扇式折叠翼巡飞导弹结构与气动数值计算  

Aerodynamic and Structure Numerical Simulation of Cruise Missile with Fan Style Wing

作　　者：许兆庆[1] 吴军基[1] 薛晓中[1] 孙慧 

机构地区：[1]南京理工大学能源与动力工程学院,江苏南京210094 [2]中国航天科技集团七院,四川成都610100

出　　处：《计算机仿真》2011年第12期24-26,231,共4页Computer Simulation

基　　金：国家部委预先研究项目(102080403)

摘　　要：研究导弹结构强度优化问题,针对设计具有扇式折叠翼与格栅舵的新式巡飞导弹,为了提高升力和结构刚度,对强度进行校核,采用数值仿真的方法进行了计算。用Patran建立结构模型,输入巡飞导弹各部分结构材料属性,之后由Nastran计算其固有模态。采用Gambit软件建立了气动模型,之后导入Fluent软件,采用密度基耦合显式求解器计算气动特性,得出了各马赫数下随攻角变化的升力与阻力系数值;依据气动计算结果,分别用数值仿真与工程算法对巡飞弹的折叠翼进行了强度校核。结果表明,满足强度要求的最大飞行攻角,为导弹的总体、弹道及控制系统设计提供依据。The numerical simulation of the cruise missile equipped with grid fins and three folding wings wee performed in this paper for investing its aerodynamic and structure characteristic.The structure model was made by using the software Patran.All of the material properties were input,and then the intrinsic mode was calculated by the software Nastran.The aerodynamic model was made by using the software Gambit,then the model was induced into Fluent to be computed by the method of density coupling after the unstructured meshes were made,and the values of lift force and drag force coefficient were obtained.The intensity of the missile folding wing was checked by the aerodynamic results,the statics mechanics calculation was performed by FEM and engineering algorithms respective,and the results of the largest angle of attack under various mach numbers were obtained.The results can afford original data for preliminary,ballistic and control design.

关 键 词：数值仿真 气动特性 固有模态 强度校核 

分 类 号：V215.1[航空宇航科学与技术—航空宇航推进理论与工程]