【摘要】 针对火箭弹发射过程中发动机燃气射流对联装发射箱前盖的冲击造成影响的问题，采用数值计算的方法开展研究。基于三维可压缩Navier-Stokes方程、Realizable k-ε两方程湍流模型、二阶迎风TVD离散格式，建立了火箭弹发射过程燃气射流冲击模型。结果表明，随着火箭弹出箱距离的增加，燃气射流对发射箱的冲击作用呈先上升后下降的趋势，出箱0.5 m距离时，发射箱前盖表面温度和压强最低，燃气射流对发射箱的冲击载荷最小，8 m距离时发射箱前盖峰值温度最高，为1 375 K，峰值压强最高，为195 k Pa,10 m距离时冲击载荷最大，为20.21 k N，随着距离继续增大，发射箱表面温度和压强以及燃气射流对发射箱的冲击载荷开始缓慢降低。以上研究结果对发射箱的安全设计和发射装置的热防护提供了参考。更多还原

【Abstract】 To investigate the impact of rocket engine gas jet on front cover of a multi-launcher canister during a rocket launching process,a numerical simulation approach was adopted to analyze the flow field after the rocket exits the canister. A gas jet impingement model was established based on the 3D compressible Navier-Stokes equations,the Realizable k-ε turbulence model,and a second-order upwind total variation diminishing( TVD) discretization scheme. The results reveal that as the canisterout height of the rocket increase,the impingement effects on the canister initially intensify and then diminish. Key findings include: At 0. 5 m out height,the front cover bears the lowest surface temperature and lowest pressure,with minimum impact loads. At 8 m height,the front cover bears the highest peak temperature of 1 375 K and highest maximum pressure of 195 k Pa.At 10 m height,the impact load peaked at 20. 21 k N,followed by a gradual reduction in temperature,pressure,and impact loads as the rocket ascended further. This study provides critical insights for safety design of launcher canisters and thermal protection strategies for launch systems.更多还原