针对某型号卫星控制力矩陀螺（CMG）在轨工作产生的微振动对星载光学遥感载荷成像产生扰动的问题，文章对CMG扰振特性及卫星基频分析，建立了CMG隔振系统模型，基于CMG扰振特征频率完成了系统错频及隔振装置参数化优化设计，并通过地面单机级及整星级微振动试验对有限元建模结果进行验证。试验结果表明，在主要扰振方向上，主要扰振频点处最佳可实现97%隔振效果，系统的固有频率在仿真与敲击实验对比中误差低于3Hz，对其他型号卫星的微振动隔振装置优化设计具有参考价值。
Abstract
The micro-vibration caused by the control moment gyros (CMG) would result in lowering the image quality of the optical sensing equipment on the satellite. Therefore, it’s necessary to design a device to resist micro-vibration. In this paper, the frequency character of CMG and the natural frequency of satellite were analyzed. Also, the FEA model was built to conduct parameterized design which involves modal control method. The vibration test of the whole isolation system was conducted under both unit-test and satellite-level test conditions to verify the pre-design. In the main vibration direction, the device could provide a maximized decrease in acceleration amplitude up to 97%, and there was only a deviation of 3Hz between the tested natural frequency and the simulated one. Therefore, the optimized isolation device may contribute to the other satellites in the future.
关键词
光学遥感卫星 /
微振动 /
错频设计
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Key words
Optical remote sensing satellite /
micro-vibration /
misalignment design.
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