| 亚音速条件下可偏转头部弹气动特性研究 |
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| 引用本文： | 李明,陈智刚,董素荣,侯秀成. 亚音速条件下可偏转头部弹气动特性研究[J]. 弹箭与制导学报, 2010, 30(5) |
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| 作者姓名： | 李明 陈智刚 董素荣 侯秀成 |
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| 作者单位： | 1. 中北大学机电工程学院,太原,030051
2. 中北大学机电工程学院,太原,030051;北京理工大学机电工程学院,北京,100081 |
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| 摘 要： | 通过数值模拟对可偏转头部弹在0.35Ma、偏转角为0°～5°时的气动特性进行相关研究。当头部发生偏转时,压心发生变化且产生横向作用力使得弹丸偏离原弹道。随着偏角的增加,压心先向着头部移动;当偏角进一步增大时,压心不再继续向前移动。攻角的存在使得阻力系数增大,而Z向力系数基本不变。
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| 关 键 词： | 数值模拟 可偏转弹丸 弹道修正 气动特性 |
Aerodynamic Characteristics of Missile with a Deflected Angle of Forehead in Subsonic Flow |
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| LI Ming,CHEN Zhigang,DONG Surong,HOU Xiucheng. Aerodynamic Characteristics of Missile with a Deflected Angle of Forehead in Subsonic Flow[J]. Journal of Projectiles Rockets Missiles and Guidance, 2010, 30(5) |
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| Authors: | LI Ming CHEN Zhigang DONG Surong HOU Xiucheng |
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| Affiliation: | LI Ming1,CHEN Zhigang1,DONG Surong1,HOU Xiucheng1,2 (1 School of Mechatronics Engineering,North University of China,Taiyuan 030051,China,2 School of Mechatronic Engineering,Beijing Institute of Technology,Beijing 100081,China) |
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| Abstract: | Based on aerodynamic characteristics of missiles with a deflected angle of forehead at the Mach 0.35 and deflection angle from 0 degree to 5 degrees by numerical simulation.Through the study,it is found that the deflection of head leads to the change of the pressure center and the generation of lateral forces which make the projectile deviate from the original trajectory.As the declination increases,the pressure center first moves toward the head,when the angle further increases,the pressure center stops to... |
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| Keywords: | numerical simulation missile with a deflected angle of forehead ballistic correction aerodynamic characteristic |
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