基于导轨结构的新型笼式皮卫星分离机构  

New cage style pico-satellite deployer based on sliding guide structure

作　　者：吴昌聚[1] 徐秀琴[1] 

机构地区：[1]浙江大学航空航天学院,浙江杭州310027

出　　处：《浙江大学学报（工学版）》2014年第3期548-554,共7页Journal of Zhejiang University：Engineering Science

基　　金：中央高校基本科研业务费专项资金资助项目(2013QNA4044)

摘　　要：针对国际上现有皮卫星分离机构存在的不足,提出采用切割器解锁、弹簧驱动、导轨限位、凸轮控制星体开始运动的时刻、锁紧轴锁紧和自带供电系统的"笼式"新型分离机构.这种结构大大降低了对星体的设计约束,避免了星体和舱门之间的碰撞和刮擦,降低了对火箭的依赖,大大提高了搭载的可能性.从分离机构的设计、分离过程理论计算以及试验验证等方面对分离机构进行了研究.仿真分析及试验结果表明:该设计能够完全满足分离机构质量、分离速度、轴向和横向过载、基频的要求,为后续分离机构的进一步研制提供了参考.In view of the drawbacks of the currently used pico-satellite deployers,a new cage style deployer was put forward,which is characteristic of cutter unlocking the door,conical spring driving the pico-satellite,oriented rail restricting the direction,cam controlling the start movement of pico-satellite,locking shaft fixing the door and having power supply system itself.This structure greatly reduces the constraint on the pico-satellite design,and avoids the collision or scratch between the pico-satellite and the deployer door.The design also reduces the dependence on the rocket and greatly increases its compatibility with the rocket.In this work,the deployer research includes designing,theoretical calculation of the deploying process and experimental verification.The results of calculation and experiment show that the design can meet the requirements fully,including the mass of the deployer,deploying velocity,overload of the axial direction and the transverse direction and basic frequency.This can be regarded as reference for the further development.

关 键 词：导轨结构 皮卫星 分离机构 分离速度 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程] TH12[机械工程—机械设计及理论]