用于光学遥感器耐受卫星平台微振动环境地面测试的六自由度平台

顾营迎; 霍琦; 李昂; 李大为; 徐振邦; 李义; 吴清文

doi:10.3788/OPE.20162409.2200

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用于光学遥感器耐受卫星平台微振动环境地面测试的六自由度平台

微纳技术与精密机械 | 更新时间：2020-07-07

- 用于光学遥感器耐受卫星平台微振动环境地面测试的六自由度平台
- Six DOF platform applied in ground test of optical remote sensor alleviation margin in satellite micro-vibration environment
- 光学精密工程 2016年24卷第9期页码：2200-2207
- 作者机构：
  
  中国科学院长春光学精密机械与物理研究所机器人系统创新研究室, 吉林长春 130033
- 作者简介：
  
  顾营迎(1984-), 男, 天津人, 博士, 副研究员, 2013年于中国科学院大学获得博士学位, 主要从事机器人视觉感知与控制方面的研究。E-mail:18686681605@163.comE-mail:18686681605@163.com
  [ "霍琦(1988-), 男, 山东菏泽人, 硕士, 实习研究员, 2011年、2014年于哈尔滨工程大学分别获得学士、硕士学位, 主要从事自动控制、电子学设计方面的研究。E-mail:514590249@qq.com" ]
- 基金信息：
  
  国家自然科学基金资助项目(11302222)
- DOI：10.3788/OPE.20162409.2200
  中图分类号： V423.6;V416.21
- 收稿日期：2015-12-11，
  
  录用日期：2016-1-20，
  
  纸质出版日期：2016-06
- 稿件说明：
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顾营迎, 霍琦, 李昂, 等. 用于光学遥感器耐受卫星平台微振动环境地面测试的六自由度平台[J]. 光学精密工程, 2016,24(9):2200-2207.

Ying-ying GU, Qi HUO, Ang LI, et al. Six DOF platform applied in ground test of optical remote sensor alleviation margin in satellite micro-vibration environment[J]. Optics and precision engineering, 2016, 24(9): 2200-2207.
顾营迎, 霍琦, 李昂, 等. 用于光学遥感器耐受卫星平台微振动环境地面测试的六自由度平台[J]. 光学精密工程, 2016,24(9):2200-2207. DOI： 10.3788/OPE.20162409.2200.

Ying-ying GU, Qi HUO, Ang LI, et al. Six DOF platform applied in ground test of optical remote sensor alleviation margin in satellite micro-vibration environment[J]. Optics and precision engineering, 2016, 24(9): 2200-2207. DOI： 10.3788/OPE.20162409.2200.

摘要

考虑空间卫星平台微振动环境对高分辨率空间光学遥感器成像质量的制约，提出了在地面测试光学遥感器耐受空间微振动环境裕度的六自由度激振平台的设计方案。建立了平台的运动学与动力学模型，推导出促动器音圈电机的传递函数并建立了Simulink模型。基于设计的模型研制了六自由度平台。对振动平台样机进行了振动加速度控制精度的验证实验，实验以典型的卫星平台微振动频率点为测试输入。实验结果表明平台振动频率为7~40 Hz时，其加速度输出相对误差可控制在7%以内。该平台借鉴了Stewart平台的并联构型，其结构简单、刚度大，振源输出精确可控，满足地面试验应用要求。

Abstract

As the micro-vibration of a satellite platform restricts the imaging quality of a high-resolution space optical remote sensor

this paper designs a six DOF(Degree of Freedom) platform for the ground test of optical remote sensor alleviation margin in satellite micro-vibration environment. The kinematics and dynamics models of the platform were constructed

and the transfer function

Simulink model of a voice coil actuators were derived. Based on the models

the platform with six DOFs was manufactured. A confirmatory experiment on the vibration acceleration control accuracy of the platform was carried out

in which the micro-vibration frequency of the typical satellite was taken as the input signal. The results show that the relative error of output acceleration has been controlled in 7% in frequencies from 7 Hz to 40 Hz. The platform takes the parallel construct of the stewart model

it has advantages in simpler structure

bigger stiffness and a controllable vibration source

and obtained results meet the requirements of the ground test applications.

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Keywords

references

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