栅格翼翼身组合体超声速滚转阻尼特性  

Roll Damping Characteristics for Missile With Grid Fins at Supersonic Speed

作　　者：邓帆[1] 陈少松[1] 王学德[1] 

机构地区：[1]南京理工大学能源与动力工程学院,南京210094

出　　处：《弹道学报》2011年第3期58-62,共5页Journal of Ballistics

摘　　要：为了研究栅格翼翼身组合体超声速的滚转阻尼特性,采用求解定常状态N-S方程的方法,对超声速阶段栅格翼翼身组合体在有攻角时的滚转阻尼特性进行了数值研究,并且与平板翼翼身组合体的滚转阻尼特性进行了比较.对平板翼翼身组合体的数值模拟结果与实验值的误差较小,该方法可作为研究复杂翼身组合体滚转阻尼特性的数值计算方法.计算结果显示在所研究的攻角范围内,栅格翼翼身组合体的滚转阻尼导数随马赫数的增加出现2次转折,Ma=2.5时出现严重的气流壅塞现象;滚转阻尼导数随攻角的增大而减小,背风面栅格翼受组合体分离流的影响较大.N-S numerical simulation based on steady-state calculation was used to predict the roll damping characteristics of missile with grid fins at supersonic speed and different angles of attack.The result was compared with that of panel fins in order to find the different aerodynamic characteristics.The computational result of panel fins model by this method well agrees with the wind tunnel data found in foreign public papers.The method can be applied to simulating the roll damping characteristics of complex aircraft.The results indicate that the roll damping derivative of the missile with grid fin tails has two turning points as Mach number increases,and the serious flow chocking phenomenon appears while Ma=2.5.This derivative decreases as angle of attack increases,and the separated flow of the missile influences the leeward grid fin greatly.

关 键 词：导弹 栅格翼 滚转阻尼导数 数值模拟 

分 类 号：TJ760.3[兵器科学与技术—武器系统与运用工程]