Abstract
A new vibration control strategy is presented to realize rapid attitude maneuvers and stabilization for a spacecraft with flexible appendages. This control strategy combines the command input shaping and the technique of passive vibration isolation for vibration sources. The analytical dynamic model of the spacecraft with control moment gyroscopes, passive vibration isolation system, and flexible appendages is constructed. Based on this analytical dynamic model and the proportion differentiation (PD) attitude control law, the modal parameters of the closed-loop system are calculated, and multiple mode input shapers are designed. Several simulations and comparative studies have shown that the combined active and passive vibration control strategy can not only improve the spacecraft motion performance, but also make the image quality of the optical payload better.
| Original language | English |
|---|---|
| Article number | 7858695 |
| Pages (from-to) | 1308-1320 |
| Number of pages | 13 |
| Journal | IEEE Transactions on Aerospace and Electronic Systems |
| Volume | 53 |
| Issue number | 3 |
| DOIs | |
| Publication status | Published - Jun 2017 |
Keywords
- Attitude stabilization control
- control moment gyros
- input shaping
- vibration control