| 引用本文: | 袁天保,刘新建,申慧君,等.弹道导弹滚动飞行稳定仿真.[J].国防科技大学学报,2004,26(2):9-12.[点击复制] |
| YUAN Tianbao,LIU Xinjian,SHEN Huijun,et al.Stability Simulation of the Spinning Ballistic Missile[J].Journal of National University of Defense Technology,2004,26(2):9-12[点击复制] |
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| 弹道导弹滚动飞行稳定仿真 |
| 袁天保1, 刘新建1, 申慧君1, 秦子增1, 谷立祥2, 付维贤2 |
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(1.国防科技大学 航天与材料工程学院，湖南 长沙 410073;2.中国运载火箭总体设计部，北京 100076)
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| 摘要: |
| 弹道导弹在助推段需要滚动突防，减少强激光照射的驻留时间，可以有效地对抗激光反导，但姿态稳定的实现则有很大的不同。利用经典控制理论和多变量频域理论设计了导弹的自动驾驶仪，仿真结果表明，对静不稳定导弹的一级助推段可以实现低滚速下的稳定飞行。 |
| 关键词: 弹道导弹 助推段 滚动 突防 |
| DOI： |
| 投稿日期：2003-08-27 |
| 基金项目: |
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| Stability Simulation of the Spinning Ballistic Missile |
| YUAN Tianbao1, LIU Xinjian1, SHEN Huijun1, QIN Zizeng1, GU Lixiang2, FU Weixian2 |
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(1.College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha 410073, China;2.Institute of Chinese Launch Vehicle,Beijing 100076, China)
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| Abstract: |
| To survive the laser's attack, ballistic missiles can spin to reduce the dwell time of the beam at a particular point on the missile. The realzation of stability is different from before. We design the missile's autopilot by the method of classical control theory and MFD technology. The simulation result shows that the unsteady aerodynamic ballistic missile can fly stablly at the low spinning rate during the first boosting phase. |
| Keywords: ballistic missile boost phase spinning penetration |
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