| 一种应用于弹道导弹控制的朗伯特导引方法 |
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| 引用本文： | 高勇.一种应用于弹道导弹控制的朗伯特导引方法[J].海军航空工程学院学报,2012,27(4):385-389. |
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| 作者姓名： | 高勇 |
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| 作者单位： | 海军驻航天科技集团公司第一研究院军事代表室,北京 100076 |
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| 摘 要： | 介绍了一种用于与弹道目标会合的三自由度拦截弹仿真,其导引方法可以使拦截弹与弹道目标的位置和速度相匹配,在会合后能够跟随目标运动。该方法采用朗伯特导引,控制在主动段飞行的导弹,使它的弹道与弹道目标的弹道重合。在与弹道目标会合之前,预先设定了一个短暂的末修段,以使拦截弹的速度与弹道目标的速度相匹配。
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| 关 键 词： | 弹道导弹 导引律 朗伯特导引 待增速度 |
A Kind of Lambert Guidance Method Designed for Control of Ballistic Missile |
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| GAO Yong.A Kind of Lambert Guidance Method Designed for Control of Ballistic Missile[J].Journal of Naval Aeronautical Engineering Institute,2012,27(4):385-389. |
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| Authors: | GAO Yong |
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| Institution: | GAO Yong (Military Representatives Office of Navy in 1 st Academy of Aerospace Science and Technology Industry Group, Beijing 100076, China) |
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| Abstract: | A three-degree-of-freedom interceptor missile simulation designed to rendezvous with a ballistic target was presented. The guidance scheme was designed to match the position and velocity of a ballistic target so that the interceptor would follow the target after the rendezvous. The guidance routine used Lambert guidance to control the missile during the boost phase and put it on course to meet the ballistic target trajectory Before rendezvous with the ballistic target, a short fourth- age burn was scheduled to match the velocity of the ballistic target |
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| Keywords: | ballistic trajectory guidance Lambert guidance guidance velocity |
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