Design of light flexible carbon fiber boom for satellite

YANG Xuan; LIANG Xu-hao; MA Xin; SHEN Feng; YANG Jian-yu

doi:10.3788/OPE.20172514.0059

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Design of light flexible carbon fiber boom for satellite

更新时间：2020-08-13

- Design of light flexible carbon fiber boom for satellite
- Optics and Precision Engineering Vol. 25, Issue 12z, Pages: 59-66(2017)
- 作者机构：
  
  1. 中国科学院大学北京,中国,100049
  2. 中国科学院国家空间科学中心北京,101499
  3. 复杂航天系统综合电子与信息技术重点实验室北京,101499
  4. 上海复合材料科技有限公司上海,201112
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20172514.0059
  CLC： TP394.1;TH691.9
- Received：23 August 2017，
  
  Revised：10 September 2017，
  
  Published：31 December 2017
- 稿件说明：
移动端阅览
杨萱, 梁旭豪, 马鑫等. 星载轻型柔性碳纤维伸杆设计[J]. 光学精密工程, 2017,25(12z): 59-66

YANG Xuan, LIANG Xu-hao, MA Xin etc. Design of light flexible carbon fiber boom for satellite[J]. Editorial Office of Optics and Precision Engineering, 2017,25(12z): 59-66
杨萱, 梁旭豪, 马鑫等. 星载轻型柔性碳纤维伸杆设计[J]. 光学精密工程, 2017,25(12z): 59-66 DOI： 10.3788/OPE.20172514.0059.

YANG Xuan, LIANG Xu-hao, MA Xin etc. Design of light flexible carbon fiber boom for satellite[J]. Editorial Office of Optics and Precision Engineering, 2017,25(12z): 59-66 DOI： 10.3788/OPE.20172514.0059.

摘要

为了给分离载荷空间探测任务中的主星和子星提供质量轻、星载占用资源低、收拢展开可靠性高、重复展开精度高的空间展开机构，设计了一款轻型柔性碳纤维伸杆。利用主星、子星组合体构型特点，进行了碳纤维伸杆收拢、展开总体布局的优化设计；采用结构机构一体化的整体设计方法对碳纤维伸杆进行构型设计，直接利用杆件直管段U型开孔设计方式，获得了柔性弯曲关节；采用碳纤维复合材料铺层层数与层间铺层角度联合分析方法，进行了伸杆杆件复合材料设计；结合实际力学环境，对伸杆杆件进行了模态分析、折叠展开分析、过载分析以及随机振动分析；此外，对伸杆实物产品进行了拉伸、弯曲、扭转、地面展开、重复展开精度测试试验。试验结果表明：碳纤维伸杆的重复展开精度优于0.018°，展开状态基频大于4 Hz，收拢状态基频大于150 Hz。星载轻型柔性碳纤维伸杆基本满足发射运载要求，能够应用于实际探测任务中。

Abstract

In order to provide space deployable mechanism with light weight

small size

high folded and deployable reliability

and high repeated deployment precision for the mother satellite and daughter satellite in the Deployable Payload Space Science Mission (DPSSM)

a light flexible carbon fiber boom was designed. In terms of the characteristic of the satellite combination configuration

the overall layout of folded and deployable boom was optimized. The configuration of the carbon fiber boom was designed based on mechanism integration method. With U-shaped hole tapped on the carbon fiber boom

flexible joints were obtained. The analysis methods of layer number and layer angle were combined to determine the carbon fiber composite material. Modal

deployment

overload and random vibration of the light flexible carbon fiber boom were simulated with real mechanics environment. In addition

several experiments were performed on the boom

including stretching test

bending test

torsional test

ground unfolding tests and repeated deployment precision test. The results indicate that the repeated deployment precision of the boom is better than 0.018°

and the base frequencies of the deployable and folded boom are higher than 4 Hz and 150 Hz respectively. The light flexible carbon fiber boom basically meets the requirements of launching

thus is feasible in real space science missions.

关键词

Keywords

references

邓宗全. 空间折展机构设计[M]. 哈尔滨:哈尔滨工业大学出版社, 2013. DENG Z Q. Design of Space Deployable and Foldable Mechanisms[M]. Harbin:Harbin Institute of Technology Press, 2013. (in Chinese)

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