某微型导弹气动特性工程估算与数值仿真研究  

Engineering Estimation and Numerical Simulation of Aerodynamic Characteristics of a Mirco Missile

作　　者：张建[1] 何志强 赵奂强 田宏亮[1] ZHAGN Jian;HE Zhi-qiang;ZHAO Huan-qiang;TIAN Hong-liang(China Airborne Missile Academy,Luoyang Henan 471009,China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《计算机仿真》2024年第6期89-92,97,共5页Computer Simulation

基　　金：航空科学基金(2019ZC012001)。

摘　　要：微型化是空空导弹发展的一个重要方向,美国在导弹微型化方面已经取得一些进展。气动特性研究对微型导弹的控制系统和弹道设计具有重要意义,利用工程和数值方法对某微型导弹气动力系数进行仿真,以风洞实验数据为基准对仿真结果的相对误差进行分析。结果表明,两种仿真方法都能够得到与风洞实验相符的结果,其中数值仿真精度相对误差最大为12.42%,相较于工程方法(相对误差不大于27.31%)精度更高,但是在微型导弹初始方案设计阶段,工程方法计算效率更高。Microminiaturization is an important direction in the development of air-to-air missiles,and the United States has made some progress in missile miniaturization.The study on aerodynamic characteristics is of great signifi⁃cance to the control system and trajectory design of micro missiles.The aerodynamic coefficients of a micro missile were simulated by engineering and numerical methods,and the accuracy of the simulation results was analyzed based on the wind tunnel experimental data.The results show that both methods can get the results consistent with the wind tunnel data.The numerical method,with the maximum relative error of 12.42%,is able to get better accuracy com⁃pared to engineering method(the relative error is less than 27.31%).However,in the initial conceptual design stage of micro-missile,the calculation efficiency of engineering method is higher.

关 键 词：微型导弹 气动特性 工程估算 数值仿真 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] TJ760.1[兵器科学与技术—武器系统与运用工程]