This paper proposes an improved design methodology and global optimization method for the design of an advanced dropped-hinge flap (ADHF) using an integrated approach. The approach implemented an actuation-driven parametric model for a hinged-flap concept. The optimization methodology incorporates an adaptive data sampling method in the update of a series of surrogate models. Inclusion of an actuation mechanism in the definition of the model eliminated a large number of gap and overlap settings that are not practically possible, leading to further savings in the number of computational fluid dynamic calculations required. Parameters for the actuation definition, flap geometries, and spoiler settings are included simultaneously in the optimization in order to consider the interactions among these factors and to obtain near-global-optimal solutions. Compared with a traditional sequential shape/mechanism optimization methodology, which can only produce one design point meeting the landing requirement, a series of design points can be obtained from the proposed methodology, meeting the requirements for both takeoff and landing configurations. The optimal result not only significantly improves $L/D$ at an angle of attack of eight by 17.8% but also decreases the distance between the hinge and the lower surface of the airfoil by 22.4%, which can reduce the fairing size. Comparisons are given between the optimized ADHF and the traditional Fowler flap, along with detailed analysis on the potential benefits by supplementing the design with spoiler deflections.

本文提出了一种改进的设计方法和全局优化方法，用于使用集成方法设计先进的下垂铰链襟翼 (ADHF)。该方法为铰链襟翼概念实现了驱动驱动的参数模型。优化方法在一系列替代模型的更新中结合了自适应数据采样方法。在模型定义中包含驱动机制消除了大量实际上不可能的间隙和重叠设置，从而进一步节省了所需的计算流体动力学计算的数量。驱动定义、襟翼几何形状和扰流板设置的参数同时包含在优化中，以便考虑这些因素之间的相互作用并获得近乎全局的最佳解决方案。与传统的顺序形状/机构优化方法只能产生一个满足着陆要求的设计点相比，从所提出的方法中可以获得一系列设计点，同时满足起飞和着陆构型的要求。优化的结果不仅显着提高$升/D$8 的攻角减少 17.8%，但也减少了 22.4% 的铰链和翼型下表面之间的距离，这可以减小整流罩尺寸。比较了优化的 ADHF 和传统的 Fowler 襟翼，并详细分析了通过用扰流板偏转补充设计的潜在好处。