中国空间科学技术

中国空间科学技术 ›› 2013, Vol. 33 ›› Issue (4): 47-54.doi: 10.3780/j.issn.1000-758X.2013.04.007

• 技术交流 • 上一篇    下一篇

基于比刚度最大的球铰接杆式支撑臂参数设计

黎彪，程刚，刘志全，丁锋   

  1. （中国空间技术研究院，北京 100094）
  • 收稿日期:2013-01-31 修回日期:2013-04-09 出版日期:2013-08-25 发布日期:2013-08-25
  • 作者简介:黎彪 1985年生，2006年毕业于北京航空航天大学飞行器设计专业，现为中国空间技术研究院飞行器设计专业博士研究生。研究方向为航天器结构与机构设计。

Configuration Parameter Design for ADAM-type Articulated Mast Based on Maximizing Specific Stiffness

 LI  Biao, CHENG  Gang, LIU  Zhi-Quan, DING  Feng   

  1. (China Academy of Space Technology, Beijing 100094)
  • Received:2013-01-31 Revised:2013-04-09 Published:2013-08-25 Online:2013-08-25

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摘要： 球铰接杆式支撑臂的构型参数设计决定了支撑臂的质量、收拢包络尺寸、刚度和强度等特性。文章提出了一种基于球铰接杆式支撑臂展开后比刚度最大的构型参数设计方法，利用MATLAB和ANSYS联合仿真，分析了不同构型参数组合下支撑臂比刚度的变化规律。结果表明，对于20~100m范围内的球铰接杆式支撑臂，纵梁与横杆的长度比及套筒半径的优选范围随支撑臂总长度增加而增加。当支撑臂总长度分别为20m、60m和100m时，对应的套筒半径优选范围分别为0.3~0.4m、0.5~0.7m和0.6~0.9m。提出了基于比刚度最大的支撑臂参数设计流程。利用提出的设计方法对SRTM任务中球铰接杆式支撑臂进行了构型参数设计，设计结果与ADAM杆构型参数相近，表明设计方法正确、可行。

关键词: 球铰接杆式支撑臂, 比刚度, 构型, 模态分析, 优化, 航天器

Abstract: The performances of the ADAM-type mast, such as mass, packaging size, stiffness and strength, are determined by its configuration parameters. A new design of configuration parameters based on maximizing specific stiffness was presented. By MATLAB and ANSYS joint simulation，the varying of specific stiffness with different configuration parameters was analyzed. The simulation results show that the optimum value of the length ratio of longeron to batten and the canister radius increases with the increase of the length of mast, when the length of ADAM-type varies in the range of 20 to 100 meters. While the length of mast is 20, 60, and 100 meters, the optimum value of the canister radius varies from 0.3 to 0.4 meter, 0.5 to 0.7 meter and 0.6 to 0.9 meter respectively. The design flow of configuration parameter based on maximizing specific stiffness is as follow: the canister radius is settled at first, then the length ratio of longeron to batten should be determined, and the number of longitudinal member could be finally settled. By this method, configuration parameters of the mast in the SRTM program are designed, and the results approximate to that of ADAM′s.

Key words: Able deployable articulated mast, Specific stiffness, Configuration, Modal analysis, Optimization, Spacecraft