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论文:2014,Vol:32,Issue(4):651-657 |
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引用本文： |
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梅春波, 秦永元, 游金川. 全导式多弹头分导子系统初始对准算法研究[J]. 西北工业大学 |
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Mei Chunbo, Qin Yongyuan, You Jinchuan. In-Flight Alignment for Guided Warheads of Genuine MIRV System[J]. Northwestern polytechnical university |
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| 全导式多弹头分导子系统初始对准算法研究 |
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| 梅春波, 秦永元, 游金川 |
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| 西北工业大学 自动化学院, 陕西 西安 710072 |
| 摘要: |
| 提出了一种适用于全导式多弹头分导系统的初始对准算法。以MEMS IMU/GPS组合作为子弹头制导系统,对准算法分3部分,由陀螺仪积分描述弹体系在惯性空间姿态变化;由GPS位置信息描述导航系在惯性空间姿态变化;采用2级减速方案及Quest算法确定载体系及导航系在对准开始时刻的相对姿态。分析了器件误差、弹体俯仰角初值、弹体机动方式及强度对对准结果的影响。Monte Carlo仿真表明,采用10°/h陀螺和0.1 m/s GPS组合时,在弹头2级减速机动下,20 s内水平误差小于0.12°(1σ),方位误差小于0.4°(1σ),完全满足分导系统初始对准精度要求,为工程应用提供了有益参考。 |
| 关键词:
空中对准
全导式多弹头分导系统
MEMS IMU/GPS
Quest
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| In-Flight Alignment for Guided Warheads of Genuine MIRV System |
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| Mei Chunbo, Qin Yongyuan, You Jinchuan |
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| Department of Automatic Control, Northwestern Polytechnical University, Xi'an 710072, China |
| Abstract: |
| An effective in-flight alignment algorithm for the guided warheads accompanied with MEMS IMU/GPS integrated system, suitable for genuine multiple reentry vehicle (MIRV), is proposed. The attitude quaternion is decomposed into three quaternions:the first one describing the warheads' inertial angular motion is updated by in-tegrating gyros measurement; the second one reflecting the warheads' position change is analytically solved with GPS postion measurement;the last one is the warheads' attitude at the time of the alignment start-up, and solved with Quest algorithm. Influence of sensors' errors, initial pitch angle, and the warhead motion on the alignment precision is analyzed. Monte Carlo simulation results and their analysis indicate preliminarily that for 10°/h gyro and 0?1 m/s GPS, under two-stage deceleration motion, the level error is less than 0?12° (1σ) and the yaw error is less than 0?4° (1σ) within 20 seconds;this can satisfy the requirement. |
| Key words:
in-flight alignment
genuine multiple reentry vehicle
MEMS IMU /GPS
Quest
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| 收稿日期: 2013-11-04
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 梅春波(1985-),西北工业大学博士研究生,主要从事惯性导航与组合导航研究。
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参考文献: |
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