Passive jitter isolation for reaction wheel of satellites

被引:0
|
作者
Oh, Choong-Seok [1 ]
Lee, Wonsuk [1 ]
Bang, Hyochoong [1 ]
机构
[1] Korea Adv Inst Sci & Technol, Div Aerosp Engn, Taejon 305701, South Korea
来源
2006 SICE-ICASE INTERNATIONAL JOINT CONFERENCE, VOLS 1-13 | 2006年
关键词
vibration isolation; jitter; satellite; reaction wheel; passive isolation;
D O I
暂无
中图分类号
TP [自动化技术、计算机技术];
学科分类号
0812 ;
摘要
Passive jitter isolation for reaction wheel of satellites is studied. The principal idea of vibration isolation is to filter out the response of the system over the corner frequency. The isolation objectives are to transmit the attitude control torque within the bandwidth of the attitude control system and to filter all the high frequency components coming from vibration equipment above the bandwidth. However, when a reaction wheels or control momentum gyros control spacecraft attitude, vibration inevitably occurs and degrades the performance of sensitive devices. Therefore, vibration should be controlled or isolated for missions such as Earth observing, broadcasting and telecommunication between antenna and ground stations. For space applications, technicians designing controller have to consider a periodic vibration and disturbance to ensure system performance and robustness completing various missions. In this paper, a passive reaction wheel jitter isolation system is studied. This paper shows the simulation and experimental results of a passive reaction wheel jitter isolation in satellite.
引用
收藏
页码:2025 / +
页数:2
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