基于商用现货的高分辨卫星微振动抑制系统设计

doi:10.3969/j.issn.1004-132X.2020.20.001

摘要/Abstract

摘要： 提出了通过合理选取和改进商用现货（COTS）的振动参数对振动部件安装位置进行优化的方法，以解决带有高分辨率光学载荷的小卫星微振动抑制问题。与其他隔振系统设计方法不同，所提方法不需对振动机理建模，而是直接通过振动部件微振动特性分析，选取合适的COTS隔振产品并对参数进行微调；利用Newmark法对蜂窝夹层结构进行动力学响应分析，得到了振动部件的合理安装位置，取得了较好的隔振效果。仿真、振动实验和飞行数据表明,振动部件在敏感频段的微振动抑制率达到90%，整星地面测量微振动引起的次镜角位移不超过0.04″，卫星在轨微振动环境能够满足相机使用要求。所提出的微振动抑制系统设计方法为后续工程实践提供了参考。

关键词: 光学小卫星, 微振动抑制, 动力学分析, 商用现货

Abstract: In order to solve the problems of micro-vibration suppression of small satellites with high-resolution optical loads，a system design method was proposed herein by modifying the parameters of COTS and optimizing the installation of the vibration components. Different from other methods based on the knowledges of vibration mechanism, the micro vibration characteristics of the vibration components and tuning the parameters were directly analyzed by the proposed method, and a reasonable location of the vibration components was obtained by analyzing the dynamics response of the honeycomb sandwich structure using Newmark method. The effectiveness of the proposed method was verified by simulations and ground tests. Results show that the micro-vibration of the vibrating components is suppressed by 90% in the sensitive frequency bands, and the secondary mirror displacements caused by the micro-vibrations of the whole-star ground measurement do not exceed 0.04″. Orbital experiments show that the satellite in-orbit micro-vibration environment meets the requirements of the camera. Thus the design method of the suppression system sets an example for other engineering practices in the future.

Key words: optical satellite, micro-vibration suppression, dynamics analysis, commercial off-the-shelf(COTS)

中图分类号:

V474.2

郭金生1;王峰1;岳程斐2. 基于商用现货的高分辨卫星微振动抑制系统设计[J]. 中国机械工程, DOI: 10.3969/j.issn.1004-132X.2020.20.001.

GUO Jinsheng1;WANG Feng1;YUE Chengfei2. Design of High-resolution Satellite Micro-vibration Suppression System Based on COTS[J]. China Mechanical Engineering, DOI: 10.3969/j.issn.1004-132X.2020.20.001.

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