摘要
In order to solve the problem of rapid turning of missile vertical launch, the thrust vector control of jet vane is designed in this paper. By applying the force analysis to the jet vane, the mathematical model of the missile's pitch motion in the vertical plane is established. At the same time the jet vane controller is designed, which introducing the missile's pitch angle position control and rate control. The simulation results show that the jet vane controller with the PID control rule can make the missile fast turn within one second. The model of jet vane thrust vector control can effectively provide sufficient control torque for a missile's quick turn.
| 源语言 | 英语 |
|---|---|
| 页 | 837-842 |
| 页数 | 6 |
| DOI | |
| 出版状态 | 已出版 - 2013 |
| 活动 | 2013 2nd International Conference on Measurement, Information and Control, ICMIC 2013 - Harbin, 中国 期限: 16 8月 2013 → 18 8月 2013 |
会议
| 会议 | 2013 2nd International Conference on Measurement, Information and Control, ICMIC 2013 |
|---|---|
| 国家/地区 | 中国 |
| 市 | Harbin |
| 时期 | 16/08/13 → 18/08/13 |
指纹
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Liu, F., & Wang, L. (2013). Research on the thrust vector control via jet vane in rapid turning of vertical launch. 837-842. 论文发表于 2013 2nd International Conference on Measurement, Information and Control, ICMIC 2013, Harbin, 中国. https://doi.org/10.1109/MIC.2013.6758092