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论文:2019,Vol:37,Issue(2):378-385 |
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引用本文： |
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陈尔康, 高长生, 荆武兴. 空间目标的轨迹和姿态数据生成[J]. 西北工业大学学报 |
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CHEN Erkang, GAO Changsheng, JING Wuxing. The Method of Trajectory and Attitude Data Generation for Space Target[J]. Northwestern polytechnical university |
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| 空间目标的轨迹和姿态数据生成 |
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| 陈尔康, 高长生, 荆武兴 |
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| 哈尔滨工业大学 航天学院, 黑龙江 哈尔滨 150001 |
| 摘要: |
| 针对空间目标的轨迹和姿态数据生成问题，对各类空间目标的特性进行了深入的分析，将其基准弹道分为4种类型并分别给出了设计方法，在此基础之上建立了分导弹道设计方法，该方法无需长时间的准备工作，大大简化了系统仿真的工作量。此外为模拟中段目标的微动特性建立了由微动特征量直接计算姿态数据的姿态数据生成方法，该方法无需进行积分计算，加快了计算速度。最后对以上方法进行了仿真验证。仿真结果表明，提出的方法能够在10 s内生成准确命中目标的四类基准弹道和分导弹道。此外，生成的姿态数据能够反映中段目标的微动特性，数据生成耗时短且无需事先准备工作，能够较好地满足系统仿真的要求。 |
| 关键词:
系统仿真
弹道导弹
发射诸元
微运动
轨迹和姿态
空间目标
数据生成
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| The Method of Trajectory and Attitude Data Generation for Space Target |
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| CHEN Erkang, GAO Changsheng, JING Wuxing |
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| School of Astronautics, Harbin Institute of Technology, Harbin 150001, China |
| Abstract: |
| To solve the problem of space targets' trajectory and attitude data generation in system simulation, the characteristics of various types of ballistic missiles and their midcourse targets are analyzed deeply. The baseline ballistic is divided into four types and design methods are given respectively, based on which multiple independently reentry vehicle (MIRV) ballistic design method is established. This method doesn't need preparations and simplifies the system simulation. In addition, an attitude data generation method according to micro-motion characteristic quantity is proposed in order to simulate midcourse target's micro-motion. This method doesn't require numerical integral and speeds up the computation. Simulation results show that four types of baseline trajectory and MIRV trajectory that can accurately hit the target are generated in ten seconds. In addition, the attitude data can reflect the micro-motion characteristic, and the time for data generation is short. This method can meet the requirements of system simulation. |
| Key words:
system simulation
ballisitc missile
firing data
micro-motion
trajectory and attitude
space target
data generation
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| 收稿日期: 2018-05-10
修回日期:
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| DOI: 10.1051/jnwpu/20193720378 |
| 通讯作者:
Email： |
| 作者简介: 陈尔康(1991-),哈尔滨工业大学博士研究生,主要从事飞行器动力学与控制研究。
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