基于CFD/RBD方法的旋转弹轨迹仿真

Trajectory Simulation of a Spinning Projectile Based on CFD/RBD Computation Method

旋转弹在飞行过程中,由于表面气动载荷分布不对称,可能会出现耦合共振、灾难偏航等现象,使导弹飞行失常偏离目标。针对此类问题,采用非定常N-S方程和刚体动力学方程耦合求解的方法,仿真旋转弹飞行轨迹。非定常气动力计算使用非结构混合网格N-S方程求解程序HUNS3D,刚体六自由度运动方程采用改进的四阶Adams预估校正法求解。将这种耦合求解方法应用于美国ARL旋转弹试验模型的轨迹仿真,并将计算得到的旋转弹姿态角、空间位置和气动力与相关文献进行对比分析,结果表明:本文方法能较精确地仿真旋转弹的飞行轨迹。

During the flight process,the asymmetric aerodynamic loads distributed on the surface of spinning projectile,it may cause coupled resonance and yaw-disaster phenomenon.Then the projectile miss the target.For such problems,the unsteady Navier-Stokes equation and rigid body dynamic（RBD）equations are solved to simulate the flight trajectory of a spinning projectile.The unsteady aerodynamic computations are conduced by using an in-house hybrid unstructured Navier-Stokes flow solver 3D（HUNS3D）.The rigid body of 6degrees of freedom（6-DOF）motion equations are solved by using an advanced Adams prediction-correction method.The coupled computation method is applied to simulate and analyze the flight trajectory of U.S.Army Research Laboratory spinning projectile test model.The computed results of the attitude angle,space position and aerodynamic force are compared with those in related literature.Results show that this method can truly simulate the flight trajectory of spinning projectile.