Abstract
Large angle attitude control law is investigated for agile turn of an advanced air-to-air missile that has high off-boresight or over the shoulder capability. The attitude dynamics and kinematics of the missile are divided into fast subsystem and slow subsystem by time scale separation. The fast subsystem control law is designed by dynamic inversion. The slow subsystem control law is designed by Lyapunov method. The robustness and precision of the system are analyzed. The simulation shows that the effect of the moment disturbance is highly reduced with the control law proposed here. The simulation result of the agile turn of the over the shoulder mission realized by attitude control method was also given as the application of the control law proposed here.
| Original language | English |
|---|---|
| Pages (from-to) | 295-299 |
| Number of pages | 5 |
| Journal | Yuhang Xuebao/Journal of Astronautics |
| Volume | 25 |
| Issue number | 3 |
| State | Published - May 2004 |
| Externally published | Yes |
Keywords
- Air-to-air missile
- Large angle attitude control
- Thrust vector control