细长旋成体导弹高空气动性能工程预测方法研究  

Research on engineering prediction method for high aerodynamic performance of slender spinning missiles

作　　者：何仕培 刘玉祥 苏日新 王利[3] 丁锴 HE Shipei;LIU Yuxiang;SU Rixin;WANG Li;DING Kai(Jiangnan Institute of Electromechanical System Design,Guiyang 550000,China;The 10th Academy of CASIC,Guiyang 550000,China;China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]江南机电设计研究所,贵州贵阳550000 [2]中国航天科工集团第十研究院,贵州贵阳550000 [3]中国航天空气动力技术研究院,北京100074

出　　处：《飞行力学》2023年第6期36-43,共8页Flight Dynamics

摘　　要：针对细长旋成体导弹高空粘性干扰效应气动性能工程预测方法研究不足的问题,开展了细长旋成体导弹高空粘性干扰效应气动性能工程预测方法研究。首先,采用数值模拟方法研究了细长旋成体导弹高空粘性干扰效应机理。然后,从流动机理出发,利用等价锥法、参考焓理论与低空部件叠加法,构建了一套考虑高空粘性干扰效应的细长旋成体气动性能工程预测方法。最后,采用CFD与风洞试验数据完成工程预测方法精度验证。结果表明:该工程预测方法可有效提升气动性能预测精度,全弹法向力系数误差基本在5%以内,压心系数偏差在0.01左右。Aiming at the problem of insufficient research on the engineering prediction method of high-altitude viscous jamming effect of slender spinning missiles,research on aerodynamic performance engineering prediction method of high-altitude viscous interference effect of slender spinning missile was carried out.Firstly,numerical simulation methods were used to study the mechanism of high-altitude viscous interference effects on slender spinning missiles.Then,starting from the flow mechanism,using the equivalent cone method,reference enthalpy theory,and low altitude component superposition method,a set of engineering prediction methods for the aerodynamic performance of slender spiral bodies considering high-altitude viscous interference effects was constructed.Finally,the accuracy verification of the engineering prediction method was completed using CFD and wind tunnel test data.The results show that the engineering prediction method can effectively improve the prediction accuracy of aerodynamic performance,the error of the normal force coefficient of the full elastic is basically within 5%,and the deviation of the center of pressure coefficient is about 0.01.

关 键 词：细长旋成体导弹 粘性干扰效应 参考焓理论 部件叠加法 工程预测方法 

分 类 号：TJ760.11[兵器科学与技术—武器系统与运用工程]