Abstract
The attitude control for large flexible spacecrafts is a key issue in space technology. Satellites with large flexible solar panels are taken as practical background. A physical simulation system for flexible satellite is used as an experiment test-bed. Vibration suppression control with flexible vibration acceleration feedback is promoted. A small accelerometer is placed at the end of the flexible penal, the measurement model of this accelerometer is established and an adaptive filter is designed for its data procession. Feedback control using the vibration information from the acceleration signal is designed. Large angle maneuver experiment is carried out. The centre body maneuvers about 25° smoothly and the precision of the attitude after maneuver is within 0.01°. The acceleration at the end point of the flexible panel during the experiment is within 0.15 m/s2, and the altitude of the first mode is 0.015 m/s2. Compared with classical PD control, physical simulation experiments verify that the control scheme with vibration information feedback can suppress flexible vibration more effectively. Only a small accelerometer is placed on the flexible panel, the control system is simple and the control scheme can be carried out in real time system.
| Original language | English |
|---|---|
| Pages (from-to) | 50-54 |
| Number of pages | 5 |
| Journal | Zhendong Ceshi Yu Zhenduan/Journal of Vibration, Measurement and Diagnosis |
| Volume | 28 |
| Issue number | 1 |
| State | Published - Mar 2008 |
Keywords
- Flexible satellite
- Physical simulation experiment
- Vibration feedback control
- Vibration suppression