| 大气层外拦截弹中段制导方法研究 |
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| 引用本文： | 刘世勇,吴瑞林,周伯昭.大气层外拦截弹中段制导方法研究[J].飞行力学,2004,22(1):64-67. |
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| 作者姓名： | 刘世勇 吴瑞林 周伯昭 |
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| 作者单位： | 国防科技大学,航天与材料工程学院,湖南,长沙,410073 |
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| 摘 要： | 针对大气层外拦截弹飞行中段采用固体燃料发动机，且关机后需要经过较长的无控滑行段才能进入末制导段的情况，提出一种基于拦截弹修正能力，且考虑无控滑行段拦截弹与目标引力差影响的中制导律。仿真表明，采用该制导律的拦截弹在发动机工作期间推力方向变化平稳，且可获得较高的制导精度。
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| 关 键 词： | 大气层外拦截弹 中段制导 设计 修正能力 |
| 文章编号： | 1002-0853(2004)01-0064-04 |
| 修稿时间： | 2003年2月21日 |
Midcourse Guidance Law for an Exoatmospheric Interceptor |
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| LIU Shi-yong,WU Rui-lin,ZHOU Bo-zhao.Midcourse Guidance Law for an Exoatmospheric Interceptor[J].Flight Dynamics,2004,22(1):64-67. |
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| Authors: | LIU Shi-yong WU Rui-lin ZHOU Bo-zhao |
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| Abstract: | A midcourse guidance law for an exoatmospheric interceptor with solid engine, which has a significant ballistic coast to the endgame after burnout, is put forward. The proposed guidance law for the commanded thrust vector orientation takes into account the different gravitational accelerations experienced by the interceptor and the target during the coast, and the diving ability of the interceptor. Simulations have shown that the orientation of the command thrust vector keeps to the stabilizing during the midcourse guidance and a high accuracy is also obtained. |
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| Keywords: | exoatmospheric interceptor midcourse guidance law ballistic missile defense |
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