Stiffness tailoring for improved aeroelastic performance of manufacturable composite wings.

该项目的重点是为飞机机翼定义新的加强概念，以降低关键位置的峰值应力。这可以减轻结构重量，从而提高新型飞机配置(如用于空中滑行的全电动飞机)的空气动力学效率。预计机翼的气动弹性性能将通过优化结构布局(例如，肋骨的对准和位置以及加强筋的弯曲)和跨机翼跨度的复合材料的刚度定制(例如，通过弯曲纤维)来改进。该项目将考虑不同的制造技术(如自动纤维贴装、离散硬度裁剪和连续丝束剪切)，并将密切模拟各种制造约束。此外，还将解决局部和机翼水平刚度要求之间的权衡问题。为了实现该项目的目标，将开发和使用一个计算框架。它将包括用于结构建模的有限元方法和各种气动解算器(如双重格子法)。Nastran将用于气动弹性调查。该框架将与优化库整合，进行多学科设计和优化研究。

This project focuses on defining new stiffening concepts for aircraft wings that reduce peak stresses in key locations. This can result in reducing structural weight leading to improved aerodynamic efficiency on novel aircraft configurations (such as fully-electric aircraft used for air taxi). It is anticipated that the aeroelastic performance of a wing will be improved by optimising structural layout (e.g. alignment and position of ribs and curving of stiffeners) and stiffness tailoring of composite materials across the span of the wing (e.g. via curving of fibres). The project will consider different manufacturing techniques (such as Automated Fibre Placement, Discrete Stiffness Tailoring, and Continuous Tow Shearing) and will closely model the various manufacturing constraints. In addition, the trade-off between local and wing level stiffness requirements will be addressed. To fulfil the project's objectives, a computational framework will be developed and used. It will consist of the finite element method for structural modelling coupled with various aerodynamic solvers (such as Doublet Lattice Method). Nastran will be used for aeroelastic investigation. The framework will be integrated with an optimization library to conduct multidisciplinary design and optimization studies.