　　要：根据利用母舱自旋实现天线展开机构的具体结构,考虑天线杆离心力、阻尼力矩等因素,建立了微小型航天器天线展开机构的运动学模型。开展二杆、四杆状态下的试验验证,计算结果与试验结果符合较好。试验结果验证了模型的合理性,为利用母舱自旋实现天线展开的机构设计提供了理论研究方法。Centrifugal force and damping are considered based on structure of antenna deployment mechanism uses space's rotate energy.A motion model of the antenna deployment mechanism of the small spacecraft is deduced and implemented.According to the model,the computer program is developed by FORTRON.The experiments of the different pressure are carried out.Calculation results coincide with the experiment results,the correct of the ejection model is tested by the experiment results.The study offers theoretical methods for constructional design of the antenna deployment mechanism.

关 键 词：航天器 展开机构 运动学分析 

分 类 号：V443.4[航空宇航科学与技术—飞行器设计]