星载轻型柔性碳纤维伸杆设计

杨萱; 梁旭豪; 马鑫; 沈峰; 杨剑宇

doi:10.3788/OPE.20172514.0059

您当前的位置：

首页 >

文章列表页 >

星载轻型柔性碳纤维伸杆设计

更新时间：2020-08-13

- 星载轻型柔性碳纤维伸杆设计
- Design of light flexible carbon fiber boom for satellite
- 光学精密工程 2017年25卷第12z期页码：59-66
- 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：
  
  民用航天专业技术预先研究项目（国家国防科技工业局）（No.Y32116ED1S）()
- DOI：10.3788/OPE.20172514.0059
  中图分类号： TP394.1;TH691.9
- 收稿日期：2017-08-23，
  
  修回日期：2017-09-10，
  
  纸质出版日期：2017-12-31
- 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)

XING ZH G, ZHENG G T. Deploying process modeling and attitude control of a satellite with a large deployable antenna[J]. Chinese Journal of Aeronautics, 2014, 27(2):299-312.

杨维垣. 空间机构分类及可靠性研究[J]. 航天器工程, 1994(3):31-39. YANG W Y. Spatial mechanism classification and reliability study[J]. Spacecraft Engineering, 1994(3):31-39. (in Chinese)

ILIEVSKI F, MAZZEO A D, SHEPHERD R F, et al.. Soft robotics for chemists[J]. Angewandte Chemie, 2011, 50(8):1890-1895.

YANG H, LIU R Q, WANG Y, et al.. Experiment and multiobjective optimization design of tape-spring hinges[J]. Structural and Multidisciplinary Optimization, 2015, 51(6):1373-1384.

BALLABEN J S, GUZMÁN A M, ROSALES M B. Nonlinear dynamics of guyed masts under wind load:sensitivity to structural parameters and load models[J]. Journal of Wind Engineering and Industrial Aerodynamics, 2017, 169:128-138.

黄丹敏. 空间铰接式伸展臂可靠性分析及仿真研究[D]. 杭州:浙江理工大学, 2014:1-2. HUANG D M. Reliability Analysis and Simulation Research of Space Articulated Deployable Mast[D]. Hangzhou:Institutes of Technology of Zhejiang, 2014:1-2. (in Chinese)

KIM K W, PARK Y. Solar array deployment analysis considering path-dependent behavior of a tape spring hinge[J]. Journal of Mechanical Science and Technology, 2015, 29(5):1921-1029.

蔡祈耀, 陈务军, 张大旭, 等. 空间薄壁CFRP豆荚杆悬臂屈曲分析及试验[J]. 上海交通大学学报, 2016, 50(1):145-151. CAI Q Y, CHEN W J, ZHANG D X, et al.. Buckling analysis and experiment of cantilever thin-walled lenticular CFRP space boom[J]. Journal of Shanghai of Jiaotong University, 2016, 50(1):145-151. (in Chinese)

马兴瑞, 于登云, 孙京, 等. 空间飞行器展开与驱动机构研究进展[J]. 宇航学报, 2006, 27(6):1123-1131. MA X R, YU D Y, SUN J, et al.. The researching evolvement of spacecraft deployment and driving mechanism[J]. Journal of Astronautics, 2006, 27(6):1123-1131. (in Chinese)

浏览量

846

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

碳纤维悬臂梁式振动检波器