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Robust aerodynamic morphing shape optimization for high-lift missions

机译：高升降机任务的强大空气动力学形状优化

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摘要

Morphing wings have a great potential to enhance the overall performances of the aircraft by adapting the wing shape to various flight conditions. However, there are some issues concerning the applicability of this idea at high-lift missions. An important problem is the need for more actuators along the airfoil that may face with the weight penalty. This mainly arises from the design parameterization methods that are unable to effectively control the leading and trailing edge deformations without modifying the middle part of the airfoil. In this work, a new parameterization method is presented for optimum morphing wing section design at high-lift missions that tends to minimize the number of actuators by increasing un-morphed middle sections of the wing. Genetic algorithm is used for shape optimization and the aerodynamic objective function is calculated by the numerical solution of the compressible turbulent flow equations. Results show that the new method is capable of generating high-lift morphing geometry with minimum shape transformation. In addition, higher lift coefficient is achieved in less computational time by the new method compared with the alternative flexible leading edge airfoil. (C) 2020 Elsevier Masson SAS. All rights reserved.
机译：变形翅膀具有巨大的潜力，可以通过将机翼形状适应各种飞行条件来增强飞机的整体性能。但是，在高升降机任务中有一些关于这个想法适用性的问题。一个重要问题是需要沿着翼型的更多的执行器，这些翼型可能面对重量惩罚。这主要是由设计参数化方法产生，这些方法无法有效地控制领先和后缘变形而不改变翼型的中间部分。在这项工作中，提出了一种新的参数化方法，用于在高升力任务处获得最佳的变形翼段设计，该设计倾向于通过增加机翼的不变性的中间部分来最小化执行器的数量。遗传算法用于形状优化，并且通过可压缩湍流流程方程的数值解计算空气动力学物体函数。结果表明，新方法能够产生具有最小形状变换的高升力变形几何形状。另外，与替代柔性柔性前缘翼型相比，通过新方法在较少的计算时间内实现更高提升系数。 （c）2020 Elsevier Masson SAS。版权所有。

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