摘要
针对导弹低温燃气弹射的压力双波峰问题,基于动网格技术,构建了考虑二次燃烧的二维轴对称模型,并验证了模型的可靠性。研究了环形腔结构平滑压力曲线的机理,以开口角度作为调整参数,分析了不同开口角度对压力冲击的平滑效果。结果表明:增加环形腔后能有效的变双峰为单峰,燃气沿着燃气发生器壁面向上扩散,氧气的消耗率下降,二次燃烧现象明显滞后;当θ=2°时,筒底的冲击压力减小了3.1%,导弹的出筒时间延迟了2.6%,导弹的出筒速度减小了5.1%。研究思路和结论可为内弹道的设计优化提供参考。
Based on dynamic mesh technology,a two-dimensional axisymmetric model considering secondary combustion was constructed for the problem of double pressure peaks shock of missile low-temperature gas-ejection,and the reliability of the model was verified.The mechanism of the smooth pressure curve of the ring cavity structure is studied.The opening angle was used as the adjustment parameter to analyze the smoothing effect of different opening angles on the pressure shock.The results show that the increase of the ring cavity can effectively change the double peak to a single peak,the gas will spread upward along the wall of the gas generator,the oxygen consumption rate will decrease,and the secondary combustion phenomenon will obviously lag;θ=2°makes the impact pressure at the bottom of the barrel is reduced by 3.1%,the missile’s delivery time is delayed by 2.6%,and the missile’s discharge speed is reduced by 5.1%.Research ideas and conclusions can provide reference for the design optimization of internal ballistics.
作者
赵谢
程洪杰
赵媛
高蕾
ZHAO Xie;CHENG Hongjie;ZHAO Yuan;GAO Lei(Lab.of Armament Launch Theory&Technology,Army Key Discipline,Rocket Forces University of Engineering,Xi’an 710025,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2020年第5期664-670,共7页
Journal of Solid Rocket Technology
基金
国家自然科学基金面上项目(51475462)。
关键词
燃气弹射
内弹道
环形腔
结构参数
冲击平滑
gas ejection
interior ballistics
ring cavity
structure parameters
impact smoothing