旋转体制下鸭式布局弹箭正弦打舵气动特性分析

为了研究鸭式布局弹箭正弦打舵滚转控制时非对称姿态飞行的气动特性,根据滚转周期内的飞行姿态建立了4组模型,进行风洞实验,得到全弹的气动力变化规律; 采用基于三维Navier-Stokes方程求解的时空二阶精度的隐式迭代算法,建立数值计算模型,对流场进行数值模拟,得到不同攻角下飞行时的弹箭各部件气动力数据。结果表明数值模拟气动力数据与风洞实验结果有相似的变化规律。采用后处理软件分析了鸭舵下洗对尾翼的影响,得到结论:鸭式布局弹箭鸭舵洗流对尾翼干扰明显,非对称姿态下鸭舵对尾翼的洗流会使弹箭产生诱导滚转力矩,且该滚转力矩随攻角增大而增大。

Analysis on Aerodynamic Characteristics of Canard-configuration Missile With Sinusoidal Rudder Under Rotating System

In order to study the aerodynamic characteristics of canard-configuration missile in asymmetric attitude flight with sinusoidal rudder rolling control,four groups of models were established according to the flight attitude in rolling period,and the wind tunnel experiment was carried out to obtain the aerodynamic characteristics of the whole missile. Based on the implicit iterative algorithm of space-time second-order accuracy solved by three-dimensional Navier-Stokes equation,the numerical calculation model was established,and the flow field was numerically simulated to obtain the aerodynamic data of each part of the missile at different angles of attack. The results show that the aerodynamic data obtained by numerical simulation have similar change rules with wind tunnel test results. The influence of canard downwash on the tail was analyzed by using post-processing software. The canard downwash has obvious interference on the tail,and the canard downwash in asymmetric attitude will cause the missile to produce induced rolling moment which increases with the increase of attack angle.