| 旋转导弹姿态稳定控制方法研究 |
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| 引用本文： | 楼朝飞,张锐,陆宙斯.旋转导弹姿态稳定控制方法研究[J].现代防御技术,2011,39(3). |
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| 作者姓名： | 楼朝飞 张锐 陆宙斯 |
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| 作者单位： | 北京电子工程总体研究所,北京,100854 |
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| 摘 要： | 旋转导弹往往采用初始静不稳定的结构形式使得在攻击目标时具有较大的过载能力,如何能够保证旋转导弹平稳地度过静不稳定段是导弹正常飞行的关键.采用姿态稳定控制方法对初始段进行控制,使导弹顺利度过静不稳定段,通过数学仿真及半实物仿真验证了该控制方法的有效性.基于正交试验设计的仿真试验表明,在各种气动干扰因素影响下,旋转导弹均能实现较高的姿态控制精度.
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| 关 键 词： | 姿态稳定控制 静不稳定 旋转导弹 |
The Attitude Stabilization Control Method for Spinning Missile |
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| LOU Chao-fei,ZHANG Rui,LU Zhou-si.The Attitude Stabilization Control Method for Spinning Missile[J].Modern Defence Technology,2011,39(3). |
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| Authors: | LOU Chao-fei ZHANG Rui LU Zhou-si |
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| Institution: | LOU Chao-fei,ZHANG Rui,LU Zhou-si(Beijing Inst.of Electronic System Engineering,Beijing 100854,China) |
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| Abstract: | Spinning missile generally adopts initial unsteady structure to make it endure much higher overload.It is necessary for a spinning missile to get through the unsteady period successfully.The attitude stabilization control method is designed for spinning missile.The design of attitude stabilization control method is given and math simulation is completed.The availability is validated by simulation data at different interference backgrounds. |
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| Keywords: | attitude stabilization control steady un-stability spinning missile |
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