摘要
针对导弹发射离箱之后,喷管处的高温高速燃气可能吹破多联装发射箱相邻前盖的情况,在进行导弹头部下沉、整体下沉等滑离参数计算的基础上,利用计算流体力学方法分析在不同导弹姿态、离箱距离等条件下燃气流对发射箱前盖表面压力、温度的影响情况,仿真结果显示各个发射箱前盖参数分布有较大差异,仿真结论对工程实践中贮运发射箱的设计具有一定的参考作用。
Aiming at the problems that the former lid of the missile was easy to be broken by high tempera- ture and high velocity jet flow, by computing sinkage of the whole body and head part of missile, depen- ding on method of computational fluid dynamic, the surface pressure and temperature is analyzed on differ- ent missile pose and leave distance. The result of simulation shows the parameter of the former friable lid exits great difference, the conclusion is important to design launch box in the engineering application.
出处
《空军工程大学学报（自然科学版）》
CSCD
北大核心
2013年第2期32-36,共5页
Journal of Air Force Engineering University(Natural Science Edition)
关键词
燃气射流
发射箱前盖
计算流体力学
jet flow
former lid of the missile
computational fluid dynamic
