扭曲尾翼弹箭气动外形多目标优化

Multi-objective Optimization on Aerodynamic Shape of Projectile with Twisted Empennages

为了提升掠飞末敏弹战术技术性能,将扭曲尾翼结构应用于弹箭气动布局,并在风洞实验基础上,结合计算流体力学、正交实验、逐步回归分析以及多目标遗传算法,对扭曲尾翼弹箭开展了以增旋、减阻为目标的气动外形多目标优化设计,最终给出了尾翼外形的Pareto优化方案。结果表明:采用扭曲尾翼结构有利于改善弹箭气动性能;所建立的气动参数代理模型,能对弹箭阻力系数和平衡转速进行准确预测,并得到了尾翼几何参数对其影响规律;基于多目标遗传算法最终得到的Pareto优化方案,达到了良好的增旋、减阻效果。该研究方法对扭曲尾翼弹箭气动优化设计具有参考意义。

The twisted empennage structure is applied to the aerodynamic configuration design of hedgehopping terminal sensitive projectile for improving its performance. In order to obtain higher balance rota- tional speed and lower drag coefficient, a multi-objective optimization design of the aerodynamic shape of projectile with twisted empennages is developed based on the wind tunnel tests. The computational fluid dynamics, orthogonal experiment design, stepwise regression analysis and genetic algorithm are applied, and the Pareto solutions of the empennage shape are provided. The results indicate that the twisted em- pennage structure can significantly improve the aerodynamic performance of projectile. An aerodynamic parameter surrogate model is established accurately to predict the projectile drag coefficient and balance rotational speed, and the influences of empennage structural parameters on the proposed model can be further obtained. The Pareto solutions based on the multi-objective genetic algorithm display a good per- formance on the increase in rotational speed and the reduction in drag.