导弹异形卷弧翼安装选型

Selection and installation of abnormity wrap around fins of missle

为在空中发射武器外形设计中引入异形卷弧翼,将其作为导弹主升力面,研究其相对于弹身的安装选型问题.模型设计采用1对异形卷弧翼,并将其沿弹体纵向平面对称布置.定义异形卷弧翼相对于弹身的安装位置角和安装偏角参数,选取2组计算模型,基于计算流体力学(Computational Fluid Dynamics,CFD)仿真计算评估这2个角度的变化对异形卷弧翼—弹身组合体纵向超音速气动参数的影响,得到组合体升力因数、阻力因数以及升阻比随2个角度参数变化而变化的规律.结果表明,在设计任务中,当安装位置角等于120°,安装偏角等于-10°时,组合体的升力因数和升阻比达到最大值.该方法可以改善导弹的升力特性,提高导弹的升阻比,使导弹获得更好的飞行性能.

To introduce abnormity wrap around fins into the profile design of air-launched weapons, the abnormity wrap around fins are taken as the primary lifting-surface of a missile, and the selection and installation in relation to the missile body are studied. In the model design, a pair of abnormity wrap around fins are installed symmetrically along the longitudinal plane of the missile. The attachment location angle and horizontal deflection angle are defined relative to the missile body. Two groups of models are established and the numerical computation based on Computational Fluid Dynamics（CFD） on the change of the two angles is done to evaluate their effect on the supersonic aerodynamic parameters of the fin-body configuration. For the fin-body configuration, the change rule of lift factor, drag factor and lift-drag ratio with the change of the two defined angles is obtained. The results indicate that the lift factor and lift-drag ratio reach the maximum when the attachment location angle equals 120° and the horizontal deflection angle equals - 10°. The method can improve the lift characteristics and lift-drag ratio of missiles and achieve better flight performance for missiles.