| 引用本文: | 张锐,袁志勇,刘忠乐,等.尾流模拟火箭弹空中弹道对模拟尾流生成区域的影响.[J].国防科技大学学报,2019,41(4):94-101.[点击复制] |
| ZHANG Rui,YUAN Zhiyong,LIU Zhongle,et al.Influence of airborne trajectory of wake simulator rocket on formation area of simulated wake[J].Journal of National University of Defense Technology,2019,41(4):94-101[点击复制] |
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| 尾流模拟火箭弹空中弹道对模拟尾流生成区域的影响 |
| 张锐1, 袁志勇1, 刘忠乐1, 张冲2 |
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(1. 海军工程大学 兵器工程学院， 湖北 武汉 430033;2. 中国人民解放军92095部队， 浙江 台州 318000)
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| 摘要: |
| 为了研究尾流模拟火箭弹的空中弹道特性对模拟尾流区域的影响，建立火箭弹质点外弹道模型、阻力板和发动机空间运动微分方程以及连接绳的受力模型，得到火箭弹无控飞行、空中转向、空中分离至爆索展开入水全过程的空间运动微分方程。对尾流模拟火箭弹全程弹道进行仿真分析，着重分析不同初始射击诸元对爆索空中弹道的影响，探究初始发射角、脉冲发动机的喷管数量、点火时间以及火箭弹空中分离时间对模拟尾流生成区域的影响。仿真结果表明：初始发射角为15°时火箭弹射程和最大射高相对比较合理；火箭弹空中转向角度依赖于脉冲发动机总冲量，与点火时刻无关；空中分离时刻对爆索入水发泡区域影响不太明显，在满足转向要求和发泡区域要求的情况下应该尽早完成空中转向和分离。 |
| 关键词: 爆索 减速板 空中弹道 推偏发动机 射击诸元 |
| DOI：10.11887/j.cn.201904014 |
| 投稿日期：2018-04-19 |
| 基金项目:国家重点基础研究发展计划资助项目（7131441） |
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| Influence of airborne trajectory of wake simulator rocket on formation area of simulated wake |
| ZHANG Rui1, YUAN Zhiyong1, LIU Zhongle1, ZHANG Chong2 |
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(1. Academy of Weaponry Engineering, Naval University of Engineering, Wuhan 430033, China;2. The PLA Unit 92095, Taizhou 318000, China)
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| Abstract: |
| In order to study the effects of the airborne ballistic characteristics of wake simulation rockets on the simulated wake area, the exterior ballistic model of the rocket projectile, the space motion differential equation of the resistance plate and the engine, the force model of the connecting rope were established. The differential equations of space motion in the whole process of uncontrolled flight, air steering, air separation and unfolding of the detonating cable were obtained. The whole trajectory of the tail-flow-simulated-rocket was simulated and analyzed. The effect of different initial firing elements on the air trajectory of the detonating cable was emphatically analyzed. The influence of initial launch angle, the number of pulse tubes, the ignition time and the rocket separation time on simulated wake generation region were investigated. The simulation results show that the range and maximum shot height of the rocket projectile are relatively reasonable when the initial launch angle is 15 degrees. The angle of the rocket′s air steering depends on the total impulse of the pulse engine and has nothing to do with the ignition time. The effect of air separation time on the water foaming area of the detonating cord is not obvious. Air steering and separation should be completed as soon as possible when the steering requirements and the requirements of the foamed area are met. |
| Keywords: bomb cord speed brake plate aerial trajectory pulse engine shooter elements |
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