| 末段修正火箭弹脉冲修正技术 |
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| 引用本文： | 葛贤坤,黄长强,韩统,赵辉.末段修正火箭弹脉冲修正技术[J].弹道学报,2006,18(4):29-32. |
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| 作者姓名： | 葛贤坤 黄长强 韩统 赵辉 |
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| 作者单位： | 空军工程大学,工程学院,西安,710038 |
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| 摘 要： | 提出了一种末段修正火箭弹的脉冲修正方案,建立了相应的弹道模型;对单个脉冲发动机的修正能力及修正时机进行了仿真研究;提出了末段多级修正的方法,并对多级修正进行了弹道数字仿真.结果表明,所提出的方案及修正方法能充分地利用单个脉冲发动机的修正能力,使多个脉冲发动机合理启动,可以大幅度提高火箭弹的命中精度.
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| 关 键 词： | 火箭弹 末段修正 脉冲控制力 弹道模型 微机械电子系统 |
| 文章编号： | 1004-499X(2006)04-0029-04 |
| 收稿时间： | 2005-12-01 |
| 修稿时间： | 2005年12月1日 |
Impulse Correction Technology for Terminal Correction Rocket |
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| GE Xian-kun,HUANG Chang-qiang,HAN Tong,ZHAO Hui.Impulse Correction Technology for Terminal Correction Rocket[J].Journal of Ballistics,2006,18(4):29-32. |
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| Authors: | GE Xian-kun HUANG Chang-qiang HAN Tong ZHAO Hui |
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| Abstract: | Impulse correction scheme of a terminal correction rocket was put torwara, ana the trajectory model was established. The correction power and correction time of single impulse jet were studied by simulation. Terminal multi-correction method was presented. The method was used in trajectory correction. The results show that this engine correction scheme has utilized the correcting capability of single engine. The multilevel impulse engine can be fired as a reasonable order. It can contribute a lot to the reduction of errors. |
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| Keywords: | rocket missile terminal correction impulse control power trajectory model micro electromechanical system |
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