| Optimum PN Guidance Law for Maneuvering Target |
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| 作者姓名： | 孙宝彩 祁载康 |
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| 作者单位： | School of Astronautics Science and Technology, Beijing Institute of Technology, Beijing 100081, China |
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| 摘 要： |
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| 关 键 词： | 控制 导航技术 飞机 机动性能 |
| 文章编号： | 1673-002X（2007）02-0121-04 |
| 修稿时间： | 2007-08-28 |
Optimum PN Guidance Law for Maneuvering Target |
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| SUN Bao-cai,QI Zai-kang.Optimum PN Guidance Law for Maneuvering Target[J].Journal of China Ordnance,2007,3(2):121-124. |
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| Authors: | SUN Bao-cai QI Zai-kang |
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| Affiliation: | School of Astronautics Science and Technology, Beijing Institute of Technology, Beijing 100081, China |
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| Abstract: | An optimum PN guidance law for maneuvering target is developed using optimal control theory. By estimating the target position and setting the cost function, the guidance law can be deduced even without knowing the missile lateral acceleration. Since the quadratic cost function can make a compromise between the miss distance andthe control constraint, the optimum guidance law obtained is more general. Also, introduced line of sight rate as the input, a practical form of this guidance law is derived. The simulation results show the effectiveness of the guidance laws. |
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| Keywords: | control and navigation technology of aerocraft optimum PN guidance law target maneuver line of sight (LOS) Maneuvering Target Guidance Law simulation results show effectiveness guidance laws practical form derived introduced line rate input general quadratic make miss distance control constraint |
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