摘要
为了合理设计空空导弹尾部的热结构,通过数值仿真对不同飞行高度、飞行速度和燃烧室内压状态下导弹尾喷流对后端热结构的影响进行分析,获得了影响导弹尾部热环境的规律。研究结果表明,导弹后端面热环境的恶劣程度随飞行马赫数和燃烧室内压的增加而增大,但在中低空情况下飞行高度变化对其影响较小,数值模拟结果与地面点火试验及空中飞行试验结果相吻合。
In order to design thermal structure of air-to-air missile tail properly, through researching the effect of exhaust plume on thermal environment of missile tail, the numerical simulations were conducted under different flight Mach number, flight height and combustor pressure. The results show that thermal environment of missile tail gets worse with the increase of flight Maeh number and combustion chamber pressure,but changes little with the varieties of flight height at middle and low altitudes. The simulation results match well with the results of ground ignition test and flight test.
出处
《弹箭与制导学报》
CSCD
北大核心
2011年第3期157-159,168,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
空空导弹
尾喷流
热环境
点火试验
数值仿真
air-to-air missile
exhaust plume
thermal environment
ignition test
numerical simulation
