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| 自适应现状制导律 | |
| 引用本文： | 夏辉,江涌. 自适应现状制导律[J]. 现代防御技术, 2003, 31(6): 28-32 |
| 作者姓名： | 夏辉 江涌 |
| 作者单位： | 中国航天科工集团公司,二院二部,北京,100854 |
| 摘 要： | 针对反弹道导弹的导弹武器的主动飞行段,提出了高精度自适应现状制导律。通过实时修正飞行程序,以消除导弹飞行过程中遇到的各种干扰的影响,保证命中精度,并对发动机推力偏差、风干扰影响下的导弹运动进行了数学仿真,仿真结果证实了自适应现状制导律是合理、可行的。 |
| 关 键 词： | 自适应现状制导 姿态修正 预测脱靶量 |
| 文章编号： | 1009-086X(2003)06-0028-05 |
| 修稿时间： | 2002-10-24 |
Adaptive actuality boost guidance law |
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| XIA Hui,JIANG Yong. Adaptive actuality boost guidance law[J]. Modern Defence Technology, 2003, 31(6): 28-32 | |
| Authors: | XIA Hui JIANG Yong |
| Abstract: | A new adaptive actuality guidance law is presented for the boost phase of anti-ballistic missile weapons.In order to ensure intercepting precision,this guidance law is used to correct the flight programming for washing away the influence of interference in flight process of missile.Computer simulation for the movement of interceptor under influence of wind and thrust divergence shows that the guidance law is reasonable and feasible. |
| Keywords: | Adaptive actuality boost guidance Attitude angle correcting Predictive miss distance |
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