Design of vibration isolator for optical payload on orbit

YANG Jian-feng; XU Zhen-bang; LIU Hong-wei; LI Yi; WU Qing-wen

doi:10.3788/OPE.20142212.3294

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Design of vibration isolator for optical payload on orbit

更新时间：2020-08-13

- Design of vibration isolator for optical payload on orbit
- Optics and Precision Engineering Vol. 22, Issue 12, Pages: 3294-3302(2014)
- 作者机构：
  
  1. 中国科学院长春光学精密机械与物理研究所,吉林长春,中国,130033
  2. 中国科学院大学北京,中国,100049
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20142212.3294
  CLC： V443
- Received：19 December 2013，
  
  Revised：27 January 2014，
  
  Published：25 December 2014
- 稿件说明：
移动端阅览
杨剑锋, 徐振邦, 刘宏伟等. 光学有效载荷在轨隔振器的设计[J]. 光学精密工程, 2014,22(12): 3294-3302

YANG Jian-feng, XU Zhen-bang, LIU Hong-wei etc. Design of vibration isolator for optical payload on orbit[J]. Editorial Office of Optics and Precision Engineering, 2014,22(12): 3294-3302
杨剑锋, 徐振邦, 刘宏伟等. 光学有效载荷在轨隔振器的设计[J]. 光学精密工程, 2014,22(12): 3294-3302 DOI： 10.3788/OPE.20142212.3294.

YANG Jian-feng, XU Zhen-bang, LIU Hong-wei etc. Design of vibration isolator for optical payload on orbit[J]. Editorial Office of Optics and Precision Engineering, 2014,22(12): 3294-3302 DOI： 10.3788/OPE.20142212.3294.

摘要

为了抑制空间光学载荷的振动

针对大口径、高分辨的光学遥感器设计了一种隔振器

并研究了隔振器的主要结构参数和布置方式.首先

使用有限单元法分析了隔振器主要参数与刚度特性之间的关系.然后

利用BP网络预测隔振器的三向刚度

搜寻了符合条件的隔振器的结构参数.结合光学载荷的一般结构形式

提出一种对称辐射式布置方式

建立了相应的理论模型

并进行了仿真研究.最后

设计、加工出了一套隔振系统原理样机

并对其静态性能及隔振性能进行了测试实验.实验结果显示:隔振系统的基频在5.31 Hz左右;对高于25Hz的振动

衰减可以达到20 dB以上;仿真和实验结果之差在8%以内.得到的结果表明

设计的隔振器可以有效降低空间飞行器传递给光学载荷的振动.

Abstract

A novel compact vibration isolator was designed and constructed to attenuate the vibration of space optical payload for a optical remote sensor with a larger aperture and high resolution. The main structural parameters and arrangement forms of the isolator were researched. Firstly

the finite element method was used to analyze the relationship between main structural parameters and three-dimensional stiffness properties of the isolator. Then

the BP network was taken to predict the three-dimensional stiffness of the isolator and to search the structural parameters that accords with conditions of the isolator. A symmetric radial arrangement form of isolator was presented

along with the theoretical model and FEA simulation by combining the general structure of optical payload. Finally

a prototype of the vibration isolator was fabricated and experimental studies were carried out. Experimental results indicate that the natural frequency of the isolator system is approximately 5.31 Hz and the vibration attenuation effect is more than 20 dB when the vibration frequency is higher than 25 Hz. The maximum error of FEA simulation is less than 8% compared with the real test. It is shown that this vibration isolator can attenuate the jitter induced by spacecrafts effectively.

关键词

Keywords

references

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