北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (12): 2625-2631.doi: 10.13700/j.bh.1001-5965.2015.0808

• 论文 • 上一篇    下一篇

含铰链间隙板式卫星天线展开精度分析

丁建中1, 王春洁1,2   

  1. 1. 北京航空航天大学 机械工程及自动化学院, 北京 100083;
    2. 北京航空航天大学 虚拟现实技术与系统国家重点实验室, 北京 100083
  • 收稿日期:2015-12-07 出版日期:2016-12-20 发布日期:2016-04-11
  • 通讯作者: 王春洁,Tel.:010-82339818,E-mail:wangcj@buaa.edu.cn E-mail:wangcj@buaa.edu.cn
  • 作者简介:丁建中,男,博士研究生。主要研究方向:多体动力学、机构间隙理论。Tel.:15911106863,E-mail:jianzhongd@buaa.edu.cn;王春洁,女,博士,教授,博士生导师。主要研究方向:数字化设计与仿真。Tel.:010-82339818,E-mail:wangcj@buaa.edu.cn

Deployment accuracy analysis of planar satellite antenna with joint clearances

DING Jianzhong1, WANG Chunjie1,2   

  1. 1. School of Mechanical Engineering & Automation, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
    2. State Key Laboratory of Virtual Reality Technology and Systems, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2015-12-07 Online:2016-12-20 Published:2016-04-11

摘要: 板式卫星天线展开机构在航天领域有着广泛的应用,其空间尺寸大,拓扑结构复杂,构件之间多用铰链联结,卫星天线对指向精度要求较高,应考虑铰链间隙对指向精度的影响。含铰链间隙的卫星天线展开机构的指向精度分析建模复杂、求解困难,为此提出了矩阵法分块建模的分析方法,将复杂的整机模型分解成锁定机构计算模型与2个单闭环机构计算模型,分别分析计算铰链间隙对其精度造成的影响,建立整机的计算模型并采用粒子群优化算法进行求解,得到某特定构型的板式卫星天线在极恶劣工况下展开的指向误差为0.067°。研究表明,建立的计算模型精度高,通过智能优化算法求解可以快速得到卫星可展开机构的指向精度极恶劣值,为展开机构的误差补偿设计提供参考。

关键词: 可展开机构, 误差分析, 铰链间隙, 运动学分析, 粒子群优化算法

Abstract: Planar folding satellite antenna deployment mechanism is widely used in the field of astronautics. It has a large and complicated topology structure, which is composed by joint-connecting rods. The existence of joint clearances makes the analysis of the antenna deployment a tough task and contributes a lot to pointing error. A matrix modeling approach is proposed to solve such kind of analysis problem. The complex multi-loop structure of a deployable mechanism is divided into locking mechanism and single-loop mechanisms. The accuracy of each mechanism is calculated separately to make the computing easier. Finally, the maximum pointing error of the entire deployable mechanism with a specific structure is calculated to be 0.067° by a particle swarm optimization algorithm, referring to the accuracy analysis results of locking mechanism and single-loop mechanisms. This proposed calculation approach is of high precision and the maximum pointing error of the satellite antenna deployable mechanism can be obtained efficiently by the intelligent optimization algorithm. It provides reference in error compensation design of the deployable mechanism.

Key words: deployable mechanism, error analysis, joint clearance, kinematic analysis, particle swarm optimization algorithm

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