Abstract
In order to realize high accuracy and stability requirements for satellite attitude control, a vibration isolation platform (VIP) is employed to interface the cluster of control moment gyros (CMGs) with the satellite bus. First, by employing the reduced satellite dynamics model, the transfer function matrix of VIP is obtained. Then, the influence of the VIP on the attitude control system is discussed. A parameter design scheme for VIP is put forward according to the above analysis. The parameters selected by using this scheme can not only satisfy the requirement for vibration isolation but also guarantee that the closed-loop attitude control system remains sufficiently stable. Finally, the rationality of this parameter selection scheme and the application of the VIP for CMGs are proved by numerical simulation.
| Original language | English |
|---|---|
| Pages (from-to) | 657-664 |
| Number of pages | 8 |
| Journal | Yuhang Xuebao/Journal of Astronautics |
| Volume | 34 |
| Issue number | 5 |
| DOIs | |
| Publication status | Published - May 2013 |
Keywords
- Attitude control
- Control moment gyro
- Micro-vibration
- Ultra quiet platform