宇航计测技术 ›› 2016, Vol. 36 ›› Issue (4): 11-14.doi: 10.12060/j.issn.1000-7202.2016.04.03

• 论文 • 上一篇    下一篇

某飞行器上红外成像装置减振结构设计

魏小林1；常虹1；林森1   

  1. 1、北京航天计量测试技术研究所，北京 100076
  • 出版日期:2016-08-15 发布日期:2016-08-15
  • 作者简介:魏小林（1984-），男，主要研究方向：飞行器结构设计。

Damping Design for the Infrared Imaging Device on Aircrafts

WEI Xiao-lin1；CHANG Hong1；LIN Sen1   

  1. 1、Beijing Aerospace Institute for Metrology and Measurement Technology，Beijing 100076
  • Online:2016-08-15 Published:2016-08-15

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摘要： 某飞行器上红外成像装置在工作过程中要承受强烈的振动和冲击等动载荷环境，为避免动态响应过大会对其内部红外探测器等精密组件造成不可逆的损坏，须对其进行阻尼减振设计。减振器作为飞行器上红外成像设备的重要部件之一，其作用是衰减外界环境传递到产品的振动，从而保证产品性能。通过介绍一种基于Ansys模态分析优化后的成像光学减振结构设计，有效改善了设备的工作环境，试验表明红外成像装置配备减振器的减振效率大于70%。

关键词: 红外成像装置, 阻尼, 减振

Abstract: The infrared imaging device on an aircraft is subjected to severe shock, impact and other dynamic loads during its working process. In order to avoid the irreversible damage of precision components caused by the big dynamic response,the device should install the damping system. An optimized vibration absorbing structure of the imaging optical system based on Finite Element Method was introduced. Experiment results show that the damping efficiency of the infrared imaging device with the damping design is over 70%.The working environment of the device is improved effectively.

Key words: Infrared imaging device, Damping, Reduce vibration

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