旋转导弹横向喷流干扰特性数值模拟  

Numerical Investigation of the Jet Interference Characteristics of a Lateral-jet-controlled Spinning Missile

作　　者：雷娟棉 高毅 勇政 LEI Juanmian;GAO Yi;YONG Zheng(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;Science and Technology on Space Physics Laboratory,Beijing 100076,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]空间物理重点实验室,北京100076

出　　处：《兵工学报》2024年第1期105-121,共17页Acta Armamentarii

摘　　要：为研究超声速来流条件下旋转导弹横向喷流干扰流场结构及喷流干扰对导弹气动特性的影响和机理,使用基于雷诺平均非定常N-S方程和滑移网格技术的非定常数值方法对旋转导弹横向喷流干扰流场进行模拟。研究旋转对导弹横向喷流控制效果的影响,给出不同条件下导弹的气动特性变化规律,分析了横向喷流对旋转导弹气动特性的影响。研究结果表明:旋转会导致导弹横向喷流控制力发生偏转,偏转方向与旋转方向相反,偏转角度随着转速增加而增加;在小攻角下,喷流干扰效应产生的附加侧向力和偏航力矩系数的瞬时值比旋转马格努斯效应产生的侧向力和偏航力矩系数的瞬时值大一个数量级,随着攻角增大,旋转马格努斯效应引起的侧向力和偏航力矩系数占全弹的比例增大,喷流引起的附加侧向力和偏航力矩量值减小;旋转导弹横向喷流控制扇面内气动系数随滚转角变化具有很强的非定常性,当喷流控制扇面角度不大时,时均侧向气动特性与对称面处滚转角下的瞬时值侧向气动特性比较接近,不同扇面角度内有喷流的时均侧向力系数和偏航力矩系数远大于无喷流时。In this study,a supersonic jet issued from a spinning missile into a supersonic freestream is numerically simulated.The 3D compressible unsteady Navier-Stokes equations and the sliding mesh method are utilized to simulate the flow field numerically.The effect of spinning motion on missile lateral jet control efficiency is studied,and the variation rules of aerodynamic characteristics of spinning missile under different conditions are given.The influence of lateral jet on the aerodynamic characteristics of spinning missile was analyzed.The results show that the spinning leads to the deflection of jet interference force and control force,and the deflection angle increases with the increase of spin rate.At small angle of attack,the additional lateral force and yaw moment coefficient caused by jet interference effect are one order of magnitude larger than those caused by Magnus effect.With the increase of angle of attack,the proportion of lateral force and yaw moment coefficient caused by Magnus effect in the whole missile increases,and the additional lateral force and yaw moment coefficient caused by jet decreases.The aerodynamic coefficients in the lateral jet control sector of the spinning missile vary with the rolling angle with strong unsteady characteristics.When the angle of the jet control sector is small,the time-averaged lateral aerodynamic characteristics are close to the transient lateral aerodynamic characteristics at the rolling angle of the symmetric surface.The time-averaged lateral force coefficient and time-averaged yaw moment coefficient with jet at different sector angles are much larger than those without jet.

关 键 词：旋转导弹 横向喷流 喷流干扰 侧向力 数值模拟 

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]