| 大气层外动能拦截器末制导分析 |
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| 引用本文： | 程凤舟,万自明,陈士橹.大气层外动能拦截器末制导分析[J].飞行力学,2002,20(1):38-41. |
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| 作者姓名： | 程凤舟 万自明 陈士橹 |
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| 作者单位： | 西北工业大学,航天工程学院,陕西,西安,710072 |
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| 摘 要： | 以大气层外动能拦截器拦截战术导弹弹头为研究目的，建立了拦截器的六自由度运动学，动力模型，以及拦截器的轨控和资控发动机推力特性和控制模型。提出了修正比例导引律的实现方案，进行了末制导过程的仿真，并分析了影响脱靶量的一些因素。仿真结果表明，在轨控和姿控发动机的作用下，拦截器可以直接命中目标。
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| 关 键 词： | 动能拦截器 反战术弹道导弹 末制导分析 大气层外状态 |
| 文章编号： | 1002-0853(2002)01-0038-04 |
| 修稿时间： | 2001年10月25 |
Terminal Guidance Analysis of Extra-Atmospheric Kinetic-Kill Vehicle |
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| CHENG Feng zhou,WAN Zi ming,CHEN Shi lu.Terminal Guidance Analysis of Extra-Atmospheric Kinetic-Kill Vehicle[J].Flight Dynamics,2002,20(1):38-41. |
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| Authors: | CHENG Feng zhou WAN Zi ming CHEN Shi lu |
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| Abstract: | This paper studies that the extra atmospheric kinetic kill vehicle intercepts the tactical missile's warhead. The six degree of freedom motion and dynamics models of the interceptor are established.The thrust performance and control model with trajectory control and altitude control, and the concept of appended proportional navigation law are studied. The simulation of the terminal guidance procedure is carried out, and some factors which affect the miss distance quantity are analyzed. Simulation results show that the interceptor could hit the target directly by means of the trajectory control system and the altitude control system. |
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| Keywords: | kinetic kill vehicle tactical missile terminal guidance |
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