A Low-impact Hinge Mechanism Based on the Lever Escapement Mechanism
An original application of the stone lever escapement mechanism on aerospace deployable hinges driven by scroll springs is presented in this paper.This application is intended to decrease the impact at the end of the deploying process.The structure of the mechanism is designed and the major parameters are determined based on the design principle of lever escapement mechanism,and the deploying time is estimated.A simulation model is developed,and a series of cases is simulated to verify the feasibility of this innovative hinge mechanism.The advantage of this application is assessed by indexes of maximum angular velocity and impact force.The maximum angular velocity can de decreased by 76.02%-80.53% with impact force decreased by 85.92-92.47%.Influence of variables of hairspring stiffness and preload moment of the scroll spring on the deployment are discussed.
Lever Escapement Mechanism Deployable Hinges Simulation low impact
Li Zhongjie Guo Hongwei Li Yuchao Liu Rongqiang Shi Wenhua
State Key Laboratory of Robotics and System,Harbin Institute of Technology,Harbin 150001,China China Academy of Space Technology,Beijing 100000,China
国际会议
天津
英文
1-6
2014-07-06（万方平台首次上网日期，不代表论文的发表时间）