| 战术弹道导弹再入段弹道仿真设计 |
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| 引用本文： | 汤阳春,娄寿春,赵辉. 战术弹道导弹再入段弹道仿真设计[J]. 弹箭与制导学报, 2006, 26(2): 98-99 |
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| 作者姓名： | 汤阳春 娄寿春 赵辉 |
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| 作者单位： | 空军工程大学导弹学院,陕西,三原,713800 |
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| 摘 要： | 在拦截TBM作战仿真系统中,需要模拟TBM再入段的弹道.文中在简化的大气模型下建立TBM的再入段方程,并采用龙格-库塔法来求解,通过仿真,可以看出模型符合仿真需要.
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| 关 键 词： | TBM 再入段 弹道仿真 龙格-库塔 |
| 收稿时间： | 2005-09-05 |
| 修稿时间： | 2005-09-05 |
Simulation Design for Reentry of the Trajectory of TBM |
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| TANG Yang-chun,LOU Shou-chun,ZHAO Hui. Simulation Design for Reentry of the Trajectory of TBM[J]. Journal of Projectiles Rockets Missiles and Guidance, 2006, 26(2): 98-99 |
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| Authors: | TANG Yang-chun LOU Shou-chun ZHAO Hui |
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| Affiliation: | Missile College of AFEU, Shaanxi Sanyuan 713800, China |
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| Abstract: | On the Anti TBM combat simulation system, it needs to simulate the reentry of the trajectory of TBM. The paper has brought out functions of the reentry trajectory of TBM in case of the predigest model of atmosphere and solved them by the Runge-Kutta method. It can be seen to be available for the simulation system through simulation result. |
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| Keywords: | TBM, reentry of the trajectory trajectory simulation Runge-Kutta |
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