某型号卫星控制力矩陀螺隔振装置设计和试验技术研究

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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.

Key words： Optical remote sensing satellite micro-vibration misalignment design.

Received: 12 July 2022 Published: 15 September 2023

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	Articles by authors
	SUN Xiaochen
	GUO Tong
	LI Xiaoli
	YAO Xiaosong
	YANG Ruochen

Cite this article:

SUN Xiaochen,GUO Tong,LI Xiaoli, et al. Design and test technology of a certain satellite control moment gyro vibration isolation device[J]. JOURNAL OF VIBRATION AND SHOCK, 2023, 42(17): 135-143.

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http://jvs.sjtu.edu.cn/EN/ OR http://jvs.sjtu.edu.cn/EN/Y2023/V42/I17/135

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