基于蜂窝加肋板结构参数匹配抑制光学卫星随机响应

谭陆洋; 王栋; 孔林; 闫勇; 李林

doi:10.3788/OPE.20162402.0372

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基于蜂窝加肋板结构参数匹配抑制光学卫星随机响应

微纳技术与精密机械 | 更新时间：2020-08-13

- 基于蜂窝加肋板结构参数匹配抑制光学卫星随机响应
- Suppression of random vibration response of optical satellite by matching honeycomb stiffened plates' structural parameters
- 光学精密工程 2016年24卷第2期页码：372-380
- 作者机构：
  
  1. 中国科学院大学北京,中国,100049
  2. 中国科学院长春光学精密机械与物理研究所, 吉林长春 130033
- 作者简介：
- 基金信息：
  
  国家836高技术研究发展计划资助项目(No.2012AA121502)()
- DOI：10.3788/OPE.20162402.0372
  中图分类号： V416.21;V474.1
- 收稿日期：2015-05-21，
  
  修回日期：2015-06-05，
  
  纸质出版日期：2016-02-25
- 稿件说明：
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谭陆洋, 王栋, 孔林等. 基于蜂窝加肋板结构参数匹配抑制光学卫星随机响应[J]. 光学精密工程, 2016,24(2): 372-380

TAN Lu-yang, WANG Dong, KONG Lin etc. Suppression of random vibration response of optical satellite by matching honeycomb stiffened plates' structural parameters[J]. Editorial Office of Optics and Precision Engineering, 2016,24(2): 372-380
谭陆洋, 王栋, 孔林等. 基于蜂窝加肋板结构参数匹配抑制光学卫星随机响应[J]. 光学精密工程, 2016,24(2): 372-380 DOI： 10.3788/OPE.20162402.0372.

TAN Lu-yang, WANG Dong, KONG Lin etc. Suppression of random vibration response of optical satellite by matching honeycomb stiffened plates' structural parameters[J]. Editorial Office of Optics and Precision Engineering, 2016,24(2): 372-380 DOI： 10.3788/OPE.20162402.0372.

摘要

以结构参数的最优匹配为设计目标

提出了一种改善光学卫星振动环境的新思路。针对某光学卫星振动试验中出现的蜂窝顶板随机振动响应过大的问题

研究了加强肋在降低简支蜂窝板随机振动响应中的作用。分析了该光学卫星蜂窝板结构的特点

探讨了它的随机载荷以及在其激励下蜂窝板式结构的动力学响应。结合卫星自身结构上的需要

提出了一种通过添加特定截面H型加强肋的方法来降低蜂窝板的响应。利用有限元法对外形尺寸为1000 mm×1000 mm×30 mm的蜂窝板模型进行随机振动分析验证

结果显示:H型加强肋能显著降低蜂窝板的振动响应

有明显减振效果。最后

根据整星振动试验结果对卫星力学模型进行了修正

并利用该方法对修正后的模型进行动力学分析和优化

分析结果表明顶板响应降幅达到了40%

为系统可接受范围

证明了提出的方法很好地抑制了结构的随机振动响应。

Abstract

To implement the optimal matching of structure parameters

a new idea was proposed to improve the vibration environments of optical satellites. As the random response of a honeycomb panel was far beyond the normal range in a satellite vibration test

adding several enforced ribs on this panel was proposed to reduce the response. The function of the enforced rib in reducing the response of simply supported honeycomb panel was researched. The characteristics of honeycomb panel structure in the optical satellite were introduced

and the random excitation load of the optical satellite and dynamic response of the honeycomb panel under this load were also discussed. According to the entire satellite structure

a method to reduce the honeycomb response by adding H enforced ribs on the panel was proposed. In order to study the function of the enforced rib

the finite element method was used to verify the random vibration of the honeycomb panel model with a size of 1000 mm×1000 mm×30 mm. The analysis results show that the H enforced ribs reduce the response of the honeycomb panel obviously. Finally

the satellite finite element model was improved by the vibration test results and its dynamical analysis and optimization was performed. The analysis results show that the response has reduced to 40%

being an acceptable level

which verifies that the H enforced rib is a good choice to reduce the response of simply supported honeycomb panels on optical satellites.

关键词

Keywords

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