空空导弹发动机尾流对后弹体烧蚀的数值分析  

Numerical Analysis for Ablation of Rocket Plume on Air-to-Air Missile to Afterbody

作　　者：白涛涛[1] 曹军伟[1] 王虎干[1] 沈欣[2] Bai Taotao;Cao Junwei;Wang Hugan;Shen Xin(China Airborne Missile Academy,Luoyang 471009,China;Military Respresentative Office in China Airborne Missile Academy,Luoyang 471009,China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]驻中国空空导弹研究院军事代表室,河南洛阳471009

出　　处：《航空兵器》2018年第4期52-56,共5页Aero Weaponry

摘　　要：针对发动机尾流对空空导弹后弹体的烧蚀现象,采用CFD流场数值计算方法开展了三维流场数值计算,并与飞行试验结果进行对比,分析了尾流烧蚀后弹体的原因,研究了飞行高度及飞行马赫数对尾流烧蚀效应的影响,结果表明:高速外流与高温尾流在后弹体附近产生的流动干扰是尾流烧蚀后弹体的主要原因;飞行马赫数一定时,尾流对后弹体的烧蚀随着飞行高度的增加而严重;飞行高度一定时,尾流对后弹体的烧蚀随着飞行马赫数的增大而减弱;数值模拟与残骸上的烧蚀形貌一致,验证了计算方法的正确性。Aiming at the ablation of rocket plume on air-to-air missile to afterbody, the 3-D flow field is simulated using CFD method, which is compared with the result of flying test, in order to analyze the common cause of ablation and investigate the influence of flying altitude and Mach number on ablation. The results show that the main factor leading to ablation of plume on afterbody is the flow interference of high speed external flow and high temperature plume. Under certain flying Mach number, the ablation of plume on afterbody will become more serious with the raise of flying altitude. Under certain flying altitude, the ablation of plume on afterbody will become weakened with the increasing of flying Mach number. The simulation results is consistent with the ablation morphology of missile wreckage which validates the correctness of computational method .

关 键 词：空空导弹 后弹体 尾喷流 烧蚀 数值模拟 

分 类 号：TJ760.1[兵器科学与技术—武器系统与运用工程] V435.14[航空宇航科学与技术—航空宇航推进理论与工程]