论文部分内容阅读
超声速飞行器的横截面积分布对其激波阻力的影响十分显著,合理的机翼和机身横截面积分布可以显著降低其激波阻力。使用类别形状函数变换(CST)方法对机身进行基于横截面积分解的CST参数化外形表示,在此基础上提出了扩展的远场组元(EFCE)超声速翼身组合体激波阻力优化算法,并使用该方法对超声速客机翼身组合体进行外形优化,使其激波阻力系数降低了39%。研究结果表明:由于只进行一个方向上的面积分解,机身CST参数化所使用的参数数量和相应优化过程的计算量比机翼大幅降低;经过EFCE激波阻力优化的机身具有较为明显的面积率修形“蜂腰”特征。
The influence of the cross-sectional area distribution of supersonic aircraft on its shock resistance is significant. Reasonable wing and fuselage cross-sectional area distribution can significantly reduce its shock resistance. Based on the cross-sectional area decomposition (CST) parametric shape representation of the fuselage by using the CST method, an extended optimization algorithm for the shock resistance of the supersonic wing-body combination was proposed The method was used to optimize the shape of the supersonic passenger wing assembly, which reduced the shock resistance coefficient by 39%. The results show that the number of parameters used in the parameterization of the fuselage CST and the computational cost of the corresponding optimization process are greatly reduced compared to the airfoil due to the area decomposition in only one direction. The airframe optimized by the EFCE shock resistance has a significant Area rate repair shape “bee waist ” features.