管式发射双鸭式布局导弹反安定面设计研究  

Study on the Aerodynamic Characteristic of Split Canard ofTube-launched Split Canard Configuration Missile

作　　者：浦钰文 陈少松[1] 徐一航 魏恺 孙宁 PU Yuwen;CHENG Shaosong;XU Yihang;WEI Kai;SUN Ning(School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,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

出　　处：《弹道学报》2023年第2期76-86,共11页Journal of Ballistics

摘　　要：为研究反安定面外形对双鸭式布局导弹气动特性的影响,对鸭式布局模型、梯形翼反安定面双鸭式布局模型和边条翼反安定面双鸭式布局模型在不同攻角、马赫数下的气动特性进行模拟,分析了阻力系数、升力系数、表面压力分布系数,力矩系数等参数的变化规律。结果表明:在反安定面面积相同的情况下,当Ma≦2时,梯形翼反安定面在中小攻角下(0°~30°)对全弹气动特性(除升阻比外)提升较大;当Ma>2时,边条翼反安定面对全弹气动特性提升较大。当Ma≦2时,两种反安定面对鸭舵升力系数产生负面影响,主要原因是反安定面会使鸭舵下表面压力系数减小。但由于边条翼反安定面的分离涡较强,在很大攻角范围内(0°~30°)与鸭舵涡产生有利的相互作用,使鸭舵上表面压力系数减小,进而鸭舵升力系数相较于梯形翼模型的有一定增加,并且鸭舵的升力系数很大攻角范围内都保持很好的线性度。在对弹头升力系数的影响中,两种反安定面在不同的速度下有不同的影响。In order to study the influence of split canard shape on the aerodynamic characteristics of split canard configuration missiles,the aerodynamic characteristics of canard configuration model,split canard configuration model with the trapezoidal split canard and split canard configuration model with striped split canard were simulated at different angle of attack(AOA)and Mach numbers.The coefficients of drag,lift,pressure and moment were analyzed.The results show that,with the same split canard area,the trapezoidal split canard has a greater improvement on the full bomb aerodynamic characteristics at small and medium angles of attack(0°-30°)when Ma≦2,and the striped split canard has a greater improvement on the full bomb aerodynamic characteristics(except the lift-to-resistance ratio)when Ma>2.In the effect on the coefficient of lift of canard,the two types of split canards have a negative effect when the Ma≦2,because the striped split canard decreases the pressure coefficient on the lower surface of the canard.In particular,the separation vortex of the striped split canard is stronger and generates favorable vortex interaction with the canard vortex,which reduces the pressure coefficient on the upper surface of the canard.Therefore,the lift coefficient of the canard is increased compared with that of the trapezoidal split canard model,and the linearity of the lift coefficient of the duck rudder is maintained over a wide range of angles of attack(0°-30°).In the effect on the warhead lift coefficient,the split canard have different effects at different velocities.

关 键 词：双鸭式布局 反安定面 数值模拟 气动特性 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] TJ011[兵器科学与技术—兵器发射理论与技术]