正常式布局亚音速导弹不同操纵状态气动特性仿真研究  

Numerical study on aerodynamic characteristics of subsonic missiles with different maneuvering states in normal layout

作　　者：吕续舰 石浩 漆超 孙瑞胜[1] Lv Xujian;Shi Hao;Qi Chao;Sun Ruisheng(School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,China;Shanghai Civil Aviation Electromechanical Systems Co.,Ltd.,Shanghai 201100,China)

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]上海民用航空机电系统有限公司,上海201100

出　　处：《南京理工大学学报》2025年第1期32-40,66,共10页Journal of Nanjing University of Science and Technology

基　　金：国家自然科学基金(51609115)。

摘　　要：正常式布局导弹因其良好的气动稳定性、结构简单、有效载荷利用率高等优点,在军事应用中占据重要地位。为研究正常式布局导弹亚音速飞行时不同操纵状态下的气动特性,采用计算流体力学(CFD)方法,建立正常式布局导弹气动特性评估模型,数值分析了某正常式布局导弹尾舵不同操纵状态下的气动特性和流场结构演化,通过风洞试验与数值仿真结果进行对比分析,验证了数值方法的可靠性。计算结果表明:尾舵滚转、偏航操纵状态下,部分舵面当地攻角过大,致使舵面失速,影响其舵面法向力,最终导致全弹升力较尾舵不操纵时下降;不同操纵状态下全弹气动特性不同的根本原因在于尾舵各舵面偏转方向存在差异,引起尾舵的舵面法向力不同,最终导致全弹的气动特性发生变化。Normal layout missiles occupy an important position in military applications because of their good aerodynamic stability,simple structure and high payload utilization.In order to study the aerodynamic characteristics of normal layout missiles with different maneuvering states during subsonic flight,the computational fluid dynamics(CFD)method is used to establish an aerodynamic characteristics evaluation model for normal layout missiles.Based on this,a numerical method is used to analyze the aerodynamic characteristics and flow field structure evolution of a normal layout missile tail rudder under different maneuvering states,and wind tunnel experiments are conducted to verify the reliability of the numerical method.The numerical results show that:under the roll and yaw maneuvering state of the tail rudder,the local attack angle of some rudder surfaces is too high,which causes the rudder surface to stall and affects the rudder surface normal force,and ultimately leads to a decrease in the whole missile lift compared to when the tail rudder is not maneuvered;the fundamental reason for the different aerodynamic characteristics of the whole missile under different maneuvering states lies in the differences in the direction of deflection of each rudder surface of the tail rudder,which leads to the difference in the rudder surface normal force,and ultimately leads to the change of the aerodynamic characteristics for the whole missile.

关 键 词：正常式布局 舵偏角 舵面法向力 气动特性 

分 类 号：TJ760.2[兵器科学与技术—武器系统与运用工程]