| 弹道导弹自由段解算的等高约束解析解 |
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| 引用本文： | 郑伟,汤国建.弹道导弹自由段解算的等高约束解析解[J].宇航学报,2007,28(2):269-272. |
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| 作者姓名： | 郑伟 汤国建 |
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| 作者单位： | 国防科技大学,航天与材料工程学院,长沙,410073 |
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| 摘 要： | 在状态空间摄动法的基础上，提出了求解终端为高度约束的弹道导弹自由段轨迹的方法，导出考虑J2项摄动的运动参数等高偏差解析解，并提出利用已有的等地心距偏差公式近似的思路。和其它解析方法相比，所提方法计算精度高，无须迭代。算例证明：解析方法的计算精度在50米以内，可以满足诸元和制导计算的要求。
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| 关 键 词： | 等高约束 解析解 自由段 弹道导弹 |
| 文章编号： | 1000-1328（2007）02-0269-04 |
| 修稿时间： | 2006-05-262006-09-30 |
Contour Restricted Analytical Solution for Free Flight Trajectory of Ballistic Missile |
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| ZHENG Wei,TANG Guo-jian.Contour Restricted Analytical Solution for Free Flight Trajectory of Ballistic Missile[J].Journal of Astronautics,2007,28(2):269-272. |
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| Authors: | ZHENG Wei TANG Guo-jian |
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| Institution: | College of Aerospace and Material Engineering, National University of Defense Technology, Changsha 410073, China |
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| Abstract: | Based on state space perturbance method, a new model is established to solve free flight trajectory of ballistic missile with contour restriction, and analytical solution was deduced considering perturbantion due to nonspherical gravitational potential. Then the approach was put forward to approximate contour restricted trajectory by formula with equip distance restriction. Compared with other analytical methods, this method can get more accurate result and consume less time. Experiment results indicate that the method can keep the end point warp within 50 meters and satisfy the requirement of firing data and guidance. |
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| Keywords: | Contour restriction Analytical solution Free flight trajectory Ballistic missile |
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