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首页> 外文会议>60th aeronautics conference and AGM : Aerospace clusters: where are we headed? >Module Discretization of a Modular Morphing Wing with Three Flight Regimes
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Module Discretization of a Modular Morphing Wing with Three Flight Regimes

机译：具有三种飞行状态的模块化变形翼的模块离散化

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Morphing wing is an emerging area of research for new aircraft design. The purpose of this research is to achieve optimal aircraft aerodynamic performance by changing the wing shape according to different flight regimes. The current research is being carried out at two levels: airfoil and wing. The research being conducted at Ryerson is the latter that looks at morphing of an entire wing including twist, dihedral, sweep, and span. A practical way of designing a morphing wing would be to use a number of modules to approximate a continuous wing. For this purpose, a method is presented for the determination of a proper number of modules that would allow a modular wing to morph to different wing shapes with respectively required aerodynamics performance. This is a two-step method: the first step for geometry discretization and the second for aerodynamic evaluation. In the first step, curvature and twist distribution from a reference wing shape are extracted and used to determine the spacing of the discretized wing modules. This is achieved by clustering more tightly spaced wing modules in areas of large total curvature, and fewer longer wing modules in areas of small total curvature. In the second step, a proper number of modules are determined by evaluating if an aerodynamic performance index has reached an acceptable value. In this paper, three flight regimes are considered: cruise, climb and descent. First, the wing profiles of these flight regimes are determined based on their respective aerodynamic requirements. These profiles are then used as the reference wing shapes for discretization to determine the number of modules and module spacing for each flight regime. The discretization algorithm is developed by integration between MATLAB and CFX. As shown in the results, the proposed method can provide an effective way of designing a modular morphing wing.
机译：变形翼是新飞机设计研究的新兴领域。这项研究的目的是通过根据不同的飞行状态改变机翼形状来实现最佳的飞机空气动力学性能。当前的研究在两个层面上进行：机翼和机翼。后者在瑞尔森（Ryerson）进行的研究着眼于整个机翼的变形，包括扭曲，二面角，后掠和跨度。设计变形机翼的一种实用方法是使用许多模块来近似连续机翼。为此目的，提出了一种用于确定适当数量的模块的方法，该方法将允许模块式机翼变形成具有各自所需的空气动力学性能的不同机翼形状。这是一个两步方法：第一步用于几何离散化，第二步用于空气动力学评估。第一步，提取参考机翼形状的曲率和扭曲分布，并用于确定离散机翼模块的间距。这是通过在总曲率大的区域内将间距较小的机翼组件聚在一起，在总曲率小的区域内将较少的较长机翼组件聚类来实现的。在第二步中，通过评估空气动力学性能指标是否已达到可接受的值来确定合适的模块数量。在本文中，考虑了三种飞行状态：巡航，爬升和下降。首先，根据各自的空气动力学要求确定这些飞行状态的机翼轮廓。然后，将这些轮廓用作离散化的参考机翼形状，以确定每种飞行状态的模块数量和模块间距。离散化算法是通过在MATLAB和CFX之间集成而开发的。结果表明，所提出的方法可以提供一种设计模块化变身机翼的有效方法。

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