变后掠翼制导火箭弹气动特性分析与弹道优化

Analysis of aerodynamic characteristics and trajectory optimization of variable-sweep wing guided rockets

为提升制导火箭弹射程,对变后掠翼制导火箭弹气动特性进行分析,并加入了弹翼后掠角动态变化策略对火箭弹弹道进行优化。采用计算流体力学(CFD)仿真计算不同后掠角下火箭弹气动参数,并进行气动特性分析,总结了其变化规律。采用hp-自适应Radau伪谱法对火箭弹的弹道进行了优化。考虑到火箭弹的弹翼变形策略,将后掠角的变化纳入计算,对不同后掠角下的固定翼和可变掠翼火箭弹的滑翔段轨迹进行了对比分析。仿真计算结果表明,相对于固定翼火箭弹,采用变后掠翼制导火箭弹可以获得10.8%至34.6%的射程增益,这对提升火箭弹射程具有一定的理论指导意义。

To enhance the range of guided rocket projectile,the aerodynamic characteristics of variable-sweep wing guided rocket projectile are analyzed,and the rocket projectile’s trajectory is optimized by adding the dynamic change strategy of wing sweep angle.The aerodynamic parameters of rocket projectile at various sweep angles are calculated by computational fluid dynamics(CFD)simulation,and the aerodynamic characteristics are analyzed to summarize deformation patterns.An hp-adaptive Radau pseudospectral method is employed to optimize the rocket projectile's trajectory.Considering the wing deformation strategy of the rocket projectile,the variation in sweep angle is incorporated into the calculations to compare and analyze the glide trajectory of both fixed-wing and variable-sweep wing rocket projectiles at different sweep angles.The simulation results indicate that variable-sweep wing guided rocket projectiles range can be increased by 10.8%to 34.6%compared with fixed-wing rocket projectiles,which has a certain theoretical significance for enhancing the projectile's range.