旋转导弹横向喷流干扰特性数值模拟

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.