| 空间动能拦截末段导引法研究及其仿真 |
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| 引用本文： | 张彦,冯书兴.空间动能拦截末段导引法研究及其仿真[J].系统仿真学报,2007,19(9):2124-2126. |
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| 作者姓名： | 张彦 冯书兴 |
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| 作者单位： | 1. 装备指挥技术学院,研究生部,北京,101416;北京航天飞行控制中心,北京,100094
2. 装备指挥技术学院,试验指挥系,北京,101416 |
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| 基金项目： | 国家高技术研究发展计划(863计划) |
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| 摘 要： | 针对空间动能拦截的特点,利用了比例导引法控制视线转率的优点,兼顾考虑了控制脱靶量以提高动能拦截精度,设计了空间动能拦截末段导引法。该导引方法基于目前发动机一般工作于脉冲条件下的实际情况,能有效地控制视线转率和脱靶量,并能够保持拦截器飞行弹道的稳定性。仿真结果验证了该方法的有效性。
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| 关 键 词： | 空间动能拦截 末段导引 脱靶量 比例导引法 |
| 文章编号： | 1004-73IX（2007）09-2124-03 |
| 收稿时间： | 2006-03-31 |
| 修稿时间： | 2007-02-27 |
Terminal Guidance Method Study and Simulation in Space Kinetic Interception |
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| ZHANG Yan,FENG Shu-xing.Terminal Guidance Method Study and Simulation in Space Kinetic Interception[J].Journal of System Simulation,2007,19(9):2124-2126. |
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| Authors: | ZHANG Yan FENG Shu-xing |
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| Abstract: | Based on the characteristics of space kinetic energy interception and advantages of proportional guidance, taking controlling the undershooting rate into account to increase precision, a terminal guidance method was designed to space kinetic energy interception problem. To the fact that the engines are almost impulse engines at present, this method can restrain the turn rate and undershooting rate effectively. Besides, it can also keep the stability of the trajectory. Simulation results indicate the validity of this method. |
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| Keywords: | space kinetic interception terminal guidance undershooting rate proportional guidance |
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