尖锥和喉道损伤对超声速进气道的影响研究  

Research on Influence of Supersonic Inlet with Cone and Throat Damage

作　　者：王意坤 卓长飞[1] 罗熙斌 Wang Yikun;Zhuo Changfei;Luo Xibin(College of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China;China Huayin Weapon Test Center,Huayin 714200,China)

机构地区：[1]南京理工大学机械工程学院,南京210094 [2]中国华阴兵器试验中心,陕西华阴714200

出　　处：《兵工自动化》2025年第1期90-97,共8页Ordnance Industry Automation

摘　　要：针对超声速进气道结构损伤会对其内外流场和性能参数造成影响的问题,采用数值模拟分析喉道穿孔和尖锥折断2种损伤类型对超声速进气道的影响,分别计算3种模型在0和4°攻角时的工况。2种损伤均会使阻力系数增大,0攻角时,喉道损伤对流场影响较大,尖锥折断损伤影响则较小;4°攻角时,损伤后流场变化较小。但2种损伤模型内部马赫数、压力以及出口截面总压恢复系数分布均与无损模型不同。尖锥折断损伤模型对称面上的沿程压力分布与无损模型相近,而喉道穿孔损伤与无损模型差异较大。结果表明,该计算可为导弹毁伤后性能降级判定提供一定的参考依据。Aiming at the problem that the structural damage of supersonic inlet will affect its internal and external flow field and performance parameters,the numerical simulation was used to analyze the effects of two types of damage,namely,throat perforation and cone breakage,on the supersonic inlet,and the working conditions of three models at 0 and 4°angles of attack were calculated respectively.When the angle of attack is 0,the throat damage has a greater impact on the flow field,while the cone break damage has a smaller impact;when the angle of attack is 4°,the flow field changes slightly after the damage.However,the internal Mach number,pressure and the total pressure recovery coefficient distribution at the exit section of the two damage models are different from those of the non-destructive model.The pressure distribution on the symmetry plane of the damage model of sharp cone fracture is similar to that of the non-destructive model,while the pressure distribution on the symmetry plane of the damage model of throat perforation is quite different from that of the non-destructive model.The calculation results can provide a reference for the judgment of missile performance degradation after damage.

关 键 词：超声速进气道 尖锥折断损伤 喉道穿孔损伤 流场变化 性能参数变化 

分 类 号：TJ761.6[兵器科学与技术—武器系统与运用工程]