航天器杆件死点特性结构锁设计与分析  

Design and Analysis of Space Aircraft Structural Lock with Dead Point

作　　者：曹晓瑞[1] 陈尚[1] 杨飞[2] 吴君[2] 

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]哈尔滨工业大学机电工程学院,黑龙江哈尔滨150001

出　　处：《机械设计与制造》2017年第6期248-251,共4页Machinery Design & Manufacture

基　　金：通用化纳星群组承载与定向释放技术(863项目:2015AA7046504)

摘　　要：针对天地往返航天器舱门需要重复开启与关闭的实际需求及传统火工分离装置只能单次解锁且伴随大冲击与振动的缺点,提出一种曲柄-摇杆四杆舱门重复锁紧机构。该机构基于平面四杆机构的死点区域来实现对舱门的可靠锁定,具有承载能力大、锁紧及解锁过程冲击微小、结构简单、重量轻及性能可靠等优点。为了更好地利用该机构的死点特性完成舱门的可靠锁紧,对机构的死点特性进行建模分析,给出使机构自锁的死点区域。对锁紧机构进行参数化建模,建立机构的参数化优化目标函数,利用MATLAB对进行机构优化设计并得到最优结构参数。仿真结果表明所提的锁紧机构可将舱门可靠地锁紧且经过优化后的锁紧机构所需的驱动力矩显著降低,具有较高的驱动效率。For the repeat opening and locking requirement of space aircraft hatch and the disadvantage of traditional pyrotechnically actuated separation devices with big impact and vibration during single unlocking, one repeated locking hatch four-bar mechanism composed of crank and rocker is proposed. Based on the dead point of planar four-bar mechanism, the hatch could be locked reliably with the advantage of high capacity, low impact, simple structure, light weight and reliable performanee. The dead point characteristic of the repeated locking mechanism is studied and the self-locking region is given. The parametric model is built and optimization object function is obtained, the structure of the repeated locking mechanism is optimized using MATLAB software and the optimal structural parameters are achieved. The simulation results show that the space aircraft hatch could be locked reliably by the proposed locking mechanism, and the driving torque during locking mechanism is decreased significantly after optimization.

关 键 词：航天器 舱门 重复锁紧 机构死点 优化 

分 类 号：TH16[机械工程—机械制造及自动化] V476.1[航空宇航科学与技术—飞行器设计]