| 引用本文: | 李湘平,鲁军勇,冯军红,等.电磁发射弹丸飞行弹道仿真.[J].国防科技大学学报,2019,41(4):25-32.[点击复制] |
| LI Xiangping,LU Junyong,FENG Junhong,et al.Simulation of flight ballistic of electromagnetic launch projectile[J].Journal of National University of Defense Technology,2019,41(4):25-32[点击复制] |
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| 电磁发射弹丸飞行弹道仿真 |
| 李湘平, 鲁军勇, 冯军红, 李开, 杜佩佩 |
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(海军工程大学 舰船综合电力技术国防科技重点实验室， 湖北 武汉 430033)
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| 摘要: |
| 针对电磁发射弹丸飞行弹道进行仿真研究，在建立刚体六自由度飞行弹道模型的基础上，采用时频分析和涡流分析方法，建立电磁-动力学耦合模型分析弹丸出膛时由于膛内振动带来的炮口扰动，采用动网格技术建立电磁-气动耦合模型分析弹托分离产生的气动扰动，从而得到了电磁发射弹丸的飞行弹道模型。以得克萨斯大学先进技术研究所设计的IAT-HVP为例，仿真分析了弹丸以1117 m/s初速、0°射角出膛时弹丸出口扰动对弹体速度和气动特性的影响，并得到其飞行200 m的弹道曲线。仿真结果表明，受电磁发射一体化弹丸出口扰动的影响，弹体落点相比理想弹道产生了24%的偏差，其中炮口扰动引起的偏差最大，其次是弹托分离。 |
| 关键词: 电磁发射弹丸 六自由度方程 飞行弹道 炮口扰动 弹托分离 |
| DOI：10.11887/j.cn.201904004 |
| 投稿日期：2018-04-27 |
| 基金项目:国家自然科学基金资助项目（51877214,51607187,51522706） |
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| Simulation of flight ballistic of electromagnetic launch projectile |
| LI Xiangping, LU Junyong, FENG Junhong, LI Kai, DU Peipei |
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(National Key Laboratory of Science and Technology on Vessel Integrated Power System, Naval University of Engineering, Wuhan 430033, China)
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| Abstract: |
| The flight ballistic of the EML (electromagnetic launch) projectile was simulated. Based on the establishment of a rigid body six degree of freedom flight external ballistic model, the time-frequency analysis and eddy current analysis method were adopted to establish the EM dynamic coupling model for the analysis of muzzle disturbance caused by the interior vibration, and the dynamic grid technology was used to establish the EM-aerodynamic coupling model for the analysis of aerodynamic disturbance brought by sabot discard. Thereby, the flight trajectory model of EML projectile was obtained. Taking the IAT-HVP designed by the advanced technology research institute of University of Texas as an example, the influence of the muzzle disturbance on the velocity and aerodynamic characteristics of the projectile was simulated and analyzed when the projectile leaves the muzzle at 1117 m/s with 0° angle of fire, and the 200 m exterior trajectory of the projectile was obtained. Simulation results show that 24% deviation of the drop point relative to idea ballistic are caused by the disturbance of the integrated projectile in the muzzle, in which the maximum is caused by the muzzle vibration, and secondly the sabot discard. |
| Keywords: electromagnetic launch projectile six degree of freedom equation flight ballistic muzzle disturbance sabot discard |
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