导弹从发射箱热发射过程的数值分析  

Numerical analysis of hot launch of missile from a launch canister

作　　者：梁晓扬[1] 苏逸飞 乐贵高[1] LIANG Xiaoyang;SU Yifei;LE Guigao(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《航空动力学报》2022年第8期1643-1653,共11页Journal of Aerospace Power

摘　　要：采用三维可压缩雷诺平均Navier-Stokes方程和k-ε湍流模型,研究了导弹出箱过程中,弹体姿态偏转后弹底周围环境及发射箱内的流场特性。首先,以超声速欠膨胀射流撞击平板实验为算例,对数值方法的有效性进行验证。其次,分别对导弹在约束期和半约束期箱内流动特性展开研究。研究表明:喷管尾流在发射箱内会形成强烈的引射效应。同时,在弹底会出现明显的回流区域,使导弹出箱时受到额外的阻力。考虑偏转后,发射装置受到的冲击载荷增大2倍以上,发射箱壁面受到的压力增加40%。而且,在半约束期,箱内的流场分布不再对称,会使得导弹受到额外的不平衡力矩。Based on the three-dimensional compressible Reynolds-averaged Navier-Stokes equation and the k-εturbulence model,the environment around the bottom of the missile and the flow field characteristics in the launch canister after deflection of the missile attitude were investigated.Firstly,the effectiveness of the numerical method was verified by the experiment of supersonic jet impinging on a flat plate.Secondly,the flow characteristics of the launch canister in the constrained and semi-confined periods were investigated respectively.The results showed that significant entrainment effect of the exhaust gas can be found in the launch canister.Meanwhile,a backflow area near the bottom of the missile can be observed,which may cause additional drag force on the missile during the launching process.After considering the deflection,the impact load on the launcher was increased by more than two times and the pressure on the launch box wall was increased by 40%.Moreover,the flow field distribution inside the box was no longer symmetrical during the semi-confinement period,making the missile subject to additional unbalanced moments.

关 键 词：射流冲击 非同时离轨 发射箱 引射效应 二次流 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]