空间无动力源可重复锁紧分离机构设计与分析  

Design and Analysis of Unpowered and Repeatable Locking Separation Mechanism for Space

作　　者：王存义 张乐乐[2] 窦伟元 颜家勇 龚康 WANG Cunyi;ZHANG Lele;DOU Weiyuan;YAN Jiayong;GONG Kang(Beijing Satellite ManufacturerCo.,Ltd.,Beijing 100094,China;Beijing Jiaotong University School of Mechanical,Electronic and Control Engineering,Beijing 100044,China)

机构地区：[1]北京卫星制造厂有限公司,北京100094 [2]北京交通大学机械与电子控制工程学院,北京100044

出　　处：《机械设计与研究》2022年第4期56-60,共5页Machine Design And Research

摘　　要：针对现有空间锁紧分离机构在深空探测与在轨服务等特定领域运用受限的问题,设计一种无动力源可重复锁紧分离机构。该锁紧分离机构基于凸轮机构原理,结合机械传动紧凑化设计实现了分离、避让、捕获、锁紧多重动作一体化集成。通过建立锁紧勾运动参数化模型,对凸轮槽构型曲线进行优化设计,得到锁紧勾满足预期动作的凸轮槽曲线,在此基础上对锁紧机构进行了动力学仿真分析,仿真结果表明:在300 N锁紧载荷工况下,操作末端操作力矩为0.14 Nm,锁紧勾行程11 mm,满足设计指标。对锁紧机构进行功能试验验证,结果表明该锁紧机构能够实现对载荷单元多次锁紧分离功能,且锁紧分离过程平缓、顺畅,验证了设计的正确性与可行性。所提出的锁紧分离机构及其设计与分析方法可为其他同类产品提供参考。In view of limited application of existing space locking separation mechanism in deep space service,an unpowered and repeatable locking separation mechanism is designed in this paper based on the principle of cam mechanism and the mechanical drive compact design.By establishing the parametric model of the locking mechanism motion,the cam groove configuration curve is optimized,including the dynamic simulation analysis of the locking mechanism.Simulation results show that the operating torque is 0.14 Nm under the 300 N lock-up load condition,and the locking mechanism stroke is 11 mm,which meets the design index.The functional test and verification of the locking mechanism show that the locking mechanism can realize the multiple lock separation function of the load unit,and the lock separation process is gentle and smooth,which verifies the correctness and feasibility of the design.The proposed lock separation mechanism and its design and analysis methods can provide reference for other similar products.

关 键 词：锁紧分离 机构设计 非火工 动力学 空间机构 

分 类 号：V423.9[航空宇航科学与技术—飞行器设计]