摘要
随着航天事业的发展,越来越多的宇航工程中会应用一些大型的在轨机构,以满足不同的任务需求,本文设计了一种可应用于航天器太阳翼的圆形空间展开机构。主要包括同步机构的设计、自锁铰链的设计以及驱动机构的设计,最后基于Adams以及RecurDyn两种多体动力学仿真软件分别对本文所设计的驱动机构和四单元扇形空间展开机构进行了动力学仿真,结果表明本文所设计的空间展开机构可实现多级展开,并具有展开的可靠性和可控性。
With the development of the aerospace industry,more and more large-scale orbital mechanisms will be applied in aerospace engineering to meet different mission requirements.A circular space deployable mechanism for applying the spacecraft solar array is designed is this paper.It mainly includes the design of synchronization mechanism,self-locking hinges and drive mechanism.Finally,based on the dynamics of multi-body system software,Adams and RecurDyn,the driving mechanism and the four-unit fan-shaped space deployable mechanism are respectively powered.The simulation results show that the present space deployable mechanism can realize the multi-level expansion and has the reliability and controllability of deployment.
作者
简世康
郭策
Jian Shikang;Guo Ce(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《机械科学与技术》
CSCD
北大核心
2020年第1期150-156,共7页
Mechanical Science and Technology for Aerospace Engineering
基金
国家自然科学基金项目(51875282)资助.
关键词
太阳翼
空间展开机构
驱动机构
动力学仿真
solar array
structural design
deployable mechanism
dynamics simulation
